ATR 72 Flight Crew Operating Manual - Revision Lists

0.00.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P1 CONTENTS AA 0.00.00 CONTENTS 0.01.00 LIST OF TEMPORARY REVISIONS (L.T.R.) 0.02.00 REASON OF TEMPORARY REVISIONS (R.T.R.) 0.03.00 SHIPPING NOTE TEMPORARY PAGES (S.N.T.P.) 0.04.00 LIST OF EFFECTIVE TEMPORARY PAGES (L.E.T.P.) 0.05.00 LIST OF NORMAL REVISIONS (L.N.R.) 0.06.00 REASON OF THE REVISION 0.07.00 SHIPPING NOTE NORMAL PAGES (S.N.N.P.) 0.08.00 LIST OF EFFECTIVE NORMAL PAGES (L.E.N.P.) 0.09.00 LIST OF MOD / MP / SB (L.O.M.) 0.10.00 CROSS REFERENCE TABLE (C.R.T.) 0.40.00 ORGANIZATION OF THE MANUAL 0.50.00 STANDARD NOMENCLATURE 0.60.00 UNITS CONVERSION TABLE 001 APR 11 . 0.01.00 FLIGHT CREW OPERATING MANUAL P1 L.T.R. LIST OF TEMPORARY REVISIONS 082 TQ FEB 12 AA No. T.R. DATE IN DESTROYED POSITION REMARKS 01 SEP 11 FEB 12 TR 01 - ENV 02 OCT 11 FEB 12 TR 02 - ENV . 0.02.00 FLIGHT CREW OPERATING MANUAL R.T.R. P1 001 ENV FEB 12 REASON OF THE TEMPORARY REVISIONS DATE REASON OF REVISIONS AFFECTED PAGES SEP 11 OEB N°04 - AP/FD ALT* mode during climb phase 3.12.20 3.12.24 OCT 11 - List of OEB corrected and updated - OEB N°05 - Inconsistency between displayed MDA and call out ”Approaching minimum” and ”Minimum Minimum”. - OEB N°06 - Take Off procedure After lift Off 3.12.20 3.12.25 3.12.26 . FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of EffectiveTemporary Pages L.E.T.P. 0-04 page 1-082 FEB 12 You must hold in your manual the following pages Issue P CH SE Page Seq Date Label Validity expression REV1 0 01 00 001 082 FEB 12 ALL L.T.R. REV1 0 02 00 001 001 FEB 12 ALL R.T.R. REV1 0 04 00 001 082 FEB 12 ALL L.E.T.P. End TQ Modification expression TQ TQ . 0.05.00 FLIGHT CREW OPERATING MANUAL L.N.R. LIST OF NORMAL REVISIONS P1 001 FEB 12 AA N°REV EDITION DATE INSERTION DATE NAME 00 APR 11 TOTAL NEW EDITION 72-- 212A “-- 600” version (Mod 5948) 01 FEB 12 (published in April 2012 due to certification process) TOTAL RE-- EDITION including “L2B2” software . 0.06.00 FLIGHT CREW OPERATING MANUAL R.N.R. REASON OF THE REVISION DATE REASON FOR ISSUE (MAJOR EVENTS) APR 11 * NEW MODIFICATION : - Mod 5948: New Avionic Suite 72-- 212A “-- 600” version. FEB 12 (published in April 2012 due to certification process) * NEW MODIFICATION : - Mod 6521: New software “L2B2” for “600” version - Mod 6635: Airport Navigation function. - COMPLETE PROCEDURE REVIEW: Emergency (except Unreliable airspeed indication) Following Failure Normal - FWS and Electronic CheckList description and human factor recommendations - Several correction and improvements - OEB 07 : VHF emitting (Mod: 6760) P1 001 FEB 12 CHAP INVOLVED ALL ALL 2.03 / 2.04 / 2.05 1.02.10 and 2.03.02 / 2. 04.01 and 2.05.01 ALL 3.12.27 . FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages 0-08 page 1-082 L.E.N.P. FEB 12 You must hold in your manual the following normal pages M P CH SE Page Seq Date Label Validity expression NORMAL REVISION N° 1 N 0 00 00 001 001 APR 11 ALL CONTENTS N 0 01 00 001 082 FEB 12 ALL L.T.R. N 0 02 00 001 001 FEB 12 ALL R.T.R. N 0 04 00 001 082 FEB 12 ALL L.E.T.P. N 0 05 00 001 001 FEB 12 ALL L.N.R. N 0 06 00 001 001 FEB 12 ALL R.N.R. N 0 08 00 001 082 FEB 12 ALL L.E.N.P. TQ N 0 09 00 001 082 FEB 12 ALL L.O.M. TQ N 0 10 00 001 082 FEB 12 ALL C.R.T. TQ N N 0 40 00 0 40 00 001 001 APR 11 002 001 APR 11 ALL ORGANIZATION OF THE MANUAL ORGANIZATION OF THE MANUAL N N 0 40 00 0 40 00 003 001 APR 11 004 001 APR 11 ALL ORGANIZATION OF THE MANUAL ORGANIZATION OF THE MANUAL N N 0 50 00 0 50 00 001 001 APR 11 002 001 APR 11 ALL STANDARD NOMENCLATURE STANDARD NOMENCLATURE N N 0 50 00 0 50 00 003 001 APR 11 004 001 APR 11 ALL STANDARD NOMENCLATURE STANDARD NOMENCLATURE N N 0 50 00 0 50 00 005 001 APR 11 006 001 APR 11 ALL STANDARD NOMENCLATURE STANDARD NOMENCLATURE N N 0 50 00 0 50 00 007 001 APR 11 008 001 APR 11 ALL STANDARD NOMENCLATURE STANDARD NOMENCLATURE Turn TQ TQ TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages 0-08 page 2-082 L.E.N.P. FEB 12 M P CH SE Page Seq Date Label Validity expression N N 0 50 00 0 50 00 009 001 APR 11 010 001 APR 11 ALL STANDARD NOMENCLATURE STANDARD NOMENCLATURE N N 0 50 00 0 50 00 011 001 APR 11 012 001 APR 11 ALL STANDARD NOMENCLATURE STANDARD NOMENCLATURE N 0 50 00 013 001 APR 11 ALL STANDARD NOMENCLATURE N N 0 60 00 0 60 00 001 001 APR 11 002 001 APR 11 ALL UNITS CONVERSION TABLE UNITS CONVERSION TABLE N 1 00 00 001 001 APR 11 ALL MOD 5948 N N 1 00 10 1 00 10 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 00 10 1 00 10 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N 1 00 10 005 001 APR 11 ALL MOD 5948 N N 1 00 20 1 00 20 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 00 20 1 00 20 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N 1 00 20 005 001 APR 11 ALL MOD 5948 N N 1 00 25 1 00 25 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 00 25 1 00 25 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 00 30 1 00 30 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 00 30 1 00 30 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 3-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 1 00 30 1 00 30 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 00 30 1 00 30 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N 1 00 30 009 001 APR 11 ALL MOD 5948 N N 1 00 40 1 00 40 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 00 40 1 00 40 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 00 40 1 00 40 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 00 40 1 00 40 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 00 40 1 00 40 009 001 APR 11 010 001 APR 11 ALL MOD 5948 MOD 5948 N 1 00 40 011 001 APR 11 ALL MOD 5948 N 1 00 50 001 001 APR 11 ALL MOD 5948 N 1 01 00 001 001 FEB 12 ALL MOD 5948 N N 1 01 10 1 01 10 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 01 10 1 01 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1 01 40 009-010001 FEB 12 ALL MOD 5948 N 1 01 40 011-012001 APR 11 ALL MOD 5948 N 1 01 40 013-014001 FEB 12 ALL MOD 5948 N 1 01 40 015-016001 APR 11 ALL MOD 5948 N 1 01 40 017-018001 FEB 12 ALL MOD 5948 N 1 01 40 019-020001 APR 11 ALL MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 5-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N 1 01 40 021-022001 FEB 12 ALL MOD 5948 N 1 01 40 023-024001 FEB 12 ALL MOD 5948 N 1 01 40 025-026001 FEB 12 ALL MOD 5948 N 1 01 40 027-028001 FEB 12 ALL MOD 5948 N 1 01 40 029-030001 APR 11 ALL MOD 5948 N 1 01 40 031-032001 FEB 12 ALL MOD 5948 N 1 01 40 033 001 FEB 12 ALL MOD 5948 N 1 02 00 001 001 FEB 12 ALL MOD 5948 N 1 02 10 001-002001 APR 11 ALL MOD 5948 N 1 02 10 003-004001 APR 11 ALL MOD 5948 N N 1 02 10 1 02 10 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 02 10 1 02 10 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 02 10 1 02 10 009 001 APR 11 010 001 APR 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20 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N 1 03 20 009-010001 APR 11 ALL MOD 5948 N 1 03 20 011 001 APR 11 ALL MOD 5948 N N 1 03 30 1 03 30 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 03 30 1 03 30 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 03 30 1 03 30 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 03 30 1 03 30 007 001 FEB 12 008 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 7-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N 1 03 30 009-010001 APR 11 ALL MOD 5948 N 1 03 30 011-012001 APR 11 ALL MOD 5948 N N 1 03 30 1 03 30 013 001 FEB 12 014 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 03 30 1 03 30 015 001 FEB 12 016 001 FEB 12 ALL MOD 5948 MOD 5948 N 1 03 30 017 001 FEB 12 ALL MOD 5948 N N 1 03 40 1 03 40 001 001 FEB 12 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 03 40 1 03 40 003 001 FEB 12 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 03 40 1 03 40 005 001 FEB 12 006 001 APR 11 ALL MOD 5948 MOD 5948 N 1 03 40 007-008001 FEB 12 ALL MOD 5948 N N 1 03 40 1 03 40 009 001 FEB 12 010 001 FEB 12 ALL MOD 5948 MOD 5948 N 1 04 00 001 001 APR 11 ALL MOD 5948 N 1 04 10 001-002001 APR 11 ALL MOD 5948 N N 1 04 10 1 04 10 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 04 10 1 04 10 005 001 FEB 12 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 04 10 1 04 10 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 8-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 1 04 10 1 04 10 009 001 APR 11 010 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 04 10 1 04 10 011 001 APR 11 012 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 04 10 1 04 10 013 001 APR 11 014 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 04 10 1 04 10 015 001 APR 11 016 001 APR 11 ALL MOD 5948 MOD 5948 N 1 04 10 017-018001 APR 11 ALL MOD 5948 N 1 04 10 019-020001 APR 11 ALL MOD 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001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 05 20 1 05 20 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N 1 05 20 005-006001 FEB 12 ALL MOD 5948 N N 1 05 20 1 05 20 007 001 FEB 12 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 05 20 1 05 20 009 001 FEB 12 010 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 05 20 1 05 20 011 001 APR 11 012 001 APR 11 ALL MOD 5948 MOD 5948 N 1 06 00 001 001 APR 11 ALL MOD 5948 N N 1 06 10 1 06 10 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 06 20 1 06 20 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 06 20 1 06 20 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 06 20 1 06 20 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 06 20 1 06 20 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 11-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N 1 06 20 009-010001 APR 11 ALL MOD 5948 N 1 06 20 011-012001 APR 11 ALL MOD 5948 N 1 06 20 013-014001 APR 11 ALL MOD 5948 N N 1 06 20 1 06 20 015 001 APR 11 016 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 06 20 1 06 20 017 001 APR 11 018 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 06 20 1 06 20 019 001 APR 11 020 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 06 20 1 06 20 021 001 APR 11 022 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 06 20 1 06 20 023 001 APR 11 024 001 APR 11 ALL MOD 5948 MOD 5948 N 1 06 20 025 001 APR 11 ALL MOD 5948 N N 1 06 30 1 06 30 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 06 30 1 06 30 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 06 30 1 06 30 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N 1 06 30 007 001 APR 11 ALL MOD 5948 N 1 06 35 001-002001 APR 11 ALL MOD 5948 N N 1 06 40 1 06 40 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 06 40 1 06 40 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 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12 ALL MOD 5948 MOD 5948 N N 1 10 20 1 10 20 005 001 APR 11 006 001 FEB 12 ALL MOD 5948 MOD 5948 N 1 10 20 007 001 APR 11 ALL MOD 5948 N N 1 10 22 1 10 22 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 10 22 1 10 22 003 001 APR 11 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 10 22 1 10 22 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 10 22 1 10 22 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 10 22 1 10 22 009 001 APR 11 010 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 17-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 1 10 22 1 10 22 011 001 APR 11 012 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 10 22 1 10 22 013 001 APR 11 014 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 10 22 1 10 22 015 001 APR 11 016 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 10 22 1 10 22 017 001 APR 11 018 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 10 22 1 10 22 019 001 APR 11 020 001 APR 11 ALL 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5948 MOD 5948 N N 1 10 40 1 10 40 003 001 APR 11 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 10 50 1 10 50 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 10 50 1 10 50 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N 1 10 50 005 001 APR 11 ALL MOD 5948 N 1 11 00 001 001 APR 11 ALL MOD 5948 N N 1 11 10 1 11 10 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 11 10 1 11 10 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 11 10 1 11 10 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 11 10 1 11 10 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 11 10 1 11 10 009 001 APR 11 010 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 11 10 1 11 10 011 001 APR 11 012 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 19-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 1 11 10 1 11 10 013 001 FEB 12 014 001 APR 11 ALL MOD 5948 MOD 5948 N 1 11 10 015-016001 APR 11 ALL MOD 5948 N 1 11 10 017 001 APR 11 ALL MOD 5948 N 1 12 00 001 001 APR 11 ALL MOD 5948 N N 1 12 10 1 12 10 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 12 10 1 12 10 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N 1 12 10 005-006001 APR 11 ALL MOD 5948 N 1 12 10 007-008001 APR 11 ALL MOD 5948 N N 1 12 10 1 12 10 009 001 APR 11 010 001 FEB 12 ALL MOD 5948 MOD 5948 N 1 12 10 011-012001 FEB 12 ALL MOD 5948 N 1 12 10 013 001 APR 11 ALL MOD 5948 N N 1 13 00 1 13 00 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N 1 13 10 001-002001 APR 11 ALL MOD 5948 N N 1 13 20 1 13 20 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 13 20 1 13 20 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N 1 13 20 005 001 APR 11 ALL MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 20-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 1 13 30 1 13 30 001 001 APR 11 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 13 30 1 13 30 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 13 30 1 13 30 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 13 30 1 13 30 007 001 FEB 12 008 001 FEB 12 ALL MOD 5948 MOD 5948 N 1 13 30 009-010001 APR 11 ALL MOD 5948 N 1 13 30 011 001 APR 11 ALL MOD 5948 N N 1 13 40 1 13 40 001 001 APR 11 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 13 40 1 13 40 003 001 APR 11 004 001 FEB 12 ALL MOD 5948 MOD 5948 N 1 13 40 005 001 APR 11 ALL MOD 5948 N N 1 13 50 1 13 50 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 13 50 1 13 50 003 001 FEB 12 004 001 APR 11 ALL MOD 5948 MOD 5948 N 1 13 50 005 001 FEB 12 ALL MOD 5948 N N 1 13 60 1 13 60 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N 1 13 60 003 001 APR 11 ALL MOD 5948 N 1 13 70 001 001 APR 11 ALL MOD 5948 N 1 13 80 001-002001 APR 11 ALL MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 21-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 1 13 80 1 13 80 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N 1 13 80 005 001 APR 11 ALL MOD 5948 N 1 14 00 001 001 APR 11 ALL MOD 5948 N 1 14 10 001 001 FEB 12 ALL MOD 5948 N N 1 14 20 1 14 20 001 001 APR 11 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 14 20 1 14 20 003 001 APR 11 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 14 20 1 14 20 005 001 FEB 12 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 14 20 1 14 20 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 14 30 1 14 30 001 001 APR 11 002 001 FEB 12 ALL MOD 5948 MOD 5948 N 1 14 30 003-004001 APR 11 ALL MOD 5948 N 1 14 30 005 001 APR 11 ALL MOD 5948 N N 1 14 40 1 14 40 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 14 40 1 14 40 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 14 40 1 14 40 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 14 40 1 14 40 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N 1 14 40 009-010001 APR 11 ALL MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 22-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N 1 14 40 011-012001 APR 11 ALL MOD 5948 N 1 15 00 001 001 APR 11 ALL MOD 5948 N 1 15 10 001-002001 APR 11 ALL MOD 5948 N N 1 15 10 1 15 10 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 10 1 15 10 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 10 1 15 10 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 10 1 15 10 009 001 APR 11 010 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 20 1 15 20 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 20 1 15 20 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 30 1 15 30 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N 1 15 30 003 001 APR 11 ALL MOD 5948 N N 1 15 40 1 15 40 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 40 1 15 40 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 40 1 15 40 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 40 1 15 40 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 23-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 1 15 40 1 15 40 009 001 APR 11 010 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 40 1 15 40 011 001 APR 11 012 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 40 1 15 40 013 001 APR 11 014 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 50 1 15 50 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 50 1 15 50 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 50 1 15 50 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N 1 15 50 007 001 APR 11 ALL MOD 5948 N N 1 15 60 1 15 60 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N 1 15 60 003 001 APR 11 ALL MOD 5948 N 1 15 65 001 001 APR 11 ALL MOD 5948 N N 1 15 70 1 15 70 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 70 1 15 70 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 70 1 15 70 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 70 1 15 70 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 70 1 15 70 009 001 APR 11 010 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 24-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 1 15 70 1 15 70 011 001 APR 11 012 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 70 1 15 70 013 001 APR 11 014 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 70 1 15 70 015 001 APR 11 016 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 15 70 1 15 70 017 001 APR 11 018 001 APR 11 ALL MOD 5948 MOD 5948 N 1 16 00 001 001 APR 11 ALL MOD 5948 N 1 16 10 001 001 APR 11 ALL MOD 5948 N N 1 16 20 1 16 20 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 20 1 16 20 003 001 FEB 12 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 20 1 16 20 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N 1 16 20 007-008001 APR 11 ALL MOD 5948 N 1 16 20 009-010001 APR 11 ALL MOD 5948 N 1 16 20 011-012001 APR 11 ALL MOD 5948 N N 1 16 30 1 16 30 001 001 FEB 12 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 30 1 16 30 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 30 1 16 30 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 25-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 1 16 30 1 16 30 007 001 APR 11 008 001 FEB 12 ALL MOD 5948 MOD 5948 N N 1 16 30 1 16 30 009 001 FEB 12 010 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 40 1 16 40 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 40 1 16 40 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 40 1 16 40 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 40 1 16 40 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 40 1 16 40 009 001 APR 11 010 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 40 1 16 40 011 001 APR 11 012 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 40 1 16 40 013 001 APR 11 014 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 40 1 16 40 015 001 APR 11 016 001 APR 11 ALL MOD 5948 MOD 5948 N 1 16 40 017 001 APR 11 ALL MOD 5948 N N 1 16 45 1 16 45 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 50 1 16 50 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 60 1 16 60 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 26-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 1 16 60 1 16 60 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 60 1 16 60 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 1 16 60 1 16 60 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N 2 01 00 001 001 APR 11 ALL MOD 5948 N N 2 01 01 2 01 01 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 01 02 2 01 02 001 700 APR 11 002 001 APR 11 ALL MOD 5555 +5948 MOD 5948 N N 2 01 03 2 01 03 001 001 APR 11 002 001 APR 11 ALL N N 2 01 03 2 01 03 003 001 APR 11 004 001 APR 11 ALL N N 2 01 03 2 01 03 005 150 APR 11 006 001 APR 11 ALL N N 2 01 04 2 01 04 001 001 APR 11 002 001 APR 11 ALL 212A 212A MOD 5948 MOD 5948 N N 2 01 04 2 01 04 003 001 APR 11 004 001 APR 11 ALL 212A 212A MOD 5948 MOD 5948 N N 2 01 04 2 01 04 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 01 05 2 01 05 001 030 APR 11 002 100 APR 11 ALL MOD 5948 +1603 MOD 5948 +4411 N N 2 01 05 2 01 05 003 001 APR 11 004 001 FEB 12 ALL MOD 5948 MOD 5948 Turn PW127F-PW127M MOD 5948 MOD 5948 PW127F-PW127M PW127F-PW127M MOD 5948 MOD 5948 MOD 5948 +3037 +(3522 or 8044) MOD 5948 TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 27-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 01 06 2 01 06 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 01 06 2 01 06 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N 2 01 06 005 001 APR 11 ALL MOD 5948 N 2 01 07 001 001 APR 11 ALL MOD 5948 N 2 01 07 001A 001 APR 11 ALL MOD 5948 N 2 01 07 001B 001 FEB 12 ALL MOD 5948 N 2 01 08 001 001 APR 11 ALL MOD 5948 N 2 01 09 001 001 APR 11 ALL MOD 5948 N N 2 01 10 2 01 10 001 200 APR 11 002 200 APR 11 ALL MOD 5948 +5465 MOD 5948 +5465 N N 2 01 10 2 01 10 003 200 APR 11 004 200 APR 11 ALL MOD 5948 +5465 MOD 5948 +5465 N 2 02 00 001 001 APR 11 ALL MOD 5948 N N 2 02 01 2 02 01 001 001 APR 11 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 02 01 2 02 01 003 001 APR 11 004 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 02 02 001 001 APR 11 ALL MOD 5948 N N 2 02 03 2 02 03 001 001 APR 11 002 080 FEB 12 ALL MOD 5948 MOD 5948 +3037 N N 2 02 03 2 02 03 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 28-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 02 04 2 02 04 001 001 FEB 12 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 04 2 02 04 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 04 2 02 04 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 04 2 02 04 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 04 2 02 04 009 001 APR 11 010 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 04 2 02 04 011 001 APR 11 012 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 05 2 02 05 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 06 2 02 06 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 06 2 02 06 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N 2 02 06 005 001 APR 11 ALL MOD 5948 N 2 02 07 001 001 APR 11 ALL MOD 5948 N N 2 02 08 2 02 08 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 08 2 02 08 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 08 2 02 08 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 29-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 02 08 2 02 08 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 08 2 02 08 009 001 APR 11 010 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 08 2 02 08 011 001 APR 11 012 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 08 2 02 08 013 001 APR 11 014 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 08 2 02 08 015 001 APR 11 016 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 02 08 2 02 08 017 001 FEB 12 018 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 02 08 2 02 08 019 001 FEB 12 020 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 02 08 2 02 08 021 001 APR 11 022 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 08 2 02 08 023 001 APR 11 024 001 APR 11 ALL MOD 5948 MOD 5948 N 2 02 08 025 001 APR 11 ALL MOD 5948 N N 2 02 09 2 02 09 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N 2 02 09 003 001 APR 11 ALL MOD 5948 N N 2 02 10 2 02 10 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 10 2 02 10 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 30-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 02 10 2 02 10 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 10 2 02 10 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N 2 02 10 009 001 APR 11 ALL MOD 5948 N N 2 02 11 2 02 11 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N 2 02 11 002A 001 APR 11 ALL MOD 5948 N N 2 02 11 2 02 11 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 11 2 02 11 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N 2 02 11 007 001 APR 11 ALL MOD 5948 N N 2 02 12 2 02 12 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 12 2 02 12 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N 2 02 12 005 001 APR 11 ALL MOD 5948 N N 2 02 14 2 02 14 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 15 2 02 15 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 16 2 02 16 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N 2 02 18 001 001 FEB 12 ALL MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 31-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N 2 02 19 001 001 APR 11 ALL MOD 5948 N 2 02 20 001 001 APR 11 ALL MOD 5948 N N 2 02 21 2 02 21 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 21 2 02 21 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 21 2 02 21 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 21 2 02 21 007 001 FEB 12 008 001 APR 11 ALL MOD 5948 MOD 5948 N 2 02 21 009 001 APR 11 ALL MOD 5948 N N 2 02 24 2 02 24 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 24 2 02 24 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 24 2 02 24 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 02 24 2 02 24 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N 2 03 00 001 001 APR 11 ALL MOD 5948 N 2 03 01 001 001 APR 11 ALL MOD 5948 N 2 03 02 001 001 APR 11 ALL MOD 5948 N 2 03 03 001 001 APR 11 ALL MOD 5948 N 2 03 04 001 001 APR 11 ALL MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 32-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 03 05 2 03 05 001 001 FEB 12 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 03 05 2 03 05 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 03 05 2 03 05 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 03 05 007 001 FEB 12 ALL MOD 5948 N N 2 03 06 2 03 06 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 03 06 2 03 06 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 03 06 2 03 06 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 03 06 2 03 06 007 001 FEB 12 008 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 03 06 2 03 06 009 001 FEB 12 010 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 03 07 2 03 07 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 03 07 2 03 07 003 001 APR 11 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 03 07 2 03 07 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 03 07 2 03 07 007 001 FEB 12 008 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 03 07 2 03 07 009 001 FEB 12 010 001 FEB 12 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 33-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 03 07 2 03 07 011 001 FEB 12 012 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 03 07 013 001 FEB 12 ALL MOD 5948 N N 2 03 08 2 03 08 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 03 08 2 03 08 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 03 08 2 03 08 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N 2 03 08 007 001 FEB 12 ALL MOD 5948 N N 2 03 09 2 03 09 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 03 10 001 001 FEB 12 ALL MOD 5948 N N 2 03 11 2 03 11 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 03 12 2 03 12 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N 2 03 13 001 001 FEB 12 ALL MOD 5948 N N 2 03 14 2 03 14 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 03 14 2 03 14 003 001 FEB 12 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 03 15 2 03 15 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 03 15 003 001 FEB 12 ALL MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 34-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 03 16 2 03 16 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 03 16 2 03 16 003 001 FEB 12 004 001 APR 11 ALL MOD 5948 MOD 5948 N 2 03 17 001 001 FEB 12 ALL MOD 5948 N N 2 03 18 2 03 18 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 03 19 001 001 FEB 12 ALL MOD 5948 N 2 03 20 001 001 FEB 12 ALL MOD 5948 N N 2 03 21 2 03 21 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 03 22 001 001 FEB 12 ALL MOD 5948 N 2 03 23 001 001 APR 11 ALL MOD 5948 N N 2 03 24 2 03 24 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 03 24 003 001 FEB 12 ALL MOD 5948 N 2 04 00 001 001 FEB 12 ALL MOD 5948 N N 2 04 01 2 04 01 001 001 APR 11 002 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 04 01 003 001 FEB 12 ALL MOD 5948 N N 2 04 02 2 04 02 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 04 02 2 04 02 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 35-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 04 02 2 04 02 005 001 APR 11 006 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 04 03 2 04 03 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 04 03 2 04 03 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 04 03 2 04 03 005 001 APR 11 006 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 04 03 007 001 FEB 12 ALL MOD 5948 N N 2 04 04 2 04 04 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 04 05 2 04 05 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 04 05 2 04 05 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 04 05 2 04 05 005 001 FEB 12 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 04 05 2 04 05 007 001 FEB 12 008 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 04 05 2 04 05 009 001 FEB 12 010 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 04 05 2 04 05 011 001 FEB 12 012 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 04 05 013 001 FEB 12 ALL MOD 5948 N N 2 05 00 2 05 00 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 36-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 05 00 2 05 00 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 00 2 05 00 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 00 2 05 00 007 001 FEB 12 008 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 01 2 05 01 001 001 APR 11 002 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 05 01 003 001 FEB 12 ALL MOD 5948 N N 2 05 02 2 05 02 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 02 2 05 02 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 02 2 05 02 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 02 2 05 02 007 001 FEB 12 008 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 02 2 05 02 009 001 FEB 12 010 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 02 2 05 02 011 001 FEB 12 012 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 02 2 05 02 013 001 FEB 12 014 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 05 02 2 05 02 015 001 FEB 12 016 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 02 2 05 02 017 001 FEB 12 018 001 FEB 12 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 37-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 05 02 2 05 02 019 001 FEB 12 020 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 02 2 05 02 021 001 FEB 12 022 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 02 2 05 02 023 001 FEB 12 024 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 05 02 025 001 FEB 12 ALL MOD 5948 N N 2 05 03 2 05 03 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 03 2 05 03 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 03 2 05 03 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 05 03 007 001 FEB 12 ALL MOD 5948 N 2 05 04 001 001 FEB 12 ALL MOD 5948 N 2 05 04 001A 001 FEB 12 ALL MOD 5948 N 2 05 04 002 001 FEB 12 ALL MOD 5948 N 2 05 04 002A 001 FEB 12 ALL MOD 5948 N N 2 05 04 2 05 04 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 04 2 05 04 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 04 2 05 04 007 001 FEB 12 008 001 FEB 12 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 38-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 05 04 2 05 04 009 001 FEB 12 010 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 04 2 05 04 011 001 FEB 12 012 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 04 2 05 04 013 001 FEB 12 014 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 04 2 05 04 015 001 FEB 12 016 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 04 2 05 04 017 001 FEB 12 018 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 05 05 001 001 FEB 12 ALL MOD 5948 N 2 05 05 001A 001 FEB 12 ALL MOD 5948 N 2 05 05 002 001 FEB 12 ALL MOD 5948 N N 2 05 05 2 05 05 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 06 2 05 06 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 06 2 05 06 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 06 2 05 06 005 001 FEB 12 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 05 06 2 05 06 007 001 FEB 12 008 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 06 2 05 06 009 001 FEB 12 010 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 06 2 05 06 011 001 FEB 12 012 001 FEB 12 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 39-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N 2 05 06 013 001 FEB 12 ALL MOD 5948 N N 2 05 07 2 05 07 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 07 2 05 07 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 05 07 2 05 07 005 001 APR 11 006 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 05 07 007 001 APR 11 ALL MOD 5948 N N 2 05 08 2 05 08 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 05 08 2 05 08 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 08 2 05 08 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 08 2 05 08 007 001 FEB 12 008 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 08 2 05 08 009 001 FEB 12 010 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 08 2 05 08 011 001 FEB 12 012 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 05 08 013 001 FEB 12 ALL MOD 5948 N N 2 05 09 2 05 09 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 09 2 05 09 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 09 2 05 09 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 40-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 05 09 2 05 09 007 001 FEB 12 008 001 APR 11 ALL MOD 5948 MOD 5948 N 2 05 09 009 001 FEB 12 ALL MOD 5948 N N 2 05 10 2 05 10 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 05 10 003 001 FEB 12 ALL MOD 5948 N 2 05 11 001 001 APR 11 ALL MOD 5948 N N 2 05 12 2 05 12 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 005 001 APR 11 006 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 007 001 FEB 12 008 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 009 001 FEB 12 010 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 011 001 FEB 12 012 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 013 001 FEB 12 014 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 015 001 FEB 12 016 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 017 001 FEB 12 018 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 019 001 FEB 12 020 001 FEB 12 ALL MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 41-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 2 05 12 2 05 12 021 001 FEB 12 022 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 023 001 FEB 12 024 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 025 001 FEB 12 026 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 12 2 05 12 027 001 FEB 12 028 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 13 2 05 13 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 13 2 05 13 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 05 13 005 001 FEB 12 ALL MOD 5948 N N 2 05 14 2 05 14 001 001 FEB 12 002 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 14 2 05 14 003 001 FEB 12 004 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 14 2 05 14 005 001 FEB 12 006 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 14 2 05 14 007 001 FEB 12 008 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 14 2 05 14 009 001 FEB 12 010 001 FEB 12 ALL MOD 5948 MOD 5948 N N 2 05 14 2 05 14 011 001 FEB 12 012 001 FEB 12 ALL MOD 5948 MOD 5948 N 2 06 00 001 001 APR 11 ALL MOD 5948 N 2 06 01 001 001 APR 11 ALL MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 42-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N 2 06 02 001 001 APR 11 ALL MOD 5948 N N 2 06 03 2 06 03 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 06 03 2 06 03 003 001 FEB 12 004 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 06 03 2 06 03 005 001 APR 11 006 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 06 03 2 06 03 007 001 APR 11 008 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 06 03 2 06 03 009 001 APR 11 010 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 06 04 2 06 04 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 2 06 04 2 06 04 003 001 APR 11 004 001 APR 11 ALL MOD 5948 MOD 5948 N 3 01 00 001 001 APR 11 ALL MOD 5948 N N 3 01 01 3 01 01 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N 3 01 01 003 001 APR 11 ALL MOD 5948 N 3 01 02 001 001 APR 11 ALL MOD 5948 N 3 01 03 001 001 APR 11 ALL MOD 5948 N N 3 01 04 3 01 04 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N 3 01 05 001 001 APR 11 ALL MOD 5948 N 3 02 00 001 001 APR 11 ALL MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages 0-08 page 43-082 L.E.N.P. FEB 12 M P CH SE Page Seq Date Label Validity expression N N 3 02 01 3 02 01 001 001 APR 11 002 001 APR 11 ALL N N 3 02 02 3 02 02 001 100 APR 11 002 100 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 02 02 3 02 02 003 100 APR 11 004 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 02 02 3 02 02 005 500 APR 11 006 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 02 02 3 02 02 007 500 APR 11 008 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 02 02 3 02 02 009 500 APR 11 010 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N 3 02 02 011 500 APR 11 ALL PW127F - PW127M MOD 5948 N 3 03 00 001 001 APR 11 ALL MOD 5948 N N 3 03 01 3 03 01 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 3 03 02 3 03 02 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N N 3 03 02 3 03 02 003 001 APR 11 004 550 APR 11 ALL MOD 5948 PW127F - PW127M MOD(4671 or 5555)+5948 N N 3 03 02 3 03 02 005 560 APR 11 006 560 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5555+5948 PW127F - PW127M BOOST OFF MOD 5555+5948 N N 3 03 03 3 03 03 001 500 APR 11 002 500 APR 11 ALL PW127F - 127M PW127F - 127M MOD 5948 MOD 5948 N 3 03 03 002A 500 APR 11 ALL PW127F - 127M MOD 5948 N N 3 03 03 3 03 03 PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 Turn 003 300 APR 11 004 500 APR 11 ALL MOD 5948 MOD 5948 TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages 0-08 page 44-082 L.E.N.P. FEB 12 M P CH SE Page Seq Date Label Validity expression N 3 03 03 004A 500 APR 11 ALL PW127F - PW127M MOD 5948 N 3 03 03 005 500 APR 11 ALL PW127F - PW127M MOD 5948 N 3 03 03 005A 500 APR 11 ALL PW127F - PW127M MOD 5948 N 3 03 03 006 550 APR 11 ALL PW127F - PW127M BOOST OFF MOD3522+5948 N 3 03 03 007 550 APR 11 ALL PW127F - PW127M BOOST OF FMOD 3522+5948 N N 3 03 04 3 03 04 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 03 04 3 03 04 003 500 APR 11 004 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 03 04 3 03 04 005 500 APR 11 006 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 03 04 3 03 04 007 500 APR 11 008 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 03 04 3 03 04 009 500 APR 11 010 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 03 04 3 03 04 011 500 APR 11 012 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N 3 03 04 013 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 N N 3 03 05 3 03 05 001 001 APR 11 002 001 APR 11 ALL N 3 03 06 001 001 APR 11 ALL MOD 5948 N 3 04 00 001 001 APR 11 ALL MOD 5948 N 3 04 01 001 500 APR 11 ALL Turn 212A PW127F-127M TQ MOD 5948 MOD 5948 MOD 5948 FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages 0-08 page 45-082 L.E.N.P. FEB 12 M P CH SE Page Seq Date Label Validity expression N N 3 04 02 3 04 02 001 300 FEB 12 002 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N 3 04 02 003 500 FEB 12 ALL PW127F - PW127M MOD 5948 N N 3 04 03 3 04 03 001 300 FEB 12 002 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N 3 04 03 003 500 FEB 12 ALL PW127F - PW127M MOD 5948 N N 3 04 04 3 04 04 001 500 APR 11 002 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 04 04 3 04 04 003 500 APR 11 004 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 04 04 3 04 04 005 500 APR 11 006 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 04 04 3 04 04 007 500 APR 11 008 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 04 04 3 04 04 009 500 APR 11 010 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N 3 04 04 011 500 FEB 12 ALL PW127F - PW127M MOD 5948 N N 3 04 05 3 04 05 001 001 APR 11 002 001 APR 11 ALL N N 3 04 05 3 04 05 003 500 FEB 12 004 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N 3 04 05 005 500 FEB 12 ALL PW127F - PW127M MOD 5948 N 3 05 00 001 001 APR 11 ALL N 3 05 01 001 500 APR 11 ALL Turn MOD 5948 MOD 5948 MOD 5948 PW127F-127M TQ MOD 5948 FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages 0-08 page 46-082 L.E.N.P. FEB 12 M P CH SE Page Seq Date Label Validity expression N N 3 05 02 3 05 02 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 05 02 3 05 02 003 500 APR 11 004 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 05 02 3 05 02 005 500 APR 11 006 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 05 02 3 05 02 007 500 APR 11 008 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 05 02 3 05 02 009 500 APR 11 010 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N 3 05 02 011 500 FEB 12 ALL PW127F - PW127M MOD 5948 N N 3 05 03 3 05 03 001 500 FEB 12 002 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 05 03 3 05 03 003 500 FEB 12 004 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 05 03 3 05 03 005 500 FEB 12 006 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 05 03 3 05 03 007 500 FEB 12 008 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 05 03 3 05 03 009 500 FEB 12 010 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 05 03 3 05 03 011 500 FEB 12 012 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 05 03 3 05 03 013 500 FEB 12 014 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 05 03 3 05 03 015 500 FEB 12 016 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages 0-08 page 47-082 L.E.N.P. FEB 12 M P CH SE Page Seq Date Label Validity expression N N 3 05 03 3 05 03 017 500 FEB 12 018 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N 3 06 01 001 500 FEB 12 ALL PW127F - 127M MOD 5948 N 3 06 02 001 500 FEB 12 ALL PW127F - PW127M MOD 5948 N 3 06 03 001 500 FEB 12 ALL PW127F - PW127M MOD 5948 N 3 07 00 001 001 APR 11 ALL N 3 07 01 001 500 APR 11 ALL PW127F - 127M MOD 5948 N N 3 07 02 3 07 02 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 07 03 3 07 03 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N 3 08 00 001 001 APR 11 ALL MOD 5948 N 3 08 01 001 020 APR 11 ALL MOD 5948 N 3 08 01 002A 520 APR 11 ALL PW127F - PW127M MOD 5948 N 3 08 01 003A 520 APR 11 ALL PW127F - PW127M MOD 5948 N 3 08 02 001 500 APR 11 ALL PW127F - PW127M MOD 5948 N N 3 08 03 3 08 03 001 200 APR 11 002 200 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N 3 08 03 003 001 APR 11 ALL MOD 5948 N 3 08 04 001 001 APR 11 ALL MOD 5948 N 3 09 00 001 001 APR 11 ALL MOD 5948 N 3 09 01 001 001 APR 11 ALL MOD 5948 Turn MOD 5948 TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 48-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N N 3 09 02 3 09 02 001 001 APR 11 002 500 FEB 12 ALL MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 02 3 09 02 003 500 FEB 12 004 500 FEB 12 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 02 3 09 02 005 300 APR 11 006 300 APR 11 ALL PW127-127F-127M PW127-127F-127M N N 3 09 02 3 09 02 007 300 APR 11 008 300 APR 11 ALL PW127-127F-127M BOOST OFF MOD 5948 PW127-127F-127M BOOST OFF MOD 5948 N N 3 09 03 3 09 03 001 001 APR 11 002 001 APR 11 ALL MOD 5948 MOD 5948 N 3 09 03 003 001 APR 11 ALL MOD 5948 N N 3 09 10 3 09 10 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 10 3 09 10 003 500 APR 11 004 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 15 3 09 15 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 15 3 09 15 003 500 APR 11 004 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 16 3 09 16 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 16 3 09 16 003 500 APR 11 004 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 17 3 09 17 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 17 3 09 17 003 500 APR 11 004 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 Turn TQ MOD 5948 MOD 5948 FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages 0-08 page 49-082 L.E.N.P. FEB 12 M P CH SE Page Seq Date Label Validity expression N N 3 09 20 3 09 20 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 20 3 09 20 003 500 APR 11 004 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 20 3 09 20 005 500 APR 11 006 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 20 3 09 20 007 500 APR 11 008 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 25 3 09 25 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 25 3 09 25 003 500 APR 11 004 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 25 3 09 25 005 500 APR 11 006 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 30 3 09 30 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 30 3 09 30 003 500 APR 11 004 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 35 3 09 35 001 500 APR 11 002 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N N 3 09 35 3 09 35 003 500 APR 11 004 500 APR 11 ALL PW127F - PW127M BOOST OFF MOD 5948 PW127F - PW127M BOOST OFF MOD 5948 N 3 10 00 001 001 APR 11 ALL MOD 5948 N N 3 10 01 3 10 01 001 500 APR 11 002 001 APR 11 ALL PW127F - 127M MOD 5948 MOD 5948 N N 3 10 02 3 10 02 001 300 APR 11 002 300 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages 0-08 page 50-082 L.E.N.P. FEB 12 M P CH SE Page Seq Date Label Validity expression N 3 10 03 001-002500 FEB 12 ALL PW127F - PW127M MOD 5948 N N 3 10 04 3 10 04 001 300 APR 11 002 300 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 10 04 3 10 04 003 300 APR 11 004 300 APR 11 ALL PW127F - PW127M PW127F - PW127M MOD 5948 MOD 5948 N N 3 11 00 3 11 00 001 001 APR 11 002 001 APR 11 ALL N N 3 11 01 3 11 01 001 500 FEB 12 002 500 FEB 12 ALL PW127F - PW127M PW127F - PW127M - KG MOD 5948 MOD 5948 N N 3 11 01 3 11 01 003 500 FEB 12 004 500 FEB 12 ALL PW127F - PW127M - KG PW127F - PW127M - KG MOD 5948 MOD 5948 N N 3 11 01 3 11 01 005 500 FEB 12 006 500 FEB 12 ALL PW127F - PW127M - KG PW127F - PW127M - KG MOD 5948 MOD 5948 N N 3 11 01 3 11 01 007 500 FEB 12 008 500 FEB 12 ALL PW127F - PW127M - KG PW127F - PW127M - KG MOD 5948 MOD 5948 N N 3 11 01 3 11 01 009 500 FEB 12 010 500 FEB 12 ALL PW127F - PW127M - KG PW127F - PW127M - KG MOD 5948 MOD 5948 N N 3 11 01 3 11 01 011 500 FEB 12 012 500 FEB 12 ALL PW127F - PW127M - KG PW127F - PW127M - KG MOD 5948 MOD 5948 N N 3 11 01 3 11 01 013 500 FEB 12 014 500 FEB 12 ALL PW127F - PW127M - KG PW127F - PW127M - KG MOD 5948 MOD 5948 N N 3 11 01 3 11 01 015 500 FEB 12 016 500 FEB 12 ALL PW127F - PW127M - KG PW127F - PW127M - KG MOD 5948 MOD 5948 N 3 11 01 017 500 FEB 12 ALL PW127F - PW127M MOD 5948 N 3 11 02 001 001 APR 11 ALL N 3 11 03 001 100 APR 11 ALL Turn MOD 5948 MOD 5948 MOD 5948 PW127F - PW127M TQ MOD 5948 FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages 0-08 page 51-082 L.E.N.P. FEB 12 M P CH SE Page Seq Date Label Validity expression N 3 11 04 001 200 APR 11 ALL PW127F - PW127M MOD 5948 N 3 11 05 001 200 APR 11 ALL PW127F - PW127M MOD 5948 N 3 11 06 001 001 APR 11 ALL MOD 5948 N 3 11 07 001 001 APR 11 ALL MOD 5948 N 3 11 08 001 200 APR 11 ALL N 3 11 09 001 001 APR 11 ALL MOD 5948 N 3 11 10 001 001 APR 11 ALL MOD 5948 N 3 11 11 001 001 APR 11 ALL MOD 5948 N 3 11 12 001 001 APR 11 ALL MOD 5948 N 3 11 13 001 001 APR 11 ALL MOD 5948 N 3 11 14 001 001 APR 11 ALL MOD 5948 N 3 11 15 001 001 APR 11 ALL MOD 5948 N 3 11 16 001 001 APR 11 ALL MOD 5948 N 3 11 17 001 001 APR 11 ALL MOD 5948 N 3 11 18 001 001 APR 11 ALL MOD 5948 N 3 11 19 001 001 APR 11 ALL MOD 5948 N 3 12 00 001 001 APR 11 ALL MOD 5948 N 3 12 10 001 001 APR 11 ALL MOD 5948 N 3 12 20 001 001 FEB 12 ALL MOD 5948 N 3 12 21 001 001 APR 11 ALL MOD 5948 Turn PW127F - PW127M TQ MOD 5948 FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Effective Normal Pages L.E.N.P. 0-08 page 52-082 FEB 12 M P CH SE Page Seq Date Label Validity expression N 3 12 22 001 001 APR 11 ALL MOD 5948 N 3 12 23 001 001 APR 11 ALL MOD 5948 N 3 12 24 001 001 FEB 12 ALL MOD 5948 N 3 12 25 001 001 FEB 12 ALL MOD 5948 N 3 12 26 001 001 FEB 12 ALL MOD 5948 End TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Modifications MODIF 0-09 page 1-082 L.O.M. PARTS FEB 12 TITLE VALIDITY 0043 REPLACE KING RADIO NAV-RADIO COMM EQUIPMENT BY COLLINS 1368 ICE AND RAIN PROTECTION - INSTALL INNER WING DE-ICING SYSTEM 1383 GENERAL - CHARACTERISTIC WEIGHTS MTOW 21.500 KG,MLW 21.350 KG,MZFW 19.700 KG - DEFINE PERFORMANCE 1603 ELECTRICAL POWER - INSTALL TRU ON PROVISION ALL ALL ALL ALL 1861 1.2 FUSELAGE - ATR 72 (ST3) FUSELAGE DEFINITION 2141 1 WATER/WASTE - TOILET TANK - INSTALL DC MOTOR 2456 2 COMMUNICATIONS - RELOCATE VHF2 ANTENNA ON UPPER FUSELAGE 2549 1 DOORS - PASSENGER/CREW DOOR MODIFY 2ND HANDRAIL ATTACHMENT FITTINGS 2735 1.2.3 ENGINE INDICATING - CHANGE SOFTWARE AS 06 IN E.E.C 3037 1.2 PNEUMATIC - ECS - MODIFY CROSSFEED VALVE OPENING CONTROL DURING TAXIING ALL ALL ALL ALL ALL ALL 3305 1.2 IGNITION - MODIFY THE CONTROL SYSTEM 3465 1 ELECTRICAL POWER - REPLACE AC GCU 3522 2.3 GENERAL - CERTIFY ATR 72 FOR 15 KT TAILWIND LANDING ALL ALL ALL Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Modifications L.O.M. 0-09 page 2-082 FEB 12 MODIF PARTS TITLE VALIDITY 3530 1.2 FLIGHT CONTROLS - ELEVATORS INSTALL CLUTCH RECONDITIONING DEVICE ON EXISTING PROVISION (PRODUCTION SCHEME) 3608 1.2 FLIGHT CONTROLS - ELEVATORS INSTALL FORCE DETECTOR RODS ON EXISTING FULL PROVISIONS ALL ALL 3663 1.2 GENERAL - INSTALL OVERBOARD EXHAUST FOR HBOV, SHROUD BLEED FUEL FLOW TRANSMITTER AND JET PUMP OF ATR72.210 ALL 3827 1.2 PROPELLERS - ADD FAILURE INDICATION OF SYNCHROPHASER 3849 2 GENERAL - INCREASE MZFW TO 20000 KGS 3986 1 LANDING GEAR - NLG EMERGENCY EXTENSION SYSTEM - ADD FREE FALL ASSISTER 4019 1 DOORS - PASSENGER/CREW DOOR REPLACE A 2ND HANDRAIL BY A SEMI AUTOMATIC HANDRAIL 4050 1 ICE & RAIN PROTECTION - AIRFOIL & PROPELLER DE-ICING - INSTALL AN AUTOMATIC CYCLE SELECTION CONTROL 4080 1 EQUIPMENT/FURNISHINGS EMERGENCY EQUIPMENT - REPLACE EMERGENCY LOCATOR TRANSMITTER 4111 1.2 CONTINUOUS IGNITION TRANSFORMATION IN "MAN IGNITION" 4116 1.2 HYDRAULIC POWER - RELOCATE GREEN PUMP CONTROL CIRCUIT BREAKER ALL ALL ALL ALL ALL ALL ALL ALL Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Modifications 0-09 page 3-082 L.O.M. FEB 12 MODIF PARTS TITLE VALIDITY 4169 1 ENGINE - STANDARD PRACTICES ENGINES - GENERAL - ADAPT FLIGHT IDLE ALL 4213 1 FLIGHT CONTROLS - FLAPS - MODIFY FLAPS CTL LOGIC (SHUNT) 4237 1.2 INDICATING & RECORDING SYSTEMS INSTALL STANDARD L52 MFC 4238 1.2 INDICATING & RECORDING SYSTEMS INSTALL STANDARD L23 MFC 4358 1 DOORS - SERVICE DOOR - REPLACE THE OLD OPENING DEVICE BY A NEW RIGID MECHANISM 4366 1.2 AUTO FLIGHT - MODIFY ELECTRICAL POWER SUPPLIES 4373 1.2 FLIGHT CONTROLS - AILERONS CONTROLS - INSTALL SPRING TAB WITH "ANTI-RAFALE" SYSTEM ALL ALL ALL ALL ALL ALL 4411 1.2 OXYGEN - DISTRIBUTION - MODIFY THE SYSTEM FOR 25% OF THE PASSENGERS 4422 1 DOORS - PASSENGER/CREW DOOR INVERT HANDLE & MODIFY SEMI AUTOMATIC HAND-RAIL 4439 2 FUSELAGE - SECT. 18 - INSTALL VERTICAL FIN WITH CARBON EPOXY BOX 4457 1.2.3 PROPELLERS - INSTALL 568F PROPELLERS ON ATR 72-210 4571 1 INDICATING & RECORDING SYSTEMS INSTALL MFC S4 ON ATR 72-210 ALL ALL ALL ALL ALL Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Modifications 0-09 page 4-082 L.O.M. FEB 12 MODIF PARTS TITLE VALIDITY 4584 1 PNEUMATIC - AIR LEAK DETECTION SYSTEM - REPLACE SENSING ELEMENTS 4585 1 FUSELAGE - CENTER SECTION (STA 11132 TO 13319) - INSTALL SOUND INSULATION BLANKETS 4671 2.3 GENERAL - INCREASE MTOW TO 22500 KGS & MZFW TO 20300 KGS & MLW TO 22350 KGS 4673 2 FLIGHT CONTROLS - AILERON TRIM PROHIBIT TRIM OPERATION WITH AP ENGAGED 4686 2 FUEL - QUANTITY INDICATION - ADD LOW LEVEL DETECTION SYSTEM 5008 1.2 ICE & RAIN PROTECTION - ICE DETECTION - MOD. OPERATION OF "ICING" LEGEND OF ICE DETECT/PTT PUSHBUTTON SWITCH 5016 1 NAVIGATION - RADAR - INSTALL NEW PRIMUS 660 WEATHER RADAR 5017 1 COMMUNICATIONS - CABIN & FLIGHT CREW CALL SYSTEM - ADD "EMER CALL" ON A NEW-LOOK CONFIG. ATTENDANT HANDSET 5040 1 LIGHTS - EMERGENCY LIGHTINGGROUND MARKING OF EVACUATION WAY IN PAX CABIN 5150 2 GENERAL - EXTENSION OF THE FWD CG LIMITS 5213 2 GENERAL - INCREASE MZFW BY 200 KG 5377 1.2 EQUIPMENT/FURNISHINGS - WIRING FOR COCKPIT ENTRANCE SECURISED ALL ALL ALL ALL TQ0064-0066 TQ0068 ALL ALL ALL ALL ALL ALL ALL Turn TQ FCOM FLIGHT CREW OPERATING MANUAL ATR 72 List of Modifications L.O.M. 0-09 page 5-082 FEB 12 MODIF PARTS TITLE VALIDITY 5434 1.2 EQUIPMENT/FURNISHINGS - INS TALL DOOR ON ELECTRICAL PROVISION 5465 2 EQUIPMENT/FURNISHINGS - SECURIZED DOOR - REPLACE FITTINGS ON STRUCTURE 5555 2 GENERAL - INCREASE MZFW AND WTOW BY 300 KGS OF 72-500 MODEL 5736 3 GENERAL - COCKPIT VOICE RECORDER ALL ALL ALL ALL 5948 NAVIGATION - INSTALL NEW AVIONICS SUITE 5961 COMMUNICATIONS - INSTALL SINGLE HF FOR THE NEW AVIONICS SUITE 5962 NAVIGATION - 2ND DME FOR NEW AVIONICS SUITE 5963 NAVIGATION - 2ND ADF FOR NEW AVIONICS SUITE ALL ALL ALL ALL End TQ . FCOM FLIGHT CREW OPERATING MANUAL ATR 72 Cross Reference Table 0-10 page 1-082 C.R.T. FEB 12 This table shows, for each delivered aircraft, the cross reference between : - the fleet serial number (F.S.N.) - the manufacturing serial number (M.S.N.) - the registration number It is the F.S.N. which appears in the L.E.N.P. or L.E.T.P. End F.S.N. M.S.N. TQ0064 0967 PR-TKI TQ0065 0971 PR-TKJ TQ0066 0987 PR-TKK TQ0067 0992 PR-TKL TQ0068 0998 PR-TKM TQ REGISTRATION . 0.40.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES ORGANIZATION OF THE MANUAL P1 001 APR 11 AA The Flight Crew Operating Manual (FCOM) provides operating crew members and flight operations engineers with information on the ATR 72 technical description, procedures and performances characteristics. It may be used as a crew manual for training purposes and flight preparation. FCOM mainly comprises : - manuel management in Part 0 - systems description in Part 1 - limitations with comments in Part 2 - procedures : normal, following failure and emergency, in Part 2 with comments - procedures and techniques in Part 2.02 - performances (conservative and simplified compared with AFM) in Part 3 - Special Operations in Part 3 - OEB (Operations Engineering Bulletin) : validated by the ATR Chief Test Pilot, their aim is to cover temporary equipment discrepancy. They are printed on pale green paper and are situated at the very end of FCOM. For any question, comment or suggestion regarding this manual, or technical documentation in general, we recommend to use following e-- mail : doc@atr.fr stating at the minimum : - aircraft model(s) - manual(s) concerned - precise page(s) if applicable DEFINITION OF THE PAGE A page is defined by : - a reference : Part / Chapter / Section / page number - Example : 2.05.10 page 20. - an effectivity criterion determining the page sequence example : Equipment, Modification, Engine... A page with a given reference may have several sequences : example : 2.05.10 page 20 No criterion . . . . . . . . . . . Sequence 001 Mod XXXX . . . . . . . . . . . . Sequence 002 Mod XXXX + YYYY . . . . . . Sequence 003 All the sequences cover, for a given reference, all technical solution or variant for aircraft types covered by the manual. Airlines receive a part of these sequences to cover their fleet. A sequence can be valid for several aircraft but an aircraft can not have several sequences: an aircraft receives the page with the highest sequence among all pages for which it has a validity. Mod 5948 0.40.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES ORGANIZATION OF THE MANUAL P2 001 APR 11 (1) GIE ATR logo, with aircraft type and manual type (2) Title of Chapter (3) Part, chapter and section in the manual (4) Page Numbering - Particular case : a page followed by an alphabetic letter must be inserted between 2 pages. Example : page 11A must be inserted between pages 11 and 12. (5) Sequence number (6) If 2 letters (XX) are indicated on the page, this one is customized to airline XX (7) Date of revision (date of page issue) (8) Zone for standard (9) Zone for unit (10) Title of section (1) Modification zone : contains expression of modifications characterizing the content of this page. (2) Indication of engine type installed on aircraft ; if there is “ALL” or if there is no Eng reference, the content of the page does not depend on a particular engine. (3) Indication of aircraft type ; if there is “ALL” or if there is no Model reference, the content of the page does not depend on a particular model. Mod 5948 0.40.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P3 001 ORGANIZATION OF THE MANUAL APR 11 RECTO- VERSO The FCOM is published in recto-- verso paper AT5 format customized for each airline. In the LENP (0.08.00) List of Effective Normal Pages, when recto and verso are printed, each sheet is represented by 2 lines : - the first line concerns the recto. - the second line concerns the verso. If only recto sheet is printed, it is represented by only one line. Then for each sheet, we find the validity line with an expression containing one or several numbers which represent FSN (Fleet Serial Number) of aircraft for which this sheet is applicable. To understand the effectivity of the sheets, you must read : Example : XX0001-- 0003 = XX FSN0001 to FSN003 - - > 3 aircraft valid XX0001 XX0003 = XX FSN0001 and FSN0003 - - > only 2 aircraft valid In CRT (0.10.00), we find the list of fleet aircraft with FSN, MSN (Manufacturer Serial Number) and registration number. MANUAL UPDATING Your manual comprises 2 types of pages : - white pages or NORMAL pages - yellow pages or TEMPORARY pages These 2 families of pages have a separated management. NORMAL PAGES (white) For its first issue FCOM was published in “white” normal pages. Then on a yearly basis at the minimum, a normal revision is performed amending previous issue by revising pages (sheet replacement), creating new pages (sheet insertion) or deleting pages (sheet deletion). Detailed and exhaustive information for manual normal revision updating is in SNNP (0.07.00), Shipping Note for Normal Pages. Operator must refer to SNNP and new LENP to update properly its manual. SNNP lists all revised, created or deleted white sheets. LENP gives aircraft validity information for all concerned white sheets. It is important to note that the action given in SNNP is valid for the sheet (recto-- verso) not for one page. Normal Revisions are listed in LNR (0.05.00) List of Normal Revisions. Reasons of revision are highlighted in RNR (0.06.00) Reason of Normal Revisions. mod 5948 0.40.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P4 001 ORGANIZATION OF THE MANUAL APR 11 AA MANUAL UPDATING (cont’d) TEMPORARY PAGES (yellow) Between two normal revisions some subjects may present a particular urgency. In those cases we perform a Temporary Revision. It may concern only one customer or the whole fleet. All temporary pages at a given moment are listed in LETP (0.04.00), List of Effective Temporary Pages. Temporary pages are recto-- only pages. When a white page exists with the same reference, a yellow page is inserted in face or before corresponding white page and its content amends the content of white page. If there is no white page with the same reference, yellow page(s) is(are) inserted just after the last adapted white page or chapter. Detailed and exhaustive information for manual temporary revision updating is in SNTP (0.03.00), Shipping Note for Temporary Pages. Operator must refer to SNTP and new LETP to update properly its manual. SNTP lists all revised, created or deleted yellow pages. LETP gives aircraft validity information for all concerned yellow sheets. It is important to note that the action given in SNTP is valid for the yellow page (no verso on yellow page). Temporary Revisions are listed in LTR (0.01.00) List of Temporary Revisions. Each operator has its own LTR as Temporary Revision does not necessarily concern all customer : TR01 for an operator may be equivalent to TR10 for another operator and TR20 for ENV. Reasons of revision are highlighted in RTR (0.02.00) Reason of Temporary Revisions. AIRCRAFT CONFIGURATION All ATR modifications having an impact on FCOM content are listed in LOM (0.09.00), List Of Modifications. As for LENP or LETP, aircraft validity are given under FSN values. We may consult CRT to have correspondence between FSN and MSN. Mod 5948 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES STANDARD NOMENCLATURE P1 001 APR 11 AA GLOSSARY OF STANDARD NOMENCLATURE AAS ABNORM (ABN) AC ACARS AC BTC AC BTR ACCU AC EBTC ACM ACP ACW ADC ADF ADI ADN ADS AFCS AFDX A/FEATH AFT AFU AGB AGL AH AHRS AHRU AIL ALT ALTM ALTN AMP ANN AOA Anti-- icing Advisory System Abnormal Alternating Current ARINC Communication Addressing and Reporting System AC Bus Tie Contactor AC Bus Tie Relay Accumulator AC Emer Bus Transfer Contactor Air Cycle Machine Audio Control Panel Alternating Current Wild Frequency Air Data Computer Automatic Direction Finding Attitude Director Indicator Avionic Data Network Air Data System Automatic Flight Control System Avionic Full Duplex Auto Feathering Rear Part Auto Feather Unit Accessory Gear Box Above Ground Level Ampere-- Hours Attitude and Heading Reference System Attitude and Heading Reference Unit Aileron Altitude Altimeter Alternate Ampere Annunciator Angle of Attack 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P2 STANDARD NOMENCLATURE AA AP APC APP ARM ARINC A/S ASAP ASD ASI ASTR ASYM ATC ATE ATPCS ATR ATSCALL ATT ATTND AUTO AUX AVAIL AZ Auto-- Pilot Active Phase Control Approach Armed Aeronautical Radio Incorporated Antiskid As Soon As Possible Accelerate Stop Distance Air Speed Indicator AC Standby Bus Transfer Relay Asymmetry Air Traffic Control Automatic Test Equipment Automatic Take off Power Control System Air Transport Racking Air Transport Selective Calling Attitude Attendant Automatic Auxiliary Available Azimuth BARO BAT BC BITE BPCU BRG BRK B-- RNAV BRT BSC BTC BTR BXR Barometric Battery Back Course Built in Test Equipment Bus Power Control Unit Bearing Brake Basic Area Navigation Bright Battery Start Contactor Bus Tie Contactor Bus Tie Relay Battery Transfer Relay 001 APR 11 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES STANDARD NOMENCLATURE AA CAB CAC CAN CAPT CAT C/B CCAS CCW CD CDI CDS CDU CFC CG CHAN CHC CHG C/L CL CL CLA CLB CLR CM CMPTR COM COMPT CNTR CONFIG CONT CORRECT CPCS CPL CPM CRC CabinCAC Core Avionic Cabinet Controller Area Network Captain Category Circuit Breaker Centralized Crew Alerting System Counter clockwise Coefficient of Drag Course Deviation Indicator Cockpit Display System Cabin Display Unit Constant Frequency Contactor Center of Gravity Channel Charge Contactor Charge Check List Condition Lever Coefficient of Lift Condition Lever Angle Climb Clear Crew Member Computer Communication Compartment Contactor Configuration Continuous Correction Cabin Pressure Control System Auto Pilot Coupling Core Processing Module Continuous Repetitive Chime P3 001 APR 11 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P4 STANDARD NOMENCLATURE AA CRS CRZ CTL CVR CW Course Cruise Control Cockpit Voice Recorder Clockwise DADC DADS DC DCA DEC DELTA P DEV DFDR DGR DH DIFF DISCH DIM DIST DME DN DSPL DU Digital Air Data Computer Digital Air Data System Direct Current Data Concentration Application Declination, Decrease Differential Pressure Deviation Digital Flight Data Recorder Degraded Decision Height Differential Discharge Light Dimmer Distance Distance Measuring Equipment Down Display Display Unit EADI EBCC EBTC ECS E/E EEC EFCP EFIS EGHR EHSI Electronic Attitude Director Indicator Emergency Battery Charge Contactor Emer Bus Transfer contactor Environmental Control System Electrical/Electronic Engine Electronic control EFIS Control Panel Electronic Flight Instrument System External Ground Handling Relay Electronic Horizontal Situation Indicator 001 APR 11 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P5 STANDARD NOMENCLATURE AA EHV ELEC ELV EMER ENG EPC EQPT ESS ET ETOPS EWD EXT EXC Electro Hydraulic Valve Electrical Elevation Emergency Engine External Power Contactor Equipment Essential Elapsed Time Extended Twin Operations Engine and Warning Display Exterior, External External Power/Service Bus Contactor F FAIL FCOC FCU FD FDA FDAU FEATH, FTR FF FGCP FGS FI FLT FMA FMS F/O FOS FQI FT FTO FU FWD FWS Farenheit Failed, Failure Fuel Cooled Oil Cooler Fuel Control Unit Flight Director Flight Display Application Flight Data Acquisition Unit Feathered, Feathering Fuel Flow Flight Guidance and Control Panel Flight Guidance System Flight Idle Flight Flight Modes Annunciators Flight Monitoring System First Officer Flight Operations Software Fuel Quantity Indication Foot, Feet Final Take Off Fuel Used Forward Flight Warning System 001 APR 11 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P6 STANDARD NOMENCLATURE AA GA GAL GC GCR GCU GEN GI GMT GND GPS GPU GRD G/S GSPD GXS Go Around Galley Generator Contactor Ground Clutter Reduction Generator Control Unit Generator Ground Idle Greenwitch Mean Time Ground Global Positioning System Ground Power Unit Ground Glide Slope Ground Speed ACW Generator/Service Bus Contactor HBV HD HDG HDLG (HDL) HEBTC HF HI HLD HMBTC HMU HOBV HP HSI HTG HU HYD Handling Bleed Valve Head Down Heading Handling Hot Emer Battery Transfer Contactor High Frequency High Hold Hot Main Battery Transfer Contactor Hydromechanical Unit Handling Overboard Valve High Pressure Horizontal Situation Indicator Heating Head Up Hydraulic IAF IAS ICP IDT IESI IF Initial Approach Fix Indicated Air Speed Index Control Panel Ident Integrated Electronic Standby Instrument Intermediate Frequency 001 APR 11 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES STANDARD NOMENCLATURE AA IGN ILS IMU IN INC IND IN/HG INHI INOP INS INST INT INU INV IOM IRS ISOL ISV ITT Ignition Instrument Landing System Initial Measurement Unit Inertial Navigation Increase Indicator Inches of Mercury Inhibit Inoperative Inertial Navigation System Instrument Interphone Inertial Navigation Unit Inverter Input Output Module Inertial Reference System Isolation Isolation Shut-- off Valve Inter Turbine Temperature KHZ KT Kilo-- Hertz Knot LAT LAV LB LBA LDG L/G LH LIM LMN LNAV LO LOC LO-- PR LP LT LVL Lateral Lavatory Pound Lowest Blade Angle Landing Landing Gear Left Hand Limitation Left Main Gear Lateral Navigation Low Localizer Low Pressure Low Pressure Light Level P7 001 APR 11 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES STANDARD NOMENCLATURE AA MAC MAN MAP MAX MB MBCC MBTC MC MCDU MCP MCT MEA MECH MFC MFCU MFD MGT MHZ MIC MIN MISC MKR MLD MLS MLW MM MMO MMPU MOD MPC MPU MSG MSN MTOW MW MZFW Mean Aerodynamic Chord Manual Ground Mapping Maximum Millibar Main Battery Charge Contactor Main Bus Transfer Contactor Master Caution Multifunction Control Display Unit Multi Function Control Panel Maximum Continous Minimum En route Altitude Mechanic Multi Function Computer Mechanical Fuel Control Unit Multi Function Display Management Megahertz Microphone Minimum Miscellaneous Marker Main Landing Gear Microwave Landing System Maximum Landing Weight Millimeter Maximum Operating Mach Multi Media Player Unit Modification Multi Purpose Computer Micro Processor Unit Messages Manufacturer Serial Number Maximum Take off Weight Master Warning Maximum Zero Fuel Weight NAC NAV ND NDB Nacelle Navigation Navigation Display Non Directional Beacon P8 001 APR 11 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P9 STANDARD NOMENCLATURE AA NDB (GPS) NEG NG NH NIL NL NLG NM NORM NP NPU NVM N/W NWS Navigation Data Base Negative Nose Gear High Pressure Spool Rotation Speed Nothing, No Object Low Pressure Spool Rotation Speed Nose Landing Gear Nautical Mile Normal Propeller Rotation Speed Navigation Processor Unit Non Volatile Memory Nose Wheel Nose Wheel Steering OBS OT OUTB OVBD OVERTEMP OVHP OVHT OVLY OVRD OXY Omni Bearing Selector Other traffic Outboard Overboard Overtemperature OverHead Paneal Overheat Overlay Override Oxygen PA PB PEBMV PEC PF PFD PFTS PIU PL PLA PNF PNL POS Passenger Address Push Button Parking/Emergency Braking Metering Valve Propeller Electronic Control Pilot Flying Primary Flight Display Power Feeder Thermal Sensor Propeller Interface Unit Power Lever Power Lever Angle Pilot Non Flying Panel Position 001 APR 11 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P 10 001 STANDARD NOMENCLATURE AA P-- RNAV PRESS PRIM PRKG PROC PROP PROX SW PRV PSI PSU PSV PT PT (TCAS) PTB PTT PTW PVCU PVM PWM PWR Precision Area Navigation Pressurization, Pressure Primary Parking Procedure Propeller Proximity Switch Pressure Regulating Valve Pound per Square Inch Passenger Service Unit Propeller Servo Valve Point Proximity traffic Power Trim Box Push To Talk, Push To Test Pitch Thumb Wheel Power and Video Control Unit Propeller Valve Module Pulse Width Modulation Power QAR QRC QT QTY Quick Access Recorder Quick Release Control Quart Quantity RA (TCAS) RA RAD/ALT RAD/INT RAIM RCAU RCDR RCL RCP RCT RCU RECIRC REV RGA Resolution Advisory Radio Altitude Radio Altitude Radio/Interphone Receiver Autonomous Integrity Monitoring Remote Control Audio Unit Recorder Recall Refuel Control Panel Rain Echo Attenuation Compensation Technique Releasable Centering Unit Recirculation Reverse Reserve Go-- Around APR 11 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P 11 STANDARD NOMENCLATURE AA RGB RH RLY RMA RMG RMI RMS RNP RPM RQD RTO RTOW RUD Reduction Gear Box Right Hand Relay Radio Management Application Right Main Gear Radio Magnetic Indicator Radio Management System Required Navigation Performance Revolution Per Minute Required Reserve Take-- Off Regulatory Take-- Off Weight Rudder SAT SB SBTC SBY SC SCU SD SDTC SEC SEL SELCAL SGL SGU SID SMK SMKG S/O (SO) SOV SPD SPLR SPLY SSR STAB STAR STBY STR STRG SVCE SW SYNPHR SYS Static Air Temperature Service Bulletin Stand By bus Transfer Contactor Stand By Single Chime, Starter Contactor Signal Conditioning Unit System Display Static Inverter Override Transfer Contactor Secondary Selector Selective Calling Single Symbol Generator Unit Standard Instrument Departure Smoke Smoking Shut Off Shut Off Valve Speed Spoiler Supply Service Bus Select Relay Stabilizer Standard Arrival Stand By Service Bus Transfer Relay Steering Service Switch Synchrophaser System 001 APR 11 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P 12 STANDARD NOMENCLATURE AA TA (TCAS) TRAFFIC Advisory TAD TAS TAT TAWS TBD TCAS TCF TCS T/D TEMP TGT TIC TK TLU TM T/O (TO) TOD TOR TOW TQ TRU TTG TTL Terrain Awareness Display True Air Speed Total Air Temperature Terrain Awareness Waring System To be Determined Traffic Collision and Avoidance System Terrain Clearance Floor Touch Control Steering Time Delay Temperature Target Turbine Inlet Control Tank Travel Limiting Unit Torque Motor Take off Take-- Off Distance Take-- Off Run Take off weight Torque Transformer Rectifier Unit Time To Go Tuned to LOC UBC U/F UHF UNCPL UNDV UNLK UTLY Utility Bus Contactor Underfloor Ultra High Frequency Uncouple Undervoltage Unlock Utility VC VCCU VCP VENT VERT Calibrated Airspeed Video Cabin Command Unit Virtual Control Panel Ventilation Vertical 001 APR 11 0.50.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES P 13 001 STANDARD NOMENCLATURE AA VHF VMCA VMCG VMCL VMHB VMO VNAV VOR VSI VU Very High Frequency Minimum Control Speed in flight Minimum Contorl Speed on ground Minimum Conrol Speed during landing approach Velocity minimum High Bank Maximum Operating Speed Vertical Navigation VHF OMNI Directionnal Range Vertical Speed Indicator Visual Unit W WARN WAT WBM WOW WX Watt Warning Weight Altitude Temperature Weight and Balance Manual Weight On Wheel Wheater Mode XFEED XFR XPDR Cross feed Transfer Transponder YD Yaw Damper ZA ZCTH ZFW ZP ZRA Aircraft Altitude Theoritical Cabin Altitude Zero Fuel Weight Pressure Altitude Radio Altimeter Altitude APR 11 . 0.60.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES UNITS CONVERSION TABLE AA Mod 5948 P1 001 APR 11 0.60.00 FLIGHT CREW OPERATING MANUAL PRELIMINARY PAGES UNITS CONVERSION TABLE AA Mod 5948 P2 001 APR 11 1.00.00 AIRCRAFT GENERAL P1 CONTENTS 001 APR 11 AA 1.00.00 CONTENTS 1.00.10 GENERAL 1.00.20 COCKPIT 1.00.25 COCKPIT DOOR SECURITY SYSTEM AND VIDEO CABIN SURVEILLANCE (if installed) DESCRIPTION LOCKING SYSTEM DESCRIPTION CALL PANEL CONTROL PANEL LOCKING SYSTEM ON/OFF CONTROL ELECTRICAL SUPPLY / SYSTEM MONITORING VIDEO CABIN SURVEILLANCE (if installed) 25.1 25.2 25.3 25.4 25.5 25.6 25.7 1.00.30 30.1 30.2 30.3 DOORS DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 1.00.40 40.1 40.2 40.3 LIGHTING DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC 1.00.50 50.1 50.2 WATER AND WASTE SYSTEM DESCRIPTION ELECTRICAL SUPPLY Mod: 5948 . 1.00.10 AIRCRAFT GENERAL P1 001 GENERAL APR 11 AA AIRCRAFT DIMENSIONS AND GROUND CLEARANCE VERTCAL CLEARANCES (A ! J) OPERATING EMPTY WEIGHT CG 25% A B C D E F G H J α K L M N P R S Mod: 5948 ft 10.80 2.16 4.00 4.88 25.33 10.46 3.97 12.50 22.87 MAXIMUM RAMP WEIGHT CG 14% m 3.29 0.66 1.22 1.49 7.72 3.19 1.21 3.81 6.97 - 1°011 5 Ft 6.3 in. 35 Ft 4.8 in. 89 Ft 1.5 in. 23 Ft 11.18 in. 13 Ft 5.4 in. 26 Ft 6.9 in. 88 Ft 9 in. ft 10.43 1.77 3.61 4.66 25.16 10.13 3.64 12.20 22.70 m 3.18 0.54 1.10 1.42 7.67 3.09 1.11 3.72 6.92 - 1°183 CG 37% ft 10.73 2.06 3.90 4.40 24.67 10.23 3.74 12.17 22.24 m 3.27 0.63 1.19 1.34 7.52 3.12 1.14 3.71 6.78 - 0°550 1.683 m 10.79 m 27.166 m 7.31 m 4.100 m 8.100 m 27.050 m 1.00.10 AIRCRAFT GENERAL P2 GENERAL AA TURNING CAPABILITY ON GROUND Mod: 5948 001 APR 11 1.00.10 AIRCRAFT GENERAL P3 GENERAL AA CABIN CROSS SECTION Mod: 5948 001 APR 11 1.00.10 AIRCRAFT GENERAL P4 GENERAL 001 APR 11 AA LOCATION OF THE TAIL PROP On ground during passengers boarding/desembarquing, the tail prop must be installed on the tail skid to avoid a possible toppling over. Note : When not used, the tail prop is stored in the rear unpressurized area of the aircraft (beyond the aft bulkhead). TAIL BUMPER At each walk around, inspect skid shoe : If it is stripped, check the red indicator : - If this indicator does not show evidence of wear, aircraft can be dispatched. - If this indicator shows evidence of wear, maintenance action is required. Mod: 5948 1.00.10 AIRCRAFT GENERAL P5 GENERAL 001 APR 11 AA LOCATION OF ANTENNAS Note : Number and location of antennas may change depending on the versions. All possibilities are drawn on these views. Mod: 5948 . 1.00.20 AIRCRAFT GENERAL P1 COCKPIT 001 APR 11 AA GENERAL For comfort, convenience and safety, various furnishings are fitted in the cockpit. Mod: 5948 1.00.20 AIRCRAFT GENERAL P2 COCKPIT 001 APR 11 AA SEATS CAPT and F/O seats are mounted each on a base secured to the floor on each side of the center pedestal. They are mechanically adjustable along the three axes for individual comfort. They are equiped with adjustable folding armrests. The observer seat is located behind the pedestal and between electronic and electric racks. When not in use, the observer seat can be stowed facing the electronic rack (position A), in the cargo compartment (position B) allowing the observer to move in the cabin. Safety pins enable the observer seat to be rocked backward in order to facilitate emergency evacuation in case of jamming. The three seats are equipped with full harness including an inertial reel with locking handle for the shoulder harness. Mod: 5948 1.00.20 AIRCRAFT GENERAL P3 COCKPIT 001 APR 11 AA SEAT POSITION SIGHT GAUGE Seat position sight gauge may be used for proper setting seat height and fore/aft position. It assures to the crew a correct view of instrument panels as well as runway environment, especially when flying low visibility instrument approaches. This indicator is composed of three colored balls. Center ball is red and is horizontally shifted compared with the other two white balls. For proper seat position, respective white ball is obscured by the red one. Mod: 5948 1.00.20 AIRCRAFT GENERAL P4 COCKPIT AA CAPT/F/O SEATS OBSERVER SEAT Mod: 5948 001 APR 11 1.00.20 AIRCRAFT GENERAL P5 001 APR 11 COCKPIT PHILOSOPHY AA COCKPIT PHILOSOPHY Status and failure indications are integrated in the pushbuttons (PB). PB positions and illuminated indications are based on a general concept with the “light out” condition for normal continuous operation according to the basic rule. With few exceptions, the light illuminates to indicate a failure or an abnormal condition. Whenever possible, the failure alert is integrated in the PB which has to be operated for corrective action. Some PB (such as ACW...) are circled in amber to help crew to find them in case of smoke (fluorescent painting). PB POSITION BASIC FUCTION IN (DEPRESSED) OUT (RELEASED) ON, AUTO, NORM OFF, MAN, ALTN, SHUT COLOR INDICATION No light illuminated except flow bars CYAN GREEN WHITE AMBER RED Mod: 5948 Normal basic operation Selection of temporarily required or unused systems Back up or alternate system selected Selection other than normal basic operation Caution indication Warning indication . 1.00.25 AIRCRAFT GENERAL P1 COCKPIT DOOR SECURITY SYSTEM 001 APR 11 AA 25.1 Cockpit door description The door has an electromagnetic locking system controlled by the pilots. In normal conditions, when the door is closed, it remains locked. In case of a loss of electrical power, the door can be locked using the manual bolt. To open the door, the locking system has to be unlocked. Upon receiving an entry request, the flight crew can authorize entry by unlocking the door which remains closed until it is pulled open. When the flight crew does not respond to a request for entry, the cabin crew may unlock the door by pressing the Emergency push-- button of the door call panel installed on cargo compartment side. The door is bulletproof, intrusion resistant and fully compliant with the rapid decompression requirements. The right door panel can be removed from the cockpit in case of the door becomes jammed by using the quick release hinges that are only accessible from inside the cockpit. 25.2 Cockpit Door Locking System Description The cockpit door locking system (CDLS) provides a means of electrically locking and unlocking the cockpit door. The system is mainly composed of : - a Door Call panel located on the cargo compartment side on the right door panel - a toggle switch, located on the center pedestal’s Cockpit Door Control panel - a Cockpit Door Control Unit located in the forward avionics bay - a buzzer - a Cockpit Door Locking System Switch located behind the first officer seat The door call panel enables the cabin crew to request access to the cockpit. There are two different access request modes : a “Routine” access request type and an “Emergency” access request. The toggle switch enables the flight crew to lock or unlock the cockpit door, following an access request, thereby allowing or denying entry into the cockpit. The Cockpit Door Control Unit is the system controller in charge of : - Locking and unlocking the electromagnetic locks, upon flight crew action - Alert annunciation to indicate failure of electromagnetic locks - Activating the access request buzzer and turning on the Door Call panel light The buzzer sounds in the cockpit for a minimum of 2 seconds (duration = duration of pushbutton activation + 2 seconds) to indicate that a routine access request has been made or sounds continuously if an emergency access procedure has been initiated. The Cockpit Door Locking System Switch enables the Cockpit Door Locking System to be switched ON or OFF at the beginning or at the end of the flight and to facilitate maintenance tasks and ground operations. Mod: 5948 1.00.25 AIRCRAFT GENERAL P2 COCKPIT DOOR SECURITY SYSTEM 001 APR 11 AA 25.3 Door Call Panel The Door Call Panel is used by the cabin crew to request pilots to open the door. OPEN Green light illuminates : The door has been unlocked either by a flight crew action or automatically (during 10 seconds) when no flight crew action has been performed during the delay (30 seconds), following an emergency access request. The door panel can then be pulled open OPEN Green light flashes : An emergency request to enter the cockpit has been made; the buzzer will sound continuously in the cockpit, but no action has yet been taken by the flight crew. 1 2 DENIED light illuminates : When the flight crew has denied access. The door remains locked. If no crew action is taken, the light remains illuminated for 3 minutes. During this delay any action on the call panel will be inhibited. CALL pushbutton switch : It is used to sound the buzzer in the cockpit for at least 2 seconds 3 4 EMER pushbutton switch : It is protected by a rotating plate to prevent inadvertent activation. It is used to initiate the emergency opening of the door when the flight crew does not respond. The buzzer will sounds continuously in the cockpit, the OPEN green light on the Door Call Panel will flash. Mod: 5948 1.00.25 AIRCRAFT GENERAL P3 COCKPIT DOOR SECURITY SYSTEM 001 APR 11 AA 25.4 Cockpit Door Control Panel The cockpit door opening is controlled by a toggle switch, located on the central pedestal 1 Toggle Switch OPEN Position : This position is used to enable the cabin crew member to open the cockpit door. The switch must be pulled and maintained in the open position until the right door panel is pulled open. To open the left door panel, move the handle located on the cockpit side and pull the left panel aft. CLOSE Position : The door is locked, and emergency access is possible for the cabin crew DENY position : Once the button has been moved to this position, the door is locked. EMERGENCY access, the buzzer and the Door Call Panel are inhibited for 3 minutes. Note - If the DENY position has not been used by the pilot for at least 3 minutes, the cabin crew is able to request either the routine or the emergency access. - The OPEN position overrides and resets any previous selection - In case of an electrical supply failure, the cockpit door is automatically unlocked. 2 FAULT/OPEN Indication OPEN light ON : The door is not closed, or not locked OPEN light flashes : The cabin crew has started an emergency access procedure. If there is no reaction from the flight crew, the door will unlock at the end of the 30 seconds delay. FAULT : This light comes on when a system failure has been identified (Example : electromagnetic lock, control unit, electrical supply) Buzzer Buzzer sounds : 3 Mod: 5948 For at least 2 seconds after the cabin crew has request an access through the CALL push-- button on the Door Call Panel, or continuously when the cabin crew has started an emergency access procedure. 1.00.25 AIRCRAFT GENERAL P4 COCKPIT DOOR SECURITY SYSTEM 001 APR 11 AA 25.5 COCKPIT DOOR LOCKING SYSTEM ON/OFF CONTROL The Cockpit Door Locking System ON/OFF Control Switch is located behind the First Officer seat. ON/OFF Control Switch ON : The cockpit door locking system is operative. OFF : The cockpit door locking system is deactivated. The door is unlocked, the door right panel can be opened from the cargo compartment side by pulling it. To open the door left panel, move the handle located on the cockpit side and pull the left panel. If the system is switched off and the aircraft power is available, the FAULT light on the pedestal Cockpit Door Control panel comes on. 25.6 ELECTRICAL SUPPLY / SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT Cockpit Door Locking System Cockpit Door Fault light Mod: 5948 DC BUS SUPPLY (C/B) DC BUS 2 ESS BUS (on central pedestal cockpit door control panel) 1.00.30 AIRCRAFT GENERAL P1 DOORS 001 APR 11 AA 30.1 DESCRIPTION LOCATION ENTRY DOORS The entry door is an outward opening, non plug type door with a net opening of 72 cm (28.5”) wide (without hand-- rail(s)) and 1.75 m (68.8”) high. The mechanism is essentially composed of two handles, a lifting cam and locking shoot bolts placed on the rear part of the door (for door operating, refer to 1.07.30). Attached to the integrated stair structure is a folding hand-- rail which, by means of a link to the fuselage structure automatically erects when the door is opened. SERVICE DOOR The service door is an outward opening, non plug type door with a net opening of 69 cm (27”) wide and 1.27 m (50”) high. Open position is forward. Door operation can be performed manually from inside or outside of the airplane (refer to 1.07.30). INTERNAL DOOR A forward opening hinged door separates the forward cargo compartment and the passenger compartment. A latch operated by a knob on the cabin side and a safety key from the cargo side is provided. In case of emergency it can be forced opened in either direction. A cockpit door security system is installed (refer to 1.00.25). Mod: 5948 1.00.30 AIRCRAFT GENERAL P2 DOORS 001 APR 11 AA CARGO DOOR The cargo door is an outward opening, non plug type door hinged at its upper edge giving a net clear opening of 1.30 m (51”) wide by 1.57 m (62”) high. The door is actuated by an electrical actuator. A hold-- open strut maintains the cargo door in the open position. It also protects door from wind gusts. ELECTRICAL OPERATING The cargo door is unlocked by two levers and operated from a panel located outside. Mod: 5948 1.00.30 AIRCRAFT GENERAL P3 DOORS 001 APR 11 AA 1 Panel cover switch Connects the Ground Handling Bus on line when the panel cover is open. 2 Ground Handling Bus “ON BAT” - Is ON when Ground Handling Bus is directly supplied by Hot main Bat Bus. Note : This light shows that the main battery is emptying even if the BAT toggle switch is in “OFF” position (visible even when the panel cover is closed). Cargo Bay light switch Allows acivation of the cargo bay light from outside. 3 4 Actuator Selection Switch Is used to operate the door (opening or closing) when the “CARGO DOOR ARMED” light is ON. 5 ”CARGO DOOR LCHD” blue light Light is ON when all door hooks and latch locks are fully engaged. Note : The door can be locked and latched only from outside. 6 ”CARGO DOOR ARMED“ green light Is ON when Actuator selection switch working conditions are met. These conditions are : - Panel cover opened - Door unlocked by operating handle : all locks are disengaged Mod: 5948 1.00.30 AIRCRAFT GENERAL P4 DOORS 001 APR 11 AA To open cargo door - Push flap to grasp handle of the upper lever. - Depress handle and pull the upper lever fully down. - Pull the lower lever fully down. - Open flap for access to cargo door control panel (green light illuminates). - Press selector to “OPEN” until door is completely opened. - Make sure selector returns to neutral position. - Lock folding strut. To close cargo door - Unlock folding strut. - Open flap for access to cargo door control panel. - Press selector to “CLOSE” until door is completely closed. - Fold back the lower lever in its recess. - Depress handle or the upper lever and fold it back in its recess. - Make sure blue light is ON (door locked in closed position) selector has returned to neutral position and green light is OFF. All the lights of the operating panel may be tested by depressing them. As long as the cargo door is not closed and all hooks engaged, the “CARGO UNLK” light illuminates amber on the cockpit overhead panel. MANUAL OPERATING In case of electrical actuator failure, it is possible to open or close the cargo door with a hand crank, introduced in an adjusted shaft drive of the actuator. FORWARD AVIONICS COMPARTMENT ACCESS HATCH An inward opening manually operated hatch in forward section of the nose landing gear bay gives external access to the avionics compartment behind the main instrument panel. COCKPIT COMMUNICATION HATCH A machined door with a net opening of 17.5 cm (7”) wide and 15 cm (6”) high is located immediately below the CAPT side window. Mod: 5948 1.00.30 AIRCRAFT GENERAL P5 001 DOORS APR 11 AA EMERGENCY EXITS COCKPIT One plug type hatch located in the cockpit roof is provided as an emergency exit for the flight crew. One escape rope is located in a compartment on top of the electric rack near the exit. Some steps are provided for hatch access in the corridor RH side. CABIN In addition to the doors already described, two plug emergency type III exits are provided. Note : All emergency exits are operable from inside or outside of the cabin. Mod: 5948 1.00.30 AIRCRAFT GENERAL P6 DOORS 001 APR 11 AA 30.2 CONTROLS DOORS PANEL (1) Doors Alert lights The light illuminates amber and the FWS is activated by the MFC when associated door is not seen locked (one or more micro switches in unlocked position). CARGO, FWD COMPT, and EMER doors only are monitored through the MFC. Door name amber labels are displayed on the SD cabin page when the associated door is detected unclosed. (2) Test Pb Enables to test the microswitches system on cabin door and service door. This test has to be performed on ground, doors open. (3) OK lights The lights illuminate when depressing test button on ground, only if cabin and service doors are open and if associated microswitches are in unlocked position. Mod: 5948 1.00.30 AIRCRAFT GENERAL P7 DOORS 001 APR 11 AA Doors displays on SD CABIN page (MFD) CABIN SIGNS MESSAGES (Cabin seat belt/No device messages status) “NO DVCE” and “SEAT BELT” messages are displayed in cyan on the dedicated area of the Memo Panel display. Mod: 5948 1.00.30 AIRCRAFT GENERAL P8 001 DOORS APR 11 AA 30.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT Doors alert Cargo door actuator Cargo door actuator control DC BUS SUPPLY (C/B) DC BUS 2 (on lateral panel CAUTION) HOT MAIN BAT BUS (on lateral panel ACTR) GND HDLG XFR BUS (on lateral panel CTL) MFC LOGIC See chapter 1.01. SYSTEM MONITORING DOORS This caution is triggered on ground when any door is detected unlocked (except the FWD COMPT door). Visual and aural alert are : - MC light flashing amber - “DOORS” amber message on EWD - Aural alert is single chime - Amber solid rectangle and door name amber label on SD cabin page - associated “UNLK” amber light on overhead panel DOOR FWD COMPT This caution is triggered on ground or in flight when the FWD COMPT door is detected unlocked. Visual and aural alert are : - MC light flashing amber - “DOOR FWD COMPT” amber message on EWD - Aural alert is single chime - Amber solid rectangle and “FWD COMPT” amber label on SD cabin page - associated “UNLK” amber light on overhead panel Mod: 5948 1.00.30 AIRCRAFT GENERAL P9 001 DOORS APR 11 AA DOOR EMER This caution is triggered in flight when the flight compartment overhead hatch is detected unlocked. Visual and aural alert are : - MC light flashing amber - “DOOR EMER” amber message on EWD - Aural alert is single chime - “EMER” amber label on SD cabin page - associated “UNLK” amber light on overhead panel DOOR LH AFT This caution is triggered in flight when the passenger/crew door is detected unlocked. Visual and aural alert are : - MC light flashing amber - “DOOR LH AFT” amber message on EWD - Aural alert is single chime - “CABIN” amber label on SD cabin page - associated “UNLK” amber light on overhead panel DOOR RH AFT This caution is triggered in flight when the service door is detected unlocked. Visual and aural alert are : - MC light flashing amber - “DOOR RH AFT” amber message on EWD - Aural alert is single chime - “SVCE” amber label on SD cabin page - associated “UNLK” amber light on overhead panel DOOR LH FWD This caution is triggered in flight when the left cargo door is detected unlocked. Visual and aural alert are : - MC light flashing amber - “DOOR LH FWD” amber message on EWD - Aural alert is single chime - “CARGO” amber label on SD cabin page - associated “UNLK” amber light on overhead panel Mod: 5948 . 1.00.40 AIRCRAFT GENERAL P1 LIGHTING 001 APR 11 AA 40.1 DESCRIPTION For aircraft lighting, different systems are installed : - controlled from the cockpit S cockpit lighting S cabin signs lighting S emergency lighting S exterior lighting - controlled from the cabin attendant panel S cabin lighting S emergency lighting S rear cargo compartment - controlled from cargo door operating panel S FWD cargo compartment COCKPIT LIGHTING The cockpit is provided with Main Instrument Panel, Overhead panel, consoles lighting. All lights installed in the cockpit are of LED type (Light Emitting Diodes). For illumination of work surfaces and side consoles, spot lights and flood lights are installed. The intensity of all instruments and panels lighting can be adjusted. A STORM function is fitted in order to increase the lighting intensity of the central panel led lights in case of stormy conditions. As soon as DC EMER BUS is powered, Left Main Instrument Panel light located below the glareshield, and one light on the overhead panel directed to the pedestal illuminate. The general cockpit illumination is obtained from two dimmable DOME lights. CABIN SIGNS LITHTING “FASTEN SEAT BELTS” cabin signs “RETURN TO SEAT” sign in the toilet and/or “NO SMOKING” cabin signs may be selected. They will be accompanied by a single chime in the cabin. CABIN AND CARGO LIGHTING The passenger compartment, galley area and entrance door area are lighted by strip lights. In addition, a separated lighting is installed into the rear cargo compartment and is operated from the cabin crew panel. The forward cargo compartment is fitted with an automatic lighting activated by the door opening. A switch located at the left side of the cockpit entrance provides cockpit lighting and emergency EXIT lights illumination for 2 min. Mod: 5948 1.00.40 AIRCRAFT GENERAL P2 LIGHTING 001 APR 11 AA EXTERIOR LIGHTING 1 2 3 4 5 6 7 Navigation lights Regulatory lights are installed on the wing tip (coverage 110°) and on the rear tail cone (coverage 140°). Taxi and to ligths Two lights are installed side by side on the nose landing gear leg. Landing lights Two landing lights are installed laterally in the forward main landing gear fairing bay. Wing lights Two lights are installed one on each side of the fuselage and are positionned to illuminate the wing leading edges and the engine air intakes in order to allow preventive checking in icing conditions. Beacon lights Two beacon lights are installed : one on the top of the vertical stabilizer and one on the bottom of the center fuselage. Strobe lights These lights are installed in each wing tip and in the tail cone. They flash white and are used as supplemental recognition light. Logo lights (optional) Two lights are installed one on each side of the lower surface of the horizontal stabilizer to illuminate the company logo on both sides of the vertical stabilizer. Mod: 5948 1.00.40 AIRCRAFT GENERAL P3 001 LIGHTING APR 11 AA EMERGENCY LIGHTING Emergency evacuation path marking near the floor is a photoluminescent system. EXIT, CEILING and EXTERIOR emergency lights are supplied with 6V DC. Two sources are available : - DC STBY BUS via a voltage divider. - 6V integral batteries charged from the DC STBY BUS with a 10 mn capacity. In case of system activation, light will be supplied by DC STBY BUS. If this source fails, the battreries will be utilized automatically. In case of flight with DC EMER BUS only, the cockpit ligthing is restricted to : - RH DOME light with the possibility to switch it off - Left Main Instrument Panel (MIP) located below the glareshield - overhead panel light illuminating the pedestal. One light is provided in the toilet, illuminating when associated door is locked. Note : Emergency flash lights are provided (see 1.07). Mod: 5948 1.00.40 AIRCRAFT GENERAL P4 LIGHTING 001 APR 11 AA 40.2 CONTROLS EXT LIGHT PANEL 1 2 3 4 5 6 7 BEACON sw BEACON OFF NAV sw NAV Both lights flash Lights are extinguished The three navigation lights illuminate steady. Ice evidence probe is enlightened. STROBE sw STROBE Stroboscopic lights flash white OFF Lights are extinguished LOGO sw LOGO Both LOGO lights illuminate steady OFF Lights are extinguished WING sw WING Both lights illuminate steady OFF Lights are extinguished L and R LAND sw Each landing light (L and R) is controlled by an individual switch LAND Associated light illuminates steady OFF Associated light is extinguished TAXI & T.O. sw taxi Both TAXI lights illuminate steady OFF Lights are extinguished MIN CAB LT SWITCH Enables to control the minimum cabin lights powered by the main battery. On the RH side of the cabin only, every second light is illuminated. Mod: 5948 1.00.40 AIRCRAFT GENERAL P5 LIGHTING 001 APR 11 AA SIGNS PANEL 1 NO SMOKING sw NO SMKG Associated signs come on in the cabin, associated with a single chime. “NO SMOKING” label is displayed in cyan on the memo panel display OFF Associated signs and memo panel label are extinguished. 2 SEAT BELTS sw SEAT BELTS “FASTEN SEAT BELTS” signs in the cabin and “RETURN TO SEAT” sign in the toilet come on associated with a single chime upon illumination. “SEAT BELTS” label is displayed in cyan on the memo panel display. OFF Associated signs and memo panel label are extinguished. Note : When switching off “NO SMOKING” or “SEAT BELTS” signs, single chime sounds in cabin. EMER EXIT LIGHT selector ON Emergency lights illuminate. ARM Normal selector position in operation. Emergency lights will : - Illuminate if DC STBY BUS voltage is under 18V or if the two generators are lost. - Extinguish if DC STBY BUS voltage is over 20V and at least one generator running. DISARM Normal selector position with engines stopped. Emergency light system is deactivated. Note : Cabin attendant’s EMER LIGHT sw will override the ARM and DISARM positions of the selector. DISARM light Illuminates amber when the emergency light system is deactivated. 3 4 Mod: 5948 1.00.40 AIRCRAFT GENERAL P6 LIGHTING 001 APR 11 AA MEMO PANEL DISPLAY Labels (”NO DVCE” or “SEAT BELT”) are displayed in cyan when associated switch is selected ON. LT PANEL MIP/PED rotary knob Selects activation and intensity of main instrument panel and pedestal integral lighting. OVHD rotary selector Selects activation and intensity of the overhead panel integral lighting. LT and RCDR PANEL FLOOD knob Selects activation and intensity of pedestal panel flood lighting. Mod: 5948 1.00.40 AIRCRAFT GENERAL P7 LIGHTING 001 APR 11 AA ANN LT PANEL 1 ANN LT sw Allows to check and to control the intensity of : - the annunciator lights on the overhead panel, main instrument panel and pedestal panels - the overhead panel flow bars. TEST : All the associated lights are tested and illuminate BRT : Associated lights, when selected, illuminate at normal brightness DIM : Associated lights, when selected, are dimmed. Mod: 5948 1.00.40 AIRCRAFT GENERAL P8 001 LIGHTING AA APR 11 SIDE PANEL 1 2 CONSOLE LT knob CONSOLE The light above the associated lateral console is ON. OFF Light is extinguished. READING LT knob Selects activation and intensity of the respective spot light. FLT COMPT LT PANEL 1 2 3 DOME sw BRT Dome lights are lighted at maximum intensity DIM Dome lights are dimmed OFF Both dome lights are OFF STBY COMPASS sw STBY COMPASSIntegral lighting of standby compass comes ON OFF Lighting is OFF STORM sw STORM A lighting increase of the Central MIP light and the Lateral MIP light to intense bightness OFF Central and Lateral MIP lights are at normal brightness. Mod: 5948 1.00.40 AIRCRAFT GENERAL P9 LIGHTING 001 APR 11 AA CABIN CREW PANEL 1 2 3 4 5 6 7 8 9 10 Galley sw (when installed) Controls galley lighting. LAV sw Controls lavatory lighting. A diffuser switches ON when lavatory latch is closed. LAT PASS sw Controls lateral passengers lighting. CEILING LT sw Controls the passengers ceiling lighting. ENTRANCE sw Controls entrance lighting. AFT CARGO sw Controls rear cargo lighting. READING LT sw When depressed passenger reading lights are operational. VENT sw (when installed) When depressed, passenger ventilation fan operates. EMER LT sw Controls emergency exit light and evacuation path marking causing emergency lights to illuminate (overriding crew switching). DIM LT sw Associated light, when selected, are dimmed. Mod: 5948 1.00.40 AIRCRAFT GENERAL P 10 LIGHTING 001 APR 11 AA 40.3 ELECTRICAL SUPPLY/MFC LOGIC ELECTRICAL SUPPLY EQUIPMENT EXTERIOR Beacon lights Navigation lights Wing lights Logo lights (when installed) Landing lights Taxi and Take off ligths Strobe ligths SIGNS Seat belts - No smoking Emergency exit lights Service plugs COCKPIT Capt normal light F/O normal light Emergency light Inst panel normal Inst panel emergency lighting Mod: 5948 DC BUS SUPPLY (C/B) DC SVCE BUS (on lateral panel NORM) . DC BUS 1 (on lateral panel ALTN) . DC SVCE BUS (on lateral panel NORM) . DC BUS 19 (on lateral panel ALTN) . DC BUS 2 (on lateral panel WING) . DC SVCE BUS (on lateral panel LOGO) . DC SVCE BUS (on lateral panel LOGO) - Nil - . DC BUS 2 (on lateral panel LOGO) - Nil - . DC BUS 2 (on lateral panel SEAT BELT NO SMOKING) DC STBY BUS (on lateral panel STBY EXIT LIGHT) . DC STBY BUS (on lateral panel 28VDC) DC BUS 1 (on lateral panel NORM) DC BUS 2 (on lateral panel EMER) DC EMER BUS (on lateral panel EMER) - Nil - Nil - AC BUS SUPPLY (C/B) - Nil - - Nil - - Nil - - Nil . ACW BUS 1 (on lateral panel) . ACW BUS 2 (on lateral panel) . ACW BUS 2 (on lateral panel TAXI and TO) . ACW BUS 1 (on lateral panel L and RCPR) . ACW BUS 2 (on lateral panel R) .-- Nil - Nil ACW SVCE BUS (on lateral panel 115RAC) - Nil - Nil - Nil ACW BUS 1 (on lateral panel NORM SPLY) AC STBY BUS (on lateral panel EMER SPLY) 1.00.40 AIRCRAFT GENERAL P 11 001 LIGHTING APR 11 AA EQUIPMENT Inst panel normal ligthting control Annunciator light test COMPARTMENT Forward and aft cargo Wheels and aft elec compt. PASSENGER Lateral left MIN cab light Lateral light Upper Reading light Lavatory light MFC LOGIC See capter 1.01. Mod: 5948 DC BUS SUPPLY (C/B) DC BUS 2 (on lateral panel NORM INST PNL SPLY CTL) . DC BUS 1 (on lateral panel ANN LT TEST) AC BUS SUPPLY (C/B) - Nil - . DC SVCE BUS (on lateral panel FWD and AFT CARGO) . DC SVCE BUS (on lateral panel WHEEL and AFT ELEC) - Nil - DC BUS 1 (on lateral panel DC BUS 1) DC ESS BUS (on lateral panel) . DC BUS 2 (on lateral panel DC BUS 2 . DC SVCE BUS (on lateral panel DC SVCE BUS) . DC UTLY BUS 1 (on lateral panel) . DC UTLY BUS 2 (on lateral panel) - Nil - - Nil - . DC SVCE BUS (on lateral panel LAV LT) - Nil - - Nil - - Nil - Nil - - Nil - . ACW BUS 1 (on lateral panel L) . ACW BUS 2 (on lateral panel R) - Nil - . 1.00.50 AIRCRAFT GENERAL P1 001 WATER AND WASTE SYSTEM APR 11 AA 50.1 DESCRIPTION For the toilet, the aircraft is equipped with a clean water system and a waste disposal system which provides adequate waste capability. It is drainable by gravity. Clean water is stored in a tank located in the pressurized section of the fuselage. The toilet flushing is obtained from a motorized pump filter unit. The flushing cycle is automatically controlled by an electrical timer. Draining, flushing and charging of the tank is accomplished at the toilet service panel, located underneath the rear fuselage. 50.2 ELECTRICAL SUPPLY EQUIPMENT Lavatory flush motor Mod: 5948 DC BUS SUPPLY AC BUS SUPPLY DC SVCE BUS (on lateral panel FLUSH MOTOR) - Nil - . 1.01.00 INTEGRATED SYSTEMS P1 CONTENTS AA 1.01.00 CONTENTS 1.01.10 10.1 10.2 10.3 INTEGRATED MODULAR AVIONICS (IMA) DESCRIPTION SCHEMATIC ELECTRICAL SUPPLY/SYSTEM MONITORING 1.01.20 20.1 20.2 20.3 20.4 20.5 20.6 MULTIFUNCTION COMPUTER (MFC) DESCRIPTION CONTROLS OPERATION ELECTRICAL SUPPLY/SYSTEM MONITORING MAINTENANCE APPLICATION SCHEMATICS 1.01.30 30.1 30.2 30.3 MULTIPURPOSE COMPUTER (MPC) DESCRIPTION SCHEMATIC ELECTRICAL SUPPLY/SYSTEM MONITORING R 1.01.35 1.01.40 Mod: 5948 MPC LOST EQUIPMENT LIST CPM/IOM LOST EQUIPMENT LIST 001 FEB 12 . 1.01.10 INTEGRATED SYSTEMS P1 INTEGRATED MODULAR AVIONICS 001 APR 11 AA 10.1 DESCRIPTION The Integrated Modular Avionic (IMA) provides computation, memory and Input/Output data processing resources, shared between several avionics applications. The Integrated Modular Avionic is mainly composed of the dual Core Avionic Cabinets (CAC 1& 2). The term CAC (Core Avionic Cabinet) designs the whole equipment composed of the rack and the set of cards. In the basic configuration, each CAC is composed of : - 1 CPM (Core Processing Module) - The CPMs provide shared memory and computation resources to execute hosted avionics applications. - 1 IOM-- S (Input/Output Module) This IO Module is dedicated to provide ARINC and discrete I/O for all functions - 1 IOM-- AP (Input/Output Module) This IO Module is dedicated to provide discrete and analog I/O for the Auto-- Flight application. - 2 IOM-- DC (Input/Output Module) The IOM-- DC provide discrete and analog I/O for Data Concentration Application (DCA) . - 1 SWM (gateway and SWitch Module) This module is dedicated to connect together CPM and other Avionics Data Network subscribers. The communication means is based on AFDX network, linking network subscribers through SWM. Mod: 5948 1.01.10 INTEGRATED SYSTEMS P2 INTEGRATED MODULAR AVIONICS 001 APR 11 AA The main applications hosted by the Core Avionic Cabinets are : - Flight Warning (FWA) - Auto-- Flight (AFCA) - Centralized Maintenance (CMA) (only on CAC 1) - Data Concentration (DCA) The CAC 1 & 2, communicate with five display units and systems by means of different data bus formats : - AFDX: Avionics Full DupleX switched ethernet - A429: ARINC 429 - Analogic - Discretes Two of the five displays units (DU2 and DU4) are dedicated to two other functions : - Flight Management Application (FMA) - Radio Management Application (RMA) (Refer to section 1.01.40 to see the lost equipment list in case of CPM and/or IOM failure). 10.2 SCHEMATIC Mod: 5948 1.01.10 INTEGRATED SYSTEMS P3 001 INTEGRATED MODULAR AVIONICS APR 11 AA 10.3 ELECTRICAL SUPPLY/SYSTEM MONITORING ELECTRICAL SUPPLY The CPM, IOM-- AP&-- DC, IOM-- S and SWM cards are connected to the 28VDC aircraft electrical network. The power supply details are shown in the table below : CAC CAC 1 CAC 2 Mod: 5948 CAC CARD DC BUS SUPPLY (C/B) CPM 1 & IOM-- S 1 DC EMER BUS (Upper Panel CPM 1 / IOM-- S 1) IOM - AP 11 DC EMER BUS (Upper Panel FGCP CHAN 1 / IOM-- AP 1) IOM - DC 12 DC STBY BUS (Upper Panel IOM-- DC 12) IOM - DC 13 DC STBY BUS (Upper Panel IOM-- DC 13) SWM 1 DC EMER BUS (Upper Panel SWM 1) CPM 2 & IOM-- S 2 DC ESS BUS SEC1 (Upper Panel CPM 2 / IOM-- S 2) IOM - AP 21 DC ESS BUS SEC1 (Upper Panel FGCP CHAN 2 / IOM-- AP 2) IOM - DC 22 DC ESS BUS SEC2 (Upper Panel IOM-- DC 22) IOM - DC 23 DC ESS BUS SEC2 (Upper Panel IOM-- DC 23) SWM 2 DC ESS BUS SEC1 (Upper Panel SWM 2) 1.01.10 INTEGRATED SYSTEMS P4 INTEGRATED MODULAR AVIONICS 001 APR 11 AA SYSTEM MONITORING CAC 1(2) This caution is generated in case of a CPM failure on one CAC. Visual and aural alerts are : - MC light flashing amber - “CPM 1(2)” amber message on EWD - Aural alert is Single Chime (SC) CPM 1 (2) + IOM 2x (1x) This caution is generated in case of a CPM failure on one CAC and a IOM-- DC failure on the other CAC. All combinations of one CAC/CPM and other CAC/IOM - DC are possible : Visual and aural alerts are : - MC light flashing amber - “CPM 1 (2) + IOM 2x (1x)” amber message on EWD - Aural alert is Single Chime (SC) IOM 1x (2x) This caution is generated in case of one IOM-- DC failure on one CAC. Visual and aural alerts are : - MC light flashing amber - “IOM 1x (2x)” amber message on EWD - Aural alert is Single Chime (SC) IOM 1x (2x) + IOM 1x (2x) This caution is generated in case of dual of IOM-- DC. All combinations of one or two CAC are possible : Visual and aural alerts are : - MC light flashing amber - “IOM 1x (2x) + IOM 1x (2x)” amber message on EWD - Aural alert is Single Chime (SC) SWITCH SGL CH This caution is generated in case of one SWM loss. Visual and aural alerts are : - MC light flashing amber - “SWITCH SGL CH” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 1.01.20 INTEGRATED SYSTEMS P1 MULTIFUNCTION COMPUTER 001 APR 11 AA 20.1 DESCRIPTION (See schematics p 15/16) On the ATR72, numerous logic functions are performed by the MFC system. It consists of two independent computers (MFC 1 and MFC 2). Each computer includes two independent modules (A and B). Each module includes : - a 28 VDC dual power supply - an input/output circuit. - a computation unit. - for modules 1A and 2A only, a hard-- wired logic independent of the computation unit. SIGNAL PROCESSING Each module receives signals from the various systems and systems controls. Each signal received by a module is then converted, if necessary, to a digital signal by the input circuit. Then : - for most of the functions, the signal is sent to the computation unit which processes the data according to the logic programmes. - for some specific functions (stick pusher, flaps), signal processing is performed in a conventional way by the hard-- wired card (to avoid computation errors or common failures). An intercard dialogue is established between all modules to allow each module to use signals processed by other modules. Signals from each system are taken into account by one or more modules depending on the degree of reliability/safety required for the system. Each module is equipped with a self test system which monitor correct operation of that module. FUNCTIONS After processing, computation unit transmits orders from the output circuit fo the various systems in order to : - monitor, control and authorize operation of the aircraft systems. - manage system failures and flight enveloppe anomalies and command triggering of associated warnings in the Flight Warning System (FWS). Mod: 5948 1.01.20 INTEGRATED SYSTEMS P2 MULTIFUNCTION COMPUTER 001 APR 11 AA 20.2 CONTROLS CONTROL PANEL Controls operation of associated module. ON : (pushbutton pressed in) the module operates. OFF : (pushbutton released) the module stops operating. the OFF white indicator light comes on. FAULT : The amber light comes on and the FWS is activated when a malfunction or electrical supply fault is detected. The module automatically becomes inoperative. This light also flashes during self-- test of the module. During powering, since all four modules are selected ON, the following sequence is executed : MFC 1A and MFC 2A FAULT lights (self-- test of these modules) flashing. MFC 1A and MFC 2A FAULT lights extinguish. MFC 1B and MFC 2B FAULT lights (self-- test of these modules) flashing. MFC 1B and MFC 2B FAULT lights extinguish. Note : If the cargo door control panel is opened, the self test of MFC 1A and 2A are already done, and only the MFC 1B and 2B are tested. Mod: 5948 1.01.20 INTEGRATED SYSTEMS P3 001 MULTIFUNCTION COMPUTER APR 11 AA 20.3 OPERATION Charts on the following pages list the implementation and availability of the functions ensured by each module. READING OF TABLES The table uses the following symbols : F, , to indicate : - location of the functions : A function is integrated in each module denoted by one of these symbols : - availability of the functions : A function can be treated : - in one module only, - in several modules (redundancy), - partially in two modules, i.e. both modules considered are to be operative to process this function. Example : SYSTEM FUNCTION FLIGHT STICK PUSHER CONTROLS STALL WARNING 1A MODULE 1B 2A 2B F F - The stick pusher function is integrated in modules 1A, 1B, 2A and 2B. - The stall warning function is integrated in modules 1B and 2B. - The stick pusher function is available if modules (1A AND 2A) OR (1A AND 2B) OR (1B AND 2A) OR (1B AND 2B) operate. This function is therefore not available if modules (1A AND 1B) OR (2A AND 2B) are lost. - The stall warning is available if module 1B OR 2B operate. This function is therefore not available if modules 1B AND 2B are lost Mod: 5948 1.01.20 INTEGRATED SYSTEMS P4 MULTIFUNCTION COMPUTER AA Mod: 5948 001 APR 11 1.01.20 INTEGRATED SYSTEMS P5 MULTIFUNCTION COMPUTER AA R Mod: 5948 001 FEB 12 1.01.20 INTEGRATED SYSTEMS P6 MULTIFUNCTION COMPUTER AA Mod: 5948 001 APR 11 1.01.20 INTEGRATED SYSTEMS P7 MULTIFUNCTION COMPUTER AA Mod: 5948 001 APR 11 1.01.20 INTEGRATED SYSTEMS P8 MULTIFUNCTION COMPUTER AA R Mod: 5948 001 FEB 12 1.01.20 INTEGRATED SYSTEMS P9 MULTIFUNCTION COMPUTER 001 APR 11 AA 20.4 ELECTRICAL SUPPLY/SYSTEM MONITORING ELECTRICAL SUPPLY Each module is supplied by two separate electrical sources (primary and alternate). Power supply switching is automatic : - from primary to alternate if primary V < 19V and if alternate V > 22V. - from alternate to primary if primary V >22V. UNIT MFC 1A Primary Supply Alternate Supply MFC 1B Primary Supply Alternate Supply MFC 2A Primary Supply Alternate Supply MFC 2B Primary Supply Alternate Supply DC BUS SUPPLY (C/B) DC ESS BUS (Upper Panel PRIM SPLY) HOT EMER BAT BUS (Upper Panel ALTN SPLY) DC BUS 1 (Upper Panel PRIM SPLY) DC EMER BUS (Upper Panel ALTN SPLY) DC EMER BUS (Upper Panel PRIM SPLY) HOT MAIN BAT BUS (Upper Panel ALTN SPLY) DC BUS 2 (Upper Panel PRIM SPLY) DC EMER BUS (Upper Panel ALTN SPLY) SYSTEM MONITORING MFC 1(2) A (B) These cautions are generated when MFC module(s) are detected failed. Visual and aural alerts are : - MC light flashing amber - “MFC 1(2) A(B)” amber message on EWD - Aural alert is Single Chime (SC) - FAULT light illuminates on the overhead panel Mod: 5948 1.01.20 INTEGRATED SYSTEMS P 10 001 MULTIFUNCTION COMPUTER APR 11 AA 20.5 MAINTENANCE LATERAL MAINTENANCE PANEL Recording of the failures is performed by the MFC 1A module. (1) ”BITE LOADED” Magnetic indicator Indicates that a failure has been recorded by the maintenance system. (2) TEST pb Used to check operation the the BITE LOADED magnetic indicator. When pressed for more than 3s. the magnetic indicator is activated. (3) ERS pb When depressed for at least 5s, the maintenance magnetic indicator is erased. This procedure also erases the MFC maintenance memory thus it has to be performed at the end of the maintenance task. (4) CONNECTOR OUTLET Enables the optional MTS (Maintenance Test Set) system to be connected. Mod: 5948 1.01.20 INTEGRATED SYSTEMS P 11/12 MULTIFUNCTION COMPUTER 001 APR 11 AA MCDU During a maintenance operation on the ground, MFC fault codes can be displayed by means of “MPC” menu on MCDU. In the “MPC” menu, select “MAINTENANCE” sub-- menu then “MFC” : - The “BASIC MEMORY” gives access to the content of the fault codes stored since the last erase (no chronological information). - The “FLIGHT FAULT” memory gives access to the fault codes which occured during the 9 previous flights. Note : To erase the maintenance memory, select “MAINT MEMORY ERASING” menu via MFC menu to erase basic memory and/or the flight memory. To erase the maintenance magnetic indicator, press “ERS” PB on the lateral maintenance panel. Mod: 5948 . 1.01.20 MFC P 13 GENERAL AA 20.6 SCHEMATICS Mod: 5948 001 APR 11 . 1.01.30 INTEGRATED SYSTEMS P1 MULTIPURPOSE COMPUTER 001 APR 11 AA 30.1 DESCRIPTION The MPC unit is including two parts : - Flight Data Acquisition Unit (FDAU) - Data Management Unit (DMU) A) FDAU Part The MPC acquires data in digital, analog or discrete format from aircraft systems for various FDAU functions : - Flight Data Recording (SSFDR) (refer to chapter Flight Instruments). - Aircraft Performance Monitoring (APM) (Refer to chapter Ice and Rain Protection). - Data broadcast to CAC (to avionics system). - Time management. - Flight time management. - Flight number management. - Configuration management (A/C type, A/C ident, APM version). B) DMU Part The MPC has the capability to manage ACMS functions (Aircraft Condition Monitoring System) in order to : - facilitate the maintenance of the aircraft. - record data for the Flight Data Monitoring purpose (FDM) The main possible ACMS functions are : - QAR/DAR recording on a PCMCIA disk (QAR when the data frame is the FDR one/ DAR when it is reprogrammed by a ground support equipment) - >FDM purpose - Management of reports (take-- off, cruise ...) - > FDM purpose - Dialogue with the following aircraft equipments: MCDU, Printer, ACARS (optional) - Other maintenance functions. Mod: 5948 1.01.30 INTEGRATED SYSTEMS P2 MULTIPURPOSE COMPUTER AA 30.2 SCHEMATIC Mod: 5948 001 APR 11 1.01.30 INTEGRATED SYSTEMS P3 MULTIPURPOSE COMPUTER 001 APR 11 AA 30.3 ELECTRICAL SUPPLY/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) MPC (in flight) DC ESS BUS (SECT 1) (on lateral panel FLT DATA RCDR / FDAU DFDR / FLT SPLY) MPC (on ground) DC EMER BUS (on lateral panel FLT DATA RCDR / FDAU DFDR / GND SPLY) SYSTEM MONITORING See on dedicated chapter (flight instrument for recording and ice & rain protection for APM) Mod: 5948 . 1.01.35 INTEGRATED SYSTEMS P1 MPC LOST EQUIPMENT LIST 001 FEB 12 AA MPC LOST EQUIPMENT LIST IMPORTANT NOTE on the DU indications: SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Local alerts on the overhead panel are functional. MPC Maintenance Access (Via MCDU) FDAU Function DFDR Indications lost: AC STBY BUS on electrical system page EMER BUS on electrical system page ESS BUS on electrical system page APM fault NL Flight time on EWD Mod: 5948 . 1.01.40 INTEGRATED SYSTEMS P1 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA CPM / IOM LOST EQUIPMENT LISTS IMPORTANT NOTE on the DU indications: SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Note: Local alerts on the overhead panel are functional. CPM 1 AP&YD R TLU Auto DE-- ICING Mode Sel Auto Prop 1 Anti Icing Left Turbo Fan CPM 2 AP&YD R TLU Auto DE-- ICING Mode Sel Auto Prop 2 Anti Icing Right Turbo Fan Mod: 5948 1.01.40 INTEGRATED SYSTEMS P2 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA CPM / IOM LOST EQUIPMENT LISTS (CONT’D) IMPORTANT NOTE:SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Note: Local alerts on the overhead panel are functional. CPM 1 + 2 AP&YD FD R SPD TGT : AUTO/MAN All speeds computed by the FMS lost (on ground: V1, VR, V2 ; in flight: VmLB0, VmHB NORMAL, VMHB ICING SPEED BUGS, VminOPS, VPROT, VMIN SPEED BANDS) R TLU Auto mode APM Messages DE-- ICING Mode Sel Auto Prop 1 Anti Icing Prop 2 Anti Icing FWS VOR 2 (VOR / ILS 1 available on IESI only) ADF 1 / ADF 2 NAV 1 NAV 2 Weather Radar T2CAS and TCAS display TAWS XPDR Enhanced Surveillance RA DH/MDA AUTO PRESS Inhibition of Distributor Valve Heating Left Turbo Fan Right Turbo Fan Mod: 5948 1.01.40 INTEGRATED SYSTEMS P 3/4 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA CPM / IOM LOST EQUIPMENT LISTS (CONT’D) IMPORTANT NOTE: SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Note: Local alerts on the overhead panel are functional. IOM DC12 PROP 1 Anti Icing R ANTI/DE-- ICING Mode Sel Auto IOM DC13 R ANTI/DE-- ICING Mode Sel Auto Left Turbo Fan R TLU Auto mode IOM DC22 PROP 2 Anti Icing R ANTI/DE-- ICING Mode Sel Auto IOM DC23 Right Turbo Fan R ANTI/DE-- ICING Mode Sel Auto R TLU Auto mode Mod: 5948 . 1.01.40 INTEGRATED SYSTEMS P 5/6 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA IMPORTANT NOTE for DU indicatings: For all of the following lost equipment list (IOM DC’s), SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Note: Local alerts on the overhead panel are functional. CPM1 IOM DC 22 VminOPS R TLU Auto mode Continuing next page Mod: 5948 . 1.01.40 INTEGRATED SYSTEMS P 7/8 CPM / IOM LOST EQUIPMENT LIST AA CPM1 IOM DC 22 - CONT’D Mod: 5948 001 FEB 12 . 1.01.40 INTEGRATED SYSTEMS P 9/10 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA IMPORTANT NOTE for DU indicatings: For all of the following lost equipment list (IOM DC’s), SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Note: Local alerts on the overhead panel are functional. CPM1 IOM DC 23 R MODE Continuing next page Mod: 5948 . 1.01.40 INTEGRATED SYSTEMS P11/12 CPM / IOM LOST EQUIPMENT LIST AA CPM1 IOM DC 23 - CONT’D Mod: 5948 001 APR 11 . 1.01.40 INTEGRATED SYSTEMS p 13/14 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA IMPORTANT NOTE for DU indicatings: For all of the following lost equipment list (IOM DC’s), SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Note: Local alerts on the overhead panel are functional. CPM2 IOM DC 12 R TLU Auto mode Continuing next page Mod: 5948 . 1.01.40 INTEGRATED SYSTEMS P 15/16 CPM / IOM LOST EQUIPMENT LIST AA CPM2 IOM DC 12 - CONT’D Mod: 5948 001 APR 11 . 1.01.40 INTEGRATED SYSTEMS P 17/18 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA IMPORTANT NOTE for DU indicatings: For all of the following lost equipment list (IOM DC’s), SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Note: Local alerts on the overhead panel are functional. CPM2 IOM DC 13 R MODE VminOPS Continuing next page Mod: 5948 . 1.01.40 INTEGRATED SYSTEMS P 19/20 CPM / IOM LOST EQUIPMENT LIST AA CPM2 IOM DC 13 - CONT’D Mod: 5948 001 APR 11 . 1.01.40 INTEGRATED SYSTEMS P21/22 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA IMPORTANT NOTE for DU indicatings: For all of the following lost equipment list (IOM DC’s), SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. . Note: Local alerts on the overhead panel are functional. IOM DC12 IOM DC13 EQT LOSS FWS PROCEDURES FWS CAUTIONS ON EWD AND ASSOCIATED MASTER CAUTION AND AURAL ALERTS (AMBERONBLACK BACKGROUND) WHEN THE A/C IS CLEAR OF ICE NO ENG ITT ENG EXCESS ITT ENG OVER LIMIT ENG 1 OVER LIM FUEL 1 TEMP HI FUEL 1 TEMP LO ENG 1 OIL TEMP LO ENG 1 OIL TEMP HI ENG 1 OIL TEMP OVHT TLU auto mode R DE-- ICING MODE SEL AUTO PROP 1 ANTI-- ICING LEFT TURBO FAN Mod: 5948 FWS CAUTIONS ON EWD FWS WARNINGS ON EWD AND ASSOCIATED MW AND CRC (REDONBLACK BACKGROUND) ENG 1 OIL PRESS * * ONLY IN CASE OF ANALOG DETECTION AND NOT DISCRETE DETECTION FWS WARNINGS ON EWD . 1.01.40 INTEGRATED SYSTEMS P23/24 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA R IMPORTANT NOTE for DU indicatings: For all of the following lost equipment list (IOM DC’s), SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Note: Local alerts on the overhead panel are functional. IOM DC12 IOM DC22 & FLAPS UNLK Mod: 5948 . 1.01.40 INTEGRATED SYSTEMS P25/26 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA IMPORTANT NOTE for DU indicatings: For all of the following lost equipment list (IOM DC’s), SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Local alerts on the overhead panel are functional. IOM DC12 IOM DC23 PANEL R TLU auto mode Mod: 5948 . 1.01.40 INTEGRATED SYSTEMS P27/28 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA IMPORTANT NOTE for DU indicatings: For all of the following lost equipment list (IOM DC’s), SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Local alerts on the overhead panel are functional. IOM DC13 IOM DC22 VminOPS R TLU auto mode Continuing next page Mod: 5948 . 1.01.40 INTEGRATED SYSTEMS P29/30 CPM / IOM LOST EQUIPMENT LIST AA IOM DC13 IOM DC22 - CONT’D Mod: 5948 001 APR 11 . 1.01.40 INTEGRATED SYSTEMS P31/32 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA IMPORTANT NOTE for DU indicatings: For all of the following lost equipment list (IOM DC’s), SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Note: Local alerts on the overhead panel are functional. IOM DC13 IOM DC23 R TLU Auto mode Mod: 5948 . 1.01.40 INTEGRATED SYSTEMS P 33 CPM / IOM LOST EQUIPMENT LIST 001 FEB 12 AA IMPORTANT NOTE for DU indicatings: For all of the following lost equipment list (IOM DC’s), SOME INDICATIONS and MONITORINGS are lost on DUs ; refer to the overhead panel. Note: Local alerts on the overhead panel are functional. IOM DC22 IOM DC23 R TLU Auto mode Mod: 5948 . 1.02.00 FLIGHT WARNING SYSTEM P1 CONTENTS 001 FEB 12 AA 1.02.00 CONTENTS 1.02.10 GENERAL 10.1 DESCRIPTION 10.2 CONTROLS 10.3 OPERATION 10.4 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 10.5 LATERAL MAINTENANCE PANEL R Mod: 5948 10.6 FWS MANAGEMENT and ELECTRONIC CHECK-- LISTS (if applicable) . 1.02.10 FLIGHT WARNING SYSTEM P 1/2 GENERAL 001 APR 11 AA 10.1 DESCRIPTION The Flight Warning System (FWS) gives to the crew an operational aid for management of normal and abnormal configurations of the aircraft systems. The FWS performs the following functions : - in case of detected alert, it draws crew’s attention through visual and aural attention getters, - in case of detected alert, it guides the crew to the system or subsystem concerned by activating an alert message, - it helps the crew to set the A/C in T.O. configuration, - it inhibits some alerts at T.O., - it allows the crew to carry out normal procedures (checklist), - it enables the crew to carry out abnormal and emergency procedures, - it allows the crew to know limitations and/or remaining actions, - it helps the crew identifying system action status required during procedure processing by displaying the relevant system page on the SD. The display area dedicated to the FWS is located on the lower part of the EWD. It is composed of three parts : - an Alerting Window on the left part - a Procedure Window on the right part - a status area dedicated to FWS information on the bottom part of the procedure window. IMPORTANT NOTE The chapter 1.02 Flight Warning System is written for the standard production version of the ATR72- 212A Modification 5948 also called ATR72- 600. On the initial production version (L2B1) the automatic procedure system will not be operative. All the Alerts, Master waning and Master cautions and alarms are operative, but in case of detected failure the automatic procedure display in the procedure window will not be operational. The crew members will have to deal with the failure on the conventional way as on the ATR72- 212A, using the QRH (Quick Reference Handbook). Mod: 5948 . 1.02.10 FLIGHT WARNING SYSTEM P 3/4 GENERAL 001 APR 11 AA ARCHITECTURE The FWS is composed of : - two modules, on each Multi Function Computer (MFC 1B and 2B) - two CPM (Core Processing Module), one on each Core Avionic Cabinet (CAC). - two IOM-- S, one on each CAC. - four IOM-- DC, two on each CAC. - two SWM, one on each CAC . - a display format dedicated to the FWS : EWD is displayed on normal configuration on the center Display Unit (DU3). - two EFIS Control Panels (EFCP); - two Master Warning pushbuttons (MW), one for each crew member; - two Master Caution pushbuttons (MC), one for each crew member; - a T.O. configuration test pushbutton; - an emergency audio cancel guarded toggle switch; - a maintenance panel to test some warnings (red) that cannot be tested at system level The FWS is managed by the FWA function of the CAC (Flight Warning Application) Mod: 5948 . 1.02.10 FLIGHT WARNING SYSTEM P5 GENERAL AA 001 APR 11 BASIC PRINCIPLES The following two principles have been adopted : - “All fligth deck lights out” concept In normal operation all the ligths are extinguished (except sometimes green or cyan light for transient phases). - Detection sequence The detection sequence comprises three different phases. PHASE FUNCTION MEANS OF DETECTION 1 2 3 DETECTION IDENTIFICATION ISOLATION AURAL ALERT + MW or MC ALERT MESSAGE IN THE ALERTING WINDOW SYSTEM CONTROL AND INDICATING PANEL ALERT LEVELS The alerts are classified in 4 levels according to their importance and to the urgency of the corrective action required. LEVEL 3 : WARNINGS This corresponds to an emergency situation requiring crew prompt corrective action. The following alerts fall into this category : - aircraft in hazardous configuration or limiting flight conditions (e.g. stall warning) - serious system failure (e.g. engine fire) These warnings are identified by : S The MW light flashing red associated with a continuous repetitive chime (CRC) and a red warning message displayed in the alerting window. S a specific aural warning. LEVEL 2 : CAUTIONS This corresponds to an abnormal situation of the aircraft requiring timely crew corrective action. Time for taking action will be left to crew’s discretion. This level mainly comprises system failures having no immediate impact on safety (e.g. engine overheat). The cautions are identified by the MC light flashing amber associated with a single chime (SC) and an amber message displayed in the alerting window. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P6 GENERAL AA 001 APR 11 LEVEL 1 : ADVISORIES This corresponds to a situation requiring crew monitoring. This level mainly comprises failures leading to a loss of redundancy or degradation of a system. These advisories are identified by an amber caution message displayed in the alerting window without aural alert. LEVEL 0 : INFORMATION This corresponds to an information situation action (eg. DME hold). This information is provided by cyan, green or white display on the control display. This level is not taken into account by the FWS. Therefore, there is no associated display in the alerting window nor on the procedure window. COLOR CODING INDICATION COLOR INTERPRETATION WARNING RED Configuration or failure requiring immediate action. CAUTION AMBER Configuration not requiring immediate action. Left to crew’s discretion GREEN Normal operation CYAN Normal transient configuration WHITE Control position indication. Neutralized abnormal configuration. INDICATION ALERT INHIBITION In order to avoid alerts during critical take off phase, inhibition follows the conditions below : - ENG oil, smoke warnings and some caution alerts are automatically inhibited before take off. Associated aural alerts are also inhibited. These inhibitions will be cancelled : S automatically as soon as one gear leg is not locked down, S by pressing RCL pb. - An emergency audio cancel sw allows the crew to cancel a nuisance aural for a whole flight (except for LDG GEAR, VMO, VFE, VLE, Stall Warning, Whooler, AP Disconnect). Associated aural will be reactivated : S at next aircraft energization, S after MFC 1B/2B reset, S after pressing RCL pb, S after T.O. Config test. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P7 GENERAL AA 001 APR 11 AURALS Two types of aurals alerts are used to alert the crew : - Non specific alert always associated with an alert message displayed in the alerting window : - A continuous repetitive chime (CRC) associated with Master Warning (MW) lights and red warning message displayed in the alerting window. - A single chime (SC) associated with Master Caution and amber caution message displayed in the alerting window. - Specific aurals for alerts not associated with the illumination of the Master Warning lights, or the Master Caution lights nor with an alert message displayed in the alerting window : S stall (cricket) S overspeed : VMO,VFE, VLE (clacker) (warnings) S AP disconnect (cavalry charge) S Trim in motion (whooler) S altitude alert (” c chord”) S calls (door bell) (cautions) S AP capability downgrading (3 click) Note : A priority order has been defined for aurals in case of simultaneous occurence of warnings : - Stall (cricket) - Nac OVHT (CRC) - Overspeed (clacker) - Excess cab ∆ P (CRC) - Flaps unlocked (CRC) - Trim in motion (whooler) - Config(CRC) - Smoke detection(CRC) - Propeller brake failure (CRC) - Oil low press (CRC) - Engine fire (CRC) - Landing gear not down (CRC) - Pitch Disconnect (CRC) - AP disconnection(cavalry charge) - Excess cabin altitude (CRC) LOCAL ALERTS All the local alerts on the control and indicating panels on the overhead panel, on the instrument panel, or on display units, are activated by the systems. The local alerts are then independent from the FWS that only takes these local alerts into account to draw crew’s attention and has no possible action on them. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P8 GENERAL 001 APR 11 AA 10.2 CONTROLS EFIS CONTRL PANEL The control panel for FWS management is composed of two EFCPs (1) PROC MENU pb Enables to display the “Procedure Menu” in the procedure window. (2) MAN DEL pb Enables to delete manually inserted procedures. (3) CLR pb Enables to clear the clearable alert messages and procedures displayed in the alerting window and in the procedure window. (4) RCL pb - A first press enables to display (in the alerting window) the alert messages previously cleared but still detected. - A second press scrolls down the alert messages list in case of overflow in the alerting window. (5)(6) n / o pbs Enables to move on upward (respectivly downward) line boxing in the procedure window. (7) V pb Enables to validate (boxed item) an action or to activate a boxed procedure or status. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P9 GENERAL 001 APR 11 AA MW/MC LIGHT (1) MASTER WARNING light Flashes red when a warning is generated with associated red label and procedures displayed on the EWD. When depressed, light will extinguish and associated aural warning will be cancelled. (2) MASTER CAUTION light Flashes amber when a caution is generated with associated amber label and procedures displayed on EWD. When depressed, light will extinguish. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 10 GENERAL AA 001 APR 11 CONTROL PANEL (1) TO CONFIG TEST pb Used before take-- off : - to check if aircraft configuration is correct for take-- off by simulating power levers at TO position (except PRK BRK ON) : - to perform an automatic RECALL (thus reactivating all aural warnings previously cancelled by Emer Audio/Cancel). When pressed, status messages are displayed on EWD. See description the table below Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 11 GENERAL 001 APR 11 AA (2) EMER AUDIO CANCEL sw Is safety wired. In case of false alert generated and undue continuous alert, EMER AUDIO CANCEL sw will allow cancelation of this unwanted aural alert. Example : If the SW is used to cancel a system X failure CRC, CRC is not cancelled for the systems other than system X. Cancelled aural warning will be reactivated : - at next aircraft enegization (MFC reset) - after MFC 1B/2B reset - after pressing RCL pb - following T.O. Config test Except for aural warning associated with : - landing gear (landing configuration) - VMO, VFE, VLE - Stall warning - Pitch trim whooler - AP Disconnect Which will be rearmed as soon as the triggering condition disappears. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 12 GENERAL 001 APR 11 AA PROCEDURE PRINCIPLES WITHOUT AIRCRAFT SYSTEM FAILURE - On the right side of the alerting window, the procedure window enables the crew to manage procedures. - Procedure window is blank when no checklist is detected by the FWS.. - When activating the ”PROCEDURE MENU” through EFCP, ”NO ACTIVE PROCEDURE” is displayed in the PROCEDURE MENU. The ”LIST” menu is displayed below. - Any procedure can be called from the “LIST” menu - During take off, some alert messages are not displayed and attention getters are not activated. When the power levers are in the take off position, the “CONFIG” warning is activated if parking brake is applied and the amber “PRKG BRK ON” message is displayed on EWD. On landing gear retraction, “TO INHIB” indication goes off and all alert messages detected but inhibited during T.O. are displayed. The inhibition at T.O. can also be manually deactivated by pressing the “RCL”pb. - Before approach when “RCL” pb is pressed, no alert message is displayed in the alerting window if no failure occured in flight. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 13 GENERAL AA 001 APR 11 WITH AIRCRAFT SYSTEM FAILURE SINGLE FAILURE DETECTION When a failure is detected, the associated alert message is displayed in the alerting window. If a procedure is associated to the detected failure, it is simultaneously displayed in the Procedure Window replacing the “PROCEDURE MENU”. The alert message remains displayed as long as the failure is detected. Alert message and Procedure can be cleared by pressing the “CLR” if it corresponds to a level 2 failure (caution message). Color Coding - Cyan items correspond to actions to be performed or choices to be made by the crew. - Amber items correspond to abnormal procedure titles, recommendations and statuses titles (even statuses deduced from emergency procedures). - Red color corresponds to emergency procedures titles and strong recommendations. - White color is used for subtitles items without associated action to be performed like notes, normal procedures titles and items associated to validated actions. “PENDING” list Displayed in the “PROCEDURE MENU” above the ”LIST” menu. It lists the titles of all the active procedures and statuses. Pressing ’RCL’ enables to display the PROCEDURE MENU and to access the active procedures and statuses through the ”PENDING” list. The entire procedure must be then taken up again as item previously validated are not memorized. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 14 GENERAL 001 APR 11 AA Status Some procedures can lead to a status. In this case, when the procedure is performed and validated, the FWS replaces the procedure by the associated status. Status titles are displayed in the ”PENDING” list between brackets. Manually inserted procedure Any normal, abnormal and emergency procedures available in the ”LIST” sub-- menu can be called. Manually called procedures are displayed in the ”PENDING” list with the ”MAN” message at the right end of the line only if at least one item has been acknowledged. MULTIPLE FAILURES DETECTION All procedures associated to alert message have the same priority level as the alert message. Level 3 alerts ( Master Warning) have priority over any Level 2 (Master Caution) or normal procedures. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 15 GENERAL 001 APR 11 AA 10.3 OPERATION NORMAL OPERATION WITHOUT AIRCRAFT SYSTEM FAILURE After engines start : No alert light illuminated in the cockpit except “PRKG BRK ON” amber message displayed on EWD if the parking brake is set. Before take off : Press TO CONFIG TEST - if aircraft is in correct configuration, no light will illuminate. - if aircraft is not in correct configuration : - MW light will flash red, - CRC aural will be generated - CONFIG red message on EWD associated with : S FLT CTL when: S Flaps are not in the TO configuration S Pitch trim is not in the TO configuration (out of the green sector) S Travel Limiter Unit (TLU) is not set to TO position (TO position - - > LO SPD) S Aileron lock disagreement (AIL LOCK light illuminated) S PWR MGT when: - Power Management not in T.O. position Before starting descent : Press RCL on EFCP. No messages displayed on EWD provided no failure occured in flight. OVERSPEED ALERT When the aircraft is in overspeed conditions, (VMO, VFE, VLE), a specific aural alert is generated which will persist until return into the following flight envelope is performed. ALERTS Flaps 0° Flaps 15° Flaps 30° Mod: 5948 for VFE (alert at VFE - 5kt) 180 kt 145 kt VLE (alert VLE - 5kt) VMO 180 kt 250 kt 150 kt 1.02.10 FLIGHT WARNING SYSTEM P 16 001 GENERAL APR 11 AA STALL ALERT To generate this alert (cricket and stick shaker), aircraft is fitted with two angle of attack probes, one on each side of the forward fuselage. Angle of attack probe information is directly processed by the FWS. Critical angle of attack detected by angle of attack probes leads to aural alert (cricket), stick shaker activation, and then stick pusher activation. In normal conditions, stick shaker and stick pusher triggering thresholds are elaborated by adding a ”nα” value to angles of attack corresponding to the basic protections. nα depends on engine 1 & 2 torques and flaps configuration. Engine 1 torque signal is processed by MFC 1A and engine 2 torque signal is processed by MFC 2A. So, two nα are computed, but only the larger one is considered. The monitoring system uses: - a microswitch signal on PL handles - both EECs - the four MFC modules The failure of one of these elements invalids the associated nα. If a nα is invalidated, the system takes into account the other one. If both nα are invalidated, system choses nα = 0. Note : System operation goes unnoticed for the crew. AIRCRAFT CRITICAL ANGLE OF ATTACK ALERT and STICK SHAKER ACTIVATION FLAPS 0° FLAPS 15° HIGH POWER 10.9° LOW POWER 10.9° Mod: 5948 STICK PUSHER ACTIVATION FLAPS 30° FLAPS 0° FLAPS 15° FLAPS 30° 10.9° 9.9° 13.4° 14.1° 12.8° 10.9° 10.4° 13.4° 14.1° 14.3° 1.02.10 FLIGHT WARNING SYSTEM P 17 001 GENERAL APR 11 AA Whenever “ICING AOA” is illuminated, the aircraft is protected by an earlier stall threshold as follows : AIRCRAFT CRITICAL ANGLE OF ATTACK ALERT and STICK SHAKER ACTIVATION FLAPS 0° FLAPS 15° TAKE OFF 8.0° 8.4° EN ROUTE 8.0° 8.4° STICK PUSHER ACTIVATION FLAPS 30° 7.7° FLAPS 0° FLAPS 15° 10.6° 10.9° 10.6° 10.9° FLAPS 30° 10.8° Notes - EN ROUTE values occurs, when 10 mn have elapsed if take off was performed flaps 15 or immediately if take off not performed flaps 15 (ferry flight for instance) - Stall alarm alert and shaker are inhibited when aircraft is on the ground - Stick pusher activation is inhibited : • on ground • during 10 seconds after lift off • in flight, provided radio altimeter is operative, when the aircraft descends below 500 ft. - If radio altimeter gives an erroneous ”< 500 ft” signal meanwhile IAS > 185 kt for more than 120 seconds (cruise), STICK PUSHER FAULT amber light will come on to notify the crew that stick pusher is inhibited. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 18 GENERAL 001 APR 11 AA WITH AIRCRAFT SYSTEM FAILURE LEVEL 3 LEVEL 2 Failure detection - aural alert : CRC - aural alert : SC - MW light flashing red - MC light flashing amber - red warning message on EWD - amber caution message on EWD identifying the failure identifying the failure - for all cases, a red light on the - local alert light on the affected system affected system control panel and/or on control panel and/or SD system page SD system page Acknowledgement of the failure by the crew - Press MW light - Press MC light S MW light extinguishes S MC light extinguishes S aural alert is cancelled Corrective action S lf the failure disappears, associated local alert light extinguishes, EWD message disappears. S If the failure does not disappear, associated local alert light remain illuminated, EWD message remain displayed. Press CLR on EFCP (after Procedure application) EWD message does not disappears EWD message disappears Before starting descent, press RCL on EFCPEWD messages, associated with systems where a failure persists, or, with a white light illuminated on the associated control panel will be displayed. Take into account the failure consequences for the landing. Press CLR on EFCP (after Procedure application). Caution alert messages will disappear. Note : The local alert lights always reflect directly the system status : they are never inhibited or cleared by any other mean than restoring normal functioning. When a local alert light disappears, the other alert sequence elements (MW/MC Iight, EWD messages, aurals) also disappear. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 19 GENERAL 001 APR 11 AA OPERATION WITH MFC’s FAILURE In case of MFC 1B and 2B failure : - MC illuminates without flashing - MFC amber message displayed on EWD - MFC 1B and 2B amber FAULT lights illuminate on overhead panel In these conditions, processing of alerts is as follows : - All level 2 alerts and “CONFIG” + “ENG OIL” + “PROP BRK” level 3 alerts are not processed. The crew has to monitor the overhead panel where the local alerts are still active. - All other level 3 alerts are processed on EWD (without MW and CRC). If both FWA are detected failed, the ”FWA not available” message is displayed on a blank black page on the Procedure Window. No alert message is displayed anymore and the crew has to monitor the instrument panels where the local alerts are still active. For failures detected by MFC, attention getters MC and SC or MW and CRC are still activated. Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 20 GENERAL 001 APR 11 AA 10.4 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT MFC 1B Primary supply Alternate supply MFC 2B Primary supply Alternate supply MFC LOGIC See chapter 1.01. Mod: 5948 DC BUS SUPPLY (CB) DC BUS 1 (Upper panel 1B PRIM SPLY) DC EMER BUS (Upper panel 1B ALTN SPLY) DC BUS 2 (Upper panel 2B PRIM SPLY) DC EMER BUS (Upper panel 2B ALTN SPLY) 1.02.10 FLIGHT WARNING SYSTEM P 21 GENERAL 001 APR 11 AA SYSTEM MONITORING FWS NOT AVAIL This message is displayed amber on the EWD when : - both AFDX switches are reported faulty (SWM 1 and 2 fault). The message is displayed on a blank black page on the lower part of the EWD. Alerts are no more displayed and the crew has to monitor the overhead panel. Attention getters MC and SC or MW and CRC are still activated. - both CPM are reported faulty (CPM 1 and 2 fault). The message is displayed on a blank black page on the lower part of the EWD. Alerts are no more computed and the crew has to monitor the overhead panel. For failures detected by MFC, attention getters MC and SC or MW and CRC are still activated. - both FWA are detected failed (FWA 1 and 2 fault). The message is displayed on a blank black page on the lower part of the EWD. Alerts are no more computed and the crew has to monitor the overhead panel. For failures detected by MFC, attention getters MC and SC or MW and CRC are still activated. Note : The crew is then headed toward the corresponding procedure to apply (see Procedure page below) Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 22 GENERAL 001 APR 11 AA CPM 1(2) This caution is generated when one of the CPM is detected faulty. Visual and aural alerts are : - MC light flashing amber - “CPM 1(2)” amber message on EWD - Aural alert is Single Chime (SC) Note : When backup FWA becomes primary, due to opposite FWA or CPM failure, the ”PROCEDURE PENDING” white message is displayed centered in the procedure window. Pressing the ’PROC MENU’ PB enables the crew to display the PROCEDURE MENU. FWS SGL CH This caution is generated when one of the FWA is detected faulty. Visual and aural alerts are : - MC light flashing amber - “FWS SGL CH” amber message on EWD - Aural alert is Single Chime (SC) MFC 1B + 2B This caution is generated when MFC modules 1B and 2B are detected failed. Visual and aural alerts are : - MC light flashing amber - “MFC 1B + 2B” amber message on EWD - Aural alert is Single Chime (SC) - FAULT light illuminates on the overhead panel Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 23 001 GENERAL APR 11 AA 10.5 LATERAL MAINTENANCE PANEL On LH maintenance panel, a “WARN” section allows testing, on ground, of several warnings which cannot be tested on their own system. This section includes : - a rotary selector to select the system to be tested ; - a Push To Test (PTT) pushbutton to activate the selected test. Note : The rotary selector must be replaced in NORM FLT position before flight. (1) “CHAN” lights Illuminates green to check the two angle of attack channels for correct operation. (2) ROTARY selector System which can be tested : - EXCESS CAB ∆P : MW, CRC, “EXCESS CAB ∆P” red message on EWD - LDG GEAR NOT DOWN : MW, CRC, “LDG GEAR NOT DOWN” red message on EWD, red light in landing gear lever. - PITCH DISCONNECT : MW, CRC, “PITCH DISCONNECT” red message on EWD. - EXCESS CAB ALT : MW, CRC, “EXCESS CAB ALT” red message on EWD; - SMK : MW, CRC, “FWD SMK”, “AFT SMK”, and “ELEC SMK” red message on EWD. - VMO: clacker Mod: 5948 1.02.10 FLIGHT WARNING SYSTEM P 24 001 GENERAL APR 11 - STICK PUSHER SHAKER - YES : S Stall cricket and both stick shakers are activated S After 5 seconds, “GPWS” amber alert message is displayed on EWD S After 10 seconds : - CHAN 1, CHAN 2 illluminate - Stick pusher is activated - Stick pusher indicators illuminate green S Select WARN rotary selector to NORM FLT S Monitor : - STICK PUSHER lights OFF - C/B 14 FU FLT CTL / STICK PUSHER / PWR SUPPLY in. - STICK PUSHER SHAKER - TEST 1 : S Stall cricket and left stick shaker are activated S After 5 seconds : - “GPWS” amber alert message is displayed on EWD - MC, “FLT CTL” amber message displayed on EWD and stick pusher FAULT pb illuminate amber - STICK PUSHER SHAKER - TEST 2 : S Stall cricket and right stick shaker are activated S After 5 seconds : - “GPWS” amber alert message is displayed on EWD - MC, “FLT CTL” amber message displayed on EWD and stick pusher FAULT pb illuminate amber - STICK PUSHER SHAKER - TEST 3 : S CHAN 1, CHAN 2 illuminate S Stall cricket and both stick shakers are activated S After 5 seconds, “GPWS” amber alert message is displayed on EWD Note : If ICING AOA is illuminated : - YES procedure is the same. - Test 1 procedure is the same except that CHAN 1, CHAN2 illuminate - Test 2 procedure is the same except that CHAN 1, CHAN 2 illuminate - Test 3 procedure is the same except that stick pusher is activated in the same time as shakers. (3) “PTT” pb After having selected a system with the rotary selector, the PTT pb allow to activate the test. As soon as a test is initiated, “MAIN PNL” amber message will be displayed on EWD. Mod: 5948 1.03.00 AIR P1 CONTENTS 001 APR 11 AA 1.03.00 CONTENTS 1.03.10 GENERAL 1.03.20 PNEUMATIC SYSTEM 20.1 DESCRIPTION 20.2 CONTROLS 20.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 20.4 LATERAL MAINTENANCE PANEL 20.5 SCHEMATIC 1.03.30 AIR CONDITIONING 30.1 DESCRIPTION 30.2 CONTROLS AND INDICATING 30.3 SD CABIN PAGE 30.4 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 30.5 SCHEMATIC 1.03.40 PRESSURIZATION 40.1 DESCRIPTION 40.2 CONTROLS 40.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 40.4 SCHEMATICS Mod: 5948 . 1.03.10 AIR P1 GENERAL 001 APR 11 AA The aircraft uses external air to supply : - the air conditioning and the ventilation systems - the pressurization system - the de-- icing system Air inlets location : - engines air intakes - main landing gear fairings - low pressure ground unit through a connector The air intended for air conditioning and pressurization is pressurized by engines compressors and delivered through the bleed valves. It is conditioned by the packs, distributed to the pressurized zones then discharged overboard through two outflow valves. A part of this air is recirculated. Electrical and electronic equipments and the forward cargo compartment are ventilated by cabin ambient air which is then recirculated or discharged outside the aircraft. The de-- icing system is described in the chapter 1.13. The MFC provides the system monitoring and failures information to crew members. Mod: 5948 . 1.03.20 AIR P1 PNEUMATIC SYSTEM 20.1 DESCRIPTION 001 APR 11 (See schematic p.10/11) Compressed air is bled from the engine compressors at the LP or HP stages. The pneumatic system consists of all the systems designed to supply air to the various aircraft systems, zones or engines, with associated control, monitoring and indicating components. It supplies under pressure air for air conditioning, pressurization and ice protection system. A protection against overheat due to possible leakage around the hot air ducts is provided. AIR BLEED - Air conditioning and pressurization The system is designed to : ¯ select the compressor stage from which air is bled, depending on the pressure and/or temperature existing at these stages. ¯ regulate air pressure in order to avoid excessive pressures. Air is generally bled from the low compressor stage (LP). At low engine speed when pressure from LP stage is insufficient, air source is automatically switched to the high compressor stage HP. (This may occur on ground and during descent at F.I.). Transfer of air is achieved by means of a pneumatically operated and electrically controlled butterfly valve, (HP valve) which remains closed in absence of electrical supply : ¯ when the HP valve is closed, air is directly bled from the LP stage through LP bleed air check valves. ¯ when the HP valve is open, the HP air pressure is admitted into the LP pneumatic ducting and closes the check valves ; air is therefore bled from HP stage only, without any recirculation into the engine. - Wing and engine de-- icing. Air is bled from the HP compressor stage. Transfer of air is achieved through a pressure regulating valve which is electrically controlled. ISOLATION Downstream of the junction of the LP and HP ducting, air is admitted into the duct by a pneumatically operated, electrically controlled butterfly bleed valve which acts as a shut off valve. It includes a single solenoid which locks the valve closed when deenergized. The bleed valve automatically closes in the following cases : - Bleed duct OVHT - Bleed duct LEAK - Actuation of associated ENG FIRE handle - Engine failure at TO (UPTRIM signal) In the absence of air pressure, the valve is spring-- loaded closed regardless of electrical power supply. Note : During a starting sequence, the bleed valves opening is inhibited. Mod: 5948 1.03.20 AIR P2 PNEUMATIC SYSTEM 001 APR 11 AA CROSSFEED The crossfeed valve installed on the crossfeed duct is designed to connect LH and RH air bleed systems. - On the ground, it opens only when air is supplied from the RH engine oprating in hotel mode. - In flight, the crossfeed valve is normally closed. This is a spring loaded closed, solenoid controlled, pneumatic shut off valve. The valve is closed with solenoid deenergized. LEAK DETECTION SYSTEM A continuous monitoring system is installed in order to detect overheat due to duct leakage and to protect the structure and components in the vicinity of hot air ducts: - Wing leading edge and wing to fuselage fairing. - Upper and lower fuselage floor, - Air conditioning pack area. In order to ensure rapid leak sensing, a Kevlar envelope is installed around the major part of the high temperature ducts to collect and direct leaking air to the sensing elements. The sensing system includes two single loop detection assemblies, one for the RH and one for the LH air duct systems. The sensing elements comprise a control lead (nickel wire) embedded in an insulating material and are integrated in an inconel tube connected to aircraft ground. Each sensing element is permanently subjected to the temperature of the compartment it protects. For any temperature higher than a preset value : 153_C (307_F) applied to a part of the sensing element, the resistance of the eutectic mixture rapidly decreases and the central lead is grounded. This results in an alert signal processed in a control unit which triggers illumination of LEAK light on overhead panel, and leak on the cabin SD page. After one second time delay, the associated pack valve, HP valve and BLEED valve (and GRD X FEED valve if the left loop is affected) are automatically latched closed. Note : In case of LEAK, the crew must consider the associated bleed system as inoperative for the rest of the flight. Mod: 5948 A 1.03.20 AIR P3 PNEUMATIC SYSTEM 001 APR 11 OVERHEAT CONTROL SYSTEM This system includes switches (thermal resistances) which are installed downsteam of the bleed valve. These switches, which are duplicated for safety, ensure that the HP bleed valve and the bleed air shut-- off valve are closed whenever any abnormal over temperature conditions occur. They operate at 274_C (525_F) and are controlled by the MFC. In case of OVHT, the associated bleed system may be recovered after a cooling time. OVERPRESSURE CONTROL SYSTEM The pressure switch is fitted on the bleed air duct upstream the bleed air shut-- off valve. When air bleed pressure > 80 psi, overpressure switch sends a signals to the MFC which closes the bleed air shut off valves. FAULT light illuminates on the corresponding air bleed push button. HP BLEED AIR THERMAL PROTECTION When this thermal sensor detects a tempetrature > 270°C on HP port, the HP bleed valve is closed and the MFC bite loaded magnetic indicator (located on maintenance panel) turn amber. Mod: 5948 A 1.03.20 AIR P4 PNEUMATIC SYSTEM 001 FEB 12 20.2 CONTROLS AND INDICATING AIR BLEED PANEL R (1) ENG BLEED pbs Controls the associated HP valve and BLEED valve. ON (pb pressed in) associated HP and bleed valves solenoids are energized. The valves will open if pressure is available. OFF (pb released) associated HP and bleed valves are closed. OFF light illuminates white. Caution “AIR BLEED 1(2)” is displayed on EWD. FAULT The light illuminates amber and a specific caution message from the FWS is displayed on EWD associated with a Caution and a Single Chime when the bleed valve position disagrees with the selected position (case of OVHT, Overpressure or LEAK). (2) OVHT light The light illuminates amber and the caution message “OVHT” from the FWS is displayed on EWD associated with a caution light and a Single Chime when either of the respective bleed duct dual overheat sw operates (T > 274 ºC/525 ºF). (3) LEAK light The light comes on amber and the caution message “LEAK” from the FWS is displayed on EWD associated with a caution light and a Single Chime when respective bleed leak detection system signal an alert (T loop > 153 ºC/307ºF). (4) X VALVE OPEN light The light illuminates amber when the GRD X FEED valve is open. This occurs on ground when the air is bled from right engine running in hotel mode (propeller brake switched on) or during taxiing with one engine running. Mod: 5948 1.03.20 AIR P5 PNEUMATIC SYSTEM 001 FEB 12 AA CABIN SD PAGE . R (1) ENGINE BLEED symbol - Green engine bleed : ON status, FULLY status, FULL OPERATIVE, NO FAULT reported - White engine bleed : OFF status, NO FAULT reported - Amber engine bleed : The engine bleed is reported faulty either because a fault directly impacts the system or another fault is detected and impacts the engine bleed air system (duct bleed leak, engine off, etc...). (2) BLEED CROSSFEED pipe - Green : air is flowing in the pipe - Grey : no air is flowing inside the pipe but the bleed crossfeed valve operation is reported faulty - Not shown : No air flows inside the pipe and the bleed crossfeed valve operates properly. Mod : 5948 1.03.20 AIR P6 PNEUMATIC SYSTEM 001 FEB 12 AA (3) BLEED CROSSFEED valve - Green : the bleed crossfeed valve operates properly and is fully open (the valve open position corresponds to the valve command) - Amber : the valve reported position does not correspond to the valve command. R (Refer to System Monitoring chapter : 1.03.20 p007_001 ) - Not shown : the valve operates properly and is fully closed as required. (4) OVHT Amber “OVHT” displayed besides the affected engine bleed. (Refer to System Monitoring chapter : 1.03.20 p007_001) R (5) LEAK Amber “LEAK” displayed besides the engine bleed on the relevant side. R (Refer to System Monitoring chapter : 1.03.20 p007_001) Mod: 5948 1.03.20 AIR P7 001 PNEUMATIC SYSTEM APR 11 AA 20.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT ENG 1 HP valve Bleed valve Fault and OVHT alert light DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) DC BUS 1 (on lateral panel ENG 1 BLEED/SO VALVES/HP) - NIL - DC ESS BUS (on lateral panel ENG 1 BLEED/SO VALVES/BLEED) - NIL - DC ESS BUS (on lateral panel ENG 1 BLEED/CAUTION) - NIL - ENG 2 HP valve Bleed valve DC BUS 2 (on lateral panel ENG 2 BLEED/SO VALVES/HP - ENG2 BLEED/SO VALVES/BLEED) - NIL - DC ESS BUS (on lateral panel) - NIL - DC ESS BUS (on lateral panel ENG 2 BLEED/CAUTION) - NIL - Crossfeed valve and associated OPEN light DC BUS 1 (on lateral panel XFEED) - NIL - LEAK Bleed leak detection system - NIL - Fault and OVHT alert light CROSSFEED LEAK lights MFC LOGIC See chapter 1.01. Mod :5948 DC BUS 1 (on lateral panel ENG 1&2 / BLEED LEAK / CAUTION) 115 VAC BUS 1 (on lateral panel ENG 1&2 / BLEED LEAK DET) - NIL - 1.03.20 AIR P8 PNEUMATIC SYSTEM 001 APR 11 AA SYSTEM MONITORING - AIR BLEED 1(2) This alert is triggered when there is a desagreement between the bleed valve position and command, due to a system failure or another fault which impacts the engine bleed air system (overpressure, engine off, etc...). Visual and aural alerts are : - MC light flashing amber - “AIR BLEED 1(2)” amber message on EWD - Aural alert is Single Chime (SC) - Bleed FAULT on overhead panel - AIR BLEED 1(2) OVHT This alert is triggered when one of the two over-- temperature switches is subjected to a temperature of 274 ºC (525 ºF) or higher. Visual and aural alerts are : - MC light flashing amber - “AIR BLEED 1(2) OVHT” amber message on EWD - Aural alert is Single Chime (SC) - Amber “OVHT” displayed besides the affected engine bleed on SD cabin page - OVHT light illumination on the overthead panel - Bleed FAULT on overhead panel - AIR LEAK 1(2) This alert is triggered when a bleed leak is detected. Note that the leak may be detected from the engine bleed source down to the pack and the bleed crossfeed valve. Visual and aural alerts are : - MC light flashing amber - “AIR LEAK 1(2)” amber message on EWD - Aural alert is Single Chime (SC) - Amber “LEAK” displayed besides the engine bleed on the relevant side on SD cabin page - LEAK light illumination on the overthead panel - Bleed FAULT on overhead panel - AIR X VALVE This alert is triggered when the valve reported position does not correspond to the valve command. Therefore the valve is either failed open or failed closed (amber open or amber closed). Visual and aural alert are : - MC light flashing amber - “AIR X VALVE” amber message on EWD - Aural alert is Single Chime (SC) - X VALVE OPEN on the overhead panel (only in open position) Mod :5948 1.03.20 AIR P 9/10 PNEUMATIC SYSTEM 001 APR 11 AA 20.4 LATERAL MAINTENANCE PANEL (1) BITE LOADED magnetic indicator Indicates that a failure - “LH or RH HP valve position disagrees with the closed selected position” - has been recorded by the maintenance system that happened when the HP bleed air thermal sensor detects a temperature > 270°C. (2) AIR BLEED LEAK Push To Test button Used to check the functionning of both ambient overheat detection circuits along the bleed air ducts. Both bleed leak detection loops are tested simultaneously. When depressed, both “LEAK” lights illuminate (test is successfull) on the overhead panel and on the SD cabin page. Mod: 5948 . 1.03.20 AIR P 11 PNEUMATIC SYSTEM AA 20.5 SCHEMATIC Mod :5948 001 APR 11 . 1.03.30 AIR P1 AIR CONDITIONING 001 APR 11 AA 30.1 DESCRIPTION AIR PRODUCTION The air conditioning system is supplied by air processed through two packs which regulate air flow and temperature as required. The two packs are installed in the main landing gear fairings and operate automatically and independently. The left pack supplies the cabin and cocpkit with conditionned air, the right pack supplies only the cabin. Note : If one pack is inoperative, the other one supplies both compartments through the mixing chamber. Hot air from the engines is admitted through pack valves and conditioned (cooled, dried, compressed) into the packs. The pack valve is pneumatically operated and electrically controlled. This butterfly valve has two functions : - Pack shut off - Pressure control and hence flow control. Normal or high flow are available. The selection of the high flow mode increases the pack entrance pressure resulting in conditioning performance improvement. Without air pressure and regardless of electrical command, the pack valve is spring-- loaded closed. It will also close without electrical supply. Note : Pack valves will be automatically closed in case of leak detection. Air Cooling is performed : - by two ground turbo fans through turbo shut off valves when : S IAS አ 150 kt and landing gear is retracted for less than 10 min. Note : In case of ENG OIL LOW PRESS, the turbo fan starts on the opposite side and is running as long as IAS አ 150 kt and regardless of landing gear position. S IAS አ 150 kt and landing gear is extended. - by ram air when IAS > 150 kt. Note : Incorrect position of a turbo fan shut off valve leads to closure of associated pack valve Mod: 5948 1.03.30 AIR P2 AIR CONDITIONING 001 APR 11 AA AIR VENTILATION Conditioned air is blown into the cabin by outlet ramps located under the overhead bins through two electrical isolating valves (CAB VENT). It is then evacuated through guides along the cabin side walls at floor level. A part of it is recirculated by the fans, the other part being evacuated overboard through the outflow valves installed in the rear under floor. An additional electrical fan is used (through a switch installed on the flight attendant panel) to increase the airflow of each passenger individual outlet. It can be used on ground and during climb, and is inhibited when one pack is OFF. The toilet is ventilated by differential pressure through a vent line. Mod: 5948 1.03.30 AIR P3 AIR CONDITIONING 001 APR 11 AA Flight deck, forward cargo compartment, electric and electronic equipments are ventilated by flow of ambient air which is : - Recirculated (underflow) to the pressurized compartment, or - Ducted overboard. The selection is operated by the overboard (OVBD) valve which controls the underfloor (U/F) valve : - OVBD full closed →U/F open - OVBD partially or full closed →U/F closed - OVBD NORMAL MODE : Automatic selection - OVBD MANUAL MODE : to be used in case of AUTO MODE failure or, on ground, to accelerate cabin heating (Full closed position). Air is extracted by a fan which may operate at different speeds depending on flight deck temperature : Rotation speed is minimum below 20° C (68° F), maximum above 52° C (126° F) and varies linearly between these values. Only when OVBD valve AUTO MODE is selected, EXHAUST mode pb may be used to control OVBD valve in a partially open position. This action is required in case of fan failure to provide cooling air flow by allowing cabin differential pressure. In case of smoke in forward cargo compartment, flight deck air extraction duct can be closed with a lever located on right side maintenance panel in order to avoid contaminated air suction to the flight deck. Mod: 5948 1.03.30 AIR P4 AIR CONDITIONING 001 APR 11 AA TEMPERATURE CONTROL The system is designed to regulate and limit the temperature of the air discharged from the packs which is supplied to the different zones : - FLT COMPT by the left pack - CABIN by the right pack and excess air from the left pack. The pack temperature control valves vary the amount of hot air that is mixed with cool air in order to establish the required temperature. In automatic mode, each pack discharge temperature is controlled by an electronic temperature controller which computes temperature control valve position taking into account : - Duct temperature - Zone temperature demand selector - Associated compartment temperature - Aircraft skin temperature In manual mode, each pack temperature control valve is controlled directly by the zone temperature control selector and limited by the pneumatic temperature sensor OVERHEAT PROTECTION When duct temperature downstream of the mixing chamber increases over T = 88° C (191° F), the limiter closes the temperature control valve progressively by a pneumatic action in order to reduce hot air flow. An OVHT caution is provided to the crew when Tduct > 92° C (200° F) (but the pack valve does not close). In case of overheat downstream of the pack compressor (T > 204° C (399° F) the pack valve closes automatically. Mod: 5948 1.03.30 AIR P5 AIR CONDITIONING 001 APR 11 AA 30.2 CONTROLS AND INDICATING COMPT TEMP PANEL 1 PACK VALVE pb pb pressed in Associated PACK VALVE is open if electrical supply and air pressure are available Note : A 6 seconds delay has been provided on right pack valve for passengers comfort purpose. OFF (pb released) Associated PACK VALVE is closed. The OFF light illuminates white. “AIR PACK” caution is displayed on EWD when one of the pack valve is commanded OFF. “AIR PACK 1+2” caution is displayed on EWD when both pack valves are commanded OFF. FAULT Mod: 5948 Illuminates amber and the caution message “AIR PACK” from the FWS is displayed on EWD associated with a Master Caution and a Single Chime when the PACK VALVE position disagrees with the selected position or in case of overheat downstream of the pack compressor (T>204° C/399° F). In the later case, the valve is latched closed automatically. 1.03.30 AIR P6 AIR CONDITIONING AA 001 APR 11 (2) FLOW pb NORM (pb released) Both pack valves are controlled automatically to give 22 PSI regulated pressure. HIGH (pb pressed in) Both pack valves are controlled to give regulated 30 PSI which increases the flow accordingly. HIGH light illuminates cyan. (3) COMPT TEMP selectors For the related compartment the temperature is either automatically controlled by the electronic controller taking into account the selector position or manually selected by direct operation of the temperature control valve through the selector. (4) TEMP SEL pb Selects the temperature control mode of operation. AUTO : (pb pressed in) Automatic mode is selected. The electronic temperature controller controls the valve position. MAN : (pb released) Manual mode is selected. The COMPT TEMP selector directly controls the position of the valve. The pneumatic temperature limiter will limit the max duct temperature below T = 88°C/190°F. The MAN light illuminates white. OVHT : Illuminates amber and the caution message “AIR DUCT OVHT” from the FWS is displayed on EWD associated with a Master Caution and a Single Chime, when an over temperature is detected in the duct (T > 92°C/198°F). It is not inhibited in MAN mode. (5) RECIRC FAN pb Selects operation of the respective circulation fan. pb pressed in : (pb depressed) Fan runs. Recirculation of a part of the cabin air to supplement the conditioned air supply is provided. Fan rotation speed linearly varies from 12700 RPM to 15600 RPM depending on temperature control valve position. If temperature measured at cabin floor level is lower than 18°C(61°F), high speed is automatically selected. OFF : (pb released) Fan stops. All the air is supplied by the packs whithout recirculation. The OFF light illuminates white. “AIR RECIRC FAN 1(2)” caution is displayed on EWD FAULT : Illuminates amber and the caution message “AIR RECIRC FAN 1(2)” from the FWS is displayed on EWD associated with a Master Caution and a Single Chime, in case of either low fan RPM (< 11400 RPM) or fan electrical motor overheat conditions. (6) COMPT ind. Air temperature in the selected compartment is indicated in °C. (7) DUCT ind. For the selected compartment, the temperature of the conditioned air before leaving the duct is indicated in °C. Duct temperature is automatically limited to max 88°C/190°F in AUTO mode or MAN mode. (8) COMPT selector Selects the zone - FLT COMPT or CABIN - for which temperature (COMPT and DUCT) reading is desired. (9) GND X FEED (See Chapter 1.03.20) Mod: 5948 1.03.30 AIR P7 AIR CONDITIONING 001 FEB 12 AA AVIONICS VENT PANEL R R (1)”OVBD VALVE” selector switch with three positions : - “AUTO” : Automatic operation of the overboard valve. The safety guard in auto position prevents valve opening control when cabin/exterior dP is greater than 1 PSI - “FULL OPEN” : (blue full open indicator on SD cabin page) : Serves to fully open the overboard valve when cabin/exterior nP is equal or lower than 1 PSI - “FULL CLOSED” : (cyan full close indicator on SD cabin page) : Overboard valve closing control (2) EXHAUST MODE pb with two steady positions - PUSHED : (NORMAL CONFIGURATION) involves electrical power supply of extraction fan. On ground, engine 1 not running (OIL LOW PRESS) : - OVBD valve full open (green full open indicator on SD cabin page) - U/F valve closed In flight, or on the ground, engine 1 running : - OVBD valve full closed (green full closed indicator on SD cabin page) - U/F valve open Mod: 5948 1.03.30 AIR P8 AIR CONDITIONING 001 APR 11 AA - RELEASED : (”OVBD” legend ON) involves extraction fan power supply shut off : In flight (normal configuration) : - Opening of overboard ventilation valve in intermediary position (green intermediate position on SD cabin page) - Closing of U/F valve - Activation of following alarms : - Master caution - Single chime - FW caution message “AIR VENT EXH” on EWD - Exhaust ovbd status on SD cabin page On ground : - Opening of overboard ventilation valve in intermediary position (green intermediate position on SD cabin page) - Closing of U/F valve - Activation of mechanic call system if power supply through ground power unit is used - Activation of following alarms : - Master caution & Single chime (if condition levers are in a position other than “FTR” or “FUEL SO”) - FW caution message “AIR VENT EXH” on EWD - Exhaust ovbd status on SD cabin page Note 1 : Aircraft on ground and external power available: if exhaust mode is set on OVBD position, a ground mechanic call is generated and intermediate position is inhibited. Note 2 : When start sequence is initiated, extract fan stops for 120s to avoid pressure shocks. Exhaust mode fault illuminates, however the ground mechanic call is not generated. “FAULT” indication on EXHAUST MODE pb “FAULT” legend comes on when “AVIONICS/VENT/EXHAUST MODE” pb is pushed and when following failures appear : - Rotation speed of air extraction fan is null or insufficient (fan failure or power supply loss) - Excessive internal temperature (fan failure or simultaneous closing of overboard vent valve and underfloor vent valve) At the same time, the following alarms appear : - Master caution & single chime (if conditions levers are in a position other than “FTR” or “FUEL SO”) - EXHAUST VENT status and amber extraction fan indicator on the SD cabin page “FAULT” legend is off when “EXHAUST MODE” pb is released (”OVBD” legend on). Mod: 5948 1.03.30 AIR P 9/10 AIR CONDITIONING 001 APR 11 AA (3) “OVBD VALVE FAULT” caution light : - Comes on amber when position of overboard valve does not correspond to control position. - Related warnings appear simultaneously : - Master Caution - Single chime - FW caution message “AIR OVBD” on EWD - OVBD amber status on SD cabin page. Mod: 5948 . AIR 1.03.30 P 11/12 AIR CONDITIONING 001 APR 11 AA 30.3 SD CABIN PAGE (1) PACK VALVE On the page SD cabin, pack indicators allow to know the pack valve status. Moreover, when high flow is selected on the Comp Temp Panel, a message shows “AIR HIGH FLOW” in cyan. (2) RECIRCULATION FAN - CABIN AIR DISTRIBUTION The SD Cabin page provides information (highlights the faulty elements.) on Recirculaton Fan Status, as well as Cabin Air Distribution Duct indication. (3) CABIN AIR DISTRIBUTION DUCT Depending on the pack valve status and the recirculation fan status, the SD Cabin page provides visual information on cabin air supply. (4)-- (5) VENTILATION : EXTRACTION FAN - OVERBOARD VALVE The SD Cabin page provides information on overboard valve and air extraction fan. (6)-- (7) TEMPERATURE MANAGEMENT - CABIN TEMPERATURE The SD Cabin page provides information about on the cabin temperature and about the temperature management.The right hand indicator provides information from the cabin and the left hand indicator provides information from flight compartment. Mod: 5948 . 1.03.30 AIR P 13 AIR CONDITIONING R 001 FEB 12 AA 30.4 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT LH SIDE Pack valve Recirculation fan DC BUS SUPPLY (C/B) DC ESS BUS (on lateral panel SYS 1/PACK VALVE) DC UTLY BUS 1 (on lateral panel PWR SUPPLY CTL) Pack and recirculation fan alert DC ESS BUS (on lateral panel SYS 1/PACK and RECIRC FAN CAUTION) FLT COMPT automatic temperature control DC ESS BUS (on lateral panel FLT COMPT/TEMP CTL/ AUTO) FLT COMPT manual temperature control DC ESS BUS (on lateral panel FLT COMPT/TEMP CTLMAN) RH SIDE Pack valve Recirculation fan DC ESS BUS (on lateral panel SYS2/PACK VALVE) DC SYS 2/UTLY BUS 2 (on lateral panel PWR SUPPLY CTL) Pack and recirculation fan alert DC ESS BUS (on lateral panel SYS2/PACK and RECIRC FAN CAUTION) Automatic temperature control DC ESS BUS (on lateral panel CABIN/TEMP CTL/AUTO) Manual temperature control DC ESS BUS (on lateral panel CABIN/TEMP CTL/MAN) Compartment and duct temperature ind. DC BUS 1 (on lateral panel COMPT and DUCT TEMP IND) Mod: 5948 1.03.30 AIR P 14 001 AIR CONDITIONING R FEB 12 AA TURBO FAN SHUT OFF VALVE 1 CTL DC BUS 1 (on lateral panel SYST 1/TURBO FAN) TURBO FAN SHUT OFF VALVE 2 CTL DC BUS 2 (on lateral panel SYST 2/TURBO FAN) OVBD valve, U/F valve DC EMER BUS (on lateral panel VALVES) Extract fan control relay DC ESS BUS (on lateral panel CTL) EXTRACT FAN Contactor DC BUS 2 (on lateral panel EXTRACT FAN) EXTRACT FAN Contactor DC BUS 1 (on lateral panel EXTRACT FAN) MFC LOGIC See chapter 1.01 Mod: 5948 1.03.30 AIR P 15 AIR CONDITIONING R 001 FEB 12 AA SYSTEM MONITORING AIR PACK A pack valve fault can be triggered by : - a disagreement between the selected pack valve position and the actual position of the pack valve. - an air temperature dowstream the air machine compressor higher than 204° C (399° F) Visual and aural alert are : - MC light flashing amber - “AIR PACK” amber message on EWD - Aural alert is Single Chime (SC) - Packs indicator in amber on SD cabin page - Pack valve FAULT on overhead panel AIR PACK 1+2 This alert is triggered when both pack valve are lost. Visual and aural alert are : - MC light flashing amber - “AIR PACK 1+2” amber message on EWD - Aural alert is Single Chime (SC) - Packs indicator in amber on SD cabin page - Pack valve FAULT on overhead panel AIR RECIRC FAN 1(2) A recirculation fan low RPM or internal overheat. A caution signal is sent to the FWS by the MFC. Visual and aural alert are : - MC light flashing amber - “AIR RECIRC FAN 1(2)” amber message on EWD - Aural alert is Single Chime (SC) - Recirculation fan in amber on SD cabin page - Recirc fan FAULT on overhead panel AIR DUCT OVHT This caution is generated when the over-- temperature switch, in the supply duct, has sensed a temperature of 92°C (197.6 °F). Visual and aural alert are : - MC light flashing amber - “AIR DUCT OVHT” amber message on EWD - Aural alert is Single Chime (SC) - Duct overheat amber alert “HOT” on the SD cabin page - OVHT on the overhead panel Mod: 5948 1.03.30 AIR P 16 AIR CONDITIONING R 001 FEB 12 AA AIR VENT EXH This caution is generated either by releasing the OVBD push-- button on Avionics Vent Panel or by an extraction fan failure (temperature or underspeed). Visual and aural alert are : - MC light flashing amber - “AIR VENT EXH” amber message on EWD - Aural alert is Single Chime (SC) - Extraction fan indicators in amber on SD cabin page - Avionics Vent/Exhaust Mode FAULT light illuminated AIR OVBD This caution is generated when there is a disagreement between the commanded position of the OVBD valve and its current position. Visual and aural alert are : - MC light flashing amber - “AIR OVBD” amber message on EWD - Aural alert is Single Chime (SC) - OVBD indicators in amber on SD cabin page - Avionics Vent / OVBD Valve FAULT light illuminated Mod: 5948 1.03.30 AIR P 17 AIR CONDITIONING R AA 30.5 SCHEMATIC Mod: 5948 001 FEB 12 . 1.03.40 AIR P1 PRESSURIZATION 001 FEB 12 AA 40.1 DESCRIPTION R The cabin pressure is controlled by an electro-- pneumatic valve and a pneumatic valve. These valves are located on the lower fuselage skin in the rear underfloor zone and are operated by either of two control sub-- systems : - A digital electro-- pneumatic sub-- system : AUTO-- mode - A pneumatic sub-- system : MAN-- mode R An overpressure relief valve and a negative pressure relief valve are fitted on both outflow valves as safety devices. The controls related to the Cabin Pressure Control System (CPCS) are located on the R.H, side of the flight deck central instrument panel. Indicating is provided through SD cabin page, on the upper part of MFD. When the system is operating in the AUTO-- mode, the pneumatic outflow valve is slaved to the electro-- pneumatic valve. Their opening will be the same. R In case of controller failure : - The positive differential pressure is limited to 6.35 PSI by a manometric capsule. - The negative differential pressure is limited to - 0.5 PSI by a non return valve. Note : The manual controller knob must be selected to NORM position in order not to disturb the automatic regulation. Mod: 5948 1.03.40 AIR P2 PRESSURIZATION 001 APR 11 AA AUTO MODE The digital controller is located on the cabin pressure control system (CPCS) panel. It consists of an electronic box with a front panel and three plug-- in modules as follows : - one module contains the electrical supply circuit, the power output circuit and subsidiary circuits. - one module holds all the input circuits (including the pressure sensor) and the output circuits. - the remaining module contains the central processor unit. With the AUTO-- mode operating, the outflow valves are driven by the controller according to the information received with respect to: - Aircraft altitude obtained from air data computer (A.D.C.) via the CAC. - Landing elevation, pre-- selected by the ELV SET trigger switch. - Take-- off elevation, memorised by the controller. - Pressure cabin altitude, obtained from a pressure transducer inside the digital controller. Mod: 5948 1.03.40 AIR P3 PRESSURIZATION 001 FEB 12 AA AMBIENT PRESSURE SENSOR R It is composed of three modules that allow acquisition, process and transmission of cabin pressure data to the CAC. Both signals (pressure and pressure variation) are designed to provide an output between 0.5 V and 4.5 V, allowing failure detections out of this range. R Signals from APS are sent to the CAC and processed to displayed as three indicators on the SD Cabin page : - Cabin altitude (ft) : Determine the equivalent altitude associated the cabin pressure. - Vs (ft/min) : Determine the equivalent altitude change associated to the pressure variation. - ∆P (PSI) : Determine the pressure difference between the outside (provided by other pressure sensor) and the inside of aircraft. DUMP FUNCTION A DUMP function is available to send a fully open electrical signal to the electropneumatic outflow valve.DUMP function is available as long as pressurization system is in AUTO mode. CAUTION : The DUMP PB is mechanically protected. No other safety device protects DUMP function from inadvertent use. Mod: 5948 1.03.40 AIR P4 PRESSURIZATION 001 APR 11 AA MANUAL MODE The electropneumatic outflow valve is maintained closed and the pneumatic outflow valve controls the cabin outlet air flow. Its control servo pressure is function of the manual controller demand. The control knob is used to select any cabin rate change from - 1500 ft/mn to + 2500 ft/mn. DITCHING MODE Two electrical motors (one for each outflow valves) maintain both outflow valves in closed position.Ditching mode is available in both automatic and manual modes. Mod: 5948 1.03.40 AIR P5 PRESSURIZATION 001 FEB 12 AA 40.2 CONTROLS R AUTO PRESS PANEL (1) LANDING ELEVATION ind. Displays in ft the landing elevation setting. The two last digits always displays 0. All digits will R extinguish in case of automatic system failure, manual mode or DUMP mode (2) ELV SET trigger switch Allows selection of the elevation of the planned destination airport in 100 ft increments. The R landing altitude ranges between - 1500 ft and 10000 ft. (3) DESCENT RATE pb Is operated to allow a fast cabin descent. NORM (pb released) The max cabin vertical speed in descent is - 400 ft/mn. FAST (pb pressed in) The max cabin vertical speed in descent is - 500 ft/mn. The FAST LIGHT illuminates blue. (4) TEST pb When depressed, the system is electrically tested. If the system is ready to use, the LANDING ELEVATION ind. displays alternately 18800 and - 8800. Fault light illuminates amber on MAN pb. In flight, this test is inhibited. (5) DUMP guarded pb This guarded pb allows selection of the dump function when in AUTO mode. NORMAL (pb released) The digital controller operates normally. ON (pb pressed in) The digital controller is out of circuit and an electrical opening signal is sent to the electropneumatic outflow valve. Both outflow valves will fully open. The ON light illuminates white. Mod: 5948 1.03.40 AIR P6 PRESSURIZATION 001 APR 11 AA MAN PRESS CONTROLS (1) MODE pb Selects the pressure control mode : pb pressed in The digital controller is in operation (AUTO mode). MAN (pb released) The digital controller is out of operation, digits extinguish and the manual controller regulates the pressure. The MAN light illuminates white. “AIR AUTO PRESS” caution is displayed on EWD. FAULT The light illuminates amber to indicate a digital controller failure “AIR AUTO PRESS” caution is diplayed on EWD. (2) MAN RATE knob In manual mode, the control knob is used to select any cabin rate of change from - 1500 ft/mn to + 2500 ft/mn. NORM This position must be used when in AUTO mode. (3) DITCH guarded pb Selects the ditch mode. ON (pb pressed in) Both outflow valves are forced to closed position regardless of the pressure control mode. The ON light illuminates white. Mod: 5948 AIR 1.03.40 P 7/8 PRESSURIZATION 001 FEB 12 AA CABIN PRESS IND The SD Cabin page gives the following information : - Cabin altitude, obtained from Ambient Pressure Sensor via the CAC - Rate of change of cabin altitude - Differential pressure between cabin pressure and outside static pressure. R After conversion, data received from APS are sent by the CAC to both MFD to be displayed. SD CABIN PAGE (1) Differential pressure indicator In the event of an excessive differential pressure, the CAC sends a warning signal to both MFCs and the alerting display is activated. (2) Cabin rate indicator Cabin rate of climb or descent are indicated on SD cabin page. Invalid rate are also indicated and can be due to sensors failure or missing connectivity. An invalid speed can be due to sensors failure (out of range measurement) or a missing connection. (3) Cabin altitude indicator Cabin and target altitude are displayed. An invalid display can be due to sensors failure (out of range measurement) or a missing connection. Mod: 5948 . 1.03.40 AIR P9 PRESSURIZATION 001 FEB 12 AA 40.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) DC BUS 1 (on lateral panel AUTO PRESS) - Nil - Ambient Pressure Sensor DC EMER BUS (on lateral APS) - Nil - DITCH DC EMER BUS (on lateral DITCH) - Nil - EQUIPMENT Digital controller MFC LOGIC See chapter 1.01 SYSTEM MONITORING EXCESS CAB ALT R R Triggered when the cabin altitude becomes greater than 10.000 ft. If Cabin altitude exceeds 13.000 ft, the digital controller fully closes both outflow valves. Visual and aural alert are : - MW light flashing red - “EXCESS CAB ALT” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) - CAB ALT alerting display on SD cabin page (White on Red background) EXCESS CAB ∆P R Triggered when the differential pressure exceeds 6.35 PSI. Visual and aural alert are : - MW light flashing red - “EXCESS CAB ∆P” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) - CAB ∆P alerting display on SD (White on Red background) Mod: 5948 1.03.40 AIR P 10 PRESSURIZATION 001 FEB 12 AA R AIR AUTO PRESS Triggered in the event of a power loss to the digital controller (more than 0.1second). Visual and aural alert are : - MC light flashing amber - “AIR AUTO PRESS” amber message on EWD - Aural alert is Single Chime (SC) - AUTO MAN switch FAULT light illuminated - “AUTO PRESS” label in amber on SD cabin page AIR DITCH Triggered when the ditch push button is depressed. Visual and aural alert are : - MC light flashing amber - “AIR DITCH” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 1.04.00 AFCS P1 CONTENTS 001 APR 11 AA 1.04.00 CONTENTS 1.04.10 GENERAL 10.1 DESCRIPTION 10.2 CONTROLS 10.3 ELECTRICAL SUPPLY / MFC LOGIC / SYSTEM MONITORING 1.04.20 AUTO PILOT / YAW DAMPER 1.04.30 FLIGHT DIRECTOR 1.04.40 OPERATION 40.1 AUTO PILOT / FLIGHT DIRECTOR MODES 40.2 AFCS ALERTS 1.04.50 ALTITUDE ALERT Mod: 5948 . GENERAL P 1/2 APR 11 001 1.04.10 Mod: 5948 ¡ FMA, FGCP, ICP, computers and pitch trim box (Cockpit and electronic rack). © Yaw and pitch servo actuators. ¢ Roll servo actuator. COMPONENTS LAYOUT The CAC 1 generates commands to the flight control actuator, and CAC 2 monitors the system. The computers (CAC1/2) receive data from the two Air Data computers (ADC), the two Attitude and Heading Reference Systems (AHRS), the radio-- altimeter, the NAV1/2 , the FMS, and from some sensors. Main components are : • two Core Avionics Cabinet (CAC 1 which controls the autopilot functions and CAC 2 which monitors the autopilots functions) • three control panel : one Flight Guidance And Control Panel (FGCP) and two Integrated Control Panel (ICP) • two Flight Mode Annunciator (FMA), one on each PFD upper part • three identical servo actuators on the three axes (pitch, roll, yaw) • one Power Trim Box (to interface with the pitch trim actuator) The aircraft is provided with an automatic flight control system. It achieves : • AutoPilot (AP) function with automatic pitch trim, Yaw Damper (YD) and turn coordination • Flight director (FD) function • altitude alert 10.1 DESCRIPTION AA AFCS . 1.04.10 AFCS P3 GENERAL AA 001 APR 11 10.2 CONTROLS FLIGHT GUIDANCE and CONTROL PANEL (FGCP) (1) - AP P/B Action on the P/B engages Auto Pilot (AP) and Yaw damper (YD) functions simultaneously. All four associated arrows illuminate green. Pressing the P/B again disengages only the AP function. (2) - YD P/B Action on the P/B engages the YD function. Both associated arrows illuminate green. Pressing the P/B again disengages the YD function (and the AP if engaged). (3) - SPEED HLD P/B Action on this P/B engages the Speed Hold (SPD HLD) function for approach only. Requested conditions : Aircraft in landing configuration, PL in White Arc (Between 37° and 49°), AP ON, LOC + GS Green, IAS < 140 kts. Pressing the P/B again disengages SPD HLD function. (4) - CPL P/B Enables selection of the side (CAPT or F/O) to be coupled to the AP/YD computers. At power up, selected side is CAPT side. (5) - VERTICAL MODES P/B Enables selection of vertical modes: IAS HOLD, VS HOLD, ALT HOLD. Pressing the P/B again disengages these functions to return in basic mode (PITCH HOLD). Note : (5) is common Vertical mode for AP and FD and (3) is vertical mode for AP only, for CAT II or CAT III and speed hold is disengaged outside white arc. Mod: 5948 1.04.10. AFCS P4 001 GENERAL APR 11 AA (6) - PITCH WHEEL (PW) In VS mode, operating the PW will change the VS value without disengaging the VS mode. Note : PW is inhibited in GS, IAS HOLD, ALT SEL CAPTURE and ALT HOLD modes. In basic mode operating the PW allows to select pitch attitude. (7) - STBY P/B Cancels all AP and FD Upper Modes (Armed, Captured or active modes). Resets them to basic modes. (8) - LATERAL MODES P/B Enable the selection of lateral modes: HDG SEL, NAV, APP, BC. Pressing the P/B again disengages these functions to return in basic mode (HDG HLD or ROLL HLD) and in case of Flux valve failure the WING LVL replaces HDG HLD basic mode. (9) - FD P/B Action on the P/B displays the Flight Director (FD) command bars. Each bar (Horizontal Bar and Vertical Bar ) will be displayed in : - upper mode - basic mode, only if AP is engaged. (Pressing the P/B again clears the display of the FD command bars). (10) - HDG Knob Sets the heading used as reference by the FGCS. The selected heading is displayed on both CAPT and F/O on EHSI and/or ND depending on display configuration. Pushing the knob permit to synchronize the heading bug with the actual heading. (11) - CRS Knob CAPT side Sets the course on CAPT EHSI and/or ND depending on display configuration (12) - CRS Knob F/O side Sets the course on F/O EHSI and/or ND depending on display configuration (13) - NAV SOURCE Selector CAPT side Selects the NAV SOURCE for CAPT EHSI and/or ND depending on display configuration (14) - NAV SOURCE Selector F/O side Selects the NAV SOURCE for F/O EHSI and/or ND depending on display configuration (15) - ALT SEL knob Controls the preselected altitude which is shown above the PFD altimeter scale. Mod: 5948 1.04.10 AFCS P5 GENERAL 001 FEB 12 AA INDEX CONTROL PANEL (ICP) (1) This P/B allows switching between Selected Manual Speed (MAN) and Automatic Speed managed by the FMS (AUTO). R Note : At power on, the manual speed target mode (MAN) is engaged (2) Speed knob used to set the SPD TGT in MAN mode. R (3) The knob is used to set the barometric reference. Pushing the knob sets standard barometric reference (29.92 INHG / 1013.25 Hpa) (4) Outer knob permits to select between DH (Decision Height) or MDA (Minimum Descent Altitude). Inner knob is used to set DH or MDA values, depending of the outer knob position. Mod: 5948 1.04.10 AFCS P6 001 GENERAL APR 11 AA GO AROUND PB The GO AROUND PB are located on the external side of each Power Lever. When pressing these P/B, the Go Around mode is engaged. All flight director modes are cancelled and the autopilot is disengaged. The FGCS provides : - heading (HDG HOLD) for the lateral mode. - safe pitch (GA) for the vertical mode via the FD bars indications Mod: 5948 1.04.10 AFCS P7 GENERAL 001 APR 11 AA CONTROL WHEEL (A) AP Quick Disconnect PB Allows to disconnect AP when depressed once. When depressed again clears the AP OFF alarm. (B) Normal Pitch Trim ROCKER Used in order to adjust the Pitch Trim (Normal Pitch Trim setting means). Note : If the AP is ON, action on this trim disengages the AP (C) Touch Control Steering (TCS) PB Located on the back side of the Control Wheel. Depressing the button allows to regain temporary manual control of the aircraft without disconnecting the AP. - Basic AP mode : Depressing the TCS button in the basic mode will cause the AP to change the pitch and roll references. The reference attitude will be the aircraft’s new pitch and roll attitude (within limits) at the time the TCS button is released. Pitch attitude resynchronisation limits are - 15°/+15°. If the button is released with a pitch attitude greater than 15° the aircraft will return to 15° and maintain that attitude. If pitch attitude selected with TCS is greater than 25° the AP will be disengaged. If the TCS is released at bank angles less than 6° the system will level the wings and, at wings level will fly the existing heading. If the bank angle is greater than 6° but less than 35° at TCS release, the AP will maintain the bank angle. At bank angles greater than 35° the aircraft will return to 35° and the AP will maintain 35°. - Modes linked to Air Data Reference : Action on TCS PB during ALT HOLD, VS HOLD or IAS HOLD modes will resynchronize the Air Data Command reference without disengaging the mode. Action of TCS PB during IAS or VS mode will generate a dashed IAS or VS reference message on FMA. - In all other modes, a TCS activation will simply allow the pilot to take manual control of the aircraft without disengaging the mode. Mod: 5948 1.04.10 AFCS P8 GENERAL AA STBY PITCH TRIM SW STBY PITCH TRIM will disengage the AP. Mod: 5948 001 APR 11 1.04.10 AFCS P9 GENERAL 001 APR 11 AA FLIGHT MODE ANNUNCIATOR (FMA) The Flight Mode Annunciator (FMA), located in the upper part of the PFD, has : - 4 columns dedicated to annunciation of : - Icing Status Information - Lateral Modes - Vertical Modes - Engagement Status of the AutoPilot. - A messages line Modes Symbols : Mod: 5948 1.04.10 AFCS P 10 GENERAL AA (1, 2, 3) Lateral modes (1) : Lateral armed mode (cyan) (2) : Lateral Capture and Hold mode (green) (3) : Bank Angle (green) : depending of the speed : - Low Bank (LO) (15° max) - High Bank (27° max) Mod: 5948 001 APR 11 1.04.10 AFCS P 11 GENERAL AA (4&5) Vertical modes (4) : Vertical Armed mode (cyan) (5) : Vertical Capture and Hold mode (green) (1, 2, 4, 5) Common modes - APP(GS&LOC) - GA Mod: 5948 001 APR 11 1.04.10 AFCS P 12 GENERAL AA (6) AP or YD engagement (7) FD bars display (8) Coupling selection (9) Provision for CAT III information (10) TCS Activation Mod: 5948 001 APR 11 1.04.10 AFCS P 13 GENERAL 001 APR 11 AA (11) AP/YD disengagement, approach category retrogression, AFCS internal failure. (See chapter 10-- 3 system monitoring) (12) Unexpected mode change, or problem in navigation parameters. (See chapter 10-- 3 system monitoring) (13) Approach category (14) Trim status (See chapters 10-- 3 System monitoring & 09 Flight controls) (15) Icing (See chapter 13 Ice and rain protection) (16) APM Message (See chapter 13 Ice and rain protection) Mod: 5948 1.04.10 AFCS P 14 001 GENERAL APR 11 AA PRIMARY FLIGHT DISPLAY (PFD) 1-- Flight Director Command bars (Green) : Display computed commands to capture and maintain a desired flight path. 2-- Speed bug & speed read out : - Cyan bug when selected manually. On Index Control Panel (ICP), the speed target (SPD TGT) has to be in MAN and selection is done with the speed knob. - Magenta bug when managed by the FMS On Index Control Panel (ICP), the speed target (SPD TGT) has to be in AUTO, and the speed is computed by the FMS Mod: 5948 1.04.10 AFCS P 15 GENERAL 001 APR 11 AA 3-- ALT bug & altitude read out : On the Flight Guidance Control Panel (FGCP), the cyan bug and the readout is set with the ALT SEL knob. The numeric ALT SEL readout is permanently displayed. 4-- VS bug & VS read out : On the Flight Guidance Control Panel (FGCP), the cyan bug and read out are set with the Pitch wheel when the VS mode is selected 5-- HDG bug & HDG read out : On the Flight Guidance Control Panel (FGCP), the cyan bug is set with the heading knob. 6-- NAV course pointer/deviation & readout : - Cyan course when selected manually. (Mode NAV and APP) On the Flight Guidance Control Panel (FGCP), when the NAV source selector is on V/ILS1 or 2, the course pointer is set with the CRS knob. - Magenta course when managed by the FMS (Mode LNAV) On the Flight Guidance Control Panel (FGCP), when the NAV source selector is on FMS 1&2, the desired track indication is computed by the FMS 7 - Minimum Descent Altitude (MDA) : The MDA is set with the ICP. This MDA is displayed by two horizontal amber lines directly on the altimeter scale. 8 - Decision Height (DH) - (CAT II ) : Linked to the radioaltimeter information, an aural and visual alert inform the crew that the decision height is reached. A DH alert is displayed on the PFD and an aural alert is generated by the T2CAS (TAWS) (Minimum, Minimum). DH on PFD : Mod: 5948 1.04.10 AFCS P 16 OPERATION 001 APR 11 AA 10.3 ELECTRICAL SUPPLY / MFC LOGIC / SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT AutoPilot Servo Motor (Roll, Yaw,Pitch) Flight Guidance Control Panel (Channel 1 & 2) DC BUS SUPPLY (C/B) DC STBY BUS (On overhead panel : PITCH SERVO, YAW SERVO, ROLL SERVO) DC EMER BUS (Overhead panel : FGCP CHAN1/IOM-- AP1) DC ESS BUS (Overhead panel : FGCP CHAN2/IOM-- AP2) Index Control Panel F/O DC ESS BUS (Overhead panel: ADC 2 FLT SPLY / ICP F/O ) Index Control Panel CAPT DC EMER BUS (Overhead panel: ADC 1 EMER SPLY / ICP CAPT ) Yaw Dynamometric Rod DC EMER BUS Quick release DC EMER BUS (Lateral panel: L NORM & STBY PITCH TRIM & RUD TLU MAN CTL) FCTL Power Trim Box DC EMER BUS (Lateral panel: L NORM & STBY PITCH TRIM & RUD TLU MAN CTL) CAC 2 DC ESS BUS (CAC Card : CPM2) (C/B overhead panel: CPM 2 / IOM-- S 2) DC ESS BUS (CAC Card : IOM-- AP2) (C/B overhead panel : FGCP CHAN2/IOM-- AP2) CAC 1 DC EMER BUS (CAC Card : CPM1) (C/B overhead panel: CPM 1 / IOM-- S 1) (CAC Card : IOM-- AP1) (C/B overhead panel: FGCP CHAN1/IOM-- AP1) Mod: 5948 GENERAL P 17/18 APR 11 001 1.04.10 (11) : AP/YD disengagement, approach category retrogression, AFCS internal failure SYSTEM MONITORING MFC LOGIC See chapter 1.01. Mod: 5948 AA AFCS . GENERAL P 19/20 (12) : Unexpected mode change, or problem in navigation parameters Mod: 5948 AA AFCS APR 11 001 1.04.10 . AFCS FAIL (14) : Trim status Mod: 5948 AA GENERAL AFCS P 21/22 APR 11 001 1.04.10 . 1.04.20. AFCS P1 AUTO PILOT/YAW DAMPER 001 APR 11 AA PURPOSE The YAW DAMPER (YD) provides yaw damping and turn coordination. To achieve these functions, AFCS computers (CAC1/2) and AP yaw actuator are used. The AUTO PILOT (AP) allows the following : - stabilizing the aircraft around its center of gravity while holding pitch attitude and heading, wing level or bank angle (AP in basic modes). - flying automatically any upper or basic mode or any mode except GO AROUND mode which must be flown manually only. AUTO PILOT ENGAGEMENT When the AP is engaged, the pitch, roll and yaw actuators are connected to the flight controls and the pitch autotrim function is activated. - Engagement with no vertical upper mode selected: The AP flies actual pitch attitude. This is the basic vertical mode (”PITCH HOLD”, displayed in green). Pitch wheel and TCS can be used to modify the pitch attitude. - Eengagement with no lateral upper mode selected : Depending of the conditions at engagement, the AP will level wings and then maintain wing level (”WING LVL”, displayed in green) or will maintain the current heading (”HDG HOLD”, displayed in green) or will maintain the current bank angle (”ROLL HOLD” ,displayed in green). These are the basic lateral modes. TCS pb may be used (see 1.04.10). - Engagement with a lateral or vertical armed upper mode selected : the AP flies basic mode until the armed mode becomes active. - Engagement with a lateral and/or vertical active upper mode selected : the AP manoeuvers to fly to zero the FD command bars. AUTO PILOT DISENGAGEMENT AP can be disengaged manually or automatically. S Manual disengagement is achieved by action on either one of the following devices : - Quick disconnect pb on control wheel - Action on Pitch Trim (normal or STBY) - AP pb on FGCP - YD pb on FGCP - GA pb on PL - Pilot’s force on the pedals over 30 daN (66 lb) - Pilot’s force on the control column (pitch axis) over 10 daN (22 lb) S Automatic disengagement occurs when : - one of the engagement conditions of the AP and/or YD is no longer met - stall warning indicator threshold is achieved - there is a disagreement between the two AHRS or between the two ADC - there is a mismatch between the two pitch trims - there is a failure of one AHRS or one ADC. Mod: 5948 1.04.20 AFCS P2 AUTO PILOT/YAW DAMPER 001 APR 11 AA MANUAL DISENGAGEMENT - Action on the AP pb on the FGCP, or quick disconnect pb on each control column, or GA mode activation, or STBY or NORMAL pitch trim switch activation or effort on control column disengage the AP function without disengaging the YD function. The AP green arrows extinguish, “AP DISENG” is displayed on FMA (white on red message reverse video) and the “cavalry charge” aural warning is generated. - Action on the quick disconnect pb (second time) clears the aural warning and message. Note : If a failure occurs, the “PITCH TRIM FAIL”, “PITCH MISTRIM”, “AILERON MISTRIM” or “RUDDER MISTRIM” message is displayed on the FMA. (RUDDER MISTRIM only with the CAT III option). The crew has to disengage AP and manually fly the aircraft. - Action on the YD pb on the FGCP or an effort on pedals disengages the AP and YD (if engages together). AP and YD green arrow extinguish. AP/YD DISENG is displayed on FMA (displayed in white on red message reverse video) and the “cavalry charge” aural warning is generated. Action on the quick disconnect pb (second time) clears the aural warning and message - The YD (if only engaged). The YD green arrows extinguish. YD DISENG is displayed on FMA (displayed in black on amber message reverse video). Action on the quick disconnect pb (second time) clears the message AUTOMATIC DISENGAGEMENT The warnings and messages are the same as those which occur in case of manual disengagement but the AP DISENG, AP/YD DISENG or YD DISENG messages are flashing. Action on “CLEAR” pb clears warnings and messages. Note: If PITCH TRIM ASYM on the EWD, AP automatically disengages and cannot be reengaged. AP/YD MONITORING RECOVERY When a monitored failure is detected, AP and/or YD is disengaged. If the pilot clears messages displayed on FMA (by using CLEAR pb) the AP computer will attempt a “monitor recovery”. The AP/YD can be again engaged. If initial failure condition still exists, AP/YD is disengaged again. Conditions which will inhibit all recovery attempts are : - Loss of AP, YD and FGCP - Trim inoperative monitor failures - Any APP mode - GA mode - LOC or BC modes Mod: 5948 1.04.30 AFCS P1 FLIGHT DIRECTOR 001 APR 11 AA FUNCTION The purpose of the FLIGHT DIRECTOR (FD) is to provide information to the pilot through the command bars on the PFD to allow a manual guidance of the aircraft : - In pitch axis if a vertical active mode is selected. - In roll axis if a lateral active mode is selected. The FD commands are satisfied when the FD bars remain centered on the PFD. If no vertical active mode is engaged, the corresponding command bar will revert to PITCH HOLD. If no lateral active mode is engaged, the corresponding command bar will according to situation revert to HDG HOLD, ROLL HOLD or WING LVL. In addition, the two bars can be removed by acting on the FD P/B on the FGCP. The following modes are available : S Vertical modes : ALT SEL, ALT, VS, IAS S Lateral modes : HDG SEL, NAV, BC S Common modes : APP (lateral and vertical guidance for approach) GA. Some modes have an initial arm status before becoming active. Their active phase is divided into a capture phase followed by a track or hold phase. When AP is engaged, it automatically follows the FD commands. If no FD active mode is selected, the system flies basic AP mode (see 1.04.20). MODE SELECTION Mode selection is achieved by action on the corresponding pb on the FGCP except for ALT SEL mode and GO AROUND mode : - ALT SEL mode is automatically armed. - GO AROUND mode is activated as soon as one of the GA pb located on the PL’s is depressed, and is disengaged by using TCS, STBY pb, by selecting a new vertical mode or by engaging AP. Note : Simultaneous armed status modes is limited to one lateral mode and two vertical modes. Therefore vertical armed modes are prioritized in the following order : - ILS GS ARM - ALT SEL ARM ACTIVATION OF ARMED MODES Only one lateral and one vertical mode can be activated simultaneously. If two vertical modes are armed, the first which meets the capture conditions becomes active. The second remains armed. Mod: 5948 1.04.30 AFCS P2 FLIGHT DIRECTOR 001 APR 11 AA MODE DISENGAGEMENT Action on the pb of an armed or active mode on the FGCP disengages that mode. Action on either GA pb on the PL’s disengages all other armed or active mode. Action on the STBY pb on the FGCP disengages all armed and active modes. ALT SEL mode will rearm automatically only if AP is engaged or if a FD mode is selected again and if aircraft flies toward the selected altitude. When a vertical (or lateral) mode becomes active, the previously active vertical (or lateral) mode is automatically disengaged. Other automatic disengageement logic conditions are detailed for each mode in chapter 1.04.40. FLIGHT GUIDANCE DISPLAYS AND ANNUNCIATIONS The HSI / ND displays navigation information: The FD uses information from the coupled HSI / ND which is selected through the CPL pb on the FGCP. Heading bug : the heading bug is controlled by the single heading knob. The heading error between actual heading and selected heading as displayed on the coupled HSI / ND is sent to the FD. Course pointer : the course pointer of each HSI / ND is controlled by the associated course knob (except LNAV mode). The course error as displayed on the coupled HSI / ND is sent to the FD. Deviations : deviations displayed on the coupled HSI / ND and used by the FD are as follows, depending on the selected navigation source: S in lateral : VOR, LOC or LNAV S in vertical : GS The ADI displays guidance information through the pitch and roll command bar. The FMA provides mode status annunciations : S lateral armed mode status is displayed in cyan (VOR, NAV, BC) S vertical armed mode status is displayed in cyan (ALT SEL, GS) S lateral active mode status is displayed in green (VOR, LOC, BC, LNAV, HDG SEL, HGD HOLD, ROLL HOLD, WING LVL) S vertical active mode status is displayed in green (IAS, VS, ALT, GS, PITCH HOLD) S At mode change, the mode annunciation is surrounded with a green box for 7 seconds S During capture phase, a star is added to the mode annunciation on FMA. Mod: 5948 1.04.40 AFCS P1 OPERATION 001 APR 11 AA 40.1 SYSTEM OPERATION VERTICAL MODES CAC 1 & CAC 2 (AFCS computers) receive data from both ADC and both AHRS. The Autopilot and Yaw damper functions use data from both ADC and both AHRS, and the FD use data from the selected sources. This selection is achieved by the CPL P/B on the FGCP. At power up, left side is coupled. The coupled side is indicated by illumination of the corresponding arrow located at each side of the CPL pb and displayed in green on the FMA (”<-- - “, “-- - >“). In case of failure on either side despite of the coupling (AHRS or ADC failed, AHRS’s or ADC’s miscomparison), AP/YD are disengaged. In this case the AP/YD can be reengaged with a ”single AHRS” or “single ADC” by selecting the operative source, with the dedicated switching source P/B on the switching control panel. During ILS approach only : DUAL CPL automatically occurs after LOC and GS track phase has begun if both NAV receivers are tuned to ILS. In DUAL CPL both arrows are illuminated, “DUAL” is displayed on FMA, and both NAV receivers are coupled to the AFCS computers which utilize average data for guidance computation. When the APP mode is manually cancelled, the FD remains coupled to the side selected prior to dual coupling. Excess DEV monitoring utilizes ILS data from both sources (CAT 2 approach). Mod: 5948 1.04.40 AFCS P2 OPERATION 001 APR 11 AA 40.2 AUTOPILOT / FLIGHT DIRECTOR MODES GENERAL - Reduced bank angle function In all lateral modes, this function selects automatically the bank angle limit (High or Low bank). Selection of either value is made by the AFCS computer by comparison between current aircraft speed and VmHB. LO BANK is selected if IAS < VmHB HI BANK is selected if IAS > VmHB + 5 The selected bank angle is displayed on the FMA by the green message “LO” - if nothing is displayed : bank angle maximum value 27° - if “LO” is displayed: bank angle maximum value 15° This limit bank angle is also displayed on the ADI by 2 green ticks : For LO BANK : For HI BANK : Mod: 5948 OPERATION P 3/4 APR 11 001 1.04.40 Mod: 5948 The bank angle can be changed and hold with the TCS, within the limits of +/-- 50°, the autopilot is automatically disengaged if bank angle is greater than 50° . - If roll angle is superior to the limit (+ /-- 15° or +/-- 27° depending of the speed - - > Low bank/ High bank), the aircraft return and hold the limit bank angle (”ROLL HOLD” green on FMA). - If roll angle is superior to 6° at activation, the autopilot held the current bank angle (”ROLL HOLD” green on FMA) - If the roll angle is inferior to 6° at mode activation: the aircraft returns to null bank angle with activation of the wing level basic mode (”WING LVL”, green on FMA), then when bank angle is less than 3° confirmed for 10s, the heading hold basic mode (“HDG HOLD”, green on FMA) is activated. - If the roll angle is less than 3° for more than 10s, at mode activation, the current heading is maintained (“HDG HOLD” green on FMA) despite of the heading bug. - Lateral basic mode - Vertical basic mode Pitch hold (”PITCH HOLD” green on FMA). The pitch basic mode enables to maintain the pitch attitude at engagement or bring it back to + or - 15° limit value. Then the pitch value, can be changed and held within the limits, with the TCS or the pitch wheel. Note: If AP engaged in basic mode only, the Flight Director cross bars will be displayed. The basic modes are engaged by means of the AP push-- button on the FGCP, if no FD mode is active prior to AP engagement. The auto pilot basic modes are : - Pitch hold (”PITCH HOLD” green on FMA) on vertical axis. - Heading hold (”HDG HOLD” green on FMA), Wing level (”WING LVL”, green on FMA) and Roll hold ( “ROLL HOLD” green on FMA”) on lateral axis. BASIC MODES AA AFCS . OPERATION P 5/6 APR 11 001 1.04.40 VS HOLD, IAS HOLD or PITCH HOLD modes can be used to fly to the selected altitude. This altitude is selected by means of the ALT SEL knob on the FGCP. £ ARM PHASE The ALT SEL armed mode is annunciated by : - a cyan “ALT SEL” message on the FMA. - a cyan bug and an altitude selected read out on the PFD altimeter. The ALT HOLD mode is annunciated on FMA by a green “ALT” and the bug & readout are displayed on the PFD. Depressing and holding the TCS button allows the pilot to maneuver the aircraft to a new altitude reference without disengaging the mode. In the ALT HOLD mode, all armed FD vertical modes are allowed, but a GS capture will override the ALT HOLD mode. Activation of the ALT pb on the FGCP selects the ALT HOLD mode and overrides all active FD vertical modes. Any lateral mode existing at engagement is mantained. ALTITUDE HOLD MODE ¤¥ During the three phases (ALT SEL ARM, ALT SEL CAP, ALT HOLD), a GS capture will override the altitude mode. ¢ HOLD PHASE When the desired altitude is reached, the ALT SEL CAP mode is automatically cancelled and ALT HOLD mode is automatically selected. The ALT HOLD mode is annunciated on the FMA by a green “ALT”. © CAPTURE PHASE When approaching the preselected altitude, the system automatically switches to the ALT SEL CAP mode and the previous vertical mode is cancelled. A command is generated to asymptomatically capture the selected altitude. ALT SEL CAPTURE is annunciated by : - a green and boxed “ALT*” (the box for mode change and the star for capture). - a green “ALT*” after 7s. Note : The ALT OFF amber message appears during Altitude Capture - When the selected altitude is changed (transition to basic PITCH HOLD mode) - When baro correction is changed (transition to basic PITCH HOLD mode) ¡ ALT SEL mode is automatically armed when the aircraft is climbing or is descending toward the selected altitude except after action on the STBY pb. In this case, ALT SEL mode rearms only if AP is engaged or if a FD mode is selected, in addition to the previous conditions. ALTITUDE SELECT MODE VERTICAL MODES Mod: 5948 AA AFCS . OPERATION P 7/8 APR 11 001 1.0440 Depressing and holding the TCS button allows the pilot to maneuver the aircraft to a new vertical speed reference without disengaging the mode. In VS hold mode any other vertical mode may be armed, and when captured will override VS hold mode. £ When the new Vs is stabilized, the VSI pointer is in front of the bug. ¢ Activation of the PW will set a new vertical speed reference. © When the Vs is stabilized, the VSI pointer is in front of the bug. 7 s after the selection the VS is annunciated by a green “VS” message on the FMA. ¡ Action on the VS pb on the control panel selects the VS hold mode and overrides all active FD vertical modes. VS existing at engagement is maintained. The VS mode is annunciated by : - a green “VS” message on the FMA. - a cyan bug and a selected Vs readout on the PFD VSI. VERTICAL SPEED HOLD MODE Mod: 5948 AA AFCS . OPERATION P 9/10 APR 11 001 1.04.40. AUTOMATIC SPEED (”AUTO”) The speed bug (magenta) is managed by the FMS. For further information, refer to FMS chapter. ¢ When the new IAS is stabilized, the ASI pointer is in front of the bug. Depressing and holding the TCS button allows the pilot to maneuver the aircraft to a new IAS reference without disengaging the mode. In IAS hold mode, any other vertical mode may be armed, and when captured will override IAS hold mode. © Actuation of the SPD TGT knob will set a new IAS reference without disengaging the mode. ¡ Action on the IAS pb on the control panel selects the IAS hold mode and overrides all active FD vertical modes. Airspeed existing at engagement is maintained. The IAS mode is annunciated by : - a green boxed “IAS” message on the FMA. - a cyan bug and the selected IAS readout on the PFD ASI. After 7s, a green IAS message is displayed on the FMA MANUAL SPEED (”MAN”) INDICATED AIRSPEED HOLD MODE Mod: 5948 AA AFCS . OPERATION P 11/12 APR 11 001 1.04.40 In the Heading Select mode, all armed roll FD Modes are allowed but the capture of any armed lateral mode will override the Heading Select mode. CAUTION : Before take off, A/C lined up with the runway heading, the vertical command bar has to be checked and centered (if necessary). Selection of turns greater than 180° will lead the system to order a turn as short as possible if selection has been made before HDG mode being engaged. If selection is made after HDG mode engagement, turning command will occur by the side selected by the pilot. £ The aircraft turn to the selected heading and after 7s a green “HDG SEL” is displayed on the FMA ¢ Action on the HDG pb on the FGCP, selects the Heading Select mode and overides any active lateral FD mode. The heading Select mode is annunciated on the FMA by a green boxed “HDG SEL” at the lateral active location. ¡ © Heading selection is made by the heading knob and is displayed on both HSI / ND. HEADING SELECT MODE LATERAL MODE Mod: 5948 AA AFCS . OPERATION P 13/14 APR 11 001 1.04.40 AFTER STATION Mod: 5948 Selection and display are identical to VOR NAV mode : ”LOC” (cyan), “LOC*” (green boxed),”LOC*”(green), “LOC” (green) - LOCALIZER MODE ¤ £ VOR TRACK mode is annunciated on the FMA by the green “VOR” message. ¢ At capture, the previous lateral mode is cancelled. VOR CAPTURE is annunciated on FMA by: - a green boxed “VOR*” (the box for mode change and the star for capture). - a green “VOR*” after 7s. © After action on the NAV pb, the VOR arm is annunciated on the FMA by a cyan “VOR” message. HDG SELECT, HDG HOLD modes can be used to steer during the VOR arm phase. - VOR NAVIGATION MODE ¡ After selection of the nav source on the FGCP ( V/ILS1 or V/ILS2) and after tuning of the VOR frequency with the MCP or RMS (via the MCDU), the requested course is set with the FGCP course knob. Depending on the selected NAV source and the frequency tuned. “VOR” or “LOC” or “LNAV” (displayed in cyan), is selected. Action on the NAV pb on the FGCP arms the lateral guidance for capture of the selected navigation source that is displayed on the active HSI / ND. NAVIGATION MODE AA AFCS . OPERATION P 15/16 APR 11 001 1.04.40. ¤ ¥ Passing over the waypoint, the LNAV mode sends a roll order to fly to the next way point. £ LNAV track mode is annunciated on the FMA, by a green LNAV message after 7s. ¢ At capture, the previous lateral mode is cancelled. LNAV capture is annunciated on FMA by: - a green box (the box for mode change). © After action on the NAV pb, the LNAV ARM is annunciated on the FMA by a cyan LNAV message. HDG SELECT, HDG HOLD modes can be used to steer during the LNAV ARM phase. ¡ The nav source is selected on the FGCP (FM1 or FM2) and the flight plan is selected on the MCDU. The managed course (HSI) and the leg to the next waypoint (ND) are in magenta - LNAV NAVIGATION MODE Mod: 5948 AA AFCS . 1.04.40 AFCS P 17/18 OPERATION 001 APR 11 AA BACK COURSE MODE The back course mode is set up and flown exactly like a front course localizer approach but selecting BC mode. In this case, glideslope capture is automatically inhibited. - Set the course pointer on the HSI / ND for the inbound published track. - Set the heading bug on the HSI / ND for the desired heading to intercept the course. Mod: 5948 . 1.04.40 AFCS P 19/20 OPERATION 001 APR 11 AA COMMON MODES ILS APPROACH MODE ¡ © Action on the APP pb on FGCP selects LOC and GS ARM modes provided the coupled NAV receiver is tuned to an ILS frequency. LOC ARM is annunciated on the FMA by a cyan “LOC” message. HDG SELECT, HDG HOLD modes can be used to steer during the LOC ARM phase. GS ARM is annunciated on the FMA by a cyan “GS” message. Any vertical mode is allowed during GS ARM phase. ¢ £ At LOC CAPTURE the previous lateral mode used to fly is cancelled. LOC CAPTURE is annunciated on the on the FMA by : - a green boxed “LOC*” (the box for mode change and the star for capture). - a green “LOC*” after 7s. ¤ LOC TRACK is annunciated on the on the FMA by the green “LOC” message. Glideslope capture is interlocked such that the localizer must be captured prior to glideslope capture. The GS capture overrides all vertical modes which were previously engaged. GS CAPTURE is annunciated on the on the FMA by : - a green boxed “GS*” (the box for mode change and the star for capture). - a green “GS*” after 7s. GS TRACK is annunciated on the on the FMA by the green GS message. Crew is advised if all aircraft CAT II conditions are met by a CAT 2 message displayed on the FMA. IF not, a CAT I message is displayed. If CAT II conditions are lost during approach, a “CAT 2 INVALID” amber message is displayed on the FMA. In addition, a “TRIPLE CLIC” aural alert is generated. Note : EXCESS DEV monitoring is enabled when CAT II conditions are met. This monitoring is available below 500 ft RA. When an excessive deviation occurs, the LOC or/and GS scales are flashing amber and “EXCESS DEV” (white on red reverse video) is flashing on the FMA, then after 7s “EXCESS DEV” is becoming steady amber Mod: 5948 . 1.04.40 AFCS P 21 OPERATION 001 APR 11 AA GA AROUND MODE (FD MODE ONLY) Action on the GA pb selects the GO AROUND mode and cancels all armed and active FD modes. The AP disengages and the FD gives commands to fly predetermined minimum safe pitch attitude and to maintain heading followed at GA engagement. The GO AROUND mode is annunciated on the FMA by a GA message as vertical mode and HDG HOLD message as lateral mode. The GO AROUND mode is cancelled by selecting another vertical mode, engaging TCS, pushing the STBY pb or engaging the AP. Mod: 5948 . 1.04.50. AFCS P1 ALTITUDE ALERT 001 APR 11 AA The purpose of the altitude alert function is to alert the crew by activation of a visual signal and an aural signal when the aircraft is reaching or leaving the preselected altitude. Preselection is displayed with a bug and a read out above the PFD altimeter scale : - In cyan when selected through the ATL SEL rotary knob. - In magenta when managed by the FMS The visual signal consists of a flashing amber readout surrounding, above the PFD altitude scale, when altitude is between H + 250 ft and H + 1000 ft or between H - 250 ft and H - 1000 ft. The aural signal consists in a “C chord” signal of 1 s duration which is activated each time the aircraft enters one of the two altitude zones defined above. Mod: 5948 . 1.05.00 COMMUNICATIONS P1 001 CONTENTS APR 11 AA 1.05.00 CONTENTS 1.05.10 GENERAL 10.1 GENERAL DESCRIPTION 10.2 RADIO MANAGEMENT FUNCTION 10.3 CONTROLS 10.4 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 1.05.20 TRAFFIC ALERT AND COLLISION AVOIDANCE SYSTEM (TCAS) 20.1 DESCRIPTION 20.2 CONTROLS 20.3 OPERATION 20.4 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING Mod: 5948 . 1.05.10 COMMUNICATIONS P1 GENERAL 001 APR 11 AA 10.1 GENERAL DESCRIPTION The aircraft communication system provides: - radio communication between aircraft and ground stations - Interphone between: o Cockpit crew stations o Cabin attendant stations o Ground crew stations - Passenger address system - Distribution through loudspeakers of aural alerts generated by FWS and T2CAS. Note: As per regulations all communications are recorded on the Cockpit Voice Recorder The communication system comprises: As standard features: - Radio Management Application - VHF System - Passenger Address - Ground Crew Call System - Cabin and Flight Crew Call System - Cabin and Service Interphone - Audio Integrating - Static Discharger - Cockpit Voice Recorder As optional features: - HF System - SELCAL - Aircraft Communication Addressing of Reporting System (ACARS) - Announcement & Music Reproducing System For general communication architecture, see schematic p 27/28. Mod: 5948 GENERAL P 2/3 APR 11 001 1.05.10 Mod: 5948 RMS consists of two redundant RMA software applications, RMA1 and RMA2, which are hosted respectively inside Display Units 2 and 4. The aim of RMA is to manage sets of radio navigation and radio communication equipments and to provide pilots communication and navigation settings awareness on different displays. These functions, which are performed by the Radio Management Application (RMA), ensure the correct management and the information exchange involving input data and equipments. The Radio Management System (RMS) handles Radio COMMunication, Radio NAVigation and TCAS/XPDR through Virtual Control Panels (VCPs), Multi Function Control Panel (MCPs) and Multi Control Display Units (MCDUs). 10.2 RADIO MANAGEMENT FUNCTION AA COMMUNICATIONS 1.05.10 COMMUNICATIONS P4 GENERAL AA GENERAL ARCHITECTURE Mod: 5948 001 APR 11 . 1.05.10 COMMUNICATIONS P5 GENERAL 001 APR 11 AA VHF COMMUNICATION SYSTEM The aircraft is equipped with two identical VHF systems independent of each other. The VHF transceiver operates in the 118.00 to 136.975MHz range with 8.33 KHz spacing. The VHF 1 or VHF 2 transceiver allows to transmit and receive voice communications through acoustic equipment (boomset, headset, hand microphone, loud-- speakers and oxygen mask). Each system comprises a transceiver connected to his antenna and to the Radio Management Application. Mod: 5948 1.05.10 COMMUNICATIONS P6 GENERAL 001 APR 11 AA HF COMMUNICATION SYSTEM (optional) The aircraft is equipped with a single HF (or as option a second HF can be fitted) system designed to operate in the two following mode: - Amplitude Modulation (AM) - Single Side Band (SSB) This system allows two way voice communications in the 2 to 29.9999 MHz range. Each system comprises a transceiver connected to the single HF antenna and to the Radio Management Application. Note: During HF communications, ADFs are inhibited to avoid interferences. HF system is SELCAL capable. Mod: 5948 1.05.10 COMMUNICATIONS P7 GENERAL 001 APR 11 AA INTERPHONE SYSTEM - To interconnect all stations (ground crew stations + cockpit + cabin attendant): - Depress INT transmissions key on the Audio Control Panel - Use PTT pushbuttons. - Cockpit crew interphone Using boom set or oxy mask: - Set the RAD/INT selector on “INT” position (on Audio Control Panel) without use of PTT pushbutton or, - Set the PTT selector (control wheels) in the forward position regardless of the RAD/INT selector position Note: In case of use of oxygen mask it is recommended to put the RAD/INT (on Audio Control Panel) to neutral position and to use the control wheels PTT forward, to avoid permanent breathing noise. - To call cabin attendant from the cockpit (see 1.05.10 p 22): - Depress the ATTND pushbutton (overhead panel) for a normal call, or press the ATTND pushbutton three times successively for an emergency call. A single chime (or three for an EMER call) is generated in the cabin and the flight deck green light illuminates on the cabin attendant panels. As soon as the cabin attendant selects CALL, the flight deck green light extinguishes. - To call cockpit from cabin attendant station: - Depress CALL pushbutton (besides the hostess panel) for a normal call or depress the EMER pushbutton for an emergency call. Associated ATTND light illuminates on overhead panel and a door bell is generated by the MFC. By pressing RESET, both visual and aural calls are cancelled. - To call the ground crew from the cockpit (see 1.05.10 p 22) : - Depress MECH pushbutton (overhead panel) A horn call is generated in the nose gear bay. - To call cockpit from ground crew: In case of ground crew call MECH pushbutton illuminates blue on overhead panel and a door bell is generated by the MFC. By pressing RESET, both visual and aural calls are cancelled. Mod: 5948 1.05.10 COMMUNICATIONS P8 GENERAL 001 APR 11 AA PASSENGER ADDRESS SYSTEM The passenger address system allows the crew and the cabin attendant to make announcements to the passengers. Passenger address system also generates single chime in the cabin. The passenger address system is connected to : - The RCAU which allows the cockpit crew to make announcements to the passengers by selecting PA key on audio control panel. - The cabin attendant handset - The cabin attendant call pb distributed in the cabin for the passengers - The cabin attendant call pb in the cockpit - The NO SMOKING/FASTEN SEAT BELTS controls - The cockpit voice recorder - Loudspeakers distributed in the cabin (one of them being installed in the toilet) DISTRIBUTION OF AURAL ALERTS Generated by FWS (refer to chapter 1.02) Generated by T2CAS (refer to 1.15) Mod: 5948 1.05.10 COMMUNICATIONS P9 GENERAL 001 APR 11 AA 10.3 CONTROLS AUDIO CONTROL PANEL 1 Volume control knob To control reception volume for associated communication or navigation facility. 2 Transmission keys To select the individual communication facility for transmission, six interlocked keys are provided. Only one key can be engaged at a time. It illuminates white when selected. 3 VOICE ONLY key When depressed, it inhibits NAV receivers station identification by activating a band cut off filter above 1020 Hz. Voice only light illuminates amber on Audio Control Panel. 4 INT/RAD selector Provides selection of transmission mode when using OXY MASK or BOOM SET mike. INT Hot mike position. Interphone is always operative between, crew stations. Other transmissions require selecting a transmission key and using a PTT pushbutton. NEUTRAL Interphone is inoperative. Other transmissions require selecting a transmission key and using a PTT pushbutton. RAD This position is required to automatically connect for transmissions BOOM SET and OXY MASK mikes without using a PTT pushbutton, when released the selector is spring-- loaded to NEUTRAL. Note : Recovering boomset/micro function when the oxygen mask is out of is container : cf 1.07.20. Mod: 5948 1.05.10 COMMUNICATIONS P 10 GENERAL 001 FEB 12 AA R MCP The Multi Function Control Panel (MCP) allows to modify some communications parameters via a keyboard. R Refer to Flight instruments chapter for more details about MCP. VCP The Virtual Control Panel (VCP) is a part of MFD. It is displayed on the bottom right of MFD. VCP communication page is displayed by pressing ”COM” on the MCP. VHF or HF pages can be selected by using arrow push buttons on MCP to select the communication equipment required. Selection on one VCP is simultaneously updated on the opposite crew member display. Mod: 5948 1.05.10 COMMUNICATIONS P 11 001 GENERAL APR 11 AA ATC CONTROL ATC Controls are located on XPDR tab of VCP (Virtual Control Panel) which is part of MFD. (1) XPDR 1 or 2 Select active transponder via MCP or MCDU. (2) XPDR Mode selection ON : Transponder is active. STBY : Power is applied to the system but prevents it from transmitting. ALT OFF : Altitude reporting is deactivated. (3) Code Display Transponder code entered via MCP or MCDU. (4) IDENT button When activated through MCP or MCDU, allows transmission of IDENT. Note : - Button visual description : - Circle : Filled color : Black (inactive mode), Cyan (selected mode), amber (failure) - Square : ticked cyan (active), not ticked (stand by) - XPDR is configured through MCDU by selecting RMS menu then XPDR page. Code, Mode, Altitude Reporting, Flight ID or Selected XPDR functions can be changed on the XPDR page. Mod: 5948 1.05.10 COMMUNICATIONS P 12 GENERAL 001 APR 11 AA COMMUNICATION MCDU page (all information are reported on the VCP) (1) Transponder code can be set from scratchpad by activating the appropriate LSK. Mod: 5948 1.05.10 COMMUNICATIONS P 13 GENERAL 001 FEB 12 AA XPDR MCDU page (all information are reported on the VCP) R (1) Transponder CODE can be set from scratchpad by activating the appropriate LSK. (2) XPDR MODE selection with LSK. ON: STBY: Transponder is active. Power is applied to the system but prevents it from transmitting. (3) ALT selection with LSK. ALT OFF: Altitude reporting is deactivated. (4) FLT ID Flight number can be set from scratchpad by activating the appropriate LSK. (5) XPDR SEL with LSK. Transponder Selection (6) IDENT with LSK. R(7) EMER Displays automatically transponder emergency code 7700 in amber, to be activated has to be confirmed by pressing on the EXECute key on MCDU. Mod: 5948 1.05.10 COMMUNICATIONS P 14 GENERAL 001 APR 11 AA VHF CONTROL VHF VCP page VCP VHF page allows managing VHF 1 and 2 frequencies. (1)Active frequency window, allows setting a new active frequency by clicking on it (MCP or MCDU). (2) Transfer switch, clicking on it transfers stand by frequency to active(MCP or MCDU). (3) Stand by frequency windows, allows setting a new stand by frequency by clicking on it (MCP or MCDU). COMMUNICATION MCDU page (1) Active frequency can be set directly from scratchpad by activating the appropriate LSK. Mod: 5948 1.05.10 COMMUNICATIONS P 15 GENERAL 001 APR 11 AA VHF MCDU page More parameters are available on MCDU VHF page: (1) Active frequency can be set directly from scratchpad, standby, preset or emergency frequency by activating the appropriate LSK. (2) Stand by frequency, set from scratch pad or preset. (3) R3 LSK allows access to preset frequencies. (4) R5 LSK allows turning off/on the squelch. (5) R6 LSK if depressed will automatically tune emergency frequency 121.500 as active. IESI (1) VHF 1 frequency display (2) SEL Multifonction pushbutton allowing selection of VHF (3) SET Multifunction rotary knob allowing tuning of VHF frequency Mod: 5948 1.05.10 COMMUNICATIONS P 16 GENERAL 001 APR 11 AA HF CONTROL HF VCP page (1) Active frequency box, allows setting a new active frequency by clicking on it. (2 Transfer switch, clicking on it transfers stand by frequency to active. (3) Stand by frequency box, allows setting a new stand by frequency. (4) Display of selected modulation (USB or AM). (5) Display of selected power output intensity (LO, MED, HI). (6) Squelch attenuation intensity, allows setting squelch attenuation by clicking on selected circle. COMMUNICATION MCDU page (all information are reported on the VCP) (1) Active frequency can be set directly from scratchpad by activating the appropriate LSK. Mod: 5948 1.05.10 COMMUNICATIONS P 17 001 GENERAL APR 11 AA HF MCDU page (1) Active frequency (green), set from scratchpad or from stand by frequency (2) TX (Green) transmission in progress (3) Stand by frequency, set from scratchpad, if R1 LSK pressed, it becomes active (4) Access to PRESET frequencies (5) By pressing R5 LSK sets required squelch attenuation intensity (6) By pressing R6 LSK sets the HF output power (7) Allows changing modulation type (USB or AM) (8) Mode selection, in standby the HF is muted VHF& HF Mod: 5948 1.05.10 COMMUNICATIONS P 18 GENERAL 001 APR 11 AA VHF & HF CONTROL SUM UP T: Tunable parameter. I: Information only. N: No information. (*): Stored preset can be selected on the Preset Page and used in appropriate tuning page as tuning parameters (Active and Standby Frequency). Mod: 5948 Mod: 5948 MCDU SUM UP AA GENERAL COMMUNICATIONS P 19/20 APR 11 001 1.05.10 . 1.05.10 COMMUNICATIONS P 21 GENERAL 001 APR 11 AA PTT SELECTOR The outboard horn of both control wheels is provided with a PTT selector controlling the transmission mode and effective only when BOOM SET or OXY MASK mike is used for transmission. Interphone Forward position springloaded to neutral transmission of flight interphone selected. INT transmission key has not to be used to communicate between cockpit crew stations. Neutral Center position. No transmission. Reception is normal. Hand microphones are connected for transmission when keyed. Radio Backward position springloaded to neutral. BOOM SET or OXY MASK is connected for transmission over the selected communication equipment. RAD PTT SW on NOSE WHEEL STEERING CONTROL HANDWHELL When depressed, BOOM SET or OXY mike is connected for transmission over the selected communication equipment. Mod: 5948 1.05.10 COMMUNICATIONS P 22 GENERAL 001 APR 11 AA HEAD SET/BOOM SET PANEL/HAND MIC PANELS Allow connection of a boom set, a head set and a hand mike. LOUDSPEAKERS VOLUME KNOBS Communication reception over cockpit loudspeakers is controlled by an individual knob for each of the two cockpit loudspeakers. Note: - normal alert volume is always available regardless of knobs position. - during any transmission, the volume of both loudspeakers is muted. Mod: 5948 1.05.10 COMMUNICATIONS P 23 GENERAL AA 001 APR 11 AUDIO SEL PB(s) Controls functioning of associated RCAU processing board. NORM (pushbutton depressed) RCAU functions normally. FAULT illuminates amber and the FWS is activated when an associated RCAU processing board failure or power loss is detected. ALTN (pushbutton released) affected crew station is connected directly to VHF 1 if CAPT station is affected or VHF 2 if F/O station is affected. Volume is adjusted by affected loudspeaker volume control. Note: On the affected side PA, interphone and other VHF can not be used any longer. CALLS PB(s) ATTND call PB: Cyan “CALL” will illuminate and chimes will be generated when receiving a normal call from the flight attendant. Amber “EMER” will illuminate and chimes will be generated, when an emergency call has been made from the flight attendant handset. When depressed the pushbutton will generate a cockpit call at the flight attendant station. MECH call pushbutton: Cyan “CALL” will illuminate and chimes will be generated when receiving a Mechanic call. When depressed it will sound the horn in the nose wheel bay in order to draw ground crew attention. RESET pushbutton: Chimes will cease and the system will be rearmed for next call by depressing the RESET pushbutton Mod: 5948 1.05.10 COMMUNICATIONS P 24 GENERAL 001 APR 11 AA EMERGENCY BEACON The transmitter is located in the ceiling of the cabin between the passengers entry door and the toilet door. The antenna is located in the fairing ahead of the stabilizer fin. This system includes its own battery. AUTO transmission is made automatically on 121.5 MHz, 243 MHz and 406 MHz when deceleration exceeds 5 g (”X MIT ALERT” Iight illuminates amber). MAN allows commanded operation (”X MIT ALERT” Iight illuminates amber). AUTO TEST RST is used in case of undue alert (reset), or to test the Emergency beacon. Two cases are possible for the test: - Net work “X MIT ALERT” illuminates amber during 2 seconds. - Failure “X MIT ALERT” Iight flashes during 15 seconds. CAUTION: The test must not be performed in MAN mode. Aircraft on ground (and electrically supplied), when the emergency beacon is triggered after 30 seconds, the mechanic call horn is triggered too. Mod: 5948 1.05.10 COMMUNICATIONS P 25 GENERAL AA 10.4 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT VHF 1 VHF 2 CAPT audio system F/O audio system XPDR 1 XPDR 2 DC BUS SUPPLY (C/B) DC EMER BUS (on overhead panel VHF 1) DC BUS 2 (on overhead panel VHF 2) DC ESS BUS (on overhead panel CAPT) DC ESS BUS (on overhead panel F/O) DC EMER BUS (on overhead panel XPDR 1) DC BUS 2 (on averhead panel XPDR 2) CAPT MCP DC EMER BUS (on overhead panel CAPT MCP) F/O MCP DC ESS BUS (on overhead panel F/O MCP) DC BUS 2 (on overhead panel TCAS) DC ESS BUS (on overhead panel ATTND) DC ESS BUS (on overhead panel PUBLIC ADRESS) DC ESS BUS (on overhead panel HF 2) DC BUS 1 (on overhead panel HF 1) DC BUS 1 (on overhead panel SEL CAS) DC BUS 2 (on overhead panel VHF 3) TCAS (if installed) Attendant call Ground crew call HF 2 (when installed) HF 1 (when a second HF is installed) SELCAL (when installed) VHF 3 (when installed) CMU (when installed) MFC LOGIC See Chapter 1.01. Mod: 5948 DC BUS 2 (on overhead panel VHF) 001 APR 11 1.05.10 COMMUNICATIONS P 26 GENERAL 001 APR 11 AA SYSTEM MONITORING AUDIO SEL CAPT This caution is generated when CAPT audio fault is detected. The RCAU on the captain side has processing failure or power loss. Visual and aural alert are : - MC light flashing amber - “AUDIO SEL CAPT” amber message on EWD - Aural alert is Single Chime (SC) - Fault illuminates amber on capt audio sel pushbutton AUDIO SEL F/O This caution is generated when F/O audio fault is detected. The RCAU on the captain side has processing failure or power loss. Visual and aural alert are : - MC light flashing amber - “AUDIO SEL F/O” amber message on EWD - Aural alert is Single Chime (SC) - Fault illuminates amber on F/O audio sel pushbutton XPDR This caution is generated when a transponder (XPDR) fault is detected. Visual and aural alert are : - MC light flashing amber - “XPDR” amber message on EWD - Aural alert is Single Chime (SC) - Amber “XPDR 1(2) FAIL” label displayed on PFD - Amber indication on XPDR VCP VHF This caution is generated when one VHF is detected failed. Visual and aural alert are : - MC light flashing amber - “VHF” amber message on EWD - Aural alert is Single Chime (SC) - Amber “FAIL” on communication page of MCDU, amber display on VCP page. VHF1+2 This caution is generated when both VHF are detected failed. Visual and aural alert are : - MC light flashing amber - “VHF 1+2” amber message on EWD - Aural alert is Single Chime (SC) - Amber “FAIL” on communication page of MCDU, amber display on VCP page. Mod: 5948 1.05.10 COMMUNICATIONS P 27 GENERAL 001 APR 11 AA HF (only if HF installed) This caution is generated when one HF is detected failed. Visual and aural alert are : - MC light flashing amber - “HF” amber message on EWD - Aural alert is Single Chime (SC) - Amber “FAIL” on communication page of MCDU, amber display on VCP page. HF 1+2 (only if 2 HF installed) This caution is generated when both HF are detected failed. Visual and aural alert are : - MC light flashing amber - “HF 1+2” amber message on EWD - Aural alert is Single Chime (SC) - Amber “FAIL” on communication page of MCDU, amber display on VCP page. “RMS” This caution is generated when one RMS is detected failed. Visual and aural alerts are : - MC light flashing amber - “RMS” amber message on EWD - Aural alert is Single Chime (SC) “RMS 1+2” This caution is generated when both RMS are detected failed. Visual and aural alerts are : - MC light flashing amber - “RMS 1+2” amber message on EWD - Aural alert is Single Chime (SC) VHF EMITTING This caution is generated when VHF is emitting for more than 29 seconds. Visual and aural alert are : - MC light flashing amber - “VHF EMITTING” amber message on EWD - Aural alert is Single Chime (SC) HF EMITTING This caution is generated when HF is emitting for more than 29 seconds. Visual and aural alert are : - MC light flashing amber - “HF EMITTING” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 . 1.05.20 COMMUNICATIONS P1 001 TCAS APR 11 AA 20.1 DESCRIPTION The TCAS (Traffic alert and Collision Avoidance System) is a part of the T2CAS. The T2CAS includes the TCAS (Traffic alert and Collision Avoidance System) and the TAWS (Terrain Avoidance Warning System). The TCAS: - Detects any aircraft, equipped with transponders, flying in its vicinity - Displays potential and predicted collision targets - Issues vertical orders to avoid conflict. - The TCAS is independent from the ground-- based air traffic control system. The TCAS detection capability is limited to intruders flying within a maximum range of 100 NM (depending on aircraft configuration and external conditions), and within a maximum altitude range of 9900 feet (above and below the threatened aircraft). The TCAS is a single system consisting of: - One TCAS transmitter receiver, - One directional top antenna, - One omni directional bottom antenna, - Two ATC Mode S transponders, - Four ATC Mode S antennas. The TCAS system is interacting with: - two PDF, - two MFD, - two overhead speakers for voice messages. Mod: 5948 1.05.20 COMMUNICATIONS P2 001 TCAS APR 11 AA DEFINITIONS (1) Advisory A message given to the pilot containing information relevant to collision avoidance. (2) Corrective resolution advisory A resolution advisory that advises the pilot to deviate from current vertical speed, e.g., CLIMB when the aircraft is in level flight. (3) Intruder A target that has satisfied the TCAS threat detection logic and thus requires a traffic advisory. (4) Mode S Type of secondary surveillance radar (SSR) equipment which provides replies to mode A and Mode C interrogations and discrete address interrogations from the ground or air. (5) Preventive resolution advisory A resolution advisory that advises the pilot to avoid certain deviations from the current vertical speed because certain vertical speed restrictions exist. (6) Proximate traffic Nearby aircraft within ¦1200 ft and 6NM which are neither an RA nor a TA. (7) Resolution advisory (RA) Aural and visual information provided to the flight crew to avoid a potential collision. (8) Threat A target that has satisfied the threat detection logic and thus requires a resolution advisory. (9) Traffic advisory (TA) Information given to the pilot pertaining to the position of another aicraft in the immediate vicinity. The information contains no resolution information. Mod: 5948 1.05.20 COMMUNICATIONS P3 TCAS 001 FEB 12 AA 20.2 CONTROLS VIRTUAL CONTROL PANEL (VCP) R TCAS function and displays are configured through the Virtual Control Panel (VCP). TCAS is accessed by depressing twice the NAV pushbutton on the MCP Selection on one VCP is simultaneously updated on the opposite crew member display. TCAS function mode (STBY, AUTO, TA ONLY) are selected via TCAS tab and Traffic display mode via OVLY tab (NORM, ABOVE or BELOW). MCP The Multi Function Control Panel (MCP) allows setting TCAS parameters. R Refer to Flight instruments chapter for more details about MCP. Mod: 5948 1.05.20 COMMUNICATIONS P4 TCAS 001 FEB 12 AA MCDU R Note: At power up, the TCAS performs an auto test and in case of malfunction will display it on the TCAS part of the PFD. (1) TCAS mode (AUTO, TA ONLY or STBY) (2) TCAS display configuration (ABV, NORM or BLW). Mod: 5948 COMMUNICATIONS 1.05.20 P 5/6 TCAS AA MFD Navigation Display page R Mod: 5948 001 FEB 12 . 1.05.20 COMMUNICATIONS P7 TCAS 001 FEB 12 AA Indication display on PFD Current TCAS mode (as selected on VCP) and preventive or corrective indications are displayed on PFD. Resolution indications on VSI tape: - Resolution Advisory: The RA display is the instrument used to fly the TCAS resolution. The resolution required vertical speed is displayed on the PFD Vertical Speed Scale as a green segment. - Corrective RA: The pilot has to adjust the vertical speed by bringing the pointer back in the green segment. - Preventive RA: If in green segment, the pilot maintains the current vertical rate. TCAS status indications: R On VSI: (1) green segment (2) red segment Mod: 5948 1.05.20 COMMUNICATIONS P8 TCAS AA On PFD: Mod: 5948 001 APR 11 1.05.20 COMMUNICATIONS P9 TCAS 001 FEB 12 AA 20.3 OPERATION R The TCAS provides two levels of threat advisories : If the traffic gets between 20 and 45 seconds (depending on aircraft altitude) of projected Closest Point of Approach (CPA), it is then considered an intruder, and an aural and visual traffic advisory is issued. This level calls attention to a developing collision threat using the traffic advisory display and the voice message, “TRAFFIC TRAFFIC”. It permits mental and physical preparation for a possible maneuver to follow, and assists the pilot in achieving visual acquisition of the threat aircraft. If the intruder gets between 20 and 35 seconds (depending on aircraft altitude), of CPA, it is considered a threat and an aural and visual resolution advisory is issued. This level provides a recommanded vertical maneuver integrated on PFD and voice messages to provide adequate vertical separation from the threat aircraft, or prevents initiation of a maneuver that would place the TCAS aircraft in jeopardy. The TCAS resolution advisories are annunciated by the following voice messages, as appropriate : A B C D E F G H I “CLIMB, CLIMB” : (Climb at the rate depicted by the green (fly to) band on the TCAS VSI). ”DESCEND, DESCEND” : (Descend at the rate depicted by the green (fly to) band ) ”MONITOR VERTICAL SPEED” : Initial preventive RAs (adjust vertical speed to a value within the illuminated green band ). ”MAINTAIN VERTICAL SPEED, MAINTAIN” : (No crossing maintain rate RAs (corrective))). ”MAINTAIN VERTICAL SPEED, CROSSING MAINTAIN” : (Altitude crossing, maintain rate RAs (corrective)). ”CLEAR OF CONFLICT” : (Range is increasing, and separation is adequate, return to assigned clearance). ”CLIMB, CROSSING CLIMB, CLIMB, CROSSING CLIMB” : (Climb at the rate depicted by the green (fly to) band on the TCAS VSI). Safe separation will best be achieved by climbing through the threat’s flight path. ”ADJUST VERTICAL SPEED, ADJUST” : (Adjust vertical speed to a value within the illuminated green band ) ”DESCEND, CROSSING DESCEND, DESCEND, CROSSING DESCEND” : (Descend at the rate depicted by the green (fly to) band on the TCAS VSI) safe separation will best be achieved by descending through the intruder’s flight path. Mod : 5948 1.05.20 COMMUNICATIONS P 10 TCAS 001 APR 11 AA The following voice messages annunciate enhanced TCAS maneuvers when the initial TCAS RA does not provide sufficient vertical separation. The tone and inflexion must constate increased urgency. A B C D “INCREASE DESCENT, INCREASE DESCENT” : (descend at the rate depicted by the green (fly to) band on the TCAS VSI). Received after “DESCEND” advisory, and indicates additional descent rate required to achieve safe vertical separation from a maneuvering threat aircraft. ”INCREASE CLIMB, INCREASE CLIMB” : (climb at the rate depicted by the green (fly to) band on the VSI). Received after “CLIMB” advisory, and indicates additional climb rate required to achieve safe vertical separation from a maneuvering threat aircraft. ”CLIMB-- CLIMB NOW, CLIMB-- CLIMB NOW” : (climb at the rate depicted by the green (fly to) band on the TCAS VSI). Received after a “DESCENT” resolution advisory and indicates a reversal in sense is required to achieve safe vertical separation from a maneuvering threat aircraft. ”DESCEND-- DESCEND NOW, DESCEND-- DESCEND NOW” : (descend at the rate depicted by the green (fly to) band on the TCAS VSI). Received after a “CLIMB” resolution advisory and indicates a reversal in sense is required to achieve safe vertical from a maneuvering threat aircraft. All TCAS aural alerts are inhibited : - below 1100 ft AGL when aircraft is climbing - below 900 ft AGL when aircraft is descending Mod: 5948 1.05.20 COMMUNICATIONS P 11 001 TCAS APR 11 AA TCAS OPERATING CHARACTERISTICS S NON ICING CONDITIONS of inhibition CONFIGURATION FLAPS 0_ FLAPS 15_ TO FLAPS 15_ Approach FLAPS 30_ RA CLIMB RA INCREASE CLIMB AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED AUTHORIZED INHIBITED AUTHORIZED INHIBITED S ICING CONDITIONS of inhibition CONFIGURATION RA CLIMB RA INCREASE CLIMB FLAPS 0_ Z < 20 000 ft Z > 20 000 ft FLAPS 15_ TO FLAPS 15_ Approach FLAPS 30_ AUTHORIZED INHIBITED AUTHORIZED AUTHORIZED INHIBITED INHIBITED INHIBITED INHIBITED INHIBITED INHIBITED S The “increase climb” RA is inhibited for certain above conditions. In non altitude crossing encounters for which a “CLIMB” RA is posted, the threat may maneuver or accelerate toward own aircraft and cause a reduction in vertical separation despite the RA. Since the “increase climb” RA is inhibited, the climb RA remains posted. As soon as the threat passes throught own aircraft’s altitude, the RA sense will be reversed and a “DESCEND” RA will be posted. If the threat never crosses through, the “CLIMB” RA will remain posted for the duration of the encounter. S “DESCEND” RA’s are inhibited : - below 1200 ft AGL during a climb at take off - below 1000 ft AGL in approach during a descent S “INCREASE DESCEND” RA’s are inhibited - below 1650 ft AGL during a climb - below 1450 ft AGLduring a descent S All RA’s are inhibited : - below 1100 ft AGL during a climb - below 900 ft AGL during a descent S There can be a case where the threat aircraft track on altitude information is lost during an RA. In this case, the RA will terminate without a “CLEAR OF CONFLICT” annunciation. Mod: 5948 1.05.20 COMMUNICATIONS P 12 GENERAL 001 APR 11 AA 20.4 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT TCAS DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) DC BUS 2 (on overhead panel TCAS) - Nil - MFC LOGIC See chapter 1.01. SYSTEM MONITORING TCAS This caution is generated when a TCAS fault is detected. Visual and aural alert are : - MC light flashing amber - “TCAS” amber message on EWD - ”TCAS FAIL”amber label on PFD - Aural alert is Single Chime (SC) Mod: 5948 1.06.00 ELECTRICAL SYSTEM P1 CONTENTS 001 APR 11 AA 1.06.00 CONTENTS 1.06.10 GENERAL 1.06.20 20.1 20.2 20.3 20.4 20.5 DC POWER DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYTEM MONITORING LATERAL MAINTENANCE PANEL SCHEMATICS 1.06.30 30.1 30.2 30.3 30.4 AC CONSTANT FREQUENCY DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYTEM MONITORING LATERAL MAINTENANCE PANEL 1.06.35 AC/DC SCHEMATIC 1.06.40 40.1 40.2 40.3 40.4 AC WILD FREQUENCY DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYTEM MONITORING LATERAL MAINTENANCE PANEL 1.06.50 50.1 50.2 50.3 EXTERNAL POWER DESCRIPTION CONTROLS LATERAL MAINTENANCE PANEL 1.06.60 DISTRIBUTION EQUIPMENT LIST Mod: 5948 . 1.06.10 ELECTRICAL SYSTEM P1 CONTENTS 001 APR 11 AA The electrical power generation is provided by the following sources : - Main and emergency batteries Two engine-- driven DC starter/generators Two AC wild frequency generators Two external power units (AC and DC) In addition, two static inverters (supplied by the DC system) provide constant frequency AC power. The ACW electrical system can also supply DC electrical system through a transformer rectifier unit (TRU). The electrical distribution is ensured by busses which feed equipments. Two separate networks (left and right) run individually and can be connected in case of generation failure thanks to bus tie contactors (BTC). Mod: 5948 1.06.10 ELECTRICAL SYSTEM P2 GENERAL AA Mod: 5948 001 APR 11 1.06.20 ELECTRICAL SYSTEM P1 DC POWER 001 APR 11 AA 20.1 DESCRIPTION GENERATION (See AC - DC schematic section 1.06.35) The 28V DC may be normally provided by : - two engines driven starter/generators, - a ground external power unit. Three sources may be used for the 28VDC emergency supply : - one main battery - one emergency battery, excluding START function - one TRU BATTERIES A 24V Ni-- CD battery of 43Ah (main BAT) is provided for engine starting and for emergency power supply including propeller feathering. A 24V Ni-- CD battery of 17 Ah (emer BAT) which, in addition to its secondary role of avoiding power transients on critical equipment during engine starts, ensures power to the emergency network (EMER BUS and STBY BUS during starting and when OVRD UND/V pb is pressed in OVRD position) even if the main battery has been completely discharged by repeated start attempts. Batteries monitoring is performed by MFC which : * connects the battery to the associated DC BUS for charging, * analyses the charge current and/or associated DC BUS voltage so as to prevent an abnormal battery operating condition or thermal runaway. Mod: 5948 1.06.20 ELECTRICAL SYSTEM P2 DC POWER 001 APR 11 AA TRU A TRU is installed in order to preserve the batteries when DC power is under emergency supply conditions (both generators failed). In this configuration,emergency DC system can be supplied by the ACW electrical system, through the TRU. STARTER GENERATOR The two DC starter/generators are driven by the engine accessory gear boxes. Each generator is a long life brushes air cooled type and is rated to deliver : - Nominal output power : 12 KW (400A) - Nominal operating voltage : 27 to 31 V (nominal setting 30 V) Starter mode : In starting mode, the starter/generator is connected by the START contactor to : - The aircraft main battery through a BATTERY START CONTACTOR, or - The external power through an EXTERNAL POWER CONTACTOR or - The aircraft main battery and the other operating generator, on ground only (cross start). In starter mode, the starter/generator cranks the engine to the point of self sustaining (associated engine START ON light illuminated on the ENG START panel). At the end of the start sequence (45 % NH), the start contactor opens (associated engine START ON light extinguished). Generator mode : When the engine reaches 61.5% NH, the starter/generator is acting as a generator. Provided associated DC GEN pb is selected and EXT PWR is not used, each generator feeds associated DC BUS through a GENERATOR CONTACTOR (GC). A GENERATOR CONTROL UNIT (GCU) associated with each generator provides the control for the generator contactor and the start contactor. The GCU monitors the point of regulation, where the voltage is maintained constant as the load varies, and provides fault detection and protection for : S over/under voltage S over/under speed S differential fault current S generator overload S power and fault current limiting S reverse current S bus tie lock out S equalizing load (in case of BTC failed closed). The BUS TIE CONTACTOR (BTC) allows DC BUS 1 and 2 to be on line when only one generator is operating or when the aircraft is powered from EXT PWR. A single BUS POWER CONTROL UNIT (BPCU) provides the control for BUS TIE CONTACTOR, BATTERY START CONTACTOR, load shedding, EXTERNAL POWER functions, and DC SVCE BUS contactors. Mod: 5948 1.06.20 ELECTRICAL SYSTEM P3 DC POWER 001 FEB 12 AA DISTRIBUTION The aircraft DC distribution network consists of eleven busses : - two main busses : DC BUS 1 and 2 - HOT MAIN BAT BUS and HOT EMER BAT BUS - DC EMER BUS, DC ESS BUS and DC STBY BUS - UTLY BUS 1 and 2 - DC SVCE BUS - GND HDLG BUS DC BUS 1 and 2 The DC BUS 1 is normally supplied by the LH engine driven generator and the DC BUS 2 by the RH engine driven generator. In case of generator failure, the associated DC BUS will be automatically supplied by the other generator through the BUS TIE CONTACTOR. DC BUS 1 normally supplies : HOT EMER BAT BUS, DC EMER BUS, DC STBY BUS, UTLY BUS 1, INV 1 and DC SVCE BUS. DC BUS 2 normally supplies : HOT MAIN BAT BUS, DC ESS BUS, UTLY BUS 2, INV 2. HOT BAT BUSSES - HOT MAIN BAT BUS and HOT EMER BAT BUS are normally supplied by main DC busses. - In case of main DC busses failure or thermal runaway of one of the batteries, the associated HOT BAT bus is supplied by its respective battery. DC ESS BUS/DC EMER BUS/DC STBY BUS In normal operation, DC EMER BUS and DC STBY BUS are supplied from HOT EMER BAT BUS. DC ESS BUS is supplied from HOT MAIN BAT BUS. In case of thermal runaway of one of the two batteries, the associated busses are transferred to DC BUS 1 supply. If DC BUS 1 is not powered, these busses are transferred to DCBUS 2 supply, by the Main Bus Transfer Contactor. If Both DC generators are lost : - When TRU is operative, DC EMER BUS, DC ESS BUS can be supplied by the ACW electrical system, through the Transformer Rectifier Unit. - When TRU is not operative, the DC EMER BUS, DC ESS BUS are supplied by their R respective HOT BAT BUS. Note :During engine starts, or when cranking, DC STBY BUS is supplied by HOT EMER BAT BUS . INV 1 remains supplied by HOT MAIN BAT BUS. In the event that batteries are used as an emergency sources, DC STBY BUS is supplied by main battery. UTLY BUS 1 and 2 The UTLY BUS 1 and 2 supply non essential loads. They are supplied by the associated main DC BUS through UTLY BUS CONTACTORS (UBC(s)). The contactors are controlled by the BPCU so that the UTLY BUS(ES) can be automatically deenergized if the supply source becomes overloaded. Mod: 5948 1.06.20 ELECTRICAL SYSTEM P4 DC POWER 001 FEB 12 AA DC SVCE BUS The DC SVCE BUS supplies power in flight, and on ground during airplane servicing operations. The DC SVCE BUS can be supplied by : - DC BUS 1. The master sw is the DC SVCE/UTLY BUS pb. When selected on, the cabin attendant controls the DC SVCE BUS supply from a sw located on the cabin attendant control panel. - EXT PWR. Only the cabin attendant pb has control. The supply of the BUS may be performed with batteries switched OFF. GND HDLG BUS The GND HDLG BUS supplies the DC loads required for airplane servicing on the ground even with BAT sw selected OFF. Since these loads are not required during flight, the GND HDLG BUS is deenergized in flight. The GND HDLG BUS can be supplied : - When EXT PWR is available, from DC SVCE BUS. - When EXT PWR is not available, from HOT MAIN BAT BUS provided : F Cargo door operating panel door is open (micro switch), or F Refueling panel is open (micro switch), or F Entry door is open (micro switch). R TRANSFER (see schematics p. 20 to p. 25) With all switches in normal position, the DC power transfer is achieved by automatic opening and/or closure of electrical contactors according to the particular electrical conditions. - On ground R F When EXT PWR is connected (p. 20) F When hotel mode is running (p. 21) R Note : The electrical power transfer is achieved in the same way as in flight as long as EXT POWER is not connected. - In flight F Both engine driven generator operating (p. 22) R * The engine driven generator 1 supplies the DC BUS 1, * The engine driven generator 2 supplies the DC BUS 2, * The BTC is open. R F If one engine driven generator fails (p. 23) * The BTC closes (BTC green flow bar illuminates), * The entire electrical network is supplied by the remaining engine driven generator. F If both engine driven generators fail (p. 24) R * DC ESS BUS, DC STBY BUS are supplied from the main battery, or from the TRU, if selected ON. * DC EMER BUS is supplied from the emergency battery or from the TRU, if selected ON. R F If both engine driven generators fail and TRU is inoperative (p. 25) * When DC STBY BUS reaches undervoltage (amber UNDV light comes ON), this bus may be recovered by selecting OVRD UND/V pb. Mod: 5948 1.06.20 ELECTRICAL SYSTEM P5 DC POWER 001 APR 11 AA 20.2 CONTROLS GENERATION 1 DC GEN pb Controls the energization of associated generator and the resetting of the protection system after failure. ON (pb pressed in) Associated generator is energized and associated generator contactor closes if the network electrical parameters (and S/G parameters) are normal. OFF (pb released) associated generator is deenergized and associated generator contactor is opened. The OFF light illuminates white. FAULT illuminates amber and the FWS is activated in event of : - A protection trip initiated by the associated GCU. If it is caused by a generator underspeed, reset will be automatic. For the other cases, a manual reset has to be performed ( but can lead to a loss of the opposite generator). - An opening of a generator contactor except if pb is selected OFF. In both cases, the BUS TIE CONTACTOR closes and affected DC BUS is automatically supplied from the remaining generator. BTC does not operate in case of DC BUS overload. Mod: 5948 1.06.20 ELECTRICAL SYSTEM P6 DC POWER 001 APR 11 AA 2 BTC pb This guarded pb controls the DC BUS TIE CONTACTOR (BTC) which, when closed, connects both main DC BUSSES. NORM (released) The BPCU automatically controls the BTC - In normal conditions with both generators operating, the BTC is opened allowing isolated operation of both generator circuits. - In case of external power operation, or single generation, the BTC is automatically closed, the flow bar is illuminated. ISOL (pressed in) The BTC is opened. ISOL light illuminates white. 3 EXT PWR pb AVAIL 4 Illuminates green when conditions of DC external power connection are met. ON Allows to connect DC external power. Refer to EXTERNAL PWR section for more informations. DC SVCE/UTLY BUS pb Controls connection/disconnection of DC SVCE BUS and both UTLY BUSSES to associated main DC BUSSES. NORM (pb pressed in) DC SVCE BUS and both UTLY BUS are available unless a load shed signal is provided by the BPCU. OFF (pb released) DC SVCE BUS and both UTLY BUSSES are disconnected from associated main DC BUS. The OFF it illuminates white. SHED Illuminates amber and the FWS is activated when a load shed condition controlled by the BPCU is present and at least one UTLY BUS is disconnected from associated main DC BUS. Mod: 5948 1.06.20 ELECTRICAL SYSTEM P7 DC POWER 001 APR 11 AA DISTRIBUTION 1 DC BUS OFF lights Illuminates amber when associated main DC BUS is not supplied. If one DC BUS is OFF, the FWS will be activated. 2 BAT CHG pbs Controls the operation of the associated BATTERY CHARGE CONTACTOR. ON (pb pressed in) The contactor is controlled by the MFC. Contactor is closed in normal operation, it opens in case of : - Thermal runaway of battery - Undervoltage of DC MAIN BUS (<25 V) - Start sequence initiated (in this case, both BCC are opened, and closed when start rotary selector leaves START or CRANK position). - An OVRD signal on BAT switch OFF (pb released). The charge contactor is opened on demand. The OFF light illuminates white. FAULT - Illuminates amber and the MFC is activated in event of : - An overheat detected by the MF. In this case, the charge contactor automatically opens. - A failure of the charge contactor. Mod: 5948 1.06.20 ELECTRICAL SYSTEM P8 DC POWER AA 3 4 5 6 TRU pb NORM 001 APR 11 (pb released) - One engine driven generator operating : S DC EMER and DC STBY BUS are supplied from HOT EMER BAT BUS. - Both engine driven generators failed : S DC EMER is supplied from HOT EMER BAT BUS S INV 1, DC STBY BUS and DC ESS BUS are supplied from HOT MAIN BAT BUS ON (pb pressed in). The TRU is connected to ACW BUS 2. ON It illuminates white. Arrow ! illuminates amber when supply of DC EMER BUS, DC STBY BUS, INV 1 and DC ESS BUS from TRU is effective. Emergency supply ind Right arrow illuminates amber when the DC ESS BUS or INV 1 are supplied from the MAIN BAT. Left arrow illuminates amber when the DC EMER BUS or INV 1 are supplied from the EMER BAT. OVRD pb When on batteries supply, this guarded pb allows to transfer the DC STBY BUS and the INV 1 from HOT MAIN BAT BUS to HOT EMER BAT BUS. NORM (pb released) The DC STBY BUS and INV 1 are supplied from the same source as DC ESS BUS. OVRD (pb pressed in) The DC STBY BUS and INV 1 are supplied from the same source as DC EMER BUS. OVRD it illuminates white (see p 21). UNDV The light illuminates amber, to indicate that DC STBY BUS voltage is below 19.5 V. OVRD may be used as necessary. BAT toggle sw The BAT three positions toggle sw is used to provide DC electrical power : - from the emer battery to the EMER BUS, - from the main battery to the ESS BUS, and DC STBY BUS, and through the INV 1, to the AC STBY BUS. OFF ESS BUS, DC STBY BUS and INV 1 are isolated from the HOT MAIN BAT BUS. DC EMER BUS is isolated from the HOT EMER BAT BUS. ON With engine driven generators OFF and EXT PWR off, ESS BUS, STBY BUS and INV 1 are supplied from the HOT MAIN BAT BUS, EMER BUS is supplied from the HOT EMER BAT BUS. With generation other than battery available, ESS BUS is supplied by the HOT MAN BAT BUS ; EMER BUS and STBY BUS are supplied by the HOT EMER BAT BUS. OVRD Allow to be sure that EMER BUS and ESS BUS are supplied by their respective battery by overriding all protections. This position is protected by a toggle guard. Note : DC STBY BUS is supplied by EMER BAT. Mod: 5948 1.06.20 ELECTRICAL SYSTEM P 9/10 001 DC POWER APR 11 AA 7 DC AMP ind. Indicates the charge (CH) discharge (DCH) current of the selected battery. 8 BAT AMP reading selector Enables to select the battery checked by the ammeter (7). CABIN ATTENDANT PANEL DC SVCE BUS pb Controls the supply of the DC SVCE BUS. Note : - Without GPU (DC BUS 1 supplying) DC SVCE BUS will be supplied if both the cockpit DC SVCE/UTLY BUS and the cabin attendant panel DC SVCE BUS are selected. As soon as one of the two pb is selected OFF, the bus is isolated. - With GPU (direct supplying) DC SVCE BUS is directly supplied provided Cabin attendant panel pb is ON. If the DC SVCE BUS cabin attendant panel is on SHED position, cargo door opening, internal ligthing and refuelling panel are not supplied. ON (pb pressed in) The light illuminates green whenever a power source is available on the aircraft. OFF (pb relased) The DC SVCE BUS is disconnected from the available power source. The ON light extinguishes. SHED Illuminates amber when : - DC source is available and the pb is relased, or the pb is pressed in and an overload shedding occurs. Mod: 5948 . ELECTRICAL SYSTEM 1.06.20 P 11/12 DC POWER AA INDICATING DC INFORMATION Mod: 5948 001 APR 11 . ELECTRICAL SYSTEM 1.06.20 P 13/14 DC POWER AA INDICATING BATTERIES INFORMATION Mod: 5948 001 APR 11 . 1.06.20 ELECTRICAL SYSTEM P 15 DC POWER 001 APR 11 AA 20.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS Generator Control Unit 1 (C/B) DC EMER BUS (on lateral panel GCU GEN 1) AC BUS SUPPLY (C/B) - Nil - Generator Control Unit 2 DC ESS BUS (on lateral panel GCU GEN 2) - Nil - Bus Power Control Unit DC EMER BUS (on lateral panel BPCU DC) - Nil - Main Battery CHG IND DC ESS BUS (on lateral panel CHG IND) - Nil - Emer Battery CHG IND DC EMER BUS (on lateral panel CHG IND) - Nil - Ess BUS and INV1 on main Bat ind (arrow) DC ESS BUS (on lateral panel IND) - Nil - Emer Bus on Bat ind (arrow) HOT EMER BAT BUS (on lateral panel or EMER BAT BUS IND) - Nil - Emer Bat Voltage ind HOT EMER BAT BUS (on lateral panel IND) - Nil - DC BUS 1 OFF IND DC EMER BUS (on lateral panel DC BUS 1 CAUTION BUS 1) - Nil - DC BUS 2 OFF IND DC EMER BUS (on lateral panel DC BUS 2 CAUTION BUS 2) - Nil - Main Bat Voltage ind HOT MAIN BAT BUS (on lateral panel IND) - Nil - DC STBY BUS undervoltage and OVRD ind DC EMER BUS (on lateral panel UNDV and OVRD IND) - Nil - DC STBY BUS control DC EMER BUS (on lateral panel CTL) - Nil - Ground Handling bus on Bat XF relay HOT MAIN BAT BUS (on lateral panel RLY) - Nil - MFC LOGIC See chapter 1.01 Mod: 5948 1.06.20 ELECTRICAL SYSTEM P 16 DC POWER 001 APR 11 AA SYSTEM MONITORING ELEC DC GEN 1+2 This warning is generated when both DC generation channels are inoperative. Visual and aural alerts are : - MW light flashing red - “ELEC DC GEN 1+2” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) - DC BUS 1(&2) OFF legend in amber boxes on SD Electrical System page - DC GEN FAULT legend in an amber circle on SD Electrical System page - FAULT light of DC GEN pb illuminates amber on overhead panel - DC BUS OFF caution lights illuminate amber on overhead panel ELEC DC 1(2) This caution is generated when DC BUS 1(2) is not supplied. Visual and aural alerts are : - MC light flashing amber - “ELEC DC 1(2)” amber message on EWD - Aural alert is Single Chime (SC) - DC BUS 1(2) OFF legend in an amber box on SD Electrical System page - DC BUS 1(2) OFF caution light illuminates amber on overhead panel ELEC DC GEN This caution is generated when one DC generation channel is inoperative. Visual and aural alerts are : - MC light flashing amber - “ELEC DC GEN” amber message on EWD - Aural alert is Single Chime (SC) - DC BUS 1(2) OFF legend in amber boxes on SD Electrical System page - DC GEN 1(2) FAULT label in amber circle on SD Electrical System page - FAULT light of DC GEN 1(2) pb illuminates amber on overhead panel - DC BUS 1(2) OFF caution lights illuminate amber on overhead panel ELEC DC EMER This caution is generated when DC EMER BUS is no longer supplied. Visual and aural alerts are : - MC light flashing amber - “ELEC DC EMER” amber message on EWD - Aural alert is Single Chime (SC) - “EMER BUS” label in an amber box on SD Electrical System page - EMER BUS light illuminates amber on overhead panel Mod: 5948 1.06.20 ELECTRICAL SYSTEM P 17 DC POWER 001 APR 11 AA ELEC DC ESS This caution is generated when DC ESS BUS is no longer supplied. Visual and aural alerts are : - MC light flashing amber - “ELEC DC ESS” amber message on EWD - Aural alert is Single Chime (SC) - “ESS BUS” label in an amber box on SD Electrical System page - ESS BUS light illuminates amber on overhead panel ELEC DC SHED This caution is generated when DC BUS is automatically shed after a source overload. Visual and aural alerts are : - MC light flashing amber - “ELEC DC SHED” amber message on EWD - Aural alert is Single Chime (SC) - “SHED” label displayed in amber on SD Electrical System page - SHED light of DC SVCE BUS pb illuminates amber on overhead panel ELEC BAT CHG This caution is generated in case of an incipient battery thermal runaway or a charge contactor failure. Visual and aural alerts are : - MC light flashing amber - “ELEC BAT CHG” amber message on EWD - Aural alert is Single Chime (SC) - “CHG FAULT” label displayed in amber on SD Electrical System page - FAULT legned of BAT CHG pb illuminates amber on overhead panel ELEC BAT DISCH This caution is generated in case of battery(ies) discharge in flight (but DC main sources available). Visual and aural alerts are : - MC light flashing amber - “ELEC BAT DISCH” amber message on EWD - Aural alert is Single Chime (SC) - Amber filled arrow displayed on SD Electrical System page ELEC CHG LOSS This caution is generated in case of a loss of charge Visual and aural alerts are : - MC light flashing amber - “ELEC CHG LOSS” amber message on EWD - Aural alert is Single Chime (SC) - “CHG FAULT” label displayed in amber on SD Electrical System page Mod: 5948 1.06.20 ELECTRICAL SYSTEM P 18 DC POWER 001 APR 11 AA 20.4 LATERAL MAINTENANCE PANEL On LH maintenance panel, a rotary selector is provided, with several indicators. The maintenance panel is protected by a transparent cover to avoid unintended inflight operation. CURRENT CHECK 1 2 3 Rotary Selector Allows to connect selected pick-- up points of the electrical network to the indicators. “GEN” position selects DC generator on DC indicators. DC voltage indicator Indicates the voltage at pick up point selected by the rotary selector. Normal readings are : - For battery without load : 25 to 28 volts - For battery under load : 23 to 28 volts DC Current indicator Indicates the current generated by selected sources. Normal reading is for each generator : less than 300 A. Mod: 5948 1.06.20 ELECTRICAL SYSTEM P 19 DC POWER 001 APR 11 AA DC UTLY/SVCE/STBY CONTACTORS MALFUNCTION INDICATION AND DC FEEDERS OVHT DETECTORS Electrical malfunctions are indicated by MFC on the “BASIC MEMORY” MCDU menu. Selection of MISC 1(2) menu gives information on DC UTLY/SVCE/STBY contactors and DC FEEDERS OVHT detectors. Mod: 5948 1.06.20 ELECTRICAL SYSTEM P 20 DC POWER AA 20.5 SCHEMATICS Mod: 5948 001 APR 11 1.06.20 ELECTRICAL SYSTEM P 21 DC POWER AA Mod: 5948 001 APR 11 1.06.20 ELECTRICAL SYSTEM P 22 DC POWER AA Mod: 5948 001 APR 11 1.06.20 ELECTRICAL SYSTEM P 23 DC POWER AA Mod: 5948 001 APR 11 1.06.20 ELECTRICAL SYSTEM P 24 DC POWER AA Mod: 5948 001 APR 11 1.06.20 ELECTRICAL SYSTEM P 25 DC POWER AA Mod: 5948 001 APR 11 . 1.06.30 ELECTRICAL SYSTEM P1 AC CONSTANT FREQUENCY 001 APR 11 AA 30.1 DESCRIPTION GENERATION The source of constant frequency (400 Hz) AC power consists of two static inverters (INV). The inverters are rack mounted and cooled by forced air with provisions for natural convection cooling. The static inverter design characteristics are as follows : - Power 500 VA - Output voltage 115 V ± 4V and 26 V ± 1V - Frequency 400 Hz ± 5 Hz - Type single phase The two inverters are powered respectively from DC BUS 1 and DC BUS 2. The input voltage range is between 18 VDC and 31 VDC for satisfactory operation. In event of one DC BUS loss, corresponding inverter is not supplied, but corresponding AC BUS is supplied by AC BTR (BTC pb). In event of both DC BUS power loss, INV1 is automatically supplied by HOT MAIN BAT BUS, or by HOT EMER BAT BUS in OVRD configuration (for each bus when OVRD UNDV is selected) or by TRU when selected ON. The maximum power available on each 26 VAC BUS is 250VA. (See AC-- DC Schematic section 1.06.35) Mod: 5948 1.06.30 ELECTRICAL SYSTEM P2 AC CONSTANT FREQUENCY 001 APR 11 AA DISTRIBUTION (115 and 26 V) INV 1 normally supplies : - AC BUS 1 - AC STBY BUS INV 2 normally supplies : - AC BUS 2 In event of inverter failure or input power loss the associated AC BUS is isolated from affected inverter and, provided the BTC pb is not in ISOL position, the AC BUS 1 and 2 are automatically tied together by the BTR (Bus Tie Relay). In event of INV 1 failure or input power loss, AC STBY BUS is automatically supplied from INV 2. Mod: 5948 1.06.30 ELECTRICAL SYSTEM P3 AC CONSTANT FREQUENCY 001 APR 11 AA 30.2 CONTROLS 1 2 3 4 INV FAULT light Illuminates amber and the FWS is activated in case of an inverter failure or a loss of power supply. BUS OFF light IIluminates amber and the FWS is activated when associated AC BUS is deenergized. OVRD pb When on batteries supply, this guarded pb allows the INV 1 and hence the AC STBY BUS to be transfered from HOT MAIN BAT BUS supply to HOT EMER BATR BUS supply. NORM (pb released). The INV 1 and AC STBY BUS are supplied from the same source as DC ESS BUS. OVRD (pb pressed in). The INV 1 and AC STBY BUS are supplied from the same source as DC EMER BUS. OVRD light illuminates white. UNDV The light illuminates amber to indicate that the DC STBY BUS voltage is below 19.5V. INV 1 require 18 V for normal operation. OVRD may be used as necessary. DC BTC pb This guarded pb controls the AC BUS TIE relay (AC BTR) which, when closed, connects both main AC BUSSES. NORM (pb released). The BPCU automatically controls the BTC and a separate logic controls the AC BTR. * In normal conditions, with both inverters running, the AC BTR is open allowing isolated operation of both inverter circuits. * In case of inverter failure, the AC BTR is automatically closed after 10s with OVRD UNDV pb released. The INV FAULT light illuminates but associated BUS OFF light extinguishes after 10s. ISOL (pb pressed in). The AC BTR is locked open, ISOL light illuminates white. Mod: 5948 1.06.30 ELECTRICAL SYSTEM P4 AC CONSTANT FREQUENCY AA INDICATING AC BUS INVERTERS Mod: 5948 001 APR 11 1.06.30 ELECTRICAL SYSTEM P5 AC CONSTANT FREQUENCY 001 APR 11 AA 30.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT INV 1 + AC BUS 1 AC voltage and frequency ind. AC BUS 2 power supply 115 VAC AC BUS 2 power supply 26 VAC AC BUS 1 control and INV 1 caution AC BUS 1 caution relay AC BUS 1 caution light INV 2 + AC BUS 2 ACV and frequency ind. AC BUS 2 power supply 115 VAC AC BUS 2 power supply 26 VAC AC BUS 2 control and INV 2 caution AC BUS 2 caution relay AC BUS 2 caution light AC BUS 1 and 2 tie line 115 VAC AC BUS 1 and 2 tie line 26 VAC AC STBY BUS power supply 115 VAC AC STBY BUS power supply 26 VAC AC STBY BUS transfer relay Mod: 5948 DC BUS SUPPLY (C/B) - Nil - Nil - Nil DC EMER BUS (on lateral panel INC CAUTION and BUS SPLY RLY) - Nil DC EMER BUS (on lateral panel LT) - Nil - Nil - Nil DC ESS BUS (on lateral panel BUS CTL and INV CAUTION) - Nil DC EMER BUS (on lateral panel LT) - Nil - Nil - Nil - Nil DC EMER BUS (on lateral panel AC EMER and STBY BUS XFR RLY) AC BUS SUPPLY (C/B) 115 VAC EMER BUS (on lateral panel FREQ IND.) 115 VAC OUTPUT INV 1 (on lateral panel 115 VAC) 26 VAC OUTPUT INV 1 (on lateral panel 26 VAC) 115 VAC BUS 1 (on lateral panel RLY) - Nil 115 VAC BUS 2 (on lateral panel FREQ IND) 115 VAC OUTPUT INV 2 (on lateral panel 115 VAC) 26 VAC OUTPUT INV 2 (on lateral panel 26 VAC) - Nil 115 VAC BUS 2 (on lateral panel RLY) - Nil 115 VAC BUS 1 (on lateral panel 115 VAC) 26 VAC BUS 1 (on lateral panel 26 VAC) OUTPUT INV 1 or 2 (on lateral panel 115 VAC) OUTPUT INV 1 or 2 (on lateral panel 26 VAC) - Nil - 1.06.30 ELECTRICAL SYSTEM P6 AC CONSTANT FREQUENCY 001 APR 11 AA MFC LOGIC See chapter 1.01. SYSTEM MONITORING ELEC AC 1(2) This caution is generated when AC BUS 1(2) is not supplied Visual and aural alerts are : - MC light flashing amber - “ELEC AC 1(2)” amber message on EWD - Aural alert is Single Chime (SC) - “AC BUS 1(2) OFF” label in amber box on SD Electrical System page - “AC BUS OFF” light illuminates amber on overhead panel ELEC INV 1(2) This caution is generated in case of under/over voltage at INV 1(2) output. Visual and aural alerts are : - MC light flashing amber - “ELEC INV 1(2)” amber message on EWD - Aural alert is Single Chime (SC) - “INV 1(2) OFF” label in amber box on SD Electrical System page - “INV 1(2)” light illuminates amber on overhead panel Mod: 5948 1.06.30 ELECTRICAL SYSTEM P7 AC CONSTANT FREQUENCY 001 APR 11 AA 30.4 LATERAL MAINTENANCE PANEL On LH maintenance panel, a rotary selector is provided, with several indicators. The maintenance panel is protected by a transparent cover to avoid unintended inflight operation. CURRENT CHECK 1 Rotary Selector 2 Allows to connect selected pick-- up points of the electrical netwwork to the indicators “INV” position selects AC current on AC indicators. AC load indicator 3 Indicates in hundred percent the load of selected AC source. Normal reading : below 0.5. Frequency indicator 4 Indicates in Hz frequency of selected AC source. Normal reading : 400 Hz5 Hz. AC voltage indicator Indicates voltage on selected AC source. Normal reading : 115 V  4 V. Mod: 5948 . Mod: 5948 30.5 SCHEMATICS AA AC/DC SCHEMATIC ELECTRICAL SYSTEM P 1/2 APR 11 001 1.06.35 . 1.06.40 ELECTRICAL SYSTEM P1 AC WILD FREQUENCY 001 APR 11 AA 40.1 DESCRIPTION GENERATION The ACW generation system consists of two “propeller” driven 3 phases generators. Each generateor is a brushless, air cooled type and is rated to deliver 20 KVA for continuous operation. Nominal set voltage 115V / 200V. Normal operating frequency range : 341 to 488 Hz (70 to 100% NP) Each generator is controlled by a Generator Control Unit (GCU) which provides the following control and protection functions : S overvoltage S power and fault current limiting S bus tie lock out S undervoltage S differential protection S under frequency S open phase S overfrequency S voltage regulation The BPCU performs the functions required for control and protection of the EXT PWR, the BUS TIES (or BTC(S)) and SVCE BUS. The TRU allows the ACW generation system to partially energize the DC electrical system from ACW BUS 2. Mod: 5948 1.06.40 ELECTRICAL SYSTEM P2 AC WILD FREQUENCY 001 APR 11 AA DISTRIBUTION The aircraft ACW distribution network consists of three busses : - Two main busses ACW BUS 1 and 2 - ACW SVCE BUS. ACW BUS 1 and 2 The ACW BUS 1 is normally supplied by the generator driven by the LH generator and the ACW BUS 2 by the RH generator. Note : * in case of generator failure, the associated ACW BUS will be automatically supplied by the other generator through the BUS TIE CONTACTORS (1 and 2). *A soon as EXT PWR is connected, selected ON and checked “acceptable” in voltage, frequency, phase, and current by the PBCU, it has priority over the engine driven generators. ACW SVCE BUS The ACW SCVE BUS supplies power in flight, and on ground during airplane servicing operations. The ACW SVCE BUS can be supplied from EXT PWR or ACW BUS 1. A sw located on the cabin attendant panel controls the power to ACW SVCE BUS. * When the ACW BUS 1 is ON, power being supplied by the generator or EXT PWR through BTC 1, the ACW SVCE BUS is automatically fed from ACW BUS 1 through contactor GXC. * When the aircraft is operating from EXT PWR with ACW BUS 1 OFF, the ACW SVCE BUS is fed from EXT PWR through contactor EXC. Note : The ACW SVCE BUS is automatically shed when one generator is off line. Mod: 5948 1.06.40 ELECTRICAL SYSTEM P3 AC WILD FREQUENCY 001 APR 11 AA 40.2 CONTROLS 1 ACW GEN pb Controls the energization of associated generator and the resetting of the protection system after failure. ON (pb pressed in) Associated generator is energized and associated generator contactor closes if the network electrical parameters are normal. OFF (pb released) Associated generator is deenergized and associated generator contactor is open. OFF light illuminates white. FAULT Illuminates amber and the FWS is activated in event of : - A protection trip initiated by the associated GCU. If it is caused by a generator underspeed, reset will be automatic. For the other cases, a manual reset has to be performed. - An opening of a generator contactor except if pb is selected OFF. In both cases, the BTC(S) are closed and affected ACW BUS is automatically supplied from the remaining generator. The light extinguishes and the fault circuit is reset when the pb is cycled to the out position. 2 ACW BUS OFF light Illuminates amber and the FWS is activated when associated ACW BUS is not supplied. Mod: 5948 1.06.40 ELECTRICAL SYSTEM P4 AC WILD FREQUENCY 001 APR 11 AA 3 BTC PB This guarded PB controls the ACW BUS TIE CONTACTORS (BTC 1 and 2) which, when closed, connects both main ACW BUSSES in parallel. NORM (PB released) BPCU Automatically controls BTC 1 and 2 : S In normal conditions, wirth both generators running, BTC 1 and 2 are open, allowing individual operation of both generator circuits. S In case of external power operation, or single generator failure, BTC 1 and 2 are automatically closed. The flow bar is illuminated. ISOL (pb pressed in) BTC 1 and 2 are open, ISOL light illuminates white. 4 EXT PWR PB Refer to EXTERNAL POWER section. CABIN ATTENDANT PANEL ACW SVCE BUS pb Connects the ACW SVCE BUS to the EXT PWR source or to the ACW BUS 1 when it is energized. ON (pb pressed in) Whenever ACW power or external AC power of acceptable quality is available, the light illuminates green. OFF (pb released) The SVCE BUS is disconnected from the available power source. The ON light extinguishes. SHED Illuminates amber when : - the ACW source is available and PB is released, or - the PB is pressed in and ACW SVCE BUS is not powered (overload shedding for example). Mod: 5948 1.06.40 ELECTRICAL SYSTEM P 5/6 ACW WILD FREQUENCY 001 APR 11 AA INDICATING BAT Mod: 5948 . 1.06.40 ELECTRICAL SYSTEM P7 001 AC WILD FREQUENCY APR 11 AA 40.3 ELECTRICAL SUPPLY / SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT GCU of ACW GEN 1 GCU of ACW GEN 2 ACW BPCU ACW BUS 1 caution relay ACW BUS 1 caution light ACW BUS 2 caution relay ACW BUS 2 caution light ACW SVCE BUS shed relay Mod: 5948 DC BUS SUPPLY (C/B) DC ESS BUS (on lateral panel GCU ACW GEN 1) DC ESS BUS (on lateral panel GCU ACW GEN 2) DC ESS BUS (on lateral panel BPCU ACW) - Nil DC EMER BUS (on lateral panel LT) - Nil DC EMER BUS (on lateral panel LT) - Nil - AC BUS SUPPLY (C/B) - Nil - Nil - Nil ACW BUS 1 (on lateral panel RLY) - Nil ACW BUS 2 (on lateral panel RLY) - Nil ACW SVCE BUS (on lateral panel ACW SVCE BUS SHED CAUTION RLY) 1.06.40 ELECTRICAL SYSTEM P8 AC WILD FREQUENCY 001 APR 11 AA SYSTEM MONITORING ELEC ACW GEN 1(2) This caution is generated when one ACW generator channel is inoperative. Visual and aural alerts are : - MC light flashing amber - “ELEC ACW GEN 1(2)” amber message on EWD - Aural alert is Single Chime (SC) - “ACW GEN 1(2) FAULT” label under an amber semi circle on SD Elec page - FAULT light of ACW GEN 1(2) pb illuminates amber on overhead panel ELEC ACW 1(2) OFF This caution is generated when ACW BUS 1(2) is not supplied. Visual and aural alerts are : - MC light flashing amber - “ELEC ACW 1(2) OFF” amber message on EWD - Aural alert is Single Chime (SC) - “ACW 1(2) OFF” label in an amber box on SD Elec page - OFF light of ACW GEN 1(2) pb illuminates white on overhead panel ELEC ACW BUS 1+2 This caution is generated when both ACW BUS are not supplied. Visual and aural alerts are : - MC light flashing amber - “ELEC ACW BUS 1+2” amber message on EWD - Aural alert is Single Chime (SC) - “ACW GEN 1(&2) FAULT” label under amber semi circles on SD Elec page - FAULT lights of ACW GEN pbs illuminate amber on overhead panel Mod: 5948 1.06.40 ELECTRICAL SYSTEM P9 AC WILD FREQUENCY 001 APR 11 AA 40.4 LATERAL MAINTENANCE PANEL On LH maintenance panel, a rotary selector is provided, with several indicators. The maintenance panel is protected by a transparent cover to avoid unintended inflight operation. CURRENT CHECK 1 2 Rotary Selector Allows to connect selected pick-- up points of the electrical network to the indicators. “GEN” position selects AC WILD Generator on AC indicators. AC indicators Refer to AC CONSTANT FREQUENCY lateral maintenance panel description. ACW BUS TIE CONTACTORS OPERATING SELECTOR It is used to open the corresponding AC Wild bus tie contactor. Mod: 5948 . 1.06.50 ELECTRICAL SYSTEM P1 EXTERNAL POWER 001 APR 11 AA 50.1 DESCRIPTION The DC and ACW electrical power system can be supplied from ground power sources, connected via the separate “External Power” receptacles which are located on the lower right side of the fuselage, just aft of the nose gear. DC SUPPLY * The power is controlled via the BUS POWER CONTROL UNIT (BPCU) which provides protection for : - overvoltage - under voltage - overcurrent - incorrect polarity When the above conditions are in the correct status, EXT PWR is considered to be of acceptable quality. AVAIL light illuminates green in the “DC” EXT PWR pb. Ext DC AVAIL is although displayed on the SD Elec page. * The AVAIL light being illuminated, THE “DC” EXT PWR pb may be selected ON. The AVAIL light remains illuminated and the ON light illuminates blue. Note :As soon as EXT PWR is connected, checked acceptable by the BPCU and selected ON, it has priority over the engine driven generators AC SUPPLY * The power is controlled via the BUS POWER CONTROL UNIT (BPCU) which provides protection for : - voltage limits - phase sequence - frequency limits - open phase - overload When the above conditions are in the correct status, the EXT PWR is considered to be of acceptable quality. The AVAIL light illuminates green in the “ACW” EXT PWR pb and this pb may be selected ON in associated contactors are closed. Ext AC AVAIL is although displayed on the SD Elec page - ACW SVCE BUS pb on the cabin attendant panel may be selected ON : S AVAIL light remains illuminated S ON light illuminates blue Note :As soon as EXT PWR is connected, checked acceptable by the BPCU and selected ON, it has priority over the “propeller” driven generators. Mod: 5948 1.06.50 ELECTRICAL SYSTEM P2 EXTERNAL POWER 001 APR 11 AA 50.2 CONTROLS AC EXTERNAL POWER RECEPTACLE PANEL 1 2 3 Nose Landing Gear Service Light Switch Allows operation of the service light in the nose gear bay. ”AC Power not used” light (white) Is on when AC external power is connected and ACW SVCE BUS is not used. ”AC Connected” light (white) Is on when AC external power is connected. DC EXTERNAL POWER RECEPTACLE PANEL 1 2 3 4 “DC connected” light (white) Is on when DC external power is connected to the aircraft. ”DC Power not used” light (white) Is on when DC external power is connected to the aircraft, and DC SVCE BUS is not used. Interphone Jack Used by ground mechanic to connect a headset to communicate with crew. Pilot call button When pressed in, sends a call (aural and visual) to the cockpit : “Mechanic call” light illuminates on the overhead panel. Mod: 5948 1.06.50 ELECTRICAL SYSTEM P3 EXTERNAL POWER 001 APR 11 AA EXTERNAL POWER SD INDICATION “EXT PWR” amber label is displayed on SD CABIN page (at the top right of the plane). This label is displayed when the receptacle is not closed (without being necessarily powered). Mod: 5948 1.06.50 ELECTRICAL SYSTEM P4 EXTERNAL POWER 001 APR 11 AA 50.3 LATERAL MAINTENANCE PANEL On LH maintenance panel, a rotary selector is provided, with several indicators. The maintenance panel is protected by a transparent cover to avoid unintended inflight operation. CURRENT CHECK 1 2 3 Rotary Selector Allows to connect selected pick-- up points of the electrical network to the indicators. “EXT PWR” position indicates on DC or/and AC indicators. DC indicators Refer to DC power lateral maintenance panel description. ”AC indicators Refer to AC Constant frequency lateral maintenance panel description. Mod: 5948 1.06.60 ELECTRICAL SYSTEM P1 DISTRIBUTION EQUIPMENT LIST AA Note : “*” = option DC BUS 1 R NORM SPLY R R - TAWS ADVISORY Mod: 5948 001 FEB 12 1.06.60 ELECTRICAL SYSTEM P2 DISTRIBUTION EQUIPMENT LIST FEB 12 AA R R 1 Mod: 5948 001 1.06.60 ELECTRICAL SYSTEM P3 DISTRIBUTION EQUIPMENT LIST AA DC BUS 2 R NORM SPLY R NORM SPLY R NORM SPLY Mod: 5948 001 FEB 12 1.06.60 ELECTRICAL SYSTEM P4 DISTRIBUTION EQUIPMENT LIST AA R R R - *RATING - ERIU SPLY 77 ENGINE INDICATION Mod: 5948 - ENG1 - OIL PRESS/TEMP 001 FEB 12 1.06.60 ELECTRICAL SYSTEM P5 DISTRIBUTION EQUIPMENT LIST AA HOT EMER BAT BUS R R R - EMER BAT AMP IND - EMER BAT VOLT IND - EMER BAT ARROW R - ADC 1/ICP CAPT HOT SPLY Mod: 5948 001 FEB 12 1.06.60 ELECTRICAL SYSTEM P6 DISTRIBUTION EQUIPMENT LIST AA HOT MAIN BAT BUS R R - MAIN BAT IND ARROW - MAIN BAT VOLT IND Mod: 5948 001 FEB 12 1.06.60 ELECTRICAL SYSTEM P7 DISTRIBUTION EQUIPMENT LIST 001 FEB 12 AA DC EMER BUS - MCP CM1 - ENG FIRE EXTINGUISHING CTRL and IND R (and - WARNING on CLA-- ENG 1+2) R R - LP VALVES 1 and 2 AUX SPLY (back-- up DC BUS 1&2) Mod: 5948 1.06.60 ELECTRICAL SYSTEM P8 DISTRIBUTION EQUIPMENT LIST AA NORM SPLY R R R NORM SPLY AVNX (IMA) Mod: 5948 - CPM 1 - IOM-- DC 12 - IOM-- DC 13 001 FEB 12 1.06.60 ELECTRICAL SYSTEM P9 DISTRIBUTION EQUIPMENT LIST AA DC ESS BUS Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 10 DISTRIBUTION EQUIPMENT LIST AA NORM SPLY R AVNX (IMA) Mod: 5948 - CPM 2 / IOM-- S 2 - IOM-- DC 22 - IOM-- DC 23 001 FEB 12 1.06.60 ELECTRICAL SYSTEM P11 DISTRIBUTION EQUIPMENT LIST AA DC STBY BUS - CPM2 / IOM-- S2 AUX SPLY R Mod: 5948 001 FEB 12 1.06.60 ELECTRICAL SYSTEM P 12 DISTRIBUTION EQUIPMENT LIST AA DC SVCE BUS R Mod: 5948 - LEFT and RIGHT CABIN LAT LT 001 FEB 12 1.06.60 ELECTRICAL SYSTEM P13 DISTRIBUTION EQUIPMENT LIST AA DC UTLY BUS 1 Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 14 DISTRIBUTION EQUIPMENT LIST AA DC UTLY BUS 2 Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 15 DISTRIBUTION EQUIPMENT LIST AA DC GND HOLG BUS Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 16 DISTRIBUTION EQUIPMENT LIST AA 115V AC STBY BUS Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 17 DISTRIBUTION EQUIPMENT LIST AA 115V AC BUS 1 Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 18 DISTRIBUTION EQUIPMENT LIST AA 115V AC BUS 2 Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 19 DISTRIBUTION EQUIPMENT LIST AA 26V AC STBY BUS Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 20 DISTRIBUTION EQUIPMENT LIST AA 26V AC BUS 1 Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 21 DISTRIBUTION EQUIPMENT LIST AA 26V AC BUS 2 Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 22 DISTRIBUTION EQUIPMENT LIST AA 115V ACW BUS 1 Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 23 DISTRIBUTION EQUIPMENT LIST AA 115V ACW BUS 2 Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 24 DISTRIBUTION EQUIPMENT LIST AA 115V ACW SVCE BUS Mod: 5948 001 APR 11 1.06.60 ELECTRICAL SYSTEM P 25 DISTRIBUTION EQUIPMENT LIST AA *115V ACW SVCE BUS 2 Mod: 5948 001 APR 11 . 1.07.00 EMERGENCY EQUIPMENT P1 CONTENTS AA 1.07.00 CONTENTS 1.07.10 GENERAL 1.07.20 OXYGEN SYSTEM 20.1 DESCRIPTION 20.2 CONTROLS 20.3 ELECTRICAL SUPPLY/SYSTEM MONITORING 20.4 SCHEMATICS 1.07.30 Mod: 5948 EMERGENCY EVACUATION 001 APR 11 . 1.07.10 EMERGENCY EQUIPMENT P1 GENERAL 001 FEB 12 AA The aircraft is equipped with fire fighting, oxygen and first aid equipment, placed throughout the cabin, readily available for use in emergency. The emergency lighting system provides aircraft illumination when all other electrical power sources are no longer available. COCKPIT R R Each crew member station is provided with : - life jacket. - smoke goggles. - Quick donning oxygen mask supplied with gaseous oxygen from one rechargeable bottle. - Flash lights. - Protective gloves. A portable fire extinguisher and a crash axe are located at the bottom of the electric rack. Depending on versions, a smoke hood, located behind left crew member station, is available for crew member use. One plug type hatch located in the cockpit ceiling is provided as an emergency exit for the cockpit crew. One escape rope is located in a compartment on top of the electric rack near the exit. Steps are provided for hatch access in the corridor RH side. CABIN R The emergency equipment is strategically distributed throughout the cabin and stowed adjacent to the two cabin attendant stations. It contains : - portable fire extinguishers - protective breathing equipments - first aid kit - crash axe - life vests (stowed under each passenger seat and at the cabin crew stations) - oxygen supply for passengers. - Flash lights. Mod: 5948 SCHEMATICS Mod: 5948 AA GENERAL EMERGENCY EQUIPMENT P 2/3 APR 11 001 1.07.10 1.07.20 EMERGENCY EQUIPMENT P1 OXYGEN SYSTEM 001 APR 11 AA 20.1 DESCRIPTION (See schematic p 7/8) The system consists of a main system supplying the cockpit crew and the passengers and two portable units for the cabin attendants. A high pressure cylinder of 2180 l (77 cu.ft) capacity, supplies oxygen to the distribution system. Nominal charge pressure of 1850 PSI is reduced to 78 PSI in the distribution system. A discharge part is provided to face overpressures. CREW MEMBERS (See schematic p 9/10) The quick donning masks are stowed in readily accessible containers adjacent to each crew member seat. The mask harness inflates automatically when the mask is pulled out of the container and it can easily be donned with one hand. A mask mounted diluter demand regulator provides dilution and emergency pressure control : - In case of pressure drop, with the dilution control in the N (normal) position, diluted oxygen is provided to 3 cockpit cew for a duration of 120 mn at demand flow (10 minutes to descend from 25 000 ft to 13 000 ft and continuation of flight between 13 000 ft and 10 000 ft for 110 minutes). - In case of smoke or noxious gas emission, with the dilution control in the 100 % position, oxygen is provided to 3 cockpit crewr for a duration of 15 minutes at demand flow. CABIN ATTENDANT PORTABLE UNITS - two 120 l (4.25 cu ft) portable oxygen bottles are stowed under the cabin attendant seats. They permit a continuous diluted flow to both cabin attendants at 13 000 ft for a duration of 30 mn. Each of these bottles is equipped with a diluted oxygen mask. - Protective breathing equipments are located in the baggage box of the cabin. PASSENGERS The main system provides passenger protection through a PAX SUPPLY valve. It controls flow to oxygen masks installed under the hat racks. Oxygen system capability allows to supply 25 % of the passengers with a continuous diluted flow for a duration of 30 mn in case of pressure drop (4 minutes to descend from 25 000 ft to 13 000 ft, 26 minutes to continue the flight between 13 000 ft and 10 000 ft) in addition to the cockpit crew 120 minutes consumption. Mod: 5948 1.07.20 EMERGENCY EQUIPMENT P2 OXYGEN SYSTEM 001 APR 11 AA 20.2 CONTROLS OXYGEN PANEL 1 2 3 HP ind. Oxygen bottle pressure is displayed in PSI X 1000. MAIN SUPPLY pb Controls the low pressure supply solenoid valve. pb pressed in : The valve is open, low pressure oxygen is supplied to the cockpit crew oxygen masks. OFF : (pb released) the valve is closed. OFF illuminates white. LO PR : illuminates amber and the FWS is activated when a low pressure (below 50 PSI) is detected in the low pressure distribution circuit. PAX SUPPLY pb ON : pb released Mod: 5948 : (pb pressed in) Passengers supply valve is open. ON illuminates cyan. Passengers supply valve is closed. 1.07.20 EMERGENCY EQUIPMENT P3 OXYGEN SYSTEM 001 APR 11 AA COCKPIT CREW OXYGEN MASK The cockpit crew oxygen masks are of the quick donning inflatable harness type, stowed in a container at each crew station. It can be donned with one hand. A regulator is incorporated in the mask. Release clips 1 Squeezing the red release clips unlocks the container doors. It also enables automatic inflation of mask harness, provided that pb 4 is held in TEST position or mask is extracted from container. The blinker momentarily displays a yellow cross. 2 Blinker Displays a yellow cross when there is oxygen flow, and black when there is no oxygen flow. 3 N/100 % rocker Controls the selection of normal or 100% oxygen for mask delivery. It is locked in the 100% position by the UNLOCK rocker. 4 TEST/RESET pb Permits a test of oxygen flow without removing the mask from the container. It is springloaded to the RESET position. TEST provided MAIN SUPPLY pb is selected ON, oxygen flows through the mask. The blinker momentarily displays yellow cross, and the flow is audible. A lengthened hose is provided on the observer mask enabling access to the cargo with the mask. RECOVERING BOOMSET/MICRO FUNCTION WHEN THE OXYGEN MASK IS OUT OF ITS CONTAINER : Oxygen mask remaining out of its container : - Close the oxygen mask container doors. - Press the test push button in front of the container and release it, yellow cross disappears. The bommset/micro function is now recovered. Note : If the pilot wants to use the oxygen mask again and recover the mask micro, he has to open the container doors. Mod: 5948 1.07.20 EMERGENCY EQUIPMENT P4 OXYGEN SYSTEM 001 FEB 12 AA UNDERSIDE OF REGULATOR R 1 UNLOCK rocker Locks N/100% rocker at 100% position. When pressed, the rocker is released. R 2 EMERGENCY selector Activates pressurization of mask delivery flow when the N/100% rocker is at 100%. Rotation of the selector in direction of the arrow gradually increases delivery pressure from zero to full pressure. Mod: 5948 1.07.20 EMERGENCY EQUIPMENT P5 OXYGEN SYSTEM 001 APR 11 AA INDICATING MFD displays crew/pax oxygen distribution system status on the top left corner of the Cabin System page. Mod: 5948 1.07.20 EMERGENCY EQUIPMENT P6 OXYGEN SYSTEM 001 APR 11 AA 20.3 ELECTRICAL SUPPLY/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) Oxygen control unit power supply DC ESS BUS (on lateral panel OXY CTL UNIT PWR SUPPLY) Pressure Ind. and alert DC ESS BUS (on lateral panel PRESS IND and CAUTION) SYSTEM MONITORING OXY This caution is generated when a low pressure (below 50 psi ) is detected in the LP distribution circuit. Visual and aural alerts are : - MC light flashing amber - “OXY” amber message on EWD - Aural alert is single chime (SC) - “LO PR” amber label on MFD cabin page - “LO PR” amber legend illuminates on overhead panel Mod: 5948 20.4 SCHEMATICS Mod: 5948 AA OXYGEN SYSTEM EMERGENCY EQUIPMENT P 7/8 APR 11 001 1.07.20 . Mod: 5948 AA OXYGEN SYSTEM EMERGENCY EQUIPMENT P 9/10 APR 11 001 1.07.20 . 1.07.30 EMERGENCY EQUIPMENT P1 EMERGENCY EVACUATION AA EMERGENCY EVACUATION IN CASE OF DITCHING A EMERGENCY EXIT B SERVICE DOOR C PASSENGER/CREW DOOR Note : Be sure that safety pin is removed. Mod: 5948 001 APR 11 1.07.30 EMERGENCY EQUIPMENT P2 EMERGENCY EVACUATION AA EMERGENCY EVACUATION IN CASE OF FORCED LANDING A EMERGENCY EXIT B SERVICE DOOR C EMERGENCY/ CREW DOR Note : Be sure that safety pin is removed. Mod: 5948 001 APR 11 1.08.00 FIRE PROTECTION P1 CONTENTS 001 APR 11 AA 1.08.00 CONTENTS 1.08.10 GENERAL 10.1 DESCRIPTION 10.2 CONTROLS 10.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING Mod: 5948 . 1.08.10 FIRE PROTECTION P1 GENERAL 001 APR 11 AA 10.1 DESCRIPTION The fire protection system is provided in order to ensure : • each engine fire - Detection for : • right nacelle overheat (on ground only) • each cargo compartment and toilets smoke • avionics compartment smoke - Extinguishing for : • each engine • cockpit, cabin and each cargo compartment • toilets waste bin ENGINE FIRE DETECTION SYSTEM Each engine is equipped with a fire detection system which consists of two identical detection loops (A and B) mounted in parallel and a fire detection control unit. The detection principle is based on the variation of resistance and capacitance of the detection cable (fire signal). If there is only a change in resistance, associated loop will be declared failed by the fire detection control unit (fault signal). ENG FIRE alert is displayed on EWD in case of fire signal detected by both loops A and B or fire signal detected by one of the 2 loops if the other one is selected OFF. RIGHT NACELLE OVERHEAT DETECTION SYSTEM (on ground only) Right nacelle is equipped with an overheat detector. When right nacelle temperature exceeds 170°C, NAC2 OVHT and /or red alarm(s), is/are displayed on EWD, and the FWS is activated. CARGO AND TOILETS SMOKE DETECTION SYSTEM Forward cargo and aft cargo are each equipped with photoelectric smoke detectors. Ambient transmittance is monitored by reflection measurement. Toilets are equipped with one ionisation type smoke detector. In case of smoke detection, “SMOKE” signal is sent to FWS through the MFC. AVIONICS SMOKE DETECTION (See schematic 1.03.30 p. 3) The avionics extract air duct is equipped with a smoke detection device (ionisation type) linked to the FWS. Smoke detection between the avionics compartment and the extract fan activates a “ELEC SMK” red alert on EWD. Mod: 5948 1.08.10 FIRE PROTECTION P2 GENERAL 001 FEB 12 AA ENGINE FIRE EXTINGUISHING SYSTEM It includes two extinguishers bottles which may be used for engine n°1 or engine n°2. They are located on each side of the fuselage. Dual squibs are installed in the discharge heads on each bottle. For fire extinguishing, the squibs are ignited by depressing the corresponding illuminated AGENT pb on the ENG FIRE panel. R The extinguishing agent (halon) is pressurized by nitrogen. COCKPIT, CABIN AND CARGO COMPARTMENTS FIRE EXTINGUISHING SYSTEM Portable extinguishers are provided to be operated manually (refer to schematic 1.07.10 R p.2/3 for location). TOILETS WASTE BIN FIRE EXTINGUISING SYSTEM The system operates automatically when fire is detected (when the temperature is greater than 78°C (172°F). Mod: 5948 1.08.10 FIRE PROTECTION P3 GENERAL 001 APR 11 AA 10.2 CONTROLS ENGINE FIRE PANEL Two identical ENG FIRE panels with fire handles are provided for control of fire detection and extinguishing. One panel controls ENG 1, the other controls ENG 2. 1 ENG FIRE handle An ENG FIRE warning light is integrated into the handle. The light illuminates red and the FWS is activated as long as the respective engine fire warning is activated (independently of handle position). Light goes off when the temperature detected by the loops drops below warning threshold. The handle has two positions : - Normal position (mechanically locked) - PULLED Pulling the handle electricallly causes for the respective engine : S PROPELLER Feathering S FUEL ENG LP VALVE closure S AIR BLEED VALVE and HP VALVE closure S DE ICE DE ICE VALVE and ISOLATION VALVE closure S ELEC ACW and DC GEN deactivation 2 SQUIB TEST pb Controls the test of the squibs in the discharge heads and their electrical circuits. When pressed in with the respective ENG FIRE handle in normal position, the two SQUIB lights illuminate if squibs and circuits are operative. 3 AGENT pbs Controls the ignition of squibs and resultant discharge of fire extinguisher bottles - SQUIB : The lights illuminate white when the ENG FIRE handle is pulled to facilitate identification of the AGENT pbs which may be activated. - DISCH : The light illuminates amber when the related fire extinguisher bottle is depressurized after discharge. Note : The discharge light will also illuminate on the non affected engine fire panel to facilitate identification of the depressurized bottle. Mod: 5948 1.08.10 FIRE PROTECTION P4 GENERAL 001 APR 11 AA 4 LOOP pb Allows activation of aural and visual alerts when a fire signal (FIRE) or a fault signal (LOOP) is generated by the fire detection control unit for the related loop. pb pressed in : Aural and visual alerts are activated when a fire or a fault signal is generated by the fire detection control unit for the related loop. 5 OFF : (pb released) Aural and visual alerts are inhibited for the related loop. The OFF light illuminates white. LOOP label is displayed on EWD. FAULT : The light illuminates amber and the FWS is activated when the associated pb is selected ON and a fault signal is generated by the fire detection control unit. LOOP alert is displayed on EWD with associated “LOOP” label. Master caution light flashing with Single Chime. TEST sw Spring Loaded in neutral position Spring loaded in neutral position allows a test of the detection of fire and fault signals when both LOOP pbs are selected ON : FAULT - FAULT lights of both LOOP A and LOOP B pb illuminate - FWS is activated, LOOP alert is displayed on EWD with associated “LOOP” label. Master caution light flashing with Single Chime. FIRE - ENG FIRE red light illuminates in associated fire handle - FUEL SO light illuminates in associated CL if CL isn’t in fuel shut off position - FWS is activated, ENG FIRE alert is displayed on EWD with associated “FIRE” label. Master warning light flashing with aural CRC - ENG FIRE on engine primary parameters page on EWD. CL FUEL LT Illuminates red in case of fire signal from associated engine. Extinguishes after CL is set at fuel shut off position or if fire detection signal is no longer sensed. Mod: 5948 1.08.10 FIRE PROTECTION P5 GENERAL 001 APR 11 AA CARGO COMPARTMENTS AND TOILET SMOKE DETECTION (1) AFT COMPT / LAV FANS Pb NORM : (Pb pressed in) one fan runs. FAULT : The fan is out of order. FAULT illuminates amber and the FWS is activated. ALTN : (Pb released) the alternate fan runs, ALTN light illuminates white. Associated pictograms are simultaneously displayed on SD cabin page as shown in the table below : (2) SMK TEST Pb Tests the smoke detectors integrity. “ELEC SMK”, “FWD SMK”, “AFT COMPT SMK” and “LAV SMK” warning are displayed on the SD cabin page and associated alerts appears on EWD. Mod: 5948 1.08.10 FIRE PROTECTION P6 GENERAL AA LEFT INTENTIONNALY BLANK Mod: 5948 001 APR 11 1.08.10 FIRE PROTECTION P7 001 GENERAL APR 11 AA 10.3 ELECTRICAL SUPPLY / MFC LOGIC / SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT ENG 1 Loop A Loop B DC BUS SUPPLY (C/B) DC EMER BUS (on lateral panel LOOP A) DC EMER BUS (on lateral panel LOOP B) Fire handle DC EMER BUS (on lateral panel FIRE HANDLE) CL light DC EMER BUS (on lateral panel CLA) ENG 2 Loop A Loop B DC EMER BUS (on lateral panel LOOP A) DC EMER BUS (on lateral panel LOOP B) Fire handle DC EMER BUS (on lateral panel FIRE HANDLE) CL light DC EMER BUS (on lateral panel CLA) Right extinguisher bottle squibs DC EMER BUS (on lateral panel SQUIBS) HOT MAIN BAT BUS (on lateral panel SQUIBS) Forward cargo Smoke detection DC ESS BUS (on lateral panel FWD smoke DETECTOR) aft cargo smoke detector Mod: 5948 DC ESS BUS (on lateral panel AFT smoke DETECTOR) 1.08.10 FIRE PROTECTION P8 001 GENERAL APR 11 AA EQUIPMENT Avionics smoke detector Toilets smoke detector Aft cargo and toilets ventilation fans PWR Aft cargo and toilets ventilation fans CTL Forward cargo ventilation fans PWR Forward cargo Fire exting CTL AUX aft compt. bay smoke detector (if installed) AUX aft compt two position valve control and PWR DC BUS SUPPLY AC BUS SUPPLY (C/B) (C/B) DC ESS BUS - Nil (on lateral panel ELEC SMK DET) DC ESS BUS - Nil (on lateral panel) - Nil AC STBY BUS (on lateral panel FANS PWR) DC ESS BUS - Nil (on lateral panel AFT FANS IND) - Nil AC STBY BUS (on lateral panel) DC ESS BUS - Nil (on lateral panel) DC ESS BUS - Nil (on lateral panel COMPT SMK AUX AFT COMPT SMK DET) DC ESS BUS (on lateral panel) - Nil - MFC LOGIC See chapter 1.01. SYSTEM MONITORING ENG FIRE This warning is triggered when an engine fire is detected. Visual and aural alerts are : - MW light flashing red - “ENG x FIRE” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) - “ENG 1(2)” legend illuminates amber on SD engine page Note : “SQUIB” legend illuminates amber when fire handle is pressed. Mod: 5948 1.08.10 FIRE PROTECTION P9 GENERAL 001 APR 11 AA ELECTRICAL SMOKE This warning is generated when smoke is detected in the avionics ventilation circuit. Visual and aural alerts are : - MW light flashing red - “ELEC SMK” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) - “ELEC SMK” red reverse video message on SD cabin page FWD CARGO SMOKE This warning is generated when smoke detected in the FORWARD cargo compartment. Visual and aural alerts are : - MW light flashing red - “FWD SMK” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) AFT COMPT SMOKE This warning is generated when smoke is detected in the aft cargo compartment in the lavatory. Visual and aural alerts are : - MW light flashing red - “AFT SMK” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) - “AFT COMPT SMK” red reverse video message on SD cabin page NAC OVHT This warning is generated when the nacelle temperature exceeds 170°C (338°F) when aircraft is on ground. Visual and aural alerts are : - MW light flashing red - “NAC OVHT” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) - “NAC OVHT” red reverse video message on SD engine page FIRE LOOP 1A (1B)(2A)(2B) This caution is generated when a Loop fault is detected. Visual and aural alerts are : - MC light flashing amber - “LOOP 1A(1B)(2A)(2B)” amber message on EWD - Aural alert is Single Chime (SC) - “FAULT” legend illuminates amber on the affected LOOP pb on overhead panel Mod: 5948 . 1.09.00 FLIGHT CONTROLS P1 001 CONTENTS AA 1.09.00 CONTENTS 1.09.10 GENERAL 1.09.20 20.1 20.2 20.3 ROLL DESCRIPTION CONTROLS ELECTRICAL SUPPLY/SYSTEM MONITORING 1.09.30 30.1 30.2 30.3 30.4 30.5 PITCH DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING LATERAL MAINTENANCE PANEL SCHEMATIC 1.09.40 40.1 40.2 40.3 40.4 YAW DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING SCHEMATIC 1.09.50 50.1 50.2 50.3 50.4 50.5 FLAPS DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING LATERAL MAINTENANCE PANEL SCHEMATIC 1.09.60 60.1 60.2 60.3 GUST LOCK DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING Mod: 5948 APR 11 . 1.09.10 FLIGHT CONTROLS P1 GENERAL 001 APR 11 AA The control of the aircraft is achieved on the three axes by : - On each wing, one aileron (spring tab equipped) and one spoiler - Two elevators (servo-- tab equipped) - A rudder (spring-- tab equipped) Ailerons, elevators and rudder are mechanically actuated. Spoilers are hydraulically actuated (blue system). Wind protection is achieved on ground by : - a locking mechanism on pitch and roll axes - a damping unit on yaw axis limiting rudder excessive travel speed. On each wing flaps are provided in two parts (inboard and outboard) mechanically linked and hydraulically activated (blue system). Mod: 5948 . 1.09.20 FLIGHT CONTROLS P1 ROLL 001 APR 11 AA 20.1 DESCRIPTION Roll control is achieved through control wheels. SPRING TAB A spring tab provides a flexible compensation which automatically increases with the aerodynamic loads applied on the ailerons, thus ensuring a reduction of the pilot’s efforts. Wheel travel : ¦ 87° Ailerons travel : 14° up, 14° down ROLL TRIM Aileron trim is performed by varying the neutral position setting of the left aileron spring tab with respect to the aileron. It is electrically controlled from a twin control switch through an electrical actuator. LH aileron trim controlled tab travel : 6.7° up, 6.7° down. Full roll trim travel requires about 30 s. Mod: 5948 1.09.20 FLIGHT CONTROLS P2 ROLL 001 APR 11 AA 20.2 CONTROLS SPOILER POSITION IND When illuminated, each blue light indicates that the associated spoiler is not in the retracted position. ROLL TRIM POSITION IND Indicates the LH aileron trim controlled tab travel. It is displayed on EWD page. Pointer color is : - White pointer when AP is engaged - Cyan in manual mode. - Amber in case of Roll Mistrim with AP engaged associated with cyan arrow. ROLL TRIM CONTROL SW Controls the roll trim actuator. For operation, both switches must be moved and held in the same direction (L WING DN or R WING DN) to energize the system (safety precaution). Mod: 5948 1.09.20 FLIGHT CONTROLS P3 ROLL 001 APR 11 AA 20.3 ELECTRICAL SUPPLY/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Spoiler position ind. DC BUS 1 (on lateral panel SPLR IND) - NIL - Roll trim DC EMER BUS (On lateral panel AIL TRIM & AIL LOCK WARN) - NIL - Roll (pitch, yaw) Trim position ind - NIL - 26 VAC BUS 1 (On lateral panel TRIM POS IND) Mod: 5948 1.09.20 FLIGHT CONTROLS P4 001 ROLL APR 11 AA SYSTEM MONITORING RETRIM ROLL REQUIRED Aileron out of trim with AP engaged : - The trim control is inhibited as long as an out-- of-- trim is not detected by AP system. - When the trim threshold limit is exceeded and a trim control is required : - The aileron trim pointer becomes amber - The rudder trim pointer becomes amber - A blue arrow is displayed - An abnormal message ”RETRIM ROLL L(R) WING DN” is triggered on the FMA Note : An inhibition logic prevents to trim the aileron in the wrong direction. - When a large aileron mistrim is present (second threshold limit reached) the aileron & rudder trim indicator becomes amber and an abnormal message ”AILERON MISTRIM” is triggered on the FMA. Mod: 5948 1.09.30 FLIGHT CONTROLS P1 001 PITCH APR 11 AA 30.1 DESCRIPTION (See schematic p 8/9) Each control column mechanically drives the associated elevator and, through a pitch coupling mechanism, the other elevator and the opposite control column. In case of jamming, pitch control will be recovered by applying on both control columns a differential force (52 daN) disengaging the pitch coupling system. The non affected channel allows the aircraft to be operated safety. System recoupling has to be performed on ground. Pitch uncoupling generates “PITCH DISCONNECT” red alert. Control column travel : 11.25° up, 6.75° down. Elevators travel : 23° up, 13° down. Elevators automatic tab travel : 50% of the pitch control course. Pitch trim is performed by off setting both tabs neutral position. Normal trim (control column) and STBY trim (pedestal) supply appropriate part of each actuator. Each trim tab is activated by a dedicated actuator. The two actuators are synchronized by a flexible shaft. In case of pitch tabs desynchronization : - an alert is generated by the FWS, - normal and STBY pitch trim control are inoperative, - AP disconnects. Trim tab travel, displayed on the pitch trim position indicator, is added to the automatic tab travel. Elevators trim controlled tab travel : 5° up, 1.5° down. Full pitch trim travel requires about 30s in normal and in STBY control. A stick pusher and a stick shaker are provided, preventing the aircraft from reaching a critical angle of attack. When the detected incidence becomes too high, the MFC sends a signal to an electric actuator which shakes the control column at stall alert thresholds. If angle of attack keeps increasing a further threshold is reached and the MFC activates the stick pusher ; the complete pitch control linkage assembly is pushed forward. Notes : 1) There are two stick shakers, one for each control column but only one stick pusher actuator located on the captain pitch channel. In case of pitch uncoupling when the pusher triggering angle of attack is reached, only the captain control column is pushed forward. 2) Loss of stick pusher does not lead to stick shaker loss 3) Left and right stick shaker operations are segregated. Mod: 5948 1.09.30 FLIGHT CONTROLS P2 PITCH 001 APR 11 AA 30.2 CONTROLS PITCH TRIM ROCKER SWITCHES On each control wheel, two pitch trim rocker switches are installed. It’s necessary to operate both rocker switches to activate the normal electrical motor of each trim actuator and to control nose up or down. The switches are spring loaded to neutral position. If both switches are operated simultaneously but in opposite direction, trimming action stops. if normal trim actuator is actuated during more than 1 second, an aural whooler is generated by the FWS. Note : Any TRIM manual operation will disengage the AP. Mod: 5948 1.09.30 FLIGHT CONTROLS P3 PITCH 001 APR 11 AA PITCH TRIM POSITION IND Indicates the right trim actuator controlled tab travel. 1 : Pitch trim pointer associated with a numerical value Pointer color : - Green associated with a numerical value when AP is engaged - Cyan associated with a numerical value in manual mode - Amber associated with a numerical value in case of : - Pitch Trim Asym - Pitch Mistrim or Pitch Trim failed with AP engaged - Pointer outside of green band in pre take off condition (Take Off CONFIG). 2 : Green sector : TO trim sector (from 0° to 2.5° UP) Identifies the take off range. If take off (or take off config test) is performed with pitch trim out of this range, CONFIG warning will be generated by the FWS. 3 : Magenta bug Indicates the managed pitch trim objective. Mod: 5948 1.09.30 FLIGHT CONTROLS P4 PITCH 001 APR 11 AA STBY PITCH CONTROL SW This guarded switch controls the electrical motor of each trim actuator. Action on this switch will disengage the AP. CAUTION : SIMULTANEOUS ACTION ON A NORMAL ROCKER SWITCH AND THE STBY SWITCH IS NOT RECOMMENDED. STICK PUSHER PB - FAULT light (amber) : Indicates a stick pusher or stick shaker failure. - OFF Position : Enables to switch OFF the stick pusher and the stick shaker system. Note : STALL WARNING aural alert is also lost. STICK PUSHER ANNUNCIATOR The stick pusher is controlled by the MFC and is a function of signals sent by the angle-- of-- attack probes. The triggering values for the secondary alarms (stick pusher) depend on the aircraft configuration. A green “STICK PUHER” indication is triggered on the FMA to indicate that the stick pusher is operating. Mod: 5948 1.09.30 FLIGHT CONTROLS P5 001 PITCH AA APR 11 30.3 ELECTRICAL SUPPLY/MFC LOGIC SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Normal pitch control DC EMER BUS (on lateral panel NORM) - Nil - Right Standby pitch control DC BUS 2 (on lateral panel R STBY PITCH TRIM) - Nil - Left Standby pitch control DC EMER BUS (on lateral panel L NORM&STBY PITCH TRIM&RUD TLU MAN CTL) - Nil - Pitch (roll, yaw trim position ind.) - Nil - 26 VAC BUS 1 (on lateral panel POS IND) Stick pusher PWR DC BUS 1 (on lateral panel PWR) - Nil - Stick pusher CTL DC BUS 1 (on lateral panel CTL) - Nil - Pitch tabs Desynchronization DC BUS 1 (on overhead panel) - Nil - Left tick Shaker DC BUS 1 (on lateral panel PWR) - Nil - Right Stick Shaker DC BUS 2 (on lateral panel CTL) - Nil - MFC LOGIC See chapter 1.01. SYSTEME MONITORING Pitch coupling mechanism disconnected(reconnected) Disconnection(Reconnection) of the Captain’s and First Officer’s channels is signaled in flight compartment by : - MW light flashing red - ”PITCH DISC”(“PITCH RECONNCT”) red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) Mod: 5948 1.09.30 FLIGHT CONTROLS P6 PITCH AA 001 APR 11 Take off out of trim range Pitch trim out of the take off range (0° DN to 2.5° UP) when PL at TO position or simulated by the TO CONFIG TEST : - MW light flashing red - ”CONFIG” red message on EWD - ”FLT CTL” amber message on EWD - Pitch trim pointer is displayed amber - Aural alert is Continuous Repetitive Chime (CRC) Pitch trim asym MFC monitors the shift between the left and right trim actuators. The monitoring threshold is set at 0.7degree of tab. In case of a detected desynchronisation : - MC light flashing amber - ”PITCH TRIM ASYM” amber message on EWD - Pitch trim pointer is displayed amber - Aural alert is Single Chime (SC) Pitch Mistrim When a pitch mistrim is present (threshold limit reached) the trim pointer becomes amber and an abnormal message ”PITCH MISTRIM” is triggered on the FMA. Pitch Trim failed with AP engaged An amber “AP PITCH TRIM FAIL” is triggered on the FMA to indicate a Pitch Trim failed with AP engaged. STICK PUSHER Fault Indicates a stick pusher failure. The following alerts appear : - MC light flashing amber - FLT CTL PUSHER amber message on EWD - FAULT on the stick pusher PB - Aural alert is Single Chime (SC) PITCH TRIM RUN AWAY The condition ”Normal trim” or ”stby trim” actuator actuated during more than 1 second is monitored by aural alert only (whooler). Mod: 5948 1.09.30 FLIGHT CONTROLS P7 001 PITCH APR 11 AA 30.4 LATERAL MAINTENANCE PANEL PITCH TRIM TEST A PTT pb is provided on RH lateral maintenance panel to test the pitch tabs shift detection unit. Test procedure - DC electrical power available - Depress and hold test button : - MC light flashing amber - PITCH TRIM ASYM amber message on EWD - Pitch trim pointer is displayed amber - Aural alert is Single Chime (SC) - Disconnection of AP if engaged ELEVATOR CLUTCH Allows to reconnect both elevators in case of declutch (see FCOM 2.02.06). Reconnection conditions : - Aircraft on ground - Gust lock ON Mod: 5948 1.09.30 FLIGHT CONTROLS P8 PITCH AA 30.5 SCHEMATICS Mod: 5948 001 APR 11 1.09.40 FLIGHT CONTROLS P1 YAW 001 APR 11 AA 40.1 DESCRIPTION (See schematic p7/8) Yaw control system consists of rudder pedals, TLU, RCU, rudder damper and trim. Rudder pedals mechanically act on a spring tab and through it on the rudder itself. SPRING TAB A spring tab provides a flexible compensation which automatically increases with the aerodynamic loads applied on the rudder, thus ensuring a reduction of the pilot’s efforts when really needed (engine failure). J Neutral position J Without airload on the surface (V = 0), when rudder pedals are moved to full deflection, the spring tab stays in line with the rudder until the rudder reaches its stops, above that point it moves the tab. J With airload on the surface (V = the spring tab has a travel in the opposite direction of the rudder which generates a compensating moment. Spring travel increases with airspeed. * Low aerodynamic forces * High aerodynamic forces SPRING HEAVILY Mod: 5948 1.09.40 FLIGHT CONTROLS P2 YAW 001 APR 11 AA TRAVEL LIMITATION UNIT (TLU) The travel limitation unit is fitted on the aircraft to limit pedals travel in order to prevent any damaging rudder travel when flying at high speed. The TLU automatic control is done through ADC 1/2, via CAC 1/2, when reaching 185 kt during an acceleration and when reaching 180 kt during a deceleration. The TLU setting (high speed or low speed) may also be performed manually in case of ADC or CAC’s failure. RELEASABLE CENTERING (RCU) A releasable centering unit is provided between, the rudder and the linkage to the pilots pedals to enable rudder position stabilization when no action is applied on the pedals. This RCU position changes with trim setting. As soon as the yaw trim control upper lever is moved to the left or lower lever to the right, the releasable centering unit is disengaged to allow trim setting. It will be re-- engaged at the new position when the yaw trim control switches are released. DAMPER The rudder is linked to the aircraft structure by a damper : - In flight this damper regulates rudder travel speed - On ground it limits excessive movement generated by gusts and avoids damaging the structural stops. YAW TRIM It is performed by offsetting the spring tab zero position. Yaw trim is electrically controlled from a twin rudder rotary selector through a trim actuator. Units of trim motor displacement are displayed on the yaw trim position indicator. Maximum value are ± 3 dots. Full yaw trim travel requires about 15s. Mod: 5948 1.09.40 FLIGHT CONTROLS P3 001 YAW APR 11 AA 40.2 CONTROLS TLU (control and indication) AUTO : normal position in flight HI SPD / LO SPD : used according to IAS after FAULT illumination. FAULT : illuminates amber when a system failure is detected. - system disagreement - both ADC failure - ADC datas incoherence - TLU position synchro failure - CAC multiple failure. TLU LO SPEED label A ”TLU LO SPEED” green label is displayed on EWD when the Travel Limiter Unit is in ”Full authority” position. Mod: 5948 1.09.40 FLIGHT CONTROLS P4 YAW 001 APR 11 AA YAW TRIM POSITION INDICATOR Indicates units of trim motor displacement. Pointer color is : - Blue in normal configuration - Amber in case of Roll Mistrim with AP engaged. YAW TRIM CONTROL SWITCHES Controls the yaw trim actuator. As a safety device both levers must be moved and held in the same direction (Nose LH or Nose RH) to energize the systrem and trim the aircraft. Mod: 5948 1.09.40 FLIGHT CONTROLS P5 YAW 001 APR 11 AA 40.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Yaw trim DC EMER BUS (on lateral panel RUD) - Nil - Yaw (pitch, roll) Trim position ind. - Nil - 26 VAC BUS 1 (on lateral panel POS IND.) - Travel limitation unit control DC BUS 1 (on lateral panel TLU CTL) - Travel limitation unit indication DC EMER BUS (on lateral panel FLAPS POS DET & IND/RUD TLU MONG) - Nil - MFC LOGIC See chapter 1.01. SYSTEM MONITORING - TLU FAULT This alert is triggered when a system failure is detected : system disagreement, both ADC failure, ADC data incoherence, TLU position synchro failure or CAC failure. Visual and aural alert are : - MC light flashing amber - ”FLT CTL TLU” amber message on EWD - FAULT on the TLU control panel - Aural alert is Single Chime (SC) - RCU failure The RCU is declutched with a trim command or a yaw damper activation. The RCU failure is triggered when a permanent +28 V is detected for more than 60s on the trim command. Visual and aural alert are : - MC light flashing amber - ”FLT CTL RUD RCU” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 1.09.40 FLIGHT CONTROLS P6 YAW 001 APR 11 AA - Rudder out of trim with AP engaged When the trim threshold limit is exceeded and a trim ontrol is required : - A cyan arrow is displayed on the EWD rudder trim indicator - An abnormal message ”RETRIM A/C NOSE L” or “RETRIM A/C NOSE R” is triggered on the FMA - RUDDER MISTRIM When a large rudder mistrim is present (second threshold limit reached) an abnormal message “RUDDER MISTRIM” is triggered on the FMA. Mod: 5948 40.4 SCHEMATICS Mod: 5948 AA YAW FLIGHT CONTROLS P 7/8 APR 11 1.09.40 . 1.09.50 FLIGHT CONTROLS P1 FLAPS 001 APR 11 AA 50.1 DESCRIPTION (See schematic p 7/8) Lift augmentation is achieved on each wing by two flaps mechanically linked with a fail safe design. The flaps control lever has three distinct positions : 0°, 15° and 30°. It is not possible to select an intermediate position. The lever and the flaps positions electrically control the flap valve which hydraulically actuates the four flap actuators. Possible asymmetry is sensed by two flap position transmitters and detected by the MFC when an angle of 6.7° is reached. Then the electrical supply to the flap control system is isolated : - The flaps stay in their present position, - The control lever has no effect on the system up to a maintenance action. A FLAP UNLK alert is provided to inform the crew of flaps spurious retraction. The alert is triggered if spurious retraction of more than 4° occurs. FLAPS HYDRAULIC POWER SUPPLY Mod: 5948 1.09.50 FLIGHT CONTROLS P2 FLAPS AA 001 APR 11 50.2 CONTROLS FLAPS CONTROL LEVER Controls the flaps operation. Distinct positions correspond to flaps 0°, 15°, 30°. To change flaps position, pull up the lever, move it to the selected position (an amber strip at the bottom of the lever is visible as long as the lever is not in one of the three distinct positions) and release the lever. Mod: 5948 1.09.50 FLIGHT CONTROLS P3 FLAPS 001 APR 11 AA FLAPS POSITION IND The flaps position indication on flight control part of EWD page is the mean value of left and right sides flaps position. In case of loss of right or left flaps position, the valid flap position is used for flap position display. If both right and left flap position are not available, flap position is not displayed. Selected flap position is indicated below Flap indicator by “SEL: xx°“ label. A flap position bullet corresponding to flaps command is filled in: - Cyan when difference between Flap position and Flap command is higher than 1° - Green when difference between Flap position and Flap command is lower than 1° Flaps Position color is : - White when flap position is at 0° - Green when the difference between flap command and position is lower than 1° (except at 0° ) - Cyan when the flaps extend or retract - Amber when : Flap Asymmetry is detected or Flap Jam is detected or Flap Command failure is detected - Red when Flap unlocked is detected. Note : Repeated appearance in flight of the cyan flap position while wing flaps have reached the selected position reveals a leakage in the hydraulic lock incorporated in the valve block. Mod: 5948 1.09.50 FLIGHT CONTROLS P4 001 FLAPS APR 11 AA 50.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Flaps control and asymmety detection Flaps position ind. DC STBY BUS (on lateral panel CTL) - Nil - - Nil - MFC LOGIC See chapter 1.01. Mod: 5948 26 VAC STBY BUS (on lateral panel POS IND) 1.09.50 FLIGHT CONTROLS P5 FLAPS 001 APR 11 AA SYSTEM MONITORING The following conditions are monitored by visual and aural alerts : FLAPS UNLK Flaps untimely retraction of more than 4° when flaps extended : - MW light flashing red - “FLAPS UNLK” red message on EWD - Flap position indication is red on the flaps indicator. - Aural alert is Continuous Repetitive Chime (CRC) TO CONFIG Flaps not in appropriate TO position when PL at TO position or simulated so by the TO CONFIG TEST : - MW light flashing red - ”CONFIG” red message on EWD - FLT CTL amber message on EWD - Flap position indication is amber on the flaps indicator. - Aural alert is Continuous Repetitive Chime (CRC) FLAP ASYM Flaps asymmetry of more than 6.7° during flaps actuation : - MC light flashing amber - “FLAP ASYM” amber message on EWD - Flap position indication is amber on the flaps indicator. - Aural alert is Single Chime (SC) FLAP JAM This alert informs that flaps have not reached the selected position. The CACs compare the half sum of RH and LH Flap position to the selected position. If the difference is higher than 1° during more than 30 seconds : - MC light flashing amber - “FLAPS JAM” amber message on the EWD - Flap position indication is amber on the flaps indicator. - Aural alert is Single Chime (SC) Note : When wing flaps are extended, the VMO alert (clacker) operates at VFE. VFE flaps 15° = 185 kt VFE flaps 30° = 150 kt Mod: 5948 1.09.50 FLIGHT CONTROLS P6 FLAPS 001 APR 11 AA 50.4 LATERAL MAINTENANCE PANEL FLAPS UNLOCK TEST On RH lateral maintenance panel, a pushbutton is provided, for maintenance purpose only, to test “Flaps unlock” alarm relays. Test procedure DC electrical power available - Hydraulic power available - Flaps extended to other than 0° position - Press and hold test button The flaps retract as long as the button is held and FLAPS UNLK red message comes on the EWD each time the flap position passes over a selectable position. - Button released : flaps come back to selected position. FLAPS ASYM TEST A periodic test to ensure correct operation of asymmetry detection system is provided on ground. Pressing test pushbutton introduces a 10° difference between values read by transmitters. It simulates an asymmetry of more than 6,7° : - operation of control lever does not cause any flap extension or retraction - appearance of “FLAP ASYM” alert and associated procedure on EWD page This test is inhibited in flight by a flight/ground condition. Mod: 5948 1.09.50 FLIGHT CONTROLS P7 FLAPS AA 50.5 SCHEMATICS Mod: 5948 001 APR 11 . 1.09.60 FLIGHT CONTROLS P1 GUST LOCK 001 APR 11 AA 60.1 DESCRIPTION A gust lock system is provided to protect the pitch and roll flight controls on ground and to limit the PL travel slightly below FI. This system includes an elevator mechanical locking device and an aileron electrico-- mechanical locking device. This system provides protection against take off with gust lock engaged, or too high power setting when in hotel mode. ELEVATOR MECHANICAL LOCKING DEVICE The system immobilizes the control column in pitch and therefore control surfaces. This device is controlled by a control lever located on the pedestal and mechanically operated through cables and gears. AILERON ELECTRO MECHANICAL LOCKING DEVICE The system is composed of two electro-- mechanical locking devices immobilizing one aileron each. Each locking device is electrically actuated through switches installed on the gust lock lever. Note : Ailerons may be locked slightly beyond the neutral position. Therefore the control wheel may be tilted (¦5°), according to the actual position of ailerons. Mod: 5948 1.09.60 FLIGHT CONTROLS P2 GUST LOCK 001 APR 11 AA 60.2 CONTROLS GUST LOCK LEVER When the gust lock is engaged, the PL travel is limited slightly below FI to provide protection against take off and too high power setting when in hotel mode. The gust lock handle can be put into the locking notch whatever the position of the flight controls is but these controls must be brought to neutral to positively engage the locking devices. Mod: 5948 1.09.60 FLIGHT CONTROLS P3 001 GUST LOCK APR 11 AA 60.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) Aileron lock ind. DC EMER BUS (on lateral panel AIL TRIM & AIL LOCK WARN) Aileron lock CTL DC ESS BUS (on lateral panel GUST LOCK AIL) MFC LOGIC See chapter 1.01. SYSTEM MONITORING The following conditions are monitored by visual and aural alerts. AIL LOCK LIT Disagreement between Aileron locking actuators and gust lock control (Temporized alert 8 sec) - MC flashing amber. - ”AIL LOCK LIT” amber message on EWD - Aural alert is Single Chime (SC) CONFIG - Aileron locking actuators not fully retracted and PL on TO position : - MW flashing red - CONFIG red message and FLT CTL amber message on EWD - Aural alert is Continuous Repetitive Chime (CRC) or - Disagreement between Aileron locking actuators and gust lock control during the T.O. CONFIG TEST : - MW flashing red - CONFIG red message and FLT CTL amber message on EWD - Aural alert is Continuous Repetitive Chime (CRC) Mod: 5948 . 1.10.00 FLIGHT INSTRUMENTS P1 CONTENTS AA 1.10.00 CONTENTS 1.10.05 05.1 05.2 05.3 INTRODUCTION SYSTEM DESCRIPTION CONTROLS AND INDICATION ELECTRICAL SUPPLY/SYSTEM MONITORING 1.10.10 10.1 10.2 10.3 10.4 AIR DATA SYSTEM (ADC) DESCRIPTION CONTROLS ELECTRICAL SUPPLY/SYSTEM MONITORING SCHEMATICS 1.10.20 20.1 20.2 20.3 AHRS SYSTEM DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 1.10.22 22.1 22.2 22.3 INDICATION ON PFD GENERAL SYSTEM DESCRIPTION ELECTRICAL SUPPLY 1.10.32 22.1 INDICATION ON MFD GENERAL 1.10.34 34.1 INDICATION ON EWD GENERAL 1.10.36 36.1 36.2 36.3 INDICATION ON IESI GENERAL CONTROLS ELECTRICAL SUPPLY/MFC LOGIC Mod: 5948 001 APR 11 1.10.00 FLIGHT INSTRUMENTS P2 CONTENTS AA 1.10.38 38.1 38.2 CDS REVERSION GENERAL CDS CONFIGURATIONS 1.10.40 40.1 40.2 R 40.3 CLOCKS GENERAL CONTROLS ELECTRICAL SUPPLY 1.10.50 50.1 50.2 50.3 Mod: 5948 FLIGHT RECORDERS DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 001 FEB 12 1.10.05 FLIGHT INSTRUMENTS P 1/2 INTRODUCTION 001 APR 11 AA 05.1 SYSTEM DESCRIPTION The Control and Display System (CDS) is an provides the main interface between cockpit crew and avionic systems. The CDS allows the flight crew to access to : - Flight information, - Aircraft environment, - Aircraft system status, - Aircraft alerts, procedures, check lists The CDS is composed of 5 display units, 6 control panels, 2 MCDUs and 2 switching panel. The CDS is managed by two Core Avionics Cabinet (CAC 1&2). Mod: 5948 . 1.10.05 FLIGHT INSTRUMENTS P3 INTRODUCTION 001 APR 11 AA Data to be displayed by the CDS are organized in “format” so as to provide a coherent set of information. There are 3 main formats : - The Primary Flight Display (PFD) format that groups data related to the flight and auto flight. - The Multi-- Function Display (MFD) format that groups data mainly related to navigation, communication and aircraft system status. - The Engine and Warning Display (EWD) that groups data related to flight control, engine primary parameters and crew alerting. Each format is divided in several windows. The upper window of MFD can display several pages. Nominal format configuration Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P4 INTRODUCTION 001 FEB 12 AA 05.2 CONTROLS AND INDICATIONS DISPLAY UNITS (DU) The Display Units DU1, DU2, DU3, DU4 and DU5 show the display images necessary for the control, monitoring and safe navigation of the aircraft. They have interfaces with most of the aircraft systems. R (1) Luminance sensors For integrated automatic dimming (illumination data is provided to the core processing function in order to adjust the brightness command for the display backlighting function). (2) Contrast setting (3) Brightness setting (4) Power switch (5) ON/OFF light White when ON, dark when OFF (6) Compact Flash Card slot The slots are used to insert the data cards containing performance, navigation, and company specific databases. All the DU, are equipped with the same slot, but only the DU 2 and 4, dedicated for the FMA and RMA, have data card. COLOR CODING : For text color refer to chap 1.00 (Color reference table) Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P5 INTRODUCTION 001 APR 11 AA CONTROL PANELS EFis Control Panel (EFCP) The EFis Control Panel allows to control the display of MFD pages, to control some Navigation Display (ND) functionalities and to control the Warning Display (WD) format (through the Flight Warning Application). The 2 EFCPs are located on the center pedestal. EFCP-- L and EFCP-- R are divided in 3 groups of dedicated controls : - MFD control - NAV control - Warning Display (WD) control Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P6 INTRODUCTION 001 APR 11 AA MFD PAGE This part of the EFCPs allows the selection of the different MFD pages : SYST PAGE Four different system pages can be displayed on the MFD, by pressing the SYS push button consecutively. Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P7 001 INTRODUCTION APR 11 AA ND PAGE Three different ND format can be displayed on the MFD, by pressing on the ND push button, and then by selecting the format on the NAV control. PERF PAGE The performance page can be displayed, by pressing on the PERF push button. MISC PAGE In provision for further developpement. VD PAGE In provision for video display MAP PAGE In provision for airport mapping display Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P8 INTRODUCTION 001 FEB 12 AA NAV CONTROL This part of the EFCPs allows to control navigation information display on PFD and ND format : R This area is composed of 4 push buttons and 1 rotary knob : - BRG1(2)push button : By pressing it, VOR1(2) or ADF1(2) or no indication is displayed. - RANGE “+”(”-- ”) push button : By pressing it, the range of the Navigation Display page is increased (decreased) - FORMAT rotary knob : By rotating it, the format of the ND is changed : ROSE, ARC, PLAN. Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P9 INTRODUCTION 001 APR 11 AA On the flight guidance coupled side, the ND is displayed by default on the MFD. If the pilot changes the ND to an other page (system for example), a mini ND page is displayed on the PFD, in place of the EHSI. In this case the format of the mini ND can the changed by the rotary knob (only ROSE and ARC). Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P 10 INTRODUCTION 001 APR 11 AA WD CONTROL This part of the EFCP allows the cockpit crew to manage alerts and procedures displayed on EWD format and generated by the Flight Warning System: The WD control right part of the EFCP-- L is unique and thus used by both cockpit crew. Note : CLR and RCL pbs also manage the procedure window. For more details, refer to the FWS chapter 1.02. Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P 11 001 INTRODUCTION APR 11 AA (1)First Officer procedure control pb Allows to move on upward/downward line in the procedure window and to validate actions (2) MAN DEL By pressing on it, procedures inserted manually are deleted (3) PROC MENU By pressing on it, procedure menu is displayed in the procedure window. (4) Captain Procedure control pb Allows to move on upward/downward line in the procedure window and to validate actions (5) CLR PB By pressing on it, a clearable alert displayed on the Alert Window is cleared. (6) RCL PB A first push enables to display in the Alert Window the alert messages previously cleared but still detected. A second push scrolls down the alert messages list in case of overflow in the Alert Window. Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P 12 INTRODUCTION 001 APR 11 AA MCP The Multipurpose Control Panel allows cockpit crew to control the virtual control panel format on MFD. 2 MCPs, one on each side (pilot/copilot) allows an independent setting on each VCP (on MFD1 and MFD2 respectively). The VCP is functionally interfaced with the Radio Management System and the Flight Management. Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P 13 INTRODUCTION AA R R (1) COM P/B Allows the selection of the COM pages on the VCP. 3 pages : - VHF - HF 1 - HF 2 (if installed) R (2) NAV P/B Allows the selection of the NAV pages on the VCP .3 pages : - VOR - ADF - ND OVLY (ND Overlay) R (3) SURV P/B Allows the selection of the surveillance pages on the VCP. 2 pages : - XPDR - TCAS R (4) Enter P/B Allows validating the selection area. R (5) Multi directionnal pad Allows choosing the selection area. R (6) ESCape key, Allows to exit current VCP function. R (7) Numeric Key Board Allows setting manually the frequency. Mod: 5948 001 FEB 12 1.10.05 FLIGHT INSTRUMENTS P 14 INTRODUCTION 001 FEB 12 AA ICP The ICP is linked to the PFD format, it controls managed speed selection and setting (through the Auto Flight Control Application), baro setting and DH/MDA setting. Each ICP is connected to one DU (1or 5) allowing an independent setting and display on PFD1 and PFD2. The ICP is split in 2 zones: SPEED TARGET control and BARO SETTING and DH control. Speed target area The SPEED TARGET area is composed by 1 AUTO/MAN push button and 1 rotary knob. The rotary knob allows setting indicated air speed target. The AUTO/MAN push button allows setting Auto/man mode : - Auto (automatic): the speed target is calculated by the FMS (Magenta). - Man (manual) : the speed target is set by the Capt / F/O (Cyan). The speed target is displayed on each PFD. Baro Setting The BARO SET internal rotary knob allows barometric pressure setting. By pushing the rotactor button, the barometric setting is set to STD setting. The BARO SET is displayed on each PFD. DH/MDA Rotary knob Outer knob allows to select between DH or MDA. Inner knob allows to set: R - Decision Height from 0ft to 990ft. (radio-- altitude) R - Minimum Descent Altitude from 0ft to 19990ft. (baro-- altitude) Note : There is no display of negative MDA. Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P 15 INTRODUCTION 001 APR 11 AA MCDU The Multi-- purpose Control and Display Unit (MCDU) allows on capt and F/O side to interface with following systems : - FMS (Flight Management function) - ACARS (Aircraft Communication Addressing and Reporting System) (if installed) - RMS (Radio Management System) - ACMS (Aircraft Condition Monitoring System) - CMS (Central Maintenance System/function) The front face consists of a pushbutton keyboard and a multi-- function alphanumeric display It comprises : - an alphanumeric keyboard - function and line keys - select keys - annunciators - a display brightness control - a 5.5” screen (14 lines with 24 characters per line). The MCDU are located on the center pedestal. Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P 16 INTRODUCTION 001 FEB 12 AA SWITCHING CONTROL The system switching allows to switch displays on the different DUs. R (1) Capt switching control panel (Displays successively PFD/EWD/MFD when P/B depressed) R (2) F/O switching control panel (Displays successively PFD/EWD/MFD when P/B depressed) R Note: Switching occurs primarily on DU 2/4, if they are inoperative switching occurs on DU 1/5 Mod: 5948 1.10.05 FLIGHT INSTRUMENTS P 17 001 INTRODUCTION AA 05.3 ELECTRICAL SUPPLY/SYSTEM MONITORING Mod: 5948 EQUIPMENT DC BUS SUPPLY (C/B) DU 1 DC BUS 1 (On overhead panel DU 1 PFD) DU 2 DC EMER BUS (On overhead panel DU 2 MFD) BACK UP SUPPLY HOT MAIN BAT BUS (On overhead panel DU 2 MFD AUX) DU 3 DC BUS 1 (On overhead panel DU 3 EWD) DU 4 DC ESS BUS SECT 1 (On overhead panel DU 4 MFD) BACK UP SUPPLY HOT EMER BAT BUS (On overhead panel DU 4 MFD AUX) DU 5 DC BUS 2 (On overhead panel DU 5 PFD) EFCP-- L DC EMER BUS (On overhead panel EFCP / CAPT) EFCP-- R DC ESS BUS SECT 1 (On overhead panel EFCP / F/O) MCP 1 DC EMER BUS (On overhead panel NAV/COM/SURV / CAPT / MCP) MCP 2 DC ESS BUS SECT 1 (On overhead panel NAV/COM/SURV / F/O / MCP) ICP 1 DC EMER BUS (On overhead panel ADC 1 EMER SPLY / ICP CAPT) ICP 2 DC BUS 2 (Flight) (On overhead panel ADC 2 / ICP F/O / FLT SPLY) DC EMER BUS (Ground) (On overhead panel ADC 2 / ICP F/O / GND SPLY ) APR 11 1.10.05 FLIGHT INSTRUMENTS P 18 001 INTRODUCTION AA MCDU 1 DC STBY BUS (On overhead panel NAV/COM/SURV / CAPT / MCDU) MCDU 2 DC BUS 2 (On overhead panel NAV/COM/SURV / F/O / MCDU) SYSTEM MONITORING MULTI DUs T HI This caution is triggered when an overheat occured on the display units. Visual and aural alerts are : - MC light flashing amber - “MULTI DUs T HI” amber message on EWD - Aural alert is Single Chime (SC) DU FAIL A fatal failure has been detected by DU software or by hardware. Mod: 5948 APR 11 1.10.10 FLIGHT INSTRUMENTS P1 AIR DATA SYSTEM 001 APR 11 AA 10.1 DESCRIPTION The flight environment data are provided by three independent air data systems : - two main systems - one stand by system MAIN SYSTEMS Aircraft is equipped with two independent AIR DATA COMPUTERS (ADC). Each computer is supplied with: - static air pressure provided by its specific static ports, - total air pressure provided by its pitot tube, - total air temperature provided by its specific TAT probe Probes and ports are located on the LH and RH side of the fuselage and are electrically heated. Mod: 5948 1.10.10 FLIGHT INSTRUMENTS P2 AIR DATA SYSTEM 001 APR 11 AA From this air data each ADC computes : - vertical speed - indicated air speed (IAS) - true air speed (TAS) - total air temperature (TAT) - static air temperature (SAT) ADC1 supplies direct data to: - CAC 1 & 2 - AHRS 1& 2 - XPDR 1 & 2 - All DU for display of CAS,TAS,SAT & TAT - MPC ADC2 supplies direct data to: - CAC1 & 2 - AHRS 1& 2 - XPDR 1 & 2 - All DU for display of CAS,TAS,SAT & TAT - MPC Data from the ADC are used by the CAC to supply data to the EECs, Presurization system, anti-- icing system, and the MFC. STAND BY SYSTEM The stand by system consists of : - two static ports - a pitot probe Stand by Air Data Systems supplies directly the IESI. Mod: 5948 1.10.10 FLIGHT INSTRUMENTS P3 AIR DATA SYSTEM AA Mod: 5948 001 APR 11 1.10.10 FLIGHT INSTRUMENTS P4 AIR DATA SYSTEM AA 10.2 CONTROLS AND INDICATIONS AIR SPEED IND (PFD) Refer to PFD section. STANDBY AIRSPEED IND (IESI) Refer to IESI section. Mod: 5948 001 APR 11 1.10.10 FLIGHT INSTRUMENTS P5 AIR DATA SYSTEM AA ALTIMETERS (PFD) Refer to PFD chapter. STANDBY AIRSPEED IND (IESI) Refer to IESI section Mod: 5948 001 APR 11 1.10.10 FLIGHT INSTRUMENTS P6 AIR DATA SYSTEM 001 APR 11 AA VERTICAL SPEED IND (VSI) (PFD) The AHRS supplies the vertical speed indicator with the baro inertial vertical speed. AHRS uses ADC baro vertical speed input. Refer to PFD chapter. TAT-- SAT IND/TAS IND TAT-- SAT IND TAS IND Mod: 5948 1.10.10 FLIGHT INSTRUMENTS P7 AIR DATA SYSTEM 001 FEB 12 AA ADC SWITCHING CONTROL CAPT SWITCHING ADC pb (1) To be used by the captain to select the opposite side ADC source. R When depressed SYS 2 illuminates white on CAPT side and CAPT/2 illuminates green on F/O side. F/O SWITCHING ADC pb (2) To be used by F/O to display data from opposite side ADC source.. R When depressed SYS 1 illuminates white on F/O side and F/O/1 illuminates green on CAPT side. When the opposite side is selected, ADC 1(2) message is displayed on the ADI corner. Mod: 5948 1.10.10 FLIGHT INSTRUMENTS P8 001 AIR DATA SYSTEM AA 10.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) ADC 1 DC EMER BUS (On overhead panel ADC 1 EMER SPLY/ICP CAPT) Back up supply HOT EMER BAT BUS (On overhead panel MFC 1A AUX/ADC1 HOT SUPPLY) ADC 2 DC BUS 2 (On overhead panel ADC 2 SPLY/ ICP F/O) MFC LOGIC See chapter 1.01. SYSTEM MONITORING “ADC” This caution is generated when one ADC is detected failed. Visual and aural alerts are : - MC light flashing amber - “ADC” amber message on EWD - Aural alert is Single Chime (SC) “ADC 1+2” This caution is generated when both ADC are detected failed. Visual and aural alerts are : - MC light flashing amber - “ADC 1+2” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 APR 11 1.10.10 FLIGHT INSTRUMENTS P9 AIR DATA SYSTEM AA “IAS DISAGREE” This caution is generated in case of Indicated Air Speed disagreement. Visual and aural alerts are : - MC light flashing amber - “IAS DISAGREE” amber message on EWD - Aural alert is Single Chime (SC) “ALT DISAGREE” This caution is generated in case of Altitude disagreement. Visual and aural alerts are : - MC light flashing amber - “ALT DISAGREE” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 001 APR 11 . 1.10.20 FLIGHT INSTRUMENTS P 1/2 AHRS 001 APR 11 AA 20.1 DESCRIPTION The attitude and heading data are provided by : - two main systems (AHRS). - Standby instruments. The AHRS is a system which supplies the crew and the autopilot with the magnetic heading, attitude data, vertical speed and lateral acceleration required for flight control and Weather radar. The aircraft is equipped with two AHRSs. Mod: 5948 . 1.10.20 FLIGHT INSTRUMENTS P3 AHRS AA 20.2 CONTROLS AND INDICATING DATA INDICATING (1) ATTITUDE (pitch and roll) (2) LATERAL ACCELERATION (3) VERTICAL SPEED (4) HEADING Mod: 5948 001 APR 11 1.10.20 FLIGHT INSTRUMENTS P4 AHRS 001 FEB 12 AA AHRS SWITCHING CAPT SWITCHING ATT/HDG pb (1) To be used by captain to display data from opposite side AHRS. R When depressed SYS 2 illuminates white on CAPT side and CAPT/2 illuminates green on F/O side. F/O SWITCHING ATT/HDG pb (2) To be used by F/O to display data from opposite side AHRS. R When depressed SYS 1 illuminates white on F/O side and F/O/1 illuminates green on CAPT side. When the opposite side is selected, AHRS 1(2) message is displayed on the ADI corner. Mod: 5948 1.10.20 FLIGHT INSTRUMENTS P5 AHRS 001 APR 11 AA STANDBY INSTRUMENTS STANDBY HORIZON A standby horizon is provided on the IESI located on the central panel. Refer to IESI chapter. STANDBY COMPASS A retractable standby magnetic compass with internal lighting is provided under glareshield. Hidden in up position. Compass control should be placed on DN for use. The compass rose is graduated in 10 degrees increments. Mod: 5948 1.10.20 FLIGHT INSTRUMENTS P6 001 AHRS FEB 12 AA 20.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) AHRS 1 DC EMER BUS (On overhead panel AHRS 1 NORM SPLY) Back up supply DC BUS 2 (On overhead panel AHRS 1 AUX SPLY) AHRS 2 DC BUS 2 (On overhead panel AHRS 2 NORM SPLY) Back up supply DC EMER BUS (ground) (On overhead panel AHRS 2 AUX SPLY GND) DC BUS 1 (flight) (On overhead panel AHRS 2 AUX SPLY FLT) R MFC LOGIC See chapter 1.01. SYSTEM MONITORING “AHRS” This caution is generated when one AHRS is detected failed. Visual and aural alerts are : - MC light flashing amber - “AHRS” amber message on EWD - Aural alert is Single Chime (SC) “AHRS 1+2” This caution is generated when both AHRS are detected failed. Visual and aural alerts are : - MC light flashing amber - “AHRS 1+2” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 1.10.20 FLIGHT INSTRUMENTS P7 AHRS AA “AHRS NOT ALIGN” This caution is generated when AHRS is not aligned. Visual and aural alerts are : - MC light flashing amber - “AHRS NOT ALIGN” amber message on EWD - Aural alert is Single Chime (SC) “HDG DISAGREE” This caution is generated in case of heading disagreement. Visual and aural alerts are : - MC light flashing amber - “HDG DISAGREE” amber message on EWD - Aural alert is Single Chime (SC) “ATT DISAGREE” This caution is generated in case of Attitude disagreement. Visual and aural alerts are : - MC light flashing amber - “ATT DISAGREE” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 001 APR 11 . 1.10.22 FLIGHT INSTRUMENTS P1 INDICATION ON PFD 001 APR 11 AA 22.1 GENERAL The PFD is divided into 6 areas : - Flight Mode Annunciator Area (FMA Area) - Airspeed area - Attitude Display Indicator (ADI Area) - Altitude area - Vertical speed area - Navigation area (HSI or ND) The PFD is located on : - In normal condition, the PFD1 (CAPT side) and PFD2 (F/O side) are respectively on the DU1 and DU5. - In abnormal condition, (manual or automatic switching), PFD can be displayed on DU2 (CAPT side) and/or DU5 (F/O side). It is controlled by : - FGCP (Flight Guidance Control Panel) - ICP (Index Control Panel) - EFCP (EFIS Control Panel) Note : For AHRS system description see chapter 1.10.20 Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P2 INDICATION ON PFD AA Displays are : - In The FMA area : Auto Flight data Icing status - In the ADI, Airspeed, altitude and vertical speed areas : Air Data Inertial Data FMS Data Radio Altimeter data ILS and Marker data T2CAS and Transponder status - In the Navigation Area : Horizontal Situation Indicator (HSI): FMS data Radio Nav (VOR, ILS, ADF, DME) data Auto Flight Target Inertial data Mini-- Navigation Display (ND) : FMS data Radio Nav (VOR, ILS, ADF, DME) data Auto flight target T2CAS data Weather Radar data and status Mod: 5948 001 APR 11 1.10.22 FLIGHT INSTRUMENTS P3 INDICATION ON PFD 001 APR 11 AA 22.2 SYSTEM DESCRIPTION FLIGHT MODE ANNUNCIATOR (FMA) Flight Mode Annunciator displays on the upper part of the PFD the icing information, autopilot operational mode status, status messages (abnormal conditions, failure, warning), primary flight data monitoring messages. The FMA display area is as follow: - 4 columns of 2 lines dedicated respectively to annunciation of icing information, lateral modes, vertical modes and engagement status of AP. - A third line displaying trim status, approach capability, and AFCS modes or internal failures. The different zones (each number corresponds at a message zone) are separated by white vertical lines : Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P4 INDICATION ON PFD 001 FEB 12 AA Icing information (zones 1&7) Icing detected: “ICING” amber label, located in zone 1 of FMA area indicating that icing is detected. Icing AOA: “ICING AOA” green label, located in zone 7 of FMA area indicating that stall alarm threshold has been lowered. Will come active when horn anti icing is selected on. Active APM: Displayed in zone 1 and 7 of FMA area when APM is has sensed a degraded condition: R - “CRZ SPD LO” amber indication in zone 7 if APM sense a 10 kt decrease compared to expected speed. - “DGD PERF” amber indicationl in zone 7 if APM detects a loss of speed or rate of climb. - “INCREASE SPEED” amber flashing indication in zone 1 and 7 if APM detects an abnormally high drag and speed below red bug (icing bug) + 10. Lateral modes (zones 2&8) Lateral Active Mode : In zone 2 of FMA area, a text indicates which lateral mode is currently engaged. Displayed labels are : Green ”ROLL HOLD”, ”HDG HOLD”, ”WING LVL”, ”HDG SEL”, ”VOR*”, ”VOR”, ”LOC*”, ”LOC”, ”BC*”, ”BC” or ”LNAV”. FMA Low Bank : ”LO” green label is displayed in zone 2 of FMA if Low Bank is active. Lateral active mode framing : It is a green rectangle displayed around lateral mode (zone 2) in order to indicate a mode change. Lateral armed mode : Cyan ”VOR”, ”LOC”, ”BC” or ”LNAV” label displayed in zone 8 of FMA area which indicates that one of these lateral mode is currently armed. Vertical modes (zone 3&9) Vertical active mode : In zone 3 of FMA area, a text indicates which vertical mode is currently active. Displayed labels are : Green ”PITCH HOLD”, ”IAS”, ”VS”, ”ALT *”, ”ALT”, ”GS*”, ”GS”, ”GA” labels. Furthermore in case of activation of the stick pusher a green “STICK PUSHER” label is displayed in zone 3 Vertical active mode framing : Green rectangle displayed in zone 3 around the vertical active mode label order to indicate a mode change or a degraded mode. Vertical armed mode : Cyan ”ALT SEL / GS”, ”ALT SEL” or ”GS” displayed in zone 9 of FMA area, which indicates that a vertical mode is currently armed. AFCS failure When both FD channel are lost, the FMA is black. The red “AFCS FAIL” label is the only message displayed in zone 3 Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P5 INDICATION ON PFD 001 APR 11 AA AP / FD Information (zones 4, 5 & 6) AP/YD annunciation : ”AP” or ”YD” green label which indicates whether AP or YD is engaged, in zone 4 of FMA area. FD selection : ”FD” green label which indicates whether FD is active or not, in zone 5 of FMA area. Side selection : Indicates which side is selected, in zone 6 of FMA area. Represented in zone 6 of FMA area by : - a green arrow ”<-- ” or - a green arrow ”-- >” or - a green “DUAL” label following the selected side. Speed Hold (zone 10) (if installed) TCS Message Green ”TCS” label in zone 11 of FMA indicates that TCS is activated. Trim status (zone 12) Displayed label are : Amber reverse video flashing or steady amber ”AP PITCH TRIM FAIL”, ”AP YAW TRIM FAIL”, ”PITCH MISTRIM”, ”AILERON MISTRIM”, ”RETRIM ROLL R WING DN”, ”RETRIM ROLL L WING DN”, ”RETRIM A/C NOSE LEFT” or ”RETRIM A/C NOSE RIGHT”. Unexpected mode change, or problem in navigation parameters ( zone 14) Displayed label are : - Red reverse video ”EXCESS DEV” or - amber reverse video (flashing for 7s then steady amber) ”FD MODE CHG”, ”CHECK NAV SRC”, ”CHECK T/O SPD” or ”SPD AUTO INOP”, or - amber ”EXCESS DEV”, ”FD MODE CHG”, ”CHECK NAV SRC” or - flashing (for 7s then removed)”AFCS TEST” - or yellow ”ATT INVALID”, ”ADC INVALID”, ”HDG INVALID”, ”NAV INVALID”, flashing (for 7s then removed) ”SPD AUTO INOP” or ”CHECK NAV SRC” Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P6 INDICATION ON PFD 001 APR 11 AA AP/YD disengagement, approach category retrogration, AFCS internal failure (zone 15) Displayed label are : - Red reverse video ”AP/YD DISENG” or ”AP DISENG”, - Amber reverse video (flashing for 7 s then removed) ”YD DISENG”, ”AP/YD INVALID”, ”AP INVALID”, ”CAT2 INVALID”, ”CAT3 INVALID”, ”FD SINGLE CH” or ”CHECK SPD HLD”,or - Yellow (flashing for 7s then removed) ”AP INHIB”, ”YD INHIB”, ”SPD HLD INHIB” or - Amber ”FD SINGLE CH” (flashing for 7s then steady amber) Approach category (zone 13) Green “CAT1” or optional “CAT2” or “CAT3” labels are displayed in zone 13 of the FMA area indicating the available approach category. Only displayed when the ILS tunning conditions are met for the approach category. Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P7 INDICATION ON PFD 001 APR 11 AA ATTITUDE DISPLAY INDICATOR ADI normal display (1) Aircraft symbol The fixed aircraft symbol is black outlined in yellow. Aircraft pitch and roll attitudes are displayed in relationship between this symbol and the movable horizon. (2) Roll attitude Displays actual roll attitude through a movable index and fixed scale reference marks at 10, 20, 30, 45 and 60 degrees. Roll indexes are displayed as yellow triangles. (3) Slip/Skid indicator Lateral acceleration index indicates the aircraft’s lateral acceleration. It is represented by a trapezoidal index that moves beneath the roll index. Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P8 INDICATION ON PFD 001 APR 11 AA (4) Horizon and pitch scale Both move with respect to the aircraft symbol to display actual pitch and roll attitude. Sky zone is colored blue and earth zone brown. In case of high pitch value a horizon or earth reference will always remain in sight. If pitch exceeds +/-- 25° degrees large red chevron will indicate excessive attitude and direction to follow to resume normal attitude Pitch scale is white and has reference marks every 2.5° up to 20° up or down, then marks at 25, 30, 50, 80° 5 Flight Director command bars (Green) Display computed commands to capture and maintain a desired flight path. The horizontal bar is related to vertical modes and the vertical to lateral ones. The commands are satisfied by flying the aircraft symbol to the command bars. 6 Selected Heading index The selected heading is indicated by a perpendicular cyan line when flight director commands bar are not displayed. . Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P9 INDICATION ON PFD 001 APR 11 AA (7) Vertical deviation indication Vertical deviation can be either from ILS source or FMS source, it is displayed on the right side of the ADI. Vertical deviation from ILS source is displayed as a cyan V shaped form, the scale being two white dots each side from a yellow reference line. Vertical deviation from FMS source is displayed as a magenta open rectangle, the scale being two white line each side from yellow reference line. The scale of the Vertical deviation (or VDEV) in FMS mode varies according to the flight phase. The value of maximum deflection is +/-- 500 ft. unless the FMS is in the approach phase when the full deflection will represent only +/-- 150 ft. When the maximum deflection value are exceeded only a partial view of the open rectangle will be in view. In case of failure the deviation scale will be crossed in red. (ref ADI display following failure) (8) Lateral deviation indication Lateral deviation can be either from ILS source or FMS source; it is displayed below the ADI. Lateral deviation from ILS source is displayed as a cyan V shaped form, the scale being two white dots each side from a yellow reference line. Lateral deviation from FMS source is displayed as a magenta open rectangle, the scale being two white lines each side from yellow reference line. The scale of the lateral deviation in FMS modes varies according to the flight phase. If the FMS is in P-- RNAV area (Approach or Terminal area) the value of the full deflection is 1 NM, i.e. 0.5 NM between each mark; otherwise the FMS is in B-- RNAV area and in this case the value of the full deflection is 5 NM, i.e. 2.5 NM between each mark. When the maximum deflection value are exceeded only a partial view of the open rectangle will be in view. In case of failure the deviation scale will be crossed in red. (ref ADI display following failure) (9) DH Indication and Annunciation The selected DH is displayed in cyan in the bottom left corner. The central rectangle displays RA (amber) readout at decision height. Maximum selectable DH is 999 ft. (10) Minimum decision altitude Displayed in cyan, the range being from 0ft to 19999ft with 1 ft increments. If baro altitude is equal or less than selected MDA, the altitude numeric readout is displayed in amber. (11) Radio altitude Numeric value displayed from 0 to 2500 ft (762m) in green digits. Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P 10 INDICATION ON PFD 001 APR 11 AA ADI display after failures (1) AHRS reversion flag Yellow AHRS 1(2) in the left upper corner of the ADI indicates in case of one AHRS failure which is remaining and is used for computation of reference data. (2) ADC reversion flag: Yellow ADC 1(2) in the upper lest corner of the ADI indicates in case of one ADC failure which is remaining and is used for computation of air data. (3) CHECK ATT flag Flashes for 9s, then steady amber message. Will be displayed on PFD when a discrepancy for pitch or roll data between AHRS 1 & 2 is detected. (4) ATT FAIL flag ADI part of PFD will turn black with a white ADI outline, ATT FAIL in red will be displayed. ATT FAIL will be displayed in case of dual AHRS failure Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P 11 INDICATION ON PFD 001 APR 11 AA AIR SPEED DATA (1) Maximum speed - speed limit band Limit band indicates the maximum speed to not exceed according to aircraft configuration. Speed Limit band is represented along the CAS tape, on the right side border, by a red band, with white oblical dashes, extended from the VMAX value to the top of the speed scale. Width is larger than selected speed bug. As example: cruise : VMO: approach flaps 15° VFE flaps 15° approach flaps 30° VFE flaps 30° Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P 12 001 INDICATION ON PFD APR 11 AA (2) Flaps extension speed (VFE NEXT) Indicates the maximum speed to command the flaps extension to the next flap lever position and avoid damaging the flaps. The bug is represented by two amber horizontal lines. (3) FLAPS RETRACTION SPEED BUG VmLB0 bug : Indicates the value of the minimum speed in Low Bank conditions (FLAPS LEVER = 0°). Normal condition VmLB0 normal : The indication is composed of a white triangle. Icing conditions VmLB0 Icing : The indication is composed of an amber triangle. (4) Target speed bug Gives the target airspeed which can be either computed by FMS or manually selected. Cyan “M-- shape” pointer displayed along the speed scale for a manual selection. Magenta “M-- shape” pointer displayed along the speed scale for an AUTO selection (computed by FMS). (5) Shaker Speed Speed below which the Flight Controls equipment activates the stick shaker. VMIN is represented along the speed tape, on the right side border, by a red band extended from the VMIN value to the bottom of the speed scale. Width is larger than selected speed bug. (6) V1 indication V1 Bug : Indicates the value of the decision speed on the speed scale. The indication is composed of an horizontal cyan line followed by a cyan “1” label. V1 readout : Indicates the value of the decision speed when value is out of the speed scale. Cyan readout displayed on the top or bottom right of the speed scale. (7) VR indication Indicates the value of the rotation speed (VR) on the speed scale. The VR bug is a horizontal cyan line followed by a space and a cyan “R“ label. (8) V2 indication Indicates the value of the initial climb speed on the speed scale. The indication is composed of an cyan triangle followed by a cyan “V2” label. (9) FLAPS RETRACTION SPEED BUG (flaps 30°) ; FLAPS position > 15° Normal conditions : White line (VmHB 15 normal), with white “F” on the right side. Icing conditions : Amber line (VmHB 15 icing), with amber “F” on the right side. Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P 13 INDICATION ON PFD 001 APR 11 AA (11) Airspeed scale A vertical tape included in a grey rectangle with graduations every 10kt, with associated numbers every 20kt, from 30kt to 450kt. The displayed part of the tape shall cover +/-- 42kt around the current aircraft computed airspeed. A yellow line represents the airspeed reference on the centre of the tape. (12) Airspeed trend Provides the predicted airspeed in 10 seconds if acceleration remains constant. The trend is a yellow arrow extending from the airspeed reference line to the predicted airspeed value on the speed scale, with a filled up end of arrow. (13) VmHB in landing configuration : The bug indicates the VmHB in landing configuration. The indication is composed of a green triangle. (14) Minimum Operationnal Speed Mini VOPS is represented along the IAS tape, on the right side border, by an empty amber band extending from the Mini VOPS value to the bottom of the speed scale or to Vmin band. Width is larger than selected speed bug. Airspeed mismatch flag “CHECK IAS” The message appears when a discrepancy is detected for airspeed data between the ADC sources. “IAS FAIL” This message appears in case of loss of the validity of the signal. Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P 14 INDICATION ON PFD 001 APR 11 AA ALTITUDE INDICATOR This indicator displays the aircraft baro-- altitude of the selected AHRS source. This altitude is the altitude computed by the ADC, corrected with the barosetting (if any), and then corrected by the AHRS. The altitude is referenced to hectoPascal and to inches of mercury. (1) Selected altitude indication Displayed above the tape: In imperial system Cyan digits when displayed in feet. “FL” fixed label followed by 3 cyan digits ranging from FL000 to FL250. Maximum operational display will be 25000 or FL250 In metric system Composed of cyan digits and a white “M” label. Maximum operational display will be 7500 M. The units are set via the MCDU (Meter or Feet) (2) Altitude below landing elevation This is a brown zone filling the bottom of the altitude tape. (3) Baro-- setting digital readout Indicates the current baro-- setting selection and the associated value in millibars and in inches of Hg. Represented by a cyan “STD“ label in a white box if barosetting selection is set to STD or if ICP invalid is set to invalid. Else it is represented by a cyan “XXXX” label readout, from 745 to 1050 HPa with 1 HPa of resolution whith a white ”/” as separation followed by a cyan “XX.XX” readout from 22 to 31 inches with 0.01 of resolution in normal operation. In case of invalidity, amber “-- - - - /-- - .-- - ” label is displayed. Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P 15 001 INDICATION ON PFD APR 11 AA (4) Altitude scale A vertical tape included in a grey rectangle with graduation from - 1000 ft to above 25000 ft, every 100 ft with longer marks and associated numbers every 500ft. A yellow line represents the altitude reference on the centre of the tape. (5) Minimum Decision Altitude indication Two amber horizontal lines indicates the selected minimum decision altitude. (6) Selected altitude bug Represented by a cyan filled M-- shaped bug, it indicates the selected target altitude. (7) Altitude numeric readout Display is in feet on the altitude scale, the readout being a digital drum counter with 20ft increments. When operating in feet the altitude is displayed as T-- shape, it reverts to a rectangle in case that metric readout is selected. Readout in meters will be displayed above the rectangular altimeter. A “NEG” label is added in place of thousands digits for negative values. It is displayed in white on the left of the first digit. Readout range is from NEG980ft to above 25000ft. The units are set via the MCDU (Meter or Feet) Altitude mismatch flags “CHECK ALT” The message appears when a discrepancy is detected for altitude data between the ADC sources. “ALT FAIL” Three white lines surrounding the tape and a red “ALT FAIL” vertical message are displayed when the baro altitude is invalid. Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P 16 INDICATION ON PFD 001 APR 11 AA VERTICAL SPEED INDICATOR This indicator displays the vertical speed information, based on both inertial (AHRS) and barometric data (ADC). (1) VS target readout Indicates the active vertical speed target value in hundreds of feet. It is composed of 2 cyan digits from 0 hundreds of fpm to +/-- 99 hundreds of fpm with 100 fpm resolution. Minus sign are displayed when the value is negative. It is located above the current vertical speed value. The thousand digit are aligned on numeric indications of the scale. The parts of the VS target that are upper than the top of the VS scale or lower that the bottom of the VS scale are not displayed. The VS target readout is associated with the cyan target bug. (2) VS pointer This is a green line (in normal operation) extended from a fixed point outside the display to a point along the scale indicating the current vertical speed. The line has a fine black outline. Only the part of the pointer which is inside the VS scale is displayed. If TCAS vertical resolution advisory exists and if the pointer points on a red band, the vertical speed pointer colour is red. Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P 17 INDICATION ON PFD 001 APR 11 AA (3) TCAS corrective advisory It is a green ”Fly-- To” band displayed just after the end of the red RA band indicating the recommended vertical speed range when a change of the aircraft vertical speed is required. (4) TCAS vertical Resolution Advisory (RA) Alerts that a vertical manoeuvre must be performed or avoided to prevent a collision or a near collision. One or two red bands are displayed on the vertical speed scale in order to show the vertical rates to be avoided. The advisories are displayed through one or two red bands on the vertical speed scale along the graduations : - a bottom red band extended from bottom of the vertical scale; - a top red band extended from the top of the vertical scale. Extremities of bands are oblique so as to be parallel to the pointer when its position is on these extremities. (5) Transponder status indication Indicates the selected transponder status. The displayed indications (spread on two lines) are: - amber “XPDR1(2) FAIL” if XPDR1(2) status is ”Failed” - white ”XPDR1(2) STBY” if XPDR mode is set to ”Standby” - green and white ”XPDR1(2) ALT OFF” if XPDR Alt report is set to ”OFF” - green “XPDR1(2) ALT” otherwise. (6) TCAS status indication Indicates the current TCAS status. The displayed indications (spread on two lines) are: - amber “TCAS FAIL” if TCAS status is “Failed” - white “TCAS STBY” if TCAS Status is set to ”STBY” - yellow “TCAS TEST“ if TCAS Status is set to ”Test in progress” - green “TA ONLY THREAT” if TCAS Status is set to ”TA Only” - green “TA ONLY NORM” if TCAS Status is set to ”TA Only”, and TCAS Altitude option selection is set to ”Normal” - green “TA ONLY ABOVE” if TCAS Status is set to ”TA Only”, and TCAS Altitude option selection is set to ”Above” - a green “TA ONLY BELOW” if TCAS Status is set to ”TA Only”, and TCAS Altitude option selection is set to ”Below” - green “TCAS THREAT” if TCAS Status is set to ”Auto” - green “TCAS NORM” if TCAS Status is set to ”Auto”, and TCAS Altitude option selection is set to ”Normal” - green “TCAS ABOVE” if TCAS Status is set to ”Auto”, and TCAS Altitude option selection is set to ”Above” - green “TCAS BELOW” if TCAS Status is set to ”Auto”, and TCAS Altitude option selection is set to ”Below”. Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P 18 INDICATION ON PFD 001 APR 11 AA (7) VS digital readout Indicates in green the current vertical speed value in hundreds of feet in normal operation. If TCAS vertical resolution advisory exists the readout is red. Minus sign are displayed. The VS readout is associated to the VS pointer. (8) VS target This is a filled “M-- shape” cyan bug located on the vertical tape between numeric indications and graduations of the scale. The VS target is associated to the VS target readout. (9) VS scale The altitude scale is the reference for vertical speed information. The “1“, “3“ and “6“ numeric white indications are displayed respectively for+/-- 1000 fpm, +/-- 3000 fpm and +/-- 6000 fpm. A yellow line represents the vertical reference on the center of the tape. The scale is outlined in white. In case of invalidity, 3 white lines surrounding a red “VS FAIL” vertical message are displayed. Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P 19 INDICATION ON PFD 001 APR 11 AA NAVIGATION INDICATORS The PFD provides on its Navigation Area the medium term flight information. The navigation area can be displayed in 2 formats : - HSI (Horizontal Situation Indicator) - Mini-- ND (Mini-- Navigation Display) NAVIGATION AREA DISPLAY LOGIC When a ND page on MFD is replaced by another page (e.g. ND is replaced by one of the System pages), the navigation part of the PFD auto-- reverts : HSI format is replaced by Mini-- ND format. ND ARC format on the MFD reverts to MINI ND ARC format on the PFD. ND ROSE and PLAN format on the MFD reverts to MINI ND ROSE format on the PFD Note : ND PLAN Mode reverts into a Mini-- ND ROSE Mode When on MFD, the ND format is displayed again, the navigation part of the PFD automatically switches back into the HSI format and the ND keeps the Mini-- ND format selected. When a Traffic Alert is triggered by TCAS, the Mini-- ND page automatically reverts to ROSE mode in 10 Nm range. When a Terrain Alert is triggered by TAWS, the Mini-- ND page automatically reverts to : - ARC mode in a 10 Nm range and DU contrast automatically reverts to 80%. - TERRAIN display mode (terrain selection becomes active on VCP) Mod: 5948 1.10.22 FLIGHT INSTRUMENTS P 20 INDICATION ON PFD AA HORIZONTAL SITUATION INDICATOR (HSI) Refer to chapter 1.15.70 22.3 ELECTRICAL SUPPLY It is associated to the DU electrical supply where the PFD is displayed. Mod: 5948 001 APR 11 1.10.32 FLIGHT INSTRUMENTS P1 INDICATION ON MFD 001 APR 11 AA 32.1 GENERAL The Multi Functional Display, presented on the inner Display Units (DUs) in normal configuration, indicates the medium term flight information for the navigation, gives synoptics of system information, displays the radio navigation and radio communication selections. The MFDs provide this information according to the formats, pages and modes selectable. The MFD is divided into 3 areas : - MFD upper window, - Memo panel display, - Virtual Control Panel window. Mod: 5948 1.10.32 FLIGHT INSTRUMENTS P2 INDICATION ON MFD 001 APR 11 AA MFD UPPER WINDOW The MFD upper window displays several formats : - Navigation Display (ND) - System Display (SYS) displays the system pages: ENGINE / FUEL, CABIN, ACW/HYD, ELEC - Performance init (PERF) - MISC (provision) - Airport MAP (provision) - Video (provision) NAVIGATIONS DISPLAY (ND) : ND is displayed in several modes : ARC MODE, ROSE MODE or PLAN MODE. Mod: 5948 1.10.32 FLIGHT INSTRUMENTS P3 INDICATION ON MFD 001 APR 11 AA SYSTEM DISPLAY (SYST) The MFD can display the following system pages (for description see relevant FCOM chapters) : - ENGINE (secondary engine parameters) - CABIN - ACW/Hydro - ELEC Mod: 5948 1.10.32 FLIGHT INSTRUMENTS P4 INDICATION ON MFD 001 APR 11 AA PERF INIT The performance page can be displayed, by pressing on the PERF push button on the EFCP. Mod: 5948 1.10.32 FLIGHT INSTRUMENTS P5 INDICATION ON MFD AA MISC PAGE In provision for further developpement. VD PAGE In provision for video display. MAP PAGE In provision for airport mapping display. Mod: 5948 001 APR 11 1.10.32 FLIGHT INSTRUMENTS P6 INDICATION ON MFD 001 APR 11 AA MEMO PANEL DISPLAY MFD Memo Panel Display provides the following information : - Fuel crossfeed control/failure device status, - Anti-- icing control/failure devices status, - De-- icing control/failure devices status, - Cabin seat belt/No smoking message status. If systems are selected and are operating normally they will be displayed in cyan. They will be displayed in amber in case of failure. Mod: 5948 1.10.32 FLIGHT INSTRUMENTS P7 INDICATION ON MFD 001 APR 11 AA VIRTUAL CONTROL PANEL (VCP) The VCP format presents the information which can be managed through the MCP, in the lower part of the MFD. Three different pages are displayed to manage the information: - VCP NAV pages - VCP COM page - SURV page Furthermore, pages are displayed when the performance data are entered in the FMS. Mod: 5948 1.10.32 FLIGHT INSTRUMENTS P8 INDICATION ON MFD 001 APR 11 AA VCP NAV pages VOR/ILS Selection of the VOR and ILS frequency, and activation of the DME HOLD function. ADF Selection of the ADF frequency ND OVLY Selection of the required overlay information on the ND: - Traffic - Weather radar - Terrain - Navaid - Airport Mod: 5948 1.10.32 FLIGHT INSTRUMENTS P9 INDICATION ON MFD AA VCP COM pages VHF Selection of the VHF frequency. HF Selection of the HF frequency. (if installed). Mod: 5948 001 APR 11 1.10.32 FLIGHT INSTRUMENTS P 10 INDICATION ON MFD AA VCP SURV pages XPDR TCAS Mod: 5948 001 APR 11 1.10.32 FLIGHT INSTRUMENTS P 11 INDICATION ON MFD 001 APR 11 AA Performance Data The performance pages can be displayed, by pressing on the PERF push button on the EFCP. Two pages are available: - TO DATA page used to: - reset the fuel used - select the icing condition - confirm the T/O data computed by the FMS - TAT SEL page used to select the source of the TAT (Total Air Temperature) Mod: 5948 . 1.10.34 FLIGHT INSTRUMENTS P1 INDICATION ON EWD 001 FEB 12 AA 34.1 GENERAL The EWD is divided into 5 areas : - Flight controls, trims, brake message and test status - Primary engine window R - Permanent Data Window : TAT (_C), SAT (_C), FT (Flight Time), Hour, FOB (Fuel On Board - KGS), GW (Gross Weight - KGS). - Alert Window - Procedure Window R Refer to the dedicated chapter, for details. Mod: 5948 . 1.10.36 FLIGHT INSTRUMENTS STANDBY NAVIGATION SYSTEM INDICATION ON IESI P1 001 APR 11 AA 36.1 GENERAL The IESI displays the following information: - Attitude - Airspeed - Altitude - Barometric pressure - VHF 1 radio communication - VOR/ILS 1 radio navigation The IESI has to be complemented with the standby compass (see section AHRS 1.10.20) for standby navigation purpose. ARCHITECTURE Mod: 5948 1.10.36 FLIGHT INSTRUMENTS STANDBY NAVIGATION SYSTEM P2 INDICATION ON IESI 001 APR 11 AA ATTITUDE (1) Fixed aircraft symbol The fixed aircraft symbol is black outlined in yellow (2) Roll scale The roll scale is in white, markers are set at 10,20,30,45,60 degrees of bank. (3) Roll index The roll index indicates the bank angle. It is in black, and outlined in yellow. (4) Lateral acceleration index Lateral acceleration index indicates the aircraft’s lateral acceleration. It is represented by a trapezoidal index that moves beneath the roll index. (5) Pitch scale The pitch scale indicates aircraft attitude and is displayed in white. The scale has markers every 2.5 degrees up to +/-- 20 . If pitch exceeds +/-- 25 degrees large red chevron will indicate excessive attitude and direction to follow to resume normal attitude. Mod: 5948 1.10.36 FLIGHT INSTRUMENTS STANDBY NAVIGATION SYSTEM INDICATION ON IESI P3 001 APR 11 AA AIRSPEED (6) Airspeed scale The actual airspeed is given in a T shaped window positioned in the center of the white moving speed tape on the left of the IESI. ALTITUDE (7) Altitude indication The altitude indication is given in a rectangular window positioned in the center of the white moving altitude tape on the right of the IESI. Altitude in meters can also be displayed on the IESI underneath the altitude tape. (8) Barometric reference The barometric reference is displayed in cyan. It corresponds to either the selected barometric pressure or the standard pressure. ILS & VOR FUNCTION (9) Glideslope & Localizer scales and indexes The deviation scales appear when the ILS MODE is selected. The indexes appear when the glideslope and localizer signals are valid and deviation scales displayed. (10) VOR scale and index The deviation scale appears when the VOR MODE is selected. In the bottom left corner TO V and FROM W are indicated in cyan followed by the selected course. Mod: 5948 1.10.36 FLIGHT INSTRUMENTS STANDBY NAVIGATION SYSTEM INDICATION ON IESI AA 36.2 CONTROLS The IESI has five push buttons and a rotary knob: - A brightness (-- ) pb (4) - A brightness (+) pb (4) - A MENU pb (5) - A STD pb (1) - A SET rotary knob (2) Mod: 5948 P4 001 APR 11 1.10.36 FLIGHT INSTRUMENTS STANDBY NAVIGATION SYSTEM INDICATION ON IESI AA TUNING ILS Tuning When MENU button is pushed and VHF NAV1 is tuned on ILS : VOR Tuning When MENU button is pushed and VHF NAV1 is tuned on VOR : Mod: 5948 P5 001 APR 11 1.10.36 FLIGHT INSTRUMENTS STANDBY NAVIGATION SYSTEM P6 001 INDICATION ON IESI APR 11 AA FLAGS (1) ATT label (red reverse video) Means that attitude data are lost. (2) IAS label (red reverse video) Means that airspeed data is lost (3) ALT label (red reverse video) Means that altitude data is lost (4) VOR, ILS, LOC or G/S label (red reverse video) Appropriate MODE is selected but invalid, no signal is sensed from selected source. (5) ATT:RST label (cyan) This message appears if the aircraft has moved during initialization of IESI (6) FAIL label (amber) FAIL amber boxed label is displayed in case of invalid signal or tuning mode off. (7) OUT OF ORDER (white) (not depicted) A fatal error has occurred and the IESI is unserviceable (8) Black screen with white frame (not depicted) The processor of the IESI is unserviceable. Mod: 5948 1.10.36 FLIGHT INSTRUMENTS STANDBY NAVIGATION SYSTEM INDICATION ON IESI AA 36.3 ELECTRICAL SUPPLY/MFC LOGIC ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) IESI (normal operation) DC ESS BUS (on overhead panel) IESI (abnormal operation e.g DC ESS BUS voltage < 19 V) MFC LOGIC See chapter 1.01 Mod: 5948 HOT EMER BUS (on overhead panel) P7 001 APR 11 . 1.10.38 FLIGHT INSTRUMENTS P1 CDS REVERSION 001 APR 11 AA 38.1 GENERAL The Control and Display System (CDS) provides manual and automatic format configuration of DU. Main formats manual reversion is controlled with two reversion push buttons. These push buttons allow a circular reversion between PFD, EWD and MFD formats. Automatic reversion occurs following DU failures or FWS request. On ground, powering aircraft with batteries, DU2 and DU4 are respectively configured as EWD and SD Engine page (power supply is not available on DU1, 3 and 5) Mod: 5948 1.10.38 FLIGHT INSTRUMENTS P2 CDS REVERSION 001 APR 11 AA 38.2 CDS CONFIGURATIONS Automatic Configurations The CDS reversion system provides automatic DU reconfiguration in case of DU failure(s). The leading rule of the automatic reconfiguration is: following PFD or EWD failure, MFD is reconfigured in PFD or EWD. The automatic reconfiguration takes into account the following parameters : - Flight/Ground Status - Pilot Flying Side : Right or Left Automatic reconfiguration can also occur on FWS request. If EWD is no more displayed because it was manually reversed in PFD or MFD (in the case of DU3 failure for instance), EWD can be automatically recalled by FWS. When one System Display page is displayed on MFD format, another System Display page can be automatically displayed on FWS request. Manual reconfiguration Manual format reconfiguration is controlled by “PFD/EWD/MFD” Push-- Buttons on CAPT and F/O sides. If DU2(4) is available, CAPT(FO) “PFD/EWD/MFD“ PB enables a circular reversion of PFD/EWD/MFD format on DU2(4). If DU2(4) is inoperative, DU1(5) takes into account the reversion command. Manual reversion overrides a DU automatic reconfiguration but if a new automatic reconfiguration occurs, current manual reversion is superseded by this new configuration. Degraded Configuration In case of AFDX loss, last DU configuration is unchanged and manual reversion is effective on DU2 and DU4. In flight, in case of DC electrical generation loss, DU2 and DU4 are respectively powered by EMER and ESS bus. DU2 and DU4 are configured depending on ”Pilot flying side”. When a fatal DU failure is detected a big “F” label is displayed on the corresponding DU. Mod: 5948 1.10.40 FLIGHT INSTRUMENTS P1 001 CLOCKS APR 11 AA 40.1 GENERAL An electronic clock provides : - On selection, a six digits display of either : Universal Time Coordinated (UTC) Date : DAY/MONTH and YEAR, Local Time (LT) GPS Time - On selection, a four digits display of either : ELAPSED TIME (ET) or CHRONOMETER TIME (CHR) - A serialized UTC, DATE and Elapse time Output - A remote controls: CHR and ET - An automatic synchronization on external data word from GPS receiver. - A display function test (TST) on front face and on a remote test The operating modes are controlled by : - A push button mode selector : DATE (DT) , GPS , INT , LOCAL TIME (LT) - A push button : ET - A push button : CHR - A push button TST The clock is supplied with two 28 VDC power supplies, one of which is a direct connection to the aircraft battery hot bus. Mod: 5948 1.10.40 FLIGHT INSTRUMENTS P2 CLOCKS 001 APR 11 AA 40.2 CONTROLS Time display - UTC from GPS or internal computed (INT) is indicated from 0 to 23 hours 59 minutes and 59 seconds. The clock automatically switches to GPS mode if the GPS data is valid and the clock is in “INT” mode. In the same way, the clock automatically switches to INT mode if the GPS becomes invalid and the clock is in GPS mode (except on power up where the Time Setting mode is active if the GPS is invalid). - LOCAL TIME (LT) is indicated from 0 to 23 hours 59 minutes and 59 seconds At first power up of the battery bus, if the local time setting is displayed, the local time is initiated with the INT value and it could be modified by set the desired time differences. At each next LOCAL TIME setting, the proposed value is synchronized with GPS or INT time, then it could be modified by set the desired time differences. Date display Months, days and years are displayed when the DATE mode is selected. Mod: 5948 1.10.40 FLIGHT INSTRUMENTS P3 CLOCKS 001 APR 11 AA MODE push button By pressing the MODE pushbutton, six annonciators (DT, GPS, INT, LT, ET and CHR) indicate which mode is selected (the functions INT, LOC and DT are available in succession, ET and CHR functions are controlled by the the ET and CHR buttons respectively, the GPS is automatically selected when GPS is valid). ELAPSED TIME (ET) pushbutton ET counter displays the aircraft flight from 0 to 23h59 minutes. The push buttons ET controls the following functions : - When selecting the ET push button, the ET display comes on. - when the elapsed time counter is stopped, by pressing the ET push button for more than two seconds the display is blanked and value is zeroed. CHRONOMETER (CHR) pushbutton The CHR displays time from 0 to 99minutes 59 seconds The CHR push-- button controls the following functions : - START : Display is active and the chronometer starts incrementing - STOP : The value displayed at the instant the push-- button was depressed is held as long as no action occurs on this push button. - RESET : the LCD display is zeroed and blanked. TEST (TST) pushbutton The TST button function starts rotating displays of the digits from 0 to 9, twice time. The function could be reset by pressing the TST button before the end of the sequence. Time Setting At the first application of power, the clock will be in UTC minutes adjustment if GPS is invalid. If the GPS data is valid, the clock data are automatically updated and switched in GPS mode. The setting is obtained by pressing the ET pushbutton to decrease the data and pressing the TST pushbutton to increase the data. Mod: 5948 1.10.40 FLIGHT INSTRUMENTS P4 CLOCKS 001 FEB 12 AA 40.3 ELECTRICAL SUPPLY Mod: 5948 EQUIPMENT DC BUS SUPPLY (C/B) CAPT CLOCK DC EMER BUS (On lateral panel CLOCK / CAPT / NORM SPLY) HOT EMER BAT BUS (On lateral panel CLOCK / CAPT / AUX SPLY) F/O CLOCK DC BUS 2 (On lateral panel CLOCK / F/O / NORM SPLY) HOT MAIN BAT BUS (On lateral panel CLOCK / F/O / AUX SPLY) 1.10.50 FLIGHT INSTRUMENTS P1 FLIGHT RECORDERS 001 APR 11 AA 50.1 DESCRIPTION The aircraft is equipped with : - a Cockpit Voice Recorder, CVR, and - a Solid State Flight Data Recorder, SSFDR. The recorders are automatically energized as soon as the aircraft is on its own electrical supply and are switched OFF automatically Ten minutes after engines cut. When the aircraft is on external power, recorders are OFF until one engine is started. They can be energized by selecting ON the RCDR pushbutton, and deenergized by pushing the RESET pushbutton. Each recorder is equipped with an underwater acoustic beacon which is used to locate the recorder in the event of an aircraft accident over the sea. The beacons actuate immediately after immersion. They should transmit a signal on 37.5 kHz for 30 days. The detection range is 3.5 km (4,000 yards). CVR All crew communications transmitted through the RCAU are recorded. In addition, a CVR microphone, located below the overhead panel, acquires cockpit conversation and aural alerts for recording. Cabin crew announcements are also recorded. Only the last 30 minutes (or 120 minutes, depending on version) are retained. All recording may be erased by pressing ERASE pushbutton provided the aircraft is on ground and the parking break is set. Mod: 5948 1.10.50 FLIGHT INSTRUMENTS P2 FLIGHT RECORDERS 001 APR 11 AA SSFDR Various aircraft parameters are sent to a Flight Data Acquisition Unit (FDAU) which converts them into digital data. Then the FDAU sends the digital data to the SSFDR. The Flight Data Acquisition Unit (FDAU) is a part of the Multi Purpose Computer (MPC). The data are recorded by the SSFDR which stores them on the Solid State memory. The 50 last hours of flight are retained. Mod: 5948 1.10.50 FLIGHT INSTRUMENTS P3 FLIGHT RECORDERS 001 APR 11 AA 50.2 CONTROLS The MCDU TIME&FLIGHT page allows to set hours, months, years and flight number before departure. These datas are used for the recording on the SSFDR. RECORD PANEL RCDR pb When depressed, both Cockpit Voice Recorder and Solid State Flight Data Recorder are energized (manual mode). On light illuminates blue. RESET pb When depressed, inhibits recording in the manual mode. EVENT pb When momentarily depressed, the Solid Sate Memory records are marked to identify a special event. Mod: 5948 1.10.50 FLIGHT INSTRUMENTS P4 FLIGHT RECORDERS 001 APR 11 AA COCKPIT VOICE RECORDER PANEL (1) Monitor ind. For test only. Movement of pointer in the white band indicates all channels are operative. (2) TEST pb When depressed and held, the test circuit is activated : - the pointer moves to a location between graduations 8 and 10 - if a headset is plugged into the jack, the 600Hz signal will be heard. (3) HEADSET jack When headset is plugged into the jack : - cockpit sounds picked up by the microphone are audible - test tone is audible when TEST pb is depressed - erase tone is audible when ERASE pb is depressed (4) ERASE pb Provides fast erasure of tape recordings when the landing gear shock absorbers are compressed and parking brake is set (depress for 2 seconds to completely erase). During erasure, a 400 Hz audio signal can be heard in the headset. (5) Microphone Picks up cockpit conversations and alert sounds. Mod: 5948 1.10.50 FLIGHT INSTRUMENTS P5 FLIGHT RECORDERS 001 APR 11 AA 50.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRCAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) SSFDR power supply AC BUS SUPP (C/B) 115 VAC STBY BUS Recorder Synchronizer - NIL-- MPC DC EMER BUS (on ground) DC ESS BUS (in flight) 26 VAC STBY BUS MFC LOGIC See Chapter 1.01 SYSTEM MONITORING DATA RECORDER This caution is generated when the Data Recorder is detected failed. Visual and aural alerts are : - MC light flashing amber - “DATA RECORDER” amber message on EWD - Aural alert is Single Chime (SC) VOICE RECORDER This caution is generated when the Voice Recorder is detected failed. Visual and aural alerts are : - MC light flashing amber - “VOICE RECORDER” amber message on EWD - Aural alert is Single Chime (SC) FDAU This caution is generated when the FDAU is detected failed. Visual and aural alerts are : - MC light flashing amber - “FDAU” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 . 1.11.00 FUEL SYSTEM P1 CONTENTS 001 APR 11 AA 1.11.00 CONTENTS 1.11.10 GENERAL 10.1. DESCRIPTION 10.2. CONTROLS AND INDICATING 10.3. ELECTRICAL SUPPLY/MFC LOGIC/ SYSTEM MONITORING 10.4. SCHEMATIC Mod: 5948 . 1.11.10 FUEL SYSTEM P1 GENERAL 001 APR 11 AA 10.1 DESCRIPTION The fuel system includes : - two tanks with one electrical pump and one jet pump is each tank the vent system the fuel quantity indicating system the refuel/defuel system with associated controls and ind. TANKS The fuel is stored in two tanks, one in each wing, formed as an integral part of the wing structure. The maximum fuel capacity is : An additional volume in each tank allows a 2 % thermal expansion of fuel without spillage. Each tank is equipped with two access doors located on the upper wing skin at each tank extremity to provide access to the interior and to essential equipment. Water drainage is provided at the low points of each tank and can be performed up to 3° ground slope. A temperature measuring device is installed in the left feeder compartment. Temperature is displayed on MFD. Mod: 5948 1.11.10 FUEL SYSTEM P2 GENERAL 001 APR 11 AA VENTS SYSTEM TANKS The vent system ensures positive pressure in the whole flight envelope. Each fuel tank is air vented via an individual vent duct and a vent float valve to a 100 l surge tank located in the outer section of the wing. The surge tank is connected to the atmosphere via a flush NACA inlet and is designed to avoid icing obstructions. Fuel collected in the surge tank is directed back to the wing tank via the vent duct. The vent system also provides protection for the tanks in the event of accidental spillage during refueling. WING CENTER BOX The wing center box over the fuselage does not store any fuel and is crossed by two fuel pipes for cross engine feed and tanks refueling. To prevent fuel vapor concentration, the box is vented and drained. Mod: 5948 1.11.10 FUEL SYSTEM P3 GENERAL 001 APR 11 AA ENGINE FEED (See schematic p16/17) In normal conditions, each engine is supplied from its associated wing tank. Fuel Flow and Fuel used parameters displayed on the MFD allow the crew to monitor fuel consumption for each engine. Each tank is fitted with a 200 I feeder compartment always full of fuel protecting the engine feed system against negative or lateral load factors. In the feeder compartment, an electrical pump and a jet pump are installed. The jet pump is activated by HP fuel from the engine HMU and is controlled by a motive flow valve. Note : Each electrical pump is able to supply one engine in the whole flight envelope. In normal operation, the electrical pump is only used to start the engine. After start, jet pump takes over automatically. If jet pump pressure drops below 350 mbar (5 PSI), the electrical pump is automatically activated to supply the engine. A crossfeed valve, controlled by an electrically operated actuator, allows both engines to be fed from one side or one engine to be fed by either tank, allowing control of an unbalance situation. Crossfeed valve indication is located on both Fuel panel and MFD. When the crossfeed valve is open,a cryan “FUEL XFEED“ label is displayed on the memo panel display and indication is displayed on the MFD system page. In this case, the two electrical pumps are automatically actuated. It is possible to use only one fuel tank by switching off the opposite pump pb. To indicate improper operation of crossfeed valve, label “FUEL XFEED” flashes on the memo panel display when: - both electrical fuel pumps are OFF - both electrical fuel pumps are ON - electrical pump 1 is OFF with fuel quantity of tank 1 greater than fuel quantity of opposite tank - electrical pump 2 is OFF with fuel quantity of tank 2 greater than fuel quantity of opposite tank At the fuel outlet of each tank, a fuel LP valve, controlled by the associated fire handle, is installed. When low level is reached in one tank, its electrical pump is automatically actuated ( ±160 kg (352 Lb) remaining fuel in the tank ). Mod: 5948 1.11.10 FUEL SYSTEM P4 GENERAL AA 001 APR 11 QUANTITY INDICATING The fuel quantity indicating system informs the crew of the quantity of fuel available in each tank during flight. The quantities are processed by Fuel Control Unit (FCU) and displayed on MFD. The fuel tank capacity measurement system is such that the figures appear in terms of weight. The system is based on the fundamental relationship between the dielectric constant of the fuel and its density, to obtain a signal proportional to the mass of fuel in the tanks from a number of capacitance probes installed in the tanks. Six probes are positionned in each tank and are electrically connected to the Fuel Control Unit (FCU), which processes the signals and provides left and right fuel quantities to the avionic system. FCU contains two independant channels (one per tank). The accuracy on the total fuel indication, on ground, with attitude within - 3° and + 1° of Pitch and 2° of Roll is : 1 % of full scale near zero level 3 % of full scale at full level For all other ground and flight conditions, outside this envelope (pitch and roll) accuracy of fuel indications will be degraded. To enable the tanks content to be determined on the ground in case of quantity indicating system failure, two magnetic level indicators are mounted in each tank through the lower wing skin. Tables allow these readings to be converted into units of fuel mass with corrections made for aircraft attitude and fuel density (Refer to chapter 2.06). Actual magnetic indicators marking is in cm of fuel in the tank. REFUEL/DEFUEL SYSTEM All refueling operations are controlled from the Refueling Control Panel (RCP) installed in the RH main landing gear fairing. Complete refueling can be achieved in about 16 mn through the single refueling connector which is located in the rear part of the RH main landing gear fairing. Both wing tanks can be refueled with a refueling flow of about 24 m3/h (106 US gal/mn) with a maximum refueling pressure of 3.5 bars (50PSI). The refueling connector is connected with two refuel valves, one for each tank. They are solenoid controlled. From the valves outlets, the fuel is distributed by pipes to diffusers which allow the fuel to enter the tank without surging. High level detection comprises two different controls : In normal operation, the high level detection is achieved by the FCU system. When the high level tank quantity is reached (2500 kg/5510 lb), the associated tank refuel valve is shut. When the high level is reached in a tank (3185 L/840 US gal for a zero bank angle) associated high level it illuminates on refueling panel and associated refuel valve is shut. The wing tanks can also be refueled by gravity via one overfiller point per tank. The system may be used to defuel the aircraft by applying a 0.77 bar (11 PSI) suction to the connector and opening the tank refuel valves. Mod: 5948 1.11.10. FUEL SYSTEM P5 GENERAL 001 APR 11 AA 10.2 CONTROLS AND INDICATING FUEL PANEL 1 PUMP pb Controls electrical pump and jet pump motive flow valve in each tank. PB pressed in : £ When jet pump delivery low pressure is detected (engine not running or jet pump pressure drop) : • electrical pump is automatically activated, • jet pump motive flow valve is controlled open but will remain closed until a sufficient pressure is available. £ 30 seconds after HP fuel pressure is available and normal jet pump functioning is sensed by the 600 mbar (8.5 PSI) pressure switch, electrical pump is automatically switched off. RUN illuminates green when electrical pump is activated. OFF (p.b. released) electrical pump is deactivated, jet pump motive flow valve is controlled closed, OFF light illuminates white. 2 LP VALVE position ind. The position of the fuel LP valve is displayed. Each valve is controlled by its associated fire handle. IN LINE Flow bar illuminates green. The valve is open. CROSS LINE The valve is closed, flow bar illuminates green and crosses the system flow line. Note : During transient phases (opening or closing), flow bars are extinguished. Mod: 5948 1.11.10. FUEL SYSTEM P6 GENERAL 001 APR 11 AA 3 FEED LO PR light Illuminates amber and the caution message “FEED LO PR” from the FWS is displayed on EWD associated with a Master Caution light and a Single Chime when the fuel delivery pressure drops below 300 mbar (4 PSI). This indicates pump failure or fuel starvation 4 X FEED pb Controls the operation of the fuel crossfeed valve. IN LINE (pb pressed in) The flow bar illuminates green in line. The valve is open. Both electrical pumps are automatically actuated. CROSS LINE (pb released) The flow bar illuminates green and crosses the system flow line. The valve is closed. Note : During transient phases (opening or closing), flow bar is extinguished. Permanent extinguishing of both bars indicates a valve fault. Mod: 5948 1.11.10 FUEL SYSTEM P7 GENERAL AA FUEL INDICATION (1) - Fuel Flow Indication (per engine) Normally in green. The unit is KG/H or LB/MN (if lb is the unit used). Amber dashes displayed for invalid data. (2) - Fuel transfer indication Normal transfer : Green Arrow No transfer : Blue horizontal dash (3) - Fuel Flow 1 + 2 Normally in green. The unit is KG/MN or LB/MN (if lb is the unit used). Amber dashes displayed for invalid data. (4) - Engine LP valve indication In line : Green : valve is open Cross line : Cyan : valve is closed (5) - XFEED valve In line : Cyan : valve is open Cross line : White : valve is closed (6) - Fuel tank quantity indication Normally in green. The unit is KG or LB (if lb is the unit used). Amber dashes displayed for invalid data. Mod: 5948 001 APR 11 1.11.10 FUEL SYSTEM P8 GENERAL 001 APR 11 AA (7) - Fuel temperature readout Normally in green. The unit is °C. Amber dashes displayed for invalid data. (8) - Engine Feed Pumps indication Green : Electric Pump is operating(”RUN” legend inside) White : Electric Pump is off (”OFF” legend inside) (9) - Motive Flow Valve indication Green : Motive Flow valve is open White : Motive Flow valve is closed (10) - Fuel Temperature indication From - 53°C to 0°C, and from 50°C to 99°C, segments, readout and pointer are displayed in amber. From 1°C to 49°C, segments, readout and pointer are displayed in green. For value equal or lower the - 54°C or equal or higher than 100°C, pointer and reverse video readout are displayed in red. For invalid temperatures, amber dashes are displayed. (11) - Fuel clog caution “CLOG” amber label displayed in case of an excessive pressure loss across the fuel filter. Mod: 5948 1.11.10 FUEL SYSTEM P9 GENERAL AA CROSSFEED INDICATION MEMO PANEL DISPLAY Mod: 5948 001 APR 11 1.11.10 FUEL SYSTEM P 10 GENERAL 001 APR 11 AA REFUEL CONTROL PANEL (1) TEST pb Pressing the test button will test the display lines and the lights. (2) HIGH LEVEL light The light illuminates amber when the high level sensor is submerged (maximum quantity reached). The corresponding refuel valve closes automatically. (3) REFUEL VALVES position light The light illuminates blue when the refuel valve is open. They extinguish during the fuel circuit test, indicating the valves have closed. (4) REFUEL VALVES switches Control the operation of the valves for each tank. They are guarded at NORM. NORM Valves are controlled by automatic fueling logic, depending on position of the mode selector switch and quantity preselection. Valves close automatically when high level is detected by the FCU. OPEN Valves open when the mode selector switch is in the refuel or defuel position and the high level sensor is not submerged. SHUT Valves close regardless of the mode selector switch position. (5) SELECTED QTY ind. The quantity for automatic refueling is controlled by the setting of the Increase/Decrease switch. The digital counter displays the preselected total fuel quantity. (6) INCREASE / DECREASE switch Used to select fuel quantity requested on board. (7) FUEL QTY ind. Three displays for left, right and preselected fuel quantity. Mod: 5948 1.11.10 FUEL SYSTEM P 11 GENERAL 001 APR 11 AA (8) Mode selector switches Controls the operating mode for automatic fueling and the activation of REFUEL VALVES switches for manual operation. OFF Refuel valves are closed, switches are not activated. REFUEL Refuel valves may be operated by auto refueling logic (REFUEL VALVES switches on NORM) or manual refueling operation. DEFUEL Refuel valves may be operated by manual defueling operation. With the mode selector in DEFUEL position and REFUEL VALVES in the OPEN position, all level protections are inhibited. (9) SURGE VALVE Provides air vent of the refuel line during suction draining of this line. OPEN The surge valve opens. Mode Selector switch must be in OFF position SHUT The surge valve is closed. Mod: 5948 1.11.10. FUEL SYSTEM P 12 001 GENERAL APR 11 AA 10.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT ENG 1 Electrical pump - Pressure sw controlling electrical pump activation/disactivation & motive flow valve opening/closure - Fuel feed pressure sw Fuel LP valve Fuel LP valve position ind. DC BUS SUPPLY (C/B) DC ESS BUS (on lateral panel ELEC PUMP) DC ESS BUS (on lateral panel CTL and CAUTION) S DC BUS 1 (on lateral panel MOTOR 1) S HOT EMER BAT BUS (on lateral panel MOTOR 2) DC EMER BUS (on lateral panel IND) ENG 2 Electrical pump DC ESS BUS (on lateral panel ELEC PUMP) - Pressure sw controlling electrical pump activation /disactivation and motive flow valve opening / closure DC ESS BUS (on lateral panel CTL and CAUTION) - Fuel feed pressure sw + IND Fuel LP valve Fuel LP valve position ind. Mod: 5948 S DC BUS 2 (on lateral panel MOTOR 1) S HOT EMER BAT BUS (on lateral panel MOTOR 2) DC EMER BUS (on lateral panel IND) 1.11.10 FUEL SYSTEM P 13 001 GENERAL FEB 12 AA EQUIPMENT Refuel Control Panel FCU Channel 1 DC BUS SUPPLY (C/B) GND HDLG BUS (on lateral panel RCP) DC ESS BUS (on lateral panel FCU CHAN 1) FCU Channel 2 CROSS FEED VALVE R DC ESS BUS (on lateral panel FCU CHAN 2) DC ESS BUS (on lateral panel X FEED) FCU will be supplied by GND HDLG BUS on ground for airplane servicing, when battery is off and refuel control panel door open. MFC LOGIC See Chapter 1.01 Mod: 5948 1.11.10. FUEL SYSTEM P 14 GENERAL 001 APR 11 AA SYSTEM MONITORING FUEL 1(2) TEMP HI This caution is triggered when the fuel temperature is greater than 50°C (with engine running). Visual and aural alert are : - MC light flashing amber - “FUEL 1(2) TEMP HI” amber message on EWD - Aural alert is Single Chime (SC) FUEL 1(2) TEMP LO This caution is triggered when the fuel temperature is lower than 0°C (with engine running). Visual and aural alert are : - MC light flashing amber - “FUEL 1(2) TEMP LO” amber message on EWD - Aural alert is Single Chime (SC) ENG FUEL CLOG This caution is triggered when the pressure of the switch fuel pump outlet filter is greater than 25 PSI. Visual and aural alert are : - MC light flashing amber - “ENG FUEL CLOG” amber message on EWD - Aural alert is Single Chime (SC) - “CLOG” amber label displayed on MFD FUEL FEED LO PR This caution is triggered when a low pressure is detected in the engine feed system (pressure below 300 mbar / 4 PSI). Visual and aural alert are : - MC light flashing amber - “FUEL FEED LO PR” amber message on EWD - Aural alert is Single Chime (SC) - “FEED LO PR” light illuminates amber on overhead panel - “FEED LO PR” amber label displayed on MFD Mod: 5948 1.11.10 FUEL SYSTEM P 15/16 GENERAL 001 APR 11 AA FUEL LO LVL This caution is triggered when: - First low level is detected by FCU when fuel gauged in one tank is less than 160 kg (352.8 lbs) In this case the fuel tank indicates a value < 160 kg (352.8 lbs) - Second low level is detected by the MFC when the feeder tank is not full. this alert is triggered when the feeder jet pump fails. In this case the fuel tank indicates a value > 160 kg (352.8 lbs) Visual and aural alert are : - MC light flashing amber - “FUEL LO LVL” amber message on EWD - Aural alert is Single Chime (SC) - First low level : LO LVL displayed amber in the tank and fuel quantity in amber on MFD (level between 160kg (352lb) and 50kg (110lb) or in red reverse video (level below 50kg (110lb) ) - Second low level Feeder tank in amber FUEL MISMATCH This caution is triggered, when the difference between fuel quantity computed by FMS and the fuel quantities processed by the FCU is greater than 200kg (440lb) during more than 10s (on ground) or 60s (in flight). Visual and aural alert are : - MC light flashing amber - “FUEL MISMATCH” amber message on EWD - Aural alert is Single Chime (SC) FUEL UNBALANCED The caution is triggered when there is a discrepancy greater than 200kg (440lb) between the left and right tanks fuel quantities. Visual and aural alert are : - MC light flashing amber - “FUEL UNBALANCED” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 . 1.11.10 FUEL SYSTEM P 17 GENERAL AA 10.5 SCHEMATIC Mod: 5948 001 APR 11 . 1.12.00 HYDRAULIC SYSTEM P1 001 CONTENTS AA 1.12.00 CONTENTS 1.12.10 GENERAL 10.1 DESCRIPTION 10.2 CONTROLS 10.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 10.4 SCHEMATIC Mod: 5948 APR 11 . 1.12.10 HYDRAULIC SYSTEM P1 GENERAL 001 APR 11 AA 10.1 DESCRIPTION The aircraft has two hydraulic systems, designated blue and green. The common hydraulic tank is located in the hydraulic bay (LH landing gear fairing). The tank is a direct air-- fluid contact type and is not pressurized. A compartment baffle ensures fluid antisplahing and limits fluid foaming. A direct reading quantity gauge is located on the tank. A low level alert is provided for each compartment when quantity drops below 2.5 l (0.67 USgal). POWER GENERATION Each system is pressurized by an ACW electrical motor driven pump. Delivery pressure of each pump is displayed. Normal operating pressure is 3000 PSI (206.9 bars). The blue circuit is also fitted with an auxiliary DC motor driven pump. Each system is provided with a 0.2 l (0.05USgal) power accumulator installed in the hydraulic bay. They damp pump delivery pulsations and any pressure surges and compensate for pump response time in the event of high output demand. On the ground, when no electrical power is available, hydraulic power may be generated by a hydraulic ground power unit, through a ground connector located in the hydraulic bay. A ground switch on the pedestal enables to energize the auxiliary pump even when no electrical power is available. Mod: 5948 1.12.10 HYDRAULIC SYSTEM P2 GENERAL 001 APR 11 AA USERS S The blue system supplies : - wing flaps extension/retraction : . Four wing flap actuating hydraulic jacks. - spoilers : . Two spoilers actuating hydraulic jacks. - nose wheel steering : . one steering hydraulic jack. - propeller brake for the RH engine. - emergency and parking braking for the four main landing gear wheels through a specific accumulator with separate pressure indicator. S The green system supplies : - landing gear extension/retraction : . three landing gear actuating hydraulic jacks . three landing gear uplock release actuators . three landing gear downlock release actuators - normal braking for the four main landing gear wheels. In case of one main hydraulic pump failure, the associated users may be supplied by the other one main hydraulic pump by opening the crossfeed valve. Note : In case of LO LEVEL alert, cross feed valve : - is inhibited to open - closes automatically if it was in open position Mod: 5948 1.12.10 HYDRAULIC SYSTEM P3 GENERAL 001 APR 11 AA 10.2 CONTROLS HYD PWR PANEL (1) Main pumps pbs Control activation/deactivation of ACW electric motor driven pumps. pb pressed in : pump is energized OFF : (pb released) pump is deactivated, OFF lt illuminates white. LO PR : The light illuminates amber and the caution message “HYD LO PR” from flight warning is displayed on EWD associated with a Master Caution light and a Single Chime when the associated pump delivered fluid pressure drops below 1500 PSI (103,5 bars). (2) Auxiliary pump pb Controls operating mode of DC auxiliary pump. AUTO (pb pressed in) pump runs as soon as the following conditions are met : - ACW blue pump pressure below 1500 PSI and, - propeller brake released and, - gear handle selected DOWN and, - at least one engine running OFF (pb released) ; auxiliary pump is deactivated, OFF illuminates white. LO PR the light illuminates amber and a caution message from FWS displayed on EWD associated with a Master Caution and a Single Chime when auxiliary pump output pressure is detected lower than 1500 PSI and functioning conditions are met. (3) XFEED pb Controls opening and closure of the crossfeed valve. pb released :crossfeed valve is closed. Both hydraulic circuits are separated. ON :(pb pressed in) crossfeed valve is selected open. Both hydraulic circuits are connected. ON light illuminates white. Mod: 5948 1.12.10 HYDRAULIC SYSTEM P4 GENERAL 001 APR 11 AA (4) OVHT light The light illuminates amber and the caution message “HYD OVHT” from FWS displayed on EWD associated with a Master Caution and a Single Chime when pump case drain line overheat is detected (T > 121° C/250° F) (5) LO LEVEL light The light illuminates amber and the caution message “HYD LO LVL” from FWS displayed on EWD associated with a Master Caution and a Single Chime when associated tank compartment fluid quantity drops below 2.5 I (0.67 USgal). The XFEED automatically closes. (6) Auxiliary pump switch Pressing the HYD PWR/AUX PUMP switch energizes the pump (during 30s) and allows it to operate in manual mode. CAUTION: This switch operates even when batteries master switch is selected “OFF”. Intensive use could discharge the main battery. Mod: 5948 1.12.10 HYDRAULIC SYSTEM P 5/6 GENERAL 001 APR 11 AA PARKING/EMERGENCY BRAKING ACCUMULATOR PRESSURE INDICATOR In addition to the PRKG BRK ON annunciation on EWD and the Parking / Emergency Braking Accumulator displayed on MFD ACW/HYD page, the aircraft is fitted with a Parking / Emergency Braking Accumulator pressure indicator located on the left maintenance panel. This indicator is used by maintenance while MFD are not energized and in case of the main indication loss. When the switch is activated, the indicator is energized for two minutes. When the hydraulic pressure of the accumalator is below 1700 PSI or above 3100 PSI, the indicator displays blinks. Brake Accumulator Hydraulic pressure is displayed in green. The displayed value has to be multiplied by 1000 (as described by the legend on the front face). Mod: 5948 . 1.12.10 HYDRAULIC SYSTEM P 7/8 GENERAL AA INDICATING Hydraulic indications are given on the ACW / HYD page of the MFD. Mod: 5948 001 APR 11 . 1.12.10 HYDRAULIC SYSTEM P9 001 GENERAL AA APR 11 10.4 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Blue Pump power - Nil - ACW BUS 1 (on lateral panel BLUE HYD PUMP) Blue pump control DC EMER BUS (on lateral panel BLUE PUMP CTL) - Nil - Blue system alert DC EMER BUS (on lateral panel ALERT) - Nil - Green pump power - Nil - ACW BUS 2 (on lateral panel GREEN HYD PUMP) Green pump control DC ESS BUS (on lateral panel GREEN PUMP CTL) - Nil - Green system alert DC EMER BUS (on lateral panel CAUTION GREEN SYS) - Nil - Auxiliary pump power DC BUS 2 (on lateral panel AUX HYD PUMP NORM PWR SUPPLY) HOT MAIN BAT BUS (on lateral panel AUX HYD PUMP GND PWR SUPPLY) - Nil - Pressure ind. DC EMER BUS (on lateral panel PRESS IND) - Nil - XFEED valve DC STBY BUS (on lateral panel XFEED) - Nil - DC BUS 2 (on lateral panel HYD PWR AUX PUMP CTL IND NORM) HOT MAIN BAT BUS (on lateral panel HYD PWR AUX PUMP CTL IND GND) - Nil - EQUIPMENT Auxiliary pump control MFC LOGIC See Chapter 1.01 Mod: 5948 1.12.10 HYDRAULIC SYSTEM P 10 GENERAL 001 FEB 12 AA SYSTEM MONITORING The hydraulic indicating system alerts the crew if a hydraulic fluid low level, low pressure or overtemperature occur. HYD BLUE LO LVL/GREEN LO LVL R This caution is generated when the fluid level falls below 2.5 L (0.67 US Gal) in one section. Aural and visual alert are : - MC light flashing amber R - “HYD BLUE LO LVL” or “HYD GREEN LO LVL” amber message on EWD - Aural alert is Single Chime - “LO LVL” amber indication on SD ACW/HYD page. - “LO LVL” amber light illuminates on the HYD PWR panel. HYD BLUE(GREEN) LO PR This caution is generated when a pump control is pressed (in) and the hydraulic fluid R pressure falls below 1500 PSI. Aural and visual alert are : - MC light flashing amber - “HYD BLUE (GREEN) LO PR” amber message on EWD - Aural alert is Single Chime. - “LO PR” amber indication on SD ACW/HYD page. - “LO PR” amber light illuminates on the HYD PWR panel. HYD AUX LO PR This caution is generated when the auxiliary pump control is pressed (in) and the hydraulic R fluid pressure falls below 1500 PSI. Aural and visual alert are : - MC light flashing amber - “HYD AUX LO PR” amber message on EWD - Aural alert is Single Chime. - AUX “LO PR” amber indication on SD ACW/HYD page. - AUX “LO PR” amber light illuminates on the HYD PWR panel. Mod: 5948 1.12.10 HYDRAULIC SYSTEM P 11/12 001 GENERAL FEB 12 AA HYD BLUE(GREEN) OVHT This caution is generated if the fluid temperature exceeds 121°C (250°F) . Aural and visual alert are : - MC light flashing amber - “HYD BLUE(GREEN) OVHT” amber message on EWD - Aural alert is Single Chime. - “OVHT” amber indication on SD ACW/HYD page. - “OVHT” amber light illuminates on the HYD PWR panel. HYD AUX OVHT R This caution is generated if the fluid temperature exceeds 121°C (250°F) Aural and visual alert are : - MC light flashing amber - “HYD AUX OVHT” amber message on EWD - Aural alert is Single Chime. - AUX “OVHT” amber indication on SD ACW/HYD page. - AUX “OVHT” amber light illuminates on the HYD PWR panel. HYD PUMPS LOSS This caution is generated in case of a loss of both main hydraulic pumps. Aural and visual alert are: - MC light flashing amber - “HYD PUMPS LOSS” amber message on EWD - Aural alert is Single Chime. - “LO LVL”, and/or “LO PR”and/or “OVHT” amber indication on SD ACW/HYD cabin page - “LO LVL”, and/or “LO PR” and/or “OVHT” amber light illumination on the HYD PWR panel HYD SYS LOSS This caution is generated in case of a loss of both hydraulic system. Aural and visual alert are: - MC light flashing amber - “HYD SYS LOSS” amber message on EWD - Aural alert is Single Chime. - “LO LVL”, and/or “LO PR”and/or “OVHT” amber indication on SD ACW/HYD cabin page - “LO LVL”, and/or “LO PR” and/or “OVHT” amber light illumination on the HYD PWR panel. Mod: 5948 . 1.12.10 HYDRAULIC SYSTEM P 13 GENERAL AA 10.4 SCHEMATIC Mod: 5948 001 APR 11 . 1.13.00 ICE AND RAIN PROTECTION P1 CONTENTS AA 1.13.00 CONTENTS 1.13.10 GENERAL 1.13.20 ANTI ICING ADVISORY SYSTEM 20.1 DESCRIPTION 20.2 CONTROLS AND INDICATING 20.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 1.13.30 ENGINE AND WING PROTECTION 30.1 DESCRIPTION 30.2 CONTROLS 30.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 30.4 SCHEMATIC 1.13.40 PROPELLER ANTI ICING 40.1 DESCRIPTION 40.2 CONTROLS 40.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 40.4 LATERAL MAINTENANCE PANEL 1.13.50 WINDOW HEAT 50.1 DESCRIPTION 50.2 CONTROLS 50.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 50.4 LATERAL MAINTENANCE PANEL Mod: 5948 001 APR 11 1.13.00 ICE AND RAIN PROTECTION P2 CONTENTS AA 1.13.60 PROBE HEAT 60.1 DESCRIPTION 60.2 CONTROLS 60.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 1.13.70 RAIN PROTECTION 70.1 DESCRIPTION 70.2 CONTROLS 70.3 ELECTRICAL SUPPLY 1.13.80 AIRCRAFT PERFORMANCE MONITORING (APM) 80.1 DESCRIPTION 80.2 CONTROLS AND INDICATING 80.3 ELECTRICAL SUPPLY/SYSTEM MONITORING Mod: 5948 001 APR 11 GENERAL P 1/2 APR 11 001 1.13.10 Note : As per FCOM 2.02.08 icing condition are considered on ground when SAT is below 5°C on ground or TAT below 7°C in flight, with any form of visible moisture. For electrical heating, the power is supplied primarily by AC wild current. Rain removal from the front windshields is achieved by windshield wipers. For the pneumatic system, the engines supply bleed air through the LH and RH deice valves regardless of the engine bleed valves position. - Electrical heating of : S propeller blades, S windshields, S probes, S flight control horns. - A pneumatic system operating on areas of the airframe : S outer center and inner wing leading edges, S horizontal tailplane leading edges, S engine air intakes and gas paths. Aircraft ice protection is provided by : An ice detector, connected to the FWS, monitors ice accretion. In addition, an icing evidence probe is installed to indicate visualy an ice accretion. In parallel, an Aircraft Performance Monitoring (APM), triggers some alerts when the performances are degradated due to ice accretion on the airframe. The ice and rain protection systems permit aircraft operation in various environmental conditions and, in particular, in icing situations. Mod: 5948 AA ICE AND RAIN PROTECTION . 1.13.20 ICE AND RAIN PROTECTION P1 ANTI ICING ADVISORY SYSTEM 001 APR 11 20.1 DESCRIPTION An anti icing advisory system (AAS) is installed. The AAS system includes : - An ice detector - An icing evidence probe - ICING AOA (green) light on central panel - ICING (amber) label on FMA - Some labels are displays on the memo panel display This system has been designed to alert the crew on the correct procedures to be applied when flying in icing conditions : - Increase of minimum maneuver/operation speeds + selection of anti-- icing - Selection of the deicing system at first indication of ice accretion - Switching the deicing system OFF when ice does not build up any more on the airframe. ICE DETECTOR The ice detector, located under the left wing, alerts the crew as soon as and as long as ice accretion is sensed by the probe. Alert is generated by the amber ICING message on FMA. The system is self tested constantly, and any failure generates a FAULT light illumination with single chime. Detection of ice accretion and associated alert are performed under following cycle : CAUTION The ice detector indicates ice accretion is building up on aircraft. Therefore, extinguishing of the icing message must be regarded as an end of ice accretion and not as an absence of ice on the aircraft. Consequently a visual check must be performed to assure aircraft is cleared of ice after having encountered ice accretion conditions. Mod: 5948 1.13.20 ICE AND RAIN PROTECTION P2 ANTI ICING ADVISORY SYSTEM 001 APR 11 AA ICING EVIDENCE PROBE Located under left side window of the cockpit, visible by both pilots, provides information of ice accretion and is shaped to retain ice when all other parts of aircraft airframe are free of ice. An integrated light is provided to help ice accretion monitoring at night using the NAV light switch. Mod: 5948 1.13.20 ICE AND RAIN PROTECTION P3 ANTI ICING ADVISORY SYSTEM 001 APR 11 AA 20.2 CONTROLS AND INDICATING ICE DETECTOR PANEL (1) ICING AOA pb - “ICING AOA” illuminates green as soon as one horns anti icing Pb is selected ON, reminding the crew of stall alarm threshold being lower in icing conditions. “ICING AOA” green label is displayed on FMA. - “ICING AOA” can only be extinguished manually by depressing it, provided both horns anti icing are selected OFF. In this case, stall alarm threshold recovers the values defined for flight in normal conditions. (2) ICE DET PTT The push to test pb is used to check the ice detector correct operation. Press and hold test button for 3 seconds. - “ICING” amber label is displayed flashing on FMA (with associated warning) if system works correctly. - “A-- ICING DETECT” alert is displayed with associated procedure on EWD. Master Caution light and Single Chime are activated. Mod: 5948 1.13.20 ICE AND RAIN PROTECTION P4 ANTI ICING ADVISORY SYSTEM 001 APR 11 AA DE- ICING INDICATOR MEMO PANEL DISPLAY (1) ANTI-- ICING message When a anti-- icing system is selected ON and is not failed, a cyan specific message is displayed, corresponding to the involved anti-- icing system. If the selected system is failed, an amber message is displayed. (2) DE-- ICING message When a de-- icing system is selected on and is not failed, a cyan specific message is displayed, corresponding to the involved de-- icing system (AIRFRAME and 1 ENG 2). For AIRFRAME: - “AIRFRAME” cyan message is displayed steady when the airframe de-- icing system is selected ON. - “AIRFRAME” message flashes when the airframe de-- icing system is still selected ON five minutes after last ice accretion detection. - “AIRFRAME” message is displayed steady amber in case of de-- icing system failure. Mod: 5948 1.13.20 ICE AND RAIN PROTECTION P5 ANTI ICING ADVISORY SYSTEM 001 APR 11 AA 20.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT Ice detector ICING AOA light DC BUS SUPPLY (C/B) - Nil DC EMER BUS (on lateral panel DE ICING-- AAS/Boots A and B ind) AC BUS SUPPLY (C/B) ACW BUS 2 (on lateral panel ICE DET PWR SPLY) - Nil - MFC LOGIC See chapter 1.01 SYSTEM MONITORING A-- ICING DETECT This caution is generated in case of ice detector failure. Visual and aural alerts are : - MC light flashing amber - “A-- ICING DETECT” amber message on EWD - Aural alert is Single Chime (SC) - “FAULT” legend illuminates amber on the ICE DETECT pb switch Mod: 5948 . 1.13.30 ICE AND RAIN PROTECTION P1 ENGINE AND WING PROTECTION 001 APR 11 30.1 DESCRIPTION (See schematic p 10/11) The operating principle is to sequentially inflate the boots in order to remove ice. The de ice valves control the delivery pressure to 1.4 bar (20.3 psi). Seven distribution valves control air supply to the boots : - valve (1) to LH engine air intake and separation chamber, - valve (2) to RH engine air intake and separation chamber, - valve (3) to LH outer wing leading edge, - valve (4) to LH center wing leading edge and LH internal wing leading edge, - valve (5) to RH outer wing leading edge, - valve (6) to RH center wing leading edge and RH internal wing leading edge, - valve (7) to horizontal tailplane leading edge, Each of these distribution valves has one input and two outputs A and B, each controlled by the MFC. Two types of boots are used : - Chordwise boots for the leading edges and the gas paths - Annular boots for the engine intakes. When deflated, the boots are held to the structure thanks to a venturi supplied by bleed air. Note : The system is designed to remain operative with one engine inoperative through a common air manifold, except icing protection of the inoperative engine which is lost. CAUTION :With this type of boots, there is no need to wait for ice accretion on airframe before selecting it ON. This system MUST be selected ON as soon as and as long as ice accretion develops on airframe. Mod: 5948 1.13.30 ICE AND RAIN PROTECTION P2 ENGINE AND WING PROTECTION 001 FEB 12 AA TIME SEQUENCE DIAGRAM NORMAL MODE (PILOTED BY MFC) BEGINNING OF THE FOLLOWING SEQUENCE AT: - 60 sec (FAST MODE (SAT > - 20° C) - 180 sec (SLOW MODE (SAT < - 20° C) OVRD MODE (SEPARATED TIMER AND FAST MODE ONLY) BEGINNING OF THE FOLLOWING SEQUENCE AT 60 SEC (FAST MODE) R Note : When de icing OVRD mode is selected, boots inflate according to a separate timer and MFC is totally bypassed. Mod: 5948 1.13.30 ICE AND RAIN PROTECTION P3 ENGINE AND WING PROTECTION 001 FEB 12 30.2 CONTROLS ENGINE ANTI- ICING AND WING DE ICING PANEL 1 2 R AIRFRAME AIR BLEED pb Controls both de ice and isolation valves. Pb pressed in Normal operation. Both DE ICE and ISOLATION VALVES are open. OFF (pb released) OFF light comes on white. Both DE ICE and isolation valves are closed. However engine de-- icing may be used (engine de-- icing selected ON will open de-- ice valve). But airframe de-- icing is never available. FAULT The light illuminates amber and the FWS is activated when : - Air pressure downstream of the de-- ice valves stays below 14 PSI. - Air temperature upstream of the de-- ice valves exceeds 230°C. ”A-- ICING BLEED” alert is displayed with associated procedure on EWD. Master Caution light and Single Chime are activated. The alert is inhibited when pb is released. AIRFRAME pb Controls the outputs A and B of both wings and stabilizers distribution valves. ON (pb pressed in) Signal is sent to the MFC in order to initiate a de-- icing cycle depending on MODE SEL pb. ON light illuminates cyan. Pb released Associated boots stay deflated. FAULT The light illuminates amber and the FWS is activated when inflation sequencing of airframe boots A or B is not correct. - Associated distribution valve output has been controlled open but no downstream pressure has been detected, or - Associated distribution valve output has been controlled closed but a downstream pressure is detected.” ”A-- ICING FRAME” alert is displayed with associated procedure on EWD. Master Caution light and Single Chime are activated. “AIRFRAME” amber label is displayed on the memo panel display of MFD. Mod: 5948 1.13.30 ICE AND RAIN PROTECTION P4 ENGINE AND WING PROTECTION 001 FEB 12 AA R R 3 ENGINE pbs Control de-- ice valves, as well as the outputs A and B of respective engine distribution valves. ON (pb pressed in) De-- ice valve is controlled open even if Airframe Airbleed is not selected ON, and a signal is sent to the MFC in order to initiate a cycle. ON light illuminates cyan. ”ENG” cyan label is displayed on the memo panel display of MFD. Pb released Associated boots stay deflated. Also controls associated de-- ice valve in closed position, after Airframe Airbleed FAULT and ENG FAULT. FAULT Light illuminates amber and FWS is activated when : - Associated distribution valve output has been controlled open but no downstream pressure has been detected, or - Associated distribution valve output has been controlled closed but a downstream pressure is detected. - AIRFRAME AIRBLEED pb selected OFF and air temperature upstream of the de-- ice valve exceeds 230°C. - Inflation sequencing of engine boots A or B is not correct. ”A-- ICING ENG” alert is displayed with associated procedure on EWD. Master Caution light and Single Chime are activated. ”ENG” amber label is displayed on the temporary selections window of MFD. 4 DE ICING MODE SEL pb > - 20° C and < - 20° C Controls the selection of wings/engines boots inflation cycles when MAN is selected on MODE SEL AUTO pb 6 FAST (pb released) timing cycle = 60 s SLOW (pb pressed in) timing cycle = 180 s - SLOW light illuminates cyan. 5 DE--ICING OVERRIDE guarded pb Controls the emergency de-- icing operation. The push-- button enables control of all dual valves (ENG and AIR FRAME). NORM (pb released) Normal operation OVRD (pb pressed in) The emergency de-- icing activation is selected (timing cycle = 60 s), the light illuminates white and all de-- icing lights extinguish. This position is used when the associated FAULT light illuminates. FAULT The light illuminates amber when both MFC modules associated to air intake boots control fail resulting in an incorrect inflation sequencing. ”A-- ICING SEL” alert is displayed with associated procedure on EWD. Master Caution light and Single Chime are activated Mod: 5948 1.13.30 ICE AND RAIN PROTECTION P5 ENGINE AND WING PROTECTION 001 FEB 12 AA 6 MODE SEL AUTO pb Pb released Normal operation (automatic operating mode). The DE-- ICING MODE SEL pb (4) is inoperative. The cycle selection is provided by ADC data computation through CAC and MFC. FAULT Illuminates amber and the FWS is activated when MFC (1B or 2B) and/or ADC or CPM or IOM failure occurs. The DE-- ICING MODE SEL pb (4) is inoperative. In this case the FAST mode is automatically activated. MAN (pb pressed in) The DE-- ICING MODE SEL pb (4) is operative and allows the crew to select the appropriate timing cycle depending on SAT. MAN illuminates white. R MEMO PANEL DISPLAY Mod: 5948 1.13.30 ICE AND RAIN PROTECTION P6 ENGINE AND WING PROTECTION 001 FEB 12 HORNS ANTI ICING PANEL HORNS ANTI ICING pbs Controls activation of following units : - RUD and L ELEV : Rudder and left elevator horns anti icing - AIL and R ELEV : Ailerons and right elevator horns anti icing ON R R R OFF FAULT (pb pressed in) : associated anti icing units are activated. ON light illuminates cyan. “HORN” cyan label is displayed on the memo panel display of MFD. As soon as a ”HORN” is selected ”ON”, ICING AOA light is illuminated on Ice Detector panel.(refer to 1.13.20 p3) (pb released) : associated anti icing units are deactivated. The light illuminates amber and the FWS is activated when electrical power is lost on one of the associated units. “HORN” amber label is displayed on the memo display panel of MFD. Note : As soon as at least one of the HORNS anti icing pb is selected ON, stall alert threshold is reduced (refer FCOM 1.02). Horns heating is inhibited on ground. MEMO DISPLAY PANEL Mod: 5948 1.13.30 ICE AND RAIN PROTECTION P7 001 ENGINE AND WING PROTECTION FEB 12 AA 30.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT De ice valves Isolation valves Distribution valves (Boots A + ENG 1) Distribution valves (Boots B + ENG 2) Controls and alerts R Left elevator and rudder horns anti icing Left elevator and rudder horns anti icing control R Right elevator and ailerons horns anti icing Right elevator and ailerons horns anti icing control MFC LOGIC See chapter 1.01. Mod: 5948 DC BUS SUPPLY (C/B) DC BUS 2 (on lateral panel SO and REG VALVE 1 and 2) DC ESS BUS (on lateral panel ISOL VALVE 1 and 2) DC EMER BUS (on lateral panel ENG 1 and AFR-- BOOTS A SPLY) DC BUS 2 (on lateral panel ENG 2 and AFR-- BOOTS B NORM SPLY) and DC EMER BUS (BACK UP) (on lateral panel ENG 2 and AFR-- BOOTS B EMER SPLY) DC EMER BUS (on lateral panel CTL and CAUTION) - Nil DC EMER BUS (on lateral panel L ELEV and RUD) - Nil DC EMER BUS (on lateral panel R ELEV and AIL) AC BUS SUPPLY (C/B) - Nil - Nil - Nil - Nil - 115 V ACW BUS 1 (on lateral panel L ELEV RUD) - Nil 115 V ACW BUS 2 (on lateral panel R ELEV R AIL L AIL) - Nil - 1.13.30 ICE AND RAIN PROTECTION P8 ENGINE AND WING PROTECTION AA 001 FEB 12 SYSTEM MONITORING A-- ICING BLEED This caution is generated when a LOW pressure is detected in the de icing common air manifold (P < 14 PSI and t > 6s) or over temperature (T > 230_C (410_F)) upstream the pressure regulating valve. Visual and aural alerts are : - MC light flashing amber - “A-- ICING BLEED” amber message on EWD - Aural alert is Single Chime (SC) - “FAULT” legend illuminates amber on the AFR AIR BLEED pb switch A-- ICING AUTO This caution is generated in case of MFC 1B or 2B and/or ADC failure (Discrepancy between outputs). Visual and aural alerts are : - MC light flashing amber - “A-- ICING AUTO” amber message on EWD - Aural alert is Single Chime (SC) - “FAULT” legend illuminates amber on the SEL/AUTO pb switch A-- ICING SEL R This caution is triggered when the stand-- by de-- icing controller detects that the MFC does not drive the de-- icing cycles of the engine boots as per schedule. The caution is triggered as soon as boots A or B are supplied for more than 20 sec or when either boots A and B are supplied simultaneously for 200 sec or boots A or B are not supplied within a 200 sec timeframe. Visual and aural alerts are : - MC light flashing amber - “A-- ICING SEL” amber message on EWD - Aural alert is Single Chime (SC) - “FAULT” legend illuminates amber on the SEL/NORM pb switch A-- ICING FRAME This caution in generated when the distribution valve output is controlled open but no downstream pressure is detected or controlled closed but downstream pressure is detected. Visual and aural alerts are : - MC light flashing amber - “A-- ICING FRAME” amber message on EWD - Aural alert is Single Chime (SC) - “FAULT” legend illuminates amber on the AIRFRAME pb switch Mod: 5948 1.13.30 ICE AND RAIN PROTECTION P 9/10 ENGINE AND WING PROTECTION 001 APR 11 AA A-- ICING ENG 1(2) This caution in generated when the distribution valve output is controlled open but no downstream pressure is detected or controlled closed but downstream pressure is detected. Visual and aural alerts are : - MC light flashing amber - “A-- ICING ENG 1(2)” amber message on EWD - Aural alert is Single Chime (SC) - “FAULT” legend illuminates amber on the ENG 1(2) pb switch A-- ICING HORNS 1(2) This caution in generated in case of a power loss on a horn anti-- icing unit. Visual and aural alerts are : - MC light flashing amber - “A-- ICING HORNS 1(2)” amber message on EWD - Aural alert is Single Chime (SC) - “FAULT” legend illuminates amber on the affected HORN pb switch Note: Anti Icing caution messages will also be generated in cases of various IOM and CPM failures that will trigger indication signals losses. (refer to 1.01.40 - CPM/IOM LOST EQUIPMENT LIST) Mod: 5948 . 1.13.30 ICE AND RAIN PROTECTION P 11 ENGINE AND WING PROTECTION AA 30.4 SCHEMATIC Mod: 5948 001 APR 11 . 1.13.40 ICE AND RAIN PROTECTION P1 PROPELLER ANTI ICING 001 APR 11 40.1 DESCRIPTION Propeller anti icing is performed by resistors installed near the surface of the inboard sections of the blade leading edges. On each propeller, the heating elements are electrically connected in three blades (every other blade). The system is supplied with 115 ACW. Two modes are available and automatically selected depending on the temperature. When selected on, the propeller anti icing system starts to heat the blades only when NP is sensed above 63%. TIME SEQUENCE DIAGRAM MODE SEL : NORMAL OPERATION LOW POWER CYCLE MODE SEL : ON HIGH POWER CYCLE Mod: 5948 1.13.40 ICE AND RAIN PROTECTION P2 PROPELLER ANTI ICING 001 FEB 12 AA 40.2 CONTROLS PROPELLER ANTI ICING PANEL 1 PROP pb Controls the respective propeller heating elements. ON 2 (pb pressed in), the heating units are supplied. The ON light illuminates cyan. ”PROP” cyan label is displayed on the memo panel display of MFD. pb released The heating elements are not supplied. FAULT The light illuminates amber to indicate that at least one blade is not electrically supplied. ”A-- ICING PROP” alert is displayed with associated procedure on EWD. Master Caution light and Single Chime are activated. ANTI--ICING MODE SEL pb Controls the duration of propeller anti icing cycles when MAN is selected on MODE SEL AUTO pb 3 . pb released LOW POWER cycle is selected. ON (pb pressed in) HIGH POWER cycle is selected. The ON lt illuminates cyan. R Note : • Low Power (pb OUT) for temperature greater than - 10° C(14° F). • High Power (pb IN) for temperature between - 10° C(14° F) and - 30° C(-- 22° F). • Below - 30°C (-- 22°F) icing problems should be non existant (no supercooled water). Mod: 5948 1.13.40 ICE AND RAIN PROTECTION P3 PROPELLER ANTI ICING 001 APR 11 AA 3 MODE SEL AUTO pb (same pb as ENGINE AND WING PROTECTION) pb released Normal operation (automatic operating mode) The ANTI-- ICING MODE SEL pb 2 is inoperative. The cycle selection is provided by ADC 1, MFC 1B, ADC 2 and MFC 2B FAULT Illuminates amber and the FWS is activated when MFC (1B or 2B) and/or ADC failure occurs. The ANTI-- ICING MODE SEL pb 2 is inoperative. In this case, the HIGH POWER CYCLE is automatically activated. MAN (pb pressed in) The ANTI-- ICING MODE SEL pb 2 is operative and allows the crew to select the appropriate timing cycle depending on SAT. MAN illuminates white. MEMO PANEL DISPLAY Mod: 5948 1.13.40 ICE AND RAIN PROTECTION P4 PROPELLER ANTI ICING 001 FEB 12 AA 40.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY R EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Propeller 1 anti icing PWR - Nil - ACW BUS 1 (on lateral panel PROP1 ANTI ICING PWR SPLY) Propeller 2 anti icing PWR - Nil - ACW BUS 2 (on lateral panel PROP2 ANTI ICING PWR SPLY) Prop anti icing CTL and Ind DC EMER BUS (on lateral panel PROP CTL and IND) MFC LOGIC See chapter 1.01. SYSTEM MONITORING A-- ICING PROP 1(2) This caution is generated when one or more blade heating unit (s) is/are inoperative. Visual and aural alerts are : - MC light flashing amber - “A-- ICING PROP 1(2)” amber message on EWD - Aural alert is Single Chime (SC) - “FAULT” legend illuminates amber on the affected PROP pb switch Note 1: In case of IOM cards or CPM losses propeller anti icing function can be lost. Refer to chapter 1.01.40 for detailed information. Note 2: Anti Icing caution messages will also be generated in cases of various IOM and CPM failures that will trigger indication signals losses. (refer to 1.01.40 - CPM/IOM LOST EQUIPMENT LIST) Mod: 5948 1.13.40 ICE AND RAIN PROTECTION P5 PROPELLER ANTI ICING 001 APR 11 AA 40.4 LATERAL MAINTENANCE PANEL On the RH Maintenance panel, controls are provided for maintenance purposes only, to check propeller anti icing system. PROPELLER ANTI ICING TEST PUSH- BUTTON This guarded push-- button is used to check the propeller anti icing system functioning. It must only be operated on ground, with propellers above 63 % NP. Test procedure : - Aircraft on ground, propeller > 63 % NP. - Mode select (overhead panel) : NORM. - Push test Button. - The system performs a short anti icing cycle. Mod: 5948 . 1.13.50 ICE AND RAIN PROTECTION P1 WINDOW HEAT 001 FEB 12 50.1 DESCRIPTION The cockpit windows are electrically heated : - The front windshields for ice protection and defogging. - The side windows for defogging only. The front windshields are protected against ice formation by an electrically heated R transparent film incorporated between two plies of glass. It is supplied with 200 V ACW, and temperature is controlled by an electronic controller which keeps the outer windshield temperature over 2°C (35°F). The inner surface remains above 21°C (70°F) to prevent mist formation. The side windows are protected by an electrically heated system consisting of small wires R embedded between two plies of glass. It is supplied with 28 volts DC and keeps the inner temperature over 21°C (70°F). Mod: 5948 1.13.50 ICE AND RAIN PROTECTION P2 WINDOW HEAT 001 FEB 12 50.2 CONTROLS (1) WINDSHIELD HTG L or R pb Controls activation of window heat systems : Pb pressed in Power is supplied to the associated window heat system. OFF (pb released) Window heat system is deactivated. The OFF light illuminates white. FAULT The light illuminates amber and the FWS is activated when there is a power loss. The light also illuminates during MFC test. R (2) SIDE WINDOWS pb Controls activation of side window heat systems : ON (pb pressed in) Power is supplied to both side windows heat systems. ON light illuminates blue. “SIDE WINDOW”cyan label is displayed on the temporary selections window of MFD. Pb released Side windows heat systems are deactivated. FAULT The light illuminates amber and the FWS is activated when there is a power loss. “SIDE WINDOW”amber label is displayed on the temporary selections window of MFD. MEMO PANEL DISPLAY Mod: 5948 1.13.50 ICE AND RAIN PROTECTION P3 WINDOW HEAT 001 FEB 12 AA 50.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY R EQUIPMENT LH Front windshield supply DC BUS SUPPLY (C/B) - Nil - Front windshield supply control - Nil - Front windshield alert DC BUS 2 (on lateral panel WDSHLD IND L) DC BUS 1 (on lateral panel side window left control) - Nil - Side window supply and control RH Front windshield supply RH Front windshield control - Nil - Front windshield alert DC BUS 1 (on lateral panel WDSHLD IND R) DC BUS 2 (on lateral panel side window rigth control) DC ESS BUS (on lateral panel side window CAUTION) Side window supply and control Side window alert MFC LOGIC See chapter 1.01. Mod: 5948 AC BUS SUPPLY (C/B) ACW BUS 1 (on lateral panel L FRONT WINDOW HTG) ACW BUS 2 (on lateral panel L FRONT CTL and CAUTION) - Nil - Nil ACW BUS 2 (on lateral panel R FRONT WINDOW HTG) ACW BUS 2 (on lateral panel R FRONT CTL and CAUTION) - Nil - Nil - Nil - 1.13.50 ICE AND RAIN PROTECTION P4 WINDOW HEAT 001 APR 11 AA SYSTEM MONITORING A-- ICING WINDOW This caution is generated in case of a loss of window heating Visual and aural alerts are : - MC light flashing amber - “A-- ICING WINDOW” amber message on EWD - Aural alert is Single Chime (SC) - “SIDE WINDOWS” amber message on the memo panel display - “FAULT” legend illuminates amber on the SIDE WINDOWS pb switch A-- ICING L(R) WSHLD This caution is generated in case of windshield system failure Visual and aural alerts are : - MC light flashing amber - “A-- ICING L(R) WSHLD” amber message on EWD - Aural alert is Single Chime (SC) - “FAULT” legend illuminates amber on the affected WINDSHIELDS HTG or SIDE WINDOW pb switch Note: Anti Icing caution messages will also be generated in cases of various IOM and CPM failures that will trigger indication signals losses. (refer to 1.01.40 - CPM/IOM LOST EQUIPMENT LIST) Mod: 5948 1.13.50 ICE AND RAIN PROTECTION P5 WINDOW HEAT 001 FEB 12 AA 50.4 LATERAL MAINTENANCE PANEL On the RH Maintenance panel, controls are provided for maintenance purposes only, to check windshield heat system. R WINDSHIELD HEATING PUSH TO TEST BUTTON Test push-- button Is used to check the windshield head controller functioning. Test procedure : - Press and hold test button for 3 seconds. - The B.I.T.E. executes a programmed check of the controllers, ending with de-- energization of both overheat power relays. - MFC magnetic indicator illuminates on the RH maintenance panel when a failure has been detected during the windshield heating cycle. Mod: 5948 . 1.13.60 ICE AND RAIN PROTECTION P1 PROBE HEAT 001 APR 11 AA 60.1 DESCRIPTION To prevent icing on air data sensors, electrical heating is provided for : - CAPT, F/O, STBY, pitot tubes - CAPT, F/O, STBY left and right static ports - F/O alpha (angle of attack) probe - CAPT alpha (angle of attack) probe - TAT probes The probes are heated both on the ground and in flight, except TAT sensors heating which are inhibited on the ground. 60.2 CONTROLS PROBE HEAT PANEL (1) PITOT lights Illuminates amber and the FWS is activated when the respective probe is not heated. - In flight or on the ground, the associated pitot is not heated (2) ALPHA, TAT lights Illuminates amber and the FWS is activated when the respective probe is not heated. (3) STAT lights Illuminates amber and the FWS is activated when the respective probe is not heated. In flight, static ports are not monitored by FWS. (4) CAPT STBY F/O pbs Controls the activation of probe heating of their respective circuits. ON (pb pressed in) Probe heating is activated. OFF (pb released) Probe heating is deactivated. OFF light illuminates white. Respective PROBE HEAT light illuminates amber. Mod: 5948 1.13.60 ICE AND RAIN PROTECTION P2 PROBE HEAT 001 APR 11 60.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT CAPT Pitot tubes Alpha probe Static ports Alerts TAT probe DC BUS SUPPLY (C/B) - Nil DC BUS 1 (on lateral pane CAPT STATl) DC ESS BUS (on lateral alert CAUTION) - Nil - F/O STAT Pitot tubes - Nil - Alpha probe - Nil - Static ports DC BUS 2 (on lateral panel F/O STAT) Alerts TAT probe DC BUS 2 (on lateral panel CAUTION) - Nil - STBY Pitot tube - Nil - Static ports Alerts MFC LOGIC See chapter 1.01 Mod: 5948 DC BUS 1 (on lateral panel STBY STAT) DC ESS BUS (on lateral panel CAUTION) AC BUS SUPPLY (C/B) ACW BUS 1 (on lateral panel PITOT) ACW BUS 1 (on lateral panel ALPHA) - Nil - Nil ACW BUS 1 (on lateral panel CPT TAT) ACW BUS 2 (on lateral panel PITOT) ACW BUS 2 (on lateral panel ALPHA) - Nil - Nil ACW BUS 2 (on lateral panel F/O TAT) ACW BUS 1 and 115 VAC STBY BUS (on lateral panel STBY PITOT NORM SPLY and EMER SPLY) - Nil - Nil - 1.13.60 ICE AND RAIN PROTECTION P3 PROBE HEAT 001 APR 11 SYSTEM MONITORING A-- ICING PROBE This caution is generated when probe (s) is/are not heated. Visual and aural alerts are : - MC light flashing amber - “A-- ICING PROBE” amber message on EWD - Aural alert is Single Chime (SC) - Affected probe light illuminates amber on the PROBES HTG panel A-- ICING PIT CPT (F/O)(SBY) This caution is generated in case of failure of the static or pitot probes. Visual and aural alerts are : - MC light flashing amber - “A-- ICING PIT CPT(F/O)(SBY)” amber message on EWD - Aural alert is Single Chime (SC) - Affected PITOT light illuminates amber on the PROBES HTG panel A-- ICING TAT CPT (F/O) This caution is generated in case of failure of theTAT probe. Visual and aural alerts are : - MC light flashing amber - “A-- ICING TAT CPT(F/O)” amber message on EWD - Aural alert is Single Chime (SC) - Affected TAT light illuminates amber on the PROBES HTG panel Note: Anti Icing caution messages will also be generated in cases of various IOM and CPM failures that will trigger indication signals losses. (refer to 1.01.40 - CPM/IOM LOST EQUIPMENT LIST) Mod: 5948 . 1.13.70 ICE AND RAIN PROTECTION P1 001 RAIN PROTECTION APR 11 AA 70.1 DESCRIPTION Rain removal from front windshields is provided by two wipers : each wiper is driven by a two speed electric motor. They are controlled by two WIPER selectors on the overhead panel : one for the Captain, and one for the F/O. Maximum speed to operate the wipers is 160 kt. 70.2 CONTROLS WIPER rotary selector Controls the windshield wiper on the associated side. FAST wiper operates at 130 cycles/mn. SLOW wiper operates at 80 cycles/mn. OFF wiper operation stops at the end-- of-- travel (Park) position. 70.3 ELECTRICAL SUPPLY EQUIPMENT Captain wiper F/O wiper Mod: 5948 DC BUS SUPPLY (C/B) DC ESS BUS (on lateral panel CAPT) DC BUS 2 (on lateral panel F/O) . AIRCRAFT PERFORMANCE MONITORING P 1/2 APR 11 001 1.13.80 Mod: 5948 There are 4 different APM alarm indication display on FMA (Flight Management Annunciator) and/or EWD: - ”Cruise Speed Low” cyan indicator (on FMA and EWD) - ”Degraded Perf” amber indicator (on FMA and EWD) - ”Increase Speed” amber flashing (on FMA and EWD) - APM FAULT (on EWD) In order to be able to compute speeds, the APM needs to know the aircraft actual weight. This information is taken from the FMS inserted value, should there be no weight information the APM will do a weight estimation and use it for flight computation. The APM will when active compare aircraft drag with theoretical drag for the actual weight. The parameters are rolled over in order to have a smoothed analysis thus avoiding spurious alarms in the cockpit. APM analysis is only done when both engines are operating, flaps and gear retracted. It is performed during climb, cruise and descent. In cruise a further monitoring of the speed will be done comparing actual speed with minimum time speed at maximum cruise power. The APM analysis will only occur if the aircraft is considered in icing conditions by the computer: - ICING AOA illuminated - Airframe de-- icing selected on - Ice accretion detected - SAT below 10°C APM OPERATION : The CAC manage APM FAULT/OFF and also APM alarm display through EWD and PFD. The CAC realizes the interface between MPC and cockpit APM Alarm and caution (displayed on EWD and PFD). APM COCKPIT INTERFACE The APM function is to monitor the aircraft drag in icing conditions in order to alert the crew of a risk of severe icing conditions. The speed in cruise will be also monitored to alert the crew of an abnormal speed decrease in icing conditions. The APM will check also that the MSIS (Minimum Severe Icing Speed) is respected. 15.1 DESCRIPTION AA ICE AND RAIN PROTECTION . 1.13.80 ICE AND RAIN PROTECTION P3 ANTI ICING ADVISORY SYSTEM 001 APR 11 AA 15.2 CONTROLS AND INDICATING APM CONTROL PANEL (1) APM PTT pb Used to test the APM function.This test shall be performed daily by the crew, to determine whether the APM components are operational. (2) APM indicator pushbutton This indicator light is used to inform the crew of an APM failure. In case of a FAULT indication, the APM shall be selected OFF through this push-- button, and in this case the OFF indication shall be illuminated. OFF APM function in OFF position (illuminates white) FAULT Illuminates amber in case of APM FAULT (“APM FAULT” alert is triggered by FWS ). The APM FAULT is inhibited on ground. The APM FAULT will be triggered by the MPC in case of internal failure or invalid aircraft parameters. Mod: 5948 1.13.80 ICE AND RAIN PROTECTION P4 AIRCRAFT PERFORMANCE MONITORING 001 APR 11 AA 15.3 ELECTRICAL SUPPLY/SYSTEM MONITORING ELECTRICAL SUPPLY As APM is a function managed by the CAC through the MPC, refer to MPC chapter (1.01.20) for Electrical Supply information. SYSTEM MONITORING APM FAULT This caution is generated when there is a problem in the APM computation, either in the MPC or in the aircraft wiring. Visual and aural alert are : - MC light flashing amber - “APM FAULT” amber message on EWD - Aural alert is Single Chime (SC) NOTE: As APM computation is not operative on Ground, the APM Fault is inhibited by the computer on Ground. CRUISE SPEED LOW This attention getter is generated only in Cruise Mode to inform the crew that the aircraft speed is 10kt lower than the theoretical maximum cruise speed and that there is a small drag increase. - “CRZ SPD LO” cyan message on FMA - Associated procedure (normal procedure) on EWD Mod: 5948 1.13.80 ICE AND RAIN PROTECTION P5 AIRCRAFT PERFORMANCE MONITORING 001 APR 11 AA DGD PERF This caution is generated when there is an abnormal drag increase that could be due to the severe icing conditions. Visual and aural alerts are: - MC light flashing amber - “DGD PERF” amber message on FMA - “DGD PERF” amber message on EWD - Aural alert is Single Chime (SC) INCREASE SPEED This caution is generated when the aircraft speed is lower than Minimum Severe Icing Speed + 2 kt. Visual and aural alerts are : - MC light flashing amber - “INCREASE SPEED” amber message on FMA - “INCREASE SPEED” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 . 1.14.00 LANDING GEAR P1 CONTENTS AA 1.14.00 CONTENTS 1.14.10 GENERAL 1.14.20 LANDING GEAR 20.1 DESCRITION 20.2 CONTROLS 20.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 20.4 LATERAL MAINTENANCE PANEL 1.14.30 NOSE WHEEL STEERING 30.1 DESCRITION 30.2 CONTROLS 30.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 30.4 SCHEMATIC 1.14.40 BRAKES ANTI SKID 40.1 DESCRITION 40.2 CONTROLS 40.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 40.4 LATERAL MAINTENANCE PANEL 40.5 SCHEMATICS Mod: 5948 001 APR 11 . 1.14.10 LANDING GEAR P1 GENERAL 001 FEB 12 AA R R The landing gear consists of a forward retracting nose gear and two retractable main gears mounted partially in the wheel well fairing and partially in the fuselage. They are hydraulically operated by green hydraulic system. Gear doors enclose the landing gear bays. Each main gear assembly has an oleopneumatic shock absorber and is equipped with two wheels. Each main wheel is fitted with brakes and anti skid. The nose gear assembly includes two wheels, an oleopneumatic shock absorber and a nose wheel steering system. In case of hydraulic or electrical power supply failure, the landing gear may be extended by gravity. Mod: 5948 . 1.14.20 LANDING GEAR P1 LANDING GEAR AA 20.1 DESCRIPTION MAIN LANDING GEAR NOSE LANDING GEAR Mod: 5948 001 APR 11 1.14.20 LANDING GEAR P2 LANDING GEAR 001 FEB 12 AA MAIN LANDING GEAR DOORS GEAR POSITION DETECTION AND INDICATION SYSTEMS The landing gear position detection and indication system consist of two independant systems. Primary system is managed by MFC module 1A. The associated gear position is displayed on the main instrument panel. Secondary system is managed by MFC module 2A. The associated gear position is displayed on the overhead panel. Each system uses its own detectors and indications : - down lock and air/ground signals from proximity sensors, - up lock signal from mechanical limit switches. Each system commands gear extension and retraction, gear anti retraction system and the warning associated to “LDG GEAR NOT DOWN”. R Note : Gear must be considered down when one system indicates three green lights ( ∇ ) Each system has its own Weight On Wheels circuit : WOW 1 into MFC module 1B and WOW 2 into MFC module 2B. The WOW signals are used by the MFC to have the system using WOW informations switched to the appropriate air/ground configuration. Mod: 5948 1.14.20 LANDING GEAR P3 LANDING GEAR 001 APR 11 AA GEAR NORMAL OPERATION Landing gear extension and retraction is performed by a control lever located on the center instrument panel. The MFC electrically controls the landing gear selector valve located in the LH main landing gear fairing. This valve supplies hydraulic pressure (green system) to : - Gear extension hydraulic line. The retraction line is then connected to tank return for extension. - Gear retraction hydraulic line. The extension line is then connected to tank return for retraction. Note 1 :The main gear wheels are automatically braked as soon as the lever is selected up. Note 2 :As soon as the gear is locked in the selected position, hydraulic pressure is released from the connecting line. Uplocking is mechanically achieved. Unlocking is hydraulically achieved. Down locking is achieved by a dual alignment folding side brace. Locking springs act as secondary alignment and ensure locking independently of hydraulic pressure availability. Unlocking is hydraulically achieved. Each main gear incorporates a door mechanism linked to it. The door is therefore operated by the gear during retraction and extension. Four doors close off the nose gear well and restore the fuselage profile. The doors are actuated mechanically by the gear itself. The two forward doors will be closed after gear extension while the two aft will remain open. Landing gear can not be retracted as long as at least one gear shock absorber senses weight on wheels. GEAR EMERGENCY EXTENSION In the event of normal system failure the landing gear can be extended mechanically. The system is controlled from the flight compartment by a push/pull handle which permits landing gear mechanical unlocking. The landing gear extends due to gravity and aerodynamic forces. Main landing gear extension is assisted by a gas actuator. Nose landing gear is assisted by a mechanical device. Mod: 5948 1.14.20 LANDING GEAR P4 LANDING GEAR 001 FEB 12 AA 20.2 CONTROLS LDG GEAR CONTROL PANEL (1) Landing gear position ind. Displays the gear position as sensed by MFC 1. ∇ illuminates green when respective down lock is sensed engaged. UNLK illuminates red when respective gear is not locked in R accordance with the lever selected position or, if on the ground, the uplock box is not in the open position. (2) Landing gear control lever The lever must be pulled out prior to selecting one of the two possible positions : Up The landing gear retraction is selected. Down The landing gear extension is selected. A red light is incorporated in the lever. Light will illuminate and the FWS will be activated through the MFC, whenever any gear is not sensed down and locked by the detection system. Mod: 5948 1.14.20 LANDING GEAR P5 001 LANDING GEAR FEB 12 AA LDG GEAR POSITION IND OVERHEAD PANEL R Display the gear position as sensed by MFC 2. ∇ illuminates green when respective down R lock is engaged.UNLK illuminates red when respective gear is not locked in accordance with R the lever selected position,or if on ground, the UPLOCK box is not in the open position. LDG GEAR EMERGENCY EXTENSION HANDLE Pulling the handle above the pedestal level will unlock the landing gear. MFD EXTENSION AND RETRACTION INDICATING R See MFD indicating descriptions in 1.14.20, page 9/10, topic LANDING GEAR. Mod: 5948 1.14.20 LANDING GEAR P6 LANDING GEAR 001 APR 11 AA 20.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) Primary detection system Landing gear CTL Ind and alert DC STBY BUS (on lateral panel LDG GEAR CTL) Secondary detection system Ind and Alert DC BUS 2 (on lateral panel IND and WARNING) Weight on wheels (air/ground detection) System 1 System 2 MFC LOGIC See chapter 1.01 Mod: 5948 DC EMER BUS (on lateral panel WOW SYS 1) DC BUS 2 (on lateral panel WOW SYS 2) 1.14.20 LANDING GEAR P7 LANDING GEAR 001 APR 11 AA SYSTEM MONITORING LDG GEAR NOT DN This warning is generated when gear are not seen downlocked in approach. It is also triggered when one of the two power levers is in IDLE position and gear are not seen downlocked. Visual and aural alerts are : - MW light flashing red - “LDG GEAR NOT DN” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) - L/G control lever grip light illuminates red Note : This warning is triggered when the flaps are at 30°, and when one of the three gears is not locked down. It is inhibited when the radio-- altitude is higher than 500 feet. Radio-- altitude failure deletes warning inhibition above 500 feet. During take-- off the warning is inhibited for 150 seconds. LDG GEAR This caution is generated when a discrepancy is detected between any gear position and L/G lever position after 30 seconds on down position. Visual and aural alerts are : - MC light flashing amber - “LDG GEAR” amber message on EWD - Aural alert is Single Chime (SC) - ”UNLK” legend illuminates red on overhead and central panel Mod: 5948 1.14.20 LANDING GEAR P8 LANDING GEAR 001 APR 11 AA 20.4 LATERAL MAINTENANCE PANEL W.O.W. SELECTOR (FOR MAINTENANCE ONLY) On the RH maintenance panel, a selector enables the weight on wheels systems to be selected to the “in flight” position when on the ground, for maintenance purposes. Mode Selector Controls the overriding of weight on wheels system. NORM The system works normally FLT The systems are forced to the in “FLIGHT” position. “MAINT PNL” amber caution is displayed on EWD. FAILURES DISPLAY A maintenance failure indication of any WOW proximity switch is provided via a specific MCDU maintenance page. Mod: 5948 1.14.30 LANDING GEAR P1 NOSE WHEEL STEERING 001 APR 11 AA 30.1 DESCRIPTION Nose wheel steering is provided by means of a servomechanism mechanically controlled from the flight compartment and powered by the blue hydraulic system. Control is achieved using the steering control hand wheel mounted on the captain’s lateral console. Nose steering angle is 60°. Nose wheel deflection of 91° is possible during towing with no pressure in the system. An internal mechanism returns the wheel to centered position when the aircraft is off the ground. A swivel valve shuts off hydraulic pressure to the steering system when the nose landing gear is not locked down and pressure is also shut off by a solenoïd valve when the main and nose gear shock absorbers are not compressed. Note : Should any gear rise from ground after all gears have been compressed, the steering control will be maintained as long as one gear at least, stays on ground. A switch is provided to deactivate the steering system if required. In case of either steering system deactivation or blue hydraulic pressure failure, the aircraft can be guided using differential braking and/or differential engine thrust. Mod: 5948 1.14.30 LANDING GEAR P2 NOSE WHEEL STEERING 001 FEB 12 AA 30.2 CONTROLS N/W STEERING SW This guarded sw controls activation/deactivation of the nose wheel steering system. It is a guarded type in the ON position. ON the steering solenoïd valve is electrically armed. The solenoïd is energized when the steering relay is excited. The valve opens when the steering hydraulic control is actuated. OFF Unpressurizes the steering system by de-- energizing the solenoïd valve. STEERING HANDWHEEL The steering handwheel controls the nose wheel steering angle up to 60 ° in either direction : - Clockwise : steering to the right - Counter clockwise : steering to the left Note : Nose wheel steering is self centering after lift - off. N/W STEERING MFD INDICATNG R See MFD indicating descriptions on table in 1.14.40 page 9/10 (topic : “NOSE WHEEL STEERING”) Mod: 5948 1.14.30 LANDING GEAR P 3/4 001 NOSE WHEEL STEERING APR 11 AA 30.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT Nose wheel steering selection valve DC BUS SUPPLY (C/B) DE EMER BUS (on lateral panel STEERING VALVE) MFC LOGIC See Chapter 1.01 SYSTEM MONITORING See MFD indicating descriptions on table chap 40 page 9/10 (topic : “NOSE WHEEL STEERING”) Mod: 5948 . 1.14.30 LANDING GEAR P5 NOSE WHEEL STEERING AA 30.4 SCHEMATIC Mod: 5948 001 APR 11 . 1.14.40 LANDING GEAR P1 BRAKES ANTI SKID 001 APR 11 AA 40.1 DESCRIPTION WHEELS AND BRAKES The four main gear wheels are equipped with mutidisc carbon brakes, each operated by hydraulically powered pistons. Two modes are available. - normal, controlled by pilot’s brake pedals and supplied by green system. - emergency and parking controlled by the emergency and parking brake handle and supplied by blue system. Each brake is equipped with an automatic adjuster, a wear indicator pin, and an overheat detector. The wheels are fitted with tubeless tires The main gear wheels are braked automatically as soon as the pilot selects up the landing gear control lever. The main gear wheels are fitted with three fusible plugs and one pressure relief valve which protect against tire and wheel burst in the event of overpressure overheat at fuse location. These fusible plugs are designed to release internal pressure when the wheel temperature exceeds 177°C/350°F. ANTI SKID SYSTEM The antiskid system is provided as soon as the gear is down and locked, and as long as the aircraft speed exceeds 10 kts. Each wheel and each pair of external or internal wheels are monitored. The aim of the system is to provide the maximum stopping performance by controlling brake pressure in order to minimize wheel slip, brake and tire wear, depending on runway conditions. Touchdown protection is ensured (spin up, locked wheel). The system consists of : - 4 wheel speed transducers (one per main gear wheel), - 1 control box - 1 antiskid module. A reference velocity signal is elaborated. The anti skid applies a deceleration law continuously adapting the actual wheel speed to the reference speed. Mod: 5948 1.14.40 LANDING GEAR P2 BRAKES ANTI SKID AA ANTI SKID BLOCK DIAGRAM Mod: 5948 001 APR 11 1.14.40 LANDING GEAR P3 BRAKES ANTI SKID 001 FEB 12 AA LOCKED WHEEL PROTECTION R The system includes locked wheel protection to preclude tire scuffing. The crossover is applied between inboard main wheels, and between outboard main wheels. For an aircraft speed above 23 kts a speed differential of 50% or greater between the two speed signals will result in generation of a locked wheel signal and thus in release of brakes. TOUCHDOWN PROTECTION At main gear compression, the braking action is inhibited as long as wheel spin up is below 35 kt or for 5s, in order to preclude inadvertent brake application prior to wheel spin up on low friction pavements or with light wheel vertical loading. In the event of electrical supply loss, the antiskid is no more operative and brakes are directly operated. Mod: 5948 1.14.40 LANDING GEAR P4 BRAKES ANTI SKID 001 FEB 12 AA 40.2 CONTROLS PILOT BRAKE PEDALS R Controls normal braking mode through the normal metering valve. R Differential braking is possible with brake pedal individually operated. EMERGENCY/PARKING BRAKE HANDLE R R Controls emergency and parking braking mode through the emergency and parking metering valve. Springloaded to the OFF position. EMER A metered pressure is applied to the brakes. PARKING Full pressure is applied to the brakes. CAUTION : Brake handle applies braking without any antiskid operation. Note 1 : In case of hydraulic power system failure, the brake accumulator allows at least 6 braking applications. Note 2 : When brake handle is not in the fully released position, amber “PRKG BRK ON” is displayed on EWD and is taken into account by the T/O CONFIG warning system. Mod: 5948 1.14.40 LANDING GEAR P5 BRAKES ANTI SKID 001 FEB 12 AA PARKING/EMERGENCY BRAKING ACCUMULATOR PRESSURE INDICATOR In addition to the PRKG BRK ON annunciation on EWD and the Parking / Emergency Braking Accumulator displayed on MFD ACW/HYD page, the aircraft is fitted with a Parking / Emergency Braking Accumulator pressure indicator located on the left maintenance panel. R This indicator is used to read Brake Accumulator Hydraulic Pressure when Batteries are OFF, R for ground towing operations or in case of the main indication loss. When the switch is activated, the indicator is energized for two minutes. When the hydraulic pressure of the accumalator is below 1700 PSI or above 3100 PSI, the indicator displays blinks. Brake Accumulator Hydraulic pressure is displayed in green. The displayed value has to be multiplied by 1000 (as described by the legend on the front face). Mod: 5948 1.14.40 LANDING GEAR P6 001 BRAKES ANTI SKID FEB 12 AA ANTI SKID PANEL (1) ANTI SKID pb. Controls activation/deactivation of the antiskid system. pb pressed in OFF R : Antiskid system is activated. : (pb released) Antiskid system is deactivated. OFF light illuminates white. (2) TEST pb Press the button initiates an automatic sequencial test to verify the primary antiskid protection capabilities of the system The test duration is approximately three seconds in flight and six seconds on ground. If initiated on ground when brake pedals are depressed, the test duration is sufficient to allow observation of the brake compression and release, thereby allowing system verification testing to be performed. “WHEELS A-- SKID” amber caution is displayed on EWD. CAUTION : Do not perform the test on the ground, engines running, without parking brake set. Note : The test is inhibited when wheel speed exceeds 17 kt ANTI SKID MFD INDICATING For anti skid test result and braking message on EWD see table page 11/12. For braking system availability and accumulator indication see table page 9/10 (topic : “BRAKES ANTI SKID”) Mod: 5948 1.14.40 LANDING GEAR P7 BRAKES ANTI SKID 001 APR 11 AA 40.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT Antiskid control for inboard wheels Antiskid control for outboard wheels Antiskid caution system Emer brake accu pressure ind. Brake temp system DC BUS SUPPLY (C/B) DC ESS BUS (on lateral panel INBOARD WHEELS) DC EMER BUS (on lateral panel OUTBOARD WHEELS) DC STBY BUS (on lateral panel CAUTION) DC STBY BUS (on lateral panel PRESS IND) DC STBY BUS (on lateral panel MONITORING SYS) SYSTEM MONITORING WHEELS A-- SKID This caution is generated in case of anti skid channel loss (power loss or loss of transducer or valve continuity). Visual and aural alerts are : - MC light flashing amber - “WHEELS A-- SKID” caution message on EWD - Aural alert is Single Chime (SC) - The lost channel will be displayed by an amber F in the brake message part of the EWD WHEELS BRK HOT This caution is generated when brake temperature is detected over 150°C (510 °F). Visual and aural alerts are : - MC light flashing amber - “WHEELS BRK HOT” caution message on EWD - Aural alert is Single Chime (SC) Mod: 5948 1.14.40 LANDING GEAR P8 BRAKES ANTI SKID 001 APR 11 AA 40.4 LATERAL MAINTENANCE PANEL BRK TEMP TEST On the RH maintenance panel, a test pb is used to test brake overheat detection system. When depressed, the FWS is activated. Mod: 5948 Mod: 5948 40.5 SCHEMATIC AA LANDING GEAR GENERAL LANDING GEAR P 9/10 APR 11 001 1.14.40 . Mod: 5948 AA LANDING GEAR GENERAL LANDING GEAR P 11/12 APR 11 001 1.14.40 . 1.15.00 NAVIGATION SYSTEM P1 001 CONTENTS AA 1.15.00 CONTENTS 1.15.10 10.1 10.2 10.3 VOR/ILS/MKR/DME SYSTEM DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 1.15.20 20.1 20.2 20.3 ADF SYSTEM DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC 1.15.30 30.1 30.2 30.3 RADIO ALTIMETER DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 1.15.40 40.1 40.2 40.3 TERRAIN AWARENESS AND WARNING SYSTEM (TAWS) DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 1.15.50 50.1 50.2 50.3 WEATHER RADAR DESCRIPTION CONTROLS ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING 1.15.60 60.1 60.2 60.3 GLOBAL POSITIONING SYSTEM (GPS) DESCRIPTION OPERATION ELECTRICAL SUPPLY/MFC LOGIC 1.15.65 65.1 FLIGHT MANAGEMENT SYSTEM (FMS) DESCRIPTION 1.15.70 70.1 70.2 70.3 70.4 70.5 NAVIGATION DISPLAY GENERAL HSI AND MINI ND ON PFD ND ON MFD NAVIGATION SELECTION IESI Mod: 5948 APR 11 . VOR/ILS/MKR/DME SYSTEM P 1/2 APR 11 001 1.15.10. Mod: 5948 NOTE : VHF-- NAV1 includes the VOR1, ILS1, MKR1 and ADF1 receivers (same LRU). VHF-- NAV2 includes the VOR2, ILS2, and MKR2 receivers (same LRU). ADF2 can be part of VHF-- NAV2 if installed. The aircraft is equipped with : - two VOR receivers - two ILS receivers - one MKR receiver - one or two DME interrogator/receiver 10.1 DESCRIPTION AA NAVIGATION SYSTEM . 1.15.10 NAVIGATION SYSTEM P3 VOR/ILS/MKR/DME SYSTEM 001 APR 11 AA VOR The aircraft is equipped with two VOR receivers operating over the range 108.00 and 117.95 MHz. The VOR information can be displayed on the HSI part of the PFD or on the Navigation Display (ND) of the MFD. Simultaneous display on PFD and MFD is possible. The VOR audio signals are transmitted to the Remote Control Audio Unit. VOR frequency selection can be performed through MCP and MCDU. Range display and source switching on HSI between VOR and ADF is controlled by the EFCP. VOR course selection is performed through FGCP. VOR pointer symbols and reminders are displayed on both HSI on the PFD and on the Navigation display on the MFD. VOR indications are displayed in white. VOR receiver 1 is used by the IESI. For general architecture refer to page 1 ILS The aircraft is equipped with two ILS receivers operating over the range 108.00 and 111.95 MHz. The ILS information is displayed on the PFD on the ADI for LOC and G/S deviation and on the HSI for LOC only. ILS frequency selection can be performed through MCP and MCDU. ILS course selection is performed through FGCP. The ILS audio signals are transmitted to the RCAU. ILS receiver 1 is used by the IESI. For general architecture refer to page 1 Mod: 5948 1.15.10 NAVIGATION SYSTEM P4 VOR/ILS/MKR/DME SYSTEM 001 APR 11 AA MARKER The MARKER system consists of the following components: - 2 VOR/ILS/MKR receivers - 1MARKER antenna - 1 MARKER antenna coupler Outer, Middle and Inner markers signals are received and processed for visual display and audio annunciation. The MARKER symbols (MARKER beacon annunciator) are displayed at the bottom right corner of the Attitude Display Indicator (ADI) of the PFD. DME The DME frequency are paired with VOR/ILS ones. The DME equipment has three channels, allowing tuning three different frequencies. The DME channels are tuned by the RMA as follow: - Channel 1 of DME is associated with frequency of VOR/ILS1 - Channel 2 of DME is associated with frequency of VOR/ILS2 - Channel 3 of DME is associated with frequency from FMS (auto tuning) The DME HOLD function allows using the DME signal from an other VOR/ILS source than the active one. A cyan “H” will appear beside the selected frequency to indicate the hold status. The distance reading is shown on Captain and First Officer Primary Flight Display (PFD) and Navigation Display (ND). DME frequency selection can be performed through MCP and MCDU. The DME audio signals are transmitted to the RCAU. For general architecture refer to page 1. Mod: 5948 1.15.10 NAVIGATION SYSTEM P5 VOR/ILS/MKR/DME SYSTEM 001 APR 11 AA 10.2 CONTROLS VCP (1) Active Frequency Indicates the tuned VOR/ILS frequency associated to DME (in cyan). (2) STBY Frequency Indicates the preset frequency (in cyan). (3) “< >” Enables to switch Active and Stby frequencies. (4) Tune Mode Indicates the tuning mode (auto or manual) (checked or unchecked). (5) DME HOLD Enables to hold the current frequency while using another one (in green). MCDU (1) Active Frequency (2) DME HOLD status (On/Off) (3) STBY Frequency (4) Marker sensitivity (5) Tune Mode (Auto or manual) The NAV MCDU page allows to tune VOR/ILS/DME frequencies, to set Tune Mode, DME Hold, and to set MKR sensibility (LO/HI position). Mod: 5948 1.15.10 NAVIGATION SYSTEM P6 VOR/ILS/MKR/DME SYSTEM AA FGCP (1) Course knob Selects course. (2) Rotary switch Selects Radio Navigation Data source EFCP (1) BRG P/B select bearing source (2) “+/-- ” P/B Increases/Decreases range of the Navigation Display page. (3) FORMAT rotary knob Changes the format of the ND Mod: 5948 001 APR 11 1.15.10 NAVIGATION SYSTEM P7 VOR/ILS/MKR/DME SYSTEM 001 APR 11 AA MKR indicating on PFD Three Symbols can be displayed : Outer (”O” on cyan background), Middle (”M” on yellow background) or Inner (black on white background). Mod: 5948 1.15.10 NAVIGATION SYSTEM P8 VOR/ILS/MKR/DME SYSTEM 001 APR 11 AA IESI (1) G/S deviation indicator (2) VOR course deviation (if VOR active) (3) LOC deviation indicator (if ILS active) (4) COURSE indication (5) TO-- FROM pointer (6) VOR1 or ILS1 source identification (7) VOR/ILS frequency VOR/ILS The IESI can display the used Navigation Source (VOR or ILS) and its frequency. According to Nav Source selected, the appropriate course deviation scale or localizer and glideslope deviation scale will be displayed. Dashes or FAIL flag is displayed in case of invalid data from selected navigation source. For further information refer to 1.10.36 IESI or to THALES user’s guide for the IESI Mod: 5948 1.15.10 NAVIGATION SYSTEM P9 001 VOR/ILS/MKR/DME SYSTEM APR 11 AA 10.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY NAV 1 DC STBY BUS (on overhead panel NAV 1) NAV 2 DC BUS 2 (on overhead panel NAV 2) DME 1 DC BUS 1 (on overhead panel DME 1) DME 2 (if installed) DC BUS 2 (on overhead panel DME 2) MFC LOGIC See chapter 1.01 SYSTEM MONITORING “SGL DME” (only if 2 DME installed) This caution is generated when one DME is detected failed. Visual and aural alerts are : - MC light flashing amber - “SGL DME” amber message on EWD - Aural alert is Single Chime (SC) “DME LOSS” This caution is generated when DME (or both if 2 installed) is detected failed. Visual and aural alerts are : - MC light flashing amber - “DME LOSS” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 1.15.10 NAVIGATION SYSTEM P 10 VOR/ILS/MKR/DME SYSTEM AA “RMS” This caution is generated when one RMS is detected failed. Visual and aural alerts are : - MC light flashing amber - “RMS” amber message on EWD - Aural alert is Single Chime (SC) “RMS 1+2” This caution is generated when both RMS are detected failed. Visual and aural alerts are : - MC light flashing amber - “RMS 1+2” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 001 APR 11 1.15.20 NAVIGATION SYSTEM P1 ADF SYSTEM 001 APR 11 AA 20.1 DESCRIPTION The aircraft is equipped with one ADF (a second one could be installed as an option). The receiver operates in the 190 to 1799 KHz range. ADF bearing pointer symbols and reminders are displayed on both HSI on the PFD and on the Navigation display on the MFD. ADF indications are displayed in green. The ADF audio signals are transmitted to the RCAU. Mod: 5948 1.15.20 NAVIGATION SYSTEM P2 ADF SYSTEM AA 20.2 CONTROLS VCP (1) Active Frequency Indicates the tuned ADF frequency (in cyan). (2) STBY Frequency Indicates the preset frequency (in cyan). (3) “< >” Enables to switch Active and Stby frequencies. (4) ADF label “ADF” label displayed in green when ADF mode is selected. (5) TONE label “TONE” label displayed in green when ADF tone is set. Mod: 5948 001 APR 11 1.15.20 NAVIGATION SYSTEM P3 001 ADF SYSTEM APR 11 AA MCDU The following ADF parameters can be displayed and set through the MCDU: - active frequency - standby frequency - Mode selection - Tone selection - Preset function that allows to store NDB frequency for subsenquent use. The ADF pages are accessed on the MCDU through the RMS key, then NAV lsk (line selection key). Mod: 5948 1.15.20 NAVIGATION SYSTEM P4 ADF SYSTEM 001 APR 11 AA 20.3 ELECTRICAL SUPPLY/MFC LOGIC ELECTRICAL SUPPLY EQUIPMENT MCP 1 DC EMER BUS (on overhead panel CAPT MCP) MCP 2 DC ESS BUS (on overhead panel F/O MCP) MFC LOGIC See chapter 1.01 Mod: 5948 DC BUS SUPPLY (C/B) 1.15.30 NAVIGATION SYSTEM P1 001 RADIO ALTIMETER APR 11 AA 30.1 DESCRIPTION The aircraft is equipped with one radio altimeter. And two in option (applicable if Mod 5967 is installed). The radio altimeter gives accurate height information when flying below 2500ft. The radio altimeter system comprises one transceiver and two antennas. The range of the display is from 0 to 2500 ft. Radio altitude information is displayed in the bottom of the ADI part of the PFD. Decision height selection is performed from the ICP (Index Control Panel). The Radio Altimeters provides information to the MFC, AFCS, TCAS and TAWS. Mod: 5948 1.15.30 NAVIGATION SYSTEM P2 RADIO ALTIMETER 001 APR 11 AA 30.2 CONTROLS Radio altitude selection is through the Index Control Panel. In order to set a Decision Height, Captain and First Officer have to select their respective ICP to DH then to set the required decision height value from 0 to 999 ft. RA DISPLAY Several altitude information are gathered on PFD : (1) Radio Altitude Indication on altitude scale Displayed when radio altitude is less than 550 ft (2) Current Radio Altitude (RA) Numeric value displayed from 0 to 2500 ft. (3) Selected Decision Height (DH) Selected by the Captain and First Officer through their respective ICP. (4) DH annunciator Indicates that the aircraft is descending through decision height. Mod: 5948 1.15.30 NAVIGATION SYSTEM P3 RADIO ALTIMETER AA 30.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT AC BUS SUPPLY (C/B) RA 1 115V AC BUS 1 (on overhead panel RA 1) RA 2 115V AC BUS 2 (on overhead panel RA 2) MFC LOGIC See chapter 1.01 SYSTEM MONITORING “RAD-- ALT LOSS” This caution is generated when the radio altimeter is detected failed. Visual and aural alerts are : - MC light flashing amber - “RAD-- ALT LOSS” amber message on EWD - Aural alert is Single Chime (SC) Mod: 5948 001 APR 11 . 1.15.40 NAVIGATION SYSTEM P1 TAWS 001 APR 11 AA 40.1 DESCRIPTION The Terrain and Traffic Collision Avoidance System (T2CAS) is designed to provide the flight crew with visual and aural warnings of possible inadvertent flight into terrain. During normal flight operations, the system remains essentially silent. It uses GPS, radio altitude, barometric altitude and other relevant data in combination with its internal database information to provide the pilot with a full time terrain display. The look ahead function compares aircraft’s position and projected flight profile with the terrain database, and if activated, also the obstacle database. TAWS alert modes are: Reactive warning modes: - Mode 1: Excessive descent rate - Mode 2: Excessive terrain closure rate - Mode 3: Loss of altitude after take-- off or go around - Mode 4: Unsafe terrain clearance not in landing mode - Mode 5: Excessive descent below glide slope - Mode 6: Excessive bank angle and altitude callouts Predictive warning modes: - Terrain Caution and Warning - Obstacle Caution and Warning Note: CPA when used in reference to TAWS refers to Collision Prediction and Alerting. TAWS is a situational awareness system. It is not intended to be used for primary navigation of the aircraft. Mod: 5948 1.15.40 NAVIGATION SYSTEM P2 TAWS 001 APR 11 AA ALERT MODES MODE 1 - EXCESSIVE DESCENT RATE This mode monitors the radio altitude and vertical speed and generates a reactive medium-- term caution and a reactive short-- term warning when the current flight path is descending at an excessive rate. Two alerts can be generated: “SINK RATE” Caution “PULL UP” Warning Mod: 5948 1.15.40 NAVIGATION SYSTEM P3 TAWS 001 APR 11 AA MODE 2 - EXCESSIVE TERRAIN CLOSURE RATE This mode monitors the radio altitude, computed airspeed, landing gear configuration, and landing flaps configuration and generates a reactive medium-- term caution and a reactive short-- term warning when the current flight path and the terrain are closing at an excessive rate. Two alerts can be generated: - “TERRAIN” caution - “PULL UP” Warning Mod: 5948 1.15.40 NAVIGATION SYSTEM P4 TAWS 001 APR 11 AA MODE 3 - LOSS OF ALTITUDE AFTER TAKE- OFF OR GO AROUND This mode monitors the radio altitude and aircraft altitude and generates a caution alert when there is loss of altitude after takeoff or a missed approach. One alert can be generated: - “DON’T SINK” Caution Mod: 5948 1.15.40 NAVIGATION SYSTEM P5 001 TAWS APR 11 AA MODE 4 - UNSAFE TERRAIN CLEARANCE NOT IN LANDING MODE This mode monitors the radio altitude, landing gear configuration, landing flaps configuration, and airspeed and generates a caution alert if there is insufficient terrain clearance when the aircraft is not in the proper landing configuration. Thus 3 alerts can be generated: - TOO LOW TERRAIN caution - TOO LOW GEAR caution - TOO LOW FLAPS caution Mod: 5948 1.15.40 NAVIGATION SYSTEM P6 TAWS AA 001 APR 11 MODE 5 - EXCESSIVE DESCENT BELOW GLIDESLOPE This mode monitors the radio altitude, glideslope deviation, localizer deviation, landing gear configuration, and glideslope inhibit/cancel. It generates a caution alert if there is excessive descent below the instrument glidepath when making a front course approach with the gear down. One alert can be generated : - “GLIDESLOPE” caution Mod: 5948 1.15.40 NAVIGATION SYSTEM P7 TAWS 001 APR 11 AA MODE 6 - EXCESSIVE BANK ANGLE AND ALTITUDE CALLOUTS This mode monitors the radio altitude and bank angle, and generates an aural annunciator (BANK ANGLE) when the aircraft bank angle exceeds a bank angle limit defined with respect to radio altitude. Mod: 5948 1.15.40 NAVIGATION SYSTEM P8 TAWS 001 APR 11 AA TERRAIN CLEARANCE FLOOR A terrain clearance floor envelope is stored in the database for each runway for which terrain data exist. The Terrain Clearance Floor (TCF) function warns of a premature descent below this floor, regardless of the aircraft’s configuration. If the aircraft descends below this floor, a TOO LOW TERRAIN aural warning sounds and the GPWS pushbutton light illuminates on the glareshield. RUNWAY FIELD CLEARANCE FLOOR The Runway Field Clearance Floor (RFCF) provides an additional envelope protection, for runways that are significantly higher than the surrounding terrain. It is contained in a circle within the 5.5 NM of the runway threshold and it is based on the geometric altitude and the runway elevation. Mod: 5948 1.15.40 NAVIGATION SYSTEM P9 TAWS 001 APR 11 AA TERRAIN AND OBSTACLE AWARNESS This function use aircraft geographic position provided by the aircraft GPS, aircraft altitude and a worldwide terrain database to predict potential conflicts between the aircraft flight path and the terrain, and to provide aural alert and graphic displays of the conflicting terrain. Terrain/ Obstacle Alerting Caution and Warning envelopes below and ahead of the aircraft path are computed as a function of airspeed and flight path angle. If the aircraft penetrates the Caution Envelope boundary, an aural message “TERRAIN AHEAD” or “OBSTACLE AHEAD” is generated with the glareshield pushbutton “GPWS” lights illuminating. Simultaneously, conflicting terrain areas are“ shown in solid yellow on the Terrain Display (MFD).“ If the aircraft penetrates the Warning Envelope boundary, an aural message “TERRAIN AHEAD, PULL UP” or “OBSTACLE AHEAD, PULL UP” is generated with the glareshield pushbutton lights illuminating red “PULL UP”. Simultaneously, conflicting terrain areas are show in solid red on the Terrain display (MFD). Terrain / Obstacle Display The terrain data can be displayed on the ND part of the MFD. When the terrain display is selected it replaces the Weather Radar display and can be available to the flight crew at any time. A discrete pop up signal is used to automatically display on the MFD the threatening terrain or obstacle with an auto range of 10 NM, whatever is the previous information displayed. Alert Level Aural warning Navigation Display Local warning Warning TERRAIN AHEAD, PULL UP - automatic 10 NM display p y - solid red area On each pilot’s glareshield, ppushbutt light ton li ht illuminates ill i t red “PULL UP” - automatic 10 NM ddisplay sp ay OBSTACLE AHEAD - solid yellow area On each pilot’s glareshield pushbutton es e d pus butto light illuminates amber “GPWS” OBSTACLE AHEAD, PULL UP Caution Mod: 5948 TERRAIN AHEAD 1.15.40 NAVIGATION SYSTEM P 10 TAWS 001 APR 11 AA The local terrain forward of the aircraft is depicted as variable density dot patterns in green, yellow or red. The density and color being a function of how close the terrain is relative to aircraft altitude.Terrain Alerts are depicted by painting the threatening terrain or obstacle as solid yellow or red. The Peaks display adds additional density patterns and level threshold to the standard mode display. At altitudes safely above all terrain for the display range chosen, the terrain is displayed independently of aircraft altitude. The Peaks display includes a solid green level to indicate the highest non threatening terrain. The red and yellow dot pattern and solid red and yellow colors are unchanged with regard to the standard display. The terrain identified as water is displayed as cyan dots. Two elevation numbers (in hundreds of feet above MSL)with the highest terrain on top and the lowest terrain under it are displayed with the corresponding colors to indicate the highest and lowest terrain currently being displayed. A single elevation number (high altitude) is displayed when the screen is fully black or blue as the result of flying over water or relatively flat terrain where there is no appreciable difference in terrain elevations. Peaks terrain background display Mod: 5948 1.15.40 NAVIGATION SYSTEM P 11 TAWS 001 APR 11 AA 40.2 CONTROLS PULL UP - GPWS P/B PULL UP GPWS Depressed illuminates red on black background for Warning triggered by GPWS Modes. The illumination is accompanied by the voice alert for the particular mode. illuminates amber on black background for Caution triggered by GPWS Modes. The illumination is accompanied by the voice alert for the particular mode Self Tests the system on ground. Inhibitis the aural and visual alert caution in flight. GPWS Selector The selector is guarded and wirelocked on NORM position. NORM GPWS operates normally. FLAP OVRD Mode 4 alert caused by flap extension at less than landing configuration is inhibited to avoid nuisance warnings in case of landing with reduced flap setting. OFF All GPWS modes are inhibited, GPWS is inoperative. Mod: 5948 1.15.40 NAVIGATION SYSTEM P 12 TAWS 001 APR 11 AA TERR Guarded pb Pressed FAULT OFF all Enhanced (TAD & TCF) modes are operative. illuminates amber when some or all Enhanced modes are lost. illiminated white when TERR pb is released to inhibit Enhanced modes. GPWS annunciator light FAULT OFF Mod: 5948 Illuminates amber when some or all GPWS basic modes are lost. Illuminates white when GPWS selector on OFF position. 1.15.40 NAVIGATION SYSTEM P 13 TAWS 001 APR 11 AA TAWS Soft Controls - VCP OVLY tab On MFDs, in normal display configuration, both captain and first officer Virtual Control Panel (VCP) OVLY tab enable Terrain background selection on respective Navigation Displays. Terrain Background Display (ND) (1) TAWS status indication (2) TAWS image When Terrain background is selected on OVLY tab of VCP : - a cyan “TERR” label is displayed on the lower right side of ND - Terrain background is displayed in different color and density and indicates the difference between local ground altitude and aircraft altitude. Mod: 5948 1.15.40 NAVIGATION SYSTEM P 14 001 TAWS APR 11 AA 40.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT PULL UP GPWS P/B GPWS light TERR pb T2CAS computer DC BUS SUPPLY (C/B) DC BUS 1 (on overhead panel TAWS ADVS) DC BUS 2 (on overhead pane T2CAS T-- R) MFC LOGIC See chapter 1.01 SYSTEM MONITORING GPWS This caution is generated when GPWS function is detected failed. Visual and aural alerts are : - MC light flashing amber - “GPWS” amber message on EWD - Illumination of GPWS annunciator FAULT light (amber) - Aural alert is Single Chime (SC) TERRAIN This caution is generated when terrain function is failed. Visual and aural alerts are : - MC light flashing amber - “TERRAIN” amber message on EWD - Illumination of TERR push button FAULT light (amber) - Aural alert is Single Chime (SC) Note : When Terrain background is selected on OVLY tab of VCP, TERRAIN function failure is indicated by ”TERR FAULT” amber label on ND (or HSI). Mod: 5948 1.15.50 NAVIGATION SYSTEM P1 WEATHER RADAR 001 APR 11 AA 50.1 DESCRIPTION The weather radar system detects atmospheric disturbances and provides the crew with display of precipitation levels for ranges up to 300NM in front of the aircraft. In addition it can display terrain mapping information. Weather Information can be displayed on the Captain and First Officer Navigation Displays (MFD pages) with RADAR background selected on Virtual Control Panel (VCP). Four colors are used, each corresponding to a different target return level. Mod: 5948 1.15.50 NAVIGATION SYSTEM P2 WEATHER RADAR 001 APR 11 AA 50.2 CONTROLS WEATHER RADAR CONTROL PANEL (1) Mode selector Enables the selection of the operating mode. OFF The radar system is turned off (terrain information are not displayed on the MFD and “TERR FAULT” amber label is illuminated). SBY (“WX STBY” displayed white on the MFD) Places the radar in a stand by with the antenna scan stopped and the transmitter inhibited. WX (“WX TX”displayed green on the MFD) Selects the weather detection mode, displaying five different levels of returns. Level 0 : Black No detectable cloud Level 1 : Green Moderate storm Level 2 : Yellow Less severe storm Level 3 : Red Strong storm Level 4 : Magenta Intense storm On the ground, the system is automatically forced in STBY position for safety. If needed, it is possible to restore the active WX mode by pressing the STAB button four times in three seconds. GMAP (“WX GMAP” displayed cyan on the MFD) Selects the ground mapping mode using four different levels of returns. Level 0 : Black No return Level 1 : Cyan Least reflective return Level 2 : Yellow Moderate return Level 3 : Magenta Strong return TST (“WX TEST” displayed on the MFD) displays a test pattern to verify the system. Mod: 5948 1.15.50 NAVIGATION SYSTEM P3 WEATHER RADAR 001 APR 11 AA (2) TILT control Is used to adjust the antenna pitch from 15o down to 15o up. (3) GAIN rotary control and push/pull switch When the switch is pushed, the system enters the preset, calibrated gain mode, in this mode, the rotary control is deactivated. When the switch is pulled, the system enters the variable gain mode, adjustable by the rotary control (G-- VAR is displayed green on the MFD). RCT push button Activates or deactivates the REACT mode which compensates for attenuation of the radar signal as it passes through rain fall. (WX RCT is displayed cyan on the MFD). The cyan field indicates areas where further compensation is not possible. Any target detected in these areas will be displayed in magenta and should be considered as dangerous. TGT push button Activates and deactivates the radar target alert mode. When activated, TGT is displayed green on the MFD and the system monitors beyond the selected range and 7.5o on each side of the aircraft heading. If a level 3 characteristic return is detected in the monitored area, the TGT legend on the MFD changes from green to amber. TGT alert can only be selected in the WX and FPL modes. STAB push button Turns the pitch and roll stability ON and OFF. SECT push button Is used to select either the normal 12 looks/mn 120o scan or the faster update 24 looks/mn 60o sector scan. Mod: 5948 1.15.50 NAVIGATION SYSTEM P4 WEATHER RADAR 001 APR 11 AA WX Background Selection Captain ND is available by pressing ND on EFCP Left and First Officer ND via EFCP Right. Thus ND format appears on MFD pages. On ND page Weather Radar background can be selected using Virtual Control Panel (lower part of MFD). Weather Radar background is updated in accordance with ND Format (ARC ROSE) and ND Range selected on EFCP left for ND Captain and EFPC right for ND First Officer. (1) Radar background (on ND) box selection (2) Terrain background (on ND) box selection The Virtual Control Panel is controlled by MCP : ND selection and display can be set by EFCP : (1) Range selection Mod: 5948 (2) : Format selection (3) : ND selection 1.15.50 NAVIGATION SYSTEM P5 001 WEATHER RADAR APR 11 AA MFD DISPLAY The Weather Radar System has several mode and warning annunciations are displayed on lower right side of ND. (1) Weather radar image Four lines are dedicated to weather function mode and warning annunciators. (2) Weather Radar Range Error (line 1) An amber “RNG” message indicates a mismatch between DU and WXR ranges. (3) Weather Radar Modes (line 2) WX Mode Annunciation Alert Color Mode Description WX WAIT WHITE Power-- up approximately 90 seconds WX STBY WHITE Normal standby (STBY position of rotary switch) or forced standby (ON and aircraft on ground) WX TEST YELLOW Test mode and no faults WX TX GREEN Normal WX on and selected for display WX DGD AMBER Invalid WX control bus, invalid WX ranges WX RCT CYAN Normal WX with react WX GMAP CYAN Ground map mode WX FAIL AMBER Test mode and faults Mod: 5948 1.15.50 NAVIGATION SYSTEM P6 WEATHER RADAR 001 APR 11 AA (4) Gain Control Status Message / Target (line 3) WX Mode Annunciation Alert Color Mode Description G-- VAR GREEN Variable Gain WX Mode Annunciation Alert Color Mode Description TGT GREEN Target alert enabled TGT AMBER Target alert enabled and level 3 WX return detected in forward 15 degrees of antenna scan (5) Tilt Angle (line 4) When Tilt mode is not OFF or STBY, a green “T” followed by cyan tilt angle value and white “°” unit are displayed. Mod: 5948 1.15.50 NAVIGATION SYSTEM P7 001 WEATHER RADAR APR 11 AA 50.3 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) Weather radar (Receiver Transmitter Antenna) DC BUS 1 - (on overhead panel WXR) MFC LOGIC See chapter 1.01 SYSTEM MONITORING In case of WEATHER RADAR failure, TERRAIN map can still be displayed (since WX RADAR and TERRAIN display are independant). Mod: 5948 . 1.15.60 NAVIGATION SYSTEM GLOBAL POSITIONING SYSTEM P1 GPS 001 APR 11 AA 60.1 DESCRIPTION The GPS is a navigation system based on satellite transmission, and provides high precision data to other systems, in any place of earth and in any weather conditions: - position - ground speed - date and time - quality and integrity criteria The GPS also performs a failure recording/reporting to the Centralized Maintenance Application (CMA). The GPS is composed of a GPS receiver and a GPS antenna. One or Two GPS receivers and antennas can be installed on the aircraft. The GPS is capable to be initialized by FMS data (latitude/longitude/altitude/UTC/Date) for quick acquisition. The GPS is connected with T2CAS, Transponders, PFDs, MFDs, Clocks (only for GPS1) and FDAU. Mod: 5948 1.15.60 NAVIGATION SYSTEM GLOBAL POSITIONING SYSTEM GPS P2 001 APR 11 AA 60.2 OPERATION The primary function of the GPS is to receive the satellite RF signal from the antenna, find the signal code phase and carrier phase and by using this signals, compute antenna position. Output data includes three dimensional aircraft position and velocities, quality and integrity criteria. In case of dual GPS installation, each GPS receiver output GPS data to other systems which have to select the GPS source used. Position Position is displayed on GPS NAV page of the MCDU. In case of double FMS failure, the GPS position (latitude, longitude) is displayed on the upper right corner of the Navigation Display. Ground Speed Ground speed is displayed on GPS NAV page of the MCDU. In case of double FMS failure the GPS Ground speed is displayed on the upper left corner of the Navigation Display. Date/Time The GPS1 provide the time information to other systems. GPS date and time can be displayed on clocks, and on MCDU. N.B: ONLY GPS1 provide time information to clocks. Quality criteria All quality criteria can be displayed on MCDU GPS pages. RAIM/PRAIM GPS RAIM and PRAIM data can be displayed on MCDU GPS pages. NB : RAIM is a function implemented into the GPS receiver and provides integrity monitoring of GPS signals for aviation application. Predictive RAIM (PRAIM) provides the pilot with RAIM availability accordance to satellite constellation predicted availability. Failure Reporting GPS reports failures to the CMA. Mod: 5948 1.15.60 NAVIGATION SYSTEM GLOBAL POSITIONING SYSTEM P3 GPS APR 11 AA 60.3 ELECTRICAL SUPPLY/MFC LOGIC ELECTRICAL SUPPLY EQUIPMENT DC BUS SUPPLY (C/B) GPS 1 DC STDBY BUS (on overhead panel GPS 1) GPS 2 (if installed) DC BUS 2 (on overhead panel GPS 2) MFC LOGIC See chapter 1.01 Mod: 5948 001 . 1.15.65 NAVIGATION SYSTEM FLIGHT MANAGEMENT SYSTEM P1 FMS 001 APR 11 AA 65.1 DESCRIPTION The aircraft is equipped with 2 Flight Management Systems, real core of the aircraft management. The FMS allow managing the aircraft during all the phases of the flight, allowing for flight plan management, flight prediction computations, wind management, and aircraft various sensors management. FMS 1(software and database) is located inside display unit 2 (DU2). FMS 2 (software and database) is located inside display unit 4 (DU4). The Flight Management System is controlled by: - 2 MCDU (Multipurpose Control and Display Unit) - 2 VCP (Virtual Control Panel) and their associated MCP (Multi Control Panel) - FGCP (Flight Guidance Control Panel) The FMS software, FMS configuration file and the Performance database are permanently stored into the respective DU. The FMS needs to have the compact flash card inserted in the DU in order to have the following functions available (some of the data are not mandatory for FMS operations): - « Standard navigation databases (2 AIRAC cycles) - « Company navigation database (not mandatory) - « Pilot navigation database (not mandatory) - « Magnetic Variation database - « Secondary FPLN (not mandatory) In normal operation, FMS 1 & 2 are synchronized and operate in dual operation even if both are achieving their own computation and exchange data through the cross talk link. For full system description and for operating instructions refer to THALES FMS PILOT’S GUIDE. Mod: 5948 . 1.15.70 NAVIGATION SYSTEM P1 NAVIGATION DISPLAY 001 APR 11 AA 70.1 GENERAL The navigation information are displayed in different format, on PFD, MFD and IESI. PFD On the flight guidance coupled side, the ND is displayed by default on the MFD. In standard configuration an HSI is displayed on the PFD. If the pilot changes the ND to an other page (system for example), a mini ND page is displayed on the PFD, in place of the HSI. In this case the format of the mini ND can be changed by the rotary knob (only ROSE and ARC). Mod: 5948 1.15.70 NAVIGATION SYSTEM P2 NAVIGATION DISPLAY 001 APR 11 AA MFD (ND PAGE) Three different ND format, can be displayed on the MFD, by pressing on the ND push button (see description below), and then by selecting the format on the NAV control. - BRG 1(2) pb Select the station (VOR or ADF) associated to the bearing pointers - Range pb Select the different operating ranges - Format knob Change the ND format (ARC, ROSE and PLAN) Mod: 5948 1.15.70 NAVIGATION SYSTEM P3 NAVIGATION DISPLAY AA IESI Mod: 5948 001 APR 11 1.15.70 NAVIGATION SYSTEM P4 NAVIGATION DISPLAY AA 70.2 HSI and mini ND on PFD HSI Mod: 5948 001 APR 11 1.15.70 NAVIGATION SYSTEM P5 NAVIGATION DISPLAY AA MINI ND The same information as on the HSI could be find on these formats. Mod: 5948 001 APR 11 1.15.70 NAVIGATION SYSTEMS P6 NAVIGATION DISPLAY 001 APR 11 AA (1) Navigation source annunciation Indicates which navigation source is selected on the own-- side FGCP. It is displayed in - cyan for VOR or ILS source selected - magenta for FMS source selected When yellow, the annunciation indicates a source reversion. (2) Radio-- navigation frequency / FMS ident Identifies the selected source either by its frequency (VOR and ILS) or by its ident (FMS). Five cyan digits from 108.00 to 117.95 MHz are displayed in case of VOR-- ILS nav source. Five amber dashes are displayed in case of invalidity. The label of valid FMS waypoint “TO” ident with maximum seven magenta characters is displayed in case of FMS nav source. (3) Selected course/desired track numeric value Provides the angle value of the associated pointer. Represented by : - White “CRS” label followed by 3 cyan digits from 001 to 360 degrees, followed by a white “°” label if the navigation selected source is ILS or VOR (in normal condition). - White “CRS” label followed by 3 amber dashes, followed by a white “°” label in case of invalidity. - White ”DTK” label followed by 3 magenta digits from 001 to 360 degrees, followed by a white “°” label if the navigation selected source is FMS. - White “DTK” label followed by 3 amber dashes, followed by a white “°” label in case of invalidity. (4) DME Channel HOLD mode Cyan “H” label, which indicates if DME channel is in HOLD Mode. (5) DME/FMS distance Indicates the distance to go to the selected navigation source (station or “TO” waypoint). Represented by : - three green digits, ranging from 0.0 to 99.9 in decimal increment and after in whole numbers followed by a white “NM” label in normal operation. - Three amber dashes followed by a white “NM” label are displayed in case of invalidity. (6) Selected heading numeric value Indicates the angle value pointed by the selected heading bug. It is represented by a white “HDG“ label followed by 3 cyan digits from 000 to 359 degrees, and by a white “°” label (in normal condition). In case of invalidity a white ”HDG” label followed by 3 amber dashes and by a white “°” label is diplayed. Mod: 5948 1.15.70 NAVIGATION SYSTEMS P7 NAVIGATION DISPLAY 001 APR 11 AA (7) TRUE heading indication (available only if IRS installed) Cyan “TRUE” label to indicate the true heading. (8) Track angle bug Indicates on the heading dial the current track. It is represented by a magenta unfilled diamond located along the heading dial and pointing towards the aircraft mock-- up. (9) Selected heading bug Indicates on the heading dial the current selected heading. It is represented by a cyan filled “M-- shape” bug along the heading dial. (10) (11) Bearing pointer The bearing pointer shows the bearing of the navigation source selected on MCP. Pointer 1: The needle head is depicted as a circle, the color is white if source is VOR and green if source is ADF. Pointer 2: The needle head is depicted as an open diamond, the color is white if source is VOR and green if source is ADF. (12) FMS Messages - “TERM” and “APPR” inform the pilots about sensitivity of deviation scales (respectively 1 NM and 0.3 NM). - “MSG” informs the pilot that a message is displayed on the MCDU. - “OFST“ means that the A/C flies along the flight plan, but with a parallel offset. (13) Heading mismatch flag Amber “CHECK HDG” label appears above the aircraft symbol in when a discrepancy is detected for heading data between the AHRS sources for captain and F/O side. (14) Course desired track deviation scale In case of excessive LOC deviation, the four dots flash amber. In case of invalidity, two red lines cross the dots. (15) TO/FROM pointer The TO/FROM pointer is a cyan triangle if VOR is selected as navigation source and magenta in case of FMS selected as navigation source. (16) Selected course/desired track pointer Pointer color is: - cyan if VOR/ILS selected as nav source - magenta if FMS selected as nav source - amber in case of excessive LOC deviation Mod: 5948 1.15.70 NAVIGATION SYSTEMS P8 NAVIGATION DISPLAY 001 APR 11 AA (17) Course/desired track deviation bar Bar color is: - cyan if VOR/ILS selected as nav source - magenta if FMS selected as nav source - amber in case of excessive LOC deviation (18) Rotating heading dial It is the reference for all angle information. In case of loss of data a white circle with “HDG FAIL” red label will be displayed. (19) Aircraft symbol and heading reference The aircraft symbol is a yellow mock-- up plane. The heading reference is a yellow unfilled triangle pointing down at the top of the compass rose. Mod: 5948 1.15.70 NAVIGATION SYSTEM P9 NAVIGATION DISPLAY AA 70.3 ND on MFD Mod: 5948 001 APR 11 1.15.70 NAVIGATION SYSTEM P 10 NAVIGATION DISPLAY AA Mod: 5948 001 APR 11 1.15.70 NAVIGATION SYSTEM P 11 NAVIGATION DISPLAY 001 APR 11 AA (1) Latitude / Longitude indication Provides the current position of the aircraft through numeric latitude and longitudes values. In case of invalidity all numbers and letters are remplaced by amber dashes. (2) Selected heading bug Cyan filled M-- shape bug (along the heading ROSE or ARC scale) which indicates the current selected heading. (3) (5) (6) (9) Bearing pointer indications Indicates the bearing of the navigation source selected on the FGCP. Pointer 1: The needle head is depicted by a circle, the color is white if source is VOR and green if source is ADF. The selected frequency is displayed in the bottom left square. (5) Pointer 2: The needle head is depicted an open diamond, the color is white if source is VOR and green if source is ADF. The selected frequency is displayed in the bottom right square. (6) (4) Heading mismatch flag (not depicted) Amber ”CHECK HDG” warns of heading discrepancy between Captain and F/O side. (7) selected heading readout (8) Aircraft reference - ARC mode location : at the geometric center of the arc heading dial. - ROSE mode location : at the geometric center of the full compass heading dial. - PLAN mode location : center of aircraft according to the lat/long position sent by the FMS, only if the scrolling and range of the flight plan selected corresponds to a representation where the aircraft is present.. Mod: 5948 1.15.70 NAVIGATION SYSTEM P 12 NAVIGATION DISPLAY 001 APR 11 AA (10)(14) Range The range can be set manually through the EFCP or be managed by the display system. Manual range in ARC mode : The range indication is composed of : - an outer white arc displaying 90 degrees of heading centred on aircraft reference - 3 cyan numeric digits, located on the outer arc left extremity - an inner white dashed arc displaying 150 degrees of heading, centred on aircraft reference and whose radius is half the radius of first arc. - 3 cyan numeric digits, located on the inner arc left extremity AUTO range in ARC mode : The range indication is composed of : - an outer white arc displaying 90 degrees of heading centred on aircraft reference - 3 white numeric digits, located on the outer arc left extremity with below a “AUTO” label - an inner white dashed arc displaying 150 degrees of heading, centred on aircraft reference and whose radius shall be half the radius of first arc. - 3 white numeric digits, located on the inner arc left extremity Manual range in ROSE mode : The range indication shall be composed of : - an outer white circle centred on aircraft reference - 3 cyan numeric digits, located on bottom left along outer circle - an inner white dashed circle, centred on aircraft reference and whose radius shall be half the radius of outer circle - 3 cyan numeric digits, located on bottom left along inner circle AUTO range in ROSE mode : The range indication is composed of : - an outer white circle centred on aircraft reference - 3 white numeric digits, located on bottom left along outer circle with above a “AUTO” label - an inner white dashed circle, centred on aircraft reference and whose radius shall be half the radius of outer circle. - 3 white numeric digits, located on bottom left along inner circle Range in PLAN mode : The range indication is composed of : - an outer white circle - 3 cyan numeric digits, located on bottom left along outer circle - an inner white circle, centred like outer circle and whose radius shall be half the radius of outer circle. - 3 cyan numeric digits, located on bottom left along inner circle Mod: 5948 1.15.70 NAVIGATION SYSTEM P 13 NAVIGATION DISPLAY 001 APR 11 AA (11) Heading dials (12) Track angle bug Green unfilled diamond located along the ROSE or ARC heading dial and pointing towards the aircraft mock-- up wich indicates the current track. (13) Heading readout (15) Static markers Provide a static reference on ROSE and PLAN compasses. (16) Ground speed value (17) True air speed value (18) Wind value (19) Wind direction indication Mod: 5948 1.15.70 NAVIGATION SYSTEM P 14 NAVIGATION DISPLAY AA SYMBOLS Mod: 5948 001 APR 11 1.15.70 NAVIGATION SYSTEM P 15 NAVIGATION DISPLAY AA 70.4 Navigation Selection Selection with MCP (1) - NAV P/B Allows the selection of the NAV pages on the VCP 3 pages: - VOR - ADF - ND OVLY (ND Overlay) (2) - Multi directional pad Allows choosing the selection area (3) - Numeric Key Board Allows setting manually the frequency (4) - Enter P/B Allows validating the selection area Mod: 5948 001 APR 11 1.15.70 NAVIGATION SYSTEM P 16 NAVIGATION DISPLAY AA ND OVLY Selection of the required overlay information on the ND: - Traffic - Weather radar - Terrain - Navaid - Airport Mod: 5948 001 APR 11 1.15.70 NAVIGATION SYSTEM P 17 NAVIGATION DISPLAY 001 APR 11 AA 70.5 IESI ILS & VOR FUNCTION (1) - Glideslope & Localizer scales and indexes The deviation scales appear when the ILS MODE is selected. The indexes appear when the glideslope and localizer signals are valid and deviation scales displayed. ILS TUNING : When MENU button is pushed and VHF NAV1 is tuned on ILS : The deviation scale appears when the VOR MODE is selected. In the bottom left corner TO Y and FROM B are indicated in cyan followed by the selected course. Mod: 5948 1.15.70 NAVIGATION SYSTEM P 18 NAVIGATION DISPLAY AA VOR TUNING : When MENU button is pushed and VHF NAV1 is tuned on VOR: Mod: 5948 001 APR 11 1.16.00 POWER PLANT P1 CONTENTS 001 APR 11 AA 1.16.00 CONTENTS 1.16.10 GENERAL 1.16.20 SYSTEMS DESCRIPTION 20.1 20.2 20.3 20.4 20.5 20.6 ENGINE FUEL SYSTEM LUBRICATION SYSTEM IGNITION SYSTEM PROPELLER SCHEMATICS 1.16.30 SYSTEMS OPERATING 30.1 30.2 30.3 1.16.40 40.1 40.2 40.3 40.4 40.5 1.16.45 45.1 45.2 45.3 GENERAL ENGINE GOVERNING PROPELLER SPEED GOVERNING CONTROLS ATPCS POWER LEVERS (PL) IDLE GATE CONDITIONS LEVERS (CL) INDICATORS & CONTROL PANELS BOOST FUNCTION DESCRIPTION OPERATION SCHEMATIC 1.16.50 LATERAL MAINTENANCE PANEL 1.16.60 ELECTRICAL SUPPLY/MFC LOGIC/SYSTEM MONITORING Mod: 5948 . 1.16.10 POWER PLANT P1 GENERAL 001 APR 11 AA The engine is a Pratt & Whitney of Canada PW127 M certified for a 2750 SHP max take-- off rating. However, in normal operation, take-- off rating will be 2475 SHP with an automatic power increase to 2750 SHP (reserve take-- off rating RTO) in case of other engine failure. Power setting is characterized by constant power lever and condition lever positions. The power adapted to the flight phase is selected by the pilot through a power management selector. The engine comprises two spool gas generators driving a six blade propeller via a free turbine/concentric shaft/reduction gear box assembly. Propeller regulation is electronically controlled. The propeller is an Hamilton Standard 568 F - Diameter Rotation 100 % Np Weight: : 3.93 m (12.9 ft) : clockwise (looking forward) : 1200 RPM : 180 kg The engine accessories are mounted on two accessory gear boxes, one driven by the HP spool, and one by the propeller reduction gear box. Mod: 5948 . 1.16.20 POWER PLANT P1 SYSTEMS DESCRIPTION 001 APR 11 AA 20.1 ENGINE MAIN COMPONENTS (See CROSS-- SECTION) 1 2 3 4 5 6 7 8 Low Press Compressor The low press compressor is a centrifugal type. High Press Compressor The high press compressor is a centrigugal type. Diffuser Pipes The diffuser pipes from the first stage lead into constant diameter cross over ducts which blend together to give a full ring with uniform flow at entry to the second stage. Combustion Chamber The combustion chamber is of the fully annular reverse flow perforated sheet metal type. Fourteen piloted air blast fuel nozzles provide quick, clean light offs. Hot inner parts are ceramic-- covered. High Press Axial Turbine The high pressure axial turbine drives the high press compressor. It incorporates a cooled vane ring and cooled blades permitting an increase in turbine inlet temperature, higher specific work and consequently a lower flow and a lighter engine. Low Press Axial Turbine The low press axial turbine drives the low press compressor. Free Turbine The two axial free turbine stages drive the reduction gear box. Accessory Gear Box Turbo machine accessories are mounted on the accessory gear box which is driven by the HP spool. The accessory gear box is located at the top of the engine and contains drives for : - The DC starter/generator, - The HP fuel pump, - The oil pumps. Mod: 5948 1.16.20 POWER PLANT P2 SYSTEMS DESCRIPTION 001 APR 11 AA 9 Propeller Reduction Gear Box The power turbine shaft is connected to the propeller reduction gear box by a coupling driveshaft having flexible diagram connections at each end. The gear box is mounted offset of the centerline of the turbo machine. The speed reduction is obtained in two stages. On the reduction gear box are installed. - The ACW generator - The Propeller Valve Module (PVM) controlled by propeller Electronic Control (PEC) - The HP pump and overspeed governor - The auxiliary feather pump - The propeller brake (on RH engine only) - The fuel cooled oil cooler (FCOC) Note : Auxiliary feather pump is driven electrically. On ground, its activation by the CL is inhibited. The other components are actuated through the reduction gear box. AIR INLET As presented on figure, the engine air intake (1) is offset and is a shallow “S” bend designed to provide uniform inlet flow to the compressor. The curvature (2) is intended to provide inertial separation and protection in the event of foreign object ingestion. It is also used to divide airflow in a primary flow directed to the engine, and a secondary flow directed to the oil cooler (3). Control of the secondary airflow is achieved by automatic oil cooler flaps positioning (4). Mod: 5948 1.16.20 POWER PLANT P3 SYSTEMS DESCRIPTION 001 FEB 12 AA 20.2 FUEL SYSTEM The fuel supplied from the A/C fuel tank flows through : - A fuel heater which includes : - a filter 1 with a by-- pass capability. - a fuel heater element 2 . The source of heat is engine oil, and the fuel temperature is thermostatically controlled. A fuel heater outlet temperature indication is provided. - A HP pump 3 with a filter. A clogging indicator is provided on pilot’s panel. - The Hydro Mechanical Unit (HMU) which has two functions : • to meter the fuel flow delivery to the engine by a metering valve assembly 4 , the excess being returned to HP pump inlet, • to provide the HP motive flow required by the fuel tank jet pump through an engine valve 5 . - A fuel flowmeter 6 . - A Fuel Cooled Oil Cooler (FCOC) 7 , that provides cooling of the lubricating system by using fuel system as cooling source. - A flow divider 8 to the fuel nozzles. R Mod: 5948 1.16.20 POWER PLANT P4 SYSTEMS DESCRIPTION 001 APR 11 AA 20.3 LUBRICATION SYSTEM (See schematic P9/10) Synthetic oil specification MIL-- L-- 23699. A single oil system supplies the turbo machinery, the reduction gear box and the propeller pitch change system. - Oil Tank Oil is contained in a 14.4 L tank 1 . A filter cap is provided on the tank. Quantity indication is checked by sight glass (or by a dipstick) on the side of the tank. - Pressure system A gear pump 2 driven by the accessory gear box supplies oil through an air cooler 3 mounted in the nacelle and a filter 4 both fitted with by-- passes in case of clogging. RGB oil is also cooled in a fuel heater, 5 as well as the FCOC 6 . An oil temperature sensor is provided. Oil pressure is controlled by a regulating valve 7 . A low temperature. valve 8 is provided to eliminate damaging pressures surges on cold starts. A pressure transducer 9 and a low pressure switch 10 are installed. - Scavenge system Scavenging is blown down or gravity drained except for N° 6 and 7 bearing cavity and the reduction gear box, on which gear pumps are used. 20.4 IGNITION SYSTEM Each engine is equipped with a high energy ignition system. It consists of two engine mounted ignition exciters (A and B) powered by the DC ESS BUS and two spark igniters, one for each ignition exciter. Ignition cycle includes two phases. During 25s, the intensity is 5 to 6 sparks/s and then, the intensity becomes 1 spark/s. The engine ignition system provides ignition for : - On ground starting using exciter A, exciter B, or exciters A+B (according to ENG START rotary selector position). Note : Using exciter A or exciter B may allow to detect an hidden failure. - In flight starting using exciters A+B regardless of start selection. In addition, for each engine, in case of NH drop below 60 % exciters A+B are automatically activated. This action is inhibited if : - NH drops below 30 %, or - EEC is deselected, or - CL is set on feather or fuel SO position, - On the failed engine in case of ATPCS sequence. Note : When EEC is deselected, excites A + B can manually be activated, using the MAN IGN push-- button. Mod: 5948 1.16.20 POWER PLANT P5 SYSTEMS DESCRIPTION 001 APR 11 AA 20.5 PROPELLER (See schematic P11/12) The propeller is driven by a free power turbine by means of a reduction gear box. Pitch (β) change is hydromechanically controlled by a Propeller Valve Module (PVM). The PVM is controlled by a Propeller Electronic Control (PEC) installed in each engine nacelle which provides the synchrophasing between the two propellers. Interface between flight deck and PEC is ensured by a Propeller Interface Unit (PIU) installed in the electronic rack. The propeller control system uses the condition lever, the PWR MGT rotary selector and the power lever to activate the pitch change mechanism through the governors and associated equipments. The system is protected against : - Low pitch angle in flight, - Overspeed, - Hydraulic pressure loss. The RH Propeller Reduction Gear Box is provided with a brake to be used on the ground for Hotel mode operation. PVM The PVM is installed on the reduction gear box and allows : - The basic speed set - Beta scheduling - Reversing - Synchrophasing - Feathering - Low pitch protection - 14° (Reverse) < βref < 78.5° (Feather) Additionally it is used, with the overspeed governor, to contain propeller overspeed. The PVM comprises : - An Electro Hydraulic Valve (EHV) which meters the pitch change oil to the pitch change actuator and allows a normal feathering of the propeller. - A protection valve which is a part of overspeed, low pitch and back-- up feathering functions. - A feather solenoid (EHV back-- up). - A Rotary Variable Differential Transducer (RVDT) which adjust and confirm PLA position. Mod: 5948 1.16.20 POWER PLANT P6 SYSTEMS DESCRIPTION 001 APR 11 AA PEC The PEC is a dual channel electronic box which provides closed loop control over the propeller pitch change system. The PEC detects, isolates and accomodates systems faults. In the event of a failure of the primary channel, control of the propeller system will automatically be transfered to the back-- up channel. Propeller speed is calculated by the PEC through EEC (altitude and airspeed data) and Np sensors. PIU The PIU (one per PEC) is an electronic box located in the electronic rack that realizes the interface between the PEC and the cockpit for propeller speed selection, and PEC fault signalisation logics. PROPELLER BRAKE (IF INSTALLED) The propeller brake is fitted on a countershaft on the RH engine reduction gearbox in order to stop the propeller (and the power turbine). When the engine is running in Hotel mode : - The HP spool drives the DC generator. - Bleed pressure is available downstream the HP compressor and supplies both packs. ENGAGEMENT LOGIC READY light must be illuminated, prior to any propeller brake activation. Loss of one of the above mentionned required conditions for engagement, will not imply propeller brake disengagement. However, when gust lock is released and propeller brake is still engaged, PROP BRK red warning is generated: - ”PROP BRK” FWS alert (EWD), - flashing ”MASTER WARNING” lights - ”CRC” aural warning Note : After a propeller braking or releasing sequence, READY light may remain illuminated for about 15 s. Mod: 5948 20.6 SCHEMATICS Mod: 5948 AA SYSTEMS DESCRIPTION POWER PLANT P 7/8 APR 11 001 1.16.20 EXTERNAL VIEW (LEFT) EXTERNAL VIEW (RIGHT) CROSS SECTION . Mod: 5948 AA SYSTEMS DESCRIPTION POWER PLANT P 9/10 APR 11 001 1.16.20 . Mod: 5948 AA SYSTEMS DESCRIPTION POWER PLANT P 11/12 APR 11 001 1.1620 . 1.16.30 POWER PLANT P1 SYSTEMS OPERATING 001 FEB 12 30.1 GENERAL The power control parameter is the torque : R The maximum torque for each flight condition, at the selected rating, is computed by the EEC and displayed on the TQ indicator on EWD (Automatic BUG). An Engine Electronic Control (EEC) provides control of fuel flow in the HydroMechanical Unit (HMU), through a stepper motor in such a way as to control the torque in accordance with outside conditions and positions of : - The power lever (PLA). - The power management selector (PWR MGT). - The bleed valves. The HMU delivers a fuel flow which generates the NH compressor rotation speed. Mod: 5948 1.16.30 POWER PLANT P2 SYSTEMS OPERATING 001 APR 11 AA 30.2 ENGINE GOVERNING MAIN UNITS (HMU- EEC- PVM- PWR MGT) HYDROMECHANICAL UNIT (HMU) - Performs fuel metering in steady state operation and protects the system in case of transients. - Commands the NH in accordance with 2 laws (NH = f (PLA)) : . 1 st law (called top) used when EEC is ON to protect NH overspeeds. . 2 nd law (called base) used when EEC is OFF. - Includes a stepper motor which adjusts the flow controlled by the hydromechanical channel, in accordance with commands transmitted by the EEC. - Ensures engine shutdown (HP fuel S/O). - Delivers a motive flow to the fuel tank jet pump. ENGINE ELECTRONIC CONTROL (EEC) - Regulates a given power, by controlling the stepper motor, to obtain a predicted torque as a function of : ¯ the power lever position ¯ the PWR MGT selector position ¯ flight conditions ¯ the position status of the bleed air valves Note : Operating line with EEC ON may be placed above or below the HMU BASE LAW depending on weather conditions Mod: 5948 1.16.30 POWER PLANT P3 SYSTEMS OPERATING 001 APR 11 AA - Ensures minimum propeller speed control, on ground and at low power (see propeller governing). - Delivers, in case of engine failure at take-- off, automatic uptrimmed take-- off power to the valid engine (ATPCS) by responding to the signal generated by the Auto-- Feather Unit (AFU) of the failed engine. - Controls the modulated opening of the Handling Bleed Valve (HBV), so as to ensure correct LP compressor operation. PROPELLER VALVE MODULE (PVM) - At high power, controls the propeller maximum speed Np, according to the PWR MGT selection. - Controls propeller pitch at low power and when using reverse. - Ensures low pitch through a solenoid (when PLA are below FI position). PWR MGT SELECTOR LINE A : One engine out operation LINE B : Normal TO or MCT LINE C : CLB LINE D : CRZ Note : Sensible sector designed to allow fix throttle engine control. Notch refer to (1) Mod: 5948 Ramp refer to(2) 1.16.30 POWER PLANT P4 SYSTEMS OPERATING 001 APR 11 AA ENGINE POWER CONTROL LAWS 1 TOP LAW (EEC ON) This is a TQ (PLA) control law, ensuring a constant power. It is backed-- up by an NH (PLA) law which becomes active : - At low power (authority of engine torque control is gradually reduced to be cancelled out at FI), - In case of engine torque control failure, - In Hotel mode. According to the rating selected on the PWR MGT rotary selector, with the PL at a set point, the EEC commands a determined engine power and therefore a torque value (for a given propeller speed). Thus, the torque which is the engine control parameter, is controlled (with PLA constant) in all ambient conditions. Mod: 5948 1.16.30 POWER PLANT P5 SYSTEMS OPERATING 001 APR 11 AA When necessary, power is automatically reduced in such a way as to maintain the torque at the maximum value, authorized for the rating considered (thermo dynamic limit). Example for : sea level, bleed off, static conditions. Mod: 5948 1.16.30 POWER PLANT P6 SYSTEMS OPERATING 001 APR 11 AA PLA quadrant has TWO CLEARLY IDENTIFIED POSITIONS Position 1 WHITE MARK (1 <-- > Notch) At this position marked by a notch the control system delivers max rated power corresponding to the mode selected. TO : P = 2475 SHP MCT : P = 2500 SHP CLB : P = 2192 SHP CRZ : P = 2132 SHP ENGINE REGULATION - Engine regulation uses pitot and static data coming from EEC. EEC data are elaborated either from the selected ADC (normal configuration) or from engine sensors and imposed data (emergency configuration). ADC is selected through the VPC TAT SEL. Note : If the selected ADC electrical supply fails, two events may occur : - If ADC 2 was selected, ADC 1 immediately takes over from ADC 2 ; - If ADC 1 was selected, engine sensors immediately take over from ADC 1. The engine torque must match the TQ BUG, except when TO is selected at the PWR MGT selector. When TO is selected at the PWR MGT selector, with the ATPCS armed : - the TQ bug corresponds to RTO - in normal T.O. configuration PL NOTCH PWR MGT TO ATPCS ARMED TQ BUG is positioned at RTO. This value must be crosschecked between engines. In the event of engine failure and automatic uptrim, the engine torque will coincide with TQ BUG (RTO). Mod: 5948 1.16.30 POWER PLANT P7 SYSTEMS OPERATING 001 APR 11 AA Example : (ISA conditions) Comment If necessary, moving the lever out of the notch will enable to set precise power setting without any discontinuity. Position (2) beginning of AMBER SECTOR This position, characterized by a ramp threshold is used during GO Around or at take off in the event of ATPCS failure. The power delivered is GA (or RTO) for NP = 100%, irrespective of the mode selected on the PWR MGT rotary selector. In this position, the engine torque agrees with the RTO torque calculated by the FDAU Note : The ramp threshold may be overriden, thus enabling the lever to be positioned up to the stop of the PLA quadrant. This procedure must remains EXCEPTIONAL. It is AN EMERGENCY PROCEDURE WHICH WILL PROVIDE UP TO 15 % more power than RTO. 2 EEC FAILURE - EEC FAULT Flashes. - NH is automatically frozen to its prior value (FAIL FIX) (PL set forward 52°) - As long as EEC Fault flashes deselection is stricly prohibited. - The PL stays ineffective until PL travel reaches 52°. S When PL reaches 52°, the reversion is automatically assured to the manual mode. - EEC FAULT light stays ON. - The pilot deselects EEC. - PL is active again and follows HMU base law. Mod: 5948 1.16.30 POWER PLANT P8 SYSTEMS OPERATING 001 FEB 12 AA 3 R BASE LAW (EEC OFF) The NH (function of PLA) base law is used when the EEC is deselected. (REVERSION MODE). . Refer to the schematic p 4 EEC Deselection Sequence A at time of EEC failure PLA = PLo (NOTCH) NH = NHo NH remains fixed at NHo value until either PL travel reaches 52° or NH reaches its overspeed protection. B NH changes to NH1 value (at that time a power increase or decrease can be noted, according to the operating point position prior to EEC failure with respect to HMU base law). C NH follows the NH (PLA) schedule of the HMU base law. This mode of operation (REVERSION) features : - Loss of torque regulation at constant power lever position (changes in ambient conditions will call for PLA adjustments to maintain maximum engine torque). Note : ¯ Loss of the EEC has no effect on the two torque indications (digital and analogic) displayed - Handling bleed valve (HBV) is still monitored by the EEC deselected with a law function of NH instead of PLA. - Loss of propeller underspeed control at low power (FUEL GOVERNING). Mod: 5948 1.16.30 POWER PLANT P9 SYSTEMS OPERATING 001 FEB 12 AA HOTEL MODE This mode, available on the RH engine only, is exclusively used on the ground to provide aircraft autonomy in terms of air conditioning and DC power supply with the gas generator operating and the propeller locked by a hydraulic brake. R - PL is controlling the power of the generator (NH = f(PL)) since the fuel governing function of the EEC is automatically cancelled when selecting feather. A throttle stop is provided by the gust lock lever to avoid an overtorque risk. Without this protection, hotel mode cannot be selected. - CL has to be set to feather prior to selecting hotel mode and must be left in this position. Hotel mode can be used with EEC ON or OFF. The gust lock stop precludes overpowering the engine. R • SM : Stepper Motor Mod: 5948 1.16.30 POWER PLANT P 10 SYSTEMS OPERATING 001 APR 11 AA 30.3 PROPELLER SPEED GOVERNING BLADE ANGLE GOVERNING This is the normal in flight governing mode. The PVM adjusts the propeller pitch according to the power setting in such a way as to maintain a constant propeller speed NP. This governing is available whether EEC is ON or OFF. PWR MGT selector commands NP propeller speed (through the PEC) PL commands power (and therefore TQ, at a given NP) FUEL GOVERNING This is the ground governing mode at low speed and low power. The EEC automatically increases the fuel flow so as to maintain a minimum propeller speed (NP = 70.8 %) CL is set in AUTO position. Note : This control mode is cancelled : - when EEC is OFF, - when the propeller is in FEATHER position. TRANSITION MODE This is the intermediate mode between the two previous ones. It only applies on ground, or in flight at low power and low speed. The NP speed is comprised between 70.8 % and NP selected. - Control operation may be summarized through the graph below, depicting evolution of the propeller speed NP function of PLA (example given in MCT mode). Mod: 5948 1.16.40 POWER PLANT P1 CONTROLS 001 APR 11 AA 40.1 ATPCS GENERAL The propulsion unit includes an ATPCS (automatic take-- off power control system) which provides in case of an engine failure during take-- off the uptrimmed take-- off power on the remaining engine combined with an automatic feathering of the failed engine. This system enables to reduce the power normally used for take-- off by an amount of about 10% below the power certified by the engine manufacturer. This is favorable to engine/propeller life without affecting the take-- off performance in case of an engine failure. Full ATPCS (i.e. uptrim and autofeather) is only available for take-- off (see arming conditions below). COMPONENTS The ATPCS operates with the following components on each engine : * The Auto Feathering Unit (AFU) which is the main system element. It conditions the torque signal coming from the engine and provides the torque indication : - to the cockpit indicators (analog pointer), - to the FDAU, - to the MFC which includes the autofeathering/uptrim logic functions, and delivers the corresponding control signals to the feather solenoid, to the feathering electrical pump and to the opposite EEC. * The EEC which transmits a signal enabling the power to increase from TO to RTO (or a n NH signal during ATPCS test at ground idle). * The feather solenoid mounted on the PVM, * The feathering electric pump installed on the reduction gear box. In the Cockpit : * The ATPCS pb on the cockpit center panel, * The PL position (sw set to 49°), * A test selector located on the pedestal. ARMING CONDITIONS Mod: 5948 1.16.40 POWER PLANT P2 CONTROLS 001 APR 11 AA TRIGGERING CONDITIONS One torque below 18% SEQUENCE AFTER TRIGGER Time ATPCS ARMED ON GROUND Trigger 2.15 s B B uptrim is triggered and bleed autofeather is activated valve is shut off on the on the affected engine remaining engine Y - feather solenoid activated - feathering electric pump energized - inhibition of autofeather on the remaining engine - ARM light extinguishes t " B ARMED IN FLIGHT autofeather is activated on the affected engine Note : Nothing happens on the affected engine for 2.15 seconds, but uptrim is energized on the remaining engine. This feature enables to perform an acceleration stop without having autofeather in order to benefit from some reversing action on the failed engine. In this case, the throttle reduction occuring within 2.15 seconds period automatically disarms the mode. Once the mode has been triggered, its cancellation can only result from either : - PWR MGT other than TO, or - ATPCS Pb set to OFF, or - both PL retarded. CAUTION : If the engine is restarted, IT WILL BE NECESSARY TO SELECT PWR MGT to MCT position after relight in order to be able to UNFEATHER the propeller. Mod: 5948 1.16.40 POWER PLANT P3 CONTROLS 001 APR 11 AA ATPCS SEQUENCE armed on ground A/FEATH FUNCTION Disarming conditions Note : During a normal flight (without engine failure) uptrim/autofeather will be disarmed after take-- off when leaving the TO position on PWR MGT. Mod: 5948 1.16.40 POWER PLANT P4 CONTROLS 001 APR 11 AA 40.2 POWER LEVERS (PL) PL is mechanically connected to the HMU and to the PVM through cables and rods. This lever controls the power plant thrust from Max rated TQ to max reverse. CAUTION :in case of engine failure, the PL remains active controlling the pitch angle, and therefore associated propeller drag as long as propeller is not feathered. For take off acceleration the pilot will push PLs from GI to the TO position which is identified by a notch. At landing, the pilot will reduce PLs to FI. Then after flight idle gate automatic unlocking, he will act on the triggers to reduce down to GI, and eventually to reverse. Reverse sector is “protected” by a spring rod : a force must be exercised by the pilot to position the PL into reverse sector. Releasing this pull force will bring PL back to around GI. When the PL are on the MAX RATED TQ position, the pilot can increase the power (if necessary) by pushing the PL up the RAMP (after GO AROUND position) to the FWD stop. Note : On the ground, the gust lock, when engaged, prevents excessive PL in the forward traction sector angle. POWER LEVER SWITCHES Mod: 5948 1.16.40 POWER PLANT P5 CONTROLS 001 APR 11 AA 40.3 IDLE GATE At take off, as soon as both landing gear absorbers are released, a gate prevents PL angle reduction below FI. At landing, as soon as one landing gear absorber is compressed, this gate is automatically retracted and the PL may travel down to GI and reverse (below GI). (1) IDLE GATE FAIL light Illuminates amber and the FWS is activated when the gate does not engage automatically in flight or does not retract automatically at landing. (2) IDLE GATE lever Enables manual override in case of failure of the automatic logic. In flight : push On graound : pull. An amber band appears. Mod: 5948 1.16.40 POWER PLANT P6 CONTROLS 001 APR 11 AA 40.4 CONDITION LEVERS (CL) They operate feathering control, HP fuel shut off valves and propellers speed (NP), controlled by PVM when in blade angle governing propulsion mode. - AUTO position controls propeller speed through PWR MGT selector position. - 100 % OVRD position sets manually Np MAX. It is necessary to act on a trigger located on the lever side to travel - from AUTO to FTR (and return), - from FTR to FUEL SO (and return). A red lt incorporated in the lever will illuminate if a fire is detected on the associated engine provided CL is not in FUEL SO position. CONDITION LEVER SWITCHES Mod: 5948 1.16.40 POWER PLANT P7 CONTROLS AA 40.5 INDICATORS & CONTROL PANELS PRIMARY ENGINE INDICATIONS Mod: 5948 001 APR 11 1.16.40 POWER PLANT P8 CONTROLS AA 001 APR 11 (1) TORQUE INDICATOR Two sensing torque probes are located on the reduction gear box. One of them sends a signal to the AFU which controls the torque analogic pointer (B). The other one sends a signal to the EEC which controls the torque digital counter (A). (A) Digital counter Actual digital torque indication is displayed. Torque readout is : - green surrounded by a grey rectangle if TQ is in green sector - amber surrounded by an amber rectangle if TQ is in amber sector - white in red reversed video if TQ is above amber sector limit - amber “LAB” label surrounded by an amber rectangle if a wrong EEC is installed - green, amber, white or red reverse video surrounded “-- - - .-- ” if EEC cannot control the HBV - amber “HBV” label surrounded by an amber rectangle in case of invalid torque value. (B) Pointer Gives the indication of actual analogic torque. Pointer is : - green in Green sector (0 - 100%) - amber in Amber sector (100 - 106%) - red if torque is higher than 106% The pointer is stopped if TQ>120% (C) Take-- Off torque objective Gives graphical round and digital indication of torque objective at take off if NP>25%. It is indicated in green. Readout is replaced by “-- - - ” amber label in case of invalidity. (D) Torque objective Gives graphical indication (triangle) of torque objective : - Magenta if Go Around is selected - Amber if Go around is not selected (E) Engine 1 and 2 Power Management selection Gives an indication of engine 1 and engine 2 power management selection. It is displayed in cyan. Label is : - “TO” if Engine Power Management is set to “Take Off” - “MCT” if Engine Power Management is set to “Maximum Continuous Thrust” - “CLB” if Engine Power Management is set to “Climb” - “CRZ” if Engine Power Management is set to “Cruise” Mod: 5948 1.16.40 POWER PLANT P9 CONTROLS 001 APR 11 AA (2) NP INDICATOR Gives digital indication of analogic NP. Readout is : - Green if NP<41.6% or 62.5%<NP<103.5% - Amber surrounded by an amber rectangle if 41.6%<NP<62.5% or 103.5%<NP<106% - white in red reversed video if NP>106% - replaced by “-- - - .-- ” label in case of NP value invalidity. (3) ITT INDICATOR (A) Digital counter Gives the numeric indication of Inter Turbine Temperature. ITT readout is : - green surrounded by a grey rectangle if ITT is in green sector - amber surrounded by an amber rectangle if ITT is in amber sector - white in red reversed video if ITT is above amber sector limit - amber “-- - - .-- ” surrounded by an amber rectangle if ITT is invalid (B) Pointer Gives the analogic indication of Inter Turbine Temperature in °C. Pointer is displayed if ITT is valid. ITT Arc Sectors Description : - Green sector : from 0°C to Amber sector, normal temperatures - Amber sector : up to 800°C, or 715°C when hotel mode is set, or 765°C during takeoff (variable according OAT) - Red point ”H” : 715°C, limit in hotel mode - Red sector : from 840°C or 715°C in hotel mode - Red line “S”: 950°C, limit during start ITT Pointer is : - green if ITT is in Green sector - amber if ITT is in Amber sector - red if ITT is in red sector The pointer is stopped if ITT>1000°C Mod: 5948 1.16.40 POWER PLANT P 10 CONTROLS 001 APR 11 AA (4) UPTRIM message Indicates uptrim status message. It is displayed in green reverse video when engine uptrim is activated. (5) AUTO FTR message Indicates auto feather in green reversed video for each engine if AUTO FTR is activated. (6) PROP BRK message Indicates in cyan, that the propeller brake is engaged on engine 2 (7) LO PITCH and NO REV message Indicates propeller in low pitch range on each side. “LO PITCH” flag is displayed in : - green reversed video in normal operation (below 8° on ground) - amber reversed video in abnormal operation “NO REV” red reverse video flag replaces “LO PITCH” flag when any propeller pitch remains above 8° after touchdown with PL retarded to GI. (8) SGL CH message It is displayed in amber : - when one channel of the propeller engine control is lost. The system will be automatically transfered to the other channel. - during the starting, when the propeller in unfeathered (PEC self test) (9) IGN message Indicates engine ignition. It is displayed in cyan. Mod: 5948 1.16.40 POWER PLANT P 11 CONTROLS 001 APR 11 AA SECONDARY ENGINES INDICATIONS The engine’s systems information are displayed on the upper part of the MFD : - The oil informations on the top, on each side of engine informations, describes the current state of the oil systems - The engine system, between oil information, displays the status of the two engines (1) Start Engine indicator Indicates the state of engine start. Green reversed video “START” label is displayed in normal configuration. Amber reversed video “START” label is displayed if there is a discrepancy between Engine Start indication and light test or if an Engine Start Fault is detected. (2) Cross Start Failure Appears to indicate that, although the opposite DC gen is connected to the network, the cross start sequence has failed. Amber “X START FAIL” label is displayed between the start engine indicators. Mod: 5948 1.16.40 POWER PLANT P 12 CONTROLS 001 APR 11 AA (3) High Pressure Turbine indicator (NH indicator) Displays the high pressure turbine speed. - From 0% to 62%, segment is displayed in white, readout and pointer are displayed in green. - From 62% to 103.1%, segment, readout and pointer are displayed in green. - From 103.2% to 106.3%, segment, pointer and a framed readout are displayed in amber. - For a value equal or higher than 106.4%, pointer is dsplayed in red, readout is diplayed in red reversed video. - For invalid value, three amber dashes are displayed instead of the digits. (4) Low Pressure turbine indicator (NL indicator) Displays the low pressure speed. NL readout is : - green if NL is lower than 104.1% - amber surrounded by an amber rectangle from 104.2% to 106.7% - in red reversed video for a value equal or higher than 106.8%. - three amber dashes instead of digits in case of invalid value . (5) Inter Turbine Temperature (ITT) digital counter Displays the Inter Turbine Temperature value in °C. ITT readout is : - green surrounded by a grey rectangle if ITT is in Green Sector - amber surrounded by an amber rectangle if ITT is in Amber Sector - in reverve red video if ITT is above Amber Sector limit temperrature. Note : See “ITT indicator pointer” in “Primary Engine Indication” section for sectors description. Mod: 5948 1.16.40 POWER PLANT P 13 CONTROLS 001 APR 11 AA (6) OIL INDICATOR (A) LO PR message Red reverve video label indicating an oil low pressure. (B )OIL pressure Displays oil pressure of engines in PSI. Oil pressure indicator ranges are : - 0 to 40 PSI : red segment , pointer and red reverse video readout - 40 to 55 PSI and above 65 PSI : amber segment, pointer and amber framed readout - 55 to 65 PSI : green segment, pointer and readout In case of value invalidity, the value is replaced by amber “-- - ” label and there is no pointer displayed. (C) OIL temperature Displays oil temperature of engines in °C. Oil temperature indicator arc ranges are : - 0 to 40°C : segment in white, pointer and readout in green - 40°C to 125°C : segment, pointer and readout in green - from - 40°C to 0°C and from 125°C to 140°C : segment, pointer and readout in amber - Below - 40°C and above 140°C pointer and readout in red A red line is set at 140°C In case of value invalidity, the value is replaced by amber “-- - - ” label and there is no pointer displayed. Mod: 5948 1.16.40 POWER PLANT P 14 CONTROLS 001 APR 11 AA ENG 1/ENG 2 CONTROL PANEL 1 EEC pb Controls the EEC of the associated engine ON : (pb pressed in) EEC adjusts HMU action, by controlling the stepper motor which lowers fuel flow ordered by HMU. OFF : (pb released) The HMU controls only NH as a function of PL angle. OFF light illuminates white. FAULT : When EEC failure is detected: Flashing amber :The fuel flow is frozen to maintain the power, when FAULT flashes, never deselect the EEC. Retard first, the PL in the green sector (FAULT become steady: PL < 52°) Reversion to HMU base law is achieved when the PL are retarded in the green sector Steady amber : automatic reversion to HMU base law 2 ATPCS pb pb pressed in : - If pressed in on ground, uptrim and autofeather function are armed. - if pressed in in flight, only the autofeather function is armed. OFF : (Pb released) Uptrim and autofeather functions are deselected. ARM : Illuminates green when arming conditions are met (see P1) Mod: 5948 1.16.40 POWER PLANT P 15 CONTROLS 001 APR 11 ENG START PANEL 1 2 3 ENG START rotary selector Selects the ignition mode and/or start sequences. OFF START ABORT Ignition circuit is deenergized. Starting sequence is disarmed or interrupted. CRANK Enables engine cranking. Ignition is inhibited. START Selects a start sequence. Ignition is selected when fuel shut-- off valve is open (controlled by CL) ; starter and ignition are automatically deactivated when NH reaches 45%. Note : There are three START positions START A Only ignition exciter A is supplied on ground. START B Only ignition exciter B is supplied on ground. START A and B Both ignition exciters are supplied. START pb Initiates the starting (or cranking) sequence of the related engine provided the ENG START selector is in one of the START positions (or CRANK). ON (pb pressed in) Initiates a sequence. The ON It illuminates white. In case of starting, it will extinguish automatically when NH reaches 45% which “identifies” sequence end. FAULT Illuminates amber and the FWS is activated if : - starter remains engaged after 45% - GCU fails during starting - On RH engine when the propeller brake is ON but the gust lock is not engaged. As soon as one engine is running and the associated DC GEN is connected to the main DC electrical network, the other engine start is accomplished as a “cross start” : initiated on Main Bat supply only, the start is assisted by the opposite DC GEN from 10% NH (on ground only). If the DC GEN is connected to the network, but the cross start does not operate normally, the amber ”X START FAIL” light illuminates on the main electrical panel. XSTART FAIL is displayed on the engine SD page. MAN IGN guarde pb Manual ignition is selected by depressing the guarded pb. Exciters are continuously energized on both engines. ON light illuminates blue. Mod: 5948 1.16.40 POWER PLANT P 16 CONTROLS 001 APR 11 AA PROP BRK PANEL (1) PROP BRK pb The PROP BRK two positions toggle switch controls the propeller brake engagement/disengagement on the RH engine provided blue hydraulic power is available. ON : propeller brake engagement OFF : propeller brake releasing UNLK : The light illuminates red and after 15 s the FWS is activated to indicate that the propeller brake is not locked in the fully locked or the fully released position. (2) Ready light Illuminates green when engagement or disengagement conditions are met. (3) PROP BRK light - Illuminates blue when the propeller brake is fully locked - Extinguished when the propeller brake is not fully locked. Note : “PROP BRK” cyan label is displayed on EWD when the propeller brake is engaged. Mod: 5948 1.16.40 POWER PLANT P 17 CONTROLS 001 APR 11 AA PWR MGT PANEL (1) PWR MGT rotary selector Made up of two independent parts (front and back). Provides FDAU, PIU and EEC with basic power requirements corresponding to the selected position. - For left engine with the back part of the selector. - For right engine with the front part of the selector. (2) PEC FAULT pbs FAULT Illuminates amber and FWS is activated when the two channels are lost. OFF (pb released) PEC is deactivated and Np is blocked at 102% whenever power is sufficient. ENGINE TEST PANEL Allows to check the correct functionning of the ATPCS. This rotary selector is spring loaded to the neutral position. Mod: 5948 . 1.16.45 POWER PLANT P1 BOOST FUNCTION AA LEFT INTENTIONALY BLANK Mod: 5948 001 APR 11 1.16.45 POWER PLANT P 2/3 BOOST FUNCTION AA LEFT INTENTIONALY BLANK Mod: 5948 001 APR 11 1.16.50 POWER PLANT P1 LATERAL MAINTENANCE PANEL 001 APR 11 AA On RH Maintenance panel, several tests and control device are provided, for maintenance purpose only. All buttons on this panel are to be used on ground only. 1 EEC/PEC SEL switch 2 Used to select EEC or PEC depending on appropriate maintenance test on Engine TRIM switches or LRU (line replaceable unit) code failures. Engine TRIM test and LRU switches 3 Switch with two stable positions used to : - Test EEC or PEC channel. Maintenance data are managed by MPC. (Selected by EEC/PEC SEL switch). - Perform EEC or PEC trim to ensure that power delivered corresponds to PL position (can be performed with engine not running and PL in the notch) or LRU code failures. BUS ARINC switches Bus arinc switches select the source. Mod: 5948 1.16.50 POWER PLANT P2 001 LATERAL MAINTENANCE PANEL APR 11 AA 4 Prop Overspeed test switches Used to test hydraulic part of overspeed governor. A First OVSPD threshold is tested at 102 % Np. on the affected engine. A + B , 2 nd OVSP threshold is tested at 106 % Np. 5 Propeller Feather Pump test switch This switch with two stables positions enables to test the feathering pump. For safety reasons, this test is impossible in flight. 6 Propeller LOW PITCH test switches - With the test switch on PLA > FI position, the PL low pitch protection switch and feather solenoid are tested. - With the test switch on PLA < FI position, secondary low pitch solenoid is tested. Note : In both cases, LOW PITCH message is displayed on EWD Mod: 5948 1.16.60 POWER PLANT ELECTRICAL SUPPLY/MFC LOGIC SYSTEM MONITORING P1 001 APR 11 AA ELECTRICAL SUPPLY EQUIPMENT ENG 1 Feather control Start control and indications Ignition system EEC . power supply . control Propeller overspeed test Mod: 5948 DC BUS SUPPLY (C/B) AC BUS SUPPLY (C/B) DC EMER BUS (+DC BUS 1) (on overhead panel FEATH CTL) - Nil - DC ESS BUS (on overhead panel START CTL and IND) - Nil - DC ESS BUS (on overhead panel IGN) - Nil - DC EMER BUS and DC BUS 1 (on overhead panel PWR SUPPLY) DC EMER BUS (on lateral overhead panel CTL and CAUTION) - Nil - DC BUS 1 (on lateral panel PROP OVSPD TEST) 1.16.60 POWER PLANT ELECTRICAL SUPPLY/MFC LOGIC P2 001 SYSTEM MONITORING APR 11 AA ELECTRICAL SUPPLY EQUIPMENT ENG 2 Feather control Start control and indications Ignition system EEC . power supply . control Propeller overspeed test Mod: 5948 DC BUS SUPPLY (C/B) DC EMER BUS (+DC BUS 1) (on overhead panel FEATH CTL) DC ESS BUS (on overhead panel START CTL and IND) DC ESS BUS (on overhead panel IGN) DC EMER BUS and DC BUS 1 (on overhead panel PWR SUPPLY) DC EMER BUS (on lateral overhead panel CTL and CAUTION) DC BUS 1 (on lateral panel PROP OVSPD TEST) 1.16.60 POWER PLANT ELECTRICAL SUPPLY/ P3 001 MFC LOGIC/SYSTEM MONITORING EQUIPMENT APR 11 DC BUS SUPPLY (C/B) Propeller brake DC ESS BUS (on lateral panel PWR SUPPLY CTL IND) Feather pump test DC SVCE BUS (on lateral panel FEATH PUMP TEST) PEC 1 + 2 (NORMAL) associated PVM and PIU DC EMER BUS (on overhead panel) PEC 1 + 2 (BACK-- UP) DC ESS BUS (on overhead panel) Idle gate MFC LOGIC See chapter 1.01. Mod: 5948 . DC BUS 1 (on overhead panel SOL) . DC BUS 2 (on overhead panel CAUTION) 1.16.60 POWER PLANT ELECTRICAL SUPPLY/MFC LOGIC P4 SYSTEM MONITORING 001 APR 11 AA SYSTEM MONITORING ENG 1(2) OUT (at take off) This warning is generated at take off in case of engine 1(2) failure. Visual and aural alerts are : - MW light flashing red - “ENG 1(2) OUT” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) ENG 1(2) OUT (in flight) This caution is generated in flight in case of engine 1(2) failure. Visual and aural alerts are : - MC light flashing amber - “ENG 1(2) OUT” amber message on EWD - Aural alert is Single Chime (SC) ENG 1+2 OUT This warning is generated in case of both engines failure. Visual and aural alerts are : - MW light flashing red - “ENG 1+2 OUT” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) NAC OVHT This warning is generated when nacelle temperature exceeds 170°C (338°F) when aircraft is on ground. Visual and aural alerts are : - MW light flashing red - “NAC OVHT” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) - NAC OVHT legend in red reverse video on SD engine page PROP BRK This warning is generated when propeller brake is not locked in full locked or in full released position. Visual and aural alerts are : - MW light flashing red - “PROP BRK” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) - UNLK red light on overhead panel Mod: 5948 1.16.60 POWER PLANT ELECTRICAL SUPPLY/MFC LOGIC P5 001 SYSTEM MONITORING APR 11 AA ENG START ITT This caution is generated when start ITT is above limit (T>800°C (1590°F)) Visual and aural alerts are : - MC light flashing amber - “ENG START ITT” amber message on EWD - Aural alert is Single Chime (SC) SINGLE ENGINE This caution is generated in case of single engine operation Visual and aural alerts are : - MC light flashing amber - “SINGLE ENGINE” amber message on EWD - Aural alert is Single Chime (SC) IDLE GATE This caution is generated in case of automatic idle gate system failure Visual and aural alerts are : - MC light flashing amber - “IDLE GATE” amber message on EWD - Aural alert is Single Chime (SC) - IDLE GATE amber light on pedestal ENG 1(2) LO PITCH This caution is generated in case of low pitch detection in flight Visual and aural alerts are : - MC light flashing amber - “ENG 1(2) LO PITCH” amber message on EWD - Aural alert is Single Chime (SC) - LO PITCH displayed amber on the primary engine indications ENG BOOST (if installed) This caution is generated when boost failure is detected Visual and aural alerts are : - MC light flashing amber - “ENG BOOST” amber message on EWD - Aural alert is Single Chime (SC) - BOOST pb FAULT light illuminates on PWR MGT panel Mod: 5948 1.16.60 POWER PLANT ELECTRICAL SUPPLY/MFC LOGIC P6 001 SYSTEM MONITORING APR 11 AA ENG 1(2) PEC This caution is generated in case of PEC failure Visual and aural alerts are : - MC light flashing amber - “ENG 1(2) PEC” amber message on EWD - Aural alert is Single Chime (SC) - PEC pb FAULT light illuminates ENG 1(2) OVER LIMIT This caution is generated when engine temperature is above limit Visual and aural alerts are : - MC light flashing amber - “ENG 1(2) OVER LIMIT” amber message on EWD - Aural alert is Single Chime (SC) - NH indicator arc amber (between 103.3 and 106.4%) or red (>106%) - NL value amber (between 104.2 and 106.8%) or red (>106.8%) ENG 1(2) PROP LIMIT This caution is generated when propoller rate is above limit Visual and aural alerts are : - MC light flashing amber - “ENG 1(2) PROP LIMIT” amber message on EWD - Aural alert is Single Chime (SC) ENG FUEL CLOG This caution is generated in case of clogging of the filter associated with HP pump Visual and aural alerts are : - MC light flashing amber - “ENG FUEL CLOG” amber message on EWD - Aural alert is Single Chime (SC) - CLOG label in amber on SD engine page ENG START This caution is generated in case of start sequence incident Visual and aural alerts are : - MC light flashing amber - “ENG START” amber message on EWD - Aural alert is Single Chime (SC) - START label in amber reverse video on SD engine page - FAULT legend in amber on the affected START pb. Mod: 5948 1.16.60 POWER PLANT ELECTRICAL SUPPLY/MFC LOGIC P7 SYSTEM MONITORING 001 APR 11 AA ELEC X START This caution is generated when on ground, during second engine start, operative DC GEN does not come on line to supply the START BUS between 10 % and 45 % NH Visual and aural alerts are : - MC light flashing amber - “ELEC X START” amber message on EWD - Aural alert is Single Chime (SC) - X START FAIL on Engine SD page - X START FAIL on overhead panel ENG START NO NH This caution is generated if NH does not incrrease during start Visual and aural alerts are : - MC light flashing amber - “ENG START NO NH” amber message on EWD - Aural alert is Single Chime (SC) ENG NO ITT This caution is generated if ITT does not increase during start Visual and aural alerts are : - MC light flashing amber - “ENG NO ITT” amber message on EWD - Aural alert is Single Chime (SC) ENG EEC This caution is generated in case of one EEC failure Visual and aural alerts are : - MC light flashing amber - “ENG EEC” amber message on EWD - Aural alert is Single Chime (SC) - FAULT light illuminate on dedicated EEC pb (Flashing if PL above 52°C) ENG EEC 1+2 This caution is generated in case of both EEC failureVisual and aural alerts are : - MC light flashing amber - “ENG EEC 1+2” amber message on EWD - Aural alert is Single Chime (SC) - FAULT light illuminates on EEC pb (Flashing if PL above 52°) Mod: 5948 1.16.60 POWER PLANT ELECTRICAL SUPPLY/MFC LOGIC P8 001 SYSTEM MONITORING APR 11 AA ENG 1(2) PEC SGL CH This caution is generated in case of PEC failureVisual and aural alerts are : - MC light flashing amber - “ENG 1(2) PEC SGL CH” amber message on EWD - Aural alert is Single Chime (SC) - SGL CH on engine page ENG 1(2) OIL PRESS This warning is generated either when oil pressure drops below 40 PSI on indicator or low pressure switch is activated. Visual and aural alerts are : - MW light flashing red - “ENG 1(2) OIL PRESS” red message on EWD - Aural alert is Continuous Repetitive Chime (CRC) - LO PR flag in red reverse video on SD engine page (when low pressure switch generates a signal to the MFC and CAC) ENG 1(2) OIL OVHT This caution is generated in case of engine oil overheat Visual and aural alerts are : - MC light flashing amber - “ENG 1(2) OIL OVHT” amber message on EWD - Aural alert is Single Chime (SC) - Oil temperature readout in red. ENG 1(2) OIL TEMP LO This caution is generated when engine oil temperature is detected too low. (T<45°C (89°F)) Visual and aural alerts are : - MC light flashing amber - “ENG 1(2) OIL TEMP LO” amber message on EWD - Aural alert is Single Chime (SC) - Oil temperature arc in white on SD engine page ENG 1(2) OIL TEMP HI This caution is generated when engine oil temperature is detected too high (125°C <T<140°C) (248°F<T<278°F) Visual and aural alerts are : - MC light flashing amber - “ENG 1(2) OIL TEMP HI” amber message on EWD - Aural alert is Single Chime (SC) - Oil temperature arc in amber - Oil temperature readout in amber Mod: 5948 2.01.00 LIMITATIONS P 1 CONTENTS AA 2.01.00 2.01.01 2.01.02 2.01.03 2.01.04 2.01.05 2.01.06 2.01.07 2.01.08 2.01.09 2.01.10 Mod 5948 C0NTENTS GENERAL WEIGHT AND LOADING AIRSPEED AND OPERATIONAL PARAMETERS POWER PLANT SYSTEMS TCAS FMS CABIN LIGHTING TAWS COCKPIT DOOR SECURITY SYSTEM (if installed) 001 APR 11 . APR 11 cs Mod 5948 2.01.01 LIMITATIONS P2 001 GENERAL APR 11 AA MANEUVERING LIMIT LOAD FACTORS FLAPS RETRACTED = - 1 G to 2.5 G FLAPS EXTENDED = 0 G to + 2 G GEAR DOWN = 0 G to + 2 G The corresponding positive accelerations limit the bank angle in turns and the severity of pull up maneuvers. CARGO DOOR OPERATION Do not operate cargo door with a cross wind component of more than 45 kt. DISPATCHABILITY For dispatch in the event of equipment failure or missing equipment refer to MEL/CDL. MAXIMUM NUMBER OF PASSENGER SEATS 74 Mod 5948 as limited by emergency exits configuration. Other limitations such as that given by the emergency evacuation demonstration must be respected. 2.01.02 LIMITATIONS P1 700 WEIGHT AND LOADING APR 11 AA DESIGN WEIGHT LIMITATIONS MAXIMUM WEIGHT KG LB TAXI 22 970 50 640 TAKE OFF 22 800 50 265 LANDING 22 350 49 273 ZERO FUEL 20 800 45 856 CENTER OF GRAVITY ENVELOPE The limits of center of gravity are given in percentage of the mean aerodynamic chord (MAC), landing gear extended. The MAC is 2.303 meters long (90.67) inches. Station O is located 2.362 meters (92.99 inches) forward of the fuselage nose. The distance from station 0 to reference chord leading edge is 13.604 meters (535.59 inches). Mod : Mod 5948 + 5555 Model : 212A 2.01.02 LIMITATIONS P2 WEIGHT AND LOADING 001 APR 11 AA PASSENGERS BOARDING / DISEMBARKING See WBM 1.10.04 p1 PASSENGERS BOARDING / DISEMBARKING - The tail prop must installed before passengers boarding / disembarking; - A possible toppling over should be taken into account from seven persons moving near the rear part of an off loading aircraft. Mod 5948 Model : 212A 2.01.03 LIMITATIONS P1 AIRSPEED AND OPERATIONAL PARAMETERS 001 APR 11 AA AIRSPEEDS * MAXIMUM OPERATING SPEED. This limit must not be intentionnaly exceeded in any flight regime. VMO = 250 kt MMO = 0.55 * MAXIMUM DESIGN MANEUVERING SPEED VA Full application of roll and yaw controls as well as maneuvers involving angles of attack near the stall should be confined to speeds below VA. VA = 175 kt CAUTION : Rapidly alternating large rudder applications in combination with large sideslip angles may result in structural failure at any speed. * MAXIMUM FLAPS EXTENDED OPERATING SPEEDS VFE FLAPS 15 185 kt FLAPS 30 150 kt * MAXIMUM LANDING GEAR EXTENDED OPERATING SPEEDS VLE = 185 kt VLO RET= 160 kt VLO LOW= 170 kt * MAXIMUM ROUGH AIR SPEED VRA= 180 kt * MAXIMUM WIPER OPERATING SPEED VWO = 160 kt * MAXIMUM TIRE SPEED : 165 kt (Ground speed). Mod 5948 2.01.03 LIMITATIONS P2 AIRSPEED AND OPERATIONAL PARAMETERS AA ROFA-- 02-- 01-- 03-- 002-- A500AA R STALL SPEEDS - VSR Mod 5948 Eng. : PW127F / PW127M 001 APR 11 2.01.03 LIMITATIONS P3 AIRSPEED AND OPERATIONAL PARAMETERS 001 APR 11 AA V1 LIMITED BY VMCG CAS (KT) V1 LIMITED BY VMCG (FLAPS 15) OUTSIDE AIR TEMPERATURE (DG.C) Mod 5948 Eng. : PW127F / PW127M 2.01.03 LIMITATIONS P4 AIRSPEED AND OPERATIONAL PARAMETERS 001 APR 11 AA ROFA--02--01--03--004--A500AA VMCA CAS (KT) VMCA (FLAPS 15) VMCL Mod 5948 Flaps VMCL (CAS) 30 98 kt 15 98 kt Eng. : PW127F / PW127M APR 11 Altitude Zp (ft) For operations on runways slope beyond 2% : refer to 3.11.18 MINIMUM RUNWAY WIDTH : 30m For narrow runways operations : refer to 3.11.10 Mod : 5948 + 3037 + (3522 or 8044) 2.01.03 LIMITATIONS P6 AIRSPEED AND OPERATIONAL PARAMETERS 001 APR 11 TAKE OFF AND LANDING (CONT’D) The maximum crosswind demonstrated is: - Take-- off: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35kt - Landing Flaps 30°: . . . . . . . . . . . . . . . . . . . . . . . . . . 35kt Braking Action TO LDG GOOD 1 1 35 kt GOOD/MEDIUM 2 2 28 kt MEDIUM 3/6 6 22 kt MEDIUM/POOR 4 5 16 kt POOR 7 7 10 kt Maximum Crosswind (TO and LDG) Runway status: 1: dry runway, 2:wet up to 3mm depth, 3 (TO only): slush or water from 3 to 6mm depth, 4 (TO only):slush or water from 6 to 12.7mm depth, 5: slush or water from 3 to 12.7mm depth, 6: compact snow, 7: ice Mod 5948 2.01.04 LIMITATIONS P1 POWER PLANT AA 001 APR 11 ENGINES ENGINE PARAMETERS Operating limits with no unscheduled maintenance action required. Beyond these limits, refer to maintenance manual. POWER SETTING TIME LIMIT TQ (%) ITT (°C) NH (%) NL (%) NP (%) OIL PRESS (PSI) OIL TEMPERATURE (°C) RESERVE TAKE OFF 10 mn (***) 100 (**) 800 103.2 104.2 101 55 to 65 0 to 125 (3) TAKE OFF 5 mn 90 (**) (*) 101.9 101.4 101 55 to 65 0 to125 (3) MAXIMUM CONTINUOUS NONE (***) 90.9 (**) 800 103.2 104.2 101 55 to 65 0 to 125 (3) 40 mini (****) - 40 to 125 (3) 55 to 65 125 (3) GROUND IDLE 66 mini HOTEL (4) MODE STARTING 715 5s 950 (2) OTHER TRANSIENT - 54 min 800 106 (*****) 5s 20 s(1) (2) 20 mn 120 120 840 106.4 106.8 108 140 During RESERVE TAKE OFF, TQ indication may exceed 100 % but not 106.3 %. (*) ITT limite depends on outside air temperature; refer to 2.01.04 P 3 for detailed information. (**) Value linked to 100 % NP. (***) - RTO: Time beyond 5 mn is linked to actual single engine operations only. - MCT rating is the max power certified for continuous use. In-- flight emergencies are the only conditions for which MCT use is authorized. (****) Up to 75 % NH only. (*****) Permissible for completion of flight provided TQ does not exceed 75.2 % during climb and 73.13 % during cruise. (1), (2), (3), (4) : see page 4. Note : Flight with an engine running and the propeller feathered is not permitted. Mod 5948 Model. : 212A 2.01.04 LIMITATIONS P2 POWER PLANT 001 APR 11 AA Note : Operation up to 106.3% torque is time unlimited when NP is below 94% Mod 5948 Model. : 212A 2.01.04 LIMITATIONS P3 POWER PLANT 001 APR 11 AA ITT LIMITS Mod 5948 Model. : 212A 2.01.04 LIMITATIONS P4 POWER PLANT 001 APR 11 AA (1) - Determine and correct cause of overtorque. - Record in engine log book for maintenance. (2) - Determine and correct cause of overtemperature. - Record in engine log book for maintenance. (3) - Temperature up to 125°C is authorized without time limitation. 20 mn are authorized between 125°C and 140°C. - Refer to ENG OIL Hl TEMP procedure. Note : Oil temperature must be maintained above 45°C to ensure inlet strut de-- icing. Oil temperature must be maintained above 71°C to ensure fuel anti - icing protection in absence of the low fuel temperature indication. (4) - Do not use engine 2 in HOTEL MODE without a qualified person (flight crew or maintenance) in the cockpit. PROPELLERS GROUND OPERATION - Engine run up must be performed into the wind. - Engine ground operations with crosswind between 5 and 20 kt should not exceed 58 % TQ. IN FLIGHT OPERATION USE OF NP SETTING BELOW 82 % IN ICING CONDITIONS IS PROHIBITED ATR airplanes are protected against a positioning of power levers below the flight idle stops in flight by an IDLE GATE device. It is reminded that any attempt to override this protection is prohibited. Such positioning may lead to loss of airplane control or may result in an engine overspeed condition and consequent loss of engine power. GROUND OR FLIGHT If a propeller is involved in an overspeed or in an engine overtorque, refer to the propeller maintenance manual. Mod 5948 Model. : 212A 2.01.04 LIMITATIONS P5 001 POWER PLANT APR 11 AA STARTER 3 STARTS WITH A 1 MINUTE 30 SECONDS MAXIMUM COMBINED STARTER RUNNING TIME, FOLLOWED BY 4 MINUTES OFF OIL SYSTEM Approved lubricating oils - Aero Shell Turbine oil 500 - Aero Shell Turbine oil 560 - Royco Turbine oil 500 - Royco Turbine oil 560 - Mobil Jet oil II - Mobil Jet oil 254 - Castrol 4000 - Castrol 5000 - Exxon Turbo oil 2380 Mixing of different brands of oil or viscosities of oil is not recommended. FUEL SYSTEM - Use of JP 4 or JET B is prohibited. - Acceptable fuels (refer to PWC Documentation to determine equivalent approved fuels). FUELS FREEZING POINT (∞C) MINIMUM FUEL TEMP (∞C) Starting Operation MAXIMUM FUEL TEMP (∞C) JET A JET A1 RT, TS1 JP 5 - 40 - 50 - 60 - 46 - 34 - 34 - 34 - 26 - 38 - 48 - 60 - 33 + 57 + 57 + 57 + 57 - Approved anti icing additives (maximum concentration allowed : 0.15 % per volume) : - Philips PFA 55 MB - MIL-- I-- 27 686 D - Ethylene Glycol Monomethyl Ether as defined in MIL-- I-- 27 686 E. Mod 5948 2.01.04 LIMITATIONS P6 POWER PLANT AA REFUELING MAXIMUM PRESSURE 3.5 BARS (50 PSI) USABLE FUEL THE TOTAL QUANTITY OF FUEL USABLE IN EACH TANK IS 2500 KG (5510 LBS) NOTE : FUEL REMAINING IN THE TANKS WHEN QUANTITY INDICATORS SHOW ZERO IS NOT USABLE IN FLIGHT UNBALANCE MAXIMUM FUEL UNBALANCE : 730 kg (1609 lb) FEEDING - EACH ELECTRIC PUMP IS ABLE TO SUPPLY ONE ENGINE IN THE WHOLE FLIGHT ENVELOPE - ONE ELECTRICAL PUMP AND ASSOCIATED JET PUMP ARE ABLE TO SUPPLY BOTH ENGINES IN THE WHOLE FLIGHT ENVELOPE Mod 5948 001 APR 11 2.01.05 LIMITATIONS P1 030 SYSTEMS AA APR 11 AIR - PRESSURIZATION MAXIMUM DIFFERENTIAL PRESSURE MAXIMUM NEGATIVE DIFFERENTIAL PRESSURE MAXIMUM DIFFERENTIAL PRESSURE FOR LANDING MAXIMUM DIFFERENTIAL PRESSURE FOR OVBD VALVE FULL OPEN SELECTION MAXIMUM ALTITUDE FOR ONE BLEED OFF OPERATION 6.35 PSI - 0.5 PSI 0.35 PSI 1 PSI 20 000 ft ELECTRICAL SYSTEM SOURCE DC GEN INV ACW GEN TRU MAX LOAD 400 A 600 A 800 A 500 VA 575 VA 750 VA 20 KVA 30 KVA 40 KVA 60 A 90 A TIME LIMIT NONE 2 mn 8s NONE 30 mn 5 mn NONE 5 mn 5s NONE 5 mn SINGLE DC GEN OPERATION In flight : if OAT exceeds ISA + 25, flight level must be limited to FL 200 HYDRAULIC SYSTEM SPECIFICATION : HYJET IV OR SKYDROL LD 4 LANDING GEAR DO NOT PERFORM PIVOTING (SHARP TURNS) ON A LANDING GEAR WITH FULLY BRAKED WHEELS EXCEPT IN CASE OF EMERGENCY MFC TAKE OFF WITH TWO OR MORE FAILED MFC MODULES IS PROHIBITED. Mod : 5948 + 1603 2.01.05 LIMITATIONS P2 SYSTEMS 100 APR 11 AA OXYGEN Reference temperature = Cabin Temperature or OAT whichever is higher, on ground = Cabin Temperature in flight Minimum bottle pressure required to cover a cabin depressurization at mid-- time of the flight, an emergency descent from 25,000 ft to 13,000 ft within less than 4 minutes and a flight continuation at an altitude below 13,000 ft. A 25 % pax oxygen consumption is assumed. In case of smoke emission, the system protects the flight crew members during 15 min. Note : At dispatch the computed flight time after decompression should be at least 1/2 of estimated flight time to destination or flight time to the longest en route alternate which ever is higher. Provision is made to cover : - unusuable quantity - normal system leakage - Ref. Temp errors. Mod : 5948 + 4411 2.01.05 LIMITATIONS P3 001 SYSTEMS APR 11 AA AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) -- Minimum height for autopilot engagement on take off : 100 ft. After T/O below 1000 f, use of autopilot is not permitted with bank angle greater than 15_. -- Minimum height for autopilot use in single source configuration: do not use AP/YD in single source configuration(one ADC and/or one AHRS lost : -- below 1000 ft AGL, or -- with stall warning inoperative. -- NAV mode for VOR approach, using either autopilot or flight director is authorized only if : -- a co--located DME is available, and -- DME HOLD is not selected -- Minimum height for use of either autopilot or flight director : -- Except during take off or approach : 1000 ft -- VS or IAS mode during approach :160 ft -- CAT 1 APP mode : 160 ft Refer to 2.02.04 for CAT II operation INSTRUMENTS MARKINGS Red arc or radial line : minimum and maximum limits Yellow arc : caution area Green arc : normal area FLAPS Holding with any flaps extended is prohibited in icing conditions (except for single engine operations); ICING CONDITIONS -- All icing detection lights must be operative prior to flight into icing conditions at night. -- The ice detector must be operative for flight into icing conditions. Mod 5948 2.01.05 LIMITATIONS P4 SYSTEMS AA PAGE LEFT INTENTIONALLY BLANK Mod 5948 001 FEB 12 2.01.06 LIMITATIONS P1 001 TCAS APR 11 AA TCAS LIMITATIONS The limitations in Part 2.01 are applicable with the addition of the following: 1-- TCAS operation is approved for use in VFR meteorological conditions (VMC) and IFR meteorological conditions (IMC). 2-- The pilot must not initiate evasive maneuvers using information from the traffic display only or from a traffic advisory (TCAS TA) only. These displays and advisories are intended only for assistance in visually locating the traffic and lack the resolution necessary for use in evasive maneuvering. 3-- Compliance with TCAS resolution advisory is required unless the pilot considers it unsafe to do so. However, maneuvers which are in the opposite direction of the resolution advisory (TCAS RA) are extremely hazardous and are prohibited unless it is visually determined they are the only means to assure safe separation. CAUTION : Once a non crossing RA has been issued the vertical speed should be accurately adjusted to comply with the RA, in order to avoid negating the effectiveness of a co-- ordinated maneuvre by the intruder. WARNING : Non compliance with a crossing RA by one airplane may result in reduced vertical separation. Therefore, safe horizontal separation must also be assured by visual means. 4-- Evasive maneuvring should be made with the autopilot disengaged, and limited to the minimum required to comply with the RA. The pilot must promptly return to the previous ATC clearance when the TCAS “CLEAR OF CONFLICT” voice message is announced. 5-- Prior to perform RA’s climb or increase climb, the crew should select the appropriate engine power setting on the power MGT rotary selector. 6-- When a climb or increase climb RA occurs with the airplane in the landing configuration or in the go-- around phase, a normal procedure of go-- around should be followed including the appropriate power increase and configuration changes. Mod 5948 2.01.06 LIMITATIONS P2 TCAS 001 APR 11 AA TCAS (CONT’D) 7-- Because of the limited number of inputs to TCAS for determination of aircraft performance inhibits, there are instances where inhibiting RAs would be appropriate, however it is not possible to do so. In these cases, TCAS may command maneuvers which may significantly reduce stall margins or result in stall warning. Conditions where this may occur include operations with a bank angle (wings level is assumed), weight, altitude and temperature combinations outside those noted below, leaving aircraft in landing configuration during climb RA on approach, engine out operations, and abnormal configurations such as landing gear not retracted or stick pusher/shaker failure. The table below entitled “Flight Envelope in which climb resolution advisory can be accomplished without stick pusher/shaker activation” outlines the parameters used in the development of the performance inhibits. This table does not consider worst turboprop flight conditions especially operations using minimum operating airspeeds as are sometimes required (e.g. obstacle clearance, ATC constraints). In all cases, stall warning must be given precedence over climb RA commands. NOTE : TCAS is viewed as a supplement to the pilot who, with the aid of the ATC system, has the primary responsibility for avoiding mid-- air collisions. WARNING : Priority must be granted to increasing airspeed when reaching stall warning even when this requires deviation from an RA command issued by the TCAS. Mod 5948 2.01.06 LIMITATIONS P3 001 TCAS APR 11 AA TCAS (CONT’D) FLIGHT ENVELOPE IN WHICH CLIMB RESOLUTION ADVISORY CAN BE ACHIEVED WITHOUT STICK PUSHER / SHAKER ACTIVATION FLIGHT REGIME G WEIGHT ALTITUDE TEMP. POWER FLAPS GEAR Take off FAR25/CS25 Take off 15 Spin up to go around power during maneuver from power for level flight AIRSPEED INITIAL MIN. Up V2 + 20 1.13 VS1g 15 UP 1.51 VS1g 1.13 VS1g Spin up to go around power during maneuver from power required for 3° Glide Slope Transition from 30 to 15 DN to Up VAPP+10 1.13 VS1g Power for level flight increase to Max Continuous Up Up Long Range Cruise Higher of 1.13 VS1g if defined or buffet onset Climb limit Approach FAR25/CS25 Climb limit Landing Transitioning to go around at RA FAR25/CS25 Enroute Critical Wt/Alt Climb limit giving 1.3G to buffet onset Temperature range up to ISA + 27° Altitude range - Enroute - Take off - Approach and landing Wings Level Assumed Mod 5948 0 0 0 25000 ft 6000 ft 7000 ft 2.01.06 LIMITATIONS P4 TCAS 001 APR 11 AA TCAS (CONT’D) 8-- Inhibition schemes 8.1-- Non icing conditions CONFIGURATION RA CLIMB RA INCREASE CLIMB FLAPS 0 AUTHORIZED AUTHORIZED FLAPS 15 TO AUTHORIZED INHIBITED FLAPS 15 APPROACH AUTHORIZED AUTHORIZED FLAPS 30 AUTHORIZED INHIBITED CONFIGURATION RA CLIMB RA INCREASE CLIMB FLAPS 0 Z < 20000 ft AUTHORIZED INHIBITED FLAPS 0 Z > 20000 ft INHIBITED INHIBITED FLAPS 15 TO AUTHORIZED INHIBITED FLAPS 15 APPROACH AUTHORIZED INHIBITED FLAPS 30 INHIBITED INHIBITED 8.1-- Icing conditions N O TE 1 : NOTE 2 : Mod 5948 Pilots are authorized to deviate from their current ATC clearance to the extent necessary to comply with a TCAS resolution advisory. Maneuvers based solely on information displayed on the traffic display are not authorized. 2.01.06 LIMITATIONS P5 TCAS 001 APR 11 AA TCAS (CONT’D) NORMAL PROCEDURES The normal procedures in Part 2.03 are applicable. EMERGENCY PROCEDURES The emergency procedures in Part 2.04 are applicable. PROCEDURES FOLLOWING FAILURES The procedures following failures in Part 2.05 are applicable with the addition of the following: The TCAS must be turned TA ONLY in the following cases: - Engine out operations - Stick pusher/shaker failure - Flight with landing gear down The TCAS must be turned STBY in the following cases: - ATC request PERFORMANCES The performances in Part 3 are applicable. Mod 5948 . 2.01.07 LIMITATIONS FLIGHT MANAGEMENT SYSTEM FMS P1 001 APR 11 AA 1 -- GENERAL The FMS: - complies with TSO C 129 and TSO C115B, - is installed in compliance with, AC 20--130A for navigation use. - has been demonstrated to meet the En--route continental B--RNAV requirements of AMC 20--4 or equivalent in single GPS configuration. - has been demonstrated to meet the P--RNAV requirements of JAA TGL no10. - has been demonstrated to meet the RNAV (GNSS) non--precision approach requirement and RNP APCH AMC 20-- 27 specification in single GPS configuration. - APVBARO--VNAVoperations hadnot beendemonstrated andare notapproved. 2 -- LIMITATIONS Compliance with the above regulations does not constitute an operational approval/authorization to conduct operations. Aircraft operators must apply to their Authority for such an approval/authorization. - The FMS pilot’s guide must be available on board. - The approval of the system is based on the assumption that the navigation database has been validated for intended use. - In single GPS configuration, the system is approved for use for oceanic and remote operations when only one long range navigation system is required. - This system is approved for RNAV En--route continental (B--RNAV) and RNAV terminal area operations like RNAV SID/STAR (P--RNAV). NOTE : This system is approved in any of the following configurations: AP coupling, FD only or raw data (HSI information). - This system is also approved as a supplemental navigation means for conventional En--route continental operations, conventional terminal operations (SID/STAR) and conventional non--precision approach (e.g. NDB, VOR/DME, LOC,...) provided : S Approved navigation equipments, other than GNSS, required for the route to be flown are installed and operational. S When the system is used to fly non--precision approach not promulgated as RNAV (GNSS) approach or when procedure coordinates (SID/STAR, Approach) cannot be guaranteed as WGS84, raw data (conventional navigation information) are displayed to verify the correct RNAV (GNSS) guidance. .../... Mod : 5948 . 2.01.07 LIMITATIONS FLIGHT MANAGEMENT SYSTEM P 1A 001 FMS APR 11 AA 2 . 01 .07 -- FMS (CONT’D) - Single GPS configurations is approved for RNAV (GNSS) non--precision approach provided: SThe crew respects the published MDA (without VNAV (VDEV) credit) SThe published approach procedure is referenced to WGS84 coordinates or equivalent. SBefore starting the approach, crew checks GNSS is operating without GPS INTEG (on ND). SAPPR annunciation must be displayed in green on PFD for final approach. NOTE : Pilots intending to conduct an RNP APCH procedure must fly the full leg starting from IAF otherwise the system will not switch to APPR mode (RNP and EHSI scale will remain at 1NM) SRNAV (GNSS) non--precision approaches are performed only if a non--GNSS approach procedure is available at destination or at alternate destination. SRNAV (GNSS) non--precision approaches must be aborted in case of GPS INTEG on ND or UNABLE RNP on ND and/or GPS or RNP annunciator on MCDU affecting the RNAV (GNSS) used for guidance. SApproved navigation equipments, other than RNAV(GNSS), required for the approach to be flown (at destination and at any required alternate airport) are installed and operational. NOTE : ILS, LOC, LOC BC, LDA, SDF and MLS approaches are not covered. - APV BARO--VNAVpart of theRNAV(GNSS) systemis not approved and can only be used as advisory means. NOTE : VDEV function must be permanently cross--checked by conventional means (primary altimeters displays) - If GNSS must be used in oceanic/remote area, B--RNAV (if DME are not available), P--RNAV or for approach phases, the availability of the GPS integrity (RAIM or FDE functions) must be checked by the operator using prediction tool available in the GNSS during the pre--flight planning phase or any other approved tool. .../... Mod : 5948 . 2.01.07 LIMITATIONS FLIGHT MANAGEMENT SYSTEM FMS P 1B 001 FEB 12 AA 2 . 01 .07 -- FMS (CONT’D) R 2 -- LIMITATIONS (CONT’D) FMS predictions: Distance, time and fuel prediction deviations have been quantified as follows: S Climb: in the range ISA --20 to ISA +20, prediction deviations are lower than 10% and decrease to zero during climb . Outside this range, they could be greater than 10% and decrease to zero during climb. S Cruise: prediction deviations are lower than 5% in the whole environmental envelope. S Descent: prediction deviations are lower than 5% in the whole environmental envelope. 3 -- PROCEDURES FOLLOWING FAILURE - SINGLE GPS SFor RNAV (GNSS) non--precision approach, in the event of GPS INTEG illumination or if “UNABLE RNP” message occurs, perform a go around unless suitable visual reference is available. SIn case of loss of navigation or navigation degradation leading to the loss of the required navigation performance crew must inform ATC and revert to alternate navigation means. Mod : 5948 . 2.01.08 LIMITATIONS P1 CABIN LIGHTING 001 APR 11 AA The general cabin illumination system must be used during not less than 15 minutes before each flight. Mod : 5948 . 2.01.09 LIMITATIONS P 1 001 TAWS APR 11 TAWS 1. Navigation is not to be predicated on the use of the terrain display. Note : The Terrain display is intended to serve as a situational awareness tool only. It does not have the integrity, accuracy or fidelity on which to solely base decisions for terrain or obstacle avoidance. 2.To avoid giving nuisance alerts, the predictive TAWS functions must be inhibited when landing at an airport that is not included in the airport database. 3.The current local QNH must be entered in the Pilot’s altimeter for proper terrain alerting. 4.QFE operation is not permitted in conjunction with TAWS. Mod : 5948 . 2.01.10 LIMITATIONS P 1 COCKPIT DOOR SECURITY SYSTEM 200 APR 11 AA COCKPIT DOOR OPERATION : NORMAL PROCEDURES This procedure should be applied, if local authorities require that the cockpit door remain closed throughout the entire flight Before Pushback or engine start COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON COCKPIT DOOR CLOSED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK With the cockpit door toggle switch on CLOSE, the cockpit door is closed and locked. After Engine Start H If routine access is requested from the cabin : The buzzer sounds in the cockpit for at least 2 seconds Prior to unlocking the door, the flight crew should identify the person requesting entry. H If entry is not authorized by the flight crew : DOOR TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DENY Emergency access, the buzzer, and the Door Call Panel are inhibited for 3 minutes. H If entry is authorized by the flight crew : DOOR TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN The flight crew should pull the toggle switch and maintain it on the OPEN position, until the cabin crew opens the door. Note : If the flight crew does not take any action after the routine cabin request, the cabin crew will be able to open the door by using the emergency access procedure. H If the emergency access is initiated from the cabin : The buzzer sounds continuously in the cockpit for 30 seconds, and the OPEN light flashes on the central pedestal’s cockpit Door Control Panel. Note : If the flight crew does not take any action, the door will unlock after 30 seconds. H If entry is not authorized by the flight crew : DOOR TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DENY Emergency access, the buzzer, and the Door Call Panel are inhibited for 3 minutes. When the situation in the cockpit permits, the flight crew should identify the person requesting entry prior to unlocking the door. H If entry is authorized by the flight crew : DOOR TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN The flight crew should pull the toggle switch and maintain it on the OPEN position, until the cabin crew opens the door. Before leaving the aircraft COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FAULT LIGHT on Door Control Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Mod :5948 + 5465 2.01.10 LIMITATIONS P 2 COCKPIT DOOR SECURITY SYSTEM 200 APR 11 AA COCKPIT DOOR OPERATION : NORMAL PROCEDURES (cont’d) Daily Check - COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . . . ON On the DOOR CALL PANEL - EMER PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH - Check OPEN LIGHT flashes In the cockpit : - Check buzzer - Check OPEN LIGHT flashes H If correct : In the cockpit : - TOGGLE SW on COCKPIT DOOR CONTROL PANEL . . . . . . . . . . DENY - Check buzzer stops - Check OPEN LIGHT extinguishes On the DOOR CALL PANEL - Check OPEN LIGHT extinguishes and DENIED LIGHT illuminates H If correct : - TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN - COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . OFF - FUNCTIONAL CHECK OF THE MANUAL LOCK BOLT(S) Mod : 5948 + 5465 2.01.10 LIMITATIONS P 3 COCKPIT DOOR SECURITY SYSTEM 200 APR 11 AA COCKPIT DOOR OPERATION : PROCEDURES FOLLOWING FAILURE Electrical Power Lost - Move the manual lock bolt to CLOSE position - Note : when the door is locked with the manual bolt, the emergency access to the cockpit is unavailable. It is recommended that at least two crew members remain in the cockpit during that time. Cockpit Door Jammed S When cockpit exit required - Cockpit door locking system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - Remove the two locking pins (left hand edge, facing the door) - Disconnect the electrical plug from the top of the door - Push and remove corresponding door panel Cockpit Door Control Panel FAULT LIGHT illuminates - Move the manual lock bolt to CLOSE position - Note : when the door is locked with the manual bolt, the emergency access to the cockpit is unavailable. It is recommended that at least two crew members remain in the cockpit during that time. DC ESS BUS Lost - Apply Cockpit Door Control Panel FAULT LIGHT illuminates procedure - Note : Cockpit Door Control Panel FAULT LIGHT is inoperative. Mod : 5948 + 5465 2.01.10 LIMITATIONS P 4 COCKPIT DOOR SECURITY SYSTEM 200 APR 11 AA COCKPIT DOOR OPERATION : OPENING THE COCKPIT DOOR FROM THE CABIN CABIN CREW ROUTINE ACCESS . . . . . . . . . . . . . . . . . REQUEST on the Door Call Panel CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PRESS CALL PB CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STAND IN COCKPIT DOOR AXIS The cabin crew should stand in the axis of the cockpit door. A buzzer sounds in the cockpit. H If entry is not authorized by the flight crew : The flight crew denies the entry request via the DOOR TOGGLE SW. The Door Call Panel red light comes ON steady, and indicates that the door is locked. Emergency access, the buzzer, and the Door Call Panel are inhibited for 3 minutes. H If entry is authorized by the flight crew : The flight crew unlocks the door via the DOOR TOGGLE SW. The Door Call Panel green light comes ON steady, and indicates that the door is unlocked. CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . PULL the DOOR RIGHT PANEL to OPEN CABIN CREW . . . . . . . . . . . . . . . . . . . UNLOCK the LEFT PANEL and PULL to OPEN The door left panel is unlocked by moving the handle located in the cockpit side on the door left panel H If there is no reaction from the flight crew : CABIN CREW SECOND ACCESS REQUEST . . . . . . REQUEST on the Door Call Panel Repeat the above procedure. H If there is no reaction from the flight crew after a second request : CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CALL THE COCKPIT To establish contact with the flight crew and request access to the cockpit. H If there is no reaction from the flight crew after a cabin crew interphone call : CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PRESS THE EMERGENCY PB Rotate the protecting plate and press the EMER PB. A buzzer sounds continuously in the cockpit for 30 seconds, and the green light flashes on the Door Call Panel. After 30 seconds, the green light comes ON steady and the cabin crew can then pull the door right panel to open and the buzzer stops. This indicates that the door is unlocked for 10 seconds. CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . PULL the DOOR RIGHT PANEL to OPEN CABIN CREW . . . . . . . . . . . . . . . . . . . UNLOCK the LEFT PANEL and PULL to OPEN The door left panel is unlocked by moving the handle located in the cockpit side on the door left panel Mod : 5948 + 5465 2.02.00 PROCEDURES AND TECHNIQUES P1 CONTENTS 001 APR 11 AA 2.02.00 CONTENTS 2.02.01 OPERATING SPEEDS 2.02.02 DATA CARD 2.02.03 AIR 2.02.04 AFCS 2.02.05 ELECTRICAL SYSTEM 2.02.06 FLIGHT CONTROLS 2.02.07 FUEL SYSTEM 2.02.08 ADVERSE WEATHER 2.02.09 LANDING GEAR/BRAKES 2.02.10 FLIGHT PATTERNS 2.02.11 POWER PLANT 2.02.12 FLIGHT CHARACTERISTICS 2.02.13 Reserved 2.02.14 FLIGHT INSTRUMENTS 2.02.15 TCAS 2.02.16 TAWS 2.02.17 Reserved 2.02.18 FMS 2.02.19 HIGH LATITUDES OPERATIONS 2.02.20 Reserved 2.02.21 MPC Multi Purpose Computer 2.02.22 ACARS Aircraft Communication Addressing and Reporting System (*) 2.02.23 VIDEO CABIN SYSTEM (*) 2.02.24 DU, General Philosophy of use (*) : if installed Mod 5948 . 2.02.01 PROCEDURES AND TECHNIQUES P1 OPERATING SPEEDS 001 APR 11 AA GENERAL - Older certification rules used as a reference the minimum speed which was recorded during defined stall penetration. This speed was established with a load factor lower than 1g. It was used as reference for all operational speeds. (example V2 = 1.2 Vsmin, VREF = 1.3 Vsmin). - New certification now uses as a reference THE ONE G STALL SPEED VSR which is typically 6 % greater than Vsmin. - In order to provide the same practical maneuver margin, the factors applied to VSR have been changed to reflect the increased value of VSR relative to Vsmin. 1.2 applied to Vsmin becomes 1.13 when applied to VSR 1.25 applied to Vsmin becomes 1.18 when applied to VSR 1.3 applied to Vsmin becomes 1.23 when applied to VSR - The ATR 72-- 212A having been certificated to the new rules, the reference stalling speed called VSR is determined as a one G stall speed and the new (reduced) factors apply accordingly. Mod : 5948 2.02.01 PROCEDURES AND TECHNIQUES P2 OPERATING SPEEDS 001 FEB 12 AA DEFINITIONS VSR 1 g stall speed for a specified configuration. It is a function of the aircraft weight. VMCG Minimum control speed on the ground from which a sudden failure of the critical engine can be controlled by use of primary flight controls only, with the other engine operating at RTO power. V1 Speed at which the pilot can make a decision following failure of critical engine: . either to continue take-- off . or to stop the aircraft VR Speed at which rotation is initiated to reach V2 at 35 ft height. V2 Take off safety speed reached before 35 ft height with one engine failed and providing second segment climb gradient not less than the minimum (2.4 %). VMCA Minimum control speed in flight at which the aircraft can be controlled with 5° bank, in case of failure of the critical engine with the other engine at RTO power (take off flaps setting and gear retracted.) VMCL Minimum flight speed at which aircraft can be controlled with 5° bank in case of failure of the critical engine, the other being set at GA power (landing flaps setting, gear extended) and which provides rolling capability specified by regulations. VFE Maximum speed for each flaps configuration R Vmin OPS Minimal flight speed according to flying conditions and aircraft configuration. Mod : 5948 2.02.01 PROCEDURES AND TECHNIQUES P3 001 OPERATING SPEEDS APR 11 AA MINIMUM MANEUVER/OPERATING SPEEDS Minimum maneuver/ operating speeds are defined in order to provide sufficient margin against stall. They will vary with : - Normal or icing conditions, weight, configuration, type of maneuver (HI or LO BANK). They are defined by a minimum ratio to the appropriate stall speed given in FCOM 2.01.03 or by V2 when applicable. NORMAL CONDITIONS FLAPS VmHB 0 15 VmLB 1.18 VSR 1.23 VSR and not less than VMCL during approach 30 V2 Not used Note : Refer to 2.02.08 for icing conditions. UTILIZATION - VMLB is the absolute minimum maneuver speed. This speed * is used for take off, and initial climb. * must be used EN ROUTE FOR OBSTACLE LIMITED SITUATIONS (refer to chapter 3.09) * should be used in flaps 0 configuration to obtain the best climb gradient. In all these cases, bank angle must be restricted to 15° . - VmHB is the minimum speed used for approach. It also provides the best two engines rate of climb. In this case, bank angle must be restricted to 30° . The speeds and bank angles are automatically calculated by the FMS according to weight and atmospheric conditions and displayed on the PFDs. These speeds are also available in a pilot oriented manner as operating data booklet in the Quick Reference Handbook, in which relevant maneuver/operating speeds are directly given for all weights. Mod : 5948 2.02.01 PROCEDURES AND TECHNIQUES P4 OPERATING SPEEDS 001 FEB 12 AA CONSERVATIVE MANEUVERING SPEEDS When performance consideration does not dictate use of minimum maneuver / operating speeds, the following conservative maneuvering speeds are recommended. R They cover all weights, normal operational maneuver and flight conditions (normal and icing conditions) : Flaps 0 : 180 kt. Flaps 15 : 150 kt. Flaps 30 : 135 kt. FINAL APPROACH SPEED VAPP = VmHB + WIND FACTOR or VMCL, whichever is higher WIND FACTOR = The highest of - 1/3 of the head wind velocity, - or the gust in full, with a maximum wind factor of 15 kt. Wind factor is added to give extra margin against turbulence, risk of wind shear etc... GO AROUND SPEED VGA VmHB landing configuration + 5 kt or 1.1 VMCA, whichever is higher. MINIMUM SPEED FOR FLAPS RETRACTION It is VmLB of the next flap setting. Example : - Minimum speed to retract flaps from 15 to 0 : VmLB0. Mod 5948 2.02.02 PROCEDURES AND TECHNIQUES P1 DATA CARDS AA Mod : 5948 001 APR 11 . APR 11 Mod 5948 2.02.03 PROCEDURES AND TECHNIQUES P2 080 AIR FEB 12 AA AIR CONDITIONING When operating from airfields with high OAT, it is essential to cooldown the cabin before boarding passengers: this is best achieved by use of a ground conditioning unit, but may also be done through the use of Hotel Mode, and in that case the following R considerations will be applied : - as soon as OAT exceeds 22° C and aircraft has remained exposed to direct sun, PRE-- CONDITIONING becomes necessary for passengers comfort, prior to boarding; - allow a reasonable period of time for pre-- conditioning, and use up to MAXIMUM POWER AVAILABLE ON R/H ENGINE (GUST LOCK STOP) together with HI FLOW selection. Note 1: HI FLOW is very effective when R/H PL is advanced beyond Gl. Note 2: Proper orientation of the aircraft on Parking area (wind blowing from 10 o’clock ideally) during Hotel Mode pre--conditioning is very favorable as it gives better efficiency and allows to continue pre--conditioning during AFT CARGO loading (hot air from RH engine exhaust blown away from service door). - If for any reasons, it has not been possible to bring cabin temperature down to comfortable values prior to boarding, the following considerations will apply : ⋅ Packs operation during taxi should be performed with HI FLOW selected. ⋅ Switch FLOW selection to NORM prior to take-- off, but keep bleeds on, unless performance limited. ⋅ As soon as CLB POWER is selected after take off, select HI FLOW and maintain HI FLOW until comfortable cabin temp is obtained. ⋅ During cruise, monitor cabin temp when operating in NORM FLOW : if cabin temp tends to increase again above comfortable values, use HI FLOW as necessary. TEMP CONTROL Temperature control is normally achieved in AUTO MODE, which incorporates all necessary protections to avoid damage to packs turbines due to freezing. In case of duct overheating, manual mode is recommended. As manual mode does not incorporate the protections of AUTO MODE, the following R considerations must be applied: - Do not use temperature selector in manual mode unless auto mode is inoperative. - When in manual mode, monitor duct temperature and adjust rotary selector to maintain positive duct temp : this is essential to avoid pack freezing. Mod : 5948 + 3037 APR 11 Mod 5948 APR 11 Mod 5948 2.02.04 PROCEDURES AND TECHNIQUES P1 AFCS 001 FEB 12 AA GENERAL The ATR 72 with Mod 5948 is equipped with a Thales AutoPilot/Flight Director. Systematic use of AP/FD is recommended in order to : - Increase the accuracy of guidance and tracking in all weather conditions, from early climb after take off down to landing minima. - Provide increased passenger comfort through SMOOTH AND REPEATABLE altitude and heading changes in all atmospheric conditions. - Reduce crew workload and increase safety. MAIN RULES OF USE D AP and YD cannot be engaged on ground : any attempt to do it will result in the message “YD INHIB” on FMA; D FD is available on ground as soon as DC normal buses are powered, but FD bars are in sight only if : R - One upper mode is selected (Green indication on FMA). - FD ON/OFF push button on FGCP is ON. Note : Mod : 5948 - FD ON/OFF push buttons, one on Left side and one on Right side act only on FD DISPLAYS (FD Bars) Left push button allows selection/deselection on Left side only. Right push button allows selection/deselection on Right side only. - STBY push button on FGCP deactivates all active and armed upper modes. - If Auto Pilot is ON, Basic Mode with associated bars are displayed. 2.02.04 PROCEDURES AND TECHNIQUES P2 AFCS 001 APR 11 AA D The references to be flown may be coupled to left or right side by the CPL push button. Changes of CPL side while coupled to VOR, LOC, or LNAV will revert to basic mode. D Modes are engaged (green indication on FMA) or armed (Cyan indication on FMA) by action on the relevant push button on FGCP. FMA must be monitored for actual state of modes of AP/YD : A second push on the push button associated to a mode already engaged (or armed) disengages (or disarms) it and revert to basic mode. Lateral mode revert to ”Heading Hold”, Vertical mode revert to ”Pitch Hold” D ALT SEL mode is automatically armed as soon as the flight path is directed towards the altitude set on PFD via FGCP. All altitudes clearance given by ATC should systematically be set on PFD via FGCP to ensure automatic level off when AP is engaged (or FD followed in case of manual fliying). Note : After ALT mode has been engaged, the aircraft remains in level flight on the new barometric setting. D When HDG changes are performed with the HDG SEL mode active, maximum bank angle is automatically selected by the system. For all lateral modes, maximum bank angle is automatically selected by the system (15 if IAS<VmHB, 27° otherwise). This allows AFCS maneuvring in all conditions, including early climb after take-- off or go around where speed may be down to Vmin OPS (Vm LB). Mod : 5948 2.02.04 PROCEDURES AND TECHNIQUES P3 AFCS 001 APR 11 AA Note : Following engine failure, auto-- pilot may be used for climb at V 2 min only AFTER LATERAL TRIMMING HAS BEEN ACHIEVED. D LATERAL TRIM with auto-- pilot engaged - Trim on ROLL axis is inhibited when there is no RETRIM ROLL request set on FMA. - As there is no auto-- trim neither on ROLL nor YAW axis, it is the pilot task to maintain lateral trimming when speed or power is substantially changed. - The autopilot will indicate only roll/yaw out of trim. - If yaw trim is requested a message : ”RETRIM AIRCRAFT NOSE LEFT/RIGHT” is displayed on FMA, and on the yaw trim indicator a cyan arrow indicating in wich direction left/right trim is required. - If roll trim is required a message : ”RETRIM ROLL L(R) WING DOWN” is displayed on FMA, and on the roll trim indicator a cyan arrow indicating in wich direction (left/right) trim is required. - If excessive lateral trim increased and last, or AILERON MISTRIM message is displayed on FMA : ⋅ DISCONNECT AP, HOLDING FIRMLY THE CONTROLS. ⋅ FLY MANUALLY PRIOR TO ADJUSTING LATERAL TRIMS. ⋅ The auto pilot may be reengaged following adjustment of the lateral trims. D AUTO PILOT/YD DISCONNECT Auto pilot may be disconnected by : - Quick disconnect push buttons on each control wheel - Action on normal or STBY Pitch Trims - AP push button on FGCP - YD push button on FGCP - GA push buttons on Power Levers - Pilot input on left or right rudder pedals over 30 daN (66 lb) - Pilot input on the control column (push or pull on pitch axis) over 10 daN (22 lb) Yaw Damper and consequently AP, may be disconnected by : - YD push button on FGCP, - Pilot input on left or right rudder pedals over 30 daN (66 lb) - At touch down when landing. CAUTION : Overriding the Autopilot on roll axis will not lead to A/P disconnection. The QUICK DISCONNECT push button is recommended for all normal AP disengagement as it leaves the YD engaged. A second push on the QUICK DISCONNECT pb will also cancel both audio and visual AUTO PILOT OFF warnings. Depressing the TCS push-- button allows to regain temporary manual control of the aircraft without disconnecting the AP. Mod : 5948 2.02.04 PROCEDURES AND TECHNIQUES P4 AFCS 001 APR 11 AA Note : Function of AP/YD are monitored on three axes. When a monitored failure is detected, the AP/YD disengages and failure message is displayed on FMA (AP/YD invalid or AP invalid). A new re-- engagement is possible only if the failure message disappears. TYPICAL AP/YD operation D TASK sharing - With AP engaged, PF will select references and modes. - With FD only (AP not engaged) PF will call for references and modes to be set by PM. D BEFORE TAKE OFF - Both FD ON First cleared altitude set on PFD. HDG bug checked on RWY HDG. NAV Mode may be armed if SID is available in FMS. Pitch Mode selected and pitch Bar set to 8°. D TAKE OFF - As power is increased, lateral guidance FD bar remains centered as runway heading is maintained, and if LNAV was preselected, LNAV Mode becomes active at 20 kt. Vertical guidance FD bar stays at 8° - Rotation is initiated to the recommended value (θ኏8°) as indicated by FD vertical guidance bar. - As soon as gear is retracted and IAS>VminOPS , IAS MODE must be selected (on FGCP) plus SPEED BUG AUTO or MAN (on ICP) by PNF (SPEED BUG MAN mode may be used but SPEED BUG AUTO is recommanded) - 12 seconds after lift-- off, AP may be engaged : it synchronizes on FD command and maintains HDG or LNAV if selected and IAS (Temporary certification, 12 seconds equals to approximately 400 feet AGL at take off). - Turn may be initiated as required using HDG sel knob or according to LNAV Mode. - When acceleration altitude is reached, setting CLB Power according to standard climb procedure increases the speed Bug automatically to climb speed if in SPEED BUG AUTO Mode. If in SPEED BUG MAN Mode, the speed Bug must be set to required climb speed through the speed target selector on ICP. Mod : 5948 2.02.04 PROCEDURES AND TECHNIQUES P5 AFCS 001 APR 11 AA • CLIMB Use IAS mode with climb speed set through the speed target selector on the ICP. IAS should be preferred to VS mode, unless a vertical speed constraint is given by ATC. Note : If airspeed is not monitored during climb and VS mode is engaged with a rate exceeding the aircraft performance the airspeed will continuously decrease : AP will disengage automatically when stall alert is activated. CAUTION : When VS mode is used, monitor airspeed. • LEVEL OFF - Level off is automatic when reaching the selected altitude. - Power must be adjusted to the new condition. • RESUME CLIMB OR DESCENT - First, the new cleared altitude must be set on PFD. - For descent, engage IAS or VS mode. - For climb, engage preferably IAS mode. - In both cases, adjust power as necessary. Mod : 5948 2.02.04 PROCEDURES AND TECHNIQUES P6 AFCS 001 APR 11 AA D NAVIGATION HDG and NAV mode for VOR approach are used as required (Refer to FCOM 1.04) Note : - Accuracy of VOR guidance is significantly improved when there is a DME associated with the VOR. Accuracy decreases if NAV VOR is engaged in DME HOLD mode. D ILS approach mode Before approach : - Select V/ILS source (on FGCP) on coupled (CPL) side. Set approach course on HSI with CRS selector and tune ILS frequency. Use HDG SEL mode to set appropriate intercept heading. Arm both LOC and GS by depressing APP pb on FGCP. Set SPEED BUG AUTO mode (SPEED BUG AUTO Mode is recommended as much as possible, nevertheless SPEED BUG MAN Mode may be used) Note : - LOC beam capture must be started (LOC* green on FMA before GS capture can take place). - LOC beam capture may lead to one initial overshoot when the capture conditions are severe (Intercept Heading = RWY HDG ¦ 90°, high IAS, reduced distance to the ILS transmitter), but, provided the distance is at least 5 Nm at the standard instrument capture speed of 180 Kts, this initial overshoot will be followed by an asymptotic capture without further oscillation, even with a 90° intercept angle. - The bank angle limit is automatically set following speed versus VMHB (15° or 27°). - When LOC capture is started: Set RWY HDG with HDG bug Set ILS frequency and set/check V/ILS source (on FGCP) on PM side, check ILS course on PM side - When GLIDE beam capture (G/S* green on FMA): First Check glide validity (according approach chart) Set Go around altitude Mod : 5948 2.02.04 PROCEDURES AND TECHNIQUES P7 001 AFCS APR 11 AA D NON PRECISION APPROACH Use of auto-- pilot is recommended with : - NAV mode for VOR or GNSS approach or LOC, - HDG SEL mode for NDB approach, - VS or IAS mode for descent. D GO AROUND When reaching decision height, or missed approach point after level off at MDA, if required visual references are not established, a go-- around must be initiated. The following procedure is recommended : - PF (if no visual reference) Announce”GO AROUND, FLAPS ONE NOTCH, SET POWER” Depress GA pbs on PLs Advance PLs to the ramp Rotate to GO AROUND pitch attitude Follow FD bars and cancel AP Disconnect Alarm Accelerate to or maintain VGA (2-- 02-- 01 p4) - Command “GEAR UP“ When climb is stabilized : - Command “HDG/IAS“ Engage AUTO PILOT PM - Announce “Minimum” - Retract FLAPS one notch - Check NP= 100 %, adjust if necessary When positive rate of climb is achieved : - Announce “Positive rate” - Set gear up - Engage HDG and IAS MODE on FGCP (if in IAS MODE+SPEED BUG AUTO mode IAS Bug is automaticaly set to Go Around speed If in IAS mode+SPEED BUG MAN mode, IAS Bug must be set manualy to Go Around speed) Note : GO AROUND mode gives (as a FD mode only): - on pitch axis, a target attitude compatible with single engine performance. - on roll axis, a steering command to maintain heading followed at GA engagement or the FMS flight PLAN if LNAV was previously engaged. As soon as climb is firmly established, and IAS>VminOPS use of HDG SEL / IAS MODE+ Speed AUTO mode is recommended. Mod : 5948 2.02.04 PROCEDURES AND TECHNIQUES P8 AFCS 001 APR 11 AA CAT 2 OPERATIONS " GENERAL CAT 2 approaches are flown with AP + FD ON. " EQUIPEMENT REQUIRED Approach with AP Autopilot 1 COURSE rotary selector 2 AP quick disconnect 1 (PF side) AP OFF warning (aural) 1 ILS receiver 2 AHRS 2 IESI 1 PFD 2 Radio altimeter 1 (with 2 displays) DH indicator 2 GA pushbutton 1 (PF side) Windshield wipers 1 (PF side) Yaw damper 1 ADC 2 Hydraulic system Blue + Green Electrical system DC: BUS1 / BUS2 / EMER / STBY / ESS ; AC: BUS1 / BUS2 / STBY ; ACW: BUS1 / BUS2 MFC modules 3 Mod : 5948 2.02.04 PROCEDURES AND TECHNIQUES P9 AFCS AA 001 APR 11 Maximum demonstrated crosswind: AutoPilot Headwind 29 kt Tailwind 10 kt Crosswind 17 kt " TASK SHARING The philosophy of the task sharing is based on the following considerations: - PF(!) task is aircraft flying during all the approach, he is in charge of speed control. Approaching DH + 100ft, he looks outside to acquire visual references. He makes decision for landing or go-- around. - PM (@) task is approach monitoring with permanent reference to the instruments. (!)PF, pilot flying, - Monitors the A/C position, the flight path parameters and the AP. - Controls the speed. - Requests checklist, flaps setting and gear extension. - Selects the modes and announces changes. (@)PM, pilot monitoring, - Is in charge of radio communications. - Monitors the flight path, the speed, the mode changes, the systems and the engines. - Reads the checklist. - Selects flaps setting and gear extension. " NORMAL APPROACH AND LANDING SEQUENCE J Prior to approach D BEFORE DESCENT, DESCENT, APPROACH AND BEFORE LANDING PROCEDURES : SEE NORMAL PROCEDURE ... / ... Mod 5948 2.02.04 PROCEDURES AND TECHNIQUES P 10 001 AFCS AA J APR 11 Before capture D PF has to perform the following tasks: - NAVAIDS set to ILS frequency, ADF set as required. - CRS set to final approach course. - APP armed. - SPEED BUG AUTO mode recommanded. D PM has to perform the following task: - NAVAIDS and ADF set as required From capture to decision height Note: The call-- outs are written in bold with “ ...”. Tasks and callouts CAT 2 events PF J Localizer capture Glide slope capture “LOC STAR” - Set runway HDG - Set ILS freq - Set/check V/ILS source (on FGCP) - Set/check ILS CRS - Check CAT 2 on FMA “GS STAR” Set GA altitude Check GA altitude Request normal sequence for LDG configuration (!): Outer marker Check altitude on RA and altimeter, or equivalent posi- and if aircraft is stabilized tion (not lower “WE CONTINUE” than 1000ft) 800 ft RA (#) Check dual coupling and no star on LOC and G/S modes “CHECK” 500 ft RA DH + 100 ft RA PNF Set LDG configuration in sequence “OUTER (!) ALTITUDE CHECKED, STABILIZED(@)” Check altitude on RA and altimeter and if aircraft stabilized “800 FT, DUAL CPL, NO STAR“ Check dual coupling and no star on LOC and G/S modes “500” Looks outside for visual references DH / auto call-- out “100 ABOVE” Monitors the instruments “DECISION” (@): Stabilized means: - On the final approach segment flight path. - Landing flaps selected, VAPP reached. - Final checklist completed. (#): Any failure that is not completely treated before 800ft AGL, or that occurs below 800ft AGL shall always lead to a missed approach. Mod. : 5948 2.02.04 PROCEDURES AND TECHNIQUES P 11 AFCS 001 APR 11 AA J If visual references sufficient Tasks and callouts CAT 2 events Visual at DH 80 ft RA PF PM “LANDING” Disconnect AP 50 ft RA “80” 80 “50” 20 ft RA “20” Reduce PL and flare J Mod : 5948 If visual references insufficient, apply GO AROUND NORMAL procedure. (2.03.20) 2.02.04 PROCEDURES AND TECHNIQUES P 12 AFCS 001 APR 11 AA D If APP P/B is engaged without an ILS frequency tuned on the coupled side, the APP mode will not arm and the FMA will display a caution message : “CHCK NAV SRC”. In this case, tune ILS and reengage APP mode. D As soon as LOC“*” mode is displayed, the approach capability (as seen by the AFCS computer), will be displayed on FMA (CAT I or CAT II). D TRACK phase, for both LOC and GS (indicated by LOC and GS green without *)take place automatically when the aircraft is on the beam. The transition to DUAL CPL intervenes at 1200ft. The standard deceleration procedure described above, normally allows to reach 800 ft RA after LOC and GS TRACK phases have been achieved. If it is not the case (excessive initial speed, etc.), new proper capture has to be made. If late capture, the dual coupling engagement is impossible. D Excess deviation is armed : - below 300 ft for LOC - between 300 ft and 100 ft for GS. Any excess deviation appearance must be announced by PM (call “DEVIATION”). This call must lead to : - AP disconnection by PF - Go around decision if visual references are not sufficient. D AP/FD behaviour must be permanently monitored by PM. In case of anomaly (sustained input not justified by LOC and GS deviations , excessive attitude*), the PM must immediately call “ GUIDANCE ”. This call must lead to : -- AP disconnection by PF - Go around decision if visual references are not sufficient. * excessive attitude means bank angle > 10° pitch attitude < --4° > +4° - In case of “GUIDANCE” or “DEVIATION” callout by PM, (or AP disconnection without visual references), a Go Around must be performed. If no discrepancy is detected on PFD (CHECK ATT messages) PFD can be used with IESI monitoring to set the initial missed approach attitude. Mod : 5948 APR 11 Mod 5948 APR 11 Mod 5948 Mod 5948 2.02.06 PROCEDURES AND TECHNIQUES P1 FLIGHT CONTROLS 001 APR 11 ATR 72 is equipped with classical mechanical primary flight controls on all three axis. The following peculiarities must be highlighted : Mod 5948 2.02.06 PROCEDURES AND TECHNIQUES P2 FLIGHT CONTROLS 001 APR 11 AA PITCH : Both elevators are connected through a pitch uncoupling device, in order to leave sufficient controllability in case of mechanical jamming of one control surface. Activation of this device : - requires heavy forces (52 daN/114 Ibs) to be applied to the control columns, which minimizes the risk of untimely disconnection. - indicated to the crew through the red warning « PITCH DISC » on the EWD. - allows the flight to be safely achieved : refer to procedures following failures. Note 1 : WHEN PITCH DISCONNECT takes place WITHOUT REAL JAMMING, speed has to be limited to 180 kt and bank angle to 30° until flaps extension to avoid overstressing the stabilizer. Note 2 : The TWO yokes must be held once the aircraft is landed. Once disconnected both elevators can be reconnected by applying the following procedure: BOTH ELEVATORS RECONNECTION ON GROUND Conditions: - Aircraft on ground and electrically powered. - Both elevators disconnected. - Red PITCH DISC alarm illuminated steady on EWD. Procedure: - Engage GUST LOCK and check both columns are locked. - Depress and hold ELEV CLUTCH guarded pb (see 1.09.30) until PITCH DISC flashes red on EWD. - Release ELEV CLUTCH pb. After a few seconds, PITCH DISC extinguishes on EWD. - Check both columns are effectively coupled. Mod. :5948 2.02.06 PROCEDURES AND TECHNIQUES P3 FLIGHT CONTROLS 001 APR 11 ROLL : D Aileron spring tabs : Flight controls are connected to the ailerons through the spring tabs, therefore, maintaining the flight controls to neutral on the ground would not prevent the ailerons from oscillating in case of strong tail wind (> 30 kt). Therefore, in strong wind conditions it is recommended : - to disengage the gust lock only when necessary before take off, - after landing, to engage the gust lock before a turn that would expose the aircraft to a tail wind component. If aileron lock is not available, it is easier to maintain the ailerons fully deflected. D Aileron trim : Ailerons forces trimming is obtained by shifting the zero position of the left aileron spring tab : this means that AILERON TRIM INDICATOR is only representative of the differential loading of the spring tab and not of the aileron position. Mod. : 5948 2.02.06 PROCEDURES AND TECHNIQUES P4 FLIGHT CONTROLS 001 APR 11 YAW: The rudder incorporates several particular features. D The releasable centering unit (threshold cam) : This threshold cam automatically synchronizes to actual rudder pedal position each time the rudder trim switch is activated. Therefore before take-- off, rudder trim setting to zero must be made with rudder pedals in neutral position. D The rudder surface damper : Structural protection of the rudder assembly against effect of wind gusts on ground is ensured by a rudder surface damper, which is designed to prevent excessive speed of deviations of the rudder surface. When taxiing with strong winds, very large rudder forces would be required to control the rudder surface: this is not necessary and rudder should be left « floating » in the wind as the damper will effectively prevent any structural damage. D The rudder trim : Rudder forces trimming is obtained by shifting the zero position of the spring tab: this means that « RUDDER TRIM INDICATIONS » are only representative of the differential loading of the spring tab, AND NOT OF THE RUDDER POSITION. Note : As speed increases, rudder trim deviation as large as 3 dots on the right may be noted while rudder surface remains substantially at neutral. D The yaw damper : Yaw damper function is provided through the YAW CHANNEL of the AP and should always be engaged in flight to improve passenger comfort. The yaw damper provides in addition a sideslip cancellation function: its goal is to keep the side slip indication centered. This can produce sustained rudder input, which can lead to the display of a RETRIM NOSE LEFT or RETRIM NOSE RIGHT message on FMA, and an arrow on the rudder trim indicator. In this case, the crew has to act manually on the rudder trim in the displayed direction until the message disappears, in order to reduce the effort sustained by the rudder actuator. If the input required by the yaw damper is too important (more than 15daN/33lbs at rudder pedals level), the command will be saturated, and the lateral acceleration will be released (the side slip indicator will not be centered). In some cases (engine failure), the yaw damper can disconnect automatically. If the system detects a too important effort (more than 15daN/33lbs) the message RUDDER MISTRIM will be displayed on the FMA, and a caution will be triggered by the FWS. The procedure is to hold firmly the commands, and disconnect the AP/YD. After lateral trimming, AP/YD can be engaged again. In order to let the rudder axis free for pilot inputs (engine failure) without the need to disconnect the YAW DAMPER on the FGCP, a force sensor has been implemented and any pilot force exceeding 30 daN/66 Ibs applied on rudder will cause the YD disengagement. Mod 5948 2.02.06 PROCEDURES AND TECHNIQUES P5 FLIGHT CONTROLS 001 APR 11 AA In order to avoid exceeding structural loads on the rudder and vertical stabilizer, the following recommendations must be observed. 1) THE RUDDER IS DESIGNED TO CONTROL THE AIRCRAFT, IN THE FOLLOWING CIRCUMSTANCIES: a) In normal operations, for directional control - During the takeoff roll, especially in crosswind condition. - During landing flare with crosswind, for decrab maneuver. - During the landing roll. - The rudder may be used as deemed necessary, for turn coordination to prevent excessive sideslip. b) To counteract thrust asymmetry Full rudder authority can be used to compensate for the yawing moment of asymmetric thrust. Note : at high speed (i.e. flaps up), thrust asymmetry (i.e. due to an engine failure) has relatively small effect on lateral control of the aircraft. The amount of rudder required to counter an engine failure and center the sideslip is small. c) In some other abnormal situations The rudder may also be used in some abnormal situations such as: - Runaway rudder trim. The rudder pedals may be used to return the rudder to neutral. - Aileron jam. The rudder may be used to smoothly control the roll. - Landing gear unsafe indication (gear not downlocked). When a main landing gear is not downlocked, the rudder may be used to establish sideslip in an attempt to downlock the landing gear by aerodynamic side forces. - Landing with landing gear not downlocked. The rudder can be used for directional control on ground. In all these normal or abnormal circumstances, proper rudder maneuvers will not affect the aircraft’s structural integrity. 2) RUDDER SHOULD NOT BE USED: - To induce roll, except in the previous case( Aileron jam) or - To counter roll, induced by any type of turbulence. Whatever the airborne flight condition may be, aggressive, full or nearly full, opposite rudder inputs must not be applied. Such inputs can lead to loads higher than the limit, or possibly the ultimate loads and can result in structural damage or failure. Note : Rudder reversals must never be incorporated into airline policy, including so-- called “aircraft defensive maneuvers” to disable or incapacitate hijackers. As far as dutch roll is concerned, yaw damper action (if selected) or RCU (Releasable Centering Unit) are sufficient to adequately dampen dutch roll oscillations. The rudder should not be used to complement the yaw damper action. Mod 5948 . 2.02.07 PROCEDURES AND TECHNIQUES P1 FUEL SYSTEM 001 APR 11 AA FUEL CROSSFEED Allows feeding of 1 or 2 engines from either side tank, especially for fuel balancing. PROCEDURE : Intended tank to be used : PUMP RUN and OFF LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . extinguished X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN LINE Opposite tank : PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF When asymmetrical feeding is completed: PUMPS both . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . X LINE R Note: R R R R R R Each electrical pump is able to supply one engine in the whole flight envelope. One electrical pump and associated jet pump are able to supply both engines in the whole flight envelope. When X FEED is selected « in line », both electrical pumps are forced to run (both RUN lights illuminate green) as long as associated PUMP pb is selected ON. CAUTION : When X FEED procedure is applied, some fuel transfer from the wing tank where the pump is running to the other wing tank (where the pump is OFF) may occur. This transfer is particularly noticeable at low power settings (X FEED in Hotel mode is the worst case). FUEL QUANTITY INDICATIONS IN FLIGHT Accurate readings require aircraft levelled without side slip and pitch attitude close to zero degree. ON GROUND Accurate readings should be made with aircraft static (not taxiing) and fuel pumps running for more than 4 minutes. This procedure should be applied each time a comparative reading before and after flight is intended with correlation to fuel used. COMMENTS - Fuel quantity indications are affected by excessive longitudinal and lateral attitudes and accelerations. - Fuel quantity indications are affected by the level of fuel in the feed tank. With pumps running, the feed tanks are filled within a few minutes. This is the normal flight case. Mod 5948 . 2.02.08 PROCEDURES AND TECHNIQUES P1 ADVERSE WEATHER 001 APR 11 This chapter is divided in 4 parts : - Icing - Cold weather operations, - Operations in wind conditions. - Volcanic Ash encounter ICING I - GENERAL Icing conditions are defined as follows : " Atmospheric icing conditions Atmospheric icing conditions exist when OAT on ground and for take-- off is at or below 5°C or when TAT in flight is at or below 7°C and visible moisture in the air in any form is present (such as clouds, fog with visibility of one mile or less, rain, snow sleet and ice crystals). " Ground icing conditions Ground icing conditions exist when the OAT is at or below 5°C when operating on ramps, taxiways and runways where surface snow, standing water or slush is present. " Regulatory requirements Certification requirements defined in JAR/FAR 25 appendix C consider droplet sizes up to 50 microns in diameter. No aircraft is certified for flight in conditions with droplets larger than this diameter. However, dedicated flight tests have linked unique ice accretion patterns to conditions of droplet sizes up to 400 microns. Procedures have been defined in case of inadvertent encounter of severe icing. " Organization of this subchapter It will address the following areas : D Operations within the certified envelope. D Information about severe icing beyond the certified envelope. D Good operating practices. Mod 5948 APR 11 (duplicated on the FMA). Accordingly, the minimum maneuver / operating speeds defined for normal (no icing) conditions (refer to FCOM 2.02.21) will automatically be increased and must be respected as long as “ICING AOA” is illuminated. These new minimum speeds are called “MINIMUM ICING SPEEDS”. They are defined further in paragraph B. Mod: 5948 APR 11 Mod 5948 2.02.08 PROCEDURES AND TECHNIQUES P4 001 ADVERSE WEATHER APR 11 AA B) MINIMUM ICING SPEEDS - The minimum maneuver/operating speeds defined for normal conditions (2.02.01) MUST BE INCREASED and the new value enforced whenever ICE ACCRETION is possible (FIight in atmospheric icing conditions), or exists (ice accretion developing or residual ice). They are defined by the following table where VSR is the non affected 1G stall speed as given in 2.01.03. FLAPS VmHB VmLB 0 1.46 VSR 1.40 VSR 1.22 VSR T/O - 2d segment 15 1.35 VSR 1.27 VSR Final Take-- Off 1.30 VSR EN ROUTE 1.24 VSR GO AROUND 30 1.32 VSR CAUTION : For obstacle clearance, the en-- route configuration with engine failure is FLAPS 15° at a minimum speed of 1.30 VSR if ice accretion is observed. - Relevant MINIMUM ICING SPEEDS are displayed on the PFD as soon as the ”ICING AOA” is illuminated (refer to 1.10.22). The icing speeds can be found for reference in the Quick Reference Handbook for all weights. Mod 5948 APR 11 (ICING on FMA + MC + SC + ICING amber on EWD) Mod 5948 2.02.08 PROCEDURES AND TECHNIQUES P6 ADVERSE WEATHER 001 APR 11 AA E) PROCEDURES IN ATMOSPHERIC ICING CONDITIONS During operations with AP ON during climb and descent, vertical speed mode should not be used unless the airspeed is carefully monitored. The recommended procedure is to use IAS mode with a speed selected which is equal to or greater than the appropriate minimum speed (VmLB or VmHB). If the selected speed is below VmHB, the autopilot will automatically limit the bank angle to 15°. CAUTION : Close attention should be paid to the appearance of an AILERON MISTRIM message flashing on the FMA and EWD: if the message appears, apply the AILERON MISTRIM procedure. Note : Permanent heating (Probes/windshield) is Always selected ON. ENTERING ICING CONDITIONS S ANTI ICING (PROP - HORNS - SIDE WINDOWS) . . . . . . . . . . . . . . . . . . ON Note : horns anti icing selection triggers the illumination of the “ICING AOA” green light and green display on FMA, and lowers the AOA stall warning threshold. S MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Confirm AUTO S MINIMUM Maneuver/Operating ICING SPEED . . . . . . . . . . . . . OBSERVED S ICE ACCRETION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR Note : 1.These procedures are applicable TO ALL FLIGHT PHASES including take off. Mod : 5948 2.02.08 PROCEDURES AND TECHNIQUES P7 ADVERSE WEATHER 001 APR 11 AA AT FIRST VISUAL INDICATION OF ICE ACCRETION, AND AS LONG AS ATMOSPHERIC ICING CONDITIONS EXIST F ANTI ICING (PROP - HORNS - SIDE WINDOWS) . . . . . . . . . . . . Confirm ON F MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Confirm AUTO F ENG DE ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON F AIRFRAME DE ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON F MINIMUM Maneuver/Operating ICING SPEED . . . . . . . . . . . . . OBSERVED BE ALERT TO SEVERE ICING DETECTION. In case of severe icing, refer to 2.04.05. F Notes:1. When ice accretion is visually observed, DE ICERS MUST BE SELECTED and maintained ON as long as icing conditions exist. 2. The ice detector may not detect certain ice accretion form (see FCOM 1.13.20). 3. If a noticeable performance decrease and (or) significant vibrations occur due to propeller residual icing then, in order to improve the deicing of the blades, it is recommended : D To check that the MODE SEL is AUTO, or that the MAN mode is selected in accordance with SAT. D To set CLs on 100 OVRD for continuous periods of not less than 5 minutes in order to benefit from an increased centrifugal effect. 4. If ice accretion is seen by the detector with HORNS ANTI ICING and/or AIRFRAME DE ICING still OFF, the ICING label will flash until corrective actions are taken. 5. Engines de-- icing must be selected ON prior to airframe de-- icing to take benefit of an immediate engines de-- icing. If not, engines de-- icing will be effective 60 or 240 seconds later depending on MODE SEL selection. Mod : 5948 2.02.08 PROCEDURES AND TECHNIQUES P8 ADVERSE WEATHER 001 APR 11 AA WHEN LEAVING ICING CONDITIONS DE ICING and ANTI ICING may be switched OFF. Note : Leaving DE ICING in operation UNNECESSARILY is detrimental to boots life. AIRFRAME cyan message is displayed flashing when the airframe deicing system is still selected on five minutes after last ice accretion detection. WHEN THE AIRCRAFT IS VISUALLY VERIFIED CLEAR OF ICE ICING AOA caption may be cancelled and normal speeds used. Note : Experience has shown that the last part to clear is the ice evidence probe. As long as this condition is not reached, the icing speeds must be observed and the ICING AOA caption must not be cancelled. Mod : 5948 001 APR 11 Mod 5948 2.02.08 PROCEDURES AND TECHNIQUES P 10 ADVERSE WEATHER AA 001 APR 11 G) SUMMARY DEFINITIONS : . ICING CONDITIONS : See Definition page 1. There is a risk of ice accretion. . ICE ACCRETION : Ice is building up on the airframe. ICING amber light illuminates and flashing yellow ICING message is displayed on the FMA. . RESIDUAL ICE : Some ice is remaining on the airframe. May be in or out of icing conditions. Mod : 5948 A APR 11 Mod : 5948 2.02.08 PROCEDURES AND TECHNIQUES P 12 ADVERSE WEATHER 001 APR 11 AA 3) Mixed icing condition Mixed icing condition may be encountered in the range of temperatures - 10°C/0°C. It is basically an unstable condition, it is extremely temperature dependent and it may change quite rapidly. This condition may surpass the ice protection capabilities because the aggregate of impinging ice crystal/snow and water droplet can adhere rapidly to the airframe surpassing the system capabilities to shed ice, causing significant reduction in airplane performance as in case of system failure. C) CONSEQUENCES OF SEVERE ICE ACCRETION The consequences of severe ice accretions are ice location dependent. If the pollution extension occurs on the lower surface of the wing, it increases the drag and the airplane speed decreases. It may lead to stall if no action is taken to recover a correct speed. If the pollution occurs first on the upper part of the wing, the drag is not affected noticeably but controllability anomalies may be encountered. Severe roll anomalies may be encountered with ”flaps 15” accretions flown with flaps 0 setting. It should be emphasized that it is not the flaps 15 configuration itself that is detrimental, but the low angle of attack that may result from such a setting, especially close to VFE. This low or negative AOA increases the wing upper side exposure to large droplet impingement. This is why holding with any flaps extended is prohibited in icing conditions (except for single engine operations). ... / ... Mod 5948 2.02.08 PROCEDURES AND TECHNIQUES P 13 ADVERSE WEATHER 001 APR 11 AA D) DETECTION - During flight, severe icing conditions that exceed those for which the airplane is certificated shall be determined by the following : Severe icing is characterized by ice covering all or a substantial part of the unheated portion of either side window, Note : This cue is visible after a very short exposure (about 30 seconds). and / or Unexpected decrease in speed or rate of climb, and / or The following secondary indications : . Water splashing and streaming on the windshield. . Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice. . Accumulation of ice on the lower surface of the wing aft of the protected areas. . Accumulation of ice on the propeller spinner farther aft than normally observed. - The following weather conditions may be conducive to severe in-- flight icing : . Visible rain at temperatures close to 0°C ambient air temperature (SAT). . Droplets that splash or splatter on impact at temperatures close to 0°C ambient air temperature (SAT). - The occurence of rain when SAT is below freezing temperature should always trigger the alertness of the crew. EXIT THE SEVERE ICING ENVIRONMENT There are no regulatory requirements to certify an aircraft beyond CS/FAR 25 Appendix C. However, in case of inadvertent encounter with such conditions “severe icing“ procedure must be applied (refer to 2.04.05). Mod 5948 APR 11 Mod 5948 2.02.08 PROCEDURES AND TECHNIQUES P 15 ADVERSE WEATHER 001 APR 11 AA IV - GOOD OPERATING PRACTICES Aircraft certification requirements describe the icing conditions likely to be encountered in commercial aviation. However, as demonstrated by experience, icing remains one of the major causes of incidents and accidents, and good airmanship prohibit any complacency in this area. The following basic rules should therefore be applied : " Know as much about your operating environment as you can. Carefully review weather packages for Pilot reports of icing conditions, tops reports, temperatures aloft forecasts and forecasts of icing, freezing drizzle and freezing rain. Monitor both Total Air Temperature and Static Air Temperature during climb and while en route. Use the weather radar. Areas of precipitation which will paint on the radar will be of sufficient droplet size to produce freezing rain when encountered in freezing temperatures or on a cold soaked aircraft. " Marginal freezing temperatures and icing conditions should create a heightened state of awareness. Remember, severe ice can still be incurred at temperatures down to approximately - 18° C, at high altitude. " Be alert to severe icing cues defined pages 12/13. " When severe icing is encountered, take appropriate steps to leave the conditions. Since these unique conditions are usually small in area and associated with very specific temperatures conditions, a change in altitude of just a couple thousand feet may place you in a totally different environment. " Make reports to ATC and Company. There is no better operational tool available today than first hand reports of these conditions. Remember that because these are localized areas and extremely temperature dependent, another aircraft passing through the same area at a different airspeed may experience different conditions. For example, a laboratory test showed for a specific, yet normal condition, rime ice up to about 150 kt, mixed ice as speed was increased to about 200 kt, glaze ice between 200 and 360 kt, and no accretion above 360 kt. Note : Reporting of icing conditions as defined in the FAA’s Airman’s information Manual (AIM) : Trace : Ice becomes perceptible. Rate of accumulation is slightly greater than the rate of sublimation. It is not hazardous even though de-- icing/anti - icing equipment is not utilized unless encountered for an extended period of time (over 1 hour). Light : The rate of accumulation may create a problem if flight is prolonged in this environment (over 1 hour). Occasional use of de-- icing/anti - icing equipment removes/prevents accumulation. It does not present a problem if the de-- icing/anti - icing equipement is used. Moderate : The rate of accumulation is such that even short encounters become potentially hazardous and use of de-- icing/anti - icing equipment or flight diversion is necessary. Severe : The rate of accumulation is such that de-- icing/anti - icing equipment fails to reduce or control the hazard. Immediate flight diversion is necessary. Mod 5948 FEB 12 Mod 5948 2.02.08 PROCEDURES AND TECHNIQUES P 17 ADVERSE WEATHER 001 FEB 12 AA CAUTION : Wing, tailplane, vertical and horizontal stabilizers, all control surfaces and flaps should be clear of snow, frost and ice before take off. PARTICULAR CASE : limited frost accretion on lower wing surfaces due to cold fuel remaining and high ambient humidity. As stated in the operational requirements, no person may take off an aircraft when frost snow or ice is adhering to the wing, control surfaces or propeller of the aircraft. FROST : frost is a light, powdery, crystalline ice which forms on the exposed surfaces of a parked aircraft when the temperature of the exposed surfaces is below freezing (while the free air temperature may beabove freezing). Frost degrades the airfoil aerodynamic characteristics. However, should the take off be conducted with frost adhering to the lower surface of the wing, check the following : - The frost is located on the lower surface of the wing only. - Frost thickness is limited to 2 mm. - A visual check of the leading edge, upper surface of the wing, control surfaces and propellers is performed to make certain that those surfaces are totally cleared of ice. - Performance decrement and procedures defined for take off in atmospheric icing conditions are applied. " DE ICING / ANTI ICING PROCEDURE - External de-- /anti-- icing will be performed as close as possible from take-- off time in order not to exceed the hold over time. Type 1 (low viscosity) or type 2/4 (high viscosity) fluids are used for these operations. The type 2/4 fluids are used for their anti icing qualities. As airflow increases the fluid is spread through the elevator gap and over the lower surface of the elevator. Depending on the brand of the fluid and the OAT, this phenomenon may temporarily change the trim characteristics of the elevator by partially obstructing the elevator gap. This may lead to a considerable increase in control forces necessary to rotate. This effect is most pronounced when center of gravity is forward. - To ensure the best possible tailplane de-- /anti-- icing, all along the fluid spraying, the control columns must be firmly maintained on the forward stop together with the aileron gust lock engaged. - De-- /anti-- icing may be performed in Hotel mode provided BLEEDS are selected OFF. If a de icing gantry is used, both engines must be shut down. For manual propeller de icing, the engines must be shut down and air intake blanked or precaution taken not to have de icing fluid in the air intake. No propeller blade should be located at 6 o’clock position during this procedure. Mod 5948 FEB 12 ENG1(2) OIL PRESS Mod 5948 Mod: 5948 2.02.08 PROCEDURES AND TECHNIQUES P 19 ADVERSE WEATHER 001 FEB 12 AA " TAXIING - The standard single engine TAXI procedure may still be used provided the friction coefficient remains at or above 0.3 (braking action medium, snowtam code 3) and nose wheel steering is not used with too large deflections. Note : If the OAT is very low, it may be necessary any way to start up engine 1 early enough to get the necessary oil warm up time (refer to Note (3) above). - For taxiing with the very low friction coefficients (icy taxiways, slush), it is recommended to use both engines, limit nose wheel travel and use with differential power as necessary. SPECIAL CASE If contaminant layer is significant enough to possibly accumulate in the brake area during ground operation, brakes disks may join due to icing during the flight, leading to possible tyres damages at subsequent landing. The following special procedure should be applied during taxi before and as close as possible to take off. Set 18% Torque on each engine and keep taxi speed down to a ”man pace” during 30 seconds using normal brakes with minimum use of nose wheel steering to ensure a symmetrical warming up of the brakes. Mod 5948 2.02.08 PROCEDURES AND TECHNIQUES P 20 ADVERSE WEATHER 001 FEB 12 AA " TAKE OFF Standard take off procedures will be used with the following additions : . If runway is contaminated (ice, snow, slush), use the relevant performance penalties defined in the performance section 3.03. . Use of reverse on contaminated runways has to be limited at very low speeds to avoid contaminant projections at the level of cockpit windshield which may reduce visibility to zero (snow, slush). In atmospheric icing conditions, refer to appropriate speeds and performance penalties and add the following : - with very cold OAT, delay start of take off roll until oil temperature is at least 45°C (this is necessary to guarantee inlet splitter de-- icing capability). After the ground de icing/anti icing procedure, using type II/IV fluids, higher than normal stick forces may be encountered. These control input forces may be more than twice the normal take off force. This should not be interpreted as a ‘pitch jam‘ leading to an unnecessary abort decision above V1. Although not systematic, this phenomenon should be anticipated and discussed during pre-- take off briefing each time de icing/anti icing procedures are performed. These increased pitch forces are strictly limited to the rotation phase and disappear after take off. In very exceptional circumstances, because of increased rotation forces, the pilot canconsider that take off is impossible and consequently initiate an aborted take off . The consequences of this decision are catered for by a specific performance penalty (Refer to AFM SUPPLEMEMTS chapter). AFTER V1, BE TAKE OFF MINDED " BEFORE LANDING If take-- off has been performed on a slush contaminated runway, this slush may seize the brakes during cruise. To prevent tire damage at touch down : in final approach, after the selection of GEAR DOWN, select the ANTISKID to OFF, then pump the brakes at least 5 times and thenreselect the ANTISKID to ON. " LANDING Same restrictions on reverse than for accelerate stop. Apply relevant performance restrictions. " PARKING When OAT is below - 5_C / 23_F, particularly in wet conditions, avoid leaving the aircraft with parking brake engaged and use chocks instead whenever possible. Mod 5948 2.02.08 PROCEDURES AND TECHNIQUES P 21 ADVERSE WEATHER 001 APR 11 AA OPERATIONS IN WINDY CONDITIONS Landing The recommended landing flap configuration is the same as the standard landing flap setting, even with strong crosswind. Large flaps extension does not impair the controllability in any manner. Moreover it minimizes the flare duration and allows a quicker speed decrease down to the taxi speed. General Precautions or special instructions may be necessary depending on the force and direction of the wind. The following FCOM pages deal with this subject : Tail wind limit and demonstrated cross wind 2 01 03 Final approach speed and wind factor 2 02 01 Cat II maximum demonstrated wind 2 02 04 Parking aircraft orientation 2 02 03 and 2 03 20 Aileron spring tabs (when equipped) 2 02 06 Taxiing with strong wind 2 02 06 Take off run 2 02 12 Rejected take off 2 02 12 Hotel mode limitation 2 03 06 and 2 05 02 Taxiing with tail wind component 2 03 09 Ditching 2 04 05 NAC OVHT 2 05 02 ELEVATOR JAM 2 05 06 PITCH DISCONNECT 2 05 06 AILERON JAM 2 05 06 SPOILER JAM 2 05 06 Mod : 5948 2.02.08 PROCEDURES AND TECHNIQUES P 22 ADVERSE WEATHER 001 APR 11 AA Windshear This phenomenon may be defined as a notable change in wind direction and/or speed over a short distance. Windshear can be encountered in the vicinity of thunderstorms, into rain showers (even without thunderstorms), during a frontal passage or on coastal airports (sea breeze fronts). Severe windshear encountered above 1000 feet, whilst unpleasant, can generally be negociated safely. However if it is encountered below 500 feet on take off or approach/landing it is potentially dangerous. As far as possible this phenomenon must be avoided. Procedure at take off : • Delay the take off. If a low level windshear is reported calculate VR, V2 at the maximum take off weight available for the day. • When clear of obstacles accelerate as much as possible and clean up the aircraft. • Climb at the normal climb speed. Procedure during an approach : If a windshear is encountered, • Initiate a normal go around procedure with 10° pitch . • When positively climbing at a safe altitude, retract the gear and complete the normal go around procedure. CAUTION : The positive rate of climb must be verified on at least two instruments. COMMENTS : 1. Leaving the gear down until the climb is established will allow to absorb some energy on impact, should the microburst exceed the aircraft capability to climb. 2. Ten degrees pitch attitude is the best compromise to ensure a climbing path together with an acceptable maximum AOA. Mod : 5948 2.02.08 PROCEDURES AND TECHNIQUES P 23 ADVERSE WEATHER 001 APR 11 VOLCANIC ASH ENCOUNTER 1- VOLCANIC ASH DESCRIPTION Volcanic ash is, essentially, extremely fine particles of glass shards and pulverized rock, the composition of which reflects the composition of the magma inside the volcano. It is composed predominantly of siliceous materials (> 50%) that are both very hard and very abrasive. The melting point of glassy silicates is around 1100_C that is close to the operating temperature of the engine at cruise thrust. The ash is accompanied by gaseous solutions of sulphur dioxide (sulphuric acid) and chlorine (hydrochloric acid). 2- AVOIDANCE Flight operations in volcanic ash are extremely hazardous and must be avoided. Flights in areas of known volcanic activity must be avoided. When a flight is planned into an area with known potential for volcanic activity: - All NOTAMS and air traffic advisories have to be checked for current status of volcanic activity. - The planned route has to well avoid the area of volcanic activity. - If possible, stay upwind of volcanic ash. The first two or three days following an explosive eruption are especially critical because high concentration of gas with hazardous concentration could be encountered at cruise levels some considerable distance from the volcano. Beyond three days, it is assume that if the ash is still visible by eye or from a satellite data, it still presents a hazard to aircraft. 3- DETECTION Volcanic ash cloud does not produce ”return” or ”echoes” on the airborne weather radar. Volcanic ash may be difficult to detect visually, especially at night or on instrumental meteorological conditions. However, the following have been reported by flight crew: - Acrid odor, similar to electrical smell, burned dust or sulfur. - Smoke or dust appearing in the cabin and cockpit, leaving a coating on cabin and cockpit surfaces. - Multiple engine malfunctions, such as stall, increase ITT, flameout. - Airspeed fluctuating erratically. - At night, static electric discharges (St. Elmo’s fire) visible around the cockpit windshields. - At night, landing lights cast sharp, distinct shadows on the volcanic ash clouds as opposed to the normally fuzzy, indistinct shadows cast on water / ice clouds. 4- EFFECTS ON POWERPLANT The melting point of volcanic ash is close to the operating temperature of the engine at cruise power. This can cause serious damage in hot section of the engine that could result in engine thrust loss and possible flame out. (.../...) Mod : 5948 2.02.08 PROCEDURES AND TECHNIQUES P 24 ADVERSE WEATHER 001 APR 11 4- EFFECTS ON POWERPLANT (CONT’D) Pilots are therefore asked to reduce engine power settings to flight idle when possible to lower the engine operating temperature below the melting point of volcanic ash. The volcanic ash, being abrasive, also damage engine components causing loss of engine thrust. The erosion also results in a decrease in the engine stall margin. Although this abrasion effect takes longer than the melting fusion of volcanic ash to shut down the engine, the abrasion damage is permanent and irreversible. Reduction of engine thrust to idle slows the rate of erosion by the compressor blades but can not eliminate it entirely while the engine is still ingesting air contaminated by volcanic ash. Propeller blades may also be degraded by erosion inducing loss of traction efficiency. Oil cooler efficiency may also be decreased either due to excessive erosion of the cooler or due to blockage of the air intake by ashes. 5 - EFFECTS ON THE AIRFRAME AND EQUIPMENT Volcanic ash abrades cockpit windows, airframe and flight surfaces. Any parts protruding from airframe such as antennas, probes, ice detectors can be damaged and may be rendered inoperable. - The abrasion of the cockpit window reduces the pilot’s forward visibility. This can lead to serious problems during landing phase. - The abrasion damage of the wing or horizontal stabilizer leading edges can either prevent the correct operation of the de-- icing boots or even detached parts of the boots with subsequent drag increase. - The abrasion damage of the landing lights can significantly reduce landing light effectiveness. - Damage to the antennas can lead to a complete loss of HF communications and a degradation of VHF communications. - Damage to the various sensors can seriously degrade the information available to the pilot through the instrument. Volcanic ash can obstruct probes and penetrate into air conditioning and equipment cooling system. It can contaminates electrical and avionic units, fuel and hydraulic system and smoke detection system. - Pitot probe can be blocked by volcanic ash resulting in unreliable airspeed indications or complete loss of airspeed indication in the cockpit. Volcanic ash columns are highly charged electrically. The static charge on the aircraft creates a ”cocoon” effect which may cause a temporary defection, or even complete loss of VHF or HF communication with ground stations. (.../...) Mod : 5948 2.02.08 PROCEDURES AND TECHNIQUES P 25 ADVERSE WEATHER 001 APR 11 6 - PROCEDURE VOLCANIC ASH ENCOUNTER FOLLOWING ITEMS HAVE TO BE APPLIED WHILE MAKING A 180 DEGREES TURN AND STARTING DESCENT (IF MSA PERMITS) ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY PL 1 + 2 (if conditions permit) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETARD MAN SPEED BUG TO VmHB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET HDG MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HDG SEL CREW OXY MASKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON / 100% CABIN CREW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY PASSENGER OXYGEN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR AIRPEED INDICATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR Note: Reducing TQ reduces ash ingestion, maximizes engine surge margin and lowers engine turbine temperature. Monitor particularly ITT; it may become necessary to set PL to Flight Idle, if conditions permit. Note: In extreme case, it may be necessary to consider precautionary engine shut down and engine restart in flight. If both engines flame out, refer to BOTH ENGINE FLAME OUT procedure (2.04.02) Note: Volcanic ash may clog the pitot probes resulting in unreliable speed indications.If airspeed is unreliable or lost, adjust airplane attitude and torque. Mod : 5948 . 2.02.09 PROCEDURES AND TECHNIQUES P1 001 LANDING GEAR/BRAKES APR 11 AA This chapter deals with the following points : - RUNWAY STATUS NORMAL TAXI TAXI WITH FAILURES EMERGENCY BRAKING RUNWAY STATUS The following table gives for take-- off and landing the equivalent runway status corresponding to the braking action or the friction coefficient. This runway status may be used for the computation of the performances. EQUIVALENT RUNWAY STATUS TAKE- OFF LANDING BRAKING ACTION GOOD FRICTION COEFFICIENT 0,40 and above 1 1 GOOD/MEDIUM MEDIUM 0,39 to 0,36 0,35 to 0,30 2 3/6 2 5/6 MEDIUM/POOR POOR UNRELIABLE 0,29 to 0,26 0,25 and below UNRELIABLE 4 7 8 5 7 8 EQUIVALENT RUNWAY STATUS : 1 : Dry runway 2 : Wet up to 3 mm depth 3 : Slush or water for depths between 3 and 6 mm 4 : Slush or water for depths between 6 and 13 mm 5 : Slush or water for depths between 3 and 13 mm 6 : Compact snow 7 : Ice 8 : Runway with high risk of hydroplaning Mod 5948 2.02.09 PROCEDURES AND TECHNIQUES P2 LANDING GEAR/BRAKES 001 APR 11 AA NORMAL TAXI CAUTION : If blue hydraulic circuit is pressurized, nose wheel steering has to be switched off for towing by a ground vehicle. - The ATR 72 is particularly easy to taxi, and even on one engine, there are no limitations to go either forward or rearward : this flexibility should be systematically used and is reflected in the standard operating procedure which assumes HOTEL MODE operation of engine 2 prior to and during passenger boarding followed by initial taxi on engine 2 only (including back track if taxi backwards required). This procedure is highly recommended as GI power is quite sufficient on one engine only to perform all taxiing (OUT and IN) and very obviously reduces block fuel by an amount which may become VERY SIGNIFICANT on large airports. CAUTION : Start up of engine 1 should be performed in a portion of taxi where captain workload is low enough to allow an efficient monitoring of the start up. - Use of brakes during taxiing may be very much reduced by systematic use of a small amount of reverse when deceleration is needed. - Radius of turn with nose wheel steering is very good and does not require any braking ON THE INNER WHEELS. CAUTION : PIVOTING (Sharp turns) UPON A LANDING GEAR WITH FULLY BRAKED WHEELS IS NOT ALLOWED, except in emergency. TAXI WITH FAILURES TAXI WITH NOSE WHEEL STEERING OFF (or without blue HYD pressure) D Obviously SINGLE ENGINE TAXI is no more possible D Taxiing remains very easy with both engines operating EEC ON : directional control is achieved primarily with differential power on engines, possibly augmented by use of differential braking. D Avoid sharp turns : turn radius without nose wheel steering should be limited to about half turn radius with nose wheel steering. TAXI WITH EEC OFF On ground EEC off, engine response is somewhat degraded. Nevertheless, as long as at least one engine is maintained at or below GI, the corresponding NP should remain high enough to keep associated ACW GEN available and thus maintain both HYD pumps. CAUTION : When taxiing with both EEC OFF, AVOID pushing both PL above GI to avoid transient loss of ACW and MAIN HYD PUMPS. Note : NOSE WHEEL steering remains available in all cases together with STBY braking, through DC AUX pump. Mod 5948 2.02.09 PROCEDURES AND TECHNIQUES P3 LANDING GEAR/BRAKES 001 APR 11 AA EMERGENCY BRAKING - Emergency braking has been made operationally easier by design of the parking brake lever which incorporates an “EMER BRAKE” notch : when the parking brake lever is set in this notch, the regulator delivers a limited pressure which : D allows the use of EMER BRAKING for abort take-- off at max V1 or at touch down for landings after GREEN pressure has been completely lost. D provides repeatable, smooth deceleration whilst minimizing the risk of blown up tires. CAUTION : Use of EMER BRAKE beyond the EMER BRAKE NOTCH ABOVE 60 Kts MUST BE AVOIDED TOPREVENT WHEELSLOCK UPAND DAMAGESTO WHEELS AND TIRES. BELOW 60 Kts, a SMALL further travel (∼ 1 cm) IS AVAILABLE WITHOUT RISKS OF DAMAGE WHEN MAXIMUM STOPPING PERFORMANCE IS REQUIRED. - A deflated tire is not easily noticeable from the cockpit : NO TAKE OFF should be started after EMER BRAKE has been used at speeds in excess of a maximum taxiing speed of 20 Kt without prior visual inspection of the main landing gear tires. Mod : 5948 . 2.02.10 PROCEDURES AND TECHNIQUES P1 FLIGHT PATTERNS APR 11 CLB procedure: AA Mod : 5948 001 2.02.10 PROCEDURES AND TECHNIQUES P2 FLIGHT PATTERNS AA Mod : 5948 001 APR 11 2.02.10 PROCEDURES AND TECHNIQUES P3 FLIGHT PATTERNS AA Mod : 5948 001 APR 11 2.02.10 PROCEDURES AND TECHNIQUES P4 FLIGHT PATTERNS AA Mod : 5948 001 APR 11 2.02.10 PROCEDURES AND TECHNIQUES P5 FLIGHT PATTERNS AA Mod : 5948 001 APR 11 2.02.10 PROCEDURES AND TECHNIQUES P6 FLIGHT PATTERNS AA Mod : 5948 001 APR 11 2.02.10 PROCEDURES AND TECHNIQUES P7 FLIGHT PATTERNS AA Mod : 5948 001 APR 11 2.02.10 PROCEDURES AND TECHNIQUES P8 FLIGHT PATTERNS AA Mod : 5948 001 APR 11 2.02.10 PROCEDURES AND TECHNIQUES P9 FLIGHT PATTERNS AA Mod : 5948 001 APR 11 . 2.02.11 PROCEDURES AND TECHNIQUES P1 001 POWER PLANT APR 11 AA START UP PROCEDURE Prior to initiating start sequence EEC FAULT light must be extinguished, if EEC FAULT is lit try to reset ; if unsuccessful, deselect EEC. During engine start or relighting, the following items must be monitored. - Correct NH increase when starting the sequence. - Starter disconnection at 45 % NH. - Maximum ITT : during a battery start one or two ITT peaks not exceeding 800°C may usually be observed. ITT peaks are of lower value if a suitable GPU is used. This example shows the start sequence of engine N° 1 on ground (engine 2 running) NH % Parameters START 1 10 0 ON illuminated STARTER/GENERATOR CLA 25 45 62 (ON extinguished) Starter FUEL SO generator * FTR IGNITION EEC ELECTRICAL SUPPLY OF STARTER/GENERATOR PLA EEC ON MAIN BAT. (MAIN BAT. + GEN 2) GI * Passing from FUEL SO to FTR is possible between 10 and 19 % NH if ITT > 200° C. ENG OIL LO PR FWS alarm is 30 seconds time delayed to avoid untimely ENG OIL LO PR during engine start. Refer to 2.02.08 p18 for specific cold weather behaviour. Note : This alert is inhibited when affected CL is in FUEL SO position. Mod 5948 2.02.11 PROCEDURES AND TECHNIQUES P2 POWER PLANT AA 001 APR 11 TAKE OFF: USE OF BLEED VALVES The aircraft is fitted with an automatic bleed valve closing in case of engine failure at take off. The closing signal is given by MFC’s when uptrim is triggered. BLEED FAULT light also illuminates on the operative engine. Engine bleed valves may be routinely selected ON (NORM FLOW) for take off. However, performance decrement has to be considered for the ground phase. This decrement is given in chapter 3.03 and may be computed by the FOS. POWER SETTING AT TAKE OFF Engine control normally uses temperature, altitude and speed data from the selected ADC but reverts to its own sensors in case of detected failure or significant offset. TAT/SAT information are valid only when the engine (propeller unfeathered) corresponding to the selected ADC is running. RTO torques must be computed using altitude and temperature information independant from aircraft sources and compared to values displayed by torque bugs. Take off power is routinely obtained by setting the power levers and the condition levers into the notches. If needed, in order to match target torque bugs set according to dependable data, it may be necessary to adjust the throttles out of the notches. UNFEATHERING AFTER AN ENGINE RESTART IN FLIGHT Unfeathering the propeller induces a limited lateral disturbance. ENGINE PARAMETERS FLUCTUATION The variation tolerances of engine parameters are shown in Figure. These tolerances must be taken into account only in stabilized flight phases. PARAMETERS TQ NH ITT NP FLUCTUATION AMPLITUDE +/- 2 % +/- 0.25 % +/- 10_C +/- 2.5 % In case of engine parameters fluctuation it can be helpful to select the corresponding EEC OFF then On according to EEC FAULT C/L before shutting the engine down. If this action cures the problem, the flight can be continued accordingly. MAN IGNITION When one or both EEC (s) has (have) been deselected, the use of MAN ignition is required when the aircraft penetrates heavy precipitation or severe turbulence areas, when ice accretion develops or when using contaminated runway for take off or landing. GO AROUND - POWER SET UP PROCEDURE The throttle movement (PF) is to be applied accross the notch up to the ramp (beginning of amber sector). WARNING : Overriding the ramp threshold up to the absolute full travel will allow to reach 1.15 x RTO TQ (EEC ON). This should be used only is case of emergency. CLs should routinely stay into the notches. Np is automatically set at 100 % provided PWR MGT is on TO position and PLA is sufficient (see 1.16.40). Mod 5948 2.02.11 PROCEDURES AND TECHNIQUES P 2A POWER PLANT 001 APR 11 PUSH BACK AND POWER BACK OPERATIONS Push- back (with towbar) - Push-- back is done after ATC clearance. - Specific phraseology is used. - Ground staff remains connected with the aircraft by using conventional signs and/or headphones with several persons according to airline policy - Parking brake released and steering OFF. - Each crew member keeps his feet on the floor. NEVER USE BRAKES during push back (to avoid tail strike and/or strain on towing system). Wait for disconnection of the tow bar by the ground staff before switching the steering ON. - Set nose wheel steering to ON. Caution: never set the hydraulic of the steering before the disconnection of the tow bar. Note:NAC OVHT and ENG FIRE can be triggered during push-- back in hotel mode, with a tail wind greater than 10kts, including aircraft direction changes throughout the procedure. If the tail wind is above this limit, the push-- back has to be done, with the propeller(s) running and unfeathered, and respecting ground safety rules and airport local rules. Power back - Before power back, both propellers are running and are unfeathered. - Power back is done after ATC clearance. - Ground staff area checked cleared before and during power back, by using conventional signs and/or headphones with several people, as per prevailing airlines policy. - Nose wheel steering remains ON. - To avoid moving forward, apply slight power back just before releasing brake. - Each crew member keeps his feet on the floor. NEVER USE BRAKES during power back (to avoid tail strike). - Power back is performed at low speed. - Use Ground Idle or positive power to decrease speed or stop. Note: NAC OVHT and ENG FIRE can be triggered, if a prolonged power-- back is maintained with a tail wind greater than 10kts, including aircraft direction changes throughout the procedure Note: In Ground Idle, after parking brake release, the aircraft moves forward. The power lever has to be retarded slightly to power back just before releasing the brake. Note: Safety glasses have to be used by the ground staff, because of the possibility of projection during power back operation. Mod 5948 . 2.02.11 PROCEDURES AND TECHNIQUES P3 POWER PLANT 001 APR 11 AA ADAPTED FLIGHT IDLE A low flight idle rating is associated with a significant increase of aerodynamic drag profitable to the descent performance (approach and landing). On the other hand, this increased drag penalises the lift at a high angle of attack. The fulfillment of these two requirements has led to an adapted flight idle providing two power settings. The FI position being selected by the pilot, the power level (high or low) is set by the EEC’s, as a function of an information provided by the MFC’s. This information is associated with a limit angle of attack equal to α stall warning - 4°. In case of high flight idle loss the aircraft behaviour during stall unchanged and the decrease of lift is negligible and covered by the regulatory margins. PROPELLER BRAKE USE Propeller brake must be used only when READY light on propeller brake control panel is illuminated. 1 - BRAKING SEQUENCE (ENG 2 Running) Notes : The DC AUX pump runs automatically as soon as - blue hydraulic pressure is below 1500 PSI and, - gear is down and, - one engine is running and stops 15 seconds after the end of prop braking sequence (PROP BRK lights illuminated). Mod 5948 2.02.11 PROCEDURES AND TECHNIQUES P4 POWER PLANT 001 APR 11 2 - RELEASING SEQUENCE (ENG2 in hotel mode) R R R Note : A pulse on AUX HYD PUMP pb starts the auxiliary hydraulic pump for 30 seconds. Selecting. Selecting propeller brake sw to OFF position within this 30 s temporization allows to keep the DC AUX PUMP running overriding the 30 seconds temporization. Mod 5948 2.02.11 PROCEDURES AND TECHNIQUES P5 001 POWER PLANT APR 11 DIFFERENCE BETWEEN AN EEC FAULT CONDITION AND AN ENGINE FLAME OUT IN FLIGHT ENGINE FLAME OUT(*) EEC FAULT POWER EVOLUTION Immediate power loss Moderate variation (either way) EEC FAULT LIGHT Not lit Immediate illumination NH Rapidly below 74 % Always above 74 % ITT rapidly below 350° C Always above 350° C POWER LEVER Totally inefficient Generally inefficient refer to FCOM 1.16.30 ASSOCIATED DC GEN LT DC GEN Fault illuminates rapidly Normal BLEED/PACK FAULT illuminates rapidly Normal (*) If automatic relight has not operated ENGINE OPERATION WITH EEC OFF - EEC deactivation may lead to an important power variation at constant throttle position. Power recovery will necessitate throttle readjustment. - Maintaining target torque may necessitate positions out of the notch since constant throttle position feature is lost. Some throttle readjustements will be necessary during climb. Engine response may be more sluggish when increasing power and a temporary throttle overtravel may be necessary to obtain a fast power response. - If EEC is selected from OFF to ON, an important power variation may result. That is why the throttle has to be reduced below 52° prior to such an action. - Landing with both EEC OFF will lead to a big propeller speed decay as the speed decreases, so that ACW power may be lost at the end of the landing run. Be ready to use nose wheel steering and emergency braking as required. Engine response during taxi will be slower. - Reverse power is reduced. Moreover, in case of acceleration stop, a one second stop must be observed at Fl before setting PLs below. Mod 5948 2.02.11 PROCEDURES AND TECHNIQUES P6 POWER PLANT 001 APR 11 AA ENGINE FAILURE SIMULATION FOR TRAINING PURPOSES Flight training requires to simulate engine failure in a representative manner for both controllability and performance aspects but without feathering engine (safety and cooling of nacelle). For a given PL position, the propeller THRUST (+) / DRAG (-- ) VARIES VERY SIGNIFICANTLY WITH IAS, particularly at low speeds, as shown by the following table. (Zp = 0 (ISA/NP max = 100%) PL Position 0 kt 50 kt 100 kt 125 kt 150 kt 40 1300 daN 710 daN 200 daN 0 daN ~0 daN 36 1270 daN 670 daN - 240 daN - 600 daN - 530 daN Fl 1240 daN 640 daN - 460 daN - 850 daN - 750 daN Gl 140 daN - 610 daN - 2070 daN Max Rev - 610 daN - 1370 daN - 2900 daN - The drag of a feathered engine is negligible between 0 and 150 kt. - The maximum drag of a failed, unfeathered, engine varies with IAS and PL position as follow : PL Position 0 kt 50 kt 100 kt 125 kt 150 kt TO 0 daN 80 daN 310 daN 470 daN 700 daN Fl (B = 14°) 0 daN 80 daN 400 daN 620 daN 750 daN The procedure for simulating engine failure is based on retarding PL to fixed positions, optimised to cover correctly the T/O and approach phases i.e. for IAS around 110/ 125 kts. IN FLIGHT - To simulate an UNFEATHERED failed engine retard PL at Fl. - To simulate a FEATHERED engine set PL to 39 for IAS 110/125 kt. Note : ISA and altitude effects are negligible. - For continued take-- off with simulated engine failure, retard PL to 39 for IAS 110/125 kt in order to simulate auto feather action. ON GROUND - Aborted T/O: Retard INITIALLY to Fl. CAUTION : - On ground, in all cases, (single engine landing or aborted T/O), the trainee must retard BOTH PL at Gl, then use reverse on «LIVE» engine only, as necessary. - Leaving the simulated « engine failed » PL at 39 or more (for single engine landings) or Fl (for aborted T/O) would lead to non representative controllability problems as the «failed » engine thrust would change its initial drag into a big increase of forward thrust as IAS decreases. - To be exact, these values request a perfect rigging of engine controls. A slight mismatch may induce a significant drag change. Pilot should monitor performances and increase PLA as necessary. Mod 5948 2.02.11 PROCEDURES AND TECHNIQUES P7 POWER PLANT 001 APR 11 REVERSE PHASES NP is the parameter to be monitored during reverse phases. (NP is the only regulated parameter in these phases) OPERATIONS OUT OF THE NOTCH When PL are retarded, during descent and approach, trim efficiency is reduced (reference point being notch), and cannot correct built-- in discrepencies between engines and their associated controls. Tolerances due to PL rigging cannot be compensated in that area. TQ split up to 8% (8 counts) can be evidenced between engines in stabilised conditions. This is built-- in and results from requirement of TQ accuracy in notch, which is the power setting used for about 90% of flight time. TQ differences are allowable and can be eventually compensated manually by crew with PL adjustment. Mod 5948 . 2.02.12 PROCEDURES AND TECHNIQUES P1 FLIGHT CHARACTERISTICS 001 APR 11 AA TAKE OFF AND LANDING RUNS - Proper crew coordination is required in order to hold the control column at all times and prevent excessive elevator or aileron deflections due to wind and/or reversed air flow from propellers. The control column is initially held. D in pitch : fully nose down, then slowly relaxed as speed increases. D in roll : neutral or deflected TOWARD the wind in case of crosswind component, as appropriate to maintain wings essentially level. Note : Excessive aileron deflections should be avoided as they affect directional control. - For take-- off, use of nose wheel steering guidance is only recommended for the very first portion of the take off run as rudder becomes very rapidly efficient when airspeed increases (~ 40 kts) and ATR 72 exhibits a natural tendency to go straight. - Action on nose wheel tiller should be smooth and progressive, particularly as ground speed increases. - Rudder must not be cycled during take-- off, particularly the first portion where nose wheel is used: combination of unnecessary rudder cycling (with an increasingly efficient rudder) and nose wheel control would then lead to uncomfortable oscillations. - Rolling take-- off technique In order not to increase the take-- off distances, power must be set quickly during the last phase of the line up turn. - for landing or aborted take off, control column holding must be transferred to the co-- pilot when the captain takes the nose wheel steering. If reverse is used, at low speeds and with high power, the reversed air flow may shake violently the flight controls, particularly with no crosswind: the control column must be held very firmly and/or, below 30 kts, the GUST LOCK may be engaged. Narrow Runways : When the aircraft is operated on a narrow runway (width < 30 m (98 ft)), whoever is the PF (CM1 or CM2), the CM1 should be ready to use Nose Wheel Steering as soon as the nose wheel is on the ground. If reverse is used, at low speeds and with high power, the reversed air flow may shake violently the flight controls, particularly with no crosswind : the control column must be held very firmly and/or, below 30 kts, the GUST LOCK may be engaged. Refer to 3.11.10 Mod 5948 2.02.12 PROCEDURES AND TECHNIQUES P2 FLIGHT CHARACTERISTICS 001 APR 11 AA ENGINE FAILURE AT TAKE OFF BELOW V1 Abort is mandatory: both PLs are retarded to Gl and full braking applied if needed. Reverse is available even on single engine down to full stop: again, control column is transferred to the co-- pilot when captain takes nose wheel steering and, in case of single reverse operation roll control must be applied (possibly to full travel) in order to minimize the tendency to bank on the side of the operating engine. AT TAKE OFF ABOVE V1 Take off must be continued. Directional control must be maintained with rudder and, as soon as aircraft becomes airborne, aileron input to stabilize heading with about 2° of bank toward the operating engine is highly recommended in order to decrease rudder deflection thence improve climb performance. Both rudder and aileron forces may be completely trimmed out, even at minimum scheduled V2. Once both yaw and roll axis are trimmed out, autopilot may be engaged. IN APPROACH Directional control must be maintained with rudder, (which disengages automatically YD and AP if previously engaged) and aileron, in a manner similar to what was described for the continued take off case. The ATPCS functioning is different between approach and take-- off. Even if TO position is selected: - Uptrim function is never available - Auto feather function may be available depending on PL position at the time of the failure. If autofeather has not operated (windmilling), the drag depends on the engine failed PL position. For this reason : - In approach, do not reduce the affected PL below 45° PLA before manually feathering the engine. - If a go around is performed, advance both PLs to the ramp. When appropriate, manually feather the failed engine. LANDING (PROPELLER FEATHERED) - Flare technique remains unchanged and rudder input required to compensate the asymmetric reduction at 20 ft is more smoothly achieved if YAW DAMPER has been disconnected in short final. - After main gear touch down, it is recommended to first lower nose wheel to ground contact before reducing PL from Fl to Gl: this allows to better control the large asymmetric associated drag increase on the live engine side. PL may be then retarded to full reverse as required but roll attitude must be controlled which requires large control wheel deflection by PNF. Mod 5948 2.02.12 PROCEDURES AND TECHNIQUES P3 FLIGHT CHARACTERISTICS 001 APR 11 AA STALLS STALL WITHOUT ICE ACCRETION In all configurations, when approaching the stall, the aircraft does not exhibit any noticeable change in flight characteristics: control effectiveness and stability remains good and there is no significant buffet down to CL max ; this is the reason why both the stall alert (audio “cricket” and shaker) and stall identification (stick pusher) are “artificial” devices based on angle of attack measurement. Recovery of stall approaches should normally be started as soon as stall alert is perceived : a gentle pilot push (together with power increase if applicable) will then allow instantaneous recovery. If the stall penetration attempt is maintained after stall alert has been activated, the STICK PUSHER may be activated : this is clearly unmistakable as the control column is suddenly and abruptly pushed forward, which in itself initiates recovery. Note : The “pushing action” is equivalent to 40daN/88 lbs applied in 0.1 second and it lasts as long as angle of attack exceeds the critical value. CAUTION : Stall training excercices without stick pusher are prohibited. STALL WITH ICE ACCRETION Even with airframe de-- icers used according to procedure (i.e. as soon as and as long as ice accretion develops on airframe), the leading edges cannot be completely cleared of ice accretion because of existence of “unprotected” elements on the leading edges and continued accretion between two consecutive boots cycles. This residual ice on leading edges changes noticeably the characteristics of flight BELOW the minimum operating speeds defined for ice accretion, as follows : - Control effectiveness remains good, but forces to manoeuver in roll and to a lesser degree in pitch, may increase somewhat. - Above the reduced angle of attack : . An aerodynamic buffeting may be felt which will increase with the amount of ice accumulated and angle of attack increase. . Stability may be slightly affected in roll, but stick pusher should prevent angle of attack increase before wing rocking tend to develop (Refer to FCOM 1.02.30 for stall alarm threshold definition). Recovery of stall in such conditions must be started as soon as stall warning is activated or buffeting and/or beginning of lateral instability and/or sudden roll off is perceived. Recovery will be best accomplished by : - A pilot push on the wheel as necessary to regain control. - Selection of flaps 15. - Increase in power, up to MCT if needed. Mod 5948 2.02.12 PROCEDURES AND TECHNIQUES P4 FLIGHT CHARACTERISTICS 001 APR 11 AA APPROACH - The deceleration capabilities of the ATR 72 provide a good operational advantage which should be used extensively: decelerated approaches reduce noise, minimize time and fuel burn and allow better integration in big airports. This is why they have been described as the « standard approaches » in section 2.02.10 (flight patterns). - Initial approach speed will vary with ATC constrainsts and turbulence, but may be up to 240 Kts. - Initial approach speed may be maintained on a typical 3° glide slope down to the following height above runway: NP DECELARATION HEIGHT 82 % (IAS x 10) ft Configuration changes should be made at VLE VFE when decelerating. This procedure allows to reach VAPP speed at 500 ft above runway. Note : If deceleration rate on approach appears unsufficient, it is always possible to increase it by setting NPs on 100 OVRD, but at the expense of an increased interior noise. R STEEP SLOPE APPROACH R Refer to 3.11.17 Mod 5948 2.02.12 PROCEDURES AND TECHNIQUES P5 FLIGHT CHARACTERISTICS 001 APR 11 AA LANDING In order to minimize landing distance variations the following procedure is recommended : D Maintain standard final approach slope (3°) and final VAPP until 20 ft is called on radioaltimeter. D At« 20ft » call by PM, reduce to FI and flare visually as required. Note : 20 ft leaves ample time for flare control from a standard 3° final slope. - During this flare the airspeed will necessary decrease, leading to a touch down speed of 5 to 10 kt lower than the stabilized approach speed. D As soon as main landing gear is on ground. - Control nose wheel impact - Both PL : GI - Both LO PITCH labels: check illuminated green. CAUTION : If a thrust dissymetry occurs or if one NO REV red reverse video label on EWD is illuminated, the use of any reverser is not allowed. In this case the propeller pitch change mechanism is probably locked at a positive blade angle, leading to a positive thrust for any PL position. - use feet brakes as required - as speed reduces, and not later than about 40 kt (estimated) Capt takes NWS control, co-- pilot hold control column fully forward. Notes : 1. Max reverse is usable down to full stop if required, but to minimize flight control shaking due to reverse operation at high powers, it is helpful to release slowly PL back to GI when reaching low ground speeds (below 40 kt estimated). 2. Max braking is usable without restriction down to full stop, whatever the runway conditions may be, provided ANTISKID is operative. 3. The tail bumper (with damping capabilities) effectively protect the tail in case of excessive attitude (resulting from prolonged/floating flares) provided the rate of sink at touchdown does not exceed 5 ft/sec. 4. In case of a significant bounce, a go around must be initiated. Mod 5948 . 2.02.14 PROCEDURES AND TECHNIQUES FLIGHT INSTRUMENTS AHRS P1 001 APR 11 AA AHRS AHRS alignment sequence takes place as soon as the battery is switched ON, and it takes nominally 1 MINUTES DURING WHICH AIRCRAFT MUST NOT BE MOVED (on ground). AHRS are normally not affected by electrical transients asociated with engine start. Note : during AHRS alignment, the alert “AHRS NOT ALIGN” is dispalyed on FWS, and “AHRS DEGRADED” is diplayed on the corresponding PFD. ON GROUND ONLY, if needed, AHRS reset may be performed by cycling all relevant C/B OFF-- ON. CAUTION : resetting AHRS C/B in flight is not recommended as in flight realignment requires 1 minutes and 30 seconds of very stable flight (which may be impossible to get in turbulences) and possibility of pulling the wrong C/B could lead to complete AHRS failure unrecoverable for the rest of the flight. CAUTION : Pilots must be aware of possible induced attitudes and heading errors in case of continuous turns, specially in high latitudes countries; therefore racetrack holding patterns are to be flown rather than circles. Mod : 5948 2.02.14 PROCEDURES AND TECHNIQUES FLIGHT INSTRUMENTS WEATHER RADAR P2 001 APR 11 AA WEATHER RADAR THe weather radar radiates power when operating in any mode other than STBY. Use of weather radar on ground in a mode other than STBY requires special care : - make certain that no personnel is working in front of aircraft within a sector of 3 meters radius and 130_ left or right of the aircraft axis. - direct aircraft nose so that no large size metal object (hangar, aircraft ...) is located within a 30 meters radius. - avoid operating radar during refueling operation of radiating aircraft or any other aircraft within a 30 meters radius. Mod : 5948 2.02.15 PROCEDURES AND TECHNIQUES P1 TCAS 001 APR 11 AA TCAS GENERAL TCAS is an airborne Traffic alert and Collision Avoidance System that interrogates ATC transponders in nearby aircraft and generates appropriate aural and visual advisories to the flight crew to provide adequate separation. Air to Air communications for coordinating maneuvers between TCAS equipped aircraft is provided by mode S ATC transponder. Note 1 : TCAS system can only generate resolution advisories for intruders equipped with operative mode S or mode C transponders (providing valid intruders altitude information). Note 2 : Traffic advisories can only be generated for intruders equipped with operative mode S, C or A transponders (TCAS system provides no indication of aircraft without operative transponders). CAUTION The TCAS equipment q p is viewed as a supplement pp to the pilot p who,, with the aid of the Air Traffic Control, has the primary responsability for avoiding mid-- air collisions. START UP AND TEST TRAFFIC display on ND: - On MCP press ”ND”. - On VCP select ”ND OVLY” tab, then select TRAFFIC ”NORM” TCAS/ XPDR mode selection: - On MCP press ”SURV”, select ”TCAS” tab and select ”STBY” mode - Select ”XPDR” tab and select ”STBY” mode To launch TCAS/XPDR Test : - Through MCDU, launch TCAS/XPDR self test and check proper aural message and visual display. GROUND OPERATION TCAS test should be carried out during cockpit preparation. Unless otherwise instructed by ATC: - on MCP press ”SURV”, select ”XPDR” tab on VCP, set ”ALT” mode and check XPDR1 selected; then on MCP press ”SURV”, select ”TCAS” tab and select ”AUTO” mode. On PFD / TCAS status indication, green message ”TCAS ABOVE” is displayed . On PFD / TTransponder status indication, green message ”XPDR1(2) ALT” is displayed Mod : 5948 2.02.15 PROCEDURES AND TECHNIQUES P2 TCAS 001 APR 11 AA TCAS (CONT’D) FLIGHT PROCEDURES Procedure is initiated by a TCAS Traffic Advisory : TA. “TRAFFIC - TRAFFIC” CPT - Decide task sharing and announce : “TCAS, I (you) have the controls.”. PF - Be minded for maneuver. Follow traffic evolution on the TCAS indicator. PM - Recall minimum safety altitude. Try to visually acquire the intruding aircraft. Then may occur a Resolution Advisory : RA. Some RA will only advise to monitor vertical speed (preventive RA). Others will advise to maneuver the aircraft. The following procedures should then apply : Sense of Resolution Advisory asking to maneuver DESCEND CLIMB CPT - Confirm “We descend.”. PF - Disconnect Auto Pilot PM - Descent at a rate in the green (fly to) band on PFD vertical. speed scale - Ask for eventual configuration changes. PF Advise ATC - Monitor IAS compared to VLE, VFE, VMO pointer - Monitor Aircraft altitude compared to minimum safety altitude. PM PM - CPT - Confirm “We climb.”. - Select proper rating on PWR MGT rotary selector (MCT en route or TO in other phases e.g. take off, approach and landing) - Disconnect Auto Pilot - Apply roughly the bugged power - Climb at a rate in the green (fly to) band on PFD vertical speed scale. - Ask for eventual configuration changes. - Adjust power to TQ objectives - Advise ATC - Monitor IAS compared VS. Note : When a climb or increase climb RA occurs with the airplane in the landing configuration or in the go - around phase, a normal go - around procedure should be followed including the appropriate power increase and configuration changes. After separation has become adequate (range increasing), TCAS will issue following RA. “CLEAR OF CONFLICT” Return promptly to last assigned ATC clearance. Mod : 5948 2.02.16 PROCEDURES AND TECHNIQUES P1 TAWS 001 APR 11 AA GPWS WARNING Note : When flying under daylight VMC conditions, should a warning threshold be deliberately exceeded or encountered due to known specific terrain at certain locations, the warning may be regarded as cautionary and the approach may be continued A go around shall be initiated in case warning cause cannot be identified immediately. J ”TERRAIN” - ” PULL UP” - POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GO AROUND - A/P . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF F When flight path is safe and caution/ warning cease : Decrease pitch attitude and accelerate. F When speed above minimum required and V/S positive : Clean up aircraft as necessary. J ”SINK RATE” Adjust pitch attitude and power to silence the warning. J “DON’T SINK” Adjust pitch attitude and power to maintain level or climbing flight. J ”TOO LOW GEAR” - ”TOO LOW FLAPS” : Perform a go around. J ”GLIDE SLOPE” - Establish the airplane on the glide slope. J ”BANK ANGLE” - Ajust roll attitude to silence the warning, Mod 5948 2.02.16 PROCEDURES AND TECHNIQUES P2 TAWS 001 APR 11 AA PREDICTIVE WARNINGS ”OBSTACLE AHEAD” J Verify the aeroplane flight path, correct it if required, if in doubt, perform a climb until the caution alert ceases. J ”TERRAIN AHEAD, PULL UP” Verify the aeroplane flight path and correct it if required, if in doubt, perform a climb until the caution alert ceases. J “AVOID TERRAIN” Immediately initiate a climb and then, based on any available information but preferably external visual reference. continue to maneuver until warning ceases. Mod 5948 2.02.18 PROCEDURES AND TECHNIQUES P1 FMS AA R Refer to FCOM part 4 (FMS user guide). Mod : 5948 001 FEB 12 . 2.02.19 PROCEDURES AND TECHNIQUES P1 HIGH LATITUDES OPERATIONS 001 APR 11 AA CONDITIONS Anomalous heading errors may occur on aircraft equipped with the SAGEM APIRS AHRS during high latitude operations, where the earth’s magnetic lines of force have inclinations of greater than 75 degrees. PROCEDURES - Take special care to keep the slip indicator centered in order to minimize heading errors. - Crosscheck AHRS heading information with GPS/GNSS. - Continous turn of more than 360_ must be avoided; for holding, it is recommended to fly racetrack patterns with straight flight legs of at least one minute between the U turns. Mod 5948 . 2.02.20 PROCEDURES AND TECHNIQUES P1 OPERATIONS BELOW --35_C GROUND TEMPERATURE 001 APR 11 AA Operating the aircraft at ground temperatures below - 35_C requires modification of certain instructions or procedures beyond the scope of the cold weather operations chapter of this manual (2.02.08 page 16) : GENERAL S Preheating of engines and flight deck is required. S Taxying must be achieved with both engines operating. S Propeller brake (if applicable) must not be engaged after the last flight of the day or for prolonged stops. S Aileron gust lock system(If applicable) must not be used in extreme cold temperature condition.Associated breakers (FLT CTL/ GUST LOCK AIL 10CE) to be pulled and tagged. S The first operation of any system using hydraulic fluid may be slower than normal. S It is recommended to use the HOTEL mode (if applicable) for short turnarounds. S Passenger, service and cargo doors should not be opened unnecessarily. HOTEL MODE (If applicable) 2,900 PSI blue hydraulic pressure is required to engage or to release the propeller brake. Therefore it may be necessary either to connect an AC GPU or to start up and unfeather the left engine prior to operate the propeller brake. START UP S During start of the second engine, the X START FAIL system may fail. Therefore the DC GPU must be kept connected until both engines have been started. S CL should be advanced to FTR between 15 and 20% NH instead of the usual 10% value. S Oil pressure indication raising time is considerably increased : OIL LO PR red warning may be activated for three minutes. During this period the engine must be maintained at IDLE condition. TAKE OFF Oil temperature must be over 0_C before TO power is applied. Mod : 5948 . 2.02.21 PROCEDURES AND TECHNIQUES MPC MULTI PURPOSE COMPUTER P1 001 APR 11 AA CONTENT 1-- APM FUNCTION LIMITATIONS/PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . 2 1.1 - LIMITATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 1.1.1 - OPERATIONS AND TECHNIQUES . . . . . . . . . . . . . . . . . . . . . . 2 1.1.1.1 - APM PRINCIPLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 1.1.1.2 - APM INTERFACES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 1.1.1.3 - APM TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 1.1.2 - NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 1.1.2.1 - WEIGHT SELECTION AND COMPUTATION . . . . . . . . . . . . . 5 1.1.2.2 - CRUISE SPEED LOW PROCEDURE . . . . . . . . . . . . . . . . . . 6 1.1.3 - EMERGENCY PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . . 6 1.1.4 - ABNORMAL AND FOLLOWING FAILURES PROCEDURES . . . . 6 1.1.4.1 - APM FAULT PROCEDURE . . . . . . . . . . . . . . . . . . . . . . . . . . 6 1.1.4.2 - DEGRADED PERF PROCEDURE . . . . . . . . . . . . . . . . . . . . . 7 1.1.4.3 - INCREASE SPEED PROCEDURE . . . . . . . . . . . . . . . . . . . . 7 1.2 - FLIGHT TIME MANAGEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 2 - DMU PART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 Mod 5948 2.02.21 PROCEDURES AND TECHNIQUES MPC MULTI PURPOSE COMPUTER P2 001 APR 11 AA 1 - APM FUNCTION LIMITATIONS/PROCEDURES 1.1 - LIMITATIONS APM does not induce any specific limitation. 1.1.1 - OPERATIONS AND TECHNIQUES 1.1.1.1 - APM principle The APM analysis is performed when the aircraft is in icing conditions: the ICING AOA is illuminated and/or if the airframe de-- icing is selected ON and/or if ice accretion has been detected at least once during the flight. The APM analysis principle is to compare the aircraft theoretical drag with an ”in-- flight drag” computed with measured parameters available. Measured parameters used by the APM are acquired each second and are smoothed over a rolling average of 30 seconds to limit noise and error measurements. Then, the drag is calculated over a rolling average of 60 seconds. This means that the drag analysis alert would start after at least 90 seconds of parameter acquisition. The drag analysis starts as soon as the aircraft enters in icing conditions with landing gears and flaps retracted. The APM analysis will only be done with both engines operating. A cruise speed monitoring will also be conducted by comparing the measured IAS to the theoretical maximum cruise IASth. Different alarm messages will be delivered to the crew depending on the drag difference between computed drag and theoretical drag, and the speed difference between measured IAS and theoretical IASth. The alarm messages will not be delivered if the static air temperature is above 10 degrees Celsius. Mod 5948 2.02.21 PROCEDURES AND TECHNIQUES MPC MULTI PURPOSE COMPUTER AA 1 - APM FUNCTION LIMITATIONS/PROCEDURES (cont’d) 1.1.1.2. - APM Interfaces Mod 5948 P3 001 APR 11 2.02.21 PROCEDURES AND TECHNIQUES MPC P4 MULTI PURPOSE COMPUTER 001 APR 11 AA 1 - APM FUNCTION LIMITATIONS/PROCEDURES (cont’d) 1.1.1.3 - APM test The APM test is activated by the crew daily, to check if all the APM components works properly. When the crew activated APM test and if the discrete ”APM ON/OFF” is ON The following test sequence shall be broadcasted to CAC1/CAC2: APM Aircrat Test Cruise Speed Low (CSL) Degraded Perf (DP) Increase Speed (IS) APM Fault FDR Fail FDAU Fail ”Cruise Speed Low” alarm is activated 1 second after activation of the APM Test Then ”Degraded Perf” alarm is activated 1 second after activation of ”Cruise Speed Low” alarm. The other alarms are activated following the diagram here above. All discrete outputs shall come back to inactive state when ”APM Aircraft Test” is deactivated. Mod 5948 2.02.21 PROCEDURES AND TECHNIQUES MPC MULTI PURPOSE COMPUTER P5 001 APR 11 AA 1 - APM FUNCTION LIMITATIONS/PROCEDURES (cont’d) 1.1.2 - NORMAL PROCEDURES 1.1.2.1 - Weight Selection and Computation Selection To determine the aircraft theoretical and ”in-- flight” performances the aircraft weight must be known. On ground just before flight and as soon as the crew has computed the gross weight on the load sheet, the crew must enter the corresponding weight in FMS corresponding data sheet through the MCDU. This parameter is available as ”Gross weight” parameter from two different sources DU2/FMS1 and DU4/FMS2. Until take off, the ”Gross weight” is continuously acquired. - if TOW1 (from FMS1) is valid, it shall be selected. - If TOW1 is invalid, then TOW2 (from FMS2) shall be selected if valid. Computation If the crew doesn’t select the take off weight before take off, then the APM shall perform a take off weight computation at the beginning of the flight. This computation is performed during the first minutes of the flight and before the APM starts the drag analysis. The actual weight is then updated in flight by internal computation. Mod 5948 2.02.21 PROCEDURES AND TECHNIQUES MPC P6 MULTI PURPOSE COMPUTER 001 APR 11 AA 1 - APM FUNCTION LIMITATIONS/PROCEDURES (cont’d) 1.1.2.2 - CRUISE SPEED LOW PROCEDURE CRUISE SPEED LOW on FMA - Appears in cruise only, to inform the crew that an abnormal drag increase induces a speed decrease of more than 10kt compared with the expected speed. ICING CONDITIONS and SPEED . . . . . . . . . . . . . . . . . . . . . MONITOR 1.1.3 - EMERGENCY PROCEDURES No specific Emergency Procedures linked to APM detection. 1.1.4 - ABNORMAL AND FOLLOWING FAILURE PROCEDURES 1.1.4.1 - APM FAULT PROCEDURE The APM Fault light function is to inform the crew that there is a problem in the APM computation, either in the MPC or in the aircraft wiring: The Fault can be triggered by MPC in the following conditions: - Invalid aircraft configuration, - Unable to retrieve input APM parameter, - MPC internal failure, - TOW estimation failed. In case of APM Fault light illumination, the crew has to select the APM OFF by pushing on the Fault light button. Note: As APM computation is not operative on Ground, the APM Fault is inhibited by the computer on Ground. Mod 5948 2.02.21 PROCEDURES AND TECHNIQUES MPC MULTI PURPOSE COMPUTER P7 001 FEB 12 AA 1 - APM FUNCTION LIMITATIONS/PROCEDURES (cont’d) 1.1.4.2 - DEGRADED PERF PROCEDURE DEGRADED PERF amber message on EWD with CAUTION light and Single Chime and on FMA. - Mainly appears in level flight after CRUISE SPEED LOW or in climb to inform the crew that an abnormal drag increase induces a speed decrease or a loss of rate of climb. - The most probable reason is an abnormal ice accretion R AIRFRAME DE-- ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON IAS ABOVE ICING BUG + 10 KT . . . . . . . . . . . . . . . . . . MONITOR AP (if engaged) . . . . . HOLD FIRMLY CONTROL WHEEL and DISENGAGE R H If SEVERE ICING conditions confirmed Or H If impossibility to maintain IAS above ICING BUG + 10 KT in level flight Or H If abnormal aircraft handling feeling SEVERE ICING procedure (2.04.05) . . . . . . . . . . . . . . . . . . . . APPLY H If normal conditions SCHEDULED FLIGHT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONTINUE ICING CONDITIONS and SPEED. . . . . . . . . . . . . . . . . . . . MONITOR Note: In case of APM messages “DEGRADED-- PERF” or “INCREASE-- SPEED” Vmin OPS automatically increased by 10 kt. R R 1.1.4.3 - INCREASE SPEED PROCEDURE INCREASE SPEED light illuminated flashing with CAUTION on EWD and on FMA and Single Chime. - Appears after DEGRADED PERF to inform the crew that the drag is abnormally high and IAS is lower than ICING BUG + 10 KT H If abnormal conditions confirmed IMMEDIATELY PUSH THE STICK TO INCREASE SPEED TO RECOVER MINIMUM IAS = ICING BUG + 10 KT SEVERE ICING procedure (2.04.05) . . . . . . . . . . . . . . . . . . . . APPLY R Mod 5948 H If normal conditions SCHEDULED FLIGHT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONTINUE ICING CONDITIONS and SPEED. . . . . . . . . . . . . . . . . . . . MONITOR Note: In case of APM messages “DEGRADED-- PERF” or “INCREASE-- SPEED” Vmin OPS automatically increased by 10 kt. 2.02.21 PROCEDURES AND TECHNIQUES MPC MULTI PURPOSE COMPUTER P8 001 APR 11 AA 1.2 - FLIGHT TIME MANAGEMENT The FDAU computes the flight time, computation starts with detection of ground/air condition (confirmation > 1sec) and stops with detection of air/ground condition (confirmation > 10sec). The current Flight Number is initialized automatically from AVIONICS system (FMS1 and FMS2) if available, otherwise manually from MCDU menu (through ACMS /MPC /INIT TIME and FLIGHT NUMBER). The following priority order is as follows: (1) Initialization from FMS1, (2) Initialization from FMS2, (3) Initialization from DMU using parameters initialized with MCDU, (4) Initialization with last Flight Number or null if never defined. Mod 5948 2.02.21 PROCEDURES AND TECHNIQUES MPC MULTI PURPOSE COMPUTER P9 001 APR 11 AA 2 - DMU (DATA MANAGEMENT UNIT) PART The DMU system is dedicated to the aircraft maintenance. The DMU has been designed to allow the user to customize the system according to his specific application, requirements, operating environment and logistics. Programming capabilities are provided, to allow modification of monitoring functions or implementation of additional monitoring functions. Mod 5948 . 2.02.24 PROCEDURES AND TECHNIQUES DU General Philosophy of use P1 001 APR 11 AA CONTENT 1 - NORMAL OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2 2 - DEGRADED OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3 3 - DISPATCH WITH ONE DU INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 3-- 1 - DISPATCH WITH DU 1 INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . 5 3-- 1 - DISPATCH WITH DU 3 INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . 6 3-- 1 - DISPATCH WITH DU 5 INOPERATIVE . . . . . . . . . . . . . . . . . . . . . . . . . . 7 4 - DUAL DC GEN LOSS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 Mod 5948 2.02.24 PROCEDURES AND TECHNIQUES DU General Philosophy of use P2 001 APR 11 AA 1- GENERAL ATR 600 instrument panel is fitted with five Display Units (DU), named DU 1 to 5 from left to right. Different formats may be displayed on these DU: PFD (Primary Flight Display), MFD (Multi Function Display) or EWD (Engine and Warning Display); in MFD format, the choice exists between different pages depending on the flight phase, such as ND (Navigation Display), SD (System Display), PERF, or other options. In normal operation, the configuration is the following: DU 1 (5) is dedicated to CM1 (2) PFD; DU 3 on central panel is dedicated to EWD; DU 2 (4) is normally dedicated to CM 1 (2) MFD. A DISPLAY push button is located on the CAPT (F/O) SWITCHING lateral console in order to cycle the three formats on DU 2 (4). In case of DU 2 (4) failure, this button is switching the DU 1 (5) format. In most of the formats, the lower part of the MFD is dedicated to VCP. On the VCP, VHF page should be selected by default, as it is the most frequently used page. Mod 5948 2.02.24 PROCEDURES AND TECHNIQUES DU General Philosophy of use P3 001 APR 11 AA 2- DEGRADED OPERATION In case of DU failure, the consequence will depend on the DU position and an automatic reversion logic is implemented so as to immediately guarantee the safety of the flight; the highest priority is given to PFD, and then to EWD. Then the crew remains free to choose the configuration via the DISPLAY pushbuttons, and the Captain will decide who is PF and PM according to failure assessment and company policy. DU2 or 4 failure is inducing the loss of the hosted FMS and RMS functions; there is no operational impact as the remaining FMS and RMS are taking over. Hereunder are presented the different failure cases, and the ATR recommended policy. DU1 failure: PFD is automatically displayed on DU2. ATR recommends PF is CM1, and CM2 keeps a normal configuration with two DU (PFD and MFD). DU2 failure: The automatic reversion has no effect; FMS1 and RMS1 are lost. ATR recommends PF is CM1, and CM2 keeps a normal configuration with two DU (PFD and MFD). DU3 failure: The automatic reversion depends on the coupling side selected on the FGCP (the system takes the information of PF/PNF side via the FGCP coupling selection): there is no change on the PF side, but the EWD is displayed in place of PNF MFD. PF can be CM1 as well as CM2; both pilots may display EWD on DU 2 or 4, thanks to the DISPLAY pushbuttons; in case EWD is not displayed on any DU and should a Warning or Caution occure, there will be an automatic reversion of EWD on the PM side. ATR recommends to keep EWD displayed on PF side most of the time, and PM keeps a normal configuration with two DU (PFD and MFD). Thanks to the high quality of the DU, EWD remains easily readable by PM in cross view. Mod 5948 2.02.24 PROCEDURES AND TECHNIQUES DU General Philosophy of use P4 001 APR 11 AA DU4 failure: (Symmetrical to DU2 failure) The automatic reversion has no effect; FMS2 and RMS2 are lost. ATR recommends PF is CM2, and CM1 keeps a normal configuration with two DU (PFD and MFD). DU5 failure: (Symmetrical to DU1 failure) PFD is automatically displayed on DU4. ATR recommends PF is CM2, and CM1 keeps a normal configuration with two DU (PFD and MFD). Mod 5948 2.02.24 PROCEDURES AND TECHNIQUES DU General Philosophy of use P5 001 APR 11 AA 3- DISPATCH WITH ONE DU INOPERATIVE According to MMEL, one DU among DU1, DU3 and DU5 may be inoperative for dispatch, but DU2 and 4 must be operative as they are hosting FMS and RMS functions. However all DU have the same P/N and are interchangeable; if DU2 (4) is inoperative, a maintenance action is required to swap with DU1 (5), and dispatch is then possible (refer to MEL). In case of a second DU failure, several cases have to be considered, and for each case, several solutions are possible; hereafter are presented ATR recommendations with the objectives of providing PF with the optimal displays to fly and navigate, and PM with the displays to communicate and monitor systems. 3.1. Dispatch with DU 1 INOP. PF is CM1 with PFD on DU2, and CM2 keeps a normal configuration with two DU (PFD and MFD). In case DU2 fails, the automatic reversion has no effect; FMS1 and RMS1 are lost. CM2 becomes PF, and CM1 tunes COM and NAV via MCDU; he/she can still monitor navigation and systems by cross-- view on DU4 with the recommended following configuration: DU3: EWD / DU4: MFD / DU5: PFD. In case DU3 fails, PFD remains on DU2, and EWD is automatically displayed on DU4 (PM side). PF remains CM1. ATR recommends the following: DU2: PFD / DU4: MFD (cruise)-- EWD (approach)/ DU5: PFD. In case DU4 fails, the automatic reversion has no effect; FMS2 and RMS2 are lost. The recommended configuration is the following: DU2: PFD / DU3: EWD / DU5: PFD. PNF tunes COM and NAV via MCDU, and in VMC cruise PNF may occasionally switch to MFD format. In case DU5 fails, PFD is automatically displayed on DU4. The recommended configuration is the following: DU2: PFD / DU3: EWD / DU4: PFD. PM tunes COM and NAV via MCDU, and in VMC cruise PM may occasionally switch to MFD format. CAUTION : a full flexibility is offered for display selection on DU2 and DU4 via both DISPLAY pushbuttons, and in case of DU1 and DU5 failure, the crew must avoid any configuration without any PFD. Mod 5948 2.02.24 PROCEDURES AND TECHNIQUES DU General Philosophy of use P6 001 APR 11 AA 3.2. Dispatch with DU 3 INOP. PF can be CM1 as well as CM2; both pilots may display EWD on DU 2 or 4, thanks to the DISPLAY pushbuttons; in case EWD is not displayed on any DU and should a Warning or Caution occure, there will be an automatic reversion of EWD on the PM side (the system takes the information of PF/PM side via the FGCP coupling selection). ATR recommends to keep EWD displayed on PF side most of the time, and PM keeps a normal configuration with two DU (PFD and MFD). Thanks to the high quality of the DU, EWD remains easily readable by PM in cross view. In case DU1 fails, PFD is automatically displayed on DU2 and EWD on DU4. ATR recommends PF is CM1 and the following configuration: DU2: PFD / DU4: MFD (cruise)-- EWD (approach)/ DU5: PFD. In case DU2 fails, EWD is automatically displayed on DU4; FMS1 and RMS1 are lost. ATR recommends PF is CM1 and the following configuration: DU1: PFD / DU4: MFD (cruise)-- EWD (approach)/ DU5: PFD. In case DU4 fails, EWD is automatically displayed on DU2; FMS2 and RMS2 are lost. ATR recommends PF is CM2 and the following configuration: DU1: PFD / DU2: MFD (cruise)-- EWD (approach)/ DU5: PFD. In case DU5 fails, PFD is automatically displayed on DU4, and EWD on DU2. ATR recommends PF is CM2 and the following configuration: DU1: PFD / DU2: MFD (cruise)-- EWD (approach)/ DU4: PFD. Mod 5948 2.02.24 PROCEDURES AND TECHNIQUES DU General Philosophy of use P7 001 APR 11 AA 3.3. Dispatch with DU 5 INOP. PF is CM2 with PFD on DU4, and CM1 keeps a normal configuration with two DU (PFD and MFD). In case DU1 fails, PFD is automatically displayed on DU2. The recommended configuration is the following: DU2: PFD / DU3: EWD / DU4: PFD. PM tunes COM and NAV via MCDU, and in VMC cruise PM may occasionally switch to MFD format. CAUTION : a full flexibility is offered for display selection on DU2 and DU4 via both DISPLAY pushbuttons, and in case of DU1 and DU5 failure, the crew must avoid any configuration without any PFD. In case DU2 fails, the automatic reversion has no effect; FMS1 and RMS1 are lost. The recommended configuration is the following: DU1: PFD / DU3: EWD / DU4: PFD. PM tunes COM and NAV via MCDU, and in VMC cruise PM may occasionally switch to MFD format. In case DU3 fails, PFD remains on DU4, and EWD is automatically displayed on DU2 (PM side). PF remains CM2. ATR recommends the following configuration: DU1: PFD / DU2: MFD (cruise)-- EWD (approach)/ DU4: PFD. In case DU4 fails, the automatic reversion has no effect; FMS2 and RMS2 are lost. PF must switch to CM1, and CM2 tunes COM and NAV via MCDU; he/she can still monitor navigation and systems by cross-- view on DU2 with the recommended following configuration: DU1: PFD / DU2: MFD / DU3: EWD. Mod 5948 2.02.24 PROCEDURES AND TECHNIQUES DU P8 General Philosophy of use 001 APR 11 AA 4- DUAL DC GEN LOSS In case of dual DC GEN loss, only DU2 and DU4 are operative. PFD is automatically displayed on PF side and EWD on PM side; CM2 must switch AHRS and ADC to SYS 1 to recover a normal PFD format on DU4. ATR recommends the following configuration: both-- CM1 is PF and always keeps PFD on DU2; he/she monitors navigation on mini bothboND; both-- CM2 mainly uses DU4 in PFD format, and may temporarily switch to EWD and bothboMFD ; he/she tunes VHF1 via VCP on MFD or MCDU1; both - IESI is used for attitudes, IAS and altitude monitoring, and may be used to tune bothbo VHF1 and V/ILS1; VOR, LOC and GLIDE deviations may also be displayed. In case EWD is not displayed on any DU and should a Warning or Caution occure, there will be an automatic reversion of EWD on PM side. CAUTION : a full flexibility is offered for display selection on DU2 and DU4 via both DISPLAY pushbuttons, and the crew must avoid configuration without any PFD. Mod 5948 2.03.00 NORMAL PROCEDURES P1 CONTENT 001 APR 11 AA 2.03.00 CONTENT 2.03.01 FOREWORD 2.03.02 PRELIMINARY 2.03.03 PANEL SCAN SEQUENCE 2.03.04 FLIGHT PREPARATION 2.03.05 EXTERIOR INSPECTION 2.03.06 PRELIMINARY COCKPIT PREPARATION WITH THE USE OF GPU 2.03.07 PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE 2.03.08 FINAL COCKPIT PREPARATION 2.03.09 HOTEL MODE START UP 2.03.10 BEFORE PROPELLER ROTATION 2.03.11 BEFORE TAXI 2.03.12 TAXI 2.03.13 BEFORE TAKE OFF 2.03.14 TAKE OFF 2.03.15 CLIMB - CRUISE 2.03.16 BEFORE DESCENT - DESCENT 2.03.17 APPROACH 2.03.18 BEFORE LANDING 2.03.19 LANDING 2.03.20 GO AROUND 2.03.21 AFTER LANDING 2.03.22 PARKING 2.03.23 LEAVING THE AIRCRAFT Mod 5948 . 2.03.01 NORMAL PROCEDURES P1 FOREWORD AA 001 APR 11 FOREWORD Procedures contained in this chapter are recommended by the manufacturer. They are consistent with the other chapters of this manual, in particular 2.02 PROCEDURES AND TECHNIQUE. Normal procedures are not certified by the Authorities, and in the judgment of the Manufacturer, are presented here in, as the best way to proceed from a technical and operational stand point. They are continuously updated, taking into account inputs from all operators and lessons of the Manufacturer’s own experience. In the same manner, they may be amended as needed by the Operator. However if the FCOM is used as the on board Operational Manual, the Manufacturer recommends channeling any suggested amendment through him for early publication so as to maintain the consistency of the Manual. The Operator should be aware that a complete rewriting of this chapter may be done under his own responsability but could lead to difficulties in updating and maintaining the necessary homogeneity with the other chapters of this manual. Mod 5948 . 2.03.02 NORMAL PROCEDURES P1 001 PRELIMINARY AA APR 11 PRELIMINARY The following sections provide expanded information related to normal procedures. Normal procedures consist of inspections, preparations and normal check lists. All items are listed in a sequence following a standardized scan of the cockpit panels (see section 2.03.03) except when required by the logic of actions priority, to ensure that all actions are performed the most efficient way. Normal procedures are divided into phases of flight and accomplish by recall. In the following assignation : - CM1 refers to the Crew Member in the left hand seat - CM2 refers to the Crew Member in the right hand seat - PF refers to the Pilot Flying - PM refers to the Pilot Monitoring After completion of a given procedure, the related normal check list is used. The normal check list developed by the manufacturers includes only the items that may have a direct impact on safety and efficiency if not correctly accomplished. All normal check lists are initiated at the Pilot’s flying command. Some normal procedures which are non routine will be found in chapter 2.02 PROCEDURES AND TECHNIQUE and in chapter 3.11 SPECIAL OPERATIONS. All steps have to be performed before the first flight of the day or following a crew change or maintenance action. Transit steps are the only ones to be completed after a transit stop. They are grouped in the FINAL COCKPIT PREPARATION. If there is any doubt as to whether the application of transit procedures covers all safety aspects, the complete preparation must be accomplished. Mod 5948 . 2.03.03 NORMAL PROCEDURES P1 PANEL SCAN SEQUENCE AA Mod 5948 001 APR 11 . 2.03.04 NORMAL PROCEDURES P1 FLIGHT PREPARATION AA 001 APR 11 FLIGHT PREPARATION TECHNICAL CONDITION OF THE AIRCRAFT The crew will verify the technical status of the aircraft in respect to airworthiness acceptability of malfunction and influence on the flight plan, using all necessary operator’s documents, in particular MEL (Minimum Equipment List). WEATHER BRIEFING The crew will receive a weather briefing which should include : - actual and expected weather conditions for take off and climb out including runway conditions, - en route significant weather : winds and temperatures, - terminal forecasts for destination and alternate airports, - actual weather for destination and alternates for short range flights and recent past weather if available, - survey of the meteorological conditions at airports along the planned route. NAV / COM FACILITIES EN ROUTE The crew will study the latest relevant NOTAMs (NOtice To AirMen) and will check that all required facilities at departure, destination and alternate airports are operational and that they fulfill the appropriate requirements. FLIGHT PLANS / OPERATIONAL REQUIREMENTS The crew will check the company flight plan, in respect to routing, altitudes and flight time. The crew will check the estimated load figures and will calculate maximum allowed take off and landing weights. The captain will decide the amount of fuel necessary for a safe conduct of the flight, taking into consideration possible economic fuel transportation. The captain will check ATC flight plan and ensure it is filed according to the prescribed procedures. Mod 5948 . 2.03.05 NORMAL PROCEDURES P1 EXTERIOR INSPECTION 001 FEB 12 AA INTRODUCTION The exterior inspection is primarily a visual check to ensure that the overall condition of the aircraft, the visible components and equipments are safe for the flight. R It is performed the CM1 before each flight. During exterior walk around, observe that the FLIGHT CONTROL SURFACES and FLAPS are clear and memorize surfaces position. Section content : EXTERIOR WALK AROUND DRAWING . . . . . . . . . . . . . . . . . . . . . . . . PAGE 2 MAIN LEFT LANDING GEAR AND FAIRING . . . . . . . . . . . . . . . . . . . . . PAGE 3 LEFT WING TRAILING EDGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 4 LEFT WING LEADING EDGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 4 LEFT ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 4 LEFT FORWARD FUSELAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 4 NOSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 5 RIGHT FORWARD FUSELAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 5 RIGHT ENGINE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 5 RIGHT WING LEADING EDGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 6 RIGHT WING TRAILING EDGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 6 MAIN RIGHT LANDING GEAR AND FAIRING . . . . . . . . . . . . . . . . . . . . PAGE 6 RIGHT AFT FUSELAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 7 TAIL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 7 LEFT AFT FUSELAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PAGE 7 ... / ... Mod 5948 2.03.05 NORMAL PROCEDURES P2 EXTERIOR INSPECTION 001 APR 11 EXTERIOR INSPECTION DRAWING ... / ... Mod 5948 2.03.05 NORMAL PROCEDURES P3 EXTERIOR INSPECTION 001 FEB 12 AA EXTERIOR INSPECTION ACTIONS MAIN LEFT LANDING GEAR AND FAIRING R PARKING BRAKE ACCU PRESSURE . . . . . . . . . . . . CHECK 1600 PSI MINIMUM MAINTENANCE DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED GEAR DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK WHEELS AND TIRES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION BRAKE TEMPERATURE SENSORS . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK BRAKE WEAR DETECTORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK LANDING GEAR STRUCTURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK HYDRAULIC LINES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK WHEEL WELL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK UPLOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN Note : On ground, the landing gear uplock box in closed position leads to red local UNLK alarm in the cockpit. The uplock box can be open by pulling the landing gear emergency extension handle. Then, replace it in its initial position. FREE FALL ASSISTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK SAFETY PIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REMOVED BEACON LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AIR CONDITIONING PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOCKED PACK RAM AIR INLET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UNOBSTRUCTED LANDING LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION TAT PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK MAGNETIC FUEL LEVEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN ... / ... Mod 5948 2.03.05 NORMAL PROCEDURES P4 EXTERIOR INSPECTION 001 FEB 12 AA EXTERIOR INSPECTION ACTIONS (CONT’D) LEFT WING TRAILING EDGE R FLAPS RAIL SEAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION EXHAUST NOZZLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR FLAPS POSITION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AILERON AND TAB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK STATIC DISCHARGERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK HORN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION LEFT WING LEADING EDGE NAV AND STROBE LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION WING DE--ICING BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION FUEL VENT NACA INLET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR MAGNETIC FUEL LEVEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN ICE DETECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK LEFT ENGINE R R LEFT COWLINGS . . . . . . . . . . . . . . . . . . . . . . . . . . ALL 4 LATCHES: CLOSED OIL COOLING FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ENGINE AIR INTAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR ENGINE DE--ICING BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION SPINNER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK PROPELLER . . . . . . . . . . . . . . . . FEATHERED / CONDITION / FREE ROTATION RIGHT COWLINGS . . . . . . . . . . . . . . . . . . . . . . . . . ALL 4 LATCHES: CLOSED INNER WING LEADING EDGE AND FAIRING . . . . . . . . . . . . . . . . . CONDITION LEFT FORWARD FUSELAGE R WING AND EMERGENCY LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION EMERGENCY EXIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED AVIONICS VENT OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN CARGO DOOR OPERATING PANEL DOOR . . . . . . . . . . . . . . . . . . . . CLOSED CARGO DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED AND LATCHED O2 BOTTLE OVERBOARD DISCHARGE INDICATION . . . . . . . . . . . . . . . GREEN ANGLE OF ATTACK PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION COCKPIT COMMUNICATION HATCH . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ICE EVIDENCE PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION STATIC PORTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR PITOT PROBES AND COVERS . . . . . . . . . . . . . . . . . . . . . CHECK / REMOVED ... / ... Mod 5948 2.03.05 NORMAL PROCEDURES P5 EXTERIOR INSPECTION 001 FEB 12 AA EXTERIOR INSPECTION ACTIONS (CONT’D) NOSE R R WIPERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION RADOME AND LATCHES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NOSE GEAR WHEELS AND TIRES . . . . . . . . . . . . . . . . . . . . . . . . CONDITION NOSE GEAR STRUCTURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION TAXI & TAKE OFF LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION WHEEL WELL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK FREE FALL ASSISTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK SAFETY PIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REMOVED NOSE WHEEL STEERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION HYDRAULIC LINES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION NOSE GEAR DOORS . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION, 2 CLOSED RIGHT FORWARD FUSELAGE R R PITOT PROBE AND COVER . . . . . . . . . . . . . . . . . . . . . . . CHECK / REMOVED STATIC PORTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR ANGLE OF ATTACK PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION EXTERNAL DC AND AC ELECTRICAL POWER ACCESS DOORS . . . . . . CHECK EMERGENCY EXIT DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED EMERGENCY EXIT LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION ANTENNAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK WING LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION RIGHT ENGINE R R INNER WING LEADING EDGE AND FAIRING . . . . . . . . . . . . . . . . . CONDITION LEFT COWLINGS . . . . . . . . . . . . . . . . . . . . . . . . . . ALL 4 LATCHES: CLOSED ENGINE AIR INTAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR ENGINE DE--ICING BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION SPINNER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK PROPELLER . . . . . . . . . . . . . . . . FEATHERED / CONDITION / FREE ROTATION Note : If propeller brake not set or not installed. RIGHT COWLINGS . . . . . . . . . . . . . . . . . . . . . . . . . ALL 4 LATCHES: CLOSED OIL COOLING FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ... / ... Mod 5948 2.03.05 NORMAL PROCEDURES P6 EXTERIOR INSPECTION 001 FEB 12 AA EXTERIOR INSPECTION ACTIONS (CONT’D) RIGHT WING LEADING EDGE WING DE--ICING BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION FUEL VENT NACA INLET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR MAGNETIC FUEL LEVEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN NAV AND STROBE LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION RIGHT WING TRAILING EDGE R HORN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION STATIC DISCHARGERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AILERON AND TAB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK FLAPS POSITION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXHAUST NOZZLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION FLAPS RAIL SEAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK MAIN RIGHT LANDING GEAR AND FAIRING R R R MAGNETIC FUEL LEVEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN TAT PROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK LANDING LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION AIR CONDITIONING GROUND CONNECTION . . . . . . . . . . . . . . . . . . . . CHECK PACK RAM AIR INLET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR AIR CONDITIONING PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK REFUELING CONTROL PANEL ACCESS DOOR . . . . . . CLOSED AND LATCHED GEAR DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK LANDING GEAR STRUCTURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK HYDRAULIC LINES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK WHEEL WELL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK UPLOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN FREE FALL ASSISTER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK SAFETY PIN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REMOVED WHEELS AND TIRES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION BRAKE WEAR DETECTORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK BRAKE TEMPERATURE SENSORS . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK REFUELING POINT ACCESS DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ... / ... Mod 5948 2.03.05 NORMAL PROCEDURES P7 EXTERIOR INSPECTION 001 FEB 12 AA EXTERIOR INSPECTION ACTIONS (CONT’D) RIGHT AFT FUSELAGE R VHF ANTENNAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SERVICE DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TAIL PROP AND TAIL SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OUTFLOW VALVES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CHECK CHECK CHECK TAIL FLIGHT CONTROLS ACCESS DOOR . . . . . . . . . . . . . . . . . . . . . . . . . LOCKED VOR ANTENNAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK STABILIZER DE--ICING BOOTS . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION LOGO LIGHTS (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK HORNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION STABILIZER, ELEVATORS AND TABS . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK STATIC DISCHARGERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK FIN, RUDDER AND TAB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK TAIL CONE, NAV AND STROBE LIGHTS . . . . . . . . . . . . . . . . . . . . . . . CHECK VORTEX GENERATORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK LEFT AFT FUSELAGE WATER SERVICE PANEL ACCESS DOOR . . . . . . . . . . . . . . . . . . . . . CLOSED TOILET SERVICE PANEL ACCESS DOOR . . . . . . . . . . . . . . . . . . . . . CLOSED CABIN DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ENTRY EMER LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONDITION Mod 5948 . 2.03.06 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION P1 WITH THE USE OF GPU 001 APR 11 AA CM2 - EMERGENCY EQUIPMENT.......................................................................CHECK Check : - Exit hatch closed, handle locked and safe tied, escape rope stowed - Life jackets (if applicable) stowed - Axe, flash lights, smoke goggles and oxygen masks stowed - Portable fire extinguisher safe tied and pressure within green area - Landing gear emergency extension handle stowed, cover closed - Protective gloves - GEAR PINS and COVERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON BOARD - All Circuits Breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - PL1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI - GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE / ON Check GUST LOCK is properly engaged to fullfill the required conditions for PROP BRAKE activation. - CL 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL S/O - FLAPS LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET Set in accordance with Actual Flap position. CAUTION Do not pressurize hydraulic systems and activate flaps without clearance from ground crew. - LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN - EEC 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED IN - BOTH WIPERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - BATTERY (Toggle switch) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Check battery voltage on captain lateral console) - MFC AUTO TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check : - MFC 1A, 2A flashing (only if cargo door panel is closed), then MFC 1B, 2B flashing. - EMER & ESS BUS SUPPLY INDICATOR . . CHECK ARROWS ILLUMINATED Check battery voltage on captain lateral console. - UNDV Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED Check battery voltage on Captain lateral console. - IESI, DU 2&4, MCDU 1 ELECTRICALLY SUPPLIED . . . . . . . . . . . . . . CHECK Mod 5948 2.03.06 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION P2 001 WITH THE USE OF GPU APR 11 AA - AVIONIC INITIALIZATION TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check Oral Warning, Caution, CRC sounds, - Check DU 2, 4 display a green ”T” - Check DU Brightness - Check MCDU 1 ON - GPU - DC EXT PWR P/B . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED / ON Check AVAIL green light is illuminated, then depress the EXT PWR P/B : - Check on OVERHEAD Panel - BTC on line, - EMER and MAIN BAT charging, - EMER and ESS BUS supply indicator amber arrow extinguished, - UNDV light extinguished - DU BRIGHTNESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - IESI ALIGNMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - ALERTING WINDOWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / CLR - OVERHEAD PANEL SCAN . . . . . . . . . . . . . ANY WHITE LIGHT EXTINGUISH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXCEPT PROBES HTG & FUEL PUMPS - ANNUNCIATOR LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST Check all Lights are illuminated (led test only) - DOME LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQRD - STBY COMPASS LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK and OFF - STORM LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK and OFF - CALL & SELCAL (If installed) . . . . . . . . . . . . CHECK LIGHT EXTINGUISHED - MIN CAB LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - FUEL PUMP & X FEED TESTS . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM FUEL PUMP & X FEED TESTS Select ENG SD page on MFD prior to test start up. - Initial set up : ENG PUMP 1 & 2 OFF Check the following on OVERHEAD Panel + associated ENG SD page : - FEED LO PR LIGHT ENG 1 + 2 . . . . . . . . . . . . . . . . . CHECK ILLUMINATED - ENG 2 PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON - RUN LIGHT ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED - FEED LO PR LIGHT ENG 2 . . . . . . . . . . . . . . . . . . . . EXTINGUISHED Mod 5948 2.03.06 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH THE USE OF GPU AA P3 001 FEB 12 - FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED - FUEL X FEED VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN LINE - MEMO PANEL DISPLAY FUEL X FEED LABEL . . . . . . . . DISPLAYED CYAN R Note: - X FEED LABEL may be flashing CYAN, in case of fuel unbalance & wrong R pump on selection. R - Check “X FEED” cyan label on MEMO PANEL DISPLAY - FEED LO PR LIGHT ENG 1+2 . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASED - FEED LO PRESS LIGHT ENG 1 . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED Note : Feed Lo Press Light may take few minutes to illuminate again - ENG 1 PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON R - RUN LIGHT ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED - FEED LO PR LIGHT ENG 1+2 . . . . . . . . . . . . . . . . . . EXTINGUISHED - ENG 1+2 FUEL PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON - DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST DOOR TEST : Depress TEST switch and check on OVERHEAD Panel. Check associated AIR CABIN SD page : - CAB OK & SVCE OK green lights . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATE (Provided associated doors are opened) - SPOILER LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED - LDG GEAR INDICATOR . . . . . . . . . . . . . . CHECK 3 GREEN / NO RED LIGHT - TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO - FLT CTL Fault Light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - SELCAL (If installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CODE - ENG 1 FIRE TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM ENGINE FIRE PROTECTION TEST : Check the following items : - ENG 1 FIRE HANDLE . . . . . . . . . . . . . . . . . . . IN / LATCHED / LOCK WIRED - Any lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - Depress SQUIB TEST P/B and check : - Both agents SQUIB lights . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATE - Select TEST SW on FAULT position and check : - Associated LOOP A and LOOP B lights . . . . . . . . . . . . . . ILLUMINATE - SC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS - MC Amber light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - LOOP (FWS ALERTING WINDOW) . . . . . . . . . . . DISPLAYED AMBER - Select TEST SW on FIRE position and check : - Associated FIRE HANDLE red light . . . . . . . . . . . . . . . . ILLUMINATES - CRC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS - MW light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - ENG 1 FIRE (EWD + FWS WINDOW) . . . . . . . . . . . DISPLAYED RED - Press MW to silence CRC and extinguish the MW : - Temporarily select CL out of FUEL S O Position and check : - Associated CL FUEL S O red light . . . . . . . . . . . . .ILLUMINATES Mod 5948 2.03.06 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH THE USE OF GPU P4 001 FEB 12 AA R - EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD - PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON / LOCKED Check PROP BRK Local Cyan light + EWD Cyan label - ENG START Rotary selector . . . . . . . . . . . . . . . . . . . . . . OFF/START ABORT - MAIN ELEC PWR Panel + associated ELEC SD page on MFD . . . . . . CHECK - CVR and SSFDR TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM CVR TEST : CVR and DFDR test, on GPU: Press on the RCDR PB (on the RCDR panel) and check ON light is illuminated. CVR: when pushing on the CVR TEST PB, the CVR pointer has to be in the green arc. Press on the RESET PB (on the RCDR panel) and check ON light is extinguished. - SIGNS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Also check the MEMO PANEL - EMER EXIT LT TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARM - EMER EXIT LT DISARM light . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - DE ICING / ANTI ICING lights . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED Except AFR AIR BLEED Amber light illuminated. - PROBES HEATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .OFF Switch off PROBES HEATING to avoid any burn injury to ground crew. (STBY PITOT TUBE is supplied by DC STBY BUS.) R - WINDSHIELD HEATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON - AC WILD ELEC PWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check on OVERHEAD Panel and associated ACW - HYD SD page - HYD PWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check on OVERHEAD panel : - BLUE and GREEN PUMPS LO PR AMBER lights . . . . . ILLUMINATED - Other LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED Check on ACW-- HYD SD Page on MFD : - BLUE and GREEN PUMPS LO PR . . . . . . . . . . . . . . . . . . . . . . . . . . AMBER - FLAPS, SPOILERS, PROP BRK, N/W STRG . . . . . . . . . . . . . . . . . . AMBER - EMER BRK ACCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - NORM BRK, LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AMBER - EMER LOC XMTR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO / NO LIGHT Check toggle SW is in AUTO position, guarded and lock wired R - ANN LT SW Position. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD Mod 5948 2.03.06 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH THE USE OF GPU P5 001 FEB 12 AA - AIR BLEED / COMPT TEMP Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check on OVERHEAD Panel & associated AIR CABIN SD page - AVIONICS VENT / OVBD VALVE . . . . . . . . . . . . . . . . . . . . AUTO / GUARDED - OXYGEN PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check on OVERHEAD Panel & associated AIR CABIN SD page - OXYGEN PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - OXYGEN MAIN SUPPLY ON OVERHEAD Panel . . . . . . . . . . . . . . . . . ON Check OXY SUPPLY CREW on AIR CABIN SD page . . . . . GREEN ARROW - PAX SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NO LIGHT - COMPT SMK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST Depress SMK TEST P/B and check : - On Alerting Window : AFT SMK, FWD SMK, ELEC SMK . . . . . . . . . . . . RED - On AIR CABIN SD page : LAV SMK, AFT COMPT SMK, FWD SMK, ELEC SMK RED - MW + MC + CRC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ACTIVATE - Press MW to silence the alarm - AVIONICS VENT EXHAUST MODE P/B . . . . . . . . . . . . . . . . . . . . . . . . RESET When test is over, press the exhaust P/B to restart the extract fan. (MECH call with sound during reset) - ENG 2 FIRE TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM PEDESTAL - ATPCS TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM R ATPCS: STATIC TEST Check the following results on EWD. - Turn the ATPCS knob to the left to the arm position and check : - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - TQ needles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . > 60 % - Turn the ATPCS knob to ENG 1 position and check : - ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPTRIM - TQ 1 needle indicates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ZERO - After 2.15 s : - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES - ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO FTR - Turn the ATPCS knob to the right to the arm position and check : - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - TQ needles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . > 60 % .../... Mod 5948 2.03.06 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH THE USE OF GPU P6 001 FEB 12 AA - Turn the ATPCS knob to ENG 2 position and check : - ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPTRIM - TQ 2 needle indicates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ZERO - After 2.15s : - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES - ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO FTR - TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK TRIMS TEST R TRIMS TEST TRIMS CHECK BEFORE EACH FLIGHT PITCH, ROLL AND YAW TRIM OPERATION . . . . . . . . . . . . . . . . . . . . CHECK STBY PITCH TRIM OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK STBY PITCH TRIM SW . . . . . . . . . . . . . CHECK GUARDED / OFF POSITION TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET FOR TAKE OFF TRIMS CHECK FOR THE FIRST FLIGHT OF THE DAY : (DAILY) refer to 2.03.24 - IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check the IDLE GATE FAIL amber light is extinguished. Check the IDLE GATE lever amber band is visible. - EMER AUDIO CANCEL . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK GUARDED - PARKING BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON Check ACCU BRAKE pressure on the dedicated indicator (Captain lateral console) or on SD ACW-- HYD Page. Use HYD AUX PUMP P/B if required. WARNING Do not pressurize hydraulic systems without cleareance from ground crew. - GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .ON - VCP : COM, NAV, SURV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CHECK - NAV ND OVLY / TRAFFIC set to ABOVE position - SURV / XPDR 1 or 2 set to STBY - TCAS set to AUTO Mod 5948 2.03.06 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH THE USE OF GPU P7 001 FEB 12 AA - MCDU BRIGHTNESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY Check “WAIT or STBY” green message on ND/PFD. - COCKPIT DOOR LOCKING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R COCKPIT DOOR DAILY CHECK: . . . . . . . . . . . . . . . . . . . . . . . . refer to 2.03.24 R CENTRAL PANEL - ICE DETECT PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST/ CHECK - STICK PUSHER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO LIGHT - APM P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO LIGHT - APM TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM APM TEST: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . refer to 2.03.24 - PEC 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED IN/NO LIGHT - BOOST (If installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK BOOST TEST: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . refer to 2.03.24 - PWR MGT rotary selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO - IESI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK NO FLAG - EWD : - EWD FLIGHT CONTROL window . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check TRIMS and FLAPS, indications - ENG 1 & 2 INSTRUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Check TQ, RTO TQ, TO TQ, NP, ITT - TAT / SAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK ENG PANEL : - EEC 1&2 P/B . . . . . . . . . . . . . . . . . . . CHECK DEPRESSED IN / NO LIGHT - ATPCS P/B . . . . . . . . . . . . . . . . . . . . . CHECK DEPRESSED IN / NO LIGHT - CAB PRESS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check no light Check the rotary selector is facing the green mark Mod 5948 2.03.06 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION P8 WITH THE USE OF GPU 001 FEB 12 AA R - AUTO PRESS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST / CHECK Depress the TEST P/B and check : - On local panel : - Cycling display between - 8800 and 18800 . . . . . . . . . . . . . . . CHECK - MC + SC + AIR AUTO PRESS on Alerting Window (1 flash) . . . CHECK - MODE SEL P/B FAULT amber light (1 flash) . . . . . . . . .ILLUMINATED - CABIN SD page : CAB ALT / VS / ∆P . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - LANDING GEAR INDICATIONS . . . . . . . . . . . . . . . . . . 3 GREEN / NO RED LT ANTISKID PANEL P/B depressed in, no LIGHT . . . . . . . . . . . . . . . . . . . CHECK GLARESHIELD : - GPWS P/B TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .PERFORM CAPTAIN LATERAL CONSOLE - COCKPIT COM HATCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN Cockpit com hatch must be opened until engine 1 start, in order to avoid that the extract fan suction creates a depressurisation when passenger doors is closed. (Ref. procedure and techniques 2.02.03). - MAINTENANCE PANEL - STICK PUSHER / SHAKER TEST (once a day) . PERMORM (refer to 2.03.24) - ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NORM FLT - N/W STEERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AS RQD - OXYGEN MASK (once a day) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OXYGEN MASK TEST (Hose and mask must be pressurized with oxygen) - DO NOT REMOVE OXYGEN MASK Mod 5948 2.03.06 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION P9 001 WITH THE USE OF GPU FEB 12 AA R - AUDIO CONTROL PANEL INT / RAD selector . . . . . . . . . . . . . . . . . . . . . . INT 1 - PRESS TO TEST & RESET P/B . . . . . . . . . . . . . . . . . . . . . . PRESS & HOLD Check : - Blinker momentarily turns yellow and then goes black (if no leak). - Oxygen flow sounds through loudspeakers 2 - PRESS TO TEST AND RESET PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD RED GRIPS ON EACH SIDE OF THE HOSE . . . . . . . . . . . . . SQUEEZE Check : - Oxygen pressure inflates the harness. - Blinker momentarily turns yellow and must turn dark if there is no leak. - Oxygen flow sounds through loudspeakers 3 - PRESS TO TEST AND RESET PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD EMERGENCY KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT Check : - Blinker momentarily turns yellow and must turn dark if there is no leak - Oxygen flow sounds through loudspeakers. CAUTION: WHEN TEST COMPLETED : Insure the oxygen mask control panel remain in the following position : - OXY LO PR LIGHT . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED - N/100% ROCKER LEVER . . . . . . . . . . . . . SET TO 100 % - CAPTAIN SWITCHING PANEL : - AUDIO 1 SEL Light . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED - ATT/HDG, ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED - TAWS PANEL : - TERR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GUARDED NO LIGHT - GPWS TOGGLE SWITCH . . . . . . . . . . . . . GUARDED / NORMAL POSITION - GPWS Associated light . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED CAPTAIN INSTRUMENT PANEL - CLOCK TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - PFD : - FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - AIRSPEED, ALTIMETER, VSI. . . . . . . . . . . . . . . . . . . . . . CHECK NO FLAG - EADI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ATTITUDE - EHSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Mod 5948 2.03.06 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH THE USE OF GPU P 10 001 FEB 12 AA R - ND / EHSI : (Select ND on MFD) - HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK & NO FLAG - MEMO PANEL DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK F/O LATERAL CONSOLE - EXTRACT AIRFLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN / GUARDED - OXYGEN MASK (once a day) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK F/O SWITCHING PANEL : - AUDIO SEL 2 Light . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK EXTINGUISHED - ATT/HDG, ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED - ELAPSE TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET F/O INSTRUMENT PANEL - CLOCK TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - PFD : - FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - AIRSPEED, ALTIMETER, VSI . . . . . . . . . . . . . . . . . . . . . CHECK NO FLAG - EADI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ATTITUDE - ND / EHSI : (Select NAV Display on MFD) - HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK & NO FLAG - MEMO PANEL DISPLAY.......CHECK - SYS PAGE - AC/DC ELEC Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - CABIN Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - ACW HYD Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - ENGINE Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION P1 WITH HOTEL MODE AA 001 APR 11 CM2 - EMERGENCY EQUIPMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check : - Exit hatch closed, handle locked and safe tied, escape rope stowed - Life jackets (if applicable) stowed - Axe, flash lights, smoke goggles and oxygen masks stowed - Portable fire extinguisher safe tied and pressure within the green area - Landing gear emergency extension handle stowed, cover closed - Protective gloves - GEAR PINS and COVERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON BOARD - All Circuit Breakers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI - GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE / ON Check GUST LOCK is properly engaged to fullfill the required conditions for PROP BRAKE activation. - CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL S/O - FLAPS LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET Set in accordance with Actual Flap Position. CAUTION Do not pressurize hydraulic systems and activate flaps without clearance from ground crew. - LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN - EEC 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED IN - BOTH WIPERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - BATTERY (Toggle switch) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Check battery voltage on captain lateral console - MFC AUTO TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORMED Check : MFC 1A, 2A flashing (only if cargo door panel is closed), then MFC 1B, 2B flashing) - EMER & ESS BUS SUPPLY INDICATOR . . CHECK ARROWS ILLUMINATED - UNDV light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED Check battery voltage on Captain lateral console. - IESI, DU 2&4, MCDU 1 ELECTRICALLY SUPPLIED . . . . . . . . . . . . . . CHECK Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE P2 001 APR11 AA - AVIONIC INITIALIZATION TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check Oral Warning, Caution, CRC sounds, - Check DU 2, 4 display a green “T” - Check DU Brightness - Check MCDU 1 ON - IESI ALIGNMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - ALERTING WINDOWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / CLR - ENG 2 FIRE TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM ENGINE FIRE PROTECTION TEST : Check the following items : - ENG 2 FIRE HANDLE . . . . . . . . . . . . . . IN / LATCHED / LOCK WIRED - Any lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - Depress SQUIB TEST P/B and check : - Both agents SQUIB lights . . . . . . . . . . . . . . . . . . . . . . ILLUMINATE - Select TEST SW on FAULT position and check : - Associated LOOP A and LOOP B lights . . . . . . . . . . . . ILLUMINATE - SC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS - MC Amber light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - LOOP (EWD + ALERTING WINDOW) . . . . . . . DISPLAYED AMBER - Select TEST SW on FIRE position and check : - Associated FIRE HANDLE red light . . . . . . . . . . . . . . ILLUMINATES - CRC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS - MW light flashing red . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - ENG 2 FIRE (EWD + ALERTING WINDOW) . . . . DISPLAYED RED - Press MW to silence CRC and extinguish the MW - Temporarily select CL out of FUEL S O Position and check : - Associated CL FUEL S O red light . . . . . . . . . . . . . ILLUMINATES Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE AA P3 001 APR 11 - ATPCS TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM ATPCS TEST : Check the following results on EWD : - Turn the ATPCS knob to the left to the arm position and check : - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - TQ needle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . > 60 % - Turn the ATPCS knob to ENG 1 position and check : - ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPTRIM - TQ 1 needle indicates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ZERO - After 2.15s : - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES - ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO FTR - Turn the ATPCS knob to the right to the arm position and check : - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - TQ needles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . > 60 % - Turn the ATPCS knob to ENG 2 position and check : - ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPTRIM - TQ 2 needles indicates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ZERO - After 2.15s : - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES - ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO FTR - SERVICE DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED - FUEL PUMP 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Check RUN LIGHT ON + FEED LO PRESS extinguished - WING LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON - PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON / LOCKED Check PROP BRK Local Cyan light + EWD Cyan label - ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START IN HOTEL MODE CAUTION Prior to any engine start, select ENG SD page Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE AA P4 001 FEB 12 START SEQUENCE: - ENGINE PROP AREA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CLEAR - ENGINE START rotary selector . . . . . . . . . . . . . . . . . . . . . . . . . START A + B A+B for the 1st flight of the day, then A or B for the next start - START 2 P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED / ON Start timing for maximum starter run time Check : - START P/B ON light illuminates - START green label on ENG SD page. - ENGINE ROTATION (NH) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR S When passing 10 % NH (maximum 19% NH if ITT > 200°c) : - CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR - TIMING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - ITT rises within 10s . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R ENGINE START IN HOT ENVIRONMENT In hot environments to prevent an engine starting from a “hot start“: High OAT or High residual ITT, it is recommended to delay the fuel opening up to 20% NH.For residual ITT below 100°C, open fuel up to 10% NH. From 100°C to 200°C delay fuel opening by 1% NH per 10°C of residual ITT, up to 200°C (20% NH) Do not exceed 20% NH for fuel opening. CAUTION - If ITT >950°c - If 840 < ITT < 950°C for more than 5s - If 800 C°° < ITT < 840°C for more than 20s R R R R } CL..................FUEL SO } CL..................FUEL SO } CL..................FUEL SO S When passing 45 % NH : - Check: - START green label EXTINGUISHES on FUEL-- ENG SD page - START P/B ON light extinguished - Check maximum start time and max ITT (Refer to Limitation chap 2.01.04) S When engines parameters are stabilized : - ENGINE START ROTARY SELECTOR . . . . . . . . OFF/START ABORT - GPU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - DC GEN 2 FAULT LIGHT . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - DC BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED - BLEED / PACK / X VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN - PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST AS RQD GIf Z > 5000ft and SAT > ISA + 25C°, advance PL 2 up to the GUST LOCK stop. Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE P5 001 FEB 12 AA R - OVERHEAD PANEL SCAN . . . . . . . . . . . . . ANY WHITE LIGHT EXTINGUISH R EXCEPT PROBES HTG & FUEL PUMP R - ANNUNCIATOR LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST R Check all Lights are illuminated (led test only) R - DOME LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD R - STBY COMPASS LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AND OFF R - STORM LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AND OFF - CALL & SELCAL (If installed) . . . . . . . . . . . . CHECK LIGHT EXTINGUISHED - MIN CAB LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - FUEL PUMP & X FEED TESTS . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM FUEL PUMP & X FEED TESTS Select FUEL-- ENG SD page on MFD prior to test start up. Initial set up : ENG PUMP 1 OFF Check the following on OVERHEAD panel + associated FUEL-- ENG SD page : - FEED LO PR LIGHT ENG 1 . . . . . . . . . . . . . . . . . . . . CHECK ILLUMINATED - ENG 2 PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON - RUN LIGHT ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATED - FEED LO PR LIGHT ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED - FUEL X FEED VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN LINE - MEMO PANEL DISPLAY FUEL X FEED LABEL . . . . . . . . ILLUMINATE CYAN Note: X FEED LABEL may be flashing CYAN, in case of fuel unbalance & wrong pump on selection. Check “X FEED” blue cyan on MEMO PANEL. - FEED LO PR LIGHT ENG 1+2 . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REALEASED - FEED LO PR LIGHT ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . .ILLUMINATED Note : Feed Lo Press Light may take few minutes to illuminate again. - ENG 1 PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON - FEED LO PR LIGHT ENG 1+2 . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - ENG 1+2 FUEL PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON - DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST DOOR TEST : Depress TEST switch and check on OVERHEAD Panel and associated AIR SD page : - CAB OK & SVCE OK green lights . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATE (provided associated doors are opened) - SPOILER LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / EXTINGUISED - LDG GEAR INDICATOR . . . . . . . . . . . . . . CHECK 3 GREEN / NO RED LIGHT Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE P6 001 FEB 12 AA - TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .AUTO - FLT CTL Fault light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - SELCAL (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CODE - ENG 1 FIRE TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM ENGINE FIRE PROTECTION TEST : Check the following items : - ENG 1 FIRE HANDLE . . . . . . . . . . . . . . . . . . . . IN / LATCHED / LOCK WIRE - Any lights . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - Depress SQUIB TEST P/B and check : - Both agents SQUIB lights. . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATE - Select TEST SW on FAULT position and check : - Associated LOOP A and LOOP B lights . . . . . . . . . . . . . . ILLUMINATE - SC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS - MC Amber light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - LOOP (ALERTING WINDOW) . . . . . . . . . . . . . . . DISPLAYED AMBER - Select TEST SW on FIRE position and check : - Associated FIRE HANDLE red light . . . . . . . . . . . . . . . . ILLUMINATES - CRC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS - MW light flashing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - ENG 1 FIRE (EWD + ALERTING WINDOW) . . . . . . DISPLAYED RED - Press MW to silence CRC and extinguish the MW - Temporarily select CL out of FUEL S O Position and check : - Associated CL FUEL S O red light . . . . . . . . . . . . . . . ILLUMINATES - EXTERNAL LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQRD - ENG START Rotary selector . . . . . . . . . . . . . . . . . . . . . OFF / START ABORT - MAIN ELEC PWR Panel + associated ELEC SD page on MFD . . . . . . CHECK DC GEN 2 extinguished. BTC on line, EMER and MAIN BAT charging, EMER and ESS BUS supply indicator amber arrow extinguished, UNDV light extinguished. - CVR and SSFDR TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM R CVR TEST :CVR and DFDR test (On BATTERY MODE or HOTEL MODE): R CVR: when pushing on the CVR TEST PB, the CVR pointer has to be in the green arc. R DFDR: the status SYST light (on the FDEP or RCDR panel) has to be extinguished. R Note: it can take over 1 minute to be extinguished after aircraft power up. Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE P7 001 FEB 12 AA - SIGNS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Also check the MEMO PANEL - EMER EXIT LT TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARM - EMER EXIT LT DISARM light . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - DE ICING / ANTI ICING Lights . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED Except AFR AIR BLEED Amber light illuminated. - PROBES HEATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Switch off PROBES HEATING to avoid any burn injury to ground crew. R (STBY PITOT TUBE is supplied by DC STBY BUS). R - WINDSHIELD HEATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON - AC WILD ELEC PWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check on OVERHEAD Panel and associated ACW-- HYD SD page - HYD PWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check on OVERHEAD panel : - BLUE and GREEN PUMPS LO PR AMBER lights . . . . . . . . . . ILLUMINATED - Other LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED Check on ACW-- HYD SD Page on MFD Check on HYD SD Page on MFD : - BLUE and GREEN PUMPS LO PR . . . . . . . . . . . . . . . . . . . . . . . . . . AMBER - FLAPS, SPOILER, PROP BRK, N/W STRG . . . . . . . . . . . . . . . . . . . . AMBER - EMER BRK ACCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - NORM BRK, LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AMBER - EMER LOC XMTR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO / NO LIGHT Check toggle SW is in AUTO position, guarded and lock wired - ANN LT SW Position . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD - AIR BLEED / COMPT TEMP Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check on OVERHEAD Panel & associated CABIN SD page - AVIONICS VENT / OVBD VALVE . . . . . . . . . . . . . . . . . . . . AUTO / GUARDED - OXYGEN PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check on OVERHEAD Panel & associated CABIN SD page - OXYGEN PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - OXYGEN MAIN SUPPLY ON OVERHEAD Panel . . . . . . . . . . . . . ON Check OXY SUPPLY CREW on CABIN SD page . . . . . GREEN ARROW - PAX SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NO LIGHT Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE P8 001 FEB 12 AA - COMPT SMK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST Depress SMK TEST P/B and check : - On Alerting Window : AFT SMK, FWD SMK, ELEC SMK . . . . . . . . . . . . RED - On CABIN SD page: LAV SMK, AFT COMPT SMK, FWD SMK, ELEC SMK....RED - MW + MC + CRC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ACTIVATE - Press MW to silence the alarm - AVONICS VENT EXHAUST MODE P/B . . . . . . . . . . . . . . . . . . . . . . . . RESET When test is over, press the exhaust P/B to restart the extract fan. (MECH call will sound during reset). PEDESTAL - TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R TRIMS TEST TRIMS CHECK BEFORE EACH FLIGHT PITCH, ROLL AND YAW TRIM OPERATION . . . . . . . . . . . . . . . . . . . . CHECK STBY PITCH TRIM OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK STBY PITCH TRIM SW . . . . . . . . . . . . . CHECK GUARDED / OFF POSITION TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET FOR TAKE OFF TRIMS CHECK FOR THE FIRST FLIGHT OF THE DAY : (DAILY) refer to 2.03.24 - IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check the IDLE GATE FAIL amber light is extinguished Check the IDLE GATE lever amber band is visible - EMER AUDIO CANCEL . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK GUARDED - PARKING BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Check ACCU BRAKE pressure on the dedicated indicator (Captain lateral console) or on SD ACW-- HYD Page. Use HYD AUX PUMP P/B if required. WARNING Do not pressurize hydraulic systems without clearance from ground crew. Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE P9 001 FEB 12 AA - GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON - VCP : COM, NAV, SURV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CHECK - NAV ND OVLY / TRAFFIC set to ABOVE position - SURV / XPDR 1 or 2 set to STBY - TCAS set to AUTO - MCDU BRIGHTNESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY Check “STBY” message on ND/PFD. R - COCKPIT DOOR LOCKING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . . CHECK COCKPIT DOOR DAILY CHECK . . . . . . . . . . . . . . . . . . . . . . . . . refer to 2.03.24 Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE P 10 001 FEB 12 AA CENTRAL PANEL R - ICE DETECT PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST / CHECK - STICK PUSHER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO LIGHT - APM P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO LIGHT R - APM TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM APM Test (daily) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . refer to 2.03.24 - PEC 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED IN/NO LIGHT - BOOTS (If installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - PWR MGT rotary selector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO - IESI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO FLAG - EWD : - EWD FLIGHT CONTROL window . . . . . . . . . . . . . . . . . . . . . CHECK Check TRIMS and FLAPS, indications - ENG 1 & 2 INSTRUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check TQ, RTO TQ, TO TQ, NP, ITT - TAT / SAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ENG PANEL : - EEC 1 & 2 P/B . . . . . . . . . . . . . . . . . . CHECK DEPRESSED IN / NO LIGHT - ATPCS P/B . . . . . . . . . . . . . . . . . . . . . CHECK DEPRESSED IN / NO LIGHT - CAB PRESS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check no light Check the rotary selector is facing the green mark Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION P 11 WITH HOTEL MODE 001 FEB 12 AA - AUTO PRESS PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TEST / CHECK Depress the TEST P/B and check - On local panel : - Cycling display between - 8800 and 18800 . . . . . . . . . . . . . . . CHECK - MC + SC + AIR AUTO PRESS on Alerting Window (1 flash) . . . CHECK - MODE SEL P/B FAULT amber light (1 flash) . . . . . . . . . ILLUMINATED - CABIN SD page : CAB ALT / VS / ∆P . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ANTISKID PANEL P/B depressed in, no LIGHT . . . . . . . . . . . . . . . . . . . CHECK GLARESHIELD : - GPWS P/B TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM CAPTAIN LATERAL CONSOLE - COCKPIT COM HATCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN Cockpit com hatch must be opened until engine 1 start, in order to avoid that the extract fan suction creates a depressurization when passenger doors is closed, (ref procedure and techniques 2.02.03). - MAINTENANCE PANEL R - STICK PUSHER / SHAKER (once a day) . . . . . . . PERFORM (refer to 2.03.24) - ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NORM FLT - N/W STEERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQRD - OXYGEN MASK (once a day) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OXYGEN MASK TEST (Hose and mask must be charged with oxygen) - DO NOT REMOVE OXYGEN MASK Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE P 12 001 FEB 12 AA - AUDIO CONTROL PANEL INT / RAD selector . . . . . . . . . . . . . . . . . . . . . INT 1 - PRESS TO TEST & RESET PB . . . . . . . . . . . . . . . . . . . . . PRESS & HOLD - Check : - Blinker momentarily turns yellow and then goes black (if no leak) - Oxygen flow sounds through loudspeakers 2 - PRESS TO TEST AND RESET PB. . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD RED GRIPS ON EACH SIDE OF THE HOSE . . . . . . . . . . . SQUEEZE Check : - Oxygen pressure inflates the harness. - Blinker momentarily turns yellow and must turn dark if there is no leak. - Oxygen flow sounds through oudspeakers 3 - PRESS TO TEST AND RESET PB . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD EMERGENCY KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT Check : - Blinker momentarily turns yellow and must turn dark if there is no leak - Oxygen flow sounds through loudspeakers. CAUTION WHEN TEST COMPLETED : Insure the oxygen mask control panel remain in the following position : - OXY LO PR LIGHT . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED - N/100% ROCKER LEVER . . . . . . . . . . . . . SET TO 100 % R - CAPTAIN SWITCHING PANEL : R - AUDIO 1 SEL Light . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED - ATT/HDG, ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISED - TAWS PANEL : - TERR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GUARDED NO LIGHT - GPWS TOGGLE SWITCH . . . . . . . . . . . . . GUARDED / NORMAL POSITION - GPWS Associated light . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED Mod 5948 2.03.07 NORMAL PROCEDURES PRELIMINARY COCKPIT PREPARATION WITH HOTEL MODE P 13 001 FEB 12 AA CAPTAIN INSTRUMENT PANEL - CLOCK TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - PFD - FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - AIRSPEED, ALTIMETER, VSI . . . . . . . . . . . . . . . . . . . . . CHECK NO FLAG - EADI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ATTITUDE R - EHSI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - ND / EHSI : (Select ND on MFD) - HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK & NO FLAG R - MEMO PANEL DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK F/O LATERAL CONSOLE - EXTRACT AIRFLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN / GUARDED - OXYGEN MASK (once a day) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - AUDIO SEL 2 Light . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED - F/O SWITCHING PANEL : - ATT/HDG, ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED - ELAPSE TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET F/O INSTRUMENT PANEL - CLOCK TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - PFD - FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - AIRSPEED, ALTIMETER, VSI . . . . . . . . . . . . . . . . . . . . . CHECK NO FLAG - EADI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ATTITUDE - ND / EHSI : (Select NAV display on MFD) R R R R R R - HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK & NO FLAG - MEMO PANEL DISPLAY.......CHECK - SYS PAGE - AC/DC ELEC Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - CABIN Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - ACW HYD Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - ENGINE Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Mod 5948 . 2.03.08 NORMAL PROCEDURES P1 FINAL COCKPIT PREPARATION 001 APR 11 AA CM2 - ATIS INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN - TAKE OFF DATA CARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1st PART FILL 1st part : Weather, W lim according to performance computation, ACC ALT, Single Eng flight path - LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET PF FMS INITIAL PREPARATION : PF should run through the 3 following steps to prepare the FMS : 1 - FMS INITIALIZATION 2 - NAVIGATION 3 - PERFORMANCE 1 - FMS INITIALIZATION : At power up, check FMS starts correctly,by checking the following TESTs results. Note : If “Power up” page doesn’t come : - Press MENU key on the MCDU - Select FMS 1 on left side : FMS 2 on right side Mod 5948 2.03.08 NORMAL PROCEDURES P2 FINAL COCKPIT PREPARATION AA 001 APR 11 - INITIALIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - CONF DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OK - NAV DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OK - STD DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .CHECK Check STD DATA base expiry date. It out of date, swap database on NAV DATA page or ask for new database loading. .0 - Press INIT Lsk to open the INIT page FMS initialization should be prepared using the following flow, performed from INIT page. Note : INIT page can be displayed at any time by : - Pressing DATA Key, - Pressing INIT .1 UNITS > - Press UNITS Lsk (see illus point 1 ) - UNITS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK In order to avoid any confusion due to previous crew insertions, check all items of the UNIT page. .2 < POS INIT - Press POS INIT Lsk - POSITION INIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CHECK On POS INIT page : - Check that LOCALIZATION MODE is BCP (GPS GREEN) and - Initialize position : INIT POS = GPS POS, then Press on SENSORS INIT to activate it Mod 5948 2.03.08 NORMAL PROCEDURES P3 FINAL COCKPIT PREPARATION 001 APR 11 AA 2 - NAVIGATION : .3 < FPLN INIT - Press FPLN UNIT Lsk - Enter the ROUTE : - Press on F-- PLN INIT then on ROUTE - Enter the ROUTE, using the route IDENT or FROM/TO - Enter the FLT ID - Press EXEC to activate F-- PLN - Enter the RWY, SID, TRANS wpt - Enter route WPT and AIRWAYS - Enter the ARRIVAL RWY, STAR, TRANS wpt. (for short legs) - Check / enter Constraints (ALT CNSTR or SPD CNSTR.) - Press TMPY to check entered data before activation. - Press EXEC to activate F-- PLN - Select PLAN on ND - F- PLN VERIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM SECONDARY F.PLN .4 FPLN - Press FPLN Key twice - SEC F- PLN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS APPROPRIATE SEC F-- PLN is routinely a copy of the active F-- PLN. However,consideration may be given to the following : a)immediate return : Make a copy of the active F-- PLN and modify it as a suitable WPT for an immediate return to the departure airfield in the event of, for example, an engine failure. b)diversion : If weather is below landing minimums at the departure airfield, the SEC F-- PLN should be that required for a diversion immediately after take off. c) RWY Departure change : If there is a chance of a change in the RWY or SID during taxi, prepare for it by copying the active F-- PLN and make the necessary modifications. Mod 5948 2.03.08 NORMAL PROCEDURES P4 FINAL COCKPIT PREPARATION 001 APR 11 AA 3 - PERFORMANCES - Press DATA key, then INIT Lsk to open INIT Page. PERFORMANCE DATA part should be prepared using the following flow. .5 WEIGHT > - Press WEIGHT Lsk - ZFW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT If the ZFW is unavailable, it is acceptable to enter the expected values in order to obtain prediction. - FOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT Similary, the flight crew may enter the expected Fuel On Board if refueling has not been completed at that time. - GW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - RESERVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT CAUTION The characteristic speeds displayed on MCDU / MFD PERF page are computed from Weights entered by crew on the MCDU. Therefore, these weight data must the be checked. (Captain’s responsibility) .6 PERF INIT > - Press PERF INIT Lsk - CRZ ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT Enter the expected CRUISE ALTITUDE. Enter ZFW before entering a CRUISE ALT. (Mind the FORMAT : i.e enter : 20000 or FL200) - CRZ MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK MAX CRUISE - DFLT FPA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / SET if RQRD Check the DEFAULT Flight Path Angle (3°). - ALTN/CRZ ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET Enter the Alternate airport and the desired cruise altitude to alternate. (Default value : FL100). Mod 5948 2.03.08 NORMAL PROCEDURES P5 001 FINAL COCKPIT PREPARATION APR 11 AA .7 PERF - Press PERF key once on MCDU TAKE OFF page : - RWY LNG / AXIS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / SET if RQRD Check the RWY length and AXIS stored in the database. Set the correct value for any change affecting TORA, TODA, ASDA (Displaced threshold, take off from intersection, work in progress reducing RWY length...) - TRANS ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK / SET if RQRD Check the transition altitude. Set a new value if required. - V1, VR, V2 . . . . . . . . . . . . . . . . . . . . . . . . CHECK / MANUALLY SET IF RQRD CAUTION V1, VR, V2 are automatically computed considering that the runway is NON- LIMITING. A MANUAL INSERTION is required for any limitation. (RWY LIMITATION, OBSTACLE, RWY CONTAMINATION...) - Press PERF key (once more) CRUISE page : WINDS INSERTION : The pilot has to choose between, 2 models : A simplified wind model and an accurate wind model. - SIMPLIFIED WIND MODEL : (Used for short flight) If required, mean winds will be entered in the PERF CRUISE page. - DEST MEANWIND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET if RQRD Enter the expected mean wind between DEP and DEST at the cruise altitude. - ALTN MEANWIND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET if RQRD Insert the MEANWIND between DEP & ALTN at FL 100 or at the FL defined in the PERF INIT page. Mod 5948 2.03.08 NORMAL PROCEDURES P6 001 FINAL COCKPIT PREPARATION APR 11 AA - ACCURATE WIND MODEL (May be used for long flight) If the accurate wind model is chosen, winds need to be entered at any wpt directly in the F-- PLN. For this, press FPLN key and : - Perform a vertical revision at the desired WPT. - Enter the ORIGIN / WIND / FL. (Up to 4 FL may be considered) - Enter WIND at each WPT until destination. Note : The last wind will be propagated downstream until destination. CAUTION Once a vertical wind profile has been entered at one way point, the SIMPLIFIED MODEL does not apply any more to the rest of the flight End of FMS Initial Preparation --------------------------------------- NAVAIDs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET Set : - NAVAIDS using MCP / VCP - COURSEs using FGCP - NAV SOURCE on FGCP and - Check on PFD : - Cross check NAV SOURCE on PFD (EHSI) - VOR / ILS 1 & 2 set MANUAL TUNE Note: If NOTAMs warn of any unreliable DME or VOR/DME, crew must deselect it from position computation. Press MCDU DATA key, select NAV FRQ page then DESELECTED those related NAVAIDs. - COM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET Mod 5948 2.03.08 NORMAL PROCEDURES P7 001 FINAL COCKPIT PREPARATION FEB 12 AA CM1 - PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON PRESS CHECK - SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON - MEMO PANEL DISPLAY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - FUEL QTY on FUEL ENG SD page (MFD) . . . . . . . . . . CHECK & BALANCED Cross check FUEL Quantity displayed on EWD, with Actual FUEL quantity displayed on ENG SD page (Measured) with paper F-- PLN Fuel. CAUTION FOB displayed on EWD permanent data is the FOB entered by the crew in the FMS - ENG FUEL USED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET ALL - ALTIMETERS (3) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET & CHECK - TAKE OFF TQ BUGS . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK GREEN DOT T/O Torque (Green dot) should be cross checked using ATIS or TWR temperature with QRH OPS DATA - RESERVE TAKE OFF TQ . . . . . . . . . . . . . . . . . . . . . . . CHECK AMBER BUGS RTO Torque (Amber Bug) should be cross checked using ATIS or TWR temperature with QRH OPS DATA. - SEATS, SEATS BELTS, HARNESS, RUDDER PEDALS . . . . . . . . . . ADJUST R PF: - DEPARTURE BRIEFING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM - FINAL COCKPIT PREPARATION C/L . . . . . . . . . . . . . . . . . . . . . . PERFORM Mod 5948 . 2.03.09 NORMAL PROCEDURES P1 HOTEL MODE START UP 001 FEB 12 AA R According to operational requirement and limitations captain can decide to start up Hotel Mode any time before start up clearance. - SERVICE DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED - FUEL PUMP 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Check RUN LIGHT ON + FEED LO PRESS extinguished - WING LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON - PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON / LOCKED Check PROP BRK Local Cyan light illuminated + EWD Cyan label displayed - ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START IN HOTEL MODE CAUTION Prior to any engine start, check FUEL- ENG SD page displayed START SEQUENCE - ENGINE & PROP AREA . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CLEAR - ENGINE START rotary selector . . . . . . . . . . . . . . . . . . . . . . . . . START A + B A+B for the 1st flight on the day, then A or B for the next start - START 2 P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED / ON Start timing for maximum starter run time Check : - START P/B ON light illuminated - START green label on ENG SD page - ENGINE ROTATION (NH) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR S When passing 10 % NH (maximum 19% NH if ITT > 200°c) : - CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR - TIMING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START - ITT rises within 10s . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ENGINE START in HOT ENVIRONMENT In hot environments to prevent an engine starting from a “hot start” : High OAT or High residual ITT, it is recommended to delay the fuel opening up to 20% NH.For residual ITT below 100_C, open fuel up to 10% NH. From 100_C to 200_C delay fuel opening by 1% NH per 10_C of residual ITT, up to 200_C (20% NH) Do not exceed 20% NH for fuel opening. Mod 5948 2.03.09 NORMAL PROCEDURES P2 001 HOTEL MODE START UP FEB 12 AA R CAUTION - If ITT < 950°°C } CL...............FUEL S O - If 840 C°° <ITT <950°°C for more than 5s } CL...............FUEL S O - If 800 C°° <ITT <840°°C for more than 20s } CL...............FUEL S O S When passing 45 % NH : Check : - START green label EXTINGUISHES on ENG SD page - START P/B ON light extinguished Check maximum start time and max ITT (Refer to Limitation chap 2.01.04) S When engines parameters are stabilized : - ENGINE START ROTARY SELECTOR . . . . . . . OFF / START ABORT - GPU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - DC GEN 2 FAULT LIGHT . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - DC BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED - BLEED / PACK / X VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN - PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST AS RQRD If Z > 5000 ft and SAT > ISA + 25C°, advance PL 2 up to the GUST LOCK stop. Mod : 5948 2.03.10 NORMAL PROCEDURES BEFORE PROPELLER ROTATION P1 001 FEB 12 AA R Note: If hotel mode wasn’t started at this point, start it now When LOAD & TRIM SHEET is received CM1 - LOAD AND TRIM SHEET . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CM1 - TAKE OFF WEIGHT / CG / PITCH TRIM . . . . . . . . . . . . . ANNOUNCE CM2 - TAKE OFF DATA CARD . . . . . . . . . . . . . . . . . . . . . . . 2nd PART FILL 2nd part : TOW, SPEED, TRIM settings - FMS WEIGHT & SPEEDS UPDATE . . . . . . . . . . . . . . . . . PERFORM Enter in the MCDU TAKE OFF page the last TO WEIGHT & TO CG PF CAUTION V1, VR, V2 are automatically computed considering that the runway is NON- LIMITING. A MANUAL INSERTION is required for any limitation. (RWY LIMITATION, OBSTACLE, RWY CONTAMINATION...) ALL - TAKE OFF DATA............................................................CONFIRMED Confirm the last TO WEIGHT & SPEED using MCP/VCP and check : - TO TRIM magenta.................................DISPLAYED on EWD - V1.......................................................DISPLAYED on PFD - V2......................................DISPLAYED on MFD PERF page WARNING PERFORMANCE CONFIRMATION must be done according to ICING or NON ICING CONDITIONS ALL - ALL TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET & CHECK -------------------------------------------------------------------CM2 - START UP CLEARANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN CM1 - GROUND CREW CLEARANCE . . . . . . . . . . . . . . . . . . . . . . OBTAIN CM1 - TAIL PROP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON BOARD CM1 - ALL DOORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED Checked on SD AIR page CM2 - CDLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON CM1 - SEAT BELTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON CM1 - BEACON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON CM1 - NOSE WHEEL STEERING (if push back) . . . . . . . . . . . . . . . . . OFF ALL - BEFORE PROPELLER ROTATION C/L . . . . . . . . . . . . . . PERFORM Mod 5948 . 2.03.11 NORMAL PROCEDURES BEFORE TAXI P1 001 FEB 12 AA BEFORE TAXI ALL - LEFT / RIGHT SIDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLEAR CM1 - - HYD AUX PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .DEPRESS Check HYD PRESS on SD HYD Page. - PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . CHECK READY LIGHT ON - PROP BRK SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - PROP BRK CYAN . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISED on overhead panel : - UNLOCK local light flashes then extinguishes - PROP BRK Local Cyan light extinguished on EWD : Cyan label disappear CM2 - NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STABILIZED CM2 - CL2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO R CM2 - PEC SGL CH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK on EWD : Single Channel label displayed for few seconds then extinguishes CM2 - LOW PITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK on EWD : Low Pitch label is displayed CM2 When NP stabilized at around 71% : Check on the overhead panel and on associated SD page - ACW GEN 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - ACW BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLOSED - HYD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R CM2 - PROBES HEATING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON R CM2 - ANTI ICING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD R CM2 - HYD TRIPLE INDICATOR . . . . . . . CHECK 3 x 3000 PSI (on SD page) CM2 - ANTISKID TEST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM ANTISKID Test : Depressed ANTISKID TEST P/B and check : On alerting window : - WHEEL A-- SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AMBER - FFFF appears for few seconds . . . . . . . . . . . . . . . . . . . . AMBER - NNNN appears at the end of the test for few seconds . . . . GREEN R Mod 5948 2.03.11 NORMAL PROCEDURES BEFORE TAXI P2 001 FEB 12 AA CM2 - FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15°° R CM2 R - ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START START SEQUENCE as per ENG 2 CAUTION Prior to all engine start, select ENG SD page CM2 - CL1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO CM2 - SGL CH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK on EWD : Single Channel label displayed for few seconds then extinguishes CM2 - LOW PITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK on EWD : Low Pitch label is displayed When NP stabilized at around 71% : Check on the overhead panel and on associated SD page CM2 - ACW GEN 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CM2 - ACW BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN R CM1 - COCKPIT COM HATCH . . . . . . . . . . . . . . . . . . . . . CHECK CLOSED R CM2 - XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS REQUIRED CM1 - FWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RCL R CM1 - Nose Wheel Steering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON R CM2 R - OVHD PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NO LIGHT Except exhaust mode FAULT light for 2mn. ALL - BEFORE TAXI C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM Mod 5948 2.03.12 NORMAL PROCEDURES P1 TAXI 001 APR 11 AA TAXI CM2 - TAXI CLEARANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAINED CM1 - TAXI & TO LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON CM2 - ELAPSED TIME . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQRD ALL - BRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECKS Brakes checks : - CM1 Set Taxi PWR - CM1 set PARKING RAKE handle from ON to EMER position - CM2 checks BRAKES while CM1 releases PARKING BRAKE - CM1 checks BRAKES after CM2 have released BRAKES - CM1 start to TAXI ALL - INTRUMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Cross check Headings, Bearings, ADI, Side slip indicators CM2 - FGCP CAUTION All actions on FGCP needs to be confirmed on FMA - HDG SEL MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT - NAV MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ARMED - NAV SOURCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - IAS BUG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET According to company policy - PITCH HOLD (# 7°) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT (Note : ALT SEL needs to be different from zero) - COUPLING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PF SIDE ALL Mod 5948 - FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK 2.03.12 NORMAL PROCEDURES P2 TAXI 001 APR 11 AA CM2 - TO CONFIG . . . . . . . . . . . . . . . . . . . TEST & CHECK OK BLUE ON EWD CM2 - ATC CLEARANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN ALL - CLEARED ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CHECK Check clearead ALT is displayed on PFD ALL - FMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . REVISE IF NECESSARY Carefully confirm that the ATC clearance agrees with the FMS (RWY, SID, Constraints) and Disarm NAV MODE if HDG is to be used at Take off. PF - TO BRIEFING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM - Take off briefing should usually be a brief confirmation of the departure briefing made at the parking bay, and should include any change (RWY, SID...) - Standard calls - For significant failure before V1, CAPTAIN will call “STOP” and will take any necessary stop actions. - Above V1 take off will be continued and no action will be taken except on CAPTAIN command ; - Single Engine procedure is............. - Acceleration Altitude is................... - Departure clearance is................... CM1 - CABIN REPORT . . . . . . . . . . . . . . . . OBTAIN FROM CABIN ATTENDANT ALL - TAXI C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETED Mod 5948 2.03.13 NORMAL PROCEDURES P1 001 BEFORE TAKE OFF FEB 12 AA Philosoply of use : All items “up to the line”, can be done at any time before entering the runway. “Below the line” items must be done when cleared to line up. CM2 - GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASE ALL - FLIGHT CONTROLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check full travel and freedom movement in PITCH, ROLL, YAW For ROLL, check spoiler lights illuminate CM2 - TCAS AUTO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R CM2 - XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ALT R CM2 - WEATHER RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD CM2 - AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM CM1 - OVERHEAD PANEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SCAN Check all light extinguished except ANTI ICING if required. ALL - DU CONFIGURATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check display : PF : - MFD = ND / VOR1+2 MAN, - MCDU = PERF - TAKE OFF page, PNF : - MFD = ND / COM, - MCDU = F/PLN page CM2 - LINE UP CLEARANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN R CM2 - BLEED VALVES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD CM1 - LANDING LIGHT & STROBE . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON R When lined up ALL - LATERAL FD BAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CENTER Check HDG = RWY HDG. If not, push to synchronize HDG CM1 - RUDDER CAM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CENTER ALL - BEFORE TAKE OFF C/L . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM Mod 5948 . 2.03.14 NORMAL PROCEDURES P1 TAKE OFF 001 FEB 12 AA R TAKE OFF R For Take Off at 100% TQ, refer to page 1A, 2A. (if applicable) CM1 - “TAKE OFF” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE R CM1 - BRAKES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASED CM1 - PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET IN THE NOTCH CM1 - FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE CM2 - FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CM2 - “ATPCS ARM” . . . . . . . . . . . . . . . . . . . . . . . CHECK then ANNOUNCE CM2 - ENGINE PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Note :Parameters should be obtained at around 60 Kt ACTUAL TQ . . . . . . . . . . . . . . . . . . . . . . . . . MATCH T.O BUG Note : If necessary, adjust PLs to obtain TO TQ (bugs ) RTO BUG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ~ 100 % Note : NP =100 % - 0.6%I+0.8% ITT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CM2 - TO INHIB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CM2 - “POWER SET” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE When reaching 70 Kt CM2 - “SEVENTY KNOTS” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE CM1 - SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . CROSS CHECK on CAPT ASI And cross check speeds with IESI ALL - “I HAVE CONTROL” / “YOU HAVE CONTROL” . . . . . . . . ANNOUNCE - If CM1 becomes PF, CM1 announce only “I HAVE CONTROL” - If CM2 becomes PF, CM1 announce “YOU HAVE CONTROL” & CM2 answer “I HAVE CONTROL” R PNF - “V1” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE Mod 5948 2.03.14 NORMAL PROCEDURES P2 TAKE OFF 001 FEB 12 AA R TAKE OFF (CONT’D) When reaching VR : R PNF - “ROTATE” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE PF - ROTATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM Note : Pitch rotates smoothly and follow FD bar. R After LIFT OFF : R PNF - “POSITIVE RATE” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE PF - “GEAR UP” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER R PNF - LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT UP R PNF - YAW DAMPER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE R PNF - TAXI & TAKE OFF LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF R PNF - IAS MODE (FGCP) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT R PNF - SPEED TARGET . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLIMB SPEED R PNF - LDG GEAR LIGHTS . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED R At ACCELERATION ALTITUDE : PF R PNF - “CLIMB PROCEDURE” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER - CLIMB PROCEDURE: - PL1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK IN THE NOTCH R - PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLIMB - NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK - BLEEDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON Note : Pack 2 valve FAULT will illuminate during 10 seconds. A 10 seconds delay is used for pack 2 valve to avoid pressure shocks. R R R - SPEED TARGET . . . . . . . . . . . . . . . . . . . . . MAGENTA 170 kt CHECK - “CLIMB PROCEDURE COMPLETED” . . . . . . . . . . . . . . . . . . ANNOUNCE R PNF - FMA MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE PF - FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Mod 5948 2.03.14 NORMAL PROCEDURES P3 TAKE OFF 001 FEB 12 AA When passing WHITE bug (F SPEED: White in Normal conditions) PF - “FLAPS ZERO” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER PM - FLAPS ZERO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT PM - “FLAPS ZERO” . . . . . . . . . . . . . . . . . . . ANNOUNCE WHEN INDICATED When passing ICING bug (F SPEED: Amber in Icing conditions) PF - “FLAPS ZERO” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER PM - FLAPS ZERO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT PM - “FLAPS ZERO” . . . . . . . . . . . . . . . . . . . ANNOUNCE WHEN INDICATED When cleared to a FL : ALL - ALTIMETERS 1+2 . . . . . . . . . . . . . . . . . . . . . SET STD & CROSS CHECK Note : Set Standard pressure by pushing BARO SET P/B ALL - AFTER TAKE OFF C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM R PNF - AFTER TAKE OFF procedure . . . . . . . . . . . . . . . . . . . . . . . COMPLETED CHARACTERISTIC SPEEDS : TAKE OFF SPEEDS Normal condition Mod 5948 2.03.14 NORMAL PROCEDURES P4 TAKE OFF AA FINAL TAKE OFF SPEEDS Normal condition FINAL TAKE OFF SPEEDS Icing condition Mod 5948 001 APR 11 2.03.15 NORMAL PROCEDURES P1 CLIMB - CRUISE 001 FEB 12 AA CLIMB Note : During Climb, check all system SD pages Cab Press to be checked periodically. Crossing FL 100 climbing (FL 100 or any other FL according to local regulation) R PNF - LANDING LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CM1 - SEAT BELTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD R PNF - PRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R CM1 - NO DEVICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CRUISE At Cruise FL : R PNF - SAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R PNF - CRUISE PARAMETERS . . . . . . . . . . . . . . . . COMPUTE WITH QRH Reaching Cruise Speed : R PNF - PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CRZ PF - CRUISE TORQUES + SPEEDS . . . . . . . . . . . . . . . . . . . . . CHECK SYSTEMS : R PNF - ALL SYSTEMS on SD Page . . . . . . . . . . . . PERIODICALLY CHECK FUEL : R PNF - FUEL / FOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON FMS : R PNF - CRZ ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R PNF - WINDs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET / CHECK ALL - PREDICTIONS : (TOD, EFOB, PRAIM) . . . . . . . . . . . . . . . CHECK Mod 5948 2.03.15 NORMAL PROCEDURES P2 CLIMB - CRUISE 001 FEB 12 CRUISE SPEED LOW ALERT CONDITION Cruise speed decrease VISUAL - CRUISE SPEED LOW on FMA AURAL NIL PROCEDURE CRUISE SPEED LOW Appears in cruise only, to inform the crew that an abnormal drag increase induces a speed decrease of more than 10 kt compared with the expected speed ICING CONDITIONS AND SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR R REDUCED POWER SETTING IN CRUISE The airline, according to its cost policy, can choose to cruise at reduced power, e.g. at long--range power or given IAS. The associated cruise derated tables need to be available on board for the flight crew. Those tables can be published with the FOS Module 2, In--flight performance, as shown in example in figure 1 page 2. The PLs are set according to the torque given in the tables. This requires a PL adjustment out of the notch. Limitations: The reduced power cruise is not allowed in case of icing conditions, as the IAS may already be decreased due to ice accretion on the airframe. In case of an engine failure, the PLs need to be immediately moved back into the notch, power management to MCT. From a maintenance point of view, reduced power operations may achieve lower engine overhaul costs as a result of the reduced power settings. Mod 5948 2.03.15 NORMAL PROCEDURES P3 CRUISE 001 FEB 12 REDUCED POWER SETTING IN CRUISE (CONT’D) Example: Figure 1: Long Range cruise performance table - ATR 72 (PW127M) This is an example of a long-- range cruise performance table generated with the FOS Module 2. In the case the cruise weight is 20t, the cruise FL 190, the torque is set to 51.6% and the cruise IAS will be 177kts. Mod: 5948 . 2.03.16 NORMAL PROCEDURES P1 BEFORE DESCENT - DESCENT 001 FEB 12 PF - FWS ALERTING WINDOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RCL R PNF - WEATHER & LANDING INFORMATION . . . . . . . . . . . . . . . . OBTAIN R PNF - LANDING DATA CARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FILL CM1 - IESI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET QNH R PNF - LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK PF FMS PREPARATION : PF should run through the following 2 steps to prepare the FMS : 1 - NAVIGATION 2 - PERFORMANCE 1 - NAVIGATION : . FPLN - Press FPLN key - Check the Route to destination - Enter the RWY, STAR, TRANS wpt - Check/enter Constrainst (ALT CNSTR or SPD CNSTR). - Prtess TMPY to check entered data before activation. (All STAR, APPR & MISSED APPR Wpt) - Press EXEC to activate F-- PLN - F- PLN VERIFICATION Cross check F-- PLN and Route on MCDU and NP MAP MODE . SECONDARY F- PLN FPLN - Press FPLN key twice - SEC F- PLN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS APPROPRIATE Press twice on F-- PLN key to open SEC F-- PLN Copy of the active F-- PLN and prepare a diversion to ALTERNATE Mod 5948 2.03.16 NORMAL PROCEDURES P2 BEFORE DESCENT - DESCENT 001 FEB 12 2 - PERFORMANCE : . PERF - Press PERF key on the MCDU to display APPROACH page - TRANS ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK If transition altitude has changed. - QNH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT - GND WIND / GUST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INSERT - - - - - - - - - - - - - - - - - - - - - - - End of FMS preparation- - - - - - - - - - - - - - - - - - - - - R PF - NAVAIDs . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET Prepare NAVAIDs using MCP VCP Set - NAVAIDs using MCP / VCP (MCDU / RMS should only be used as back up) - COURSEs using FGCP - Check on PFD : - Cross check NAV SOURCE on PFD (EHSI) - VOR / ILS 1&2 set MANUAL TUNE Remark : If ATIS warns of any unreliable DME or VOR/DME, crew must deselected. Press DATA key, select NAV FRQ page then DESELECTED those related NAVAIDs. R PF - GO AROUND TQ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R ALL - DH / MDA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET & CHECK R ALL - ARRIVAL BRIEFING . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE R ARRIVAL BRIEFING: Main points are : Mod 5948 - Minimum safe altitude - Weather at destination - Approach procedures - Decision Altitude / Height - Go around Procedures - Alternate - Extra fuel 2.03.16 NORMAL PROCEDURES P3 BEFORE DESCENT - DESCENT 001 FEB 12 DESCENT R PNF - DESCENT CLEARANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAIN R PF - ASSIGNED ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT R PF - IAS or VS MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD R ALL - DESCENT C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE Crossing FL 100 : (FL 100 or any other FL according to local regulation) R PNF - LANDING LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON R CM1 - SEAT BELTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON R CM1 - NO DEVICES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON R CM1 - SEAT BELTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON R ALL - FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R PNF - PRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R PNF - ALL SYSTEMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Mod 5948 2.03.16 NORMAL PROCEDURES P4 BEFORE DESCENT - DESCENT CHARACTERISTIC SPEEDS FINAL APPROACH SPEEDS Normal condition FINAL APPROACH SPEEDS Icing condition Note : ATR Philosophy is to perform all approaches using Speed Auto mode/ Mod 5948 001 APR 11 2.03.17 NORMAL PROCEDURES P1 APPROACH 001 FEB 12 AA - Passing TRANSITION LEVEL or when cleared to an ALTITUDE (According to local regulation) : ALL - ALTIMETERS 1+2 + IESI . . . . . . . . . . . . . . . SET QNH & CROSS CHECK ALL - PRESSURIZATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Note : Check Cabin ALT, RATE, DIFF pressure on SD pages R CAUTION Max ∆ P authorized at landing = 0.35 psi CM1 - CABIN REPORT . . . . . . . . . . . . . . . . OBTAIN FROM CABIN ATTENDANT ALL - APPROACH C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM Mod 5948 . 2.03.18 NORMAL PROCEDURES P1 BEFORE LANDING 001 FEB 12 AA - DU CONFIGURATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check display : PF : - MFD= ND ARC / VOR1+2 MAN, - MCDU = PERF APP page PM :-- MFD - MCDU = ND / COM = FPLN page - When cleared for approach : ALL NAV SOURCES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK ALL FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . X CHECK - When passing DECELERATION POINT : PF - PL 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETARD AS RQRD ALL - SPEED SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AUTO - At appropriate speed : PF - “FLAPS 15” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER R PNF - FLAPS 15 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT R PNF - “FLAPS 15” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE When FLAPS 15 are extended R PNF - YAW TRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CENTER - At appropriate speed : PF - “GEAR DOWN” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER R PNF - LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN R PNF - PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO R PNF - TAXI & TAKE OFF LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON When 3 green lights are illuminated : R PNF - “LDG GEAR DOWN” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE R PNF - TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK LO SPEED Mod 5948 2.03.18 NORMAL PROCEDURES P2 BEFORE LANDING 001 FEB 12 AA - At appropriate speed : R PF - “FLAPS 30” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER R PNF - FLAPS 30 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT R PNF - “FLAPS 30” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE When FLAPS 30 are extended ALL - SPEED versus ICING CONDITIONS (ICING AOA LT) . . . . . . . . . . . CHECK R PF - PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST TO MAINTAIN V APP Note : Vapp must be updated with the actual wind, in perf page ALL - BEFORE LANDING C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM Mod : 5948 2.03.19 NORMAL PROCEDURES P1 LANDING AA 001 FEB 12 R R PNF At DH +500 ft (Or MDA + 500ft) “FIVE HUNDRED ABOVE“ . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE R PNF At DH +100 ft (Or MDA + 100ft) “ONE HUNDRED ABOVE” . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE At DH (Or MDA) : R PNF “MINIMUM” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE PF - “LAND” or “GO AROUND, SET POWER, FLAPS” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE AS APPROPRIATE PF - AP DISCONNECT . . . . . . . . . . . . . . . . . . PERFORM & ANNOUNCE AP Disconnect PB press twice R PNF - FLIGHT PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK R At 20 ft (radio altimeter) PF - PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI PF - FLARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM R PNF PF R PNF R PNF After touch down : - IDLE GATE AUTOMATIC RETRACTION . . . . . . . . . . . . . . . . CHECK - PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI - BOTH LOW PITCH GREEN LABEL . . . . . . . . . . . . . . . . . . . . CHECK - “2 LOW PITCH” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE ENGINE S LO PITCH LIGHT PM ANNOUNCE PF ACTION on REVERSE 2 ENG 2 LO PITCH green “2 LOW PITCH” Normal use 1 LO PITCH green & 1 NO REV reverse video red “NO REVERSE” No reverse 2 NO REV red reverse video “NO REVERSE” No reverse 1 ENG 1 LO PITCH green & 1 LO PITCH amber or NO REV reverse video “ONE LOW PITCH” Use with care PF CM1 CM2 R PNF ALL - REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE AS RQRD - NOSE WHEEL STEERING . . . . . . . . . . . . . . . . . . . . . . . . CONTROL - CONTROL WHEEL . . . . . . . . . . . . . . . . . . . . . . . . . . HOLD AS RQRD - “SEVENTY KNOTS” . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE - “I HAVE CONTROL” / “YOU HAVE CONTROL” . . . . . . . ANNOUNCE If PF is CM1, CM1 announce only “I HAVE CONTROL” If PF is CM2, CM2 announce “YOU HAVE CONTROL” & CM1 answer : “I HAVE CONTROL” Mod 5948 . 2.03.20 NORMAL PROCEDURES P1 GO AROUND 001 FEB 12 AA Simultaneously: PF - “GO AROUND, SET POWER, FLAPS ONE NOTCH” . . . . . . . . ANNOUNCE PF - GO AROUND P/B on PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS PF - PL 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADVANCE TO RAMP PF - PITCH ATTITUDE . . . . . . . . . . . . . . . . . . ROTATE to GO AROUND PITCH R PNF - FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETRACT ONE NOTCH PNF - POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK & ADJUST Check TQ & NP = 100% R PNF - “POSITIVE RATE” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE PF - “GEAR UP” . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER R PNF - LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT UP PNF - YAW DAMPER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON PNF - TAXI & TAKE OFF LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PF - “HDG, LO BANK, IAS VGA” . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER PNF - HDG, LO BANK, IAS VGA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT PNF - SPEED TARGET VGA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Check speed target to VGA / AUTO mode PNF - “GEAR UP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE PNF - “FLAPS 15°° “ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ANNOUNCE PNF - FMA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK When passing ACCELERATION ALTITUDE PF - PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETARD IN THE NOTCH Then, refer to Take Off procedure Mod 5948 . 2.03.21 NORMAL PROCEDURES P1 001 AFTER LANDING FEB 12 AA When runway vacated : CM1 - “AFTER LANDING PROCEDURE” . . . . . . . . . . . . . . . . . . . . . . . ORDER CM2 - AFTER LANDING PROCEDURE : R - TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET - FLAPS 0 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT - GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE - FLIGHT CONTROL . . . . . . . . . . . . . . . . . . . . . CHECK LOCKED - TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY - XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD - RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY - LANDING LIGHT AND STROBE . . . . . . . . . . . . . . . . . . . . . OFF - PROBES HTG / ANTI ICING / DE ICING . . . . . . . . . . . . . . . OFF CM2 - ATPCS TEST (Last flight of the day) . . . . . . . . . . . . . . . . PERFORM CAUTION Do not perform ENG TEST while taxiing as ACW is temporary lost and, subsequently, both main HYD pumps are temporarily lost as well. R ATPCS TEST (dynamic test: once a day) . . . . . . . . . . . . . . . . . Refer to 2.03.24 Mod 5948 2.03.21 NORMAL PROCEDURES P2 AFTER LANDING 001 FEB 12 AA R After at least one minute : CM1 - CL1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO CAUTION Prior to ENG FTR, select HYD SD page, to check HYD pressure for Normal brake efficiency Note : Keep running at least one minute at GI power before shutting down to assist in reducing residual heat build up in the engine nacelle. Note : After the last flight of the day, maintain feather position for 20 seconds before selecting FUEL SO to allow oil level check by maintenance. CM2 - ACW BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CLOSED ALL - AFTER LANDING C/L . . . . . . . . . . . . . . . . . . . . . . . . . . . COMPLETE CM2 - ACW BUSSES . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK SUPPLIED Mod 5948 2.03.22 NORMAL PROCEDURES P1 001 PARKING FEB 12 AA R Note : If possible, park the aircraft with wind relative to the nose at 10 o’clock, to minimize noise and exhaust gas inconvenience when in hotel mode. Marshaller in sight (last turn): CM2 - HYD SYST PRESS . . . . . . . . . . . . . . . . . . . . . . . . CHECK 3x 3000 psi CM1 - TAXI & TO LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF At the stand: CM1 - PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Check HYD PRESS 3x 3000 psi CM1 - CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR CM1 - READY LIGHT . . . . . . . . . . . . . . . . . . . . . . . . CHECK ILLUMINATED CM1 - PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE CAUTION Engage PROP BRK only when NP STABILISED CM1 - UNLK LIGHT . . . . . . . . . CHECK ILLUMINATED THEN EXTINGUISHED CM1 - PROP BRK LIGHT . . . . . . . . . . . . . . . . . . . . . CHECK ILLUMINATED CAUTION If PROP BRK is used, insure that propeller area is clear and protected CM1 - PROP 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK STOPPED CM1 - BEACON . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF If GPU is used for disembarking : CM1 - DC EXT PWR PB . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESSED IN If GPU available CM1 - CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO R CM1 - TAIL PROP . . . . . . . INSTALLED (CHECK WITH CABIN ATTENDANT) CM1 - SEAT BELT SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CM1 - XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STBY CM1 - PARKING CHECK LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . PERFORM Mod 5948 . 2.03.23 NORMAL PROCEDURES P1 LEAVING THE AIRCRAFT AA 001 APR 11 LEAVING THE AIRCRAFT - OXYGEN MAIN SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - ICE & RAIN PROTECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - EXT LIGHTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - EMER EXIT LT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISARM - RADAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO - FUEL PUMPS 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - CDLS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF If GPU was used for disembarking : - DC EXT PWR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF - BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Mod 5948 . 2.03.24 NORMAL PROCEDURES P1 DAILY CHECKS 001 FEB 12 AA STICK PUSHER / SHAKER TEST (once a day) - Release gust lock - Push control column in nose down position - Select WARN rotary selector (LH maintenance panel) to STICK PUSHER YES - Depress and maintain PTT - Monitor stall cricket and stick shaker. - After ten seconds, monitor: CHAN 1 and CHAN2 illuminate green on LH maintenance panel. STICK PUSHER lights illuminate green on both pilots FMA. Stick pusher actuator operates. - Select WARN rotary selector to NORM FLT - Reengage the gust lock ATPCS TEST (dynamic test: once a day) (autofeather and uptrim while engines running) Conditions: - PL 1 + 2 in GI - CL 1 + 2 in AUTO. - ATPCS P/B depressed in, OFF light extinguished - PWR MGT on TO position Check the following results on EWD: - Turn the ATPCS knob to the left to the arm position and check - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - TQ INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE - NP & NH INDICATION . . . . . . . . . . . . . . . . . . . . . . . DECREASE - Turn the ATPCS knob to ENG 1 position and check : - ENG 2 UPTRIM LIGHT . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - TQ 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NO CHANGE - NP, NH . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE SLIGHTLY - TQ 1 needles indication . . . . . . . . . . . DECREASE BELOW 18 % - After 2.15 s : associated propeller is automatically feathered - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - PROP 1 AUTO FTR LABEL . . . . . . . . . . . . . . . . . DISPLAYS - Turn the ATPCS knob to the right to the arm position and check : - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - TQ INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE - NP & NH INDICATION . . . . . . . . . . . . . . . . . . . . . . . DECREASE - Turn the ATPCS knob to ENG 2 position and check : - ENG 1 UPTRIM LIGHT . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - TQ 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NO CHANGE - NP, NH . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE SLIGHTLY - TQ 2 needles indication . . . . . . . . . . . DECREASE BELOW 18 % - After 2.15 s : associated propeller is automatically feathered - ARM light . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHED - PROP 2 AUTO FTR LABEL . . . . . . . . . . . . . . . . . DISPLAYS CAUTION : Do not perform ATPCS TEST while taxiing as ACW is temporarily lost and consequently, both main hyd pumps are temporarlily lost as well. Note : If ENG TEST must be repeated, wait 10 minutes before setting ATPCS selector in ENG position in order not to damage feathering pumps. (Winding heating). Mod: 5948 2.03.24 NORMAL PROCEDURES P2 DAILY CHECKS 001 FEB 12 AA TRIMS CHECK FOR THE FIRST FLIGHT OF THE DAY - PITCH, ROLL AND YAW TRIM OPERATION . . . . . . . . . . . . . . . . . . . CHECK - Check the normal trim activation in both directions by simultaneously depressing both control rocker switches. - For few seconds depress independently each single control rocker switch and check the non-- activation of the corresponding TRIM in both possible directions. - TRIMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET FOR TAKE OFF COCKPIT DOOR DAILY CHECK (DAILY): - COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . . . . ON In the cargo compartment, on the DOOR CALL panel : - EMER P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS - CHECK OPEN LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLASHES In the cockpit, check - BUZZER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SOUNDS - OPEN LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLASHES - DENIED ACCESS TEST : In the cockpit : - TOGGLE SW on the COCKPIT DOOR CTL panel . . . . . . . . . DENY - CHECK BUZZER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SILENCES - CHECK OPEN LIGHT . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES In the cargo compartment, on the DOOR CALL panel : - OPEN LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISHES - DENIED LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ILLUMINATES - AUTHORIZED ACCESS TEST : In the cargo compartment, on the DOOR CALL panel : - EMER P/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS In the cockpit : - TOGGLE SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OPEN - DOOR LOCKING SYSTEM . . . . . . . . . . . . . . . . . . . . . . . . UNLOCK - COCKPIT DOOR LOCKING SYSTEM SW . . . . . . . . . . . . . . . . . . . . . . . OFF - COCKPIT DOOR CTL panel FAULT LIGHT . . . . . . . . . . . . . . . . . . . . CHECK - FUNCTIONAL CHECK OF THE MANUAL LOCK BOLTs. Mod: 5948 2.03.24 NORMAL PROCEDURES P3 DAILY CHECKS 001 FEB 12 AA APM TEST: 1 - Press and hold the APM PTT TEST P/B for all test duration and check: 2 - Check FMA : - CRZ SPEED LOW - DGD PERF - INCREASE SPEED (flashing) 3 - Check : APM FAULT light (Local alarm) 4 - Check on FWS ALERTING Window (flashing) - INCREASE SPEED - DEGRADED PERF - APM FAULT Release APM PTT TEST P/B and check : - ALL ALARMS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTINGUISH ENG BOOST TEST (IF INSTALLED): Conditions : - PL 1 + 2 at GI - EEC 1 + 2 selected ON. OFF extinguished. Test : - ENG BOOST pushbutton pressed-- in - ON illuminated - FAULT extinguished - ENG BOOST pushbutton released-- out - ON extinguished - FAULT extinguished Note:Test can be performed disregarding engine running condition (both engines running, one engine running or both engines shut-- off) Mod: 5948 . 2.04.00 EMERGENCY PROCEDURES P1 CONTENTS AA 2.04.00 2.04.01 2.04.02 001 FEB 12 CONTENTS INTRODUCTION POWER PLANT Alert Procedure ENG 1(2) FIRE ENG 1(2) FIRE OR SEVERE MECHANICAL DAMAGE IN FLIGHT ENG 1(2) FIRE OR SEVERE MECHANICAL DAMAGE ON GROUND ENG 1(2) FIRE AT TAKE OFF ENG 1(2) FIRE R ENG 1(2) FIRE ENG 1+2 OUT ENG 1(2) OUT 2.04.03 Alert BOTH ENGINES FLAME OUT ENG 1(2) FLAME OUT AT TAKE OFF SMOKE Procedure SMOKE ELEC SMK ELECTRICAL SMOKE AIR COND SMOKE FWD SMK FWD SMOKE AFT SMK AFT SMOKE AUX AFT SMK AUX AFT COMPT SMOKE 2.04.04 ELECTRICAL SYSTEM Alert Procedure ELEC DC GEN 1+2 DUAL DC GEN LOSS 2.04.05 Alert MISCELLANEOUS Procedure EMERGENCY DESCENT DITCHING FORCED LANDING ON GROUND EMERGENCY EVACUATION BOMB ON BOARD SEVERE ICING RECOVERY AFTER STALL OR ABNORMAL ROLL CONTROL UNRELIABLE AIRSPEED INDICATION Mod : 5948 . APR 11 PM -- Pilot monitoring Mod : 5948 2.04.01 EMERGENCY PROCEDURES P2 INTRODUCTION 001 FEB 12 AA PROCEDURES INITIATION - No action will be taken (apart from depressing MW pb): . Until flight path is stabilized. . Under 400 ft above runway (except for propeller feathering after engine failure during approach at reduced power if go around is considered). - Before performing a procedure, the crew must assess the situation as a whole, taking into consideration the failures, when fully identified, and the constraints imposed. ANALYSIS OF CONSEQUENCES OF A FAILURE ON THE FLIGHT Basic airmanship calls for a management review of the remaining aircraft capabilities under the responsability of CM1. R FWS ALERTING ( see page 3 ) Mod : 5948 2.04.01 EMERGENCY PROCEDURES P3 INTRODUCTION 001 FEB 12 AA R FWS ALERTING When the TO inhibition signal computed by FMA is actived, all alerts are inhibed exept (this inhibition is cancelled automatically at landing gear retraction or manually by action on the RCL push-- button) : WARNING CAUTION - ENG 1 (2) OUT - LDG GEAR NOT DN - CONFIG - NAC OVHT - PROP BREAK - ENG 1 (2) OIL PRESS - FLAPS UNLK - PITCH DISC - EXCESS CAB ∆P - EXCESS CAB ALT - TRIM RUNAWAY - AP DISCONNECTION - APCH CAPABILITY - FD MODE REVERSION - ALTITUDE ALERT - PITCH TRIM ASYM - FLT CTL TLU - AP PITCH TRIM - PICH MISTRIM - AILERON MISTRIM - RUDDER MISTRIM - AP YAW TRIM - ADC 1+2 - AHRS 1+2 - IRS 1+2 - ATT DISAGREE - IAS DISAGREE - ALT DISAGREE - MFC 1B + 2B - FLT CTL TLU - ADC - AHRS - AHRS NOT ALIGN - IRS - IRS NOT ALIGN - IRS IN ALIGN - HDG DISAGREE - IRS ATT ONLY - DATA RECORDER - CALLS - VLE, VFE EXCEED Mod : 5948 . 2.04.02 EMERGENCY PROCEDURES P1 POWER PLANT 001 FEB 12 AA ENG 1 (2) FIRE OR SEVERE MECHANICAL DAMAGE IN FLIGHT ALERT CONDITION VISUAL AURAL Fire signal -- MW light flashing red -- Associated ENG 1(2) FIRE red message on EWD + Red reverse video FIRE 1 (2) on EWD engine indications -- red light in associated FIRE handle CRC -- FUEL SO red light in associated CL PROCEDURE ENG 1 (2) FIRE OR SEVERE MECHANICAL DAMAGE IN FLIGHT R PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL J If condition persists after 10 seconds AGENT 1 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH J If condition persists after 30 seconds AGENT 2 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH LAND ASAP SINGLE ENG OPERATION procedure (2.05.02) . . . . . . . . . . . . . . . . . . . APPLY COMMENTS - Fire handle remains illuminated as long as a fire is detected. - The 10 seconds delay allows to reduce nacelle ventilation in order to increase the agent effect. - CRC stops when depressing MW. May also be cancelled by use of EMER AUDIO CANCEL SW. - Do not attempt to restart engine. - Refer to SINGLE ENG OPERATION procedure. Mod : 5948 2.04.02 EMERGENCY PROCEDURES P2 POWER PLANT 001 FEB 12 AA ENG 1 (2) FIRE OR SEVERE MECHANICAL DAMAGE ON GROUND ALERT CONDITION VISUAL AURAL Fire signal -- MW light flashing red -- Associated ENG 1(2) FIRE red message on EWD + Red reverse video FIRE 1 (2) on EWD engine indications -- red light in associated FIRE handle CRC OR ATPCS sequence or engine flame out -- Fuel SO red light in associated CL PROCEDURE ENG 1 (2) FIRE OR SEVERE MECHANICAL DAMAGE ON GROUND R PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI / REVERSE AS RQD F When aircraft stopped PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL J If condition persists AGENT 1 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH J If condition persists after 30 seconds AGENT 2 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH J If evacuation required EMER EVACUATION ON GROUND procedure (2.04.05)) . . . . . . . APPLY COMMENTS - Same comments as in flight - The aircraft may be stopped using full reverse - Notify ATC the nature of the emergency and state intentions. - Only VHF 1 is available on battery - Battery is left ON until leaving the aircraft to ensure cabin communication. Only PA is available on battery. Mod : 5948 2.04.02 EMERGENCY PROCEDURES P3 001 POWER PLANT FEB 12 AA R ENG 1 (2) FIRE AT TAKE OFF ALERT CONDITION VISUAL AURAL Fire signal -- MW light flashing red -- Associated ENG 1(2) FIRE red message on EWD + Red reverse video FIRE 1 (2) on EWD engine indications -- red light in associated FIRE handle CRC -- Fuel SO red light in associated CL R PROCEDURE ENG 1 (2) FIRE AT TAKE OFF Note: Captain may decide to shut down affected engine before reaching acceleration altitude, but not before 400ft AGL. F When airborne LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP F At acceleration altitude PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT F At VFTO J If normal condition FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0° J If icing condition FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 15° PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO FIRE HANDLE illuminated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL J If fire persists after 10 seconds AGENT 1 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH J If fire persists after 30 seconds AGENT 2 affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH BLEED engine alive . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF if necessary LAND ASAP SINGLE ENG OPERATION procedure (2.05.02) . . . . . . . . . . . . . . . . . . . . APPLY COMMENTS - Same comments as ENG FIRE IN FLIGHT procedure. Mod : 5948 2.04.02 EMERGENCY PROCEDURES P4 001 POWER PLANT AA FEB 12 BOTH ENGINES FLAME OUT ALERT CONDITION VISUAL AURAL Both engines flame--out -- MW light flashing red -- Associated ENG 1+2 OUT red message on EWD CRC PROCEDURE BOTH ENGINES FLAME OUT PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI J If NH drops below 30 % (no automatic relight) CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO FUEL SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OPTIMUM SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Vm HB COMMUNICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VHF 1 ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . START A & B ENG 2 RELIGHT ENG 2 START pb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON F When NH above 10% CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR ENG 2 RELIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR CL 2 then PL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD ENG 1 RELIGHT ENG 1 START pb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON F When NH above 10% R R R CL 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR ENG 1 RELIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR CL 1 then PL 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD J If neither engine starts CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . OFF/START ABORT FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FORCED LANDING or DITCHING procedure(2.04.05) . . . . . . . . . . . . APPLY CAUTION : Do not select AVIONICS VENT EXHAUST MODE to OVBD. J If at least one engine recovered CL / PL engine(s) recovered . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD J If one engine not recovered CL engine NON recovered . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO LAND ASAP SINGLE ENG OPERATION procedure(2.05.02) . . . . . . . . . . . . . . APPLY SYSTEMS affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE APM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Mod : 5948 2.04.02 EMERGENCY PROCEDURES P5 POWER PLANT 001 APR 11 AA COMMENTS - Fuel supply check consists in checking correct fuel quantity and correct pressure (use Engine secondary SD page to have access to fuel data). - The optimum airspeed to achieve best lift to drag ratio is Vm HB. IF BOTH ENG ARE LOST - If landing gear extension is scheduled, emergency extension has to be performed. - In short final, reduce speed as required by landing field in order to touch down with minimum vertical speed; Mod : 5948 2.04.02 EMERGENCY PROCEDURES P6 POWER PLANT AA 001 FEB 12 ENG 1 (2) FLAME OUT AT TAKE OFF ALERT An engine flame out may be recognized by : - Sudden dissymetry - TQ decrease - Rapid ITT decrease CONDITION VISUAL AURAL engine flame out or ATPCS sequence -- MW light flashing red -- Associated ENG 1 (2) OUT red message on EWD + AUTO FTR and UPTRIM labels on EWD CRC PROCEDURE ENG 1(2) FLAME OUT AT TAKE OFF R UPTRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AUTOFEATHER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK J If no uptrim PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADVANCE TO THE RAMP F When airborne LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP BLEED 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF, IF NOT FAULT F At acceleration altitude ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET F At VFTO PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IN THE NOTCH PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET J If normal conditions SPD DGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK VFTO FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0° J If icing conditions SPD DGT . . . . . . . . . . . . . . . . . . . . . . CHECK VFTO ICING FLAPS 15_ FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN 15° PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO BLEED engine alive . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF if necessary J If damage suspected FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL LAND ASAP SINGLE ENG OPERATION procedure(2.05.02) . . . . . . . . . . . . . . . . . APPLY J If no damage suspected ENG RESTART IN FLIGHT procedure(2.05.02) . . . . . . . . . . . . . . . . . APPLY J If unsuccessful : LAND ASAP SINGLE ENG OPERATION procedure(2.05.02) . . . . . . . . . . . . . . . . . APPLY Mod : 5948 2.04.03 EMERGENCY PROCEDURES P1 SMOKE 001 FEB 12 AA SMOKE PROCEDURE SMOKE CREW OXY MASKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON / 100% GOGGLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET CREW COMMUNICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ESTABLISH RECIRC FANS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON R R R R R SMOKE SOURCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY J If source not identified or electrical smoke suspected Note : ELEC SMK may be activated by an air conditioning smoke source ELECTRICAL SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . APPLY J If air conditioning smoke identified AIR COND SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . APPLY J If FWD SMK illuminated or smoke in FWD zone of aircraft FWD SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY J If AFT SMK illuminated or smoke in AFT zone of aircraft AFT SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY J If AUX AFT COMPT SMK illuminated (depending on models) AUX AFT COMPT SMK procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . APPLY Mod : 5948 2.04.03 EMERGENCY PROCEDURES P2 SMOKE AA 001 FEB 12 ELECTRICAL SMOKE ALERT CONDITION Smoke detected in the avionics ventilation circuit VISUAL AURAL -- MW light flashing red -- ELEC SMK red message on EWD CRC -- associated ELEC SMK red indication on SD cabin page. PROCEDURE ELECTRICAL SMOKE SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH DC SVCE AND UTLY BUS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF DC BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ISOL ACW GEN 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF SUSPECTED EQUIPMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF J If smoke origin not identified LAND ASAP ACW TOTAL LOSS procedure(2.05.04) . . . . . . . . . . . . . . . . . . . . . . . APPLY J If smoke origin identified NOT AFFECTED EQUIPMENTS . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE R F During descent when nP below 1 PSI OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . NORM COMMENTS - Avionics compartment ventilation without cabin contamination is ensured by : - selecting AVIONICS VENT EXHAUST mode OVBD - shuting off the recirculation fans - selecting the PACKS AIR FLOW HIGH. - Auto isolation is prepared on the main electrical system by opening the BTC. - Suspected equipment may be shut off contingently by pulling out associated circuit breaker. - When nP < 1 PSI, OVBD VALVE is selected FULL OPEN and AVIONICS VENT EXHAUST mode NORM in order to recover air evacuation capability through the EXTRACT FAN without any pressurization problem. Mod : 5948 2.04.03 EMERGENCY PROCEDURES P3 SMOKE 001 FEB 12 AA AIR COND SMOKE PROCEDURE AIR COND SMOKE R R SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY PACK VALVE 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA J If smoke persists PACK VALVE 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON PACK VALVE 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CAUTION : Evacuation of air conditioning smoke may trigger electrical smoke warning. Disregard it. ENGINES PARAMETERS . . . . . . . . . . . . . . . . . . . . . CAREFULLY MONITOR J If any anomaly occurs such as : - ENG OVER LIM amber message on EWD - Total loss of NL indication - Engine abnormality clearly identified (NH, NL, ITT indications, noise, surge...) R CAUTION : Confirm which engine is showing signs of abnormal operation in order to avoid shutting down the safe engine. PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO LAND ASAP SINGLE ENG OPERATION procedure . . . . . . . . . . . . . . . . . . . . . . . . APPLY COMMENTS - Ensure crew communication is established. Avoid the use of interphone position to minimize interference from oxygen mask breathing noise. Check oxygen mask at 100%. - Recirculation fans are switched off to limit cabin contamination. Mod : 5948 2.04.03 EMERGENCY PROCEDURES P4 SMOKE 001 FEB 12 AA FWD SMOKE ALERT CONDITION Smoke detected in the forward cargo compartment Smoke detected in the forward cargo compartment (CARGO VERSION ONLY) VISUAL AURAL - MW lt flashing red - FWD SMK red message on EWD - Associated FWD SMK red indication on SD Cabin page. - MW lt flashing red - FWD SMK red message on EWD - Associated FWD SMK red indication on SD Cabin page. CRC CRC PROCEDURE FWD SMK SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY R R 1) PASSENGERS VERSION CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADVISE AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH EXTRACT AIR FLOW LEVER (RH MAINT PANEL) . . . . . . . . . . . . . . . . . CLOSED CABIN CREW WITH PORTABLE EXTINGUISHER LOCATE and KILL SOURCE OF SMOKE LAND ASAP D During descent when P below 1 PSI OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . NORM 2) CARGO VERSION CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN CAB ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX INCREASE ENG 2 BLEED (Except when in single bleed operation) . . . . . . . . . . . . . . . . . . OFF PACK VALVE 2 (Except when in single pack operation) . . . . . . . . . . . . . . . . . . . OFF CAB VENT AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FLIGHT COMPT TEMP SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOT CAUTION : LAND ASAP. If a quick landing is not possible : climb and maintain minimum FL160, FL 200 is recommended. When “Excess CAB ALT“ warning, maintain FL 160, maintain CAB ALT Max increase. Note : Smoke alert may be generated during smoke evacuation process. Mod : 5948 2.04.03 EMERGENCY PROCEDURES P5 SMOKE 001 APR 11 AA COMMENTS - Ensure crew communication is established. Avoid the use of interphone position to minimize interference from oxygen mask breathing noise. Check oxygen mask at 100%. - Cargo ventilation without cabin or cockpit contamination is ensured by: - selecting AVIONICS VENT EXHAUST mode OVBD - shuting off the recirculation fans - selecting HIGH the PACKS AIR FLOW - isolating the cockpit panels ventilation by selecting EXTRACT AIR FLOW to CLOSED. - Cabin crew is in charge to locate and kill source of smoke with the extinguisher. - Cabin crew uses the portable oxygen bottle with the full face mask on 100 % position with full pressure. A fire extinguisher (3 kg - 7 Lbs) is available at the left front Locker). - When nP < 1 PSI, OVBD VALVE is selected full open and avionics VENT NORM in order to recover air evacuation capability through the extract fan without any pressurization problem. Mod 5948 2.04.03 EMERGENCY PROCEDURES P6 SMOKE AA 001 FEB 12 AFT SMOKE ALERT CONDITION Smoke detected in the aft cargo compartment or in the lavatory Smoke detected in the aft cargo compartment (CARGO VERSION ONLY) VISUAL AURAL - MW lt flashing red - AFT SMK red message on EWD - Associated LAV SMK or AFT COMPT SMK or AFT SMK red indication on SD cabin page. - MW lt flashing red - AFT SMK red message on EWD - Associated AFT SMK red indication on SD cabin page. CRC CRC PROCEDURE AFT SMOKE R R SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY 1) PASSENGERS VERSION CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADVISE FOR ACTION AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HIGH 2) CARGO VERSION CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN CAB ALT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX INCREASE ENG 2 BLEED (Except when in single bleed operation) . . . . . . . . . . . . . . . . . . OFF PACK VALVE 2 (Except when in single pack operation) . . . . . . . . . . . . . . . . . . . OFF CAB VENT AIR FLOW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FLIGHT COMPT TEMP SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HOT CAUTION : LAND ASAP. If a quick landing is not possible : climb and maintain minimum FL 160, FL 200 is recommended. When “Excess CAB ALT” warning maintain FL 160, maintain CAB ALT Max increase. Note : Smoke alert may be generated during smoke evacuation process. COMMENTS (PASSENGERS VERSION ONLY) - The cabin crew is in charge to locate and kill the source of smoke, if possible, using the portable fire extinguisher located in the cabin. Before entering the aft cargo area, the cabin attendant must wear an oxygen mask. To leave the aft cargo door open may induce some cabin contamination therefore it must be avoided. Mod 5948 2.04.03 EMERGENCY PROCEDURES P7 001 SMOKE FEB 12 AA AUX AFT COMPT SMOKE ALERT CONDITION Smoke detected in the auxiliary aft cargo compartment VISUAL - MW light flashing red - AUX AFT SMK red message on EWD - Associated AUX AFT COMPT SMK red indication on SD cabin page. - SQUIB white light on COMPT SMK panel AURAL CRC PROCEDURE AUX AFT COMPT SMOKE (depending on models) R SMOKE procedure(2.04.03) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY AUX AFT COMPT AGENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH COMMENTS Aux aft cargo ventilation valve closes as soon as the aux aft cargo smoke signal is generated and remains closed when the extinguishing agent has been discharged to improve the agent efficiency. Mod : 5948 . 2.04.04 EMERGENCY PROCEDURES P1 001 ELECTRICAL SYSTEM FEB 12 DUAL DC GEN LOSS ALERT CONDITION VISUAL AURAL DC generation channel is inoperative -- MW light flashing red -- ELEC DC GEN 1+ 2 red message on EWD and 2 DC GEN amber message on EWD. CRC -- DC GEN 1(2) fault + DC BUS 1(2) OFF + INV 2 FAULT + AC BUS 1(2) OFF + SHED on overhead panel and in AC/DC SD page. PROCEDURE DUAL DC GEN LOSS R PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CAPT DC GEN 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF then ON J If no generator recovered HYD GREEN PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON R Make sure that TRU arrow illuminates, BAT arrows extinguish. Note : If TRU FAULT LAND ASAP MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN AVIONICS VENT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD BAT SW . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD F/O ATT HDG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SWITCH TO SYS 1 F/O ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SWITCH TO SYS 1 AP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD CAUTION: AP may be used in single source with limitations, especially the use of AP is prohibited below 1000ft AGL. COM / SURV / NAV . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE MCDU 1 XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET XPDR 1 ATC (VHF 1 or HF or HF 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY MIN CAB LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Note : NAV lights switch set to ON is necessary to provide IEP illumination TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN MODE LO SPD F When TLU LO SPD illuminates TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO CAUTION: Avoid large rudder input if IAS above 180 kt. STICK PUSHER / SHAKER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF STICK PUSHER / SHAKER FAULT procedure(2.05.06) . . . . . . . . . . . APPLY SIDE WINDOWS / WINDSHIELD HTG . . . . . . . . . . . . . . . . . . . . . . . . . OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . to be continued next page .../... Mod : 5948 2.04.04 EMERGENCY PROCEDURES P2 ELECTRICAL SYSTEM 001 FEB 12 DUAL DC GEN LOSS R .../... DE-- \ ANTI-- ICING MODE SEL AUTO FAULT procedure(2.05.09) . . . . APPLY AUTO PRESS FAULT procedure(2.05.08) . . . . . . . . . . . . . . . . . . . . . APPLY BUS EQUIPMENT LISTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Note: Periodically compare PFD with IESI, crosscheck HDG / TK / STBY-- HDG F Before descent PAX INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE PA HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Note: Selecting HYD X FEED ON allows to recover green hydraulic system. F At touch down IDLE GATE LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL COMMENTS - Safety analysis leads us to consider the case when the DUAL DC GEN LOSS is due to : . Single engine operation, . DC GEN inoperative on the operating engine. In such a case, HYD GREEN PUMP has to be set to OFF position in order not to overload the ACW GEN of the remaining engine. - Selecting TRU ON allows to recover EMER, ESS and STBY (AC and DC) buses supply from ACW generators. - HYD X FEED is opened in order to pressurize the whole hydraulic system from blue pump. - Minimum cabin light must be switched OFF to limit the electrical load of the TRU. - As DC BUS 1 is lost, automatic pressurization is lost. - Both stick pusher and stick shaker are lost without FAULT alarm. - DC STBY BUS undervoltage may occur due to a failure of the STBY BUS system circuit. In this event, the OVRD function may be used to transfer the STBY BUS supply from the MAIN BAT BUS to the EMER BAT BUS. - TLU AUTO mode is lost and MAN MODE must be used. MAN MODE acts on TLU standby actuator which remains powered even if TLU is in LO SPD established position. When TLU SW is set to AUTO position, TLU standby actuator electrical power is off. - PA must be used for pax instructions because cabin signs are not supplied in emergency. Mod : 5948 2.04.05 EMERGENCY PROCEDURES P1 MISCELLANEOUS 001 FEB 12 AA EMERGENCY DESCENT PROCEDURE EMERGENCY DESCENT R R OXYGEN MASKS / CREW COMMUNICATIONS . . . . . . . . . . . . . . . . . . AS RQD GOGGLES . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD OXYGEN PAX SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD SPEED . . . . . . . . . . . . . . MMO / VMO (or less if structural damage is suspected) SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ATC (VHF 1 / HF) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY MEA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK COMMENTS - Oxygen may be used with N/100 % rocker in N position if air in the cabin is not contaminated. - Maximum airspeed is MMO/VMO. But if structural damage is suspected, use the flight controls with care and reduce speed as appropriate. Landing gear may be extended in order to increase rate of descent. - Notify ATC of the nature of the emergency encountered and state intentions. In the event ATC cannot be contacted, select code A7700 or transmit the distress message on one of the following frequencies (VHF) 121,5 MHz or (HF) 8364 KHz. Only VHF 1 is available on battery. - CL are selected 100% OVRD to increase drag and consequently to increase the rate of descent. Mod : 5948 2.04.05 EMERGENCY PROCEDURES P2 MISCELLANEOUS 001 FEB 12 DITCHING PROCEDURE DITCHING R R R S Preparation (time permitting) ATC (VHF1 or HF) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY XPDR) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMERGENCY CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF TERR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CABIN AND COCKPIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PREPARE . Loose equipment secured . Survival equipment prepared . Belts and shoulder harnesses locked. AUTO PRESS - LDG ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET S Approach AUTO PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP PACKS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL CLOSE HYD AUX PUMP pushbutton . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS FLAPS (if available) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30_ LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UP S 30 secondes before impact or 1250 ft above sea level DITCH pb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . OFF / START ABORT CABIN REPORT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAINED S Before ditching (200 ft) MINIMIZE IMPACT SLOPE OPTIMUM PITCH ATTITUDE FOR IMPACT . . . . . . . . . . . . . . . . . . . . . . . . 9_ BRACE FOR IMPACT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER Note : In case of night ditching, shutting down both engines may be performed, at captain discretion, immediately after the impact ( avoiding loss of landing lights during flare out). CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO FIRE HANDLES 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF S After ditching Note : After ditching, one aft door will be under the water line. CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY EVACUATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE S Before leaving aircraft BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MM Mod : 5948 APR 11 A7700 Mod : 5948 2.04.05 EMERGENCY PROCEDURES P4 MISCELLANEOUS 001 APR 11 AA AIRCRAFT ATTITUDE IN CASE OF DITCHING Note : This illustration is given as an example. It is not necessary the LH wing which is down. Mod : 5948 2.04.05 EMERGENCY PROCEDURES P5 MISCELLANEOUS 001 FEB 12 FORCED LANDING PROCEDURE FORCED LANDING R R S Preparation (time permitting) ATC (VHF1 or HF) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMERGENCY CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY SIGNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF TERR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CABIN and COCKPIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PREPARE . Loose equipment secured . Survival equipment prepared . Belts and shoulder harnesses locked. AUTO PRESS - LDG ELEVATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET S Approach HYD AUX PUMP pushbutton . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DEPRESS FLAPS (if available) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30_ LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD AUTO PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . OFF / START ABORT CABIN REPORT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OBTAINED S Before impact (200 ft) BRACE FOR IMPACT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER Note : In case of night forced landing, shutting down both engines may be performed, at captain discretion, immediately after the impact (avoiding loss of landing lights during flare out). CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO FIRE HANDLES 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF S After impact, when aircraft stopped CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY AGENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH EVACUATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE S Before leaving aircraft BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Mod : 5948 APR 11 Mod : 5948 2.04.05 EMERGENCY PROCEDURES P7 MISCELLANEOUS 001 FEB 12 R EMERGENCY EVACUATION ON GROUND PROCEDURE EMER EVACUATION ON GROUND R R AIRCRAFT / PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . STOP / ENGAGE AUTO PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP ATC (VHF1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO MIN CAB LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY FIRE HANDLES 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL AGENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH AS RQD ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . OFF / START ABORT FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF EVACUATION (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE F Before leaving aircraft BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF COMMENTS Careful analysis is required to decide passenger evacuation, however useful time should not be wasted. Notify ATC on the nature of the emergency and state intentions. Only VHF 1 is available on battery. On battery, only PA is available to communicate with cabin crew. Mod : 5948 2.04.05 EMERGENCY PROCEDURES P8 MISCELLANEOUS 001 FEB 12 BOMB ON BOARD PROCEDURE BOMB ON BOARD R R AUTO PRESS-- LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . CABIN ALTITUDE ALT SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DESCENT TO CABIN ALTITUDE AVOID LOAD FACTORS HANDLE BOMB CAREFULLY - AVOID SHOCKS PLACE BOMB NEAR SERVICE DOOR PREFERABLY IN A BAG ATTACHED TO THE DOOR HANDLE. SURROUND IT WITH DAMPING MATERIAL CABIN ATTENDANT OXYGEN AND FIRE EXTINGUISHER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MOVE FORWARD PAX . . . . . . . . . . . . . . . . . . . . . . . . . . . MOVE FORWARD/CRASH POSITION D When Z aircraft = Z cabin R APPROACH CONFIG FLAPS 15 GEAR DOWN . . . . . . . . . . . . . . . SELECTED AUTO PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DUMP SERVICE DOOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UNLOCK LAND ASAP Mod : 5948 2.04.05 EMERGENCY PROCEDURES P9 MISCELLANEOUS 001 FEB 12 SEVERE ICING R R R R MINIMUM ICING SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . INCREASE by 10 kt PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTCH AP (if engaged) . . . . . . . . . . FIRMLY HOLD CONTROL WHEEL and DISENGAGE SEVERE ICING CONDITIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ESCAPE ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY Note: In case of APM messages “DEGRADED-- PERF” or “INCREASE-- SPEED” Vmin OPS automatically increased by 10kt. H If an unusual roll response or uncommanded roll control movement is observed : Push firmly on the control wheel FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EXTEND 15_ R H If the flaps are extended, do not retract them until the airframe is clear of R ice. H For approach, if the aircraft is not clear of ice : GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAP/GPWS OVRD STEEP SLOPE APPROACH (²4.5_) . . . . . . . . . . . . . . . . . PROHIBITED APP/LDG CONF . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN FLAPS 15_ APP SPEED . . “REDUCED FLAPS 15 LDG icing speeds “ 5 kt Multiply landing distance FLAPS 30 by 2.12 DETECTION Visual cue identifying severe icing is characterized by ice covering all or a substantial part of the unheated portion of either side window and / or Unexpected decrease in speed or rate of climb and / or The following secondary indications : . Water splashing and streaming on the windshield . Unusually extensive ice accreted on the airframe in areas not normally observed to collect ice . Accumulation of ice on the lower surface of the wing aft of the protected areas . Accumulation of ice on propeller spinner farther aft than normally observed The following weather conditions may be conducive to severe in-- flight icing : . Visible rain at temperatures close to 0_C ambient air temperature (SAT) . Droplets that splash or splatter on impact at temperatures close to 0_C ambient air temperature (SAT) Mod : 5948 2.04.05 EMERGENCY PROCEDURES P 10 MISCELLANEOUS 001 APR 11 AA COMMENTS - Since the autopilot may mask tactile cues that indicate adverse changes in handling characteristics, use of the autopilot is prohibited when the severe icing defined above exists, or when unusual lateral trim requirements or autopilot trim warnings are encountered while the airplane is in icing conditions. - Due to the limited volume of atmosphere where icing conditions usually exists, it is possible to exit those conditions either : . by climbing 2000 or 3000 ft, or . if terrain clearance allows, by descending into a layer of air temperature above freezing, or . by changing course based on information provided by ATC. Mod : 5948 2.04.05 EMERGENCY PROCEDURES P 11 001 MISCELLANEOUS FEB 12 RECOVERY AFTER STALL OR ABNORMAL ROLL CONTROL PROCEDURE RECOVERY AFTER STALL OR ABNORMAL ROLL CONTROL R R R R R CONTROL WHEEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH FIRMLY H If flaps 0_ configuration FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15_ PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTCH ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY H If flaps are extended PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTCH ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY Note: This procedure is applicable regardless the LDG GEAR position is (DOWN or UP). Mod : 5948 2.04.05 EMERGENCY PROCEDURES P 12 MISCELLANEOUS 001 FEB 12 UNRELIEABLE AIRSPEED INDICATION ALERT In case of disagreement between both ADC, AP (if engaged) disconnects being unable to identify the valid ADC. To make the difference with an isolated drifting, here the three airspeed indicators are drifting, and indicate erroneous airspeed. PROCEDURE UNRELIABLE AIRSPEED INDICATION AP/YD/FD BARS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF/OFF/STBY PITCH AND TQ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN H If at take off or GA below 1500 ft PITCH IMMEDIATELY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8_ ICING / VOLCANIC ASHES CONDITIONS . . . . . . . . . . . . . . . . . . . . . . . ESCAPE PROBE HEATING, DE-- /ANTI-- ICING . . . . . . . . . . . . . . . . . . . . . . . . CHECK ON APM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF WARNING: respect STALL alarm. Note: Use any GPS Speed information if available. F Take off phase, at or above acceleration altitude ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN AT LEAST 30 SECONDS FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0_ PITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8_ Note: Use climb table here after to adjust pitch if required. AFTER TAKE OFF normal procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY LAND AT THE NEAREST SUITABLE AIRPORT F Climb TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CLB PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTCH Altitude (ft) 5000 10000 15000 20000 Normal conditions pitch Icing conditions pitch 7° 5° 4° 3° 6° 4° 3° 2° .to be continued next page../... Mod : 5948 2.04.05 EMERGENCY PROCEDURES P 13 MISCELLANEOUS 001 FEB 12 UNRELIEABLE AIRSPEED INDICATION (cont’d) .../... F Cruise ALTITUDE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI SPD Note: Average pitch in cruise is around 0° PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CRZ PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTCH F Descent TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI SPD PITCH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN AT --2.5° PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST 30% TQ DESCENT normal procedure(2.03.16) . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY F Initial approach TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD APPROACH normal procedure(2.03.17) . . . . . . . . . . . . . . . . . . . . . . . . . APPLY CAUTION : Transition from clean configuration to LDG configuration is to be performed in level flight -- REFER TO ALTIMETER -- (if possible 30 seconds between each step). NOTE: Refer to following tables to adjust TQ: Aircraft configuration -- Average speed Flaps 0° -- 180 kt TQ (Altitude of 3000ft) 14 T 35% 18 T 45% 22 T 50% FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15° Flaps 15° -- 150 kt 45% 45% 50% LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30° Flaps 30° -- 130 kt 45% 45% 50% F Final Approach . PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST 35% TQ . BEFORE LANDING normal procedure (2.03.18) . . . . . . . . . . . . . . . . . . APPLY NOTE: Set an average pitch of --5° for a 3° slope approach. COMMENTS - Drift of all the airspeed indications occurs if pitots are partially or fully obstructed. - This obstruction may be due to the severe icing or volcanic ashes. - NEVER REENGAGE the autopilot and/or the yaw damper. The autopilot computer uses the airspeed data to compute the deflection of the rudder. With an erroneous airspeed, the autopilot orders inappropriate deflections of the rudder, which can lead to severe structural damages and lost of control of the aircraft. - The stall alert is triggered with the angle of attack, and has to be respected Mod : 5948 . 2.05.00 PROCEDURES FOLLOWING FAILURE P1 001 CONTENTS 2.05.00 CONTENTS 2.05.01 INTRODUCTION 2.05.02 POWER PLANT Alert Procedure R SINGLE ENG SINGLE ENG OPERATION R ENG START START FAULT ELEC X START X START FAIL ABNORMAL PARAMETERS DURING START R ENG START ITT EXCESSIVE ITT DURING START R ENG START NO ITT NO ITT DURING START ENG START NO NH NO NH DURING START NAC OVHT R NAC OVHT ABNORMAL ENG PARAMETERS IN FLIGHT FIRE LOOP 1A FIRE LOOP 1A (1B)(2A)(2B) FAULT (1B)(2A)(2B) PROP BRK ABNORMAL PROP BRK (IF APPLICABLE) ENG RESTART IN FLIGHT ENG EEC ENG EEC 1+2 ENG 1(2) OUT R R IDLE GATE R ENG PROP NP1(2) ENG 1(2) PEC SG CH ENG 1(2) PEC ENG LO PITCH R ENG 1(2) OVER LIMIT ENG 1(2) PROP LIM ENG1(2) OIL TEMP L ENG1(2) OIL TEMP H ENG 1(2) OIL OVHT00 ENG 1(2) OIL PRESS ENG BOOST Mod : 5948 ENG STALL ONE EEC FAULT BOTH EEC FAULT ENG 1(2) FLAME OUT IN FLIGHT ENG 1(2) FLAME OUT ON GROUND IDLE GATE FAIL UNEXPECTED 100% NP ON ONE OR BOTH ENGINES PEC 1(2) SGL CH PEC 1(2) FAULT LO PITCH IN FLIGHT ENG 1(2) OVER LIMIT PROP 1(2) OVER LIMIT ENG 1(2) OIL TEMP BELOW 45_C ENG 1(2) OIL TEMP HIGH ENG 1(2) OIL LO PR ENG BOOST FAULT (IF APPLICABLE) FEB 12 2.05.00 PROCEDURES FOLLOWING FAILURE P2 001 CONTENTS 2.05.03 FUEL Alert FUEL 1(2) TEMP LO FUEL 1(2) TEMP HI ENG FUEL CLOG FUEL FEED LO PR Procedure FUEL 1(2) ABNORMAL TEMP FUEL LO LVL FUEL LO LVL ENG EXCESS ITT FUEL LEAK FUEL MISMATCH FUEL MISMATCH FUEL UNBALANCED FUEL UNBALANCED 2.05.04 FUEL CLOG FEED LO PR ELECTRICAL SYSTEM Alert ELEC DC 1 Procedure DC BUS 1 OFF R ELEC AC 1 AC BUS 1 OFF ELEC DC 2 DC BUS 2 OFF R ELEC AC 2 AC BUS 2 OFF ELEC ACW 1(2) ACW BUS 1(2) OFF ELEC ACW 1+2 ACW TOTAL LOSS ELEC DC ESS DC ESS BUS OFF ELEC DC EMER DC EMER BUS OFF ELEC DC GEN DC GEN FAULT ELEC INV 1(2) INV 1(2) FAULT ELEC ACW GEN 1(2) ACW GEN FAULT ELEC DC SHED DC SVCE/UTLY BUS SHED R ELEC BAT CHG MAIN (or EMER) BAT CHG FAULT R ELEC CHG LOSS EMER + MAIN BAT CHG LOSS ELEC BAT DISCH BAT DISCHARGE IN FLIGHT ELEC AC SBY BUS AC STBY BUS FAULT ELEC DC SBY BUS DC STBY BUS FAULT ELEC STBY BUS UND/V DC STBY BUS UND/V STBY BUS / STBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS Mod : 5948 FEB 12 2.05.00 PROCEDURES FOLLOWING FAILURE P3 CONTENTS 2.05.05 001 FEB 12 HYDRAULIC Alert R HYD BLUE LO LVL (HYD GREEN LO LVL) HYD PUMPS LOSS HYD SYS LOSS Procedure HYD BLUE (GREEN) LO LVL BOTH MAIN HYD PUMPS LOSS BOTH HYD SYS LOSS R HYD BLUE(GREEN) (AUX) LO HYD BLUE (GREEN) LO PR PR HYD BLUE (GREEN) OVHT HYD BLUE(GREEN) (AUX) OVHT HYD AUX LO PR HYD AUX OVHT 2.05.06 HYD AUX LO PR HYD AUX OVHT FLIGHT CONTROLS Alert FLAPS UNLK Procedure FLAPS UNLK FLAPS JAM FLAPS ASYM FLAPS JAM / UNCOUPLED / ASYM REDUCED FLAPS LANDING FLT CTL PUSHER STICK PUSHER / SHAKER FAULT PITCH TRIM ASYM PITCH TRIM ASYM PITCH TRIM INOPERATIVE PITCH DISC PITCH DISCONNECT FLT CTL RUD RCU DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTERING UNIT FAIL R PITCH DISC PITCH DISCONNECT PITCH RECONNECTION ON GROUND R PITCH RECONNECT PITCH RECONNECT FLT CTL TLU TLU FAULT AIL LOCK LIT AIL LOCK LIT ELEVATOR JAM AILERON JAM / SPOILER JAM RUDDER JAM Mod : 5948 2.05.00 PROCEDURES FOLLOWING FAILURE P4 CONTENTS 2.05.07 LANDING GEAR Alert Procedure LDG GEAR GRAVITY EXTENSION LANDING WITH ABNORMAL LDG GEAR LDG GEAR LDG GEAR UNSAFE INDICATION LDG GEAR RETRACTION IMPOSSIBLE WHEELS A-- SKID ANTI-- SKID FAULT WHEELS BRK HOT BRK TEMP HOT 2.05.08 AIR Alert AIR BLEED 1(2) Procedure BLEED VALVE 1(2) FAULT AIR BLEED1(2) OVHT BLEED 1(2) OVHT AIR LEAK 1(2) BLEED 1(2) LEAK R AIR X VALVE X BLEED VALVE OPEN AIR PACK PACK VALVE FAULT AIR PACK 1+2 BOTH PACK VALVES FAULT AIR RECIR FAN 1(2) RECIRC FAN 1(2) FAULT AIR DUCT OVHT DUCT OVHT R CAB ALT CABIN ALTITUDE EXCESS CAB ALT EXCESS CAB ALT AIR AUTO PRESS AUTO PRESS FAULT EXCESS CAB nP EXCESS CAB nP AIR VENT EXH AVIONICS VENT EXHAUST MODE FAULT AIR OVBD OVBD VALVE FAULT Mod : 5948 001 FEB 12 2.05.00 PROCEDURES FOLLOWING FAILURE P5 001 CONTENTS 2.05.09 DE/ANTI ICE Alert R A-- ICING BLEED Procedure AIRFRAME AIR BLEED FAULT A-- ICING FRAME A-- ICING SEL DE-- ICING AIRFRAME FAULT DE-- ICING MODE SEL FAULT A-- ICING AUTO MODE SEL AUTO FAULT A-- ICING DETECT ICE DETECT FAULT A-- ICING ENG 1(2) DE-- / ANTI-- ICING ENG 1(2) FAULT A-- ICING PROP 1(2) ANTI-- ICING PROP 1(2) FAULT A-- ICING HORNS 1(2) ANTI-- ICING HORNS 1(2) FAULT A-- ICING L WSHLD A-- ICING R WSHLD A-- ICING WINDOWS SIDE WINDOW / WINDSHIELD HTG FAULT A-- ICING PROBE A-- ICING PIT CPT(F/O)( SBY) A-- ICING TAT CPT(F/O) PROBES HTG FAULT 2.05.10 AUTOPILOT Alert AILERON MISTRIM Procedure AILERON MISTRIM or EXCESSIVE LATERAL TRIM REQUIRED or ABNORMAL FLIGHT CHARACTERISTICS R PITCH MISTRIM PITCH MISTRIM R RUDDER MISTRIM RUDDER MISTRIM AP PITCH TRIM AP PITCH TRIM FAIL 2.05.11 Mod : 5948 AIRCRAFT PERFORMANCE MONITORING Refer to 2.02.21 FEB 12 2.05.00 PROCEDURES FOLLOWING FAILURE P6 CONTENTS 2.05.12 AVIONICS Alert AUDIO SEL CAPT (F/O) R RMS 1 + 2 Procedure AUDIO SEL FAULT AHRS RMS 1 + 2 FAULT ONE AHRS FAIL R AHRS 1+2 AHRS 1 + 2 LOSS AHRS NOT ALIGN AHRS NOT ALIGN ADC ADC 1+2 ADC FAIL ATT DISAGREE ATTITUDE DISAGREE HDG DISAGREE HEADING DISAGREE ALT DISAGREE ALTITUDE DISAGREE IAS DISAGREE IAS DISAGREE R VHF 1+2 VHF 1 + 2 LOSS R DU(n) DISCREPANCY DUs DISCREPANCY DU DISCREPANCY R DU TEMP HI ONE DU TEMP HI R MULTI DUs T HI SEVERAL DUs TEMP HI FWS SGL CH AVNX FWS SGL CH SWITCH SGL CH AVNX SGL SWITCH FWS 1 + 2 LOSS AVNX SWITCH 1+2 LOS CPM 1 AVNX CPM 1 LOSS CPM 2 AVNX CPM 2 LOSS CPM 1+2 AVNX CPM 1+2 LOSS Mod : 5948 001 FEB 12 2.05.00 PROCEDURES FOLLOWING FAILURE P7 001 CONTENTS 2.05.12 AVIONICS Alert IOM 12 Procedure AVNX IOM 12 LOSS IOM 13 IOM 22 AVNX IOM 13 LOSS AVNX IOM 22 LOSS IOM 23 AVNX IOM 23 LOSS IOM 12 + 13 AVNX IOM 12 + IOM 13 LOSS IOM 12 + 22 AVNX IOM 12 + IOM 22 LOSS IOM 12 + 23 AVNX IOM 12 + IOM 23 LOSS IOM 13 + 22 AVNX IOM 13 + IOM 22 LOSS IOM 13 + 23 AVNX IOM 13 + IOM 23 LOSS IOM 22 + 23 AVNX IOM 22 + IOM 23 LOSS CPM 1 + IOM 22 AVNX CPM 1 + IOM 22 LOSS CPM 1 + IOM 23 AVNX CPM 1 + IOM 23 LOSS CPM 2 + IOM 12 AVNX CPM 2 + IOM 12 LOSS CPM 2 + IOM 13 AVNX CPM 2 + IOM 13 LOSS 2.05.13 MISCELLANEOUS Alert IOM 12 R RAD-- ALT LOSS AIR AFT DET FAN DOOR EMER DOOR LH(RH) FWD DOOR LH(RH) AFT DOOR FWD COMPT Procedure COCKPIT DOOR CONTROL PANEL FAULT (If installed) LOSS OF RADIO ALTIMETER INFORMATION SMK DET FANS FAULT DOORS UNLK IN FLIGHT COCKPIT WINDOW CRACKED OXY R OXYGEN LO PR VOLCANISH ASH ENCOUNTER Mod : 5948 FEB 12 2.05.00 PROCEDURES FOLLOWING FAILURE P8 CONTENTS 2.05.14 MFC Alert MFC 1A Procedure MFC 1A FAUL MFC 1B MFC 2A MFC 1B FAULT MFC 2A FAULT MFC 2B MFC 2B FAULT MFC 1A + 1B MFC 1A+1B FAULT MFC 1A + 2A MFC 1A+2A FAULT MFC 1A + 2B MFC 1A+2B FAULT MFC 1B + 2A MFC 1B+2A FAULT MFC 2A + 2B MFC 2A+2B FAULT MFC 1B + 2B MFC 1B+2B FAULT Mod : 5948 001 FEB 12 2.05.01 PROCEDURES FOLLOWING FAILURE P1 INTRODUCTION 001 APR 11 GENERAL The procedures following failures represent the actions applicable after a failure to ensure adequate dafety and to ease the further conduct of the flight. They are applied according to the “Read and Do” principle except for the memory items. PRESENTATION The procedures are presented in the basic check list format with an adjacent expanded section which provides: - indication of the particular failure, alert condition - explanation for actions where the reason is not self evident - additional background information The abbreviations used are identical with the nomenclature on the cockpit panels. All actions are printed in CAPITAL letters. Q : a preceding black square is used to identify a pre-- condition (in bold) for given action(s). O : a preceding black dot is used to indicate the moment (in bold) when given action(s) have to be applied. TASK SHARING For all procedures, the general task sharing stated below is applicable. The pilot flying remains pilot flying throughout the procedure. PF, Pilot Flying, responsible for: - PL - flight path and airspeed control - aircraft configuration - navigation PM, Pilot Monitoring, responsible for: - check list reading - execution of required actions - actions on overhead panel - CL - communications The AFCS is always coupled to the PF side (CPL selection). Mod : 5948 2.05.01 PROCEDURES FOLLOWING FAILURE P2 INTRODUCTION 001 FEB 12 AA PROCEDURES INITIATION - No action will be taken (apart from depressing MW pb): . Until flight path is stabilized. . Under 400 ft above runway (except for propeller feathering after engine failure during approach at reduced power if go around is considered). - Before performing a procedure, the crew must assess the situation as a whole, taking into consideration the failures, when fully identified, and the constraints imposed. ANALYSIS OF CONSEQUENCES OF A FAILURE ON THE FLIGHT Basic airmanship calls for a management review of the remaining aircraft capabilities under the responsability of CM1. R FWS ALERTING ( see page 3 ) Mod : 5948 2.05.01 PROCEDURES FOLLOWING FAILURE P3 INTRODUCTION 001 FEB 12 AA R FWS ALERTING When the TO inhibition signal computed by FMA is actived, all alerts are inhibed exept (this inhibition is cancelled automatically at landing gear retraction or manually by action on the RCL push-- button) : WARNING CAUTION - ENG 1 (2) OUT - LDG GEAR NOT DN - CONFIG - NAC OVHT - PROP BREAK - ENG 1 (2) OIL PRESS - FLAPS UNLK - PITCH DISC - EXCESS CAB ∆P - EXCESS CAB ALT - TRIM RUNAWAY - AP DISCONNECTION - APCH CAPABILITY - FD MODE REVERSION - ALTITUDE ALERT - PITCH TRIM ASYM - FLT CTL TLU - AP PITCH TRIM - PICH MISTRIM - AILERON MISTRIM - RUDDER MISTRIM - AP YAW TRIM - ADC 1+2 - AHRS 1+2 - IRS 1+2 - ATT DISAGREE - IAS DISAGREE - ALT DISAGREE - MFC 1B + 2B - FLT CTL TLU - ADC - AHRS - AHRS NOT ALIGN - IRS - IRS NOT ALIGN - IRS IN ALIGN - HDG DISAGREE - IRS ATT ONLY - DATA RECORDER - CALLS - VLE, VFE EXCEED Mod : 5948 . 2.05.02 PROCEDURES FOLLOWING FAILURE P1 001 POWER PLANT FEB 12 AA SINGLE ENG OPERATION ALERT CONDITION Engine flame out VISUAL AURAL - MC light flashing amber - SINGLE ENG amber message on EWD SC PROCEDURE SINGLE ENG OPERATION R R R PWR MGT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MCT ENG BOOST (if installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON LAND ASAP FUEL PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF DC GEN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ACW GEN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PACK affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF APM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TA ONLY OIL PRESSURE AND NP ON FAILED ENGINE . . . . . . . . . . . . . . . . . . . MONITOR Note: In icing conditions, FLAPS 15 will be selected to improve drift down performances and single engine ceiling. Note: Refer to QRH pages (4.61) and (4.62) to determine single engine gross ceiling. Note: If during the flight, a positive oil pressure has been noted on the failed engine for a noticeable period of time, maintenance must be informed. Note: monitor fuel balance. Recommended operational maximum fuel unbalance is 200 kg (440 lb). ● When FUEL CROSS FEED is required FUEL PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON FUEL PUMP on operating engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF To be continued next page(...\...) Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P2 POWER PLANT 001 FEB 12 AA PROCEDURE SINGLE ENG OPERATION (cont’d) ● For approach MAX APPROACH SLOPE for Steep Slope Approach . . . . . . . . . . . . . . . . 5.5_ BLEED NOT AFFECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CL live engine . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD V APP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN 1.1 VMCA H IF AFFECTED ENGINE NP ABOVE 10% V APP . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN V REF + 10kt D When V APP is increased SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15 Note: Refer to 4.64 to determine 1.1VMCA, and to 4.65 to determine landing distance. Note: ILS CAT 2 prohibited. R ● At touch down CAUTION: Do not reduce below FI before nose wheel is on the ground. SINGLE ENG OPERATION COMMENTS - Refer to section Procedures and Techniques for fuel unbalance. - For approach and landing, comply with Procedures and Techniques, Flight Patterns sub-- section 2.02.10. Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P3 001 POWER PLANT FEB 12 AA START FAULT ALERT CONDITION Start sequence incident VISUAL AURAL - MC light flashing amber - ENG START amber message on EWD + amber reverse video START indication - associed START FAULT amber light on overhead panel SC START FAULT ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . OFF / START ABORT ■ If above 45 % NH START ON LIGHT . . . . . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED START . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TO BE CONTINUED X START FAIL ALERT CONDITION VISUAL AURAL On ground, during second engine start, operative DC GEN does not come on line to supply the START BUS between 10 % and 45 % NH - MC light flashing amber - ELEC X START amber message on EWD - X START FAIL amber light on overhead panel SC PROCEDURE X START FAIL R CONTINUE NORMAL ENGINE START MAINTENANCE ACTION IS REQUIRED Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P4 001 POWER PLANT FEB 12 AA ABNORMAL PARAMETERS DURING START PROCEDURE ABNORMAL PARAMETERS DURING START ■ If ITT tends to exceed 900_ _C, or no ITT, or no NH CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . OFF / START ABORT Then refer to the relevant procedure: ■ EXCESSIVE ITT DURING START procedure (2.05.02 page 4) ■ NO ITT DURING START procedure (2.05.02 page 5) ■ NO NH DURING START procedure (2.05.02 page 5) R EXCESSIVE ITT DURING START ALERT CONDITION VISUAL ITT incident during start - MC light flashing amber - ENG START ITT amber message on EWD AURAL SC PROCEDURE EXCESSIVE ITT DURING START ● When NH below 30 % ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . CRANK START PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ● After 15 seconds R ENG START ROTARY SELECTOR . . . . . . . . . . . . . . OFF / START ABORT CAUTION: If ITT exceeds 950_C, maintenance action is required Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P5 001 POWER PLANT FEB 12 AA NO ITT DURING START ALERT CONDITION NO ITT during start VISUAL - MC light flashing amber - ENG START NO ITT amber message on EWD AURAL SC PROCEDURE NO ITT DURING START ● After 30 seconds, to allow fuel draining ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . . . . . . . CRANK START PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ● After 15 seconds ENG START ROTARY SELECTOR . . . . . . . . . . . . . . OFF / START ABORT NO NH DURING START ALERT CONDITION NO NH during start VISUAL - MC light flashing amber - ENG START NO NH amber message on EWD AURAL SC PROCEDURE NO NH DURING START R Note : On BAT only, OIL PRESS IND is not available. ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . START A or START B START PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON ■ If after 10 seconds OIL pressure increases R CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR Continue START procedure, being informed NH indicator is inoperative. ■ If after 10 seconds no OIL pressure R ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . OFF / START ABORT Suspect starter motor failure. Maintenance action is required. Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P6 POWER PLANT 001 FEB 12 AA NAC OVHT ALERT CONDITION VISUAL AURAL Nacelle temperature exceeds 170°C (338°F) when aircraft is on ground - MW flashing red - NAC OVHT red message on EWD CRC PROCEDURE NAC OVHT ■ If during hotel mode operation PL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO ■ If during taxi AIRCRAFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . STOP PL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SLIGHTLY INCREASE POWER ■ If NAC OVHT persist within 30 seconds R PARKING BREAK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE PL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO FUEL PUMP 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF RETURN TO PARKING R COMMENTS - In case of tailwind component greater than 10 kt and just after engine start, propeller must be unfeathered rapidly to take advantage of the wind created by propeller rotation and consequently to avoid exhaust gas return flow in the nacelle. - When taxiing with tail wind component, use of reverse requires special care as air flow created by propeller reversing combined with tail wind will induce an exhaust gas return flow which may damage the nacelle. It is consequently recommended not leave PL in reverse position for any period of time exceeding 10 seconds. - NAC OVHT alert is inhibited when both wow systems detect aircraft airborne. Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P7 POWER PLANT 001 FEB 12 AA ABNORMAL ENG PARAMETERS IN FLIGHT PROCEDURE ABNORMAL ENG PARAMETERS IN FLIGHT R R R J If Intermittent fluctuations or unrealistic steady indication ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF F When adequate flight situation PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI EEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF J If normal engine operations recovered ONE EEC FAULT procedure (2.05.02 page12) . . . . . . . . . . . . . . . APPLY J If abnormal fluctuations or indications persist - or - J If TQ = 0% and NP < 77% PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO LAND ASAP SINGLE ENG OPERATIONS procedure (2.05.02 page1) . . . . . . . APPLY J If “HBV” indication on display AVOID SUDDEN PL MOVEMENTS COMMENTS - AFU provides TQ indication to the cockpit intruments. (needle). - Untimely TQ indication drop lasting more than 2.15 seconds will induce an ATPCS sequence if ATPCS was already armed. - With engine at high power, a spurious ATPCS sequence would provoke an automatic feathering and a very significant overtorque deselecting ATPCS will avoid such a possibility. - With no reliable TQ indication, engine power monitoring is assured on the affected engine through NH / NP indications. - Refer to 2.02.11 page 2. Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P8 POWER PLANT 001 FEB 12 AA FIRE LOOP 1A (1B) (2A) (2B) FAULT ALERT CONDITION R Fire loop fault detected VISUAL AURAL - MC flashing amber - FIRE LOOP 1A (1B) (2A) (2B) amber message on EWD CRC PROCEDURE FIRE LOOP 1A (1B) (2A) (2B) FAULT LOOP AFFECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P9 POWER PLANT 001 FEB 12 AA ABNORMAL PROP BRK (If applicable) ALERT CONDITION VISUAL AURAL Propeller brake not locked in full locked or in full released position - or-Propeller brake engaged and GUST LOCK released - or-Propeller brake engaged and propeller rotating - UNLK red light on overhead panel - MW+PROP BRK red message on EWD - or-- with action on PROP BRK SW : - UNLK red light on overhead panel then after 30 seconds - MW+PROP BRK red message on EWD CRC PROCEDURE ABNORMAL PROP BRK (If applicable) R R J If on ground J If propeller rotation and FWS PROP BRK alert - or J If UNLK light and FWS PROP BRK alert CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO MAINTENANCE ACTION IS REQUIRED J If FWS PROP BRK alert only J If GUST LOCK ON CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO J If DC and AC GPU are not available ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . START CL 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO F When READY light illuminates PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF UNLK LIGHT . . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED PROP BRK PWR SPLY C/B . . . . . . . . . . . . . . . . . . . . . . . . . PULL J If GUST LOCK OFF GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON F According to operational situation PROP BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ALL PROP BRK LIGHTS . . . . . . . . . . . . . CHECK EXTINGUISHED J If in flight CONTINUE NORMAL OPERATION ENG 2 PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR F After landing CL 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO MAINTENANCE ACTION IS REQUIRED Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 10 POWER PLANT 001 FEB 12 AA ENG RESTART IN FLIGHT PROCEDURE ENG RESTART IN FLIGHT R R R R FUEL SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FUEL SO PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CAUTION: After ATPCS sequence PWR MGT rotary selector must be set to MCTposition before engine restart in order to cancel propeller feathering. ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . . . . . . . START A & B START PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON Note : AP-- YD may disconnect during start F When NH above 10 % CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR RELIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR CL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO PL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ADJUST TO OTHER ENGINE ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . OFF/START ABORT SYSTEMS AFFECTED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE APM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF COMMENTS - Engine relighting in flight is only guaranteed within the envelope and always necessitate starter assistance. - The power may be restored immediately after relighting provided OIL TEMP > 0°C. - Should the engine fail to light up within 10 seconds, select fuel to shut off, the ignition OFF and allow engine to be ventilated for 30 seconds minimum prior to making another attempt. Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 11 POWER PLANT 001 FEB 12 AA ENG STALL ALERT An engine stall may be recognized by : - varying degrees of abnormal engine noise (rumbling bangs) - fluctuating engine parameters - abnormal PL response - rapid ITT increase PROCEDURE ENG STALL R R R PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI ENG PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK J If abnormal engine parameters CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO LAND ASAP SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . . APPLY J If normal engine parameters DE-- /ANTI-- ICING ENG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SLOWLY ADVANCE J If stall recurs Reduce thrust and operate below the stall threshold J If normal operations recovered Continue normal operation Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 12 POWER PLANT 001 FEB 12 ONE EEC FAULT ALERT CONDITION EEC failure VISUAL AURAL - MC light flashing amber - ENG EEC amber MESSAGE on EWD - associated EEC FAULT amber light on central panel SC PROCEDURE ONE EEC FAULT R R R R ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CAUTION: DO NOT DESELECT EEC FLASHING. F When adequate flight situation PL affected side . . . . . . . . . . . . . . . . . . . . . . . . RETARD IN GREEN SECTOR EEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET J If EEC recovered ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE POWER J If EEC fault persists EEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HANDLE THROTTLE WITH CARE F In the following cases : icing conditions, engine(s) flame out, emergency descent, severe turbulence, heavy rain MAN IGN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON F In final approach CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD V APP . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN V REF + 10 kt SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15 Note: Refer to Part 4 to determine landing distance Note: If engine failure during go around, do not reduce PL below 45°before feathering F After landing TAXI WITH THE AFFECTED ENGINE FEATHERED Note: ACW BTC must be checked closed in order to avoid the loss of ACW bus on ground COMMENTS Refer to 2.05.02 page 14. mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 13 POWER PLANT 001 FEB 12 BOTH EEC FAULT ALERT CONDITION VISUAL AURAL Both EEC failure - MC light flashing amber - ENG EEC 1+2 amber message on EWD - EEC FAULT amber light(s) on central panel SC PROCEDURE R R R R R R EEC 1 + 2 FAULT ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CAUTION: DO NOT DESELECT EEC FLASHING. F When adequate flight situation PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RETARD IN GREEN SECTOR EEC 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET J If EEC 1 + 2 recovered ATPCS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE POWER J If only one EEC recovered ONE EEC FAULT procedure (2.05.02 page 12) . . . . . . . . . . . . . . . . . APPLY J If EEC 1+2fault persists EEC 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESTORE POWER, . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HANDLE THROTTLES WITH CARE TQ IND ENG 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR F In the following cases : icing conditions, engine(s) flame out, emergency descent, severe turbulence, heavy rain MAN IGN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON F In final approach CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD V APP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN V REF + 10 kt SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15 Note: Refer to Part 4 to determine landing distance Note: If engine failure during go around, do not reduce PL below 45°before feathering F After landing BRAKE HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD CAUTION : Both main HYD pumps will be lost at low speed. Note: Revers power is reduced TAXI ON BOTH ENGINES, HANDLE THROTTLES WITH CARE COMMENTS : Refer to 2.05.02 page 14. Mod : 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 14 POWER PLANT 001 APR 11 ONE EEC FAULT (CONT’D) COMMENTS specific for ONE EEC FAULT - When EEC fails, two cases must be considered : High Power Low Power PL set forward 52_ PL set aft of 52_ in green sector EEC FAULT light flashes, NH is EEC FAULT comes on steady, EEC is automatically frozen to its prior value (FAIL automatically deselected (Automatic FIX) reversion) - Feathering the engine with EEC failed for taxi and static operation will avoid prolonged time in NP restricted band (propeller limitation). BOTH EEC FAULT (CONT’D) COMMENTS specific for BOTH EEC FAULT - During reduction at touch down, both ACW GEN may be lost and therefore both main HYD pumps. - Both digital torque indications are lost when TQ are below 20%. Mod 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 15 POWER PLANT 001 FEB 12 AA ENG 1(2) FLAME OUT IN FLIGHT ALERT CONDITION VISUAL AURAL Engine 1(2) flame out - MW light flashing amber - ENG 1(2) OUT amber message on EWD SC PROCEDURE ENG 1(2) FLAME OUT IN FLIGHT PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI J If NH drops below 30% (no immediate relight) CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO J If damage suspected FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL LAND ASAP SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . APPLY J If no damage suspected ENG RESTART IN FLIGHT procedure (2.05.02 page 10) . . . . . . . . . . APPLY J If engine out confirmed LAND ASAP SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . APPLY R R COMMENTS - Shut down the engine if no immediate relight. - The causes of engine flame out can generally be divided into two categories : . External causes such as icing, very heavy turbulence, fuel mismanagement. These causes, which may affect both engines can generally be easily determined and an immediate relight can be attempted. . Internal causes which as engine stalls or failures usually affect a single engine and are not so easily determined. In these cases, the engine is shut down then the cause of the flame out investigated. If it cannot be positively determined what caused the flame out, the need for engine restart should be evaluated against the risk or further engine damage or fire that may result from a restart attempt. - If damage is suspected, as precautionary measure, the FIRE handle is pulled. Mod 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 16 POWER PLANT 001 FEB 12 AA ENG 1(2) FLAME OUT ON GROUND PROCEDURE ENG 1(2) FLAME OUT ON GROUND R PL 1+ 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI STOP THE AIRCRAFT D When aircraft stopped PARKING BRK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO ENG FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL FUEL PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF RETURN TO PARKING IDLE GATE FAIL ALERT Automatic idle gate system failure - MC light flashing amber - IDLE GATE amber message on EWD - IDLE GATE FAIL amber light on pedestal SC PROCEDURE IDLE GATE FAIL F In flight IDLE GATE LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PUSH F At touch down IDLE GATE LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL COMMENTS - In flight, pushing idle gate lever sets the stop at FI. - On ground, pulling the lever removes the stop and allows reduction below FI (GI and reverse). - One reason for IDLE GATE FAIL alert may be a problem in the WOW (Weight On Wheel) system. Other systems may be affected. Report to maintenance. Mod 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 17 001 POWER PLANT FEB 12 AA R UNEXPECTED 100% NP ON ONE OR BOTH ENGINES ALERT CONDITION VISUAL AURAL Unexpected 100% NP on one or - MC light flashing amber two engines - ENG PROP NP 1(2) amber message on EWD SC PROCEDURE UNEXPECTED 100% NP ON ONE OR BOTH ENGINES R CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD PEC 1(2) SGL CH ALERT CONDITION Anomaly detection on either PEC channel VISUAL AURAL - MC light flashing amber - ENG 1(2) PEC SGL CH amber message on EWD - SGL amber message on SD page SC PROCEDURE PEC 1(2) SGL CH R DO NOT RESET PEC IN FLIGHT - NO CREW ACTION REQUIRED ANTICIPATE A PEC FAULT AT LANDING MAINTENANCE ACTION IS REQUIRED COMMENTS - In case of PEC FAULT at landing : . do not set PLs below FI before nose wheel is on the ground . do not use reverse on affected engine Mod 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 18 POWER PLANT 001 FEB 12 AA PEC 1(2) FAULT ALERT CONDITION VISUAL AURAL Anomaly detection on both PEC channels - MC light flashing amber - ENG 1(2) PEC amber message on EWD - Associated FAULT light on central panel SC PROCEDURE PEC 1(2) FAULT R J If below 400 ft GO AROUND procedure (2.03.17) . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY R F Above 400 ft or at acceleration altitude CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD PEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET J If PEC recovered CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AUTO J If PEC fault persists PEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AVOID sudden PL movements F Before landing CL 1+2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100% OVRD Reverse is not available on affected side. F After landing TAXI ON BOTH ENGINES Note: ACW BTC must be checked closed in order to avoid the loss of ACW bus on ground. R R R R COMMENTS - Expect NP blocked at 102.5% (overspeed stop) - Do not set PLs below FI before nose wheel is on ground. - Reverse is not available because the secondary low pitch stop retraction solenoïd is disabled which forbids the blades to go below the low pitch protection. - When the PEC is deenergized a NP cancel signal is sent to the EEC to cancel the EEC NP governing mode (that controls the NP speed at 850 rpm) on ground. - ACW may be lost if NP drops below 65.5% on the affected engine. - CL is set to OVRD to minimize NP transient when PEC is switched OFF/RESET. Mod 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 19 POWER PLANT 001 FEB 12 AA LO PITCH IN FLIGHT ALERT CONDITION Low pitch detection in flight VISUAL AURAL - MC light flashing amber - ENG LO PITCH amber message on EWD - associed amber LO PITCH flag on EWD SC PROCEDURE LO PITCH IN FLIGHT PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO R LAND ASAP SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . APPLY COMMENTS - If a low pitch is detected, pitch increases and returns to values which do not generate alert. If failure still persists, pitch will decrease again which causes a cycling situation. Mod 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 20 POWER PLANT 001 FEB 12 ENG 1(2) OVER LIMIT ALERT CONDITION VISUAL AURAL ITT above limit in flight or on ground except at start or TQ in red range or NH in red range or NL in red range - MC light flashing amber - ENG 1(2) OVER LIMIT amber message on EWD - associated ITT flag on EWD OR any parameter in red range (TQ, NH, NL) SC PROCEDURE ENG 1(2) OVER LIMIT PL affected side . . . . . . . . . . . . . . . . . . RETARD TO RESTORE NORMAL VALUES R R J If TQ, NH, and/or ITT still over limit and if conditions permit PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO LAND ASAP SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . . APPLY J If All (TQ, NH, and/or ITT) below limit or if conditions do not permit Note: BLEED VALVE may be selected OFF in order to reduce ITT on the affected engine. COMMENTS - Red limits must not be deliberately exceeded. - Check indication to determine limit exceedance and proceed accordingly. - Over limit conditions and primary engine(s) parameters must be recorded for maintenance purposes. - If conditions do not permit engine shut down, land as soon as possible using the minimum power required to sustain safe flight. Mod 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 21 POWER PLANT 001 FEB 12 AA PROP 1(2) OVER LIMIT ALERT CONDITION Propoller speed in red range VISUAL AURAL - MC light flashing amber - ENG 1(2) PROP LIM amber message on EWD SC PROCEDURE PROP 1(2) OVER LIMIT R R PL affected side . . . . . . . . . . . . . . . . . . . . . . . RETARD TO SET NP BELOW 106% PEC affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RESET PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD Note: 106% allowed to complete a flight without overshooting 73% TQ in CRZ and 75 % in CLB. J If NP decreases below 106% CONTINUE NORMAL FLIGHT J If NP remains above 106% and conditions permit PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO LAND ASAP SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . APPLY COMMENTS - Red limits must not be deliberately exceeded. - Transients in amber sector are normal during engine acceleration. - Check indication to determine limit exceedance and proceed accordingly. - Over limit conditions and primary engine(s) parameters must be recorded for maintenance purposes. - If conditions do not permit engine shut down, land as soon as possible using the minimum power required to sustain safe flight. Nevertheless NP 106% is allowed to complete a flight Mod 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 22 POWER PLANT 001 FEB 12 AA ENG 1(2) OIL TEMP BELOW 45_ _C ALERT VISUAL CONDITION Engine oil temp below 45_C - MC light flashing amber - ENG 1(2) OIL TEMP L amber message on EWD AURAL SC PROCEDURE ENG 1(2) OIL TEMP BELOW 45_ _C R R J If icing conditions are expected or present ENG POWER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . If possible, INCREASE J If no icing conditions NO CREW ACTION REQUIRED Mod 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 23 POWER PLANT 001 FEB 12 AA ENG 1(2) OIL TEMP OVHT ENG 1(2) OIL TEMP HIGH ALERT CONDITION VISUAL AURAL Engine oil temp between 125_C and 140_C - MC light flashing amber - ENG 1(2) OIL TEMP H amber message on EWD SC Engine oil temp above 140_C - MW light flashing red - ENG 1(2) OIL OVHT amber message on EWD SC PROCEDURE ENG 1(2) OIL TEMP HIGH R J If OIL TEMP between 125_ _C and 140_ _C OIL TEMP AND PRESS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR Note : If OIL temperature rise follows PL reduction, advancing PL may reduce OIL temperature . Note : If OIL temperature rise occurs in steady state conditions, a power reduction should permit a reduction in OIL temperature. J If OIL TEMP between 125_ _C and 140_ _C for more than 20 minutes PL affected side . . . . . . . . . . RETARD TO SET MINIMUM POSSIBLE POWER CAUTION : Flight time must be minimized to reduce engine operating time in these abnormal conditions. J If OIL TEMP above 140_ _C PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO LAND ASAP SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . . APPLY COMMENTS - Normal steady oil temperature is in the range 71/99_C. - Increased power setting may reduce the OIL TEMP due to the increase of fuel flow across the fuel/oil heat exchanger. - If an OIL TEMP rise occurs in steady state condition a failure of the oil cooler flap may be suspected, if no other engine malfunction is noted. In this case reducing power may limit temperature excursion. Mod 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 24 POWER PLANT 001 FEB 12 AA ENG 1(2) OIL LO PR ALERT CONDITION VISUAL AURAL Oil pressure drops below 40 PSI - MW light flashing red - ENG 1(2) OIL PRESS red message on EWD - LO PR flag in MFD system page CRC PROCEDURE ENG 1(2) OIL LO PR R PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI J If ENG OIL PRESS in red range and LO PR flag CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO LAND ASAP SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . . APPLY J If ENG OIL PRESS in red range and no LO PR flag CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO J If LO PR flag ENG RESTART IN FLIGHT procedure (2.05.02 page 10) . . . . . . . . . . APPLY J If LO PR flag still missing. LAND ASAP SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . APPLY J If ENG OIL PRESS in normal range and LO PR flag DISREGARD MAINTENANCE ACTION IS REQUIRED COMMENTS Refer to 2.05.02 page 26. Mod 5948 2.05.02 PROCEDURES FOLLOWING FAILURE P 25 POWER PLANT 001 FEB 12 AA ENG OIL LO PR (CONT’D) COMMENTS R - Engine oil low pressure is identified thanks to two low pressure detectors: - the first one driving LO PR red flag on engine secondary page MFD. - the second one is the source of oil pressure indication on engine secondary page MFD. Low pressure condition from any of these two detectors will trigger FWS alert (MW+CRC+ENG 1(2) OIL on EWD) - If LO PR flag only is activated, alert must be disregarded, oil press local alert indication press indication (in red range) must be constantly monitored during flight. - If Local alert only is activated (press indication in red range) provided LO PR flag on MFD is checked operative, twin engine operation should be resumed. - NP > 10% after a shut off procedure may indicate an incomplete feathering. In this case, the approach speed is increased to compensate the extra drag of the incompletely feathered propeller. Mod 5948 . 2.05.03 PROCEDURES FOLLOWING FAILURE P1 FUEL 001 FEB 12 AA FUEL 1(2) ABNORMAL TEMP ALERT VISUAL CONDITION Fuel temp is greater than 50_C with engine running AURAL - MC light flashing amber - FUEL 1(2) TEMP HI amber message on EWD SC Fuel temp is lower than 0_C - MC light flashing amber with engine running - FUEL 1(2) TEMP LO amber message on EWD SC PROCEDURE FUEL 1(2) ABNORMAL TEMP R J If too high (>50_ _C) Note : AVOID rapid throttle movement. OIL TEMP AND ENGINES PARAMETERS . . . . . . . . . . . . . . . . . . . MONITOR J If too low (<0_ _C) Note : If repair can’t be done, use anti-- icing additive for next refueling COMMENTS - Fuel is heated through a FUEL/OIL heat exchanger. Increasing fuel flow may reduce fuel temperature. - Rapide throttle movement with high temperature fuel may cause surge or flame out. - In case of too low temperature, anti icing additive is needed to prevent ice formation in the fuel supply system. Record it in the maintenance book. Mod 5948 2.05.03 PROCEDURES FOLLOWING FAILURE P2 FUEL 001 FEB 12 AA FUEL CLOG ALERT CONDITION VISUAL AURAL Pressure of the switch fuel pump outlet filter is greater than 25 PSI. - MC light flashing amber - ENG FUEL CLOG amber message on EWD - CLOG flag on MFD system page SC PROCEDURE FUEL CLOG R R J If FUEL CLOG engines 1 + 2 ENGINES PARAMETERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR J If abnormal engines parameters LAND ASAP MAINTENANCE ACTION IS REQUIRED J If FUEL CLOG one engine only ENGINE PARAMETERS affected side . . . . . . . . . . . . . . . . . . . . . . . MONITOR Mod 5948 2.05.03 PROCEDURES FOLLOWING FAILURE P3 FUEL 001 FEB 12 AA R FUEL FEED LO PR ALERT CONDITION Engine feed low pressure VISUAL - MC light flashing amber - FUEL FEED LO PR amber message on EWD - FEED LO PR amber light on overhead panel. AURAL SC PROCEDURE R R R FUEL FEED LO PR PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM ON ENGINE affected side . . . . . . . . . . . . . . MONITOR FOR POSSIBLE RUN DOWN J If engine runs down or if fuel quantity decreases significantly PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO FUEL PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL LAND ASAP SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . . . . APPLY CAUTION : Do not open X FEED valve. COMMENTS - The illumination of FEED LO PR light associated with PUMP RUN light identifies a LEAK in the fuel line which may lead to engine rundown. - If engine runs down or if fuel quantity decreases significantly, affected line must be isolated by selecting the pump OFF and by closing the fuel shut-- off valve. - If PUMP RUN does not illuminate, pump system may be defective and a X FEED attempt may be performed in order to restore engine supply. Max fuel unbalance has to be considered. Mod : 5948 2.05.03 PROCEDURES FOLLOWING FAILURE P4 FUEL 001 FEB 12 AA FUEL LO LVL ALERT CONDITION Fuel quantity indication below 160 kg / 352 lb - or Feeder tank not full VISUAL AURAL - MC light flashing amber - FUEL LO LVL amber message on EWD - Feeder tank in amber with fuel quantity in amber on MFD (level between 160kg and 50kg) or in red reverse video (level below 50kg) SC PROCEDURE FUEL LO LVL R R AVOID EXCESSIVE AIRCRAFT ATTITUDES J If Fuel low level both tanks LAND ASAP J If Fuel low level one tank only J If leak suspected FUEL LEAK procedure (2.05.03 page 5) . . . . . . . . . . . . . . . . . . . . . . APPLY J If no leak suspected J If fuel tank quantity < 160 kg / 352 lb FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON J If fuel tank quantityI ≥ 160 kg / 352 lb, FUEL COMSUMPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR FUEL X FEED is not necessary Note: Feeder jet pump malfunction is suspected COMMENTS - After fuel pump is selected ON, feeder tank is full within 10 minutes. - The LO LVL alert for each side will be triggered by : . the fuel remaining indicated on FQI, when it is less than 160 kg / 352 lb. . the secondary low level detection system, when feeder tank is not completely full. - In case of feeder jet pump malfunction, fuel quantity unusable in each fuel tank is raised from 20 kg / 44 lb to 130 kg / 287 lb. Mod 5948 2.05.03 PROCEDURES FOLLOWING FAILURE P5 001 FUEL FEB 12 AA FUEL LEAK ALERT CONDITION A fuel leak may be detected by either : - sum of fuel on board (FOB), read in steady flight at cruise level, and fuel used (FU), FOB+FU significantly less than fuel at departure, or - passenger observation (fuel spray from engine or wing tip), or - total fuel quantity decreasing at an abnormal rate, or - fuel imbalance, or - a tank emptying too fast (leak from engine or a hole in a tank), or - excessive fuel flow (leak from engine), or - fuel smell in the cabin VISUAL AURAL NIL NIL PROCEDURE FUEL LEAK F When a leak is confirmed LAND ASAP R R Mod 5948 J If leak from engine (excessive fuel flow or feed spray from engine) PL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FI CL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO FUEL PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FIRE HANDLE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL SINGLE ENG OPERATION procedure (2.05.02 page 1) . . . . . . . . . . APPLY J If excessive fuel flow was identified before engine shutdown FUEL X FEED valve can be opened J In all other cases, FUEL X FEED valve must remain closed J If leak not located FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN CLOSED Note : The FUEL X feed must remain closed to prevent the leak affecting both sides. F Before landing ATC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY 2.05.03 PROCEDURES FOLLOWING FAILURE P6 FUEL 001 FEB 12 AA FUEL MISMATCH ALERT CONDITION VISUAL AURAL the difference between fuel quantity computed by FMS and the fuel quantities processed by the FCU is greater than 200kg during more than 10s (on ground) or 60s (in flight). - MC light flashing amber - FUEL MISMATCH amber message on EWD SC PROCEDURE FUEL MISMATCH R R R J If leak suspected FUEL LEAK procedure (2.05.03 page 5) . . . . . . . . . . . . . . . . . . . . . . . . APPLY J If normal fuel condition FOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UPDATE IN CRZ PITCH RANGE Note : CRZ PITCH RANGE : 3_DN ; 5 _UP Mod 5848 2.05.03 PROCEDURES FOLLOWING FAILURE P7 FUEL 001 FEB 12 AA FUEL UNBALANCED ALERT CONDITION discrepancy greater than 100 Kg between the left and right tanks fuel quantities. VISUAL - MC light flashing amber - FUEL UNBALANCED amber message on EWD AURAL SC PROCEDURE FUEL UNBALANCED R R R R J If FUEL LEAK suspected FUEL LEAK procedure (2.05.03 page 5) . . . . . . . . . . . . . . . . . . . . . . . . APPLY J If normal fuel condition JIf LEFT TANK QTY > RIGHT TANK QTY FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON FUEL PUMP LEFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON FUEL PUMP RIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF JIf LEFT TANK QTY < RIGHT TANK QTY FUEL X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON FUEL PUMP RIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON FUEL PUMP LEFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF R Mod : 5848 F When fuel balanced RESUME NORMAL FUEL OPERATIONS . 2.05.04 PROCEDURES FOLLOWING FAILURE P1 ELECTRICAL SYSTEM DC BUS 1 OFF ALERT CONDITION DC BUS 1 not supplied (short circuit R protection) VISUAL - MC light flashing amber - ELEC DC 1 amber message and ELEC DC GEN amber message on EWD - DC GEN 1 FAULT, DC BUS 1 OFF, AC BUS 1 OFF, INV 1 FAULT and DC SVCE/UTLY BUS SHED amber lights on overhead panel - DC GEN 1 FAULT, DC BUS (1) OFF, DC BUS 1 OFF, INV 1 FAULT and DC SVCE/UTLY BUS SHED amber message on AC/DC SD page 001 FEB 12 AURAL SC PROCEDURE DC BUS 1 OFF R DC GEN 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AUTO PRESS FAULT procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY DC SVCE AND UTLY BUS SHED . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN ON ADC CAPT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IAS / BARO ALT Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY DC BUS 1 EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK F At touch down IDLE GATE LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL DC BUS 1 LOST EQUIPMENT LIST R R R R R R R Flight controls - CAPT STICK SHAKER & PUSHER Indicating/recording - DU1 & DU3 Engines - IDLE GATE (AUTO mode) - ENG 1 oil press / temp Navigation and Communications - Weather Radar - TAWS advisory - DME Note : If two DME are installed, DME remains operational * - HF 1 *-- SELCAL *-- OBSVR AUDIO SYS Ice & rain protection - CAPT STATIC PROBES - STBY STATIC PROBES - CAPT SIDE WINDOW Air - ENG1 & 2 - BLEED LEAK CAUTION - DUCT/COMPT Cockpit and cabin temperature indication - Automatic Pressure CTL - RECIRC FAN 1 Lights - CABIN - LAT LT (LEFT) - CAPT NORM LT (DOME, MIP, CHARTHOLDER, STORM) - ANN LT TEST - LMU - PED & LT Information systems *-- EFB1 PWR (*) if installed .../... Mod 5948 . 2.05.04 PROCEDURES FOLLOWING FAILURE P 1A 001 ELECTRICAL SYSTEM FEB 12 DC BUS 1 OFF (CONT’D) For more information on BUS EQUIPMENT LISTS see 1.06.60 COMMENTS - DC SVCE/UTLY BUS pushbutton may be maintained ON with SHED illuminated in order to keep DC UTLY BUS 2 on line. - Stick pusher is lost. AC BUS 1 OFF ALERT CONDITION AC BUS not supplied (short circuit protection) VISUAL AURAL - MC light flashing amber - ELEC AC 1 amber message on EWD - associated INV FAULT and BUS OFF amber lights on overhead panel - associated INV FAULT and BUS OFF amber message on AC/DC SD page SC R PROCEDURE AC BUS 1 OFF Note : Wait for 10 seconds in order to confirm the failure. DC BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ISOL THEN ON J IF AC BUS 1 OFF persists AC BUS 1 EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . CHECK AC BUS 1 LOST EQUIPMENT LIST 115 AC BUS 1 26 AC BUS 1 - RAD ALT / GPWS / TCAS - ENG 1 & 2-- BLEED LEAK DETECTION For more information on BUS EQUIPMENT LISTS see 1.06.60 Mod 5948 . 2.05.04 PROCEDURES FOLLOWING FAILURE P2 001 ELECTRICAL SYSTEM AA FEB 12 DC BUS 2 OFF ALERT CONDITION DC BUS 2 not supplied (short circuit protection) VISUAL AURAL - MC light flashing amber - ELEC DC 2 amber message and ELEC DC GEN amber message on EWD - DC GEN 2 FAULT, DC BUS 2 OFF, AC BUS 2 OFF, INV 2 FAULT and DC SVCE/UTLY BUS SHED amber lights on overhead panel - DC GEN 2 FAULT, DC BUS 2 OFF, AC BUS 2 OFF, INV 2 FAULT and DC SVCE/UTLY BUS SHED amber message on AC/DC SD page SC PROCEDURE DC BUS 2 OFF R DC GEN 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CAPT F/O SWITCHING ADC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SWITCH TO SYS 1 ICP F/O LOST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE ICP CAPT VHF 1 / XPDR 1 / VOR-- ILS 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS PAX INSTRUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE PA DC SVCE / UTLY BUS PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN ON DC BUS 2 EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY Note: ILS CAT 2 IS PROHIBITED FAfter touch down TAXI ON BOTH ENGINES FAt Parking Connect GPU before CL1 set to FUEL SO R DC BUS 2 LOST EQUIPMENT LIST Flight controls - F/O STICK SHAKER - TLU auto mode Indicating/recording - F/O MCDU - DU5 Ice & rain protection - F/O STATIC PROBES - F/O WIPER - F/O SIDE WINDOW Hydraulic - AUX HYD PUMP auto mode To be continued next page ...\... Mod 5948 . 2.05.04 PROCEDURES FOLLOWING FAILURE P 2A 001 ELECTRICAL SYSTEM FEB 12 DC BUS 2 OFF (CONT’D) R DC BUS 2 LOST EQUIPMENT LIST(CONT’D) Engines - IDLE GATE CAUTION Air - RECIRC FAN 2 Landing gear - Secondary indication Navigation and Communications - ICP F/O - VOR-- ILS 2 ( CAT II capability lost) *-- ACARS - VHF 2 - ( TAWS & TCAS) - XPDR 2 - ADC 2 * - GPS 2 *-- DOOR VIDEO Lights - TAXI and TO - WING - FLT COMPT - OVHD - LMU - F/O NORM LT (UTILITY SPOT & FLOOD, CHARTHOLDER) - (NO DVCE) & SEAT BELTS Doors - DOORS AFT LH & RH Monitoring - CDLS SPLY Information systems *-- EFB2 PWR (*) if installed For more information on BUS EQUIPMENT LISTS see 1.06.60 COMMENTS - CM1 is pilot flying due to complete loss of CM2 panel. Mod 5948 . 2.05.04 PROCEDURES FOLLOWING FAILURE P3 ELECTRICAL SYSTEM 001 FEB 12 AA R AC BUS 2 OFF ALERT VISUAL CONDITION AC BUS not supplied (short circuit protection) AURAL - MC light flashing amber - ELEC AC 2 amber message on EWD - associated INV FAULT and BUS OFF amber lights on overhead panel - associated INV FAULT and BUS OFF amber message on AC/DC SD page SC PROCEDURE R AC BUS 2 OFF R Note : Wait for 10 seconds in order to confirm the failure. DC BTC . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ISOL THEN ON J If AC BUS 2 OFF persists CABIN TEMP SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN AC BUS 2 EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK AC BUS 2 LOST EQUIPMENT LIST R R 115 AC BUS 2 26 AC BUS 2 - CABIN TEMPERATURE SENSOR FAN - * RAD ALT 2 - PRINTER (*) If installed For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60 COMMENTS - The DC BTC pushbutton controls also the AC BTR. The reset of this pushbutton may help to recover the affected AC BUS. - In case of inverter failure, the AC BUS OFF light illuminates during 10 seconds through the BTR temporizing, then extinguishes. The AC BUS is then available. An AC BUS failure is effective as soon as the light stays on after 10 seconds. Mod 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P4 ELECTRICAL SYSTEM ACW BUS 1 (2) OFF ALERT CONDITION ACW BUS not supplied (short circuit protection) 001 FEB 12 VISUAL AURAL - MC light flashing amber - ELEC ACW 1 (2) amber message on EWD - associated ACW GEN FAULT and ACW BUS OFF amber lights on overhead panel - associated ACW GEN FAULT and ACW BUS OFF amber message on HYD/ACW SD page. SC PROCEDURE R ACW BUS 1 (2) OFF LEAVE AND AVOID ICING CONDITIONS AS LONG AS ICING CONDITIONS EXIST ICE ACCRETION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP ACW GEN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF J If ACW BUS 1 OFF CAPT SWITCHING ADC . . . . . . . . . . . . . . . . . . . . . . . . SWITCH TO SYS 2 HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON J If Icing condition ANTI ICING PROP 1(2) FAULT procedure(2.05.09) . . . . . . . . . . . APPLY ANTI ICING HORNS 1(2) FAULT procedure(2.05.09) . . . . . . . . . . APPLY ACW BUS 1 LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . CHECK PERIODICALLY COMPARE IAS & ALT TO IESI Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY ACW BUS 1 LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . CHECK J If ACW BUS 2 OFF F/O SWITCHING ADC . . . . . . . . . . . . . . . . . . . . . . . . . SWITCH TO SYS 1 HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON PERIODICALLY COMPARE IAS & ALT TO IESI J If Icing condition ANTI ICING PROP 1(2) FAULT procedure(2.05.09) . . . . . . . . . . . APPLY ANTI ICING HORNS 1(2) FAULT procedure(2.05.09) . . . . . . . . . . APPLY ACW BUS 1 LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . CHECK PERIODICALLY COMPARE IAS & ALT TO IESI Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY ACW BUS 1 LOST EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . CHECK J If IAS discrepancy occurs UNRELIABLE AIRSPEED INDICATION procedure (2.05.12) . . . . . . . APPLY F After touch down TAXI ON BOTH ENGINES Mod 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P5 ELECTRICAL SYSTEM 001 FEB 12 + ACW BUS 1 OFF / ACW BUS 2 OFF ACW BUS 1 LOST EQUIPMENT LIST Ice & rain protection - PROBES HTG - CAPT PITOT - PROBES HTG - CAPT ALPHA R - PROBES HTG - CAPT TAT R - ANTI-- ICING PROP 1 - L WINDSHIELD HTG - ANTI-- ICING RUD & L ELEV HORNS Hydraulic R - MAIN BLUE PUMP Lights - L LANDING LIGHT - L AND REAR STROBES - FLT COMP - OVHD ( integrated inst & panel) ACW BUS 2 LOST EQUIPMENT LIST Ice & rain protection - ICE DETECTOR R - PROBES HTG - F/O PITOT - PROBES HTG - F/O ALPHA - PROBES HTG - F/O TAT - ANTI-- ICING PROP 2 - R WINDSHIELD HTG - ANTI-- ICING AIL & R ELEV HORNS Hydraulic - GREEN PUMP Electrical power - TRU (not available) Lights - TAXI AND TO LIGHTS - R LANDING LIGHT - RIGHT STROBE For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60 COMMENTS - Monitor airspeed on non affected side due to loss of affected side pitot heating. Mod 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P6 ELECTRICAL SYSTEM 001 FEB 12 AA ACW TOTAL LOSS ALERT CONDITION ACW total loss VISUAL AURAL - MC light flashing amber - ELEC ACW 1+2 amber message on EWD - both ACW GEN FAULT and ACW BUS OFF amber message on HYD/ACW SD page SC PROCEDURE R ACW TOTAL LOSS LEAVE AND AVOID ICING CONDITIONS AS LONG AS ICING CONDITIONS EXIST ICE ACCRETION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP ACW GEN 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OFF PERIODICALLY COMPARE IAS & ALT on PFDs WITH IESI Note : IESI probes are de-- iced by AC STBY BUS. IESI becomes the reference instrument. ACW TOTAL LOSS EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY HYD MAIN PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF LDG GEAR NORMAL OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOST NORMAL BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LOST LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.5 Note : Refer to Part 4 to determine LDG DIST F Before landing LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN HYD BLUE PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK FLAPS 15_ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD LDG GEAR GRAVITY EXTENSION procedure (2.05.07 page 1) . . . . . . . APPLY FLAPS 30_ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD F After touch down REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD BRAKE HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD TAXI ON BOTH ENGINES Mod 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P7 ELECTRICAL SYSTEM 001 FEB 12 AA ACW TOTAL LOSS R ACW TOTAL LOST EQUIPMENT LIST Ice & rain protection - ICE DETECTOR - PROBES HTG - CAPT and F/O PITOT - PROBES HTG - CAPT and F/O R ALPHA - PROBES HTG - CAPT and F/O TAT - L and R WINDSHIELD HTG - ANTI-- ICING (all) HORNS - ANTI-- ICING PROP 1 + 2 Hydraulic R - MAIN BLUE & GREEN PUMP Electrical power - TRU (not available) Lights - TAXI AND TO LIGHTS - LANDING (all) - STROBES(all) - FLT COMP - OVHD(integrated inst & panel) For more information on BUS EQUIPMENT LISTS see FCOM 1.06.60 COMMENTS - IESI speed tape will be used as a reference as both sides pitot heating is lost. - The HYD DC AUX PUMP allows flaps extension, maintains the nosewheel steering and powers the emergency brake accumulator. - If a go around has to be performed : . landing gear will not retract . flaps will retract with a lower speed than normal normal due to DC AUX PUMP size. - Landing distance is multiplied by 1.5 due to loss of normal braking. Mod 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P8 ELECTRICAL SYSTEM 001 FEB 12 AA DC ESS BUS OFF ALERT CONDITION VISUAL AURAL DC ESS BUT not supplied - MC light flashing amber - ELEC DC ESS amber message on EWD - DC ESS OFF message on AC/DC SD page SC PROCEDURE R DC ESS BUS OFF LEAVE AND AVOID ICING CONDITIONS HYD GREEN PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON J If DC ESS BUS recovered CAUTION: DO NOT RESTORE HYD GREEN PUMP TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN ON MAINTENANCE ACTION IS REQUIRED J If DC ESS BUS FAULT persists TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . F/O DESCENT TOWARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FL100 / MEA ANTI/DE-- ICING MODE SEL AUTO FAULT procedure (2.05.09) . . . . . . . . APPLY PERF PAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT TAT 2 ADC CAPT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IAS / BARO-- ALT LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE DC ESS BUS EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY J If Cockpit Door Locking System installed COCKPIT DOOR MANUAL LOCK BOLT(S) . . . . . . MOVE TO CLOSE POSITION CAUTION: At least two crewmembers must remain in the cockpit during that time Note: Cockpit Door Control Panel FAULT LIGHT is inoperative. Note: When the door is locked with the manual bolt(s), the emergency access to the cockpit is unavailable. F Before landing ANTI-- SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ANTI-- SKID FAULT procedure (2.05.07) . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY F After touch down TAXI ON BOTH ENGINES COMMENTS - For DC ESS BUS OFF LOST EQUIPMENT LIST refer to 1.06.60 pages 9 and 10. Mod 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P9 ELECTRICAL SYSTEM AA 001 FEB 12 DC EMER BUS OFF ALERT CONDITION DC EMER BUS no longer supplied VISUAL - MC light flashing amber - ELEC DC EMER amber message on EWD - EMER BUSS OFF message on AC/DC SD page AURAL SC PROCEDURE R DC EMER BUS OFF LEAVE AND AVOID ICING CONDITIONS HYD MAIN BLUE PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON J If DC EMER BUS recovered CAUTION: DO NOT RESTORE HYD MAIN BLUE PUMP TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN ON MAINTENANCE ACTION IS REQUIRED J If DC EMER BUS FAULT persists TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF VHF 2 / XPDR 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE DESCENT TOWARD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FL 100 / MEA STBY PITCH TRIM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE AS RQD LANDING ELEVATION . . . . . . . . . . . . . . . . . . . . . SET PRESSURE ALTITUDE CAUTION: Minimize flight time to reduce time without engine fire detection TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS ICE ACCRETION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR IEP DC EMER BUS OFF EQUIPMENT LIST . . . . . . . . . . . . . . . . . . . . . . . CHECK Affected equipment fault Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY J If ice accretion DE-- ICING AIRFRAME FAULT procedure (2.05.09) . . . . . . . . . . . . . . . . APPLY DE-- ICING MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVRD DE-- ICING MODE SEL FAULT procedure(2.05.09) . . . . . . . . . . . . . . . . APPLY ANTI-- ICING PROP FAULT procedure(2.05.09) . . . . . . . . . . . . . . . . . . . APPLY ANTI-- ICING HORNS FAULT procedure(2.05.09) . . . . . . . . . . . . . . . . . . APPLY F Before landing ANTI-- SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF N/W STEERING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF ANTI-- SKID FAULT procedure (2.05.07) . . . . . . . . . . . . . . . . . . . . . APPLY F After touch down TAXI ON BOTH ENGINES COMMENTS - For DC EMER BUS OFF LOST EQUIPMENT LIST refer to 1.06.60 pages 7 and 8. - ACW powered blue hydraulic pump is lost. HYD X FEED must be selected to open position to pressurize blue hydraulic circuit. Mod 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P 10 ELECTRICAL SYSTEM AA 001 FEB 12 DC GEN FAULT ALERT CONDITION VISUAL One DC generation - MC light flashing amber channel inoperative - ELEC DC GEN amber message on EWD - associated DC GEN FAULT amber light on overhead panel - associated DC GEN FAULT message on AC/DC SD page. AURAL SC PROCEDURE DC GEN FAULT R DC GEN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF J If OAT exceeds ISA + 25 FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 MAX F After touch down TAXI ON BOTH ENGINES F At parking J If DC GEN 2 FAULT Connect GPU before CL1 set to FUEL SO COMMENTS - If OAT exceeds ISA+25, the maximum allowed flight level is FL 200 due to ventilation problem of the remaining DC generator. INV 1(2) FAULT ALERT CONDITION Under/Over voltage at INV output VISUAL - MC light flashing amber - ELEC INV 1(2) amber message on EWD - associated INV FAULT amber light on overhead panel - INV 1(2) FAULT message on AC/DC SD page AURAL SC PROCEDURE INV 1(2) FAULT R MAINTENANCE ACTION IS REQUIRED COMMENTS - After 10 seconds following INV FAULT, the AC BTC is automatically closed causing affected AC BUS and AC STBY BUS to be supplied from the remaining inverter. Mod 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P 11 ELECTRICAL SYSTEM AA 001 FEB 12 ACW GEN FAULT ALERT CONDITION VISUAL AURAL One ACW generation channel inoperative - MC light flashing amber - ELEC ACW GEN 1 (2) amber message on EWD - associated ACW GEN FAULT amber light on overhead panel - ACW GEN 1 (2) FAULT message on HYD/ACW SD page SC PROCEDURE R ACW GEN FAULT R ACW GEN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF LEAVE AND AVOID ICING CONDITIONS J If ACW GEN 2 FAULT F After touch down TAXI ON BOTH ENGINES DC SVCE/UTLY BUS SHED ALERT CONDITION VISUAL AURAL One DC UTLY BUS automatically shed after a source overload - MC light flashing amber - ELEC DC SHED amber message on EWD - DC SVCE/UTLY BUS SHED amber light on overhead panel - SHED message on AC/DC SD page SC PROCEDURE DC SVCE/UTLY BUS SHED R DC SVCE/UTLY BUS PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD COMMENTS - For DC SVCE/UTLY BUS SHED LOST EQUIPMENT LIST refer to 1.06.60 pages 12 to 14. - It is crew decision to select DC SVCE/UTLY BUS pushbutton OFF or not. In case this pushbutton is selected OFF, it will : . confirm automatic shedding of affected DC UTLY BUS . shut off the non affected DC UTLY BUS and the DC SVCE BUS Mod 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P 12 ELECTRICAL SYSTEM 001 FEB 12 AA R MAIN ( OR EMER) BAT CHG FAULT ALERT CONDITION VISUAL AURAL Incipient battery thermal runaway or charge contactor failure - MC light flashing amber - ELEC BAT CHG amber message on EWD - associated CHG FAULT amber light on overhead panel - associated CHG FAULT message on AC/DC SD page SC PROCEDURE R MAIN (or EMER) BAT CHG FAULT CHG associated . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Mod 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P 13 ELECTRICAL SYSTEM 001 FEB 12 AA R EMER + MAIN BAT CHG LOSS ALERT CONDITION VISUAL AURAL MFC failure leading to dual battery charge contactors loss - MC light flashing amber - ELEC CHG LOSS amber message on EWD - both amber arrows illuminated on overhead panel - CHG FAULT message on AC/DC SD page NIL PROCEDURE R EMER + MAIN BAT CHG LOSS MFC MODULES, one at a time . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF / RESET J If EMER + MAIN BAT recovered MAINTENANCE ACTION IS REQUIRED J If EMER + MAIN BAT CHG LOSS persists J If no BAT arrow MAINTENANCE ACTION IS REQUIRED J If BOTH BAT arrows illuminated CAUTION : if one ACW GEN is lost, HYD MAIN BLUE PUMP to be set to OFF and HYD X FEED to be set to ON TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON JIf TRU online MINIMIZE FLIGHT TIME( without battery charge) JIf TRU FAULT LAND ASAP COMMENTS - This case should only occur following a MFC software failure. Mod 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P 14 ELECTRICAL SYSTEM 001 FEB 12 AA BAT DISCHARGE IN FLIGHT ALERT CONDITION VISUAL AURAL Battery(ies) discharge in flight (but DC main sources available) - MC light flashing amber - ELEC BAT DISCH amber message on EWD - Left and/or Right amber arrow(s) illuminated on overhead panel - MAIN (EMER) BAT amber message on AC/DC SD page SC PROCEDURE R BAT DISCHARGE IN FLIGHT ENG START ROTARY SELECTOR . . . . . . . . . . . . . . . . . . . OFF / START ABORT CAUTION : if one ACW GEN is LOST, HYD MAIN BLUE PUMP to be set to OFF and HYD X FEED to be set to ON TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON J If BAT discharge disappears CONTINUE NORMAL FLIGHT - MAINTENANCE ACTION IS REQUIRED J If battery(ies) still discharging TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AS RQD HYD MAIN BLUE PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS RQD LAND ASAP Mod : 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P 15 ELECTRICAL SYSTEM AA 001 FEB 12 AC STBY BUS FAULT ALERT CONDITION TBD VISUAL - MC light flashing amber - ELEC AC SBY BUS amber message on EWD AURAL SC PROCEDURE AC STBY BUS FAULT R APM . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI or LO SPD ACCORDING TO IAS SPEED TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE DC STBY BUS FAULT ALERT CONDITION ELEC DC STBY BUS ± 19.5 V VISUAL AURAL - MC light flashing amber - ELEC DC SBY BUS amber message on EWD SC PROCEDURE DC STBY BUS FAULT R R EMER BAT CHG . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF then ON J If DC STBY BUS FAULT persists CAUTION : if one ACW GEN is LOST, HYD MAIN BLUE PUMP to be set to OFF and HYD X FEED to be set to ON TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON J If DC STBY BUS recovered CAUTION : DO NOT RESTORE HYD MAIN BLUE PUMP J If DC STBY BUS FAULT still persists TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AS RQD HYD MAIN BLUE PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS RQD AVNX IOM 12 + IOM 13 LOSS procedure(2.05.12) . . . . . . . . . . . . . . . . APPLY LOST EQUIPMENT LIST(1.06.60) . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK F Before landing LDG GEAR GRAVITY EXTENSION procedure(2.05.07) . . . . . . . . . . . APPLY REDUCED FLAPS LANDING procedure(2.05.06) . . . . . . . . . . . . . . . APPLY Mod : 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P 16 ELECTRICAL SYSTEM AA 001 FEB 12 DC STBY BUS UND/V ALERT CONDITION DC STBY BUS UND/V <18 V VISUAL AURAL - MC light flashing amber - ELEC STBY UND/V amber message on EWD SC PROCEDURE DC STBY BUS UND/V J If no DUAL DC GEN LOSS CAUTION : If one ACW GEN is LOST, HYD MAIN BLUE PUMP to be set to OFF and HYD X FEED to be set to ON TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON J If STBY BUS UND/V disappears TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAINTAIN ON MAINTENANCE ACTION IS REQUIRED J If STBY BUS UND/V persists TRU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AS RQD HYD MAIN BLUE PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON AS RQD DC STBY BUS FAULT procedure(2.05.04) . . . . . . . . . . . . . . . . . . . . . APPLY J If DUAL DC GEN LOSS and TRU not available FFor approach only STBY BUS OVRD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SELECT Mod : 5948 2.05.04 PROCEDURES FOLLOWING FAILURE P 17 ELECTRICAL SYSTEM AA STBY BUS AND BAT ONLY LOST EQUIPMENT LISTS Mod 5948 001 FEB 12 2.05.04 PROCEDURES FOLLOWING FAILURE P 18 ELECTRICAL SYSTEM AA STBY BUSSES AND BAT ONLY LOST EQUIPMENT LISTS (CONT’D) Mod 5948 001 FEB 12 2.05.05 PROCEDURES FOLLOWING FAILURE P1 HYDRAULIC 001 FEB 12 AA HYD BLUE (GREEN) LO LVL ALERT CONDITION VISUAL AURAL Tank compartment fluid quantity below 2,5 l (0,67 US gal) - MC light flashing amber - HYD BLUE LO LVL (HYD GREEN LOLV) amber message on EWD + on ACW HYD SD page amber LO LVL display - associated LO LVL amber light and LO PR amber Iight on MAIN PUMP pushbutton, on overhead panel SC PROCEDURE R HYD BLUE (GREEN) LO LVL J If blue system affected HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OFF HYD MAIN BLUE PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HYD AUX PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF FFor approach REDUCED PLAPS LANDING procedure(2.05.06) . . . . . . . . . . . . . . . . APPLY FAfter touch down USE NORMAL BRAKE FOR STEERING TAXI ON BOTH ENGINES J If green system affected HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OFF HYD GREEN PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.5 Note : Refer to Part 4 to determine landing distance F Before landing LDG GRAVITY EXTENSION procedure(2.05.07) . . . . . . . . . . . . . . . APPLY F After touch down REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD BRK HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD TAXI ON BOTH ENGINES HYD SYS LOST EQUIPMENT LIST BLUE R FLAPS / SPOILERS / N/W STEERING PROP BRK (If installed) EMER AND PARKING BRK(on accumulator only) Mod 5948 GREEN LDG GEAR EXT / RET NORMAL BRK . 2.05.05 PROCEDURES FOLLOWING FAILURE P 1A HYDRAULIC 001 FEB 12 AA HYD BLUE LO LVL/HYD GREEN LO LVL COMMENTS - In case of LO LVL, X FEED remains closed and X FEED valve operation is automatically inhibited. - For emergency/parking brake, the brake accumulator allows at least six applications of braking force at full braking pressure. - If green system affected, landing distance is increased due to loss of normal braking. If a go around has to be performed, landing gear will not retract. Mod 5948 . 2.05.05 PROCEDURES FOLLOWING FAILURE P2 HYDRAULIC 001 FEB 12 AA BOTH MAIN HYD PUMPS LOSS ALERT VISUAL CONDITION Loss of hydraulic pump information AURAL - MC light flashing amber - HYD PUMPS LOSS amber message on EWD SC PROCEDURE BOTH MAIN HYD PUMPS LOSS R R R MAIN BLUE AND GREEN PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK OFF LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.5 Note : Refer to Part 4 to determine landing distance F Before landing LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN HYD BLUE PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK FLAPS 15_ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD LDG GEAR GRAVITY EXTENSION procedure (2.05.07) . . . . . . . . . . . . . APPLY FLAPS 30_ . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD F After touch down REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD BRK HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD TAXI ON BOTH ENGINES BOTH MAIN HYD PUMPS LOST EQUIPMENT LIST BLUE GREEN Recovered when LDG GEAR lever is DOWN FLAPS / SPOILERS / N/W STEERING PROP BRK (if applicable) EMER AND PARKING BRK (on R accumulator only) LDG GEAR EXT / RET NORM BRK COMMENTS - For emergency/parking brake, the brake accumulator allows at least six applications of braking force at full braking pressure. - Landing distance is increased due to loss of normal braking. If a go around has to be performed, landing gear will not retract. Mod 5948 . 2.05.05 PROCEDURES FOLLOWING FAILURE P3 HYDRAULIC 001 FEB 12 AA BOTH HYD SYS LOSS ALERT CONDITION VISUAL AURAL Loss of hydraulic system information - MC light flashing amber - HYD SYS LOSS amber message on EWD SC PROCEDURE BOTH HYD SYS LOSS R R R MAIN AND AUX PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF F For approach GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAP OVRD LDG GEAR GRAVITY EXTENSION procedure (2.05.07) . . . . . . . . . . . . . APPLY V APP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VmHB 0 + 5 KT + WIND EFFECT LDG DIST . . . . . . . . . . . . . . . . . . . . . MULTIPLY LDG DIST FLAPS 30 BY 2.9 Note: Refer to Part 4 to determine VmHB and LDG DIST Note : LDG Gear cannot be retracted CAUTION : Tail strike may occur if pitch attitude exceeds 8° during the flare depending upon vertical speed at touch down. F After touch down REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD BRK HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD TAXI ON BOTH ENGINES BOTH HYD SYS LOST EQUIPMENT LIST BLUE R FLAPS / SPOILERS / N/W STEERING PROP BRK (if applicable) EMER AND PARKING BRK (on accumulator only) GREEN LDG GEAR EXT / RET NORM BRK COMMENTS - The landing distance is increased due to loss of flaps and normal braking. - For emergency/parking brake, the brake accumulator allows at least six applications of braking force at full braking pressure. - If a go around has to be performed, landing gear will not retract. Mod 5948 2.05.05 PROCEDURES FOLLOWING FAILURE P4 001 HYDRAULIC FEB 12 AA HYD BLUE (GREEN) LO PR / HYD BLUE (GREEN) OVHT ALERT CONDITION VISUAL AURAL Pump delivery - MC light flashing amber pressure below 1500 - HYD BLUE (GREEN) (AUX) LO PR amber PSI (103.5 bar) message on EWD - associated pump LO PR amber light on overhead panel and amber indication on ACW/HYD SD page SC Pump case drain line temperature above 121_C SC - MC light flashing amber - HYD BLUE (GREEN) (AUX) OVHT amber message on EWD - associated OVHT amber light on overhead panel and amber indication on ACW/HYD SD page PROCEDURE HYD BLUE (GREEN) LO PR / HYD BLUE (GREEN) OVHT R HYD PUMP affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF HYD X FEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON HYD AUX LO PR / HYD AUX OVHT R HYD AUX PUMP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF COMMENTS - Failed system users are supplied by the non affected pump when opening the cross feed. - In case of overheat, an attempt to restore the system may be performed after OVHT alert has extinguished. Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P1 FLIGHT CONTROL 001 FEB 12 AA FLAPS UNLK ALERT CONDITION Flaps untimely retraction of more than 3_ when flaps extended VISUAL - MW light flashing red - FLAPS UNLK red message on EWD AURAL CRC PROCEDURE FLAPS UNLK R R R J If before V1 TAKE OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ABORT J If after V1 VR, V2 . . . . . . . . . . . . . . . . . . SPEED BUGS AUTOMATICALLY INCREASED J If FLAPS UNLK during approach GO AROUND procedure (2.03.20) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . APPLY VGA . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS F When possible FLAPS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0_ REDUCED FLAPS LANDING procedure (2.05.06) . . . . . . . . . . . . . . . . . APPLY Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P2 FLIGHT CONTROL 001 FEB 12 AA FLAPS JAM / UNCOUPLED / ASYM ALERT FLAPS UNCOUPLED : No specific alert. FLAPS ASYM / JAM : CONDITION Flaps asymmetry of more than 6.7_ during flaps actuation VISUAL AURAL - MC light flashing amber - FLAPS ASYM amber message on EWD SC Flaps have not - MC light flashing amber reached the selected - FLT CTL amber messsage on EWD position after 30s. - FLAPS JAM amber message on EWD SC PROCEDURE FLAPS JAM / UNCOUPLED / ASYM FLAPS CTL LEVER . . . . . . . . . . . . . . . . . . . NEAR FLAPS PRESENT POSITION R F For approach REDUCED FLAPS LANDING procedure (2.05.06) . . . . . . . . . . . . . . . . . APPLY Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P3 001 FLIGHT CONTROL FEB 12 AA REDUCED FLAPS LANDING PROCEDURE REDUCED FLAPS LANDING R GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAP OVRD STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . . . . PROHIBITED R R Note : Refer to Part 4 to determine VmHB and LDG DIST Note: ILS CAT 2 IS PROHIBITED CAUTION : Tail strike may occur if pitch attitude exceeds 8° during the flare depending upon vertical speed at touch down. COMMENTS - GPWS must be selected GPWS OVRD / FLAP OVRD to prevent nuisance alerts on final approach. Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P4 FLIGHT CONTROL 001 FEB 12 AA STICK PUSHER / SHAKER FAULT ALERT CONDITION Stick pusher / shaker fault VISUAL - MC light flashing amber - FLT CTL PUSHER amber message on EWD - FAULT amber light in STICK PUSHER pushbutton AURAL SC PROCEDURE STICK PUSHER / SHAKER FAULT R STICK PUSHER / SHAKER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TA ONLY IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS+10KT SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15 Note : Refer to Part 4 to determine VmHB/VmLB and LDG DIST CAUTION : AP single source prohibited below 1000 ft AGL is prohibited. COMMENTS - The minimum maneuvering speeds are increased by 10 kt in order to increase stall margin. - If ALPHA probes are not heated, ice accretion may modify alpha probes indication. If angle of attack information offsets 4_, STICK PUSHER / SHAKER FAULT light illuminates. When living icing conditions, as soon as alpha probes are cleared of ice, STICK PUSHER / SHAKER may be recovered by selecting it ON. Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P5 FLIGHT CONTROL 001 FEB 12 AA PITCH TRIM ASYM ALERT CONDITION Pitch tabs desynchronisation VISUAL - MC light flashing amber - PITCH TRIM ASYM amber message on EWD AURAL SC PROCEDURE PITCH TRIM ASYM R AP DISCONNECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM MANUALLY PITCH TRIM INOPERATIVE procedure (2.05.06) . . . . . . . . . . . . . . . . . . . . . APPLY Note: ILS CAT 2 IS PROHIBITED COMMENTS - When a PITCH TRIM ASYM alert is generated, AP automatically disconnects and cannot be reengaged. However, it is recommended to manually confirm AP disconnection. - Don’t use the trims anymore and apply PITCH TRIM INOPERATIVE procedure. PITCH TRIM INOPERATIVE ALERT Both normal and standby pitch trim controls are inoperative. PROCEDURE PITCH TRIM INOPERATIVE R EXISTING CONFIGURATION AND SPEED . . . . . . MAINTAIN AS LONG AS POSSIBLE F For approach STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . . . PROHIBITED FLAPS . . . . . . . . . . . . . . . . . . EXTEND AT VFE FOR EACH CONFIGURATION IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS + 10 KT SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15 Note: ILS CAT 2 IS PROHIBITED Note : Refer to Part 4 to determine VmHB / VmLB and LDG DIST COMMENTS - Maintain existing configuration and speed as long as possible to avoid high forces on the columns. - The landing distance is increased due to landing speed increase. Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P6 FLIGHT CONTROL AA 001 APR 11 DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTERING UNIT FAIL ALERT DUTCH ROLL TENDANCY: no specific alert RUDDER RELEASABLE CENTERING UNIT FAIL CONDITION releasable centering unit clutch energized more than 60s with Y/D off VISUAL - MW light flashing amber - FLT CTL RUD RCU amber message on EWD AURAL SC PROCEDURE DUTCH ROLL TENDENCY / RUDDER RELEASABLE CENTERING UNIT FAIL J If YD is available YD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE J If YD is not available LOCK THE RUDDER PEDALS WITH THE FEET TO PREVENT UNEXPECTED RUDDER PEDAL MOVEMENT Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P7 FLIGHT CONTROL 001 FEB 12 AA PITCH DISCONNECT ALERT CONDITION Pitch coupling mechanism disconnected VISUAL - MW light flashing red - PITCH DISC red message on EWD AURAL CRC PROCEDURE PITCH DISCONNECT R R R R FREE COLUMN(S) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY PF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FREE CONTROL COLUMN SIDE IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT MAX BANK ANGLE . . . . . . . . . . . . . . . . . . . . . . . . 30_ MAX UNTL FLAPS EXTENSION LEAVE AND AVOID ICING CONDITIONS IAS MINI . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS + 10 KT JIf one elevator is stuck to full down position IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154 KT EXTEND FLAPS IF NECESSARY JIf elevator jamming occurs at take off IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 161 KT MAINTAIN FLAPS IF NECESSARY JIf other cases IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT F For approach STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . . . PROHIBITED LAND AT AIRPORT WITH MINIMUM CROSSWIND IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS + 10 KT SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15 F For landing PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . REDUCE SMOOTHLY TO FLARE Note: ILS CAT 2 IS PROHIBITED Note : Refer to Part 4 to determine LDG DATA F When on ground PITCH RECONNECTION ON GROUND procedure (2.05.06) . . . . . . . . . APPLY COMMENTS - As both elevator channels are disconnected, pitch control efficiency is reduced. Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P8 FLIGHT CONTROL 001 FEB 12 AA PITCH RECONNECTION ON GROUND This procedure may be applied on ground after a PITCH DISCONNECT. PROCEDURE PITCH RECONNECTION ON GROUND GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ENGAGE BOTH COLUMNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK LOCKED ELEV CLUTCH GUARDED PB . . . . . . . . . . . . . . . . . . . . . . . DEPRESS AND HOLD F When PITCH DISC extinguishes on EWD ELEV CLUTCH GUARDED PB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RELEASE PITCH RECONNECT ON EWD . . . . . . . . . . . . . . . . . . . . CHECK EXTINGUISHED GUST LOCK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BOTH COLUMNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK COUPLED PITCH RECONNECT ALERT CONDITION Pitch recoupling system actived VISUAL AURAL - MW light flashing red - PITCH RECONNCT red message on EWD CRC PROCEDURE PITCH RECONNECT R NO CREW ACTION MAINTENANCE ACTION IS REQUIRED Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P9 FLIGHT CONTROL 001 FEB 12 AA TLU FAULT ALERT CONDITION VISUAL Both ADC are lost, or - MC light flashing amber disagree between actual and - FLT CTL TLU amber message on theoretical TLU position, or EWD TLU synchro position failure - TLU FAULT amber light on overhead panel AURAL SC PROCEDURE TLU FAULT R R J If ADC 1 + 2 are lost J If IAS above 185 kt TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI SPD J If IAS below 185 kt TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD DISREGARD TLU FAULT ALERT J If at least one ADC operates J If IAS above 185 kt TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . HI SPD J If TLU FAULT alarm persists SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT MAX TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD J If IAS below 185 kt SPEED . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT MAX TLU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . LO SPD DISREGARD TLU FAULT ALERT J If TLU LO SPEED message missing IAS . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmin OPS + 10 KT SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15 LAND AT AIRPORT WITH MINIMUM CROSSWIND Note : Maximum demonstrated crosswind (dry runway) with TLU HI SPD mode : 15 kt. COMMENTS - If both ADC are lost, TLU automatic functioning is lost. TLU must be set manually according to IAS read on the STBY ASI. Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P 10 FLIGHT CONTROL 001 FEB 12 AA AIL LOCK LIT ALERT CONDITION VISUAL AURAL Disagree between aileron locking actuators and gust lock control (temporized alert 8 seconds) - MC light flashing amber - AIL LOCK LIT amber message on EWD SC Aileron locking actuators not - MW light flashing red fully retracted and PL on TO - CONFIG red message on EWD position, or - AIL LOCK LIT amber message on Disagree between aileron EWD locking actuators and gust lock control during the TO CONFIG test CRC PROCEDURE AIL LOCK LIT R R J If before take off RETURN TO PARKING REFER TO MMEL ATA 27 ITEM 70--1 GUST LOCK SYSTEM J If after landing TAKE SPECIAL CARE FOR TAXI (WIND EFFECTS) F At parking USE STANDBY SYSTEM FOR AILERON LOCK AT PARKING MAINTENANCE ACTION IS REQUIRED COMMENTS - A malfunction of an aileron locking actuators is pointed out according two levels of protection: . an amber alarm, before take off, with a 8 seconds temporization . a red alarm if either TO CONFIG test is performed or both PL are on TO position Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P 11 FLIGHT CONTROL 001 FEB 12 AA ELEV JAM ALERT There is no indication of an elevator jam other than an inability to operate the control column. PROCEDURE ELEVATOR JAM R CONTROL COLUMNS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . UNCOUPLE FREE COLUMN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IDENTIFY IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT LEAVE AND AVOID ICING CONDITIONS IAS MINI . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN Vmini OPS + 10 KT J If one elevator is stuck to full down position IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 154 KT EXTEND FLAPS IF NECESSARY J If elevator jamming occurs at take off IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 161 KT MAINTAIN FLAPS IF NECESSARY J If other cases IAS MAX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 180 KT PITCH DISCONNECT procedure (2.05.06) . . . . . . . . . . . . . . . . . . . . . . . . APPLY Note: ILS CAT 2 IS PROHIBITED COMMENTS - Both pilots accomplish a firm action on their own column IN THE WAY REQUIRED BY THE JAMMING CONDITION. One of the two channels must yield; force required 52 daN (115 lb). - If uncoupling is unsuccessful, when trajectory under control and above safety altitude, apply opposite efforts on both control columns. - Stick pusher acts on left hand elevator. If left hand control column is jammed, stick pusher must be considered inoperative. - The maximum speed authorized if elevator jamming occurs at take off is linked to the elevator take off position. - If right hand control column is jammed, AutoPilot is no more available. - After uncoupling, only one pilot has control and actuates one elevator only. Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P 12 FLIGHT CONTROL 001 FEB 12 AA AILERON JAM / SPOILER JAM ALERT There is no indication of an aileron jam other than an inability to operate the control wheel laterally. Spoiler jam may be detected when a SPLR light is illuminated on the overhead panel with control wheel at neutral position. PROCEDURE AILERON JAM / SPOILER JAM R R R R BANK ANGLE LIMIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25_ MAX HYD MAIN BLUE AND AUX HYD PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . OFF LAND AT AIRPORT WITH MINIMUM CROSSWIND F For approach STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . . . PROHIBITED HYD MAIN BLUE AND AUX HYD PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . . ON V APP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOT LESS THAN V REF + 10 KT SPD TGT MAN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE IF NECESSARY LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.15 Note : Refer to Part 4 to determine landing distance Note: ILS CAT 2 IS PROHIBITED CAUTION : Do not extend FLAPS in turn. F When in landing configuration HYD MAIN BLUE AND AUX HYD PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . OFF F Immediately after touch down HYD MAIN BLUE AND AUX HYD PUMPS . . . . . . . . . . . . . . . . . . . . . . . . . ON COMMENTS - Bank angle is limited to 25_ due to reduced roll control efficiency. - Blue pump and AUX pump are selected OFF in order to decrease drag from associated extended spoiler. These pumps are selected ON again when necessary then selected OFF. They must be reselected ON immediately after touch down in order to recover nose wheel steering. Mod 5948 2.05.06 PROCEDURES FOLLOWING FAILURE P 13 FLIGHT CONTROL 001 FEB 12 AA RUDDER JAM ALERT There is no indication of a rudder jam other than an inability to operate the rudder pedals. PROCEDURE RUDDER JAM R R R STEEP SLOPE APPROACH (≥4.5_) . . . . . . . . . . . . . . . . . . . . . . . PROHIBITED LAND AT AIRPORT WITH MINIMUM CROSSWIND LANDING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLAPS 30_ USE DIFFERENTIAL POWER TO MINIMIZE SIDESLIP Note: ILS CAT 2 IS PROHIBITED F At touch down NOSE DOWN BEFORE REDUCTION BELOW FI Mod 5948 . 2.05.07 PROCEDURES FOLLOWING FAILURE P1 LANDING GEAR 001 FEB 12 AA LDG GEAR GRAVITY EXTENSION PROCEDURE LDG GEAR GRAVITY EXTENSION R R LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN EMER EXTENSION HANDLE . . . . . . . . . . . . . PULL ABOVE PEDESTAL LEVEL . . . . . . . . . . . . . . . . . . . . AND MAINTAIN UP TO GREEN LIGHTS ILLUMINATED CAUTION : Do not twist handle when operating. TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TA ONLY J If ABNORMAL LDG GEAR indication LANDING WITH ABNORMAL LDG GEAR procedure (2.05.07) . . . . . . . . APPLY Note : LDG Gear cannot be retracted COMMENTS - Although gravity extension is possible up to VLO, it is recommended to perform it at a lower speed compatible with flight conditions. - Pulling the handle mechanically releases the up locks. Pushing the handle back resets the uplocking system. TRAINING - After gravity extension for training purposes, reset the emergency extension handle before normal retraction. If handle is maintained pulled, hydraulic configuration will inhibit gear retraction. Mod 5948 2.05.07 PROCEDURES FOLLOWING FAILURE P2 LANDING GEAR 001 FEB 12 AA LANDING WITH ABNORMAL LDG GEAR PROCEDURE LANDING WITH ABNORMAL LDG GEAR R R R F Preparation CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY ATC / XPDR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY / AS RQD SEAT BELTS / NO DVCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON GPWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CABIN AND COCKPIT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PREPARE LOOSE AND SURVIVAL EQUIPMENT SECURED AND PREPARED BELTS AND SHOULDER HARNESS . . . . . . . . . . . . . . . . . . . . . . . . LOCKED FUEL QTY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IF POSSIBLE, REDUCE J If abnormal nose LDG GEAR CG LOCATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . IF POSSIBLE, AFT J If abnormal main LDG GEAR FUEL UNBALANCE . . . . . . . . . . . . . . . . . . . . . IF POSSIBLE, ESTABLISH Note: Reduced fuel on side with failed LDG GEAR, and do not exceed fuel unbalance limit ( 730 kg ). F Approach LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM DOWN LDG GEAR EMER EXT HANDLE . . . . . . . . . . . . . . . . . . . CONFIRM PULLED MAN IGN . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF CABIN REPORT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CONFIRM OBTAINED F Before landing BLEEDS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BRACE FOR IMPACT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ORDER F At touch down PL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . GI CL 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FTR THEN FUEL SO F After touch down FIRE HANDLES 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . PULL F When aircraft stopped PARKING BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . SET CABIN CREW (PA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . NOTIFY FUEL PUMPS 1 + 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF AGENT 1 ENG 1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH AGENT 1 ENG 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISCH EVACUATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INITIATE F Before leaving aircraft BAT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF To be continued next page...\... Mod 5948 2.05.07 PROCEDURES FOLLOWING FAILURE P3 LANDING GEAR AA 001 APR 11 LANDING WITH ABNORMAL LDG GEAR (CONT’D) COMMENTS - The procedure is intended for use when one or more landing gear fail to extend and/or lockdown following the application of either normal or gravity extension procedure. It is considered preferable to use all available gear locked down rather than carry out a belly landing. Under these circumstances, a hard surface runway landing is to be recommended. Full advantage should be taken from foam spread on the runway. - Notify ATC of the nature of emergency encountered and state intentions. - Notify the cabin crew of the nature of emergency encountered and state intentions. Specify the available time. - GPWS is selected OFF to avoid nuisance warnings. - Burn fuel off down to the minimum possible impact weight. This reduces VAPP and as a consequence the load factor for impact and the energy which must be dissipated. Mod 5948 2.05.07 PROCEDURES FOLLOWING FAILURE P4 LANDING GEAR AA 001 APR 11 LDG GEAR UNSAFE INDICATION ALERT CONDITION VISUAL AURAL Any gear not seen down locked, and Flaps 30, and ZRA < 500 ft - MW light flashing red - LDG GEAR NOT DN red message on EWD - Red light in landing gear lever - Any green ∇ light not illuminated on either panel CRC which may not be silenced by depressing MW PB Any gear not seen down locked, and At least one PL at FI, and ZRA < 500 ft CRC which may be silenced by depressing MW PB Note : The second condition is inhibited during 150 seconds after the retraction of at least one landing gear leg, to cover the case of the one engine go around. Note : In both cases, ZRA condition is inhibited in case of radio altimeter failure. PROCEDURE LDG GEAR UNSAFE INDICATION J If LDG GEAR selected DOWN J If GREEN light OFF on one panel only UNSAFE INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISREGARD J If GREEN light OFF on both panels LDG GEAR GRAVITY EXTENSION procedure (2.05.07 page 1) . . . . APPLY J If LDG GEAR selected UP J If RED light ON on one panel only UNSAFE INDICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DISREGARD J If RED or GREEN light ON on both panels LEAVE AND AVOID ICING CONDITIONS IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 160 KT MAX LDG GEAR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TA ONLY Mod 5948 2.05.07 PROCEDURES FOLLOWING FAILURE P5 LANDING GEAR AA 001 APR 11 LDG GEAR UNSAFE INDICATION (CONT’D) COMMENTS Landing gear selected DOWN - If all green lights are illuminted on one panel, the unsafe indication is false. - If overhead panel (detection system 2) gives false indication, use of emergency audio cancel will be requested to cancel aural warning CRC as soon as flaps will be selected 30. - If one gear remains unlocked, perform turns to increase load factor and perform alternating side slips in an attempt to lock the gear. Landing gear selected UP - If light illuminated on one indicator but indications are normal on the other panel, the unsafe indication is false. - Flight with landing gear extended has a significant effect on fuel consumption and climb gradient : see 3.11 - SPECIAL OPERATIONS. - Landing gear down selection may be delayed if peformance requires. Mod 5948 2.05.07 PROCEDURES FOLLOWING FAILURE P6 LANDING GEAR 001 FEB 12 AA LDG GEAR RETRACTION IMPOSSIBLE PROCEDURE LDG GEAR RETRACTION IMPOSSIBLE R LEAVE AND AVOID ICING CONDITIONS LDG GEAR LEVER . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DOWN IAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . VLE MAX FWS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . RCL TCAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . TA ONLY IDLE GATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MONITOR ANTI- SKID FAULT PROCEDURE ANTI- SKID FAULT R ANTI-- SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF LDG DISTANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.4 Note : Refer to Part 4 to determine LDG DIST F AT touch down REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD NORMAL BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE WITH CARE BRAKE HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD BRK TEMP HOT PROCEDURE BRK TEMP HOT J If BRK TEMP HOT occurs before take off TAKE OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DELAY J If BRK TEMP HOT occurs in flight LEAVE LDG GEAR DOWN FOR 1 MINUTE AFTER TAKE OFF FOR COOLING EXCEPT IN CASE OF EMERGENCY Mod 5948 2.05.07 PROCEDURES FOLLOWING FAILURE P7 001 LANDING GEAR AA APR 11 ANTI- SKID FAULT ALERT CONDITION VISUAL AURAL Anti-- skid channel loss (power loss or loss of transducer or valve continuity) - MC light flashing amber - WHEELS A--SKID amber message on EWD SC PROCEDURE ANTI- SKID FAULT ANTI SKID . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF LDG DIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MULTIPLY BY 1.4 F At touch down REVERSE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD NORMAL BRAKE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . USE WITH CARE BRAKE HANDLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . EMER AS RQD COMMENTS - landing distance is increased due to reduced braking efficiency. BRK TEMP HOT ALERT CONDITION VISUAL AURAL Brake temperature over 150_C - MC light flashing amber - WHEELS BRK HOT amber message on EWD SC PROCEDURE BRK TEMP HOT J If BRK TEMP HOT occurs before take off TAKE OFF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DELAY J If BRK TEMP HOT occurs in flight LEAVE LDG GEAR DOWN FOR 1 MINUTE AFTER TAKE OFF FOR COOLING EXCEPT IN CASE OF EMERGENCY Mod 5948 M . 2.05.08 PROCEDURES FOLLOWING FAILURE P1 001 AIR AA APR 11 BLEED VALVE 1 (2) FAULT ALERT CONDITION VISUAL AURAL Bleed valve position in disagree with command - MC light flashing amber - AIR BLEED 1(2) amber message on EWD + air bleed amber indication on Air Cabin SD page - Associated BLEED and PACK FAULT amber lights on overhead panel SC PROCEDURE BLEED VALVE 1(2) FAULT PACK VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES COMMENTS - Following the detection of a FAULT, the affected BLEED VALVE will close automatically and the associated PACK VALVE will close due to lack of air supply. The associated actions confirm automatic operation and extinguish related alerts, allowing flight to be continued with one pack supplied. - Pack should be confirmed closed first due to PACK FAULT inhibition (as soon as BLEED is selected OFF, PACK FAULT light extinguishes). - A failure of Handling Bleed Valve combined with BLEED OFF operation may lead to engine stall. Engine stall may be prevented through slow power levers movements, especially when advancing the power levers. - An engine stall is indicated by one or a series of mild surges. These will normally stop without crew action, however a slight power reduction, if appropriate, will restore normal operation. Mod 5948 2.05.08 PROCEDURES FOLLOWING FAILURE P2 001 AIR AA APR 11 BLEED 1(2) OVHT ALERT CONDITION VISUAL AURAL Overheat in bleed duct : T duct > 274_C / 525_F - MC light flashing amber - AIR BLEED1(2) OVHT amber message on EWD + amber Bleed indication on Air Cabin SD page - Associated OVHT, BLEED and PACK FAULT amber lights on overhead panel SC PROCEDURE BLEED 1(2) OVHT PACK VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES COMMENTS - Following the detection of an overheat, the affected BLEED VALVE will close automatically and the associated PACK VALVE will close due to lack of air supply. The associated actions confirm automatic operation and extinguish related alerts, allowing flight to be continued with one pack supplied. - Pack should be confirmed closed first due to PACK FAULT inhibition (as soon as BLEED is selected OFF, PACK FAULT light extinguishes). - System may be restored in flight after OVHT alert has extinguished. Mod 5948 2.05.08 PROCEDURES FOLLOWING FAILURE P3 AIR 001 FEB 12 AA BLEED 1(2) LEAK ALERT CONDITION VISUAL AURAL Bleed leak detected as long as bleed air distribution duct work 1(2) side - MC light flashing amber - AIR LEAK 1(2) amber message on EWD - Associated LEAK, BLEED and PACK FAULT amber lights on overhead panel - Amber bleed and pack valve associated with the amber label LEAK, on the Cabin SD page SC PROCEDURE BLEED 1(2) LEAK R PACK VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF BLEED VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES CAUTION : Bleed (Affected side) must not be restored in flight. Note : If a bleed leak occurs on ground during taxi, go back to parking. COMMENTS - Following the detection of a leak, the affected BLEED VALVE will close automatically and the associated PACK VALVE will close due to lack of air supply. The associated actions confirm automatic operation and extinguish related alerts, allowing flight to be continued with one pack supplied. - Pack should be confirmed closed first due to PACK FAULT inhibition (as soon as BLEED is selected OFF, PACK FAULT light extinguishes). - System must not be restored in flight because it may create hazards. Mod 5948 2.05.08 PROCEDURES FOLLOWING FAILURE P4 001 AIR FEB 12 AA X VALVE OPEN ALERT CONDITION VISUAL AURAL X valve open while it - MC light flashing amber should be closed - AIR X VALVE amber message on EWD - X VALVE OPEN amber light on overhead panel - Amber X valve, on the Cabin SD page SC PROCEDURE R X BLEED VALVE OPEN CAUTION : Do not supply both packs from one single bleed. COMMENTS - If both bleeds are available, no special procedure has to be applied. In case of bleed failure, associated pack must be selected OFF. PACK VALVE FAULT ALERT CONDITION Pack valve position disagrees with command or overheat downstream of the compressor (T > 204_C / 393_F) VISUAL AURAL - MC light flashing amber - AIR PACK amber message on EWD - Associated PACK FAULT amber light on overhead panel - Amber Pack valve, on the Cabin SD page SC PROCEDURE PACK VALVE FAULT PACK VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES COMMENTS - If both bleeds are available, no special procedure has to be applied. In case of bleed failure, associated pack must be selected OFF. Mod 5948 2.05.08 PROCEDURES FOLLOWING FAILURE P5 AIR 001 FEB 12 AA BOTH PACK VALVES FAULT ALERT CONDITION Pack valve position disagrees with command or overheat downstream of the compressor (T > 204_C / 393_F) VISUAL AURAL - MC light flashing amber - AIR PACK 1+2 amber message on EWD - Associated PACK FAULT amber light on overhead panel - Both amber Pack valves, on the Cabin SD page. SC PROCEDURE BOTH PACK VALVES FAULT R MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 100 / MEA F When ∆P below 1PSI OVBD VALVE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . FULL OPEN MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX INCREASE COMMENTS - No air is entering in the cabin. Leaks will increase cabin altitude. RECIRC FAN FAULT ALERT CONDITION VISUAL Recirculation fan underspeed or fan electrical motor overheat - MC light flashing amber - AIR RECIRC FAN 1(2) amber message on EWD - associated RECIRC FAN FAULT amber light on overhead panel - Amber recirculation fan, on the Cabin SD page AURAL SC PROCEDURE RECIRC FAN 1(2) FAULT RECIRC FAN affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF Mod 5948 2.05.08 PROCEDURES FOLLOWING FAILURE P6 AIR 001 FEB 12 AA DUCT OVHT ALERT VISUAL AURAL - MC light flashing amber - AIR DUCT OVHT amber message on EWD + amber DUCT OVHT on Air Cabin SD page. - associated TEMP SEL OVHT amber light on overhead panel SC CONDITION Overheat in the duct (T duct > 92_C / 200_F) PROCEDURE DUCT 1(2) OVHT R R TEMP SEL affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN COMPT TEMP SELECTOR affected side . . . . . . . . . . . . . . . . . . . . . . . . . . COLD CAUTION : Monitor DUCT TEMP and make sure it remains positive. J If DUCT OVHT alert persists PACK VALVE affected side . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OFF MAX FL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 200 / MEA AVOID LARGE QUICK POWER CHANGES AT HIGH ALTITUDES COMMENTS - The OVHT alert light will remain as long as overtemperature is detected in the duct. It is not inhibited when in MAN mode. - When alert disappears, controlling COMPT TEMP manually is required. - If alert does not disappear, the temperature control valve is jammed open. Pack valve has to be closed. Mod 5948 2.05.08 PROCEDURES FOLLOWING FAILURE P7 AIR 001 FEB 12 AA EXCESS CAB ALT ALERT CONDITION Cabin altitude above 10000 ft. VISUAL AURAL - MW light flashing red - EXCESS CAB ALT red message on EWD + red reverse video ALT flashing on air cabin SD page. CRC PROCEDURE EXCESS CAB ALT R R CABIN PRESS IND . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK J If rapid decompression EMERGENCY DESCENT procedure (2.04.05 ) . . . . . . . . . . . . . . . . . . . APPLY J If cabin altitude above 10 000 ft MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . DECREASE J If EXCESS CAB ALT persists CREW OXYGEN MASKS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ON CREW COMMUNICATIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . ESTABLISH OXYGEN PAX SUPPLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD OXYGEN PRESSURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CHECK DESCENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . AS RQD / MEA COMMENTS - Check first for pressurization system fault. If system fault, apply appropriate procedure (manual regulation). If no abnormal indication, start descent. Mod 5948 2.05.08 PROCEDURES FOLLOWING FAILURE P8 AIR 001 FEB 12 AA AUTO PRESS FAULT ALERT CONDITION Air auto press amber light on EWD VISUAL AURAL - MC light flashing amber - FAULT amber light on MAN pushbutton - AUTO PRESS displayed amber on the cabin SD page SC PROCEDURE AUTO PRESS FAULT MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . AS RQD TO SET CABIN RATE R R R R F Before descent J If CAB ALT above landing elevation MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . DECREASE 400 FT/MN DN J If CAB ALT below landing elevation MAN RATE KNOB . . . . . . . . . . . . . . . . . . INCREASE 1000 FT/MN UP MAX F When CAB ALT = landing elevation MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK COMMENTS No comment. Mod 5948 2.05.08 PROCEDURES FOLLOWING FAILURE P9 AIR AA LEFT INTENTIONALLY BLANK Mod 5948 001 FEB 12 2.05.08 PROCEDURES FOLLOWING FAILURE P 10 AIR AA LEFT INTENTIONALLY BLANK Mod 5948 001 FEB 12 2.05.08 PROCEDURES FOLLOWING FAILURE P 11 AIR 001 FEB 12 AA EXCESS CAB ∆P ALERT CONDITION Differential pressure exceeds 6.35 PSI VISUAL AURAL - MW light flashing red - EXCESS CAB ∆P red message on EWD - The ∆P value is displayed white on red bacckground on the Cabin SD page. - DIFF PRESS local IND exceeds 6.6 PSI CRC PROCEDURE EXCESS CAB ∆P R R MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 O’CLOCK CAB PRESS MODE SEL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAN MAN RATE KNOB . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MAX INCREASE J If Excess cab ∆P persists DESCENT TO A COMPATIBLE FL / MEA . . . . . . . . . . . . . . . . . . . . . INITIATE Mod 5948 2.05.08 PROCEDURES FOLLOWING FAILURE P 12 AIR 001 FEB 12 AA AVIONICS VENT EXHAUST MODE FAULT ALERT CONDITION VISUAL AURAL Underspeed or overheat of extract fan (T > 90_C / 194_F) - MC light flashing amber - AIR VENT EXH amber message on EWD - Exhaust vent is displayed amber on the Cabin SD page. - EXHAUST MODE FAULT amber light on overhead panel SC PROCEDURE AVIONICS VENT EXHAUST MODE FAULT EXHAUST MODE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . OVBD COMMENTS - EXHAUST MODE to OVBD position controls the OVBD valve to partially open and stops the extract fan; ventilation air is then discharged overboard instead of being directed to the underfloor valve. Ventilation is ensured by ∆P between cabin and outside air. Mod 5948 2.05.08 PROCEDURES FOLLOWING FAILURE P 13 AIR 001 FEB 12 AA OVBD VALVE FAULT ALERT CONDITION OVBD valve position not corresponding with aircraft condition VISUAL AURAL - MC light flashing amber. - AIR OVBD amber

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