HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 HIGHLIGHTS This letter transmits Revision 8 of Hamilton Sundstrand’s Component Maintenance Manual 24-23-34, Date Jun 15/15. The components in this Component Maintenance Manual are used on these aircraft: •Russian Regional Jet We recommend that you put this revision into your manual without delay. After you have put the revised pages in your manual, mark the Record of Revisions sheet with the new revision number and date, and write the date that you insert the revised pages into your manual and your initials on the Record of Revisions sheet in the appropriate spaces. The revised pages of this manual were reprinted. Please replace these pages of your manual with the sections of this revision. General format and layout changes were made in addition to these technical changes. If you have questions about this manual, you can contact Hamilton Sundstrand Technical Publications by email at mailto:tech.pubs@hs.utc.com or fax at (860) 660-9014. The changes made to the manual during this revision are described in the table that follows: Page Description Change Driver Reference All Affected Pages Updated to incorporate general format, administrative and template changes. Non-Technical Change; no substantiation data required. 10040 Added “REPLACED BY ITEM -350A” to item 350. Added item -350A. IH-15326-124424 NPC C15-0105-R Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 Page HI-1 Jun 15/15 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 Page HI-2 Jun 6/14 Hamilton Sundstrand Corporation, a UTC Aerospace Systems Company TITLE PAGE COMPONENT MAINTENANCE MANUAL WITH ILLUSTRATED PARTS LIST GENERATOR CONTROL UNIT PART NUMBER(S) 1709225 1709225A 1709225B © 2008, 2010, 2012-2015 Hamilton Sundstrand Corporation PROPRIETARY THIS DOCUMENT IS THE PROPERTY OF UTC AEROSPACE SYSTEMS. YOU MAY NOT POSSESS, USE, COPY OR DISCLOSE THIS DOCUMENT OR ANY INFORMATION IN IT, FOR ANY PURPOSE, INCLUDING WITHOUT LIMITATION, TO DESIGN, MANUFACTURE OR REPAIR PARTS, OR OBTAIN ANY GOVERNMENT APPROVAL TO DO SO, WITHOUT UTC AEROSPACE SYSTEM’S EXPRESS WRITTEN PERMISSION. NEITHER RECEIPT NOR POSSESSION OF THIS DOCUMENT ALONE, FROM ANY SOURCE, CONSTITUTES SUCH PERMISSION. POSSESSION, USE, COPYING OR DISCLOSURE BY ANYONE WITHOUT UTC AEROSPACE SYSTEM’S EXPRESS WRITTEN PERMISSION IS NOT AUTHORIZED AND MAY RESULT IN CRIMINAL AND/OR CIVIL LIABILITY. Information Subject to Export Control Laws Subject to the EAR, ECCN 9E991 This information is subject to the export control laws of the United States, specifically including the Export Administration Regulations (EAR), 15 C.F.R. Part 730 et. seq. Transfer, retransfer, or disclosure of this data by any means to a non-U.S. person (individual or company), whether in the United States or abroad, without any required export license or other approval from the U.S. Government is prohibited, including without limitation any diversion to a military end user or use in a military end use application. The data in this document were developed only to maintain systems and/or parts manufactured by or for Hamilton Sundstrand or approved by Hamilton Sundstrand. The data may not be applicable to any other systems and/or parts, regardless of their apparent similarity to systems and/or parts manufactured by or for Hamilton Sundstrand or approved by Hamilton Sundstrand. Do not rely in any way on data in this document to maintain or otherwise support systems and/or parts that were not manufactured by or for Hamilton Sundstrand or approved by Hamilton Sundstrand without evidence that the Federal Aviation Administration or other regulatory agency has determined that the data in this document is valid for such use. Hamilton Sundstrand assumes no liability whatsoever, whether contractual, warranty, tort or otherwise, for unauthorized alteration or alterations not performed in accordance with Hamilton Sundstrand approved procedures. Page T-1 CAGE Code: 99167 24-23-34 ORIGINAL ISSUE: REVISION: 8 Dec 15/08 Jun 15/15 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 Page T-2 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 RECORD OF REVISIONS REVISION NUMBER ISSUE DATE DATE INSERTED BY 1 Feb 5/10 Feb 9/10 HS 2 Dec 15/10 Dec 22/10 HS 3 May 14/12 May 15/12 HS 4 Jan 16/13 Jan 18/13 HS 5 Apr 4/13 Apr 4/13 HS 6 Jun 6/14 Jun 6/14 HS 7 Sep 29/14 Oct 1/14 HS 8 Jun 15/15 Jun 19/15 HS REVISION NUMBER ISSUE DATE DATE INSERTED BY Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. RECORD OF REVISIONS 24-23-34 Page RR-1 Jun 15/15 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. RECORD OF REVISIONS 24-23-34 Page RR-2 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 RECORD OF TEMPORARY REVISIONS Table 1 Temporary Revision Number Issue Date Date Inserted/ Inserted By Date Removed/ Removed By Date Incorporated Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. RECORD OF TEMPORARY REVISIONS 24-23-34 Page RTR-1 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. RECORD OF TEMPORARY REVISIONS 24-23-34 Page RTR-2 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 SERVICE BULLETIN LIST Table 2 Service Bulletin/ Revision Number 1709225-24-1 Issue Date Sep 25/13 Date Incorporated or No Effect Sep 29/14 Title Electrical Power - Generator Control Unit - Upgrade GCU from 1709225A to 1709225B Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SERVICE BULLETIN LIST 24-23-34 Page SBL-1 Sep 29/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SERVICE BULLETIN LIST 24-23-34 Page SBL-2 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 LIST OF EFFECTIVE PAGES Subject Page Date TITLE PAGE T-1 T-2 Jun 15/15 Jun 6/14 RECORD OF REVISIONS RR-1 RR-2 Jun 15/15 Jun 6/14 RECORD OF TEMPORARY REVISIONS RTR-1 RTR-2 Jun 6/14 Jun 6/14 SERVICE BULLETIN LIST SBL-1 SBL-2 Sep 29/14 Jun 6/14 LIST OF EFFECTIVE PAGES LEP-1 LEP-2 LEP-3 LEP-4 LEP-5 LEP-6 Jun 15/15 Jun 6/14 Jun 6/14 Jun 15/15 Jun 6/14 Jun 6/14 TABLE OF CONTENTS TOC-1 TOC-2 TOC-3 TOC-4 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 INTRODUCTION INTRO-1 Jun 6/14 INTRO-2 Jun 6/14 INTRO-3 Jun 6/14 INTRO-4 Jun 6/14 INTRO-5 Jun 6/14 INTRO-6 Jun 6/14 INTRO-7 Jun 6/14 INTRO-8 Jun 6/14 INTRO-9 Jun 6/14 INTRO-10Jun 6/14 INTRO-11Jun 6/14 INTRO-12Jun 6/14 INTRO-13Jun 6/14 INTRO-14Jun 6/14 INTRO-15Jun 6/14 INTRO-16Jun 6/14 DESCRIPTION AND OPERATION 1 2 3 4 5 6 Subject Page 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Sep 29/14 Date Sep 29/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. LIST OF EFFECTIVE PAGES 24-23-34 Page LEP-1 Jun 15/15 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subject TESTING AND FAULT ISOLATION Page Date 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94 95 96 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 1001 1002 Jun 6/14 Jun 6/14 Subject Page 1003 1004 1005 1006 1007 1008 1009 1010 1011 1012 1013 1014 1015 1016 1017 1018 1019 1020 1021 1022 1023 1024 1025 1026 1027 1028 1029 1030 1031 1032 1033 1034 1035 1036 1037 1038 1039 1040 1041 1042 1043 1044 1045 1046 1047 1048 1049 1050 Date Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. LIST OF EFFECTIVE PAGES 24-23-34 Page LEP-2 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subject Page 1051 1052 1053 1054 1055 1056 1057 1058 1059 1060 1061 1062 1063 1064 1065 1066 1067 1068 1069 1070 1071 1072 1073 1074 1075 1076 Date Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 SCHEMATICS AND WIRING DIAGRAMS 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 2017 2018 2019 2020 2021 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Subject Page 2022 2023 2024 2025 2026 2027 2028 2029 2030 2031 2032 2033 2034 2035 2036 2037 2038 2039 2040 2041 2042 2043 2044 2045 2046 2047 2048 2049 2050 2051 2052 2053 2054 2055 2056 2057 2058 2059 2060 2061 2062 2063 2064 2065 2066 2067 2068 2069 Date Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. LIST OF EFFECTIVE PAGES 24-23-34 Page LEP-3 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subject Page Date 2070 2071 2072 2073 2074 2075 2076 2077 2078 2079 2080 2081 2082 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 DISASSEMBLY 3001 3002 Jun 6/14 Jun 6/14 CLEANING 4001 4002 Jun 6/14 Jun 6/14 CHECK 5001 5002 Jun 6/14 Jun 6/14 REPAIR 6001 6002 Jun 6/14 Jun 6/14 ASSEMBLY 7001 7002 7003 7004 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 FITS AND CLEARANCES 8001 8002 Jun 6/14 Jun 6/14 SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLE MATERIALS 9001 9002 9003 9004 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 ILLUSTRATED PARTS LIST 10001 10002 10003 10004 10005 10006 10007 10008 10009 10010 10011 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Subject Page 10012 10013 10014 10015 10016 10017 10018 10019 10020 10021 10022 10023 10024 10025 10026 10027 10028 10029 10030 10031 10032 10033 10034 10035 10036 10037 10038 10039 10040 10041 10042 10043 10044 10045 10046 10047 10048 10049 10050 10051 10052 10053 10054 10055 10056 10057 10058 10059 Date Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 15/15 Jun 6/14 Jun 6/14 Jun 15/15 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Sep 29/14 Sep 29/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 15/15 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. LIST OF EFFECTIVE PAGES 24-23-34 Page LEP-4 Jun 15/15 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subject Page 10060 10061 10062 10063 10064 Date Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 Jun 6/14 STORAGE 15001 15002 Jun 6/14 Jun 6/14 Subject Page Date Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. LIST OF EFFECTIVE PAGES 24-23-34 Page LEP-5 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. LIST OF EFFECTIVE PAGES 24-23-34 Page LEP-6 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 TABLE OF CONTENTS PAGE SUBJECT INTRODUCTION TASK 24-23-34-99F-801-A 1. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . INTRO-1 DESCRIPTION AND OPERATION TASK 24-23-34-870-801-A 1. FUNCTIONAL DESCRIPTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 TASK 24-23-34-870-802-A 2. GCU CONTROL AND PROTECTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 TASK 24-23-34-870-803-A 3. PHYSICAL DESCRIPTION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 TASK 24-23-34-870-804-A 4. OPERATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 TASK 24-23-34-870-805-A 5. INPUT/OUTPUT PWB ASSEMBLY A2 DETAILED CIRCUIT DESCRIPTIONS . . . . . . 19 TASK 24-23-34-870-806-A 6. MICROPROCESSOR PWB ASSEMBLY A3 DETAILED CIRCUIT DESCRIPTIONS . . 49 TASK 24-23-34-870-807-A 7. POWER SUPPLY/VOLTAGE REGULATOR PWB ASSEMBLY A4 DETAILED CIRCUIT DESCRIPTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71 TASK 24-23-34-870-808-A 8. ARINC INTERCONNECT PWB ASSEMBLY A5 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90 TASK 24-23-34-870-809-A 9. LEADING PARTICULARS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95 TESTING AND FAULT ISOLATION TASK 24-23-34-700-801-A 1. GENERAL INFORMATION FOR TESTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1001 TASK 24-23-34-700-802-A 2. ENVIRONMENTAL CONDITIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1003 TASK 24-23-34-700-803-A 3. TEST REQUIREMENTS SPECIFICATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1003 TASK 24-23-34-700-804-A 4. TEST PROGRAM SOFTWARE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1004 TASK 24-23-34-700-805-A 5. TEST SOFTWARE CONFIGURATION INFORMATION . . . . . . . . . . . . . . . . . . . . . . 1004 TASK 24-23-34-700-806-A 6. PRETESTING CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1005 TASK 24-23-34-700-807-A 7. CYCLICAL REDUNDANCY CHECK NUMBERS . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1005 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 TABLE OF CONTENTS Page TOC-1 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 SUBJECT PAGE TASK 24-23-34-700-808-A 8. TESTING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1005 TASK 24-23-34-810-801-A 9. FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1011 TASK 24-23-34-700-809-A 10. A3 PWB REPLACEMENT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1012 TASK 24-23-34-700-810-A 11. A5 PWB ASSEMBLY DIELECTRIC AND BONDING TESTS. . . . . . . . . . . . . . . . . . . 1012 TASK 24-23-34-810-802-A 12. FAULT ISOLATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1014 TASK 24-23-34-810-803-A 13. USING FAULT ISOLATION CHARTS AND DATA . . . . . . . . . . . . . . . . . . . . . . . . . . . 1015 TASK 24-23-34-810-804-A 14. TEST STRUCTURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1017 SCHEMATICS AND WIRING DIAGRAMS TASK 24-23-34-995-801-A 1. GENERAL. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001 TASK 24-23-34-995-802-A 2. USE OF SCHEMATICS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2001 DISASSEMBLY TASK 24-23-34-000-801-A 1. GENERAL INFORMATION FOR DISASSEMBLY . . . . . . . . . . . . . . . . . . . . . . . . . . . 3001 TASK 24-23-34-000-802-A 2. DISASSEMBLY OF THE GCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3001 CLEANING TASK 24-23-34-100-801-A 1. GENERAL INFORMATION FOR CLEANING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4001 CHECK TASK 24-23-34-210-801-A 1. GENERAL INFORMATION FOR CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5001 TASK 24-23-34-210-802-A 2. CHECK . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5001 REPAIR TASK 24-23-34-300-801-A 1. GENERAL INFORMATION FOR REPAIR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6001 ASSEMBLY TASK 24-23-34-400-801-A 1. GENERAL INFORMATION FOR ASSEMBLY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7001 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 TABLE OF CONTENTS Page TOC-2 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 SUBJECT PAGE TASK 24-23-34-400-802-A 2. ASSEMBLY OF THE GCU . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7002 FITS AND CLEARANCES TASK 24-23-34-205-801-A 1. GENERAL INFORMATION FOR FITS AND CLEARANCES . . . . . . . . . . . . . . . . . . . 8001 TASK 24-23-34-205-802-A 2. TORQUE REQUIREMENTS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8001 SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLE MATERIALS TASK 24-23-34-940-801-A 1. SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLE MATERIALS . . 9001 ILLUSTRATED PARTS LIST TASK 24-23-34-950-801-A 1. ILLUSTRATED PARTS LIST INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10001 2. VENDOR LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10006 EQUIPMENT DESIGNATOR INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10007 NUMERICAL INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10019 DETAILED PARTS LIST . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10023 STORAGE TASK 24-23-34-550-801-A 1. GENERAL INFORMATON FOR STORAGE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15001 TASK 24-23-34-550-802-A 2. PREPARATION FOR STORAGE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15002 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 TABLE OF CONTENTS Page TOC-3 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TABLE OF CONTENTS 24-23-34 Page TOC-4 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 INTRODUCTION 00 TASK 24-23-34-99F-801-A 1. GENERAL INFORMATION Subtask 24-23-34-99F-001-A00 A. Scope (1) This Component Maintenance Manual (CMM) gives the maintenance instructions for the Generator Control Unit (GCU), base Part Number (PN) 1709225 Series. The maintenance instructions include tests which show if the unit is serviceable. There are also procedures to repair or replace parts which are not serviceable. Subtask 24-23-34-99F-002-A00 B. Unit Identification (1) The GCU has an identification plate which shows the: • Part Name, which identifies the GCU with words • Part No., which identifies the GCU with a number • Serial No., which identifies each unit (2) A separate modification plate is located near the identification plate. The modification plate contains a “mod dot” matrix and as a SB is incorporated the SB dash (sequence) number is marked. Refer to the applicable Standard Practices Manual for more details. Subtask 24-23-34-99F-003-A00 C. Manual Description And Use (1) This Component Maintenance Manual was written by the Technical Publications Department of Hamilton Sundstrand Corporation. The address is shown below: Hamilton Sundstrand Corporation Technical Publications Department 4747 Harrison Ave. Rockford, IL 61108-7929 This manual includes: • Title Page • Record of Revisions • Record of Temporary Revisions • Service Bulletin List • List of Effective Pages • Table of Contents • Introduction • Description and Operation • Maintenance Procedures • Illustrated Parts List • Storage (2) Refer to the Table of Contents to find the applicable section. (3) An explanation of the use of the Illustrated Parts List (IPL) is supplied in the introduction to that section. (4) The manual will be revised as necessary to reflect current information. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-1 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subtask 24-23-34-99F-004-A00 D. Procedure Verification Table Intro-1 Table Intro-1 Procedure Verification Section Verification Method Date (by Demonstration) Testing and Fault Isolation Performance - Disassembly Performance - Assembly Performance - Engineering Technical Review Completed Nov 15/10. Subtask 24-23-34-99F-005-A00 E. Maintenance Task and Subtask Usage (1) This Component Maintenance Manual uses Maintenance Task Oriented Support System (MTOSS) to organize the maintenance information. It is organized by maintenance tasks and subtasks, graphics and tables. Each task consists of one or more subtasks. Each subtask contains procedural steps and can contain one or more graphics or tables. (2) Each anchor element begins with a title that describes: • “TASK”, “Subtask” or “Action/Result List” • ATA Chapter-Section-Subject Number • Function Code - this describes the maintenance actions. Brief descriptions of each of the function codes that can be used in this manual are given below. The “Term” column shows the Function Code. The “Definition” column describes the function. • Sequence Number - The sequence number is used to uniquely identify the task, subtask, graphic or table. The combination of the function code and sequence number is unique within this manual. Sequence numbers 801 thru 999 are reserved for task identification. Subtasks use 001 thru 800. Tables and graphics can use 001 thru 999 since they have function codes that identify as tables and graphics. • Configuration Letter/Variation Number - The configuration letter and variation number are shown together at the end of the MTOSS code (e.g. “A00” in “TASK 2423-34-99F-801-A00”). It will normally default to “A00”. The “A” indicates that this is the first configuration that is described. If there were another configuration (that had different procedural requirements), it would have “B00” as a configuration letter/ variation number. The “00” indicates that this is the first variation of the procedure. This number is there to accommodate different variations of the procedure against the same configuration. Table Intro-2 Function Codes Term Definition 000 Removal and Disassembly 010 Removal 020 Remove Modular Sections Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-2 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table Intro-2 Function Codes (Continued) Term Definition 030 Disassemble Modular Sections 040 Disassemble Subassembly 050 Remove Accessory/Power Plant Component 060 Disassemble Accessory 070 Disassemble Accessory Subassembly 080 Remove Test Equipment 090 Disassemble Support Equipment 100 Cleaning 110 Chemical 120 Abrasive 130 Ultrasonic 140 Mechanical 160 Miscellaneous 170 Foam/Water Wash 180 Testing of Solutions 200 Inspection 205 Fits and Clearances 210 Check 220 Visual/Dimensional 230 Penetrant 240 Magnetic 250 Eddy Current 260 X-Ray 270 Ultrasonic 280 Special 300 Repair 310 Welding and Brazing 320 Machining 330 Stripping and Plating 340 Plasma and Flame Spraying 350 Miscellaneous Repairs Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-3 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table Intro-2 Function Codes (Continued) Term Definition 360 Bonding and Molding/Sealing 370 Heat Treating 380 Surface Treating 390 Machine Riveting and Flaring 400 Installation and Assembly 410 Install 420 Install Modular Sections 430 Assemble Modular Sections 440 Assemble Subassembly 450 Install Items Removed for Access 460 Assemble Accessory 470 Assemble Accessory Subassembly 480 Install Test Equipment 490 Assemble Support Equipment 500 Material Handling 510 Shipping 520 Receiving 530 Packing 540 Unpacking 550 Storage 560 Marshalling/Positioning 570 Engine Ferry/Pod Maintenance 600 Servicing/Preserving/Lubricating 610 Servicing 620 Preserving 630 Depreserving 640 Lubricating 700 Testing/Checking 710 Oil Flow 720 Air Flow 730 Fuel Flow Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-4 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table Intro-2 Function Codes (Continued) Term Definition 740 Water Flow 750 Electrical/Return to Service 760 Engine 770 Accessory/BITE 780 Pressure Check 790 Leak Check 800-900 Miscellaneous 810 Fault Isolation 820 Adjusting/Aligning/Calibrating 830 Rigging 840 SB Incorporation 850 PN Change/Reidentification 870 Description and Operation 880 Approved Vendor Process 890 Airline Maintenance Program 910 Special Equipment Maintenance 920 Standard Equipment Maintenance 930 Tool Fabrication 940 Special Tool and Consumables Listing 94A Consumables 94B Special Tools/Non Standard Tools 94C Fixtures/Test Equipment 94D Standard Tools 950 IPL Detailed Parts List 960 IPL Equipment Designator Index 970 IPL Numerical Index 980 IPL Vendor List 990 Illustrations, Tables, Front Matter, etc. 995 Schematics and Wiring Diagrams 99A Tables 99B Illustrations Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-5 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table Intro-2 Function Codes (Continued) Term Definition 99C Task Level MTOSS 99D Access 99E References 99F General/Introduction Subtask 24-23-34-99E-001-A00 F. Standard Practices Manuals (1) This manual references the Standard Practices Manual (SPM) 20-10-01 which has common maintenance practices that may be applicable for this type of equipment. You can get a copy of the SPM at our website (http://www.hsvas.com). Subtask 24-23-34-99F-006-A00 G. Reporting Problems (1) We welcome suggestions on how we can improve our documentation. Your comments and suggestions will be analyzed by our Technical Publications, Technical Service and Engineering departments, as applicable. Please contact your Hamilton Sundstrand Field Service Representative or Technical Publications personnel by email at mailto:tech.pubs@hs.utc.com or fax (860) 660-9014 to notify us of problems that you find in this manual. They will enter your issues into a system that will assure that they are addressed by the appropriate personnel within Hamilton Sundstrand. This process will determine how your comments or suggestions will be added to future manual revisions. Subtask 24-23-34-99F-007-A00 H. Training (1) We offer Air Transport Association (ATA) Specification Number 104 level training on our products. You can find information about our training policies, eligibility, schedules, etc. at our website (http://hsvas.utc.com). Subtask 24-23-34-99F-008-A00 I. Safety Advisory (1) Scope (a) This publication describes processes that may require the use of chemicals, solvents, paints, or other materials that can affect a person’s health or safety. It may also cover high energy procedures that can affect a person’s health or safety. Warnings are placed just ahead of these procedures to bring attention to the existence of a procedure or material that is dangerous. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-6 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (2) Significance of Material Safety Data Sheets (MSDS) and How to Obtain MSDS WARNING: BEFORE USING ANY OF THE MATERIALS SPECIFIED IN HAMILTON SUNDSTRAND MAINTENANCE PUBLICATIONS, BE AWARE OF ALL HANDLING, STORAGE, AND DISPOSAL PRECAUTIONS RECOMMENDED BY THE MANUFACTURER OR SUPPLIER. FAILURE TO COMPLY WITH MANUFACTURER'S OR SUPPLIER'S RECOMMENDATIONS MAY RESULT IN PERSONAL INJURY OR DISEASE. THE USER OF THIS PUBLICATION SHOULD OBTAIN THE MATERIAL SAFETY DATA SHEETS (OCCUPATIONAL SAFETY AND HEALTH ACT (OSHA) FORM 20 OR EQUIVALENT) FROM THE MANUFACTURERS OR SUPPLIERS OF MATERIALS TO BE USED. THE USER MUST BECOME COMPLETELY FAMILIAR WITH THE MANUFACTURER OR SUPPLIER INFORMATION AND ADHERE TO THE PROCEDURES, RECOMMENDATIONS, WARNINGS, AND CAUTIONS OF THE MANUFACTURER OR SUPPLIER FOR THE SAFE USE, HANDLING, STORAGE, AND DISPOSAL OF THESE MATERIALS. (a) Refer to the materials list at the beginning of each section of this manual for materials used in the maintenance of the covered equipment. (b) If you do not have a copy of the manufacturer’s MSDS for the materials covered in the materials list, contact the manufacturer and request that a MSDS be supplied before you use the material. (3) Purpose (a) The warnings bring your attention to the existence of a procedure that can affect a person’s health or safety. (b) Short warnings are provided in this maintenance publication to alert operating and maintenance personnel to potential hazards that could result in personal injury or health hazards. The warnings do not replace the manufacturer's recommendations. When there is a reference to the Warnings Registry SPM 2000-04, that publication will provide more information about the dangers of the material. The information contained in the Warnings Registry is a summary of the manufacturer’s MSDS. The long warnings provide three principle parts of safety: (1) a listing of the known dangers, (2) what is needed to do to protect you from the dangers, and (3) what to do if the dangers occur. (c) The detailed warnings in Warnings Registry SPM 20-00-04 are a summary of the manufacturer’s MSDS and are not intended to replace the material on the sheet, but are intended to supplement them. (d) Cautions are provided in the maintenance publication or service bulletin to alert operating and maintenance personnel to conditions that could result in equipment damage. (4) Definitions Applying to Warnings (a) Flammable: a material that can catch fire easily and can be explosive. These materials are labeled according to the flash point of the material. (b) Flash Point: the lowest temperature at which a flammable liquid gives off fumes that can burn. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-7 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (c) Ignition Source: includes flames, sparks, or heat. 1 Flames: materials that are burning such as lit matches, propane torches, or pilot lights. 2 Sparks: materials such as lighted cigarettes, electrical motors, or static electricity. 3 Heat: any source of energy that will raise the temperature of a flammable material to its flash point and could include hot parts, heated tools, or direct sunlight. (d) Corrosive: acidic or alkaline material that will remove human tissue or create chemical reactions with other materials. (e) Toxic: material that is poisonous. (f) Reactive: material that will make fumes, burn, or can be explosive when mixed with certain other materials. (g) Shock (Electrical): the result of any source of electricity more than 50 volts that causes current to flow through a person and can result in dangerous burns to human tissues or death. (h) Exposure: contact with the material or physical process without protection. Contact may be by the eyes, breathing, touch, skin absorption, or swallowing. (i) Irritation: any sense of pain, soreness, rash, or general discomfort. (5) Reporting Materials or Processes Not Covered (a) You may contact Technical Publications personnel by email at mailto:tech.pubs@hs.utc.com or fax at (860) 660-9014 if you find a material in a Hamilton Sundstrand maintenance document that is known to be covered by a material safety data sheet (MSDS), but is not covered by a warning in the procedure. Subtask 24-23-34-99F-009-A00 J. Abbreviations and Acronyms (1) Abbreviations and Acronyms with their definitions are shown in the Definition List below. Table Intro-3 Abbreviations and Acronyms Term Definition A Amperes ac, AC alternating current A/D analog-to-digital Adc Amperes direct current ADC analog-to-digital converter Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-8 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table Intro-3 Abbreviations and Acronyms (Continued) Term Definition AGC auxiliary generator contactor AGCCCF auxiliary generator contactor control circuit failure AGCF auxiliary generator contactor failure AGCS auxiliary generator control switch AGEN auxiliary generator ALE address latch enable APU auxiliary power unit ARINC Aeronautical Radio, Inc. ASIC application specific integrated circuit ASSY assembly ASTM American Society for Testing and Materials ATA Air Transport Association BC bus controller BG bus grant BHE bus high enable BIT built-in test BITE built-in test equipment BMS boot memory select bps bytes per second BPT break power transfer BR bus request BTC bus tie contactor C Celsius CFDS centralized fault display system CL clear cm centimeter CMC central maintenance computer CMD command CMM Component Maintenance Manual CMOS complimentary metal oxide semiconductor CMS central maintenance system Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-9 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table Intro-3 Abbreviations and Acronyms (Continued) Term Definition CPU central processing unit CS chip select CSD constant speed drive CT current transformer CTA current transformer assembly DAC digital-to-analog converter dc, DC direct current DMA direct memory access DOC delta overcurrent DP differential [current] protection DPCT differential protection current transformer DPI differential pressure indicator DSP digital signal processor DT/R data transmit/receive EAR Export Administration Regulations ECB electronic control box ECMU electrical contactor management unit ECU engine control unit EFF effectivity EMF electromotive force EMI electromagnetic interference EOC end of conversion EP external power EPA external power [contactor] A EPB external power [contactor] B EPC external power contactor EPCF external power contactor failure EPGS electrical power generating system EPI external power interlock EPLD electrically programmable logic device EPROM electrical programmable read only memory Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-10 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table Intro-3 Abbreviations and Acronyms (Continued) Term Definition EPS external power switch EPSEQ external [power] phase sequence ESDS electrostatic discharge sensitive F Fahrenheit FADEC full authority digital electronic control FET field effect transistor FIG. figure FMCS fault memory chip select FTOR fault timer OR [logic] GAPCU Ground and Auxiliary Power Control Unit GC generator contractor GCR generator control relay GCS generator control switch GCU Generator Control Unit GEN generator GLSH galley shed HIRF high intensity radiated field(s) Hz hertz IDG integrated drive generator I/O input/output in. inch IPL illustrated parts list IPT inadvertent paralleling ISO isolated ISOPS isolated power supply ITA interface test adapter JFET junction field effect transistor kbps kilo bytes per second kg kilogram kHz kilohertz kVA kilovolt-amperes Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-11 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table Intro-3 Abbreviations and Acronyms (Continued) Term Definition L-L line-to-line L-N line-to-neutral lb. pound LCS level chip select LED light emitting diode LFM locked flight memory LOP low oil pressure LRU line replaceable unit LSB least significant bit LSS line/switch sense LSW least significant word mA milliampere mAdc milliamperes direct current max maximum MCU modular concept unit MHz megahertz min minimum MOSFET metal oxide semiconductor field effect transistor ms millisecond MSB most significant bit MSD moisture sensitive device MSDS Material Safety Data Sheets MSW most significant word MTOSS Maintenance Task Oriented Support System MUX multiplexer N/A not applicable NBPT no break power transfer NEG, N negative NHA next higher assembly NMI non-maskable interrupt No. number Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-12 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table Intro-3 Abbreviations and Acronyms (Continued) Term Definition NPN negative positive negative NRZ non-return to zero NVM non-volatile memory N•m Newton meters OC overcurrent OE output enable OF overfrequency OL overload OPC open cable OV overvoltage oz-in. ounce-inch(es) PMG permanent magnet generator PN Part Number PNP positive negative positive POK power okay POR point of regulation POS positive PR power ready PRR power ready relay PS power supply PUR power-up reset PWB printed wiring board PWM pulse-width modulation QAD quick attach-detach RAM random access memory RC resistive-capacitance REV revision RF radio frequency, reference RMS root-mean-square ROLS remote oil level sense rpm revolutions per minute Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-13 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table Intro-3 Abbreviations and Acronyms (Continued) Term Definition RT remote terminal s second SB service bulletin SDAC system data acquisition concentrator SDI source/destination identifier SIC system isolation contactor SOPMG shorted/open permanent magnet generator SPM Standard Practices Manual SPMG shorted permanent magnet generator SRAM static random access memory SRD shorted rotating diode SSM signal status matrix SSR solid-state relay STIM stimulus SV servo valve SYNC synchronize, synchronization TCK test clock TDI test data input TDO test data output TMS test mode select TRST test reset TRU transformer rectifier unit TTL transistor-to-transistor logic TVS transient voltage suppressor UART universal asynchronous receiver/transmitter UF underfrequency UP unbalanced phase UPC unbalanced phase current US underspeed UV undervoltage V volt Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-14 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table Intro-3 Abbreviations and Acronyms (Continued) Term Definition Vac volts-alternating current Vavg volts-average VCVS voltage controlled voltage source Vdc volts-direct current VR voltage regulator VREF reference voltage Vrms volts-root-mean-square W watt WRN warning www World Wide Web ° degree differential = equals micro - minus, negative # number % percent + plus, positive ± plus or minus ohms phase Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-15 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. INTRODUCTION 24-23-34 Page INTRO-16 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 DESCRIPTION AND OPERATION 00 TASK 24-23-34-870-801-A 1. FUNCTIONAL DESCRIPTION Subtask 24-23-34-870-001-A00 A. Overall Functional Description (1) The GCU monitors and controls the integrated drive generators (IDG) when they are powering the aircraft load buses. The GCU controls operation of the generator line contactor (GLC) and bus tie contactor (BTC). The GCU contains built-in test equipment (BITE) for fault isolation of its main associated generating channel. Main generating channel faults sensed by the GCU are communicated to the Ground and Auxiliary Power Control Unit (GAPCU). The GAPCU gathers all fault information for the electrical power generating system (EPGS), translates fault codes into English messages, and transmits these messages to the Centralized Fault Display System (CFDS). The GCU is shown in Figure 1. Figure 1 HE-242334-101776 Figure 1 GCU Subtask 24-23-34-870-002-A00 B. System Level Functional Description (1) The EPGS has two main generating channels that are powered by engine-driven IDGs. The GCU monitors its IDG channel and ensures its IDG is providing correct electrical power to the main electrical buses. Refer to Figure 2 for the RRJ EPGS single line diagram. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 1 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2 LEFT IDG (GENERATOR 1) APU GENERATOR EXTERNAL POWER RIGHT IDG (GENERATOR 2) RAT AGC1 (K31) EPC1 (K41) LEFT GCU 75A LGC (K1) RIGHT GCU EPC2 (K42) AGC2 (K32) RGC (K2) 75A LEFT 115 VAC BUS RIGHT 115 VAC BUS GAPCU GSC1 (K43) GSC2 (K44) RGLC1 (K5) RGLC2 (K6) RIGHT ESS BUS SERVICE BUS LEFT ESS BUS 25A 25A 25A RAT GCU 115/200 VAC CONTROL OUTPUT CONTROL INPUT COIL CURRENT TRANSFORMER HE-242334-101889 Figure 2 EPGS Single Line Diagram Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 2 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (2) Each IDG is monitored and controlled by a GCU. The GCU provides closed-loop regulation of the generator output voltage and frequency. The GCU also monitors the quality of power from the generator. Switches on the flight deck are used to control the GCU. If the generator control switch (GCS) is on (or the switch is set to off and then to on) and generator power quality is acceptable, the generator line contactor (GLC) closes and allows the generator to power its associated bus. (3) A bus tie contactor (BTC) enables another ac electrical source (auxiliary generator, external power, or another IDG) to assume the loads of the shutdown IDG. The GCU prevents closure of the BTC if a fault is detected on a load bus. Faults are detected by the current transformers (CT) located internal and external to the generator. (4) The auxiliary generator provides backup power in case of main generator failure and supplies power while the aircraft is on the ground. An auxiliary power unit (APU) drives the auxiliary generator. (5) The auxiliary generator is connected to the tie bus by the auxiliary generator line contactor (AGLC). The AGLC serves the same function for the APU channel as the GLC does for the IDG channel. Most control and protective functions are similar between the IDG and APU channels. (6) The auxiliary generator is monitored and controlled by the GAPCU. The GAPCU provides closed-loop regulation of the auxiliary generator output voltage. The GAPCU also monitors the quality of power from the generator. An auxiliary generator control switch (AGCS) located on the flight deck is used to control the GAPCU. If the AGCS is on (or it is set to off and then to on) and generator power quality is acceptable, the AGLC closes to provide power to the tie bus. (7) When the aircraft is on the ground, provision is made for supplying electrical power from an external source. (8) Ground power is plugged into the external power (EP) connector on the outside of the aircraft. The GAPCU does not have direct control over external (ground) power voltage, frequency, and phase sequence. The GAPCU monitors external power quality and performs EP protective functions. The GAPCU controls closure and opening of the external power contactor (EPC). If ground power quality is acceptable, the EPC closes to connect ground power to the aircraft buses. If ground power quality is unacceptable, the GAPCU prevents EPC closure or, if the EPC is closed, opens the EPC to disconnect power from the aircraft buses. (9) Each GCU and the GAPCU supply the flight crew with electrical power system information for all ac power channels: primary, auxiliary, and external. The information (frequency, voltage, percent load, and IDG oil output temperature) is transmitted over an ARINC 429 data bus to the system data acquisition concentrator (SDAC). The GAPCU communicates over an ARINC 429 data bus with the centralized fault display interface unit (CFDIU). (a) Normal Operation (Refer to Figure 2) 1 The main generating channels operate independently of each other. The IDG 1 Channel powers the loads on main AC Bus 1 and IDG 2 Channel powers the loads on main AC Bus 2. The APU generator does not have primary priority for any loads, but may be connected to assume the electrical loads of either or both main generators. External power is applied to the tie bus and may be connected to assume the electrical loads of either or both main generators. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 3 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 Control of the electrical buses is accomplished by aircraft contactor control logic (that is, break-before-make or break-power transfer). The decision to close the bus tie contactor (s) is made by the aircraft contactor logic. The GCU protective functions prevent BTC operation under certain conditions. For example, a GCU would prevent BTC closure if another generator would be feeding a fault on its associated channel. 3 Normal automatic system operation is established when all control switches on the electric power control panel are in the latched (in) or ON (normal position). Initially, both engines and the APU are shut down and backup 28 Vdc is supplied to each GCU and to the GAPCU. a Connection of External Power 1) External power present at the ac external power receptacle is sampled by the GAPCU. If external voltage and frequency are within acceptable limits, phase sequence is correct and pin E/F interlock is complete, the external power “AVAIL” light comes on at the external power receptacle and in the external power switch (EPS) on the flight deck. A momentary push of the EPS closes the EPC and connects external power to the tie bus. The external power “ON” light in the EPS comes on and the “AVAIL” light goes off. Both AC Bus 1 and AC Bus 2 are powered through the closed EPC and BTCs. The AC GND/FLT buses are also automatically powered from main AC BUS 2. b Startup of APU 1) The APU generator is the next power source available in a startup sequence. After the APU generator startup, the GAPCU closes its internal APU generator power ready relay (PRR) when the APU generator voltage and frequency are within acceptable limits, phase sequence is correct, and the APU is at 95 percent of its operating speed. APU generator power can be applied to AC Bus 1 and AC Bus 2 by a momentary push of the EPS to OFF position. The EPC opens and the AGLC closes. c Main Engine Startup 1) When IDG input speed exceeds the underspeed trip point, voltage and frequency are acceptable, and phase sequence is correct, a power ready (PR) signal is generated which causes the associated BTC to open and the GLC to close. The second ac bus remains powered by the APU generator. Start up of the second engine results in a similar transfer of the second ac bus to its associated IDG. Normal flight configuration is established when both IDGs are powering their respective buses. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 4 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 d Main Engine Startup Without APU 1) If the APU generator is not available and both ac buses are initially supplied by external power, the first IDG channel that comes up to operating speed automatically assumes the loads on its associated ac bus. The second IDG channel remains powered by the external power source through the closed BTC and EPC. Startup of the second engine results in automatic transfer of the second ac bus to the associated IDG. The EPC remains closed after closure of the second GLC. External power remains available on the tie bus until external power is removed. e Engine Shutdown 1) Engine shutdown in ground mode operation opens the GLC closes the BTC. The APU generator, if available, assumes the load of the channel that shuts down. In the event the APU generator is not available, the second IDG channel assumes the other IDG channel's loads. External power, if available, can power both left and right buses if the EPC is closed. (b) Manual Operation 1 Normal automatic system operation may be bypassed by use of the appropriate switch on the flight deck electric power control panel. The same switches also reset the system following a protective trip. Control switch functions are summarized as follows: a Generator Control Switch (GCS) 1) The GCS is a switch with latched ON and OFF positions to enable automatic or manual channel operation. NOTE: The auxiliary generator control switch (AGCS) operates in the same manner as the IDG channel GCS. 2) In the ON position the generator is excited and the GLC is allowed to close. NOTE: The auxiliary generator line contactor (AGLC) operates in the same manner as the IDG channel GLC. 3) In the OFF - RESET position the generator is de-excited. The ON to OFF transition of the switch resets protective trips within the control unit. b IDG Disconnect Switch 1) The IDG disconnect switch is used by the flight crew when the GCU detects an IDG fault such as oil output overtemperature (oil output temperature exceeds 185 °C [365 degrees °F]) or low oil pressure (less than 140 pounds per square inch [965 kilo pascals]). An IDG fault can cause serious damage to the IDG. When pushed, the IDG disconnect switch trips the GCR in the GCU, and applies power to the IDG disconnect solenoid. The solenoid energizes to mechanically isolate the IDG from the engine gearbox. The IDG may be reconnected only after the aircraft has landed and the engine has been shut down. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 5 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 c Fire Switch 1) When pushed, the fire switch trips the GCR in the GCU to deexcite the generator. d External Power Switch (EPS) 1) The EPS is a momentary action push button switch that “flip-flop” logic within the GAPCU to open or close the EPC while on the ground. e Additional Signals 1) In addition to the GCS and NBPT signals supplied by the GAPCU, the GAPCU also issues a GALLEY SHED signal to the ECMU in the event of an overload condition on the auxiliary generator or external power channels. The GCU also issues a GALLEY SHED signal if the event of an IDG overload condition. (c) Main Generators 1 Two 40 kilovolt-ampere (kVA) IDGs are used by the RRJ as main ac power sources. An IDG consists of a mechanical and hydraulic constant speed drive (CSD) connected to an oil-cooled generator in a single housing. 2 The aircraft engine drives the IDG. Each IDG is attached to the engine accessory gearbox mounting pad by means of a quick attach and detach (QAD) adapter kit. 3 The CSD portion of the IDG takes the variable input speed from the engine gearbox and converts it to a constant output speed of 24,000 revolutions per minute (rpm) that drives the generator. A frequency regulator in the GCU controls the IDG speed (generator frequency). 4 The generator is a two-pole machine that converts the mechanical power from the CSD into three-phase electrical power at a constant frequency of 400 Hz. Generator output voltage is a nominal 115 Vac line-to-neutral (L-N) or 200 Vac line-to-line (L-L). Continuous output capacity at the input to the GLC is 40 kVA. 5 The generator actually consists of three distinct generators: the exciter generator, the permanent magnet generator (PMG), and the main generator. This configuration results in a generator that provides its own excitation and does not require any brushes or slip rings. The exciter and main generator are mounted on the common generator shaft and the PMG is mounted on the output ring gear of the CSD section of the IDG. The ring gear speed is directly proportional to the speed of the generator shaft (in an approximate 1-to-2 ratio). 6 The PMG uses a sixteen-pole permanent magnet rotor. The three phase, 110 Vac (L-L) PMG output is rectified in the GCU and powers the exciter generator field (stator). A voltage regulator within the GCU controls the exciter field current. This regulator provides closed-loop control of the generator output voltage based on the point-of-regulation (POR) line voltage. The PMG output also powers the GCU electronics and associated relays and contactors through the GCU power supplies. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 6 Sep 29/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 7 The three-phase output from the exciter rotor is rectified by diodes mounted on the generator rotor. The resulting dc power supplies the rotating field of the main generator. The main generator output is taken from the threephase stator winding. 8 Each phase of the main generator stator winding runs through a current transformer (built into the generator) that allows the generator current to be monitored by the GCU. Other components within the IDG include an oil pressure sensing switch, temperature sensors (bulbs) for measuring inlet and outlet oil temperature. A disconnect solenoid and a thermal disconnect are used to disconnect the IDG from the aircraft engine. (d) Auxiliary Generators 1 Like the main generators, the auxiliary generator is rated at 115/200 Vac, 40 kVA. The auxiliary generator input speed is determined by the APU. The APU generator speed is constant and no CSD is required. The assembled auxiliary generator and APU are mounted in the tail section of the aircraft. 2 The auxiliary generator is a two-pole machine that is driven at 24,000 rpm to give a 400 Hz output frequency. The auxiliary generator PMG rotor has eight poles. 3 The auxiliary generator consists of three generators mounted on the same shaft: the PMG, the exciter generator, and the main generator. The generator provides its own excitation and does not require any brushes or slip rings. 4 The PMG uses an eight-pole permanent magnet rotor. The three-phase, 110 Vac (L-L) PMG output is rectified in the GAPCU and powers the exciter generator field (stator). A voltage regulator in the GAPCU controls the exciter field current. The regulator provides closed-loop control of the generator output voltage based on the point-of-regulation (POR) line voltage. The PMG output also powers the GAPCU electronics and associated relays and contactors through the GAPCU power supplies. 5 The three phase-output from the exciter rotor is rectified by diodes mounted on the rotor. The resulting dc power supplies the rotating field of the main generator. The main generator output is taken from the three-phase stator winding. 6 Each phase of the main generator stator winding runs through a current transformer, built into the generator, to allow the generator current to be monitored by the GAPCU. (e) Current Transformer Assemblies 1 A current transformer assembly (CTA) consists of three individual transformers mounted in a single housing. The generator power feeders are run through the assembly but no electrical connection is made. A current is induced in each transformer proportional to the current flowing in the feeder. The CTA has a 1-to-1000 ratio; that is, a 1.000 ampere current through each feeder induces a 0.001 ampere current in each of the transformer windings. The sensed currents are sent to the GCUs and the GAPCU for further processing. 2 Three-hole CTAs are used on three wire feeders. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 7 Sep 29/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 3 The three-hole CTA is used as the line CT that enables the GCUs and GAPCU to monitor the generator line currents in each phase. Short circuits to ground on the feeders or in associated wiring are detected by comparing the line current to the corresponding generator current, monitored through the generator CT. This forms the differential [current] protection (DP) circuit. (f) Control Units 1 The GCU and GAPCU have two main aircraft tasks: a Control and protection. To monitor and control the quality of electric power supplied to the aircraft. b Built-In-Test Equipment (BITE). To collect and analyze fault data and to save this in NVM for later retrieval by maintenance personnel over the centralized fault display system (CFDS). 2 An additional feature that enables the control and protection, BITE and ARINC 429 communication is interactive unit-to-unit communications over a MIL-STD-1553 redundant channel (channel A or channel B) communications bus. 3 A test data link (RS485 protocol) is used for both software download and system debugging (through a feature of the data within the control unit). This feature is only available when the control unit is removed from the aircraft and specific test equipment hardware and software is attached. TASK 24-23-34-870-802-A 2. GCU CONTROL AND PROTECTION Subtask 24-23-34-870-003-A00 A. GCU Control and Protection Functions (1) The GCU provides protection for the generating channel, aircraft feeders and loads. Trip thresholds and time delays prevent nuisance trips and provide coordination with other control units for isolation of faults. Table 1 summarizes the GCU control and protective functions. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 8 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1 Table 1 GCU Control and Protection Functions GENERATOR FUNCTION SENSING THRESHOLD Overvoltage (OV) Highest POR phase Undervoltage (UV1) Lowest POR 105.5 -0 +1.5 phase V (UV2) 123.5 +1.5 V TIME DELAY TRIPS REMARKS Inverse GCR, GC Channel reset limited to two attempts with fault present. 4.5 seconds (max) (UV1) GCR, GC UV1: locked out by US, UF1, open GCR; UV2: locked out by US, UF1, not VR enabled. GCR, GC, SVS Channel reset limited to two attempts with fault present. GCR, GC, SVS UF1 and UF2 locked out by US and servo valve command (open). 68 1.5 V 160 ms (max) (UV2) Overfrequency (OF1) POR equiv (PMG)* 417.5 25 Hz 4.0 seconds (max) (OF2) POR equiv (PMG)* 440 5 Hz 160 ms (max) (OF3) POR equiv (PMG)* 457 2 Hz 50 ms (max) Underfrequency (UF1) POR equiv (PMG) 382.5 2.5 Hz 4.5 seconds (max) 362.5 2.5 Hz 150 ms (max) (UF2) Underspeed (US) Engine speed for IDG (ARINC429) Overcurrent (OC) Generator CTs 80 ms from US to shutdown 2.5 seconds from US to startup Current (Imax) Inverse (OC1) +15 A (min) above rated 70 ms (max) load (OC2) GC GCR Staged Isolation. Channel reset limited to two attempts with fault present. * 400 Hz. (POR) = 1200 Hz. (PMG) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 9 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1 GCU Control and Protection Functions (Continued) GENERATOR FUNCTION SENSING THRESHOLD TIME DELAY TRIPS Phase Sequence POR (PSEQ) Voltage Phase Sequence Not A-B-C 40 ms (max) GCR Manual Disconnect (DISC) Discrete Switch Discrete Input 40 ms (max) GCR, GC, SVS Fire Switch (FIRE) Discrete Switch Discrete Input 40 millisecond (max) GCR, GC, SVS PMG Phase-toPhase Short/ Open PMG or Phase-toChassis (CBIT only) SPMG-STS bit SPMG-STS bit None active Shorted Rotating GEN CT Diode (SRD) phases A,B,C Exciter Field Current REMARKS No software protection latch set. None 5 seconds (max) GCR, GC Differential Protection (DP) Generator 50 10 A and Line CT delta for each phase measurement 80 ms (max) GCR, GC Channel reset limited to two attempts with fault present. Open Phase Feeder GEN current Generator current < 10 Amps on one Phase with > 30 Amps on the other two Phases 2.5 seconds (max) GCR, GC Locked out by DP. Channel reset limited to two attempts with fault present. Servo Valve Deterioration (SV) POR equivalent (PMG) 2 seconds (max) GCR, GC, SVS Channel reset limited to two attempts with fault present. Modulation of +5 Hz about frequency reference CPU Failsafe GCR, GC, SVS Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 10 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (a) Overvoltage (OV) Protection 1 Alternating current voltage is provided by the three-phase IDG output. Each phase is sensed at the point-of-regulation (POR). The GCU senses the POR voltage to provide overvoltage protection for equipment on the ac load buses of the aircraft. 2 An OV fault is detected when the highest of the three phase voltages sensed at the POR exceeds 123.5 ±1.5 Vac. The time delay is inverse; that is, the higher the OV, the faster the generator control relay (GCR) and generator contactor (GC) trip. If the software completes two consecutive OV measurements and the fault is not present, the time delay is reset. The OV fault is limited to two reset attempts by use of the GCS. After two reset attempts, the channel is locked out and can only reset by a GCU cold start. (b) Undervoltage (UV) Protection 1 There are two UV functions recognized by the GCU: UV1 and UV2. A UV1 fault is detected when the lowest of the three phase voltages sensed at the POR is below 105.5 -0, +1.5 V. The UV1 time delay is 5 seconds (maximum). The GCR and GC trip. 2 A UV2 fault is detected when there is no overcurrent condition and the lowest of the three phase voltages sensed at the POR is below 68 ±1.5 V. The UV2 time delay is 160 milliseconds (ms) (maximum). The GCR and GC trip. 3 If the software completes two consecutive UV measurements and the fault is not present, the time delay is reset. (c) Overfrequency (OF) Protection 1 There are three OF functions recognized by the GCU: OF1, OF2, and OF3. An OF1 fault is detected when the PMG frequency exceeds 417.5 ±2.5 Hz (POR equivalent). The OF1 time delay is 4 seconds (maximum). The GCR, GC, and servo valve switch (SVS) trip. An OF fault condition resets when the frequency measured is 4 Hz below the fault threshold. The OF fault is limited to two resets. 2 An OF2 fault is detected when the PMG frequency exceeds 440 ±5 Hz (POR equivalent). The OF2 time delay is 160 ms (maximum). The GCR, GC, and SVS trip. An OF fault condition resets when the frequency measured is 4 Hz below the fault threshold. The OF2 is limited to two reset attempts by use of the GCS. After two reset attempts, the channel is locked out and can only reset by a GCU cold start. 3 The OF3 fault is detected when the PMG frequency exceeds the POR equivalent of 457 ±2 Hz. The OF3 time delay is 50 ms (maximum). The GCR and GC trip. An OF fault condition resets when the frequency measured is 4 Hz below the fault threshold. (d) Underfrequency (UF) Protection 1 A UF1 fault is detected when the PMG frequency is below 382.5 ±2.5 Hz (POR equivalent). The UF1 time delay is 4.5 seconds (maximum). The GCR, GC, and SVS trip. The UF1 fault is locked out by underspeed and an open servo valve switch command. An UF1 fault condition resets when the frequency measured is 4 Hz above the fault threshold. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 11 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 A UF2 fault is detected when the PMG frequency is below 362.5 ±2.5 Hz (POR equivalent). The UF2 time delay is 150 ms (maximum). The GCR, GC, and SVS trip. The UF2 fault is locked out by underspeed and an open servo valve switch command. An UF2 fault condition resets when the frequency measured is 4 Hz above the fault threshold. (e) Underspeed (US) Protection 1 The US protection monitors engine speed for IDG (ARINC429). The US function determines the minimum IDG and engine load carrying speed and provides coordination of the underfrequency and undervoltage protective functions. Input speed derived from the full authority digital engine control (FADEC) is provided to the GCU. A US fault is set when any of the conditions that follow occur: a FADEC is valid and the input speed is below 4450 rpm for 500 -0, +40 ms b FADEC is invalid and the PMG frequency is < 380 Hz c An IDG disconnect has occurred d The Fire Switch has been pushed 2 If any of these conditions occurs, the IDG is US and the engine is shutdown. The GC opens. (f) Overcurrent (OC) Protection 1 An OC fault is detected when current on any generator phase exceeds the maximum rated load for a channel by 15 amperes. This overcurrent condition is called Imax. The Imax condition for an aircraft is 116 +15 amperes. 2 If an Imax condition is present, the GCU time delay for an OC protective trip is inverse. That is, the higher the Imax fault, the faster the protective trip occurs. When the OC protection trip occurs, the GCU opens and locks out its associated BTC in an attempt to isolate the OC fault. If BTC lockout isolates the fault, no further action is taken. If the fault is still present after 60 milliseconds after BTC lockout, the GCU trips the GCR to isolate the generator from the fault. NOTE: If an OC condition occurs within 200 milliseconds of BTC closure, the OC protection trip is prevented to allow aircraft circuit breakers to clear any faults that may be present on the transfer bus. 3 Reset of a generating channel affected by an OC fault is limited to two cycles of the GCS. After two resets have been attempted, the channel is locked-out and must be reset by a GCU cold start. (g) Overload (OL) Protection 1 An overload (OL) condition exists when an overcurrent (Imax) condition on a generator has persisted for 9 to 11 seconds. The GCU closes its internal galley shed relay to provide a ground-level signal to the galley switch FAULT light. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 12 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 There is no automatic galley load shedding for a generator OL condition. If an OL condition is present, the closed galley shed relay in the GCU causes the galley switch FAULT light to come on. The flight crew is prompted by the ECAM display and Master Caution chime to set the galley control switch to OFF and remove all galley loads. If the OL condition persists, the GCU assumes protective functions for an OC fault. (h) Phase Sequence (PSEQ) Protection 1 A PSEQ fault is detected when the generator phase sequence measured at the POR is not (A-B-C). If a PSEQ fault persists for 40 milliseconds (maximum), the GCR trips. The GCR trip is locked out if the lowest phase voltage is less than 40 ±2 Vac. If the software completes two consecutive PSEQ measurements and the fault is not present, the time delay is reset. (i) Manual IDG Disconnect (DISC) Protection 1 The IDG contains a manually operated disconnect solenoid. When the solenoid is turned on, it separates the clutch teeth of the IDG input shaft. The separated input mechanically disconnects the IDG transmission from the engine gearbox drive. Disconnect protection is accomplished through a DISCONNECT switch on the aircraft flight deck. The DISC time delay is 40 milliseconds (maximum). The GCR and GC trip and the servo valve switch opens. Once the IDG has been disconnected, reset cannot be accomplished until the aircraft is on the ground. (j) Fire Trip (FIRE) Protection 1 The FIRE switch on the aircraft flight deck provides emergency shutdown of the IDG channel in case of an engine fire. The FIRE switch trip time delay is 40 milliseconds (maximum). The GCR and GC trip and the servo valve switch opens. If the software completes two consecutive FIRE switch measurements and the fault is not present, the time delay is reset. (k) PMG Phase-to-Phase Shorted/Open PMG Phase Protection 1 Shorted and Open Permanent Magnet Generator (SOPMG) protection is used for BITE purposes only so as to sustain operation with a PMG open or short. The SOPMG protection detects an open PMG phase or a phase-tophase PMG short circuit at channel startup. A PMG ripple detection circuit in the GCU has a setpoint to activate the SPMG-STS signal. The SPMGSTS signal is used by the BITE function to detect and identify an SOPMG. A PMG fault that results in a protection trip is isolated in Fault Isolation BIT (FIT). (l) Shorted Rotating Diode (SRD) Protection 1 The main generator field is controlled by the output of the exciter that is rectified by six diodes in the generator rotor. If one or more of the diodes short, there is an increase in exciter field current ripple and an increase in exciter field supply voltage. The SRD fault is detected by the highest phase generator current > 174 amps for more than 5.5 seconds (maximum). The GCR and GC trip. If the software completes two consecutive SRD measurements and the fault is not present, the time delay is reset. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 13 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (m) Differential Protection (DP) 1 Differential Protection detects a condition where the current (for a given generator phase) measured at the generator differs from the current (same phase) measured on the ac feeder (line or load bus). This condition happens when a short occurs on the feeder or a connector. The DP fault is detected when the main feeder current differs from the generator current by 50 ±10 amperes. If the DP condition exists for 80 milliseconds (maximum), the GCR and GC trip. After a DP fault trip, the GCU software allows two resets of the electrical system using the GCS before it locks out further attempts. If the software completes two consecutive DP measurements and the fault is not present, the time delay is reset. (n) GLC Failure (GLCF) Protection 1 The GLCF protection trips the channel when the PR command is absent but 25 5 amperes of current is flowing through the GLC. This fault is sometimes called a welded or stuck GLC contact failure. If the GLCF condition exists for 160 milliseconds, the GCR trips and the BTC is locked out. The GLCF trip is locked out by a DP fault. If the software completes two consecutive GLCF measurements and the fault is not present, the time delay is reset. Reset of a generating channel affected by a GLCF fault is limited to two cycles of the GCS before the GCU software locks out further attempts. (o) Servo Valve Deterioration (SV) Protection 1 The GCU uses PMG frequency to measure IDG output frequency. The SV protection detects a frequency deviation (modulation) that exceeds ±5 Hz (POR equivalent) about the frequency reference (400 Hz POR equivalent) at a rate of 240 milliseconds. The SV time delay is 2 seconds (maximum). The GCR and GC trip and the servo valve switch opens. After an SV trip, the GCU software allows two resets of the electrical system using the GCS before it locks out further attempts. If the software completes two consecutive SV measurements and the fault is not present, the time delay is reset. TASK 24-23-34-870-803-A 3. PHYSICAL DESCRIPTION A. The GCU is dimensionally an ARINC 600, size 3MCU case. The case is of sheet aluminum, spot-welded, open construction with a removable cover that provides complete access to internal subassemblies. Refer to Figure 3 for the arrangement of the GCU. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 14 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 3 HE-242334-101890 Figure 3 Arrangement of GCU Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 15 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 B. The removable cover includes the front, top, and side panels of the GCU. The front panel of the chassis has two NAS622-style hold-down hooks to secure the unit to the ARINC 600 rack. The front panel also has an identification plate, and a handle for removal and handling of the GCU. C. The rear panel of the chassis contains a rectangular-shaped opening to accept the installation of an ARINC 600-style connector, shell size 2. The connector is keyed to polarization position 20. D. The GCU contains five Printed Wiring Board (PWB) assemblies. They include Interconnect PWB Assembly A1, Input/Output (I/O) PWB assembly A2, microprocessor PWB assembly A3, Power Supply/Voltage Regulator (PS/VR) PWB assembly A4, and ARINC Interconnect PWB Assembly A5. E. The PWB assemblies are electrically connected to each other and to external sources through the use of interconnect assemblies. Interconnect PWB assembly A1 connects the PWB assemblies A2 through A4 to each other. ARINC Interconnect PWB Assembly A5 connects the PWB assemblies A2 and A4 to external input signals. ARINC Interconnect PWB Assembly A5 also interfaces GCU output signals, from the PWB assemblies, to their external destinations. RRJ GCUs have a blocking post assembly installed between the A2 and A3/A4 PWB assembly guides. The blocking post assembly prevents installation of the A3 PWB assembly outside the guides. F. The top and bottom of the GCU contains ventilation holes to provide for the passage of air through the unit by convection. The air provides cooling for internal subassemblies within the GCU. The air inlet is through the bottom, while the air exhaust is through the top of the unit. The pattern and size of the ventilation holes are in accordance with the ARINC 600 specification. TASK 24-23-34-870-804-A 4. OPERATION Subtask 24-23-34-870-004-A00 A. GCU Top Level Functional Descriptions (1) The functional block diagram for the GCU is shown in Figure 4. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 16 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 4 Figure 4 GCU Functional Block Diagram Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 17 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (2) Interconnect PWB Assembly A1 (a) Interconnect PWB assembly A1 is a 10 layer circuit card. It contains no active circuit, but provides the interconnection for the various analog and control (discrete) signals. These PWB assemblies can be plugged directly into connectors P1 (A2), P2 (A3), or P3 (A4). The connector P2 incorporates jack screws to improve retention. (3) Input/Output PWB Assembly A2 (a) The Input/Output PWB assembly A2 performs input/output signal conditioning of various signals for the GCU. In addition, it serves as a link between the ARINC interconnect PWB assembly A5 and interconnect PWB assembly A1. An isolation barrier is maintained between the external signals that are referenced to power return (PSA5_RTN or PWRGND) and internal signals that are referenced to signal ground (ANAGND or DIGGND). Signal ground is separated into two signals, analog ground (ANAGND1) and digital ground (DIGGND1). (4) Microprocessor PWB Assembly A3 (a) Microprocessor PWB assembly A3 provides system protection and control to manage the overall operation of the GCU. The microprocessor circuits contain an 80C186 microprocessor and provide system test and protection. The memory circuits contain Non-Volatile Memory (NVM) and a line decoder/demultiplexer. The input/output interface circuits use analog multiplexers to provide an interface between the Digital Signal Processor (DSP), Analog-to-Digital Converters (ADCs) and the Application Specific Integrated Circuit (ASIC). There are two connectors on this assembly, A3J2 and A3J1. A3J1 is the main connector which interfaces with other PWB assemblies through front interconnect PWB assembly A1. The connector A3J1 incorporates jack screws to improve retention. A3J2 is a test connector that does not have a mating connector within the unit. It is used for board testing, microprocessor emulation, and programming the on-board programmable devices. (5) Power Supply/Voltage Regulator PWB Assembly A4 (a) The power supply/voltage regulator PWB assembly A4 accepts three-phase PMG power and +28 Vdc battery power (PSU28V), and converts them into 15 Vdc, +5 Vdc, PWR15V, PWRN15V, and PWR28V output voltages for use within the GCU. (b) The PWB assembly A4 interfaces (through the 62-pin A4P1 connector) with the ARINC interconnect PWB assembly A5 and connects to circuits [PMG power source, exciter field interface, power ready relay and the external +28 Vdc power sources (PSU28V)] outside the GCU. (c) The PWB assembly A4 connects to the Interconnect PWB assembly A1, through the 62-pin connectors A4J1 and A1P3, and interfaces with the other PWBs within the GCU. (d) The PWB assembly A4 also performs the following functions: Voltage Regulator (VR) Disable Protection, Shorted PMG Protection, Exciter Field Pulse-Width Modulation (PWM) Drive, Exciter Field (±) Volts Monitor, Exciter Field Current Monitor, Exciter Drive Protection, PMG Transformer Power, Hybrid Power, Power-Up Reset (PUR) DC Voltage Monitor, PMG Frequency Sensing, Power Ready Relay Control, GLC Control, GCR Relay Protection, and Built-In-Test (BIT). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 18 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (6) ARINC Interconnect PWB Assembly A5 (a) ARINC interconnect PWB assembly A5 consists of a 6 layer circuit board connected by a flexible printed wiring board to an ARINC 600-style connector. The circuit board contains surface mounted filter capacitors provided for filtering various signals. (b) The ARINC 600-style connector section allows signals from the aircraft and other EPGS components to enter the GCU through the connector. The signals include input/output power and drive signals, controller input/output signals, and communication interface signals. TASK 24-23-34-870-805-A 5. INPUT/OUTPUT PWB ASSEMBLY A2 DETAILED CIRCUIT DESCRIPTIONS Subtask 24-23-34-870-005-A00 A. General Description (1) Refer to Figure 2002. The PWB assembly A2 provides isolation between external signals and the internal GCU electronics. It provides both discrete and analog circuit sensing. This PWB receives the generator and line current transformer assemblies (CTA), the point-of-regulation (POR), and the RS485, ARINC 429 and Inter-LRU interfaces. The PWB assembly A2 also interfaces with the electrical contactor management unit (ECMU), contactors, and flight deck. (2) The PWB assembly A2 has the hardware to receive twenty-seven discrete inputs. Nineteen inputs can be either OPEN/GROUND or GROUND/OPEN, while eight inputs are 28V/OPEN signals. The PWB assembly A2 has the hardware to output sixteen discrete signals. Twelve outputs can be either OPEN/GROUND or GROUND/ OPEN and four outputs are 28V/OPEN signals. (3) The PWB assembly A2 receives sixteen discrete inputs. Ten of the inputs are configured as GROUND/OPEN signals, and six inputs are configured as 28V/OPEN signals. Six discrete signals are output, with one of the outputs configured as a 28V/ OPEN signal and the remaining five outputs configured as GROUND/OPEN signals. (4) The Input/Output (I/O) port provides BIT stimulus and enable outputs to the exciter field and servo valve interfaces on the power supply/voltage regulator PWB assembly A4, as well as the A4 voltage monitor. Driver command signals are also sent from PWB assembly A2 to the PWB assembly A4 power ready relay and GCR circuits. (5) The PWB assembly A2 receives status bit inputs for the I/O port from the PWB assembly A4. (6) The PWB assembly A2 receives the following input signals (refer to Table 2): Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 19 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 2 Table 2 Analog and Discrete Inputs Signal Name (GCU Input) Schematic Block Signal Type POR_PHA ANALOG_1 POR_PHB Current Level (A) Voltage Level (Vac) Nom Max Nom Max ANALOG 2.0 mA 6.0 mA 115 Vac 130 Vac ANALOG_1 ANALOG 2.0 mA 6.0 mA 115 Vac 130 Vac POR_PHC ANALOG_1 ANALOG 2.0 mA 6.0 mA 115 Vac 130 Vac POR_PHN ANALOG_1 ANALOG 2.0 mA 6.0 mA 0.0 Vac 0.0 Vac GEN_CT_PHA ANALOG_1 ANALOG 231.0 mA 900.0 mA 0.5 Vac 2.5 Vac GEN_CT_PHB ANALOG_1 ANALOG 231.0 mA 900.0 mA 0.5 Vac 2.5 Vac GEN_CT_PHC ANALOG_1 ANALOG 231.0 mA 900.0 mA 0.5 Vac 2.5 Vac GEN_CT_COM ANALOG_1 ANALOG 900.0 mA 0.0 Vac 0.0 Vac LINE_CT_PHA1 ANALOG_2 ANALOG 261.0 mA 900.0 mA 0.5 Vac 2.5 Vac LINE_CT_PHB1 ANALOG_2 ANALOG 261.0 mA 900.0 mA 0.5 Vac 2.5 Vac LINE_CT_PHC1 ANALOG_2 ANALOG 261.0 mA 900.0 mA 0.5 Vac 2.5 Vac LINE_CT_COM1 ANALOG_2 ANALOG 900.0 mA 0.0 Vac 0.0 Vac LINE_CT_PHA2 ANALOG_2 ANALOG 261.0 mA 900.0 mA 0.5 Vac 2.5 Vac LINE_CT_PHB2 ANALOG_2 ANALOG 261.0 mA 900.0 mA 0.5 Vac 2.5 Vac LINE_CT_PHC2 ANALOG_2 ANALOG 261.0 mA 900.0 mA 0.5 Vac 2.5 Vac LINE_CT_COM2 ANALOG_2 ANALOG 0.0 mA 900.0 mA 0.0 Vac 0.0 Vac OIL_TMP_COM ANALOG_3 ANALOG 10.0 mA 20.0 mA 0.0 Vdc 0.0 Vdc OIL_TMP_OUT ANALOG_3 ANALOG 5.0 mA 20.0 mA 1.0 Vdc 5.0 Vdc OIL_TMP_IN ANALOG_3 ANALOG 5.0 mA 20.0 mA 1.0 Vdc 5.0 Vdc PR_1A* 330_340_DIS GROUND/OPEN 0.5 mA 20.0 mA 28.5 Vdc 32.0 Vdc PR_1B* 330_340_DIS GROUND/OPEN 10.0 mA 20.0 mA 28.5 Vdc 32.0 Vdc PR_3B* 330_340_DIS GROUND/OPEN 30.0 mA 100.0 mA 28.5 Vdc 32.0 Vdc PR_3A* 330_340_DIS GROUND/OPEN 5.0 mA 20.0 mA 28.5 Vdc 32.0 Vdc PR_2A 330_340_DIS OPEN/GROUND 1.33 A 2.73 A 28.5 Vdc 32.0 Vdc FUEL_CUTOFF* COM_DIS1 GROUND/OPEN 1.0 mA 1.5 mA 15.0 Vdc 15.0 Vdc LOW_OIL* COM_DIS2 GROUND/OPEN 1.0 mA 1.5 mA 15.0 Vdc 15.0 Vdc PIN_PRG_A* COM_DIS2 GROUND/OPEN 1.0 mA 1.5 mA 15.0 Vdc 15.0 Vdc PIN_PRG_B* COM_DIS2 GROUND/OPEN 1.0 mA 1.5 mA 15.0 Vdc 15.0 Vdc NOTE: 0.0 mA 0.0 mA An asterisk (*) after a signal name indicates an active low condition. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 20 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 2 Analog and Discrete Inputs (Continued) Signal Name (GCU Input) Schematic Block Signal Type PIN_PRG_C* COM_DIS2 PIN_PRG_D* Current Level (A) Voltage Level (Vac) Nom Max GROUND/OPEN 1.0 mA 1.5 mA 15.0 Vdc 15.0 Vdc COM_DIS1 GROUND/OPEN 1.0 mA 1.5 mA 15.0 Vdc 15.0 Vdc PIN_PRG_E* COM_DIS1 GROUND/OPEN 1.0 mA 1.5 mA 15.0 Vdc 15.0 Vdc PIN_PRG_F COM_DIS1 28V/OPEN 1.0 mA 1.5 mA 28.5 Vdc 32.0 Vdc PIN_PRG_PAR* COM_DIS2 GROUND/OPEN 1.0 mA 1.5 mA 15.0 Vdc 15.0 Vdc GCS_OFF COM_DIS1 28V/OPEN 1.0 mA 1.5 mA 28.5 Vdc 32.0 Vdc GCS_ON COM_DIS2 28V/OPEN 1.0 mA 1.5 mA 28.5 Vdc 32.0 Vdc DISC_SW MISC_DIS 28V/OPEN 1.0 mA 1.5 mA 28.5 Vdc 32.0 Vdc FIRE_SW MISC_DIS 28V/OPEN 1.0 mA 1.5 mA 28.5 Vdc 32.0 Vdc S2_IN MISC_DIS 28V/OPEN 1.0 mA 1.5 mA 28.5 Vdc 32.0 Vdc 28V/OPEN 2.0 mA 3.0 mA 28.5 Vdc 32.0 Vdc GCS_28V_CMD FILTER_CAPS_ SPARES NOTE: Nom Max An asterisk (*) after a signal name indicates an active low condition. Subtask 24-23-34-870-006-A00 B. Analog 1 Circuits (1) Three Phase Point-of-Regulation (POR) (a) The circuit steps the POR voltage down and provides isolation and signal conditioning for the voltage and frequency sensing circuits. The main ac generator voltage is measured at the POR/GLC on the contactor/CTA interface. The ferrite beads (A2FB1 through A2FB4) on each POR input provide electromagnetic interference (EMI) filtering for high frequencies. The resistivecapacitance (RC) networks to analog ground (ANAGND1) provide anti-alias filters to eliminate unwanted signals. Because all POR phase sense circuits operate in an identical way, only the POR Phase A sense circuit is discussed here. 1 POR Phase A a The POR phase A voltage (normally 115 Vrms L-N at 400 Hz) signal POR_PHA, is fed through ferrite bead A2FB1 (for EMI protection) to the isolation 28:1 step-down transformer A2T1. Transformer A2T1 reduces the voltage to a 4.1 Vrms signal (for a POR voltage of 115 Vrms L-N). The nominal signal is two-pole low pass filtered by a SalenKey filter with a roll-off frequency of approximately 1500 Hz. The model for a Salen-Key filter consists of a voltage controlled-voltage source [VCVS (A2AR1-3)] and two low-pass RC circuits. The two low-pass RC circuits consist of resistors A2R1 and A2R2, feedback capacitor A2C1, and capacitor A2C2. The analog output is routed to the I/O interface section of PWB assembly A3 as the A3U19-19 input ANALOG_01H (refer to Subtask 24-23-34-870-008-A00). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 21 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 POR Zero Crossing Detector a The generator CTAs produce a sinusoidal current proportional to the related load current. The phase currents, GEN_CT_PHA, B, and C, are measured at the generator CTs on the IDG interface. The ferrite beads (A2FB5 through A2FB8) on each generator CTA input provide EMI filters for high frequencies. The RC networks to analog ground (ANAGND1) provide anti-alias filters to eliminate unwanted signals. b Because all generator CT phase sense circuits operate in an identical way, only the Generator CT Phase A sense circuit is discussed here. Subtask 24-23-34-870-007-A00 C. Analog 2 Circuits (1) Three Phase Line CT Sense (a) The line current transformers produce a sinusoidal current proportional to the related load current. (b) The phase currents are sent to the GCUs as LINE_CT_PHA2, B2, and C2. The signal LINE_CT_PHA1 is used for open cable detection. (c) The current draw is measured near the POR/GLC on the contactor/CTA interface. Ferrite beads (A2FB11 through A2FB18) on each line CT input provides EMI filters for high frequencies. The RC networks to analog ground (ANAGND1) provide anti-alias filters to eliminate unwanted signals. Because all line CT phase sense circuits operate in an identical way, only the Line CT Phase A1 and A2 sense circuits are discussed here. 1 Line CT Phase A1 a The signal LINE_CT_PHA1 is fed through ferrite bead A2FB11 to burden resistors A2R31 and A2R32, where it develops a voltage proportional to the line currents across the 1:4 step-up isolation transformer A2T11. Transformer A2T11 output voltage is proportional to, and isolated from, the line current input. The output voltage signal is two-pole low pass filtered by a Salen-Key filter with a roll-off frequency of approximately 1500 Hz. The model for a Salen-Key filter consists of a VCVS A2AR3-10 and two low-pass RC circuits. The two low-pass RC circuits consist of resistors A2R33 and A2R34, feedback capacitor A2C21, and capacitor A2C22. The analog output is routed to the I/O interface section of PWB assembly A3 as the A3U18-19 input ANALOG_05H (refer to Subtask 24-23-34-870-008-A00). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 22 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 Line CT Phase A2 a The signal LINE_CT_PHA2 is fed through ferrite bead A2FB15 to burden resistors A2R43 and A2R44, where it develops a voltage proportional to the line currents across the 1:4 step-up isolation transformer A2T14. Transformer A2T14 output voltage is proportional to, and isolated from, the line current input. The output voltage signal is two-pole low pass filtered by a Salen-Key filter with a roll-off frequency of approximately 1500 Hz. The model for a Salen-Key filter consists of a VCVS A2AR1-12 and two low-pass RC circuits. The two low-pass RC circuits consist of resistors A2R45 and A2R46, feedback capacitor A2C27, and capacitors A2C28. The analog output is routed to the I/O interface section of PWB assembly A3 as the A3U19-5 input ANALOG_06H (refer to Subtask 24-23-34-870-008-A00). Subtask 24-23-34-870-008-A00 D. Analog 3 Circuits (1) The IDG oil inlet and outlet temperature bulbs are monitored by the GCU to provide oil overtemperature and delta temperature protection. An IDG oil overtemperature condition does not cause a protective trip, but alerts the flight crew to disconnect the IDG before it is damaged by high oil temperature. (2) Oil Temperature Sense (a) All IDGs contain two identical sensing circuits (OIL_TMP_IN and OIL_TMP_OUT) with common signal (OIL_TMP_COM) that measures the inlet and outlet oil temperatures. The input and output temperatures, sent to the PWB assembly A3 as the analog signals ANALOG_13H and ANALOG_14H, enter multiplexers at A3U18-5 as (IN15) and A3U19-11 as (IN9). 1 Oil Temperature Sense Circuit Description a The 15-volt power supply, PWR15V, provides voltage to high-precision 5-volt reference A2U2. The output of voltage reference A2U2 is applied to two voltage dividers. Resistor A2R61 and the input temperature bulb form one voltage divider. Resistor A2R67 and the output temperature bulb form another voltage divider. The two identical circuits sense the voltage across each temperature bulb and provide isolation between PWRGND and DIGGND. Voltage is returned to PWRGND. Transient voltage suppressors A2VR1 through A2VR3 prevent transient voltage spikes. Each TVS conduct when the voltage across its line exceeds the zener avalanche rating of 9 volts. b Voltage developed between IDG oil temperature input (OIL_TMP_IN) and the IDG oil temperature return (OIL_TMP_COM) is proportional to the temperature of the input oil. The differential amplifier A2AR5 through the differential filter resistors A2R63 and A2R64, and capacitor A2C42 sense the voltage. The difference between the inputs (pins 2 and 3) of amplifier A2AR5, becomes A2AR5-6 output signal OIL_IN. The OIL_IN signal is sent to the microprocessor on the PWB assembly A3 as analog signal ANALOG_13H (A3U18-5) (refer to Subtask 24-2334-870-008-A00). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 23 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 c Voltage developed from IDG oil temperature output (OIL_TMP_OUT) to the IDG oil temperature return (OIL_TMP_COM) is proportional to the temperature of the output oil. The differential amplifier A2AR6 through the differential filter resistors A2R65 and A2R66, and capacitor A2C43 sense the voltage. The difference between the inputs (pins 2 and 3) of the amplifier A2AR6, becomes A2AR6-6 output signal OIL_OUT. The OIL_OUT signal is sent to the microprocessor on the PWB assembly A3 as the analog signal ANALOG_14H (A3U19-11). Subtask 24-23-34-870-009-A00 E. RS485 Interface (1) The GCU communicates with test equipment through the RS485 communications bus. The RS485 interface is used for factory testing and diagnostic purposes together with downloadable test software. A test link connects to the GCU through the main connector. A test enable pin at the main connector enables the test link function in the embedded software. (2) The embedded flight software is downloadable into flash memory of the GCU by the test link, only when the test pin is enabled, and a valid download command is received from the test link within 50 ±10 ms of cold start. (3) Three pass-through signals (TEST_LNK_POS, TEST_LNK_NEG and B_SYNCMC*) pass directly through the A2 PWB from the A2J1 connector to the A2P1 connector. TEST_LNK_POS and, TEST_LNK_NEG make up the serial bus test link. B_SYNCMC*, a test point used for acceptance testing, is not related to the serial test link. Subtask 24-23-34-870-010-A00 F. ARINC 429 Receiver (1) This circuit is responsible for the conversion of the ARINC 429 signal into two digital signals read by the microprocessor. One of the digital signals goes to a logic high when the ARINC 429 signal is high and the other goes to a logic high when the ARINC input is low. (a) Full Authority Digital Engine Control (FADEC) Interface 1 The GCU receives engine speed information from the FADEC through the ARINC 429 serial link. a Receiver/Isolation Circuit 1) The FADEC signal, RX_429_POS, is limited by diodes A2D136 and A2D137 and bi-directional TVS A2VR61 to prevent voltage spikes that appear on the line. The FADEC signal RX_429_NEG is limited by diodes A2D138 and A2D139 and TVS A2VR62 to prevent voltage spikes that appear across the line. The limited signals are passed to the operational amplifier A2AR9 (pins 2 and 3), configured as a unity gain differential mode amplifier with a gain of 1. Resistors A2R461 through A2R464 set the gain of amplifier A2AR9. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 24 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2) The differential output of A2AR9-1 passes through either the resistor A2R470 to comparator A2AR11-3 or through resistor A2R465 to comparator A2AR10-2. Comparator A2AR11 is setup for positive hysteresis by the current-limiting resistor A2R469 and 5.1 V zener diode A2VR64 which apply a reference voltage at A2AR11-2 through positive feedback resistor A2R471 and the pull-up resistor A2R472. If the signal at A2AR11-3 is greater than the reference signal at pin 2, the output at pin 7 transitions low to power ground (PWRGND). 3) The comparator A2AR10 is setup for positive hysteresis by the current-limiting resistor A2R466 and 5.1 V zener diode A2VR63 which apply a reference voltage A2AR10-3 through positive feedback resistor A2R467 and pull-up resistor A2R468. If the signal at A2AR10-2 is greater than the reference signal at pin 3, the output at pin 7 transitions high (PWR15V). 4) If either pin 7 of comparators A2AR11 and A2AR10 transition low, the corresponding internal LED of the optically coupled logic gate A2U78 turns on. Turn-on of gate A2U78 drives the output logic (A429_RXA or A429_RXA_L) high. These signals are sent from the A2 PWB to the ASIC on PWB assembly A3. Signal A429_RXA is the inverse of the signal A429_RXA_L; therefore, only one signal can be high at any one time. Subtask 24-23-34-870-011-A00 G. Communications 1 (COMS_1) (1) Digital signals from the microprocessor transmit over two redundant ARINC 429 buses at either a high rate [100-kilohertz (kHz)] or a low rate (12.5 kHz). Isolation is maintained between the signal ground and the ARINC 429 data bus. (a) System Data Acquisition Concentrator (SDAC) Interface 1 The GCU transmits generating channel status information to either the SDAC1 or the SDAC2 through the ARINC 429 serial link. An ARINC 429 data word consists of 32 bits, with bit 1 transmitted and received first. The first eight bits of each ARINC word provide a label identifying the data in the word. A three digit octal number (050) specifies a GCU. 2 Bits 9 and 10 are the source/destination identifier (SDI) of the ARINC word. The SDIs of GCU1 and GCU2 are 01 and 10, respectively. 3 Bits 11 through 29 are part of the data field, which is either numeric and/or discrete. Bits 30 and 31 form the sign status matrix (SSM), which is dependent on the data type (numeric or discrete) and indicates the status of the data source. The SSM code 00 indicates normal operation for discrete data and a failure warning for numeric data. Code 11 indicates faulty operation for discrete data and normal operation for numeric data. The SSM code 01 indicates no computed data, while the code 10 indicates a functional test for either data type. 4 Bit 32 provides an odd parity bit, so the total number of 1’s in a data word including the parity bit is always odd. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 25 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (b) Transmitter/Isolation Circuit 1 The A3 PWB ASIC digital signals, A429_TXA and A429_TXA_L, enter Schmitt trigger inverter A2U1 at pins 9 and 11 to provide noise protection. The inverted signals are inputs to the optically coupled logic gate A2U7 (pins 2 and 3). A logic low signal turns on the corresponding internal LED. When the internal LED turns on, the output of A2U7-7 or A2U7-6 transitions high. The signal, A429_TXA, is the opposite of signal A429_TXA_L; therefore, only one signal can be high at any one time. The resistors A2R110 and A2R111 bypass leakage current from the internal LEDs, so the logic gate A2U7-7 or A2U7-6 outputs stay low when the LEDs are turned off. 2 The power supply voltage from gate A2U7-8 is provided by the positive 5 Vdc power supply (PWR5V). The 5 Vdc power supply, input from voltage regulator A2U6-2, uses resistors A2R105 through A2R107 to step down the +15 Vdc power supply (PWR15V). Capacitors A2C52 and A2C53 filter the input, capacitors A2C55 and A2C56 improve transient response, and capacitor A2C54 improves ripple rejection. Protection diode A2D6 prevents capacitors A2C55 and A2C56 from discharging into the voltage regulator at periods of low input voltage. 3 The transmitter’s high rate (HI_RATE) signal connects to the cathode of the internal LED of the opto-coupler A2U10. The resistor A2R114 bypasses leakage current from the internal LED and holds the opto-coupler’s output low. A low HI_RATE signal provides a ground path for the LED and turns on the opto-coupler A2U10. 4 When opto-coupler A2U10 is turned on, a high logic signal goes to quad analog switch A2U9 at pins 1, 8, 9 and 16. The high logic signal closes all four switches and puts capacitors A2C65 and A2C66, A2C61 and A2C62, A2C67 and A2C68, and A2C59 and A2C60 in parallel. 5 The two redundant ARINC 429 transmitters A2U8 and A2U11 receive a logic signal from gate A2U7-7 that enters transmitters A2U8-4 and A2U11-4 as redundant channel A data. A logic signal from gate A2U7-6 is sent to transmitters A2U8-13 and A2U11-13 as redundant channel B data. The internal clock inputs (A2U8-14 and A2U11-14) and synchronous inputs (A2U8-3 and A2U11-3) receive a PWR5V signal through resistor A2R108. The voltage reference inputs (A2U8-1 and A2U11-1) also receive a PWR5V signal. 6 The CA (A2U8-5 and A2U11-5) and CB (A2U8-12 and A2U11-12) outputs determine the transmission rate of the transmitters. Capacitors A2C66, A2C62, A2C68 and A2C60 force the transmitters into a high (100 kHz) transmission rate. When capacitors A2C65, A2C61, A2C67 and A2C59 are added in parallel with the other capacitors, the transmission frequency rate decreases to 12.5 kHz. 7 The transmitter 1 serial data channel A output signal OUTA (A2U8-6), limited by bi-directional TVS A2VR11, prevents voltage spikes that appear across the line. The limited signal routes through ferrite bead A2FB21 and outputs to the SDAC1 as the signal TX1_429_POS. 8 The transmitter 2 serial data channel A output signal OUTA (A2U11-6), limited by bi-directional TVS A2VR13, prevents voltage spikes that appear across the line. The limited signal routes through ferrite bead A2FB23 and outputs to the SDAC2 as the signal TX2_429_POS. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 26 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 9 The transmitter 1 serial data channel B output signal OUTB (A2U8-11), limited by bi-directional TVS A2VR12, prevents voltage spikes that appear across the line. The limited signal routes through ferrite bead A2FB22 and outputs to the SDAC1 as the signal TX1_429_NEG. 10 The transmitter 2 serial data channel B output signal OUTB (A2U11-11), limited by bi-directional TVS A2VR14, prevents voltage spikes that appear across the line. The limited signal routes through ferrite bead A2FB24 and outputs to the SDAC2 as the signal TX2_429_NEG. (c) Inter-LRU Interface 1 The GCU communicates with the GAPCU through the inter-LRU communications bus. Inter-LRU communications are accomplished through the Bus B channel of a serial transceiver which supports the inter-LRU serial bus (Manchester-encoded data bus). GCUs are remote terminals (RTs). Each GCU and GAPCU has bi-directional communication through a Manchester-encoded data bus. The GAPCU is the bus controller. The A2U5 transceiver has two identical channels but only one (channel B) is used by the GCU at this time. a Channel A 1) Channel A is not used by the GCU. b Channel B 1) The A2U5 transceiver’s Channel B receives transmit high (TXB), transmit low (TXB_L), and transmit inhibit (TXINH_B) signals from the microprocessor interface circuit on the PWB assembly A3. These are logic high (2.5 V) and logic low (0.5 V) input signals that drive Channel B to output corresponding signals. When TXB is high and TXB_L low, transceiver A2U5 outputs a logic high to the data bus (BUSB and RXB high, and BUSB_L and RXB_L low). If TXB is low and TXB_L is high, the output is a logic low to the data bus. When transceiver A2U5 (Channel B) receives a logic low on both TXB and TXB_L, the output to the data bus is zero volts. A high TXINH_B input prevents transmission on the corresponding data bus. 2) The BUS_B and BUS_B_L outputs are coupled with the isolation transformer A2T26 to the bus link interface as the Manchester II bi-phase signal across LRU_SER_APOS and LRU_SER_ANEG. The bus link connects to the GAPCU and interfaces the outputs from Channel B with data bus A. 3) When a high logic signal is on the data bus, transceiver A2U5 sends a high logic on the RXB and logic low on the RXB_L outputs. The opposite is true when a logic low is received on the data bus. The RXB and RXB_L signals are sent to the microprocessor interface circuit on the PWB assembly A3. NOTE: Isolation transformers A2T21 through A2T25 and resistors A291 through A2R102 are used only by the GAPCU for communication with up to four GCUs. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 27 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subtask 24-23-34-870-012-A00 H. Discrete Inputs (1) The GCU receives sixteen discrete inputs. Ten of the inputs are configured as GROUND/OPEN signals, and six inputs are configured as 28V/OPEN signals (refer to Table 2). (2) The PWB assembly A2 receives status bits from the PWB assembly A4. (a) Typical Inputs 1 Discrete input information from control switches and auxiliary (AUX) contacts are inputs to the PWB assembly A2, conditioned further and converted to a logic signal. The input signals (GROUND/OPEN, 28V/ OPEN, or OPEN/GROUND) are representative of switch closures on relays, push button switch contacts, or hard-wired discrete signals. 2 The typical ground/open discrete signal input (active low), conditioned by a low-pass filter, provides a path to ground for an opto-coupler circuit. The discrete input 15 Vdc (DIS_IN_15V) signal, tied to the anode of the optocoupler’s internal light emitting diode (LED), provides 15 Vdc power (through a blocking diode) to the ground/open inputs for normal operation and removes it for BIT purposes. The discrete BIT ground (DIS_BIT_GND) signal provides a path to ground, during BIT testing, for the cathode of the internal LED through a blocking diode and a discrete bit opto-coupler. 3 The typical 28V/open discrete signal input is conditioned by a low-pass filter and provides a drive signal for an opto-coupler circuit. The DIS_BIT_15V signal, tied to the anode of the opto-coupler’s internal LED, provides a 15 Vdc signal to the 28V/open inputs for BIT purposes. 4 The typical open/ground discrete signal input (active high), conditioned by a low-pass filter, provides a path to ground for an opto-coupler circuit. The DIS_IN_15V signal, tied to the anode of the opto-coupler’s internal LED, provides nominal 15 Vdc power (through a blocking diode) to the open/ ground inputs for normal operation and removes it for BIT purposes. The DIS_BIT_GND signal provides a path to ground, during BIT testing, for the cathode of the internal LED through a blocking diode and a discrete bit opto-coupler. (b) Common Discrete Inputs 1 and 2 1 These discrete inputs (FUEL_CUTOFF*, LOW_OIL*, GCS_ON, GCS_OFF, PIN_PRG_PAR* and PIN_PRG_A* through PIN_PRG_F) are provided to all GCUs. The discrete inputs (TEST_EN* and FTOR_ON*) are provided to all GCUs for test purposes only. The discrete inputs (BTC_CLOSED* and GND_AIR_SW*) are provided to all GCUs. The outputs for the tri-state buffers A2U67 and A2U70, enabled by the inputs RD02062C and RD020624 (pins 1 and 19), are from the I/O port. a Fuel Cutoff Input 1) The fuel cutoff signal, FUEL_CUTOFF*, is manually provided by the two engine master control switches on the flight control panel and indicates a removal of fuel flow to the respective IDG. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 28 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2) The active (low) ground/open discrete signal input, FUEL_CUTOFF*, is conditioned by a low-pass T-filter (resistors A2R317 and A2R316, and capacitor A2C145). Blocking diode A2D70 provides a path to ground for the opto-coupler A2U62-2 when the discrete signal input is active (low). This turns on the opto-coupler and pulls the output (A2U62-7) to ground (DIGGND1). The signal at pin 7 routes to the tri-state octal buffer at A2U67-4 and outputs to the data bus as signal DATA_BUS<2> from A2U67-16 when enabled by the control signal RD02062C* (refer to Subtask 24-23-34-870-013-A00). 3) The DIS_IN_15V signal, tied to the anode (A2U62-1) of the optocoupler’s internal LED, provides nominal 15 Vdc power through blocking diode A2D46 to the ground/open inputs during normal operation and removes it for BIT purposes. Capacitor A2C146 filters the DIS_IN_15V signal. Resistor A2R319 bypasses leakage current from the internal LED when the discrete input signal transitions open. The output A2U62-7 is held high by pullup resistor A2R320 and the power supply POS5V. 4) The DIS_BIT_GND signal provides a path to ground (PWRGND), during BIT testing, for the cathode (A2U62-2) of the internal LED through isolation resistor A2R318, blocking diode A2D71 and discrete bit opto-coupler A2U56. b Low Oil Pressure Input 1) An active low oil pressure (LOW_OIL*) signal is provided by a discrete low (ground) input from a low oil pressure (LOP) sensor located on the IDG. This fault does not cause a protective trip, but causes the GCU to light the IDG “FAULT” lamp on the flight deck electric power control panel. The crew is prompted to disconnect the IDG before severe damage occurs. 2) The active (low) ground/open discrete signal input, LOW_OIL*, is conditioned by a low-pass T-filter (resistors A2R362 and A2R361, and capacitor A2C165). Blocking diode A2D95 provides a path to ground for the opto-coupler A2U48-2 when the discrete signal input is active (low). This turns on the opto-coupler and pulls the output (A2U48-7) to ground (DIGGND1). The signal at pin 7 routes to the tri-state octal buffer at A2U70-4 and outputs to the data bus as signal DATA_BUS<2> from A2U70-16 when enabled by the control signal RD020624* (refer to Subtask 24-23-34-870013-A00). 3) The DIS_IN_15V signal, tied to the anode (A2U48-1) of the optocoupler’s internal LED, provides nominal PWR15V through blocking diode A2D46 to the ground/open inputs during normal operation and removes it for BIT purposes. Capacitor A2C166 filters the DIS_IN_15V signal. Resistor A2R364 bypasses leakage current from the internal LED when the discrete input signal transitions open. The output A2U48-7 is held high by pullup resistor A2R365 and the power supply POS5V. 4) The DIS_BIT_GND signal provides a path to ground (PWRGND), during BIT testing, for the cathode (A2U48-2) of the internal LED through isolation resistor A2R363, blocking diode A2D96 and discrete bit opto-coupler A2U56. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 29 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 c Pin Programming Inputs (Ground/Open) 1) The pin programming inputs, PIN_PRG_A and PIN_PRG_B are ground/open signals that connect the ARINC 600 harness to all GCUs. The following is an example of pin programming bit decoding for an aircraft with SAM 146 engines and a GCU in number 1 position (refer to Table 3 and Table 4). Table 3 Table 3 GCU Pin Programming Pin B Bit Pin A Bit 0 1 Table 4 Table 4 Hexadecimal Identifier Identifier Aircraft Engine GCU Number 1H RRJ SAM 146 1 2H RRJ SAM 146 2 2) The active (low) ground/open discrete signal input, PIN_PRG_A*, is conditioned by a low-pass T-filter (resistors A2R377 and A2R376, and capacitor A2C171). Blocking diode A2D102 provides a path to ground for the opto-coupler A2U68-3 when the discrete signal input is active (low). This turns on the opto-coupler and pulls the output (A2U68-6) to ground (DIGGND1). The signal at pin 6 routes to the tri-state octal buffer at A2U70-13 and outputs to the data bus as signal DATA_BUS<5> from A2U70-7 when enabled by the control signal RD020624* (refer to Subtask 24-23-34-870-013-A00). 3) The DIS_IN_15V signal, tied to the anode (A2U68-4) of the optocoupler’s internal LED, provides nominal PWR15V through blocking diode A2D46 to the ground/open inputs during normal operation and removes it for BIT purposes. Capacitor A2C172 filters the DIS_IN_15V signal. Resistor A2R379 bypasses leakage current from the internal LED when the discrete input signal transitions open. The output A2U68-6 is held high by pullup resistor A2R380 and the power supply POS5V. 4) The DIS_BIT_GND signal provides a path to ground (PWRGND), during BIT testing, for the cathode (A2U68-3) of the internal LED through isolation resistor A2R378, blocking diode A2D103 and discrete bit opto-coupler A2U56. d BTC Closed Input 1) The BTC closed (BTC_CLOSED*) signal provides BTC status to all GCUs through auxiliary contacts on the BTC. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 30 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2) The active (low) ground/open discrete signal input, BTC_CLOSED*, is conditioned by a low-pass T-filter (resistors A2R307 A2R306, and capacitor A2C141). Blocking diode A2D66 provides a path to ground for the opto-coupler A2U61-2 when the discrete signal input is active (low). This turns on the opto-coupler and pulls the output (A2U61-7) to ground (DIGGND1). The signal at pin 7 routes to the tri-state octal buffer at A2U67-8 and outputs to the data bus as signal DATA_BUS<0> from A2U67-12 when enabled by the control signal RD02062C* (refer to Subtask 24-2334-870-013-A00). 3) The DIS_IN_15V signal, tied to the anode (A2U61-1) of the optocoupler’s internal LED, provides 15 Vdc power through blocking diode A2D46 to the ground/open inputs during normal operation and removes power for BIT tests. Capacitor A2C142 filters the DIS_IN_15V signal. Resistor A2R309 bypasses leakage current from the internal LED when the BTC status signal transitions open. The output A2U61-7 is held high by pull-up resistor A2R310 and the power supply POS5V. 4) The DIS_BIT_GND signal provides a path to ground (PWRGND), during BIT testing, for the cathode (A2U61-2) of the internal LED through isolation resistor A2R308, blocking diode A2D67 and discrete bit opto-coupler A2U56. e Ground/Air Switch Input 1) The ground/air switch (GND_AIR_SW*) signal indicates whether the aircraft is in the air or on the ground to the GCU. 2) When the aircraft is on the ground, the active (low) ground/open discrete signal input, GND_AIR_SW*, is conditioned by a lowpass T-filter (resistor A2R312 and A2R311, and capacitor A2C143). Blocking diode A2D68 provides a path to ground for the opto-coupler A2U61-3 when the discrete signal input is active (low). This turns on the opto-coupler and pulls the output (A2U616) to ground (DIGGND1). The signal at pin 6 routes to the tri-state octal buffer at A2U67-6 and outputs to the data bus as signal DATA_BUS<1> from A2U67-14 when enabled by the control signal RD02062C* (refer to Subtask 24-23-34-870-013-A00). 3) The DIS_IN_15V signal, tied to the anode (A2U61-4) of the optocoupler’s internal LED, provides 15 Vdc power through blocking diode A2D46 to the ground/open inputs during normal operation and removes it for BIT tests. Capacitor A2C144 filters the DIS_IN_15V signal. Resistor A2R314 bypasses leakage current from the internal LED when the ground/air switch status signal transitions open. The output A2U61-6 is held high by pull-up resistor A2R315 and the power supply POS5V. 4) The DIS_BIT_GND signal provides a path to ground (PWRGND), during BIT testing, for the cathode (A2U61-3) of the internal LED through isolation resistor A2R313, blocking diode A2D69 and discrete bit opto-coupler A2U56. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 31 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 f Generator Control Switch (OFF) Input 1) The generator control switch provides a manual OFF request (GCS_OFF) from the flight deck control panel to the associated GCUs to remove the generator from the main electrical bus and de-excite the generator. 2) An active 28V signal, GCS_28V_CMD, is provided by the 28 Vdc power supply (PWR28V) to the GCS on the flight deck. The GCS_28V_CMD signal is low-pass filtered by capacitor A2C278 and resistor A2R481. When the GCS is set to OFF, the active (off) 28V/open discrete signal GCS_OFF is provided to the GCU. This voltage signal, further conditioned by a low-pass T-filter (resistors A2R332 and A2R333 and filter capacitor A2C151), provides a drive signal through the blocking diode A2D77 to the opto-coupler A2U65-1. Capacitor A2C152 also filters the 28 Vdc signal. Resistor A2R334 bypasses leakage current from the internal LED when the GCS off signal transitions to the inactive (open) state (refer to Figure 5). Figure 5 HE-242334-101892 Figure 5 Generator Control Switch Operation Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 32 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 3) An active (high) signal turns on the opto-isolator A2U65 and pulls the output (A2U65-7) to ground (DIGGND1). When the GCS_OFF signal is inactive (open), pin 7 is held high by the pullup resistor A2R335 and the +5 Vdc power supply, POS5V. The output signal at pin 7 goes to the tri-state octal buffer at A2U67-13 and to the data bus as signal as signal DATA_BUS<5> from A2U67-7 when enabled by the control signal RD02062C* (refer to Subtask 24-23-34-870-013-A00). g Generator Control Switch (ON) Input 1) The generator control switch provides a manual ON request (GCS_ON) from the flight deck control panel to the associated GCUs to connect the generator to the main electrical bus, excite the generator, and allow the GLC to close. 2) An active 28V signal, GCS_28V_CMD, is provided by the 28 Vdc power supply (PWR28V) to the GCS on the flight deck. The GCS_28V_CMD signal is low-pass filtered by capacitor A2C278 and resistor A2R481. When the GCS is set to OFF, the active (off) 28V/open discrete signal GCS_OFF is provided to the GCU. This voltage signal, conditioned by a low-pass T-filter (resistors A2R372 and A2R373 and filter capacitor A2C169), provides a drive signal through the blocking diode A2D100 to the optocoupler A2U65-4. Capacitor A2C170 also filters the 28 Vdc signal. Resistor A2R374 bypasses leakage current from the internal LED when the GCS “ON” signal transitions to the inactive (open) state (refer to Figure 5). 3) An active (high) signal turns on the opto-isolator A2U65 and pulls the output A2U65-6 to ground (DIGGND1). When the GCS_ON signal is inactive (open), pin 6 is held high by the pull-up resistor A2R375 and the +5 Vdc power supply POS5V. The output signal at A2U65-6 is sent to the tri-state octal buffer at A2U70-11. Buffered outputs enter the bus DATA_BUS<4> at A2U70-9 when enabled by the control signal RD020624* (refer to Subtask 24-2334-870-013-A00). 4) The watchdog reset (WD_RESET*) signal, which enters the PWB assembly A3 from A2U70-11, causes the watchdog to reset when the signal transitions from high to low (falling edge). h Pin Programming Input (28V/OPEN) 1) The pin programming input, PIN_PRG_F, is a 28V/open signal that connects the ARINC 600 harness to the GCU. Refer to Table 3 for the GCU pin programming chart. 2) The active (high) 28V/open discrete signal input PIN_PRG_F, conditioned by a low-pass T-filter (resistors A2R337 and A2R338, and filter capacitor A2C153), provides a drive signal (through the blocking diode A2D80 to the opto-coupler A2U66-4. Capacitor A2C154 also filters the nominal 28 Vdc signal. Resistor A2R339 bypasses leakage current from the internal LED when the PIN_PRG_F signal transitions inactive (open). The output from A2U66-6 is held high by pull-up resistor A2R340 and the power supply POS5V. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 33 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 3) An active (high) signal turns on the opto-isolator A2U66 and pulls the output (A2U66-6) to ground (DIGGND1). The output signal at pin 6 routes to the tri-state octal buffer at A2U67-15 and outputs to the bus as signal DATA_BUS<6> at A2U67-5 when enabled by the control signal RD02062C* (refer to Subtask 24-23-34-870013-A00). 4) During BIT testing, the active (high) DIS_BIT_15V signal passes through current-limiting resistors A2R336 and A2R338, and diodes A2D79 and A2D80 before being tied to the anode (A2U664) of the opto-coupler’s internal LED. This turns on the optocoupler and pulls pin 6 to ground (DIGGND1). 5) The DIS_BIT_GND signal provides a path to ground (PWRGND), during BIT testing, for the anode (A2U66-4) of the internal LED through blocking diode A2D81 and discrete bit opto-coupler A2U56. i Test Enable Input 1) The test enable (TEST_EN*) signal allows the GCU to communicate over the RS485 test link during testing only. It also unlocks flight memory for download of test or flight software. 2) The active (low) ground/open discrete signal TEST_EN* input connects to the cathodes of the opto-coupler A2U68-2 and solidstate relay A2U69-2 internal LEDs. The anodes (A2U68-1 and A2U69-1) receive 15 Vdc voltage from the PWR15V supply voltage. Resistors A2R381 and A2R384 bypass leakage current from the internal LEDs when the test enable (TEST_EN*) signal transitions inactive (open). Transition of the TEST_EN* holds opto-coupler A2U68 and solid-state relay A2U69 in the OFF state. 3) When the TEST_EN* signal is driven active (connected to ground), the cathode (A2U69-2) of the optically-coupled solidstate relay A2U69 is pulled low through resistor A2R385. This turns on the internal LED, closes the relay, and connects TEST_EN_RTN to digital ground (DIGGND1), through a low-pass T-filter consisting of resistors A2R386 and A2R387, and capacitor A2C173. 4) The active (low) TEST_EN* signal also pulls the cathode (A2U682) of the opto-coupler A2U68 to ground. This turns on the optocoupler’s internal LED that causes the output (A2U68-7) to transition low as an inactive (low) LFM (Locked Flight Memory) signal. The signal at A2U68-7 also routes to the octal tri-state buffer A2U70-15 where it outputs (pin 5) to the data bus (DATA_BUS<6>) when enabled by the control signal RD020624* (refer to Subtask 24-23-34-870-013-A00). 5) When the TEST_EN* signal is inactive (open), the output at A2U68-7 is pulled high by resistor A2R383 and the POS5V supply voltage, driving the LFM signal active, and locking the flight memory. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 34 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 j Fault Timer OR (FTOR) Monitor Input 1) The fault timer OR monitor (FTOR_ON*) signal mirrors the fault timer OR discrete (FTOR*) signal, and marks the beginning and end of the various protective fault time delays. This function is used only during shop testing of the GCU. 2) The active (low) FTOR_ON* signal, from the discrete output section of PWB assembly A2, enters the octal tri-state buffer at input A2U70-17 and exits to the bus DATA<7> at A2U70-3 when enabled by the control signal RD020624* (refer to Subtask 24-2334-870-013-A00). (c) Miscellaneous Discrete Inputs 1 Discrete inputs (DISC_SW, FIRE_SW, and S2_IN) are provided to the GCU. The auxiliary contactor input, BTC_LK, is provided all GCUs. The RD020620 output from the I/O port enables the tri-state buffer A2U73 at pins 1 and 19. a IDG Disconnect Request Switch Input 1) The disconnect request switch provides a 28V/open input signal, DISC_SW, to all GCUs and directly to the disconnect solenoid in the IDG. The energized disconnect solenoid mechanically disconnects the IDG from the engine gearbox input shaft. 2) The active (high) 28V/open discrete signal input, DISC_SW, is conditioned by a low-pass filter (resistor A2R402 and filter capacitor A2C181), to provide a drive signal through blocking diode A2D107 and current-limiting resistor A2R403 to optocoupler A2U71-4. Capacitor A2C182 also filters the 28 Vdc signal. 3) An active (high) signal turns on the opto-isolator A2U71 and pulls the output (A2U71-6) to ground (DIGGND1). Resistor A2R404 bypasses leakage current from the internal LED. When the DISC_SW signal transitions inactive (open), the output A2U71-6 is held high by pull-up resistor A2R405 and the +5 Vdc power supply. The output at A2U71-6 enters to the tri-state octal buffer at A2U73-13 and exits to the bus as DATA_BUS<5> from A2U73-7 when enabled by control signal RD020620* (refer to Subtask 2423-34-870-013-A00). 4) During BIT testing, the active (high) DIS_BIT_15V signal passes through current-limiting resistors A2R401 and A2R403, and diodes A2D106 and A2D107 before being tied to the anode (A2U71-4) of the opto-coupler’s internal LED. The opto-coupler turns on and pulls pin 6 to ground (DIGGND1). 5) The DIS_BIT_GND signal provides a path to ground (PWRGND), during BIT testing, for the anode (A2U71-4) of the internal LED through blocking diode A2D108 and discrete bit opto-coupler A2U56. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 35 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 b Fire Switch Input 1) The fire switch provides a 28V/open input signal, FIRE_SW, to the GCU, which causes immediate de-excitation and trip of the appropriate generating channel in response to fire switch closure. 2) The active (high) 28V/open discrete signal input, FIRE_SW, conditioned by a low-pass filter (resistor A2R407 and filter capacitor A2C183), provides a drive signal (through the blocking diode A2D110 and the current-limiting resistor A2R408) to the opto-coupler A2U72-4. Capacitor A2C184 also filters the nominal 28 Vdc signal. 3) An active (high) signal turns on the opto-isolator A2U72 and pulls the output (A2U72-6) to ground (DIGGND1). Resistor A2R409 bypasses leakage current from the internal LED. When the FIRE_SW signal transitions inactive (open), the output at A2U726 is held high by pull-up resistor A2R410 and the +5 Vdc power supply POS5V. The output at A2U72-6 enters the tri-state octal buffer at A2U73-15 and exits to the bus as signal DATA_BUS<6> from A2U73-5 when enabled by the control signal RD020620* (refer to Subtask 24-23-34-870-013-A00). 4) During BIT testing, the active (high) DIS_BIT_15V signal passes through current-limiting resistors A2R406 and A2R408, and diodes A2D109 and A2D110 before being tied to the anode (A2U72-4) of the opto-coupler’s internal LED. The opto-coupler turns on and pulls pin 6 to ground (DIGGND1). 5) The DIS_BIT_GND signal provides a path to ground (PWRGND), during BIT testing, for the anode (A2U72-4) of the internal LED through blocking diode A2D111 and discrete bit opto-coupler A2U56. c GLC Fault 1) The GCU receives a 28-volt signal (S2_IN) from a set of normally closed auxiliary contacts in the GLC to detect a GLC control circuit fault (GLC fault) condition. 2) A low-pass filter (resistor A2R412 and filter capacitor A2C185) and a bi-directional TVS A2VR56 condition the active (high) 28V/ open discrete signal input, S2_IN. The TVS provides protection against voltage spikes. Diode A2D113 and the current-limiting resistor A2R413 provide a drive signal path to the opto-coupler A2U71-1. Capacitor A2C186 also filters the 28 Vdc signal. 3) An active (high) signal turns on the opto-isolator A2U71 and pulls the output (A2U71-7) to ground (DIGGND1). Resistor A2R414 bypasses leakage current from the internal LED when the S2_IN signal transitions inactive (open). The output A2U71-7 is held high by pull-up resistor A2R415 and the +5 Vdc power supply POS5V. The output signal at pin 7 enters the tri-state octal buffer at A2U73-17 and exits to the bus as DATA_BUS<7> from A2U73-3 when enabled by the control signal RD020620* (refer to Subtask 24-23-34-870-013-A00). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 36 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 4) During BIT testing, the active (high) DIS_BIT_15V signal passes through current-limiting resistors A2R411 and A2R413, and diodes A2D112 and A2D113 before being tied to the anode (A2U71-1) of the opto-coupler’s internal LED. This turns on the opto-coupler and pulls pin 7 to ground (DIGGND1). 5) The DIS_BIT_GND signal provides a path to ground (PWRGND), during BIT testing, for the anode (A2U71-1) of the internal LED through blocking diode A2D114 and discrete bit opto-coupler A2U56. d Galley Shed Monitor Input 1) The galley shed monitor (GLY_SHED_ON) signal mirrors the galley shed discrete output signal GLY_SHD_2A*, and indicates that the generating channel has exceeded its rated load capability. 2) The active (high) signal GLY_SHED_ON, from the discrete output section of PWB assembly A2, enters to the octal tri-state buffer at A2U73-8 and exits to the bus as DATA<0> from A2U73-12 when enabled by the control signal RD020620* (refer to Subtask 24-2334-870-013-A00). e DG Disconnect Lamp Monitor Input 1) The IDG disconnect lamp monitor (DISC_LMP_ON*) signal mirrors the IDG disconnect discrete output DISC_LAMP*. Signal DISC_LMP_ON* indicates the IDG disconnect switch has tripped the GCR and supplied power to the IDG disconnect solenoid. The solenoid mechanically disconnects the IDG from the engine gearbox. 2) The active (low) signal DISC_LMP_ON*, from the discrete output section of PWB assembly A2, enters to the octal tri-state buffer at A2U73-6 and exits to the data bus line as signal DATA<1> from A2U73-14 when enabled by the control signal RD020620* (refer to Subtask 24-23-34-870-013-A00). f BTC Lockout Auxiliary Contactor Input 1) The BTC lockout auxiliary contact (BTC_LK) signal monitors the ability of the relay to lockout the BTC. An active signal BTC_LK indicates a lock-out condition; an inhibited BTC closure. 2) The active (high) signal BTC_LK, from the discrete output section of PWB assembly A2, enters to the octal tri-state buffer at A2U732 and exits to the bus as DATA<3> from A2U73-18 when enabled by the control signal RD020620* (refer to Subtask 24-23-34-870013-A00). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 37 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subtask 24-23-34-870-013-A00 I. Input/Output (I/O) Port (1) The PWB assembly A2 Input/Output (I/O) port circuit consists of tri-state buffers A2U12 and A2U13, dual 2-to-4 line decoder/demultiplexers A2U21 and A2U22, octal D-type flip-flops A2U14, A2U15 and A2U16, and inverting tri-state buffers A2U17 through A2U20 and A2U38. The I/O port connects to the PWB assembly A3 microprocessor through data bus (DATA_BUS<15…0>) and provides sixteen logic level inputs to the microprocessor during a read operation. Three address lines (B_ADR<4…2>), the read/write signals IO_RD1* and IO_WR1* and RESET* provide the interface logic. When RESET* is active (low) all outputs are set low. When the RESET* signal goes inactive (high), the microprocessor resumes normal operation. Sixteen logic level inputs from the microprocessor are provided to the PWB assembly A2 during a write operation. Data from the write operation is latched for later use by a read back function or stored as its compliment on the data lines. Refer to Table 5 for input/output interfacing. Table 5 Table 5 Input/Output Interface IO_RD1* IO_WR1* B_ADR_4 B_ADR_3 B_ADR_2 Chip Select Device H L H L X WR020630 A2U14, A2U15 H L L L X WR020620 A2U16 L H H H H RD02063C A2U12 L H H H L RD020638 A2U13 L H L H H RD02062C A2U67 L H L H L RD020628 A2U19, A2U20 L H L L H RD020624 A2U60, A2U70 L H L L L RD020620 A2U73, A2U77 NOTE: An “X” indicates “don’t care” condition. (a) Decoders 1 The decoder multiplexers A2U21 and A2U22 receive active (low) read and write control strobe signals (IO_WR1* and IO_RD1*) and address inputs (B_ADR_4 through B_ADR_2). Enabled by the correct decoded address signals, A2U21 and A2U22 route the read and write enable signals (RD020620*, RD020624*, RD020628*, RD02062C*, RD020638*, RD02063C*, WR020620*, and WR020630*) to the discrete and internal input/output latched interfaces (refer to Table 5). a Miscellaneous Discrete Read Input 1) When the read signal RD020620* is active (low) it enables the tristate buffer driver A2U73. The buffer driver A2U73 transfers data from the DISC_SW, FIRE_SW and S2_IN as discrete inputs, or the GLY_SHED_ON, DISC_LMP_ON* and BTC_LK as discrete output monitor signals onto the bi-directional tri-state DATA_BUS<7…0> bus lines. Data stored on the latched interfaces is provided to the PWB assembly A3 microprocessor. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 38 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2) An active (low) read signal IO_RD1* enables half of the dual twoto-four line decoder A2U22-1. An inactive read signal is held high by pull-up resistor A2R129 to ensure proper address decoding. The decoder’s select input S1 (A2U22-3), pulled low to DIGGND1 by resistor A2R130 and select input S0 (A2U22-2), is controlled by the input address signal B_ADDR_4. If both select inputs are low, the decoder outputs a low signal at the Y0 output (A2U22-4), through resistor A2R132, as an enable input for the other half of decoder A2U22-15. Resistor A2R132 provides a series impedance to allow in-circuit testing. 3) The decoder’s select inputs, S1 (A2U22-13) and S0 (A2U22-14), are controlled by the input address signals B_ADDR_2 and B_ADDR_3, respectively. If both select inputs are low, the decoder outputs a low signal at the Y0 output (A2U22-12) to tristate buffer driver A2U73 as the active (low) read signal RD020620*. b Common Discrete 1 Read Input 1) When the read signal RD02062C* is active (low), the tri-state buffer driver A2U67 is enabled. Data transfers from the BTC_CLOSED*, GND_AIR_SW*, FUEL_CUTOFF*, GCS_OFF, DISC_STS*, and PIN_PRG_D* through PIN_PRG_F discrete inputs onto the bi-directional tri-state DATA_BUS<7…0> bus lines. Data stored on the latched interfaces is then provided to the PWB assembly A3 microprocessor. 2) An active (low) read signal IO_RD1* enables half of the dual twoto-four line decoder A2U22-1. An inactive read signal is held high by pull-up resistor A2R129 to ensure proper address decoding. The decoder’s select input S1 (A2U22-3), pulled low to DIGGND1 by resistor A2R130 and select input S0 (A2U22-2), is controlled by the input address signal B_ADDR_4. If both select inputs are low, the decoder outputs a low signal at the Y0 output (A2U22-4), through resistor A2R132, as an enable input for the other half of decoder A2U22-15. Resistor A2R132 provides a series impedance for circuit testing. 3) The decoder’s select inputs, S1 (A2U22-13) and S0 (A2U22-14) are controlled by the input address signals B_ADDR_2 and B_ADDR_3, respectively. If both select inputs are high, the decoder outputs a low signal at the Y3 output (A2U22-9), to tristate buffer driver A2U67 (Common Discrete 1 Input section), as the active (low) read signal RD02062C*. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 39 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (b) Input Buffers 1 When the read signals, RD020638* and RD02063C*, are active (low) they enable the tri-state input buffers A2U12 and A2U13 to transfer data from various status signals from the PWB assembly A4 onto the bi-directional tristate DATA_BUS<7…0> bus lines. These signals are exciter field overcurrent status (EXC_OC_STS), power ready 2 on status (PR2_ON_STS), power ready 2 trip status (PR2_TR_STS*), power ready 13 status (PR13_STS), isolated power supply bit (ISOPS_BIT), SPMG status (SPMG_STS), and servo valve overcurrent (SV_OC_STS). When the read signals, RD020638* and RD02063C*, are active (low) they enable the tri-state input buffers A2U12 and A2U13 to transfer data from various monitor signals from the PWB assembly A2 onto the bi-directional tri-state DATA_BUS<7…0> bus lines. These signals are IDG warning on (IDG_WRN_ON*), underspeed on (UNDRSPD_ON*), no-break power transfer on (NBPT_ON*), and synchronize power on (SYNC_ON). Data bits stored on the latched interfaces is provided to the microprocessor of PWB assembly A3. 2 An active (low) read signal IO_RD1* enables half of the dual two-to-four line decoder A2U22-1. An inactive read signal is held high by pull-up resistor A2R129 to ensure proper address decoding. The decoder’s select input S1 (A2U22-3), pulled low to DIGGND1 by resistor A2R130 and select input S0 (A2U22-2), is controlled by the input address signal B_ADDR_4. If select input S0 is high, the decoder outputs a low signal at the Y1 output (A2U225), through resistor A2R131, as an enable input for the decoder A2U21-1. Resistor A2R131 provides a series impedance for circuit testing. 3 The decoder’s select inputs, S1 (A2U21-3) and S0 (A2U21-2), are controlled by the input address signals, B_ADDR_3 and B_ADDR_2, respectively. If both select inputs are high, the decoder outputs a low signal at the Y3 output (A2U21-7), through resistor A2R127, to tri-state buffer driver A2U12 as the active (low) read signal RD02063C*. The read signal allows data to transfer over the data bus to the microprocessor on the PWB assembly A3. 4 If select input S1 is high and input S0 is low, the decoder outputs a low signal at the Y2 output (A2U21-6), through resistor A2R128, to tri-state buffer driver A2U13 as the active (low) read signal RD020638*. Resistors A2R127 and A2R128 provide a series impedance for circuit testing. (c) Output Latches 1 Positive transitions of the write enable signals, WR020630* and WR020620*, at the D-type flip-flop (A2U14 through A2U16) CLK inputs (pin 11) enable the transfer of microprocessor inputs from the bi-directional tristate DATA_BUS<15…0> bus lines. When WR020630* and WR020620* transition low, the flip-flops latch inputs onto the bus as READBACK<15…0>. 2 The Discrete Output 3, Discrete Output 2 and Discrete Output 1 circuits use the latched inputs on A2U14. The Discrete Output 3, and ARINC 429 transmitter circuits use latched inputs on A2U15. Latched inputs on A2U15 are used by the PWB assembly A4 as Servo Valve, Hi Volt DC, Power Ready Relay and Power-Up Reset. Latched inputs on A2U16 are used by the discrete BIT and analog circuits. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 40 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 3 An active (low) write signal IO_WR1* enables half of the dual two-to-four line decoder A2U21-15, while an inactive write signal is held high by pull-up resistor A2R133 to ensure correct address decoding. Decoder select inputs S1 (A2U21-13) and S0 (A2U21-14) are controlled by the input address signals B_ADDR_3 and B_ADDR_4. 4 If both select inputs are low, the decoder outputs a low signal at the YO output (A2U21-12), through resistor A2R124, to D-type flip-flop A2U16 as the active (low) write signal WR020620*. Resistor A2R124 provides a series impedance for circuit testing. When the write signal [A2U16-11 (clock input)] transitions low, data on the data bus is latched and provided to the module. 5 If select input S1 is low and input S0 is high, the decoder outputs a low signal at the Y1 output (A2U21-11), through resistor A2R123, to D-type flipflops A2U14 and A2U15 as the active (low) write signal WR020630*. Resistor A2R123 provides a series impedance for circuit testing. When the write signal [A2U14-11 and A2U15-11 (clock input)] transitions low, data on the data bus is latched and provided to the module. 6 The RESET* signal provided to the clear (CL) inputs A2U14-1, A2U15-1, and A2U16-1, clears the contents of A2U14 through A2U16 by setting the outputs to logic low. Pull-down resistor A2R126 ensures correct reset signal operation. (d) Fail-safe Buffers 1 Fail-safe buffers (A2U17, A2U18, and A2U38) provide fail-safe protection by active fail-safe signal FAILSAFE1. The FAILSAFE1 input comes from PWB assembly A3 microprocessor. Latched outputs on A2U14, through inverting buffer A2U17, are sent to the Discrete Output 3, Discrete Output 2 and Discrete Output 1 circuits on the PWB assembly A2. Latched outputs on A2U15, through inverting buffer A2U18, are sent to the Discrete Output 3, and ARINC 429 circuits on the PWB assembly A2. Latched outputs (Servo Valve, Hi Volt DC, Power Ready Relay and Power-Up Reset) on A2U15 are sent to PWB assembly A4. Latched outputs on A2U16, routed to inverting buffer A2U38, are sent to the Analog 3 and Discrete BIT Support circuits. 2 The inverted tri-state buffers (A2U17, A2U18, and A2U38) are disabled by an active (high) FAILSAFE1 signal. The FAILSAFE1 signal is held high by pull-up resistor A2R121 to ensure correct operation. The latched data (READBACK<14...0>) is buffered and inverted by A2U17 and A2U18. The inverted outputs are sent out as discrete command signals and BIT stimulus commands. The signal READBACK<15> is sent directly to the PWB assembly A4 as the BIT stimulus PUR_STIM. Latched data on DATA_BUS<7...0> is buffered and inverted by A2U38 before it is sent out as analog control and discrete BIT support signals. (e) Readback Buffers 1 When read signal RD020628* is active (low), it enables the inverting tristate readback buffer drivers A2U19 and A2U20 to transfer and invert data from the READBACK<15…0> bus onto the bi-directional tri-state DATA_BUS<15…0> bus lines. Data stored on the latched interfaces for the PWB assembly A3 microprocessor verify the integrity of the data bus communication between the PWB assembly A2 and the other PWBs. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 41 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 When read signal RD020628* is active (low), it enables the inverting tristate buffer drivers A2U19 and A2U20 to transfer data from the READBACK<15...0> data bus onto the bi-directional tri-state DATA_BUS<7…0> bus lines. This data is then provided to the PWB assembly A3 microprocessor. 3 An active (low) read signal IO_RD1* enables half of the dual two-to-four line decoder A2U22-1, while an inactive read signal is held high by pull-up resistor A2R129 to ensure correct address decoding. The decoder’s select input S1 (A2U22-3), pulled low to DIGGND1 by resistor A2R130, and select input S0 (A2U22-2) are controlled by the input address signal B_ADDR_4. If both select inputs are low, the decoder outputs a low signal at the Y0 output (A2U22-4), through resistor A2R132, as an enable input for the other half of decoder A2U22-15. Resistor A2R132 provides a series impedance for circuit testing. 4 The decoder’s select inputs, S1 (A2U22-13) and S0 (A2U22-14), are controlled by the input address signals B_ADDR_2 and B_ADDR_3. If select input S1 is low and input S0 is high, the decoder A2U22 outputs a low signal at the Y1 output (A2U22-11), through resistor A2R125, to inverting tristate buffer drivers A2U19 and A2U20 as the active (low) read signal RD020628*. The read signal allows data to transfer over the data bus to the microprocessor on the PWB assembly A3. Resistor A2R125 provides a series impedance for circuit testing. Subtask 24-23-34-870-014-A00 J. Discrete Outputs (1) The PWB assembly A2 outputs six discrete signals, with one of the outputs configured as a 28V/OPEN signal and five outputs are configured as GROUND/ OPEN signals. (2) The PWB assembly A2 also outputs BIT stimulus and enable signals to the exciter field and servo valve interfaces on the power supply/voltage regulator PWB assembly A4. The voltage monitor circuits on the PWB assembly A4 use these outputs. Driver command signals are also sent from PWB assembly A2 to power ready relay and GCR circuits on the PWB assembly A4. Monitor signals are sent to the discrete input section of the PWB assembly A2. (3) The 28V/OPEN signal outputs a nominal 28 Vdc, fed back to the GCU, through the switch and relay contacts to provide status information. (4) The GROUND/OPEN signal provides a power ground (PWRGND) output, fed back to the GCU, through the switch and relay contacts to provide status information. (5) The PWB assembly A2 sends the following analog and discrete outputs (refer to Table 6): Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 42 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 6 Table 6 Analog and Discrete Outputs Signal Name (GCU Output) Schematic Block Signal Type Current Level (Adc) Voltage Level (Vdc) Nom Max Nom Max N_BTC_LKOUT* DISCRETE_OUT_3 GROUND/OPEN 0.65 mA 1.50 mA 28.5 Vdc 32.0 Vdc FTOR* DISCRETE_OUT_3 GROUND/OPEN 5.0 mA 28.5 Vdc 32.0 Vdc GLY_SHD_2A* DISCRETE_OUT_3 GROUND/OPEN 70.0 mA 100.0 mA 28.5 Vdc 32.0 Vdc IDG_WRN* DISCRETE_OUT_2 GROUND/OPEN 30.0 mA 100.0 mA 28.5 Vdc 32.0 Vdc 20.0 mA UNDERSPEED* DISCRETE_OUT_1 GROUND/OPEN 40.0 mA 100.0 mA 28.5 Vdc 32.0 Vdc SYNC_D1 DISCRETE_OUT_1 28V/OPEN 30.0 mA 100.0 mA 28.5 Vdc 32.0 Vdc (a) Discrete Output 1 1 The discrete output SYNC_D1 is provided to the generator control switch FAULT lamp relay by the GCU. The discrete output UNDERSPEED* is provided to control an aircraft relay which inhibits IDG disconnect action when IDG speed is below the underspeed set point of the GCU. The monitor and status outputs UNDRSPD_ON*, SYNC_ON* and SYNC_FLT* are sent to the I/O port section of the PWB assembly A2. 2 The active (low) ground/open discrete output signal UNDERSPEED* enables the manual IDG disconnect function when the IDG input speed exceed the underspeed threshold. Underspeed is detected when the SAM 146 engine IDG input speed is below 4450 rpm. The disconnect function is disabled when the IDG input speed falls below the threshold. 3 A logic low signal UNDRSPD_CMD* applied to the cathode of opto-coupler A2U23 through resistor A2R141 causes the opto-coupler to turn on its output transistor. Approximately 9 volts is provided (through the divider network of A2R143, A2R144, and A2U23 collector-emitter junction) to the input (pin 1) of low side switch A2U76. Switch A2U25 turns on and provides a path to ground for the output UNDERSPEED*. Resistor A2R142 bypasses leakage current from the internal LED to ensure that A2U23 cannot energize unintended. 4 When A2U25 is on, approximately 28 volts is applied to the high gain optocoupler A2U24 through the current-limiting resistor A2R146. Capacitor A2C76 makes the opto-coupler less sensitive to noise from external sources which may be present on the UNDERSPEED* output. Resistor A2R145 ensures that the leakage current to switch A2U25 cannot trigger opto-coupler A2U24. The output of the opto-coupler A2U24 (UNDRSPD_ON*), low when energized, is sent to the microprocessor over the data bus interface (refer to Subtask 24-23-34-870-013-A00). Resistor A2R147 provides a pull-up for the output when the opto-coupler is off. Switch A2U25 is thermally protected against overcurrent and overtemperature conditions. 5 Diode A2D11 prevents voltage present on the UNDERSPEED* output from being sent to the 28 Vdc power supply. Capacitor A2C77 removes any high intensity radiated field(s) (HIRF) from the control circuit of the driver. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 43 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 6 When the UNDRSPD_CMD* signal is high, the opto-coupler A2U23 deenergizes and removes the drive from switch A2U25. (b) GCS FAULT Lamp Relay Drive Circuit 1 The GCU outputs the SYNC_D1 signal to a flight deck relay to power the GEN FAULT lamp. Output signal SYNC_D2 is not used in this application. 2 A logic low signal SYNC_CMD* applied to the cathode of opto-coupler A2U26 through resistor A2R148 causes the opto-coupler to turn on its output transistor. Approximately 5 volts is applied through the divider network of A2R150, A2R151, and the A2U26 collector-emitter junction to the input (pin 2) of switch A2U27. Switch A2U27 turns on and provides 27 volts to the anode of A2D12 and approximately 26.3 volts on the output SYNC_D1. 3 Resistor A2R149 bypasses leakage current from the internal LED to ensure that opto-coupler A2U26 cannot energize unintended. 4 When switch A2U27 turns on, 27 volts is also applied to high gain optocoupler A2U29 through the current-limiting resistor A2R156. Capacitor A2C79 makes the opto-coupler less sensitive to noise present on SYNC_D1 from external sources. The output SYNC_ON* of opto-coupler A2U29, low when energized, is sent to the microprocessor over the data bus interface (refer to Subtask 24-23-34-870-013-A00). Resistor A2R158 provides a pull-up for the output when the opto-coupler is off. Switch A2U27 is thermally protected against overcurrent and overtemperature conditions. 5 When the signal SYNC_CMD* is high, the opto-coupler A2U26 deenergizes which removes the drive from switch A2U27. (c) Discrete Output 2 1 The discrete output IDG_WRN* is provided to the flight deck relay IDG disconnect switch FAULT lamp by the GCUs. The monitor and status outputs NBPT_ON* and IDG_WRN_ON* are routed to the I/O port section of the PWB assembly A2. The monitor and status output DIS_LMP_ON* is routed to the miscellaneous discrete input section of the PWB assembly A2. a IDG Fault Lamp Drive Circuit 1) The active (low) ground/open discrete output signal IDG_WRN* is sent from the GCU to the flight deck IDG disconnect switch FAULT lamp drive relay. This is an indication of an IDG fault condition caused by high oil temperature or low oil pressure. 2) A logic low signal IDG_WRN_CMD* applied through resistor A2R181 to the cathode of opto-coupler A2U35, causes the optocoupler to turn on its output transistor. Approximately 5 volts through the voltage divider network of A2R182, A2R183, and A2U35 collector-emitter junction to the input (pin 1) is provided to switch A2U36. Switch A2U36 turns on and provides a path to ground for the output IDG_WRN*. Resistor A2R181 bypasses leakage current from the internal LED of opto-coupler A2U35 to ensure opto-coupler A2U35 cannot turn on. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 44 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 3) When switch A2U36 is on, approximately 28 volts is applied to the high gain opto-coupler A2U37 through the current-limiting resistor A2R185. Capacitor A2C96 makes the opto-coupler less sensitive to noise from external sources which may be present on the output IDG_WRN*. Resistor A2R184 ensures that the leakage current on switch A2U36 cannot trigger opto-coupler A2U37. The output IDG_WRN_ON* of the opto-coupler A2U37, low when energized, is sent to the microprocessor over the data bus interface (refer to Subtask 24-23-34-870-013-A00). Resistor A2R186 provides pull-up for the output when the opto-coupler is off. The low side switch A2U36 is thermally protected against overcurrent and overtemperature conditions. 4) The diode A2D21 prevents voltage present on the output IDG_WRN* from being sent to the PWR28V power supply. Capacitor A2C97 prevents any HIRF from entering the control circuit of the driver. When signal IDG_WRN_CMD* is high, the opto-coupler A2U35 turns off to remove the drive from switch A2U36. (d) Discrete Output 3 1 The discrete output signal GLY_SHD_2A* is provided to the flight deck galley control switch FAULT drive lamp relay by the GCUs. The discrete output signal fault timer OR* (FTOR*) is used only for shop test purposes by the GCUs. The discrete output signal N_BTC_LKOUT* is provided to the BTC by the GCUs. a Galley Shed Drive Circuit 1) The active (low) ground/open discrete output GLY_SHD_2A* signal is sent from the GCU to the flight deck galley control switch FAULT lamp drive relay. This input gives a local flight deck lamp warning of an IDG overload condition, which requires a galley load shed action. 2) A logic low signal GLY_SHD_CMD* applied to resistor A2R192 causes the optically coupled solid-state relay (SSR) A2U88 to turn on. The relay contacts close, and pins A2U88-4 and A2U88-6 are pulled low (PWRGND). Current flow energizes the coil of mechanical relay A2K1. Bypass diode A2D26 provides protection against arcing and voltage spikes. The poles of the relay provide an interface to the aircraft. 3) When the GLY_SHD_CMD* signal is inactive (high), SSR A2U88 turns off to remove the drive from relay A2K1. Resistor A2R192 bypasses leakage current from the internal LED of A2U88 to ensure that the SSR cannot turn on. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 45 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 4) When the coil of relay A2K1 turns off, a path exists through the normally closed contact (A2K1-3) of galley shed on (GLY_SHD_ON_STAT) status signal. Signal GLY_SHD_ON_STAT indicates the galley-shed relay is open. The 28-volt power supply current is applied to the internal LED of high gain opto-coupler A2U29. The current’s return path goes through the normally closed contact A2K1-3 of the relay. The output of opto-coupler A2U29-7, low when turned on, is sent to the microprocessor as the inactive status signal GLY_SHD_ON, over the data bus interface (refer to Subtask 24-23-34-870-013-A00). Capacitor A2C101 makes the opto-coupler A2U29 less sensitive to external noise. Pull-up resistor A2R195 provides a pull-up for the output when the opto-coupler is off. 5) When the coil of relay A2K1 is turned off, a path exists through a normally closed contact A2K1-5 of the relay for an ECMU galley not shed signal (GLY_SHD_2B*). The GLY_SHD_2B* signal goes active with a return path to ground (PWRGND). Capacitor A2C103 prevents any HIRF from entering the control circuit of the driver. 6) When the relay A2K1 turns on, the opto-coupler A2U29 turns off and its output (A2U29-7) is pulled high by resistor A2R195. The microprocessor determines a galley load shed has occurred (A2K1 contacts have pulled-in) when the signal GLY_SHD_ON goes active (high). Capacitor A2C102 prevents any HIRF from entering the control circuit of the driver. 7) The contact A2K1-6 provides a path to ground (PWRGND) for the flight deck relay signal GLY_SHD_2A*. Signal GLY_SHD_2A* turns on a galley fault lamp on the flight deck control panel. Capacitor A2C104 prevents any HIRF from entering the control circuit of the driver. b Fault Timer OR (FTOR) Drive Circuit 1) The ground/open discrete output FTOR* signal transitions active (low) at the beginning of a protective fault condition. The active (low) transition marks the beginning of a fault timer delay. The signal goes inactive when the fault condition is removed. The FTOR* signal is used only for GCU shop test purposes. 2) A logic low signal FTOR_CMD* applied through resistor A2R197 to the cathode of opto-coupler A2U39 causes the opto-coupler to turn on its output transistor. Approximately 5 volts through the voltage divider network of A2R198, A2R199, and A2U39 collector-emitter junction is applied to the input (pin 1) to switch A2U40. Switch A2U40 turns on and provides a path to ground for the FTOR* output. Resistor A2R197 bypasses leakage current from the internal LED of opto-coupler A2U39 to ensure optocoupler A2U39 cannot turn on. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 46 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 3) When switch A2U40 is on, approximately 28 volts is applied to high gain opto-coupler A2U34 through the current-limiting resistor A2R201. Capacitor A2C105 makes the opto-coupler less sensitive to noise from external sources which may be present on the FTOR* output. Resistor A2R200 ensures that the leakage current to the low side of switch A2U40 cannot trigger optocoupler A2U34. The output of the opto-coupler A2U34 (FTOR_ON*), low when energized, is sent to the microprocessor over the data bus interface (refer to Subtask 24-23-34-870-013A00). Resistor A2R202 provides a pull-up for the output when the opto-coupler is off. Switch A2U40 is thermally protected against overcurrent and overtemperature conditions. 4) Diode A2D27 prevents voltage present on the output (FTOR*) from being sent to the 28 Vdc power supply. Capacitor A2C106 prevents any HIRF from entering the control circuit of the driver. 5) When FTOR_CMD* signal is high, the opto-coupler A2U39 turns off to remove the drive from switch A2U40. c BTC Lockout Drive Circuit 1) The BTC, controlled by the ECMU, is inhibited (locked out) by the GCU in the event a fault condition. (For example, a welded GLC fault, overcurrent, or inadvertent paralleling trip (IPT) all require isolation of the generating channel from the transfer bus.) The BTC Lockout relay is a magnetically latched relay in the GCU with a BTC lockout command signal and an auxiliary contactor sense signal as outputs. 2) A logic low trip signal BTC_LK_TR* applied to resistor A2R206 causes the optically coupled SSR relay A2U42 to turn on. The relay contacts close, and pins A2U42-4 and A2U42-6 are pulled low (PWRGND). Current flow turns on the trip coil of mechanical latching relay A2K2. The bypass diode A2D29 provides protection against contact arcing and voltage spikes. The poles of the relay are used to interface to the aircraft. When the BTC_LK_TR* signal is inactive (high), the SSR A2U42 turns off to remove the drive from the trip coil of relay A2K2. Resistor A2R206 bypasses leakage current from the internal LED of SSR A2U42 to ensure it cannot turn on. 3) A logic low close signal BTC_LK_CL* applied to resistor A2R204 causes the optically coupled SSR A2U41 to turn on. The relay contacts close, and pins A2U41-4 and A2U41-6 are pulled low (PWRGND). Current flow turns on the close coil of mechanical latching relay A2K2. The bypass diode A2D28 provides protection against contact arcing and voltage spikes. When the BTC_LK_CL* signal is inactive (high), SSR A2U41 turns off to remove the drive from the close coil of relay A2K2. Resistor A2R204 bypasses leakage current from the internal LED of SSR A2U41 to ensure it cannot turn on. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 47 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 4) When the trip coil of relay A2K2 is turned off and the close coil is turned on, paths exist through the contacts A2K2-A3 and A2K2B3 for the BTC lockout command signal N_BTC_LKOUT* and an auxiliary contactor sense signal BTC_LK. These signals indicate the BTC relay is still closed. Capacitor A2C103 prevents any HIRF from entering the control circuit of the driver. 5) When the trip coil of relay A2K2 turns on and the close coil turns off, paths to ground exist through the contacts (A2K2-A1 and A2K2-B1) which are unconnected. Signal BTC_LK goes active (high) because contact A2K2-B3 is open. When contact A2K2-B3 is open, +5 Vdc passes through pull-up resistor A2R207. An active BTC_LK signal indicates a successful lockout condition has occurred (A2K2 has pulled-in) after a protective trip. The BTC lockout signal is sent to the microprocessor over the data bus interface (refer to Subtask 24-23-34-870-013-A00). When the signal N_BTC_LKOUT* goes inactive (high) because contact A2K2-A3 is open (indicating a BTC lockout), 28 Vdc passes through the bi-directional TVS A2VR32 to suppress any voltage spikes which may appear on the line. 6) When contact A2K2-B3 is open, +5 Vdc passes through pull-up resistor A2R207. An active BTC_LK signal indicates a successful lockout condition has occurred (A2K2 has pulled-in) after a protective trip. The BTC lockout signal is sent to the microprocessor over the data bus interface (refer to Subtask 2423-34-870-013-A00). When the signal N_BTC_LKOUT* goes inactive (high) because contact A2K2-A3 is open (indicating a BTC lockout), 28 Vdc passes through the bi-directional TVS A2VR32 to suppress any voltage spikes which may appear on the line. Subtask 24-23-34-870-015-A00 K. Discrete BIT Support (1) These signals provide an active stimulus to various GCU circuits at GCU self-test. Discrete BIT outputs (DIS_BIT_15V and DIS_BIT_GND) are provided to the discrete input circuits to the GCU. The discrete BIT output signal (DIS_IN_15V) is provided to the discrete input circuits. The discrete BIT input signals (BIT_15V_CNT*, BIT_GND_CNT* and DIS_15V_CNT*) are received from the I/O port’s output latch A2U16. (2) The DIS_BIT_15V circuit receives an input signal BIT_15V_CNT* from the I/O port on PWB assembly A2 (refer to Subtask 24-23-34-870-013-A00). When a logic low input signal is applied to resistor A2R262, the optically-coupled SSR A2U55 is turned on, its contacts close, and pins A2U56-4 and A2U56-6 are pulled high (PWR15V). When the signal BIT_15V_CNT* is inactive (high), SSR A2U55 turns off to remove the PWR15V signal from the DIS_BIT_15V output. Resistor A2R262 bypasses leakage current from the internal LED of SSR A2U55 to ensure it cannot turn on. (3) The DIS_BIT_GND circuit receives a BIT_GND_CNT* input signal from the input/ output port on PWB assembly A2 (refer to Subtask 24-23-34-870-013-A00). When a logic low input signal is applied to resistor A2R264, the SSR A2U56 is turned on, its contacts close, and pins 4 and 6 are pulled low (PWRGND). When the signal BIT_GND_CNT* is inactive (high), SSR A2U56 turns off to remove the PWRGND signal from the output. DIS_BIT_GND. Resistor A2R264 bypasses leakage current from the internal LED of SSR A2U56 to ensure it cannot turn on. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 48 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (4) The DIS_IN_15V circuit receives an input signal DIS_15V_CNT from the input/output port on PWB assembly A2 (refer to Subtask 24-23-34-870-013-A00). When a logic low input signal is applied to resistor A2R266, the SSR A2U57 is turned on, its contacts close, and pins A2U57-4 and A2U57-6 are pulled high (PWR15V). The PWR15V signal is sent to the discrete input circuits through the blocking diode A2D46. When the signal DIS_15V_CNT is active (high), SSR A2U57 turns off to remove the PWR15V signal from the output DIS_IN_15V. Resistor A2R266 bypasses leakage current from the internal LED of SSR A2U57 to ensure it cannot turn on. TASK 24-23-34-870-806-A 6. MICROPROCESSOR PWB ASSEMBLY A3 DETAILED CIRCUIT DESCRIPTIONS Subtask 24-23-34-870-016-A00 A. General Description (1) Refer to Figure 2003. The PWB assembly A3 provides system protection and control to manage the overall operation of the GCU. The microprocessor circuits contain an 80C186 microprocessor and provide system control and protection. The memory circuits contain Non-Volatile Memory (NVM) and a line decoder/demultiplexer. The input/output interface circuit uses analog multiplexers to provide an interface between the digital signal processor, analog-to-digital converter (ADC) and the Application Specific Integrated Circuit (ASIC). There are two connectors, A3J2 and A3J1, on the PWB assembly A3. Connector A3J1 connects PWB assembly A3 with the other boards through the interconnect PWB assembly A1. Connector A3J2 is a test connector. Connector A3J2 is used for board testing and programming the on-board programmable devices. Subtask 24-23-34-870-017-A00 B. Microprocessor (1) The 16-bit microprocessor A3U1 used is an 80C186 device with an interrupt controller, timer/counters, chip selects, and data bus control signals. The microprocessor performs system control, protection, and built-in-test (BIT) functions as defined by execution of the instructions stored within the memories of the memory interface. The processor uses the address/data bus AD<19...0> to communicate with the system and memory interfaces. (a) Resets 1 The microprocessor’s reset input, RES* (A3U1-24) is connected to the watchdog signal RESET*. When this signal is active (low), all the microprocessor outputs are tri-stated and the microprocessor is reset. 2 An active (high) RESET signal from A3U1-57 indicates the microprocessor is being reset. The output RESET is sent to the watchdog timer input A3U13-19 as the RESET_FB signal. (b) Timer Inputs and Outputs 1 The microprocessor’s timer 1 input, TMRIN1 (A3U1-21), is connected to the signals FREQ_IN_1 and PULSE_OUT through the watchdog timer’s electrically programmable logic device (EPLD) A3U13-15 and A3U13-18. The input TMR_IN1 is connected to the test connector A3J2-66. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 49 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 Signal FREQ_IN_1, whose frequency is monitored by the microprocessor’s BIT, is sent from the PMG zero-crossing circuit (PMG_ZC) on the PWB assembly A4. The signal is pulled high internally by the watchdog timer A3U13. Signal FREQ_IN_1 is divided to produce a pulse lasting one mechanical revolution of the PMG rotor. This pulse is present as the output PULSE_OUT and is sent to the input TMR_IN1. The microprocessor uses this pulse to trigger the central processing unit (CPU) clock pulses to the timer. 3 When the microprocessor’s timer 0 input, TMRIN0 (A3U1-20), is pulled active high, it triggers the timer 0 output, TMROUT0 (A3U1-22). The timer output is a 1600 Hz clock pulse is routed over the control bus CONTROL<15> to the PWB assembly A4 PMG zero-crossing circuit. The timer 0 output over bus CONTROL<15> exits the PWB assembly A3 as the BIT stimulus signal FREQ_OUT_1 and the test connector A3J2-24 as signal TMR_OUT0. 4 The timer 1 output, TMROUT1 (A3U1-23), is not used but is sent over bus CONTROL<16> to pin A3J1-77. The timer 1 output over bus CONTROL<16> exits the PWB assembly A3 as the test connector A3J2-11 as signal TMR_OUT1. (c) Interrupts 1 The maskable interrupt request lines [INT0 (A3U1-45) and INT1 (A3U1-44)] are enabled by high-level pulses. The INT0 input is received from the input/ output interface section of PWB assembly A3 as the signal COMINT (A3U21-29) or the test connector A3J2-52. The INT1 input is not used but is routed to connector A3J1-81 or the test connector A3J2-51 as the signal SPARE_INT. Signal SPARE_INT is pulled low (DIGGND1) by resistor A3R1. The interrupt acknowledge lines INTA0 (A3U1-42) and INTA1 (A3U141) are not connected. 2 The non-maskable interrupt line [NMI (A3U1-46)] is pulled inactive (low) by resistor A3R146, which is connected to DIGGND1. (d) Clock Signal 1 The microprocessor’s internal crystal oscillator is used to create a timing reference. A 40 megahertz (MHz) crystal (A3G1) is connected to a 5 Vdc power supply POS5V. The crystal is connected to the microprocessor’s X1 pin (A3U1-59). The processor internally divides the 40 MHz frequency by two to create the internal clock frequency of 20 MHz. The system receives a 20 MHz frequency, on which all device timings are based. This 20 MHz clock output comes from the processor at the CLKOUT pin (A3U1-56). Signal CLKOUT is sent over bus CONTROL<0> to the I/O Interface section of PWB assembly A3 as signal CPU_CLKOUT. The DSP clock signal is sent through resistor A3R13 as the signal DSP_CLK to the I/O Interface section of PWB assembly A3. Oscillator A3G2 provides a 12 MHz clock signal through A3R10, buffer A3U2 (pins 2 and 18), and resistor A3R24 as the signal B_EXT_CLK. Signal B_EXT_CLK goes through the resistor A3R10 and becomes the signal ASIC_CLK. Signal B_EXT_CLK is not used but is sent to pin A3J1-37. Signal ASIC_CLK is sent to the I/O Interface section of PWB assembly A3. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 50 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (e) Control Bus 1 The local bus control signals are sent over buses CONTROL<17...1> to the I/O interface and memory sections of the PWB assembly A3. These signals provide memory/peripheral control (ALE, WR*, RD* and BHE*), transceiver control (DEN*) and local bus arbitration (HOLD and HLDA). 2 The data enable output signal DEN* (A3U1-39), enables output drivers of the transceivers. Signal DEN* is active (low) during memory or I/O cycles. Signal DEN* is sent over bus CONTROL<1> to the I/O interface A3U21-3 and test connector A3J2-28. 3 The address latch enable (ALE) output A3U1-61 provides a pulse to latch the address when it is valid. Signal ALE is sent over bus CONTROL<3> to the I/O interface A3U21-2 and the test connector A3J2-19. 4 The write (WR*) output A3U1-63, indicates data on the bus is to be written into a memory or I/O device. The active (low) signal WR* is sent over bus CONTROL<4> to the I/O interface A3U21-8; the memory interfaces A3U2031, A3U4-27 and A3U3-27; and the test connector A3J2-12. Signal WR* is buffered by A3U7-13 and A3U7-7, passed through resistor A3R56, and sent to PWB assembly A2 as the signal B_WR*. 5 The read (RD*) input/output A3U1-62 indicates the microprocessor is performing a memory or I/O read cycle. Signal RD* is sent over bus CONTROL<5> to the I/O interface A3U21-7; the memory interfaces A3U2025, A3U5-14, A3U4-22 and A3U3-22; and the test connector A3J2-5. Signal RD* is buffered by A3U7-4 and A3U7-16, passed through resistor A3R52, and sent to PWB assembly A2 as signal B_RD*. 6 The bus high enable (BHE*) output A3U1-64, enables the data to go to the most significant bit half of the data bus (AD15 through AD8) when it is active (low). A high level output disables data from the high byte of the data bus. A low-level output sends data onto the high byte data bus. Signal BHE* is sent over bus CONTROL<6> to the I/O interface A3U21-6 and the test connector A3J2-67. Signal BHE* is buffered by A3U8-4 and A3U8-16; passed through resistor A3R44; and sent to PWB assembly A2. 7 The hold acknowledge (HLDA) outputA3U1-51, is sent over bus CONTROL<12> to the I/O interface A3U21-34 and the test connector A3J262. The HLDA output is an active (high) response to a hold request. The hold request (HOLD) signal A3U1-50 is enabled from the I/O interface A3U21-27 or the test connector A3J2-26. 8 The microprocessor’s internal chip select logic provides memory and peripheral chip select decoding. The peripheral chip select outputs, PCS0* (A3U1-25), PCS4* (A3U1-30) and MCS0* (A3U1-38), provide control signals to the input/output interface circuits and are sent over buses CONTROL<8>, CONTROL<7> and CONTROL<17>, respectively. The upper memory chip select (UCS*) output A3U1-34, is used to access the boot memory and is sent over bus CONTROL<13>. The lower memory chip select (LCS*) output A3U1-33, is used for random access memory (RAM) and is sent over bus CONTROL<14>. 9 The bus cycle status output (S<0...2>*), signals A3U1-52 through A3U1-54, indicate which of the microprocessor data bus cycles have been initiated. The outputs are routed to the PWB assembly A3 input/output interface over buses CONTROL<9…11>. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 51 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (f) Direct Memory Access (DMA) 1 The DMA request 0 and request 1 inputs, DRQ<0…1> (A3U1-18 and A3U1-19), receive their signals from the ASIC in the I/O Interface section (A3U21-180 and A3U21-179). The DMA request logic is done internally by the ASIC. 2 One of the DRQ<0…1> signals transitions active (high) when its respective DMA Channel is ready to perform a direct memory transfer. Transfer occurs when the DMA_REQ signal from the I/O interface section of PWB assembly A3 is active (high). 3 The asynchronous ready input, ARDY (A3U1-55), is ready to inform the processor that the addressed memory space or I/O device has completed a data transfer. A rising-edge signal ARDY at pin 55 is asynchronous to the CLKOUT signal at A3U1-56 and is active (high). The ARDY signal is received from the I/O interface section (A3U21-26). The synchronous ready input, SRDY (A3U1-49) is tied low to yield control to the ARDY pin. The TEST* input/output signal at A3U1-47 is also tied low, allowing instruction execution to resume. (g) Address and Data Buses 1 The lower address/data bus lines, AD<15…0> (A3U1-1 through A3U1-8, and A3U1-10 through A3U1-17), are time multiplexed to allow the bus to work as an address bus during one time period and as a data bus during another period. As an address bus, the lines carry address information to the memory and I/O ports. As a data bus, the lines carry read/write data for memory and input/output data for I/O devices. The buses AD<15…0> outputs to I/O interface A3U21; the memory section (static memory A3U3 and A3U4, flash memory A3U5, NVM A3U20, and data bus transceiver A3U24 and A3U25); and the A3J2 test connector. 2 The upper address bus lines, A<19…16> (A3U1-65 through A3U1-68), are time multiplexed with CPU status signals. The bus A<19…16> signals sent to the A3J2 test connector and to the I/O interface A3U21 of PWB assembly A3. (h) Watchdog Timer 1 The watchdog timer is a re-triggerable monostable multivibrator (one-shot timer). The watchdog timer provides two functions: microprocessor reset signals and failed microprocessor detection. A watchdog timer failsafes the module and the LRU in the event of a microprocessor hardware or software failure. The watchdog timer trigger is an active (rising-edge) input pulse, whose duration is twelve clock cycles, which is sent from ASIC device A3U21-102 under software control once every software cycle. 2 Failure to re-trigger the watchdog timer within a window of 7.5 1.0 ms to 15 3 ms results in a pulsed reset. Under normal conditions, the watchdog timer never times out while power is applied to the GCU. If it does, either the microprocessor or watchdog timer circuit has failed. Failure to recover from a pulsed reset results in a latched reset or failsafe. 3 After a pulsed reset, if another error is detected within a certain time period, a global output disable (Failsafe) is provided to the power supply and logic sections of the PWB assembly A2, the I/O and memory sections of the PWB assembly A3, and the logic sections of the PWB assembly A4. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 52 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 4 The GCU remains in failsafe until the GCS is cycled OFF to ON or power is removed and re-applied. a Watchdog Timer Circuit 1) The watchdog timer circuit consists of oscillator A3G3; EPLD A3U13; NPN transistors A3Q1, A3Q2, A3Q3 and A3Q6; PNP transistors A3Q4 and A3Q5; and several resistors. 2) The watchdog oscillator A3G3 receives a +5 Vdc signal through pull-up resistor A3R4 at input A3G3-1. The 1.6 megahertz (MHz) square wave output at A3G3-3 is fed to the watchdog timer clock (Y0) input A3U13-11. The watchdog time base is separate from the microprocessor or ASIC system clocks. b Watchdog Inputs 1) The watchdog tri-state (WD_TRISTATE*) input A3U13-2, is normally held inactive (high) internally by the watchdog timer A3U13. When WD_TRISTATE* is active (low), all A3U13 outputs are tri-stated. 2) The Y0 input A3U13-11, is pre-scaled to a 100-kilohertz (kHz) signal and exits as the watchdog clock (WD_CLK) signal A3U1330. Signal WD_CLK provides timing logic to the I/O section of PWB assembly A3 as timer/counter 0 (TC<0>) input A3U21-73. Signal WD_CLK is sent to connector A3J1-38 as signal B_WD_CLK. Signal WD_CLK is monitored and causes the failed microprocessor-protection (Failsafe) to go active if no clock signal is sensed. 3) The overfrequency enable (OF_ENA) input A3U2-8, is held inactive (low) by a pull-down resistor A3R147. The signal OF_ENA input is buffered by tri-state buffer A3U2 and is sent to EPLD A3U13-6. When signal OF_ENA* is pulled high by an external input, the redundant PMG overfrequency detection in A3U13 is enabled. 4) The locked flight memory (LFM) input A3U13-4, is a buffered test enable for the test link serial bus. The test enable signal is received from the serial test link of PWB assembly A2. A pulsed power-up reset is issued when the LFM signal and the fetch from non-read only memory (non-ROM) input EXECERR* at A3U13-9, are both active. If the LFM signal is inactive, the signal EXECERR* is ignored and the execution of boot code from SRAM is allowed during software download. 5) The manual reset (MAN_RST*) signal A3U13-24, is held inactive (high) by a pull-up internal to A3U13. Signal MAN_RST* is received from test connector A3J2-61 and forces a power-up reset when active (low). 6) The watchdog timer reset (WD_RESET*) signal A3U13-5, is a switched input from the generator control switch (GCS) to the watchdog EPLD. An OFF to ON cycle of the GCS causes the signal WD_RESET*. An OFF to ON cycle of the GCS resets the watchdog timer if it is in shutdown mode. If the watchdog timer is not in shutdown mode, signal WD_RESET* is ignored. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 53 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 7) A software-forced shutdown (SW_SD) input A3U13-10, is driven by latch A3U9-3 and A3U9-2 outputs from the memory section of the PWB assembly A3. This latch is addressable by the microprocessor. The signal SW_SD forces the GCU into failsafe mode while under software control. 8) The simulated single event (S_EVENT) signal A3U13-36, is held inactive (high) by a pull-up internal to A3U13. The simulated test signal is received through the test connector A3J2-1. 9) The modulus select (MODSEL) for frequency input A3U13-17, comes from the connector A3J1-39. When high, the number of PMG electrical cycles per revolution is assumed to be six. When low, there is assumed to be four electrical cycles per mechanical revolution. 10) The DSP watchdog enable (DSPWD_ENA*) input A3U13-16, is normally held inactive (high) internally by the watchdog timer A3U13. When signal DSPWD_ENA* is active (low), the DSP watchdog trigger is enabled. 11) The microprocessor’s watchdog trigger (UP_WDTRG) input A3U13-8, is monitored for an active rising-edge output from the ASIC watchdog port. The internal edge detector produces a single pulse, called a re-trigger, which lasts for one clock cycle on the rising-edge of the trigger input. 12) The DSP watchdog trigger (DSP_WDTRG) input A3U13-3, is monitored for an active rising-edge output from the ASIC watchdog port. The internal edge detector produces a single pulse, called a re-trigger, which lasts for one clock cycle on the rising-edge of the trigger input. 13) The test disable (TEST_DIS*) inputs A3U13-14 and A3U13-43, is pulled inactive (high) by a pull-up internal to A3U13. An active (low) signal allows the watchdog timer to be disabled during testing. When signal TEST_DIS* is active (low), the watchdog timer cannot time out. 14) The In-System Programmable clock (ISP_SCLK) signals A3U137 and A3U13-33, are held inactive (high) by a pull-up internal to A3U13. The simulated test clock signal is received through the test connector A3J2-3. 15) The ISP enable (ISPEN*) signal A3U13-13, is held inactive (high) by a pull-up internal to A3U13. The test enable signal is received through the test connector A3J2-2. c Watchdog Outputs 1) The reset status request command (RST_SRC) output A3U1339, indicates the source of the last reset. It could be a cold reset that requires a cold start from the microprocessor or a warm reset that requires a warm restart from the microprocessor. The RST_SRC signal is sent to the memory section of the PWB assembly A3. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 54 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2) The system reset (SYS_RST) output A3U13-38, provides a hardware reset to all the digital logic in the LRU. An active (high) signal SYS_RST holds the PNP transistor A3Q4 in the OFF state. When A3Q4 is OFF, the watchdog reset (RESET*) signal stays active (low) through resistor A3R14 and DIGGND1. An active (low) signal RESET* is the ORed result of active (high) SYS_RST and active (low) power-up reset (PU_RESET*) signals. 3) An inactive (low) signal SYS_RST provides a ground path for the base of PNP transistor A3Q4 through resistors A3R17 and A3R18. Transistor A3Q4 turns on to force the signal RESET* inactive (high). 4) Signal RESET* is tied to the test connector A3J2-37, and the logic sections of PWB assembly A2 and PWB assembly A4 through connector A3J1-58. Signal RESET* is sent to the microprocessor A3U1 at its reset (RES*) input A3U1-24 and the memory and I/O interface sections of PWB assembly A3. 5) A power-up reset (PU_RESET*) input from the PWB assembly A4, enters the PWB assembly A3 at A3J1-97. A low input to PNP transistor A3Q5 causes it to turn on. Transistor A3Q4 turns off and allows signal RESET* to transition low through resistor A3R14. 6) The failsafe (F_SAFE*) output A3U13-37, is an active (low) signal to disable the GCU outputs. Signal F_SAFE* is sent to PWB assembly A2 memory section and to octal tri-state buffer A3U122. 7) Signal F_SAFE* is hardware-linked to the logic sections of PWB assemblies A2 and A4 as FAILSAFE1 and FAILSAFE2. An inactive (high) signal F_SAFE* causes NPN transistors A3Q1, A3Q2 and A3Q3 to turn on. Resistors A3R19, A3R20, and A3R21 form a base-biased voltage divider to turn on transistor A3Q2. Resistors A3R19, A3R22, and A3R23 form a base biased voltage divider to turn on transistor A3Q3. When transistors A3Q2 and A3Q3 are turned on, signals FAILSAFE1 and FAILSAFE2 are tied to DIGGND1 and held inactive (low). 8) The error status request command (ERR_SRC1) output A3U1332, is the least significant bit (LSB) cause of a pulsed (warm) reset. The ERR_SRC2 output A3U13-31, is the most significant bit (MSB) cause of a pulsed (warm) reset. If both status bits are low, the cause of the warm reset is an early re-trigger. If both status bits are high, the cause of the warm reset is a non-ROM fetch (a fetch from invalid memory). If only the least significant status bit (ERR_SRC1) is high, the cause of a warm reset is a logic high on either the OF_ENA, DSP_WDTRIG, or S_EVENT pins. If only the most significant status bit (ERR_SRC2) is high, the cause of a warm reset is a late re-trigger. 9) The pulse output (PULSEOUT) of A3U13-18, is sent to the TMRIN1 input A3U1-21. The signal is a pulse that lasts one mechanical revolution of the PMG shaft and is used by the microprocessor to determine the PMG shaft period (that is, the number of CPU clock pulses for one PMG shaft revolution). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 55 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 10) An active (low) PU_RESET* signal A3U13-20, causes the base of transistor A3Q5 to pull-up to 5 Vdc. Transistor A3Q5 turns off and allows the signal RESET* to stay active (low) through resistor A3R14 and DIGGND1. 11) The reset feedback (RESET_FB) input A3U13-19, uses an external feedback to monitor the microprocessor reset output. If the reset feedback input disagrees with the applied signal SYS_RST when the GCU goes to failsafe mode. 12) The PMG frequency (FREQ_IN_1) input A3U13-15, is a square wave signal received from the PMG zero crossing detector circuit on PWB assembly A4. The square wave signal is pulled to a + 5 Vdc active (high) peak through a pull-up internal to A3U13. (i) Input/Output Interface Buffers 1 The I/O interface buffer circuit provides buffering between the PWB assembly A3 I/O interface and memory sections and the ARINC 600 interface section of PWB assembly A5. It also provides clock pulses for use by several other sections. 2 Oscillator A3G2 produces a 12 MHz square wave at A3U2-2, which is buffered by the tri-state buffer A3U2 to create the bus external clock (B_EXT_CLK) signal A3U2-18. The signal B_EXT_CLK, passes through isolation resistor A3R24. This signal is an output from connector A3J1-37. This output is not used. 3 The synchronize mode code (SYNCMC*) signal A3U2-4, from the I/O interface A3U21 of the PWB assembly A3, is buffered by the tri-state buffer A3U2. The buffered output is the bus synchronize mode code (B_SYNCMC*) signal A3U2-16. Signal B_SYNCMC* passes through isolation resistor A3R25 to the rear connector A5P1. 4 The external chip select EXT_CS* signal A3U2-6, from the I/O interface section of PWB assembly A3, is buffered by A3U2. The buffered signal creates the bus external chip select (B_EXT_CS*) signal A3U2-14. Signal B_EXT_CS* passes through isolation resistor A3R26 as an output to the interconnect PWB assembly A1. This output is not used. 5 The data transmit/receive (DT_R*) signal A3U2-11, from the I/O interface section of PWB assembly A3, is buffered by A3U2. The buffered output creates the bus data transmit/receive (B_DT_R*) signal A3U2-9. Signal B_DT_R* passes through isolation resistor A3R27 as an output to the interconnect PWB assembly A1. This output is not used. 6 The upper write (UWR*) memory pulse signal A3U2-13, from the I/O interface section of PWB assembly A3, is buffered by A3U2. The buffered output creates the bus upper write memory (B_UWR*) pulse signal A3U2-7. Signal B_UWR* is sent to the memory section of PWB assembly A3 and the test connector A3J2-64. 7 The upper write memory enable (UWR_ENA*) signals A3U2-1 and A3U219, from the test connector A3J2-54, tri-states the buffer outputs for programming through connector A3J2. Signal UWR_ENA* is pulled active (low) by pull-down resistors A3R8 and A3R9. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 56 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (j) Serial Bus Test Link 1 The differential bus transceiver A3U14 provides a line driver/receiver for the serial bus test link. This device allows data to transfer in either direction, from or to the advanced microprocessor interface [ASIC (A3U21)]. The transceiver’s direction is controlled by the transmit enable (NRZ_ENA) signal A3U14-3. The non-return to zero (NRZ) universal asynchronous receiver/transmitter (UART) provides signals from the I/O interface section of PWB assembly A3. 2 If the signal NRZ_ENA, is active (high) and the transmit output (NRZ_TX) signal A3U14-4 is at a high level, the test link positive (TEST_LINK_POS) signal A3U14-6 goes active (high). If signal NRZ_TX is inactive (low), the test link negative (TEST_LINK_NEG) signal A3U14-7 goes inactive (high). Signals TEST_LINK_POS and TEST_LINK_NEG, connected by current bypass resistors A3R29 through A3R32, are sent to the rear connector A5P1. 3 The input A3U14-2 of the bus transceiver is pulled active (low) by pull-down resistor A3R28. If the transmit enable NRZ_ENA signal is inactive (low) and the differential between the positive and negative test link signals is less than or equal to - 0.2 Vdc then the receive NRZ_RX output A3U14-1 goes low. If signal NRZ_ENA is inactive (low) and the differential between the positive and negative test link signals is greater than or equal to + 0.2 Vdc, then the receive output NRZ_RX goes high. Signal NRZ_RX is sent to the I/ O interface section of the PWB assembly A3. Subtask 24-23-34-870-018-A00 C. Memory (1) The memory interface provides boot code, flight code, fault storage and variable storage capabilities for the microprocessor. The boot code is executed at power-up and is hardware write protected at all times. The flight code is executed after initialization is complete and can be programmed in the unit. The flight code memory is write protected during flight mode. Fault storage memory is used to store a record of all faults encountered by the system. Variable storage is used by the microprocessor for temporary information. (2) All of the memories are connected to the appropriate latched address bus lines LA<19…0>. Static random access memory (SRAM) consists of two devices that can access a word with no wait states. The upper device in each pair is connected to the data bus lines AD<15…8> and the lower device to AD<7...0>. Each device has a separate chip select. The fault storage memory is a single byte wide device mapped on the lower byte of the data bus, AD<7…0>, and uses three wait states. (a) Flash Memory 1 The flash erasable programmable read only memory (EPROM) A3U5, contains 512K x 8 bytes of segmented non-volatile memory (NVM) for storing the boot and flight codes. It cannot lose data after power is removed and provides specific microprocessor power-up instructions to initialize the system. 2 The boot code resides at the top of the memory map and fills 32K x 8 bytes of memory space. The boot segments are write disabled at the GCU level. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 57 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 3 The DSP download code fills 6K x 8 bytes per load (32K by 8 bytes allocated) of memory and resides with the flight code, which fills 448K x 8 of memory space. Both the DSP download code and the flight code are programmable at the GCU level. DSP download and flight codes are programmed over the RS485 testing serial link while executing the boot code. 4 The executable memory chip select (EMCS*) signal, pulled inactive (high) by resistor A3R33, selects the EPROM. Signal EMCS*, from the microprocessor section of PWB assembly A3, allows data to be written or read as words only. 5 The write inputs are connected to the bus upper memory write (B_UWR*) pulse signal. This signal is connected to test connector A3J2 for programming purposes. Resistor A3R34 pulls the signal B_UWR* to the inactive state. When signal B_UWR* goes inactive, test equipment can bypass the microprocessor signal WR* for programming purposes. 6 The read (RD*) inputs are connected to bus (CONTROL<5>). (b) Static Random Access Memory (SRAM) 1 The static random access memory (SRAM) devices, A3U3 and A3U4, each contain 32K x 8 bytes of RAM used for temporary data storage. RAM is volatile and any information stored is lost when the system powers down. The SRAM devices provide high speed read and write memory for the microprocessor. Data is saved for use in logic and protection calculations. Signal low-level byte chip select (LLCS*), pulled inactive (high) by resistor A3R38, is the low byte RAM chip select for the SRAM. The high-level byte chip select (HLCS*), pulled inactive (high) by resistor A3R40, is the high byte RAM chip select for the SRAM. These signals, from the I/O interface section of PWB assembly A3, allow data to be written or read as individual bytes. The write (WR*) inputs are connected to bus CONTROL<4>, and the read (RD*) inputs are connected to bus CONTROL<5>. (c) Non-Volatile Memory (NVM) 1 The fault storage memory device A3U20 contains 32K x 8 bytes of segmented non-volatile memory (NVM) which is used for storing flight status information and BIT generated fault code messages. It cannot lose data after power is removed. The low fault memory chip select (LFMCS*) signal, from the I/O interface section of PWB assembly A3, is the LFMCS* which is pulled inactive (high) by resistor A3R36. The WR* inputs are connected to bus CONTROL<4>, and the RD* inputs are connected to bus CONTROL<5>. (d) Memory Interface Buffers 1 The data bus, AD<15…0>, is buffered using tri-state octal bus transceivers A3U24 and A3U25 to create the bus lines, DATA<15…0>. These devices allow data to transfer in either direction, from or to the microprocessor. The direction is determined by the ASIC transceiver direction (DT_R*) signal A3U21-9. The transceiver enable (XCVR_ENA*) signal A3U21-13, are pulled inactive (high) by resistor A3R37. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 58 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 The microprocessor’s byte high enable (BHE*) signal from A3U1-64, read enable (RD*) from A3U1-62, and write enable (WR*) from A3U1-63 are sent over bus CONTROL<6…4>. The latched address lines LA<12…0> inputs are buffered using tri-state octal buffers A3U7 and A3U8. Enable inputs A3U7-1, A3U7-19, A3U8-1, and A3U8-19 are held active (low) by the resistor A3R39. Resistors A3R43 through A3R58 provide isolation for the buffered address lines, B_ADR_<12…0>, and the buffered byte high enable (B_BHE*), buffered read enable (B_RD*), and buffered write enable (B_WR*) signals. Address lines B_ADR_<4…2> and B_ADR_<12…7> are provided to the I/O port on PWB assembly A2. (e) Read/Write Decoder 1 The buffered address lines B_ADR_<5, 6> are fed to a dual two-to-four line decoder A3U11. The decoder is enabled by an active (low) write command (PCS4WR*) from A3U11-1 or an active (low) read command (PCS4RD*) from A3U11-15. The read/write decoder handles the read and write operations from the microprocessor to the PWB assembly A2 and PWB assembly A4 of the GCU. The signals PCS4WR* and PCS4RD* are held inactive (high) by pull-up resistors A3R41 and A3R42. 2 An active (low) signal PCS4WR* and logic low signals B_ADR_<5, 6> enable the clock inputs of the D-type flip-flops A3U9 and A3U10 to transition low and latch the flip-flop outputs. 3 An active (low) signal PCS4WR*, logic high signal B_ADR_<5>, and logic low signal B_ADR_<6> enable the output IO_WR1* from A3U11-5 to go active (low). An active output signal IO_WR1* enables devices on the PWB assembly A2 for a microprocessor write operation. Resistor A3R59 provides isolation. 4 An active (low) signal PCS4WR*, a logic low signal B_ADR_<5>, and a logic high signal B_ADR_<6> enable the output signal IO_WR2* from A3U11-6 to go active (low). Resistor A3R60 provides isolation. The signal IO_WR2* is unused by the PWB assembly A2 and PWB assembly A4. 5 An active (low) signal PCS4WR*, a logic high signal B_ADR_<5>, and a logic high signal B_ADR_<6> enable the output IO_WR3* from A3U11-7 to go active (low). Resistor A3R61 provides isolation. The signal IO_WR3* is not used by the PWB assembly A2 and PWB assembly A4. 6 An active (low) signal PCS4RD* and a logic low signal B_ADR_<5, 6> cause the output at A3U11-12 to go low, the tri-state octal buffer A3U12 is enabled and allows input signals to pass through. 7 An active (low) signal PCS4RD*, a logic high signal B_ADR_<5>, and a logic low signal B_ADR_<6> enable the output IO_RD1* from A3U11-11 to go active (low). An active output signal IO_RD1* enables devices on the PWB assembly A2 for a microprocessor read operation. Resistor A3R62 provides isolation. 8 An active (low) signal PCS4RD*, a logic low signal B_ADR_<5>, and a logic high signal B_ADR_<6> enable the output IO_RD2* from A3U11-10 to go active (low). Resistor A3R63 provides isolation. The output signal IO_RD2* signal is unused by the PWB assembly A2 and PWB assembly A4. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 59 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 9 An active (low) signal PCS4RD*, a logic high signal B_ADR_<5>, and a logic high signal B_ADR_<6> enable the output IO_RD3* from A3U11-9 to go active (low). Resistor A3R64 provides isolation. The output signal IO_RD3* is not used by the PWB assembly A2 or PWB assembly A4. (f) Input Buffers to Data Bus 1 The octal tri-state buffer A3U12 receives signals from the PWB assembly A3 before putting them on the data bus. The majority of the input signals (INPUTS<7…0>) are status lines. The signals ERR_SRC1 (INPUT<0>), RST_SRC* (INPUT<1>), F_SAFE* (INPUT<2>), and ERR_SRC2 (INPUT<3>) are sent from the watchdog section of the PWB assembly A3. The boot request signal BOOT_REQ* (INPUT<4>) and the DSP status DSP_STAT (INPUT<6>) are sent from the DSP of the PWB assembly A3. The signal LFM (INPUT<5>) is sent from the PWB assembly A2. The end of conversion (EOC*) signal (INPUT<7>) is sent from the twelve-bit ADC of the PWB assembly A3 I/O interface section. (g) Buffered Data Bus 1 The data bus lines (DATA<15…0>) are pulled high and buffered by resistor network A3R65. They are terminated by resistors A3R81 through A3R96 to create B_DATA<15…0>. 2 The unbuffered data lines (DATA<15…0>) are sent to D-type flip-flops A3U9 and A3U10. The data on the bus lines is latched when decoder A3U11-4 is low and is held until the next bus cycle. During the first part of the bus cycle, the clock pulse from the decoder A3U11-4 is low. The risingedge of CLK pulse latches the data and saves it in flip-flops A3U9 and A3U10. The previous contents of the flip-flops are overwritten. 3 The bus lines DATA<4…0> (A3U9-14, 13, 8, 17 and 18) are latched and output as the remote terminal address lines RTADR<4…0> (A3U9-15, 12, 9, 16 and 19), to the PWB assembly A3 I/O interface section. The data line DATA<5> from A3U9-4, is latched and sent as the remote terminal parity bit (RTPAR) from A3U9-5, to the PWB assembly A3 I/O interface section. The data line DATA<6> from A3U9-3, is latched and output as the software shutdown signal SW_SD from A3U9-2, to the PWB assembly A3 I/O interface section. The data line DATA<7> from A3U9-7, is latched and output as the reference selector REF_SEL from A3U9-6, to the PWB assembly A3 I/O interface section. The data line DATA<8> from A3U10-18, is latched and output as the DSP interrupt bit DSP_INT* from A3U10-19, to the PWB assembly A3 I/O interface section. The data lines DATA<15…9> are inputs to the D-type flip-flop A3U10, but have no connections on the output side. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 60 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subtask 24-23-34-870-019-A00 D. Input/Output (I/O) Interface (1) The input/output interface circuits use two 16-channel analog multiplexers to provide an interface between the DSP, the 12-bit ADC and the ASIC. (a) Application Specific Integrated Circuit (ASIC) 1 The ASIC A3U21 is a custom I/O peripheral interface device that provides logic and various support functions for the microprocessor system. Internal support functions include a non-return-to-zero (NRZ) format UART, an interLRU (1553) serial link, EIA 485 (RS485) communications, ARINC 429 UART, programmable high speed analog data acquisition, 80186 watchdog functions, four programmable timer/counters, phase sequence detection, DSP interface port logic, 80186 memory chip select and address latching, and discrete peripheral I/O support. a 80186 Address Latching 1) The ASIC A3U21 provides a 20-bit output data latch that demultiplexes the lower address/data bus (AD<15…0>), the upper address bus (A<16>, A<17>, A<18> and A<19>) and the bus high enable (BHE*) signals. These signals are outputs from ASIC A3U21 as the latched address bus LA<19…0>. b 80186 Memory Chip Select 1) The ASIC supports the boot/execution, fault and scratchpad RAM memory segments and one large block I/O segment, either directly or indirectly. 2) Boot/execution memory, on the flash EPROM device A3U5, is accessed by EMCS* from A3U21-22. The ASIC provides ample logic for high/low byte access and a hardware write lockout (UWR*) signal from A3U21-10 on the upper 32K of its memory. The boot/execution memory is mapped into address space by internal ASIC register EMCS. 3) The fault memory, on the fault storage memory device A3U20, is accessed by the ASIC-generated signal LFMCS* from A3U21-21. The fault memory is mapped into address space by internal ASIC register FMCS. Signal LFMCS* also controls the number of wait states to be used. During power-up, signal LFMCS* is disabled until the register is written. 4) The scratchpad RAM is mapped into the SRAM devices A3U3 and A3U4 by the ASIC-generated signals HLCS* from A3U21-18 and LLCS* from A3U21-19. The scratchpad RAM memory is mapped into address space by internal ASIC register LCS. 5) The block chip select (BLKCS*) is an ASIC-generated signal from A3U21-25. Signal BLKCS* is not connected externally. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 61 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 c ARINC 429 UART 1) The ARINC 429 UART circuit embodies one isolated transmit channel and one isolated receive channel which are capable of low [12.5 kilo bits per second (kbps)] and high (100 kbps) bit rate operation. The A429CONT register provides overall control of ARINC communication functions. 2) The ARINC 429 UART is capable of receiving and transmitting data to the registers A429MSW (most significant word) and A429LSW (least significant word). The single level buffered ARINC 429 UART loses any data not read before another word is received. The RX word received bit (A429_RXA) from A3U21-63 or A429_RXA_L from A3U21-64 of the A429CONT register is cleared upon reading the A429MSW register. 3) ARINC transmission is started when a word is written into the A429MSW register. An active (high) TX ready bit (A429_TXA) from A3U21-65 or A429_TXA_L from A3U21-66) and an active (high) ARINC 429 enable bit allows the data to be transmitted to external line drivers and receivers. An inactive (low) ARINC 429 enable bit allows the data to be read to the A429MSW register. d Non-Return-to-Zero (NRZ) Format UART 1) The NRZ UART is capable of receiving and transmitting byte length data to the NRZDATA register. The single level buffered NRZ UART loses any data not read before another word is received. The RX byte received bit (NRZ_RX) from A3U21-69, of the NRZCONT register is cleared upon reading the NRZDATA register. 2) Transmission is started when a word is written into the NRZDATA register. An active (high) TX ready bit (NRZ_TX) from A3U2167and transmit enable signal (NRZ_ENA) from A3U21-68 allows the data to be transmitted onto the serial test link. An inactive (low) signal NRZ_ENA allows the voltage differential on the serial test link to be applied to the NRZ_RX of A3U21-69. 3) The NRZ UART transmits and receives at a programmable baud rate of 9600 bits per second (bps) or 19200 bps. Words are transmitted least significant bit (LSB) first. The data words are eleven bits long [eight bits plus one start bit (logic low), one stop bit (logic high) and one parity bit]. e Timers/Counters 1) The ASIC has four programmable timer/counters that are labeled TC<3…0>. In timer mode, the inputs time the interval between the consecutive rising-edges of a signal. In counter mode, the inputs count a signal’s rising-edges for a programmable interval. 2) The timer/counters are controlled by the read and write registers TMCCONT3 through TMCCONT0. A write signal to the register starts timer/counter operation or reset a running timer/counter. The results are accessed through the read only registers, TMCRES3 through TMCRES0. The TMCOVFL register contains data bits to indicate a timer/counter overflow. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 62 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 3) The timer/counter 3 (TC<3>) signal from A3U21-70, is pulled high internally by the ASIC and is connected to the test connector A3J2-4 as frequency reference unit test (TEST_FRU) signal. The timer/counter 2 (TC<2>) signal from A3U21-71, is not used but is connected to connector A3J1-18. The timer/counter 1 (TC<1>) signal from A3U21-72, is sent from PWB assembly A2 as the FREQ_IN_2 signal, POR_ZC. The timer/counter 0 (TC<0>) signal from A3U21-73, is sent from the PWB assembly A3 microprocessor section as the watchdog clock (WD_CLK) signal from A3U13-30. f High-Speed Data Acquisition 1) The ASIC provides high-speed analog-to-digital (A/D) data acquisition for the DSP, transmission, reception of DSP supervisory data, and five channels of PWM waveform generation. Each of the fifteen high speed A/D channels is converted within 48 software cycles of 12.0 MHz for a conversion time of 4.0 microseconds (ms) and a repetition rate of 69.4 ms. Each of the seventeen low speed A/D channels is converted within 48 system clocks of 12.0 MHz for a conversion time of 4.0 ms and a repetition rate of 2.5 milliseconds (ms). 2) All high-speed data transfers are addressable by the DSP, where the A/D data is buffered by an internal 16 x 16 RAM. All low speed data transfers are addressable by the microprocessor, where the A/D data is buffered by a 32 x 16 RAM. 3) The ASIC provides four multiplexed address MUXADR (3…0) and two bank select lines MUXCS (1…0) for support of two 16channel multiplexers. 4) Four ADC control lines, ADOE (address output enable) and ADSTB (2…0) (address strobe) are user programmable. The register ADOECONT (address control) selects the ADOE pin and defines how often the A/D channel addresses MUXCS (1…0) and MUXADR (3…0) are allowed to update. The registers ADSTBCONT(2..0) (address strobe control) selects address strobe lines ADSTB(2…0) by defining the pulse width and pulse width delay. Register ADCONT provides global control of the ADOECONT and ADSTBCONT registers and PWM generation. 5) One channel of synchronous PWM and four channels of asynchronous PWM generation are provided by the ASIC. The synchronous 12-bit saw-tooth pulse width modulator 1 (PWM_1) signal runs at four times the POR zero crossing rate (1,600 Hz) and is synchronous to the PMG frequency. The PWM_1 signal active high outputs are centered about the POR cycle’s 160 degree, 280 degree and 40 degree marks. Four asynchronous 10-bit saw-tooth PWM signals: PWM_2, PWM_3, PWM_4 and PWM_5 run at 11.72 kHz. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 63 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 6) The PWM_1 and PWM_2 duty cycles are controlled by unsigned words from the 64 x 16 dual terminal RAM. Increasing the magnitude of this word increases the duty cycle of the PWM output. The PWM_3, PWM_4 and PWM_5 duty cycles are controlled by unsigned words from the microprocessor. Increasing the magnitude of this word increases the duty cycle of the PWM output. The ADCONT register’s bits enable the PWM output patterns. 7) The microprocessor reads generated PWM waveform data through registers PWM3, PWM2, and PWM1. The microprocessor reads DSP supervisory data through the DSPREAD (digital signal processor read) register and write miscellaneous data to the DSPWRITE (DSP write) register. g DSP Interface Port Logic 1) The DSP reads data from the ASIC through the boot memory select (BMS*) from A3U21-177. During DSPBOOT (DSP boot) download, the register is addressed. The bus master request (BR*) signal from A3U21-173 and the bus master grant (BG*) signal from A3U21-170 control the handshaking to enable the DSP data bus (DSP_DATA<23…8>). h Inter-LRU Serial Link 1) Inter-LRU communications are accomplished through a dual channel MIL-STD-1553B UART which supports the inter-LRU serial bus (Manchester 1553 data bus) as both a bus controller (BC) and remote terminal (RT). Each LRU has bi-directional communications through redundant Manchester 1553 receive data buses [M1553RX (A or B)] and transmit data buses [M1553TX (A or B)]. Identical information is provided to both data buses. The control logic is not redundant. The GAPCU is the communications supervisor. 2) The serial bus does not implement all protocol requirements of MIL-STD-1553B. Terminal (RT to RT) transfers, status word busy, terminal flag and service request bits, and reset bus conditions are not used. Only transmit status word, transmit last command word, reset, transmitter shutdown and override, and synchronize without data word and dynamic bus control mode codes are used. 3) The microprocessor is put into states HOLD from A3U1-50 and HLDA from A3U1-51 during conflicts between the receive and transmit data buffers interface and the microprocessor’s RAM. 4) The remote terminal addresses (RTADR<4…0>) and odd address parity bit (RTPAR) are determined by the data bus inputs to the D-type flip-flop A3U9. 5) An external input, SUBSYS (subsystem) from A3U21-62, sets the subsystem flag bit in the status word. The signal is tied to digital ground (DIGGND1) because the subsystem flag is not used. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 64 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 i Low Speed Discrete I/O Support 1) The ASIC provides low speed discrete I/O support through a parallel data, address and control bus. The ASIC A3U21-4 receives the microprocessor output, PCS4*, from A3U1-30, to indicate I/O transfers on the low speed I/O bus. The parallel data bus consists of 16 bits of bi-directional data (B_DATA<15…0>). The address bus, B_ADR<6…0>, provides 7-bits of address. The I/O control bus consists of a PCS4*-qualified read/write line and a BHE* signal. These bus lines are buffered to isolate them from the ASIC and microprocessor buses. (b) Watchdog Support 1 The watchdog timer A3U13 receives a trigger input from the ASIC read/ write watchdog port, WDOG. A 16-bit linear feedback shift register supplies a watchdog key value to the WDOG port and the DSP watchdog. To trigger the watchdog timer, the microprocessor or the DSP reads the port and returns a 2’s complement value. The watchdog trigger pulse is twelve clock cycles long. (c) Analog Multiplexers (Fast Mux) 1 The two 16-channel analog multiplexers A3U18 (MUX2 channels 16 - 31) and A3U19 (MUX1 channels 0 - 15) are controlled by the ASIC multiplexer address bus (MUXADR<3…0>) from A3U21-113 through A3U21-116, and two multiplexer selects (MUXCS<1…0>) from A3U21-111 and A3U21-112. The multiplexers select one of 32 inputs to be present at one of the outputs (A3U18-28 or A3U19-28). 2 The information at the combined outputs is fed through resistor A3R138 to the buffer amplifier A3U27-3 and passed to the ADC A3U16-4. The selected analog input is converted to a hexadecimal value for microprocessor interpretation. a POR Sense 1) Output from the PWB assembly A2, the three phase POR ac voltage sense (POR_PHABC) signals, are sent to the PWB assembly A3 as the analog inputs: ANALOG_01H, ANALOG_02H, and ANALOG_03H. The analog inputs are passed through isolation resistors A3R128, A3R127 and A3R126 before they enter the multiplexer at A3U19-19 (IN1), A3U19-20 (IN2), A3U19-21 (IN3). b Exciter Drive BIT Monitor Sense 1) Output from the PWB assembly A4, the exciter drive BIT monitor sense (EX_FLD_POS_MON, EX_FLD_NEG_MON and EX_FLD_I_MON) signals, are sent to the PWB assembly A3 as the analog inputs: ANALOG_02L, ANALOG_04L and ANALOG_15L. The analog inputs are passed through isolation resistors A3R125, A3R121 and A3R108 before they enter the multiplexer at A3U19-23 (IN5), A3U19-10 (IN10), and A3U18-9 (IN11). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 65 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 c Line CT Sense 1) For PWB assembly A2, the ANALOG_05H signal is used for open cable sensing. 2) For PWB assembly A2, the three phase line current #2 sensing (LINE_CT_PHABC2) signals are sent to the PWB assembly A3 as the analog inputs ANALOG_06H, ANALOG_09H and ANALOG_12H. The analog inputs are passed through isolation resistors A3R118, A3R112 and A3R123 before they enter the multiplexers at A3U19-5 (IN15), A3U18-21 (IN3) and A3U19-26 (IN8). d Generator CT Sense 1) Three-phase generator current sensing (GEN_CT_PHABC) outputs from the PWB assembly A2 are sent to the PWB assembly A3 as analog inputs ANALOG_04H, ANALOG_07H, and ANALOG_10H. The analog inputs are passed through isolation resistors A3R119, A3R113 and A3R124 before they enter the multiplexers at A3U19-6 (IN14), A3U18-20 (IN2) and A3U19-25 (IN7). e Servo Valve Current Monitor Sense 1) The servo valve current monitor (SV_I_MON) output from the PWB assembly A4, is sent to the PWB assembly A3 as the analog input ANALOG_13L. The analog input is passed through isolation resistor A3R109 before it enters the multiplexer at A3U18-11 (IN9). f Oil Temperature Monitor Sense 1) The PWB assembly A2 oil temperature monitor sense outputs are sent to the PWB assembly A3 as analog inputs ANALOG_13H (OIL_TMP_IN) and ANALOG_14H (OIL OUT TEMP). The signals pass through the isolation resistors A3R106 and A3R122 before they enter the multiplexers at A3U18-5 (IN15) and A3U19-11 (IN9). g 28 Vdc Power Monitor Sense 1) The PWB assembly A4’s 28 Vdc power monitor (PWR28V_MON) output is sent to the PWB assembly A3 as analog input ANALOG_06L. The signal passes through the isolation resistor A3R120 before it enters the multiplexer at A3U19-8 (IN12). h 15 Vdc Power Monitor Sense 1) The PWB assembly A4’s 15 Vdc power monitor (PWR15V_MON) output is routed to the PWB assembly A3 as the analog input ANALOG_10L. The signal passes through the isolation resistor A3R111 before it enters the multiplexer at A3U18-24 (IN6). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 66 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 i Isolated 5 Vdc Monitor Sense 1) The PWB assembly A4’s isolated 5 Vdc monitor (ISO5V_MON) output is routed to the PWB assembly A3 as the analog input ANALOG_12L. The signal passes through the isolation resistor A3R110 before it enters the multiplexer at A3U18-26 (IN8). j Additional Mux Inputs 1) The multiplexer inputs at A3U19-22 (IN4) and A3U19-7 (IN13) are pulled to +15 Vdc through resistor A3R103. The multiplexer input A3U19-9 (IN11) is pulled to -15 Vdc through resistor A3R129. 2) The multiplexer input A3U19-24 (IN6) is pulled to -7.5 Vdc through resistor A3R130. The -7.5 Vdc signal is received from the voltage follower A3U23. The NEG15V signal voltage, divided by resistors A3R131 and A3R132, enters at A3U23-3 and exits at A3U23-1. 3) The multiplexer input A3U18-22 (IN4) is pulled to -15 Vdc through resistor A3R129 and multiplexer input A3U18-23 (IN5) is pulled to analog ground (ANAGND1) through resistor A3R115. The multiplexer input A3U18-25 (IN7) is pulled to +15 Vdc through resistor A3R103. 4) The multiplexer input A3U18-10 (IN10) is pulled to +7.5 Vdc through resistor A3R104. The +7.5 Vdc signal is received from the voltage follower A3U23. The POS15V signal voltage, divided by resistors A3R101 and A3R102, enters at A3U23-5 and exits at A3U23-7. 5) The +5 Vdc signal from A3U15, a high-precision voltage reference, enters at A3U23-10 and exits at A3U23-8. The multiplexer input A3U18-8 (IN12) is pulled to +5 Vdc through resistor A3R116. 6) The multiplexer input A3U18-7 (IN13) is pulled to -15 Vdc through resistor A3R129. (d) Voltage Reference 1 The high-precision 5 Vdc reference A3U15 and low-power, high speed analog switch A3U22 provide a voltage reference signal for the overvoltage sensing circuit on PWB assembly A2. Analog switch A3U22 and operational amplifier A3U27 (pins 2,3, and 6) control the voltage gain of the analog input to the A/D/ converter A3U16. 2 Analog switch A3U22 is controlled by the reference select (REF_SEL) IN1 and gain select (GAIN_SEL) IN2 inputs. A logic high REF_SEL input at A3U9-2 from the PWB assembly A3 memory section causes the analog switch A3U22-15 input (IN1) to go high. This closes the switch and pulls the 5 Vdc reference low to 0.652 Vdc. A logic low REF_SEL input opens the switch and returns the voltage reference to 5 Vdc. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 67 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 3 A logic high GAIN_SEL input at A3U21-5 from the PWB assembly A3 ASIC causes the analog switch A3U22-10 input (IN2) to go high. This closes the switch and pulls the inverting input of operational amplifier A3U27-2 to analog ground (ANAGND1). Operational amplifier A3U27 is changed from a fast voltage follower (low gain) configuration to a non-inverting amplifier (high gain) configuration. 4 The high-precision 5 Vdc reference A3U15-6 provide a 5 Vdc voltage to voltage follower A3U23-1and, through resistor A3R133, to switch A3U2216. When switch A3U22-15 input (IN1) goes high, output A3U22-16 is pulled to ground to drop the reference voltage to 0.652 Vdc. Voltage follower A3U23-14 and 5 Vdc reference A3U15-6 provide a +5 Vdc voltage reference (VREF) to connector A3J1-1. a Analog-to-Digital Converter (ADC) 1) The ADC A3U16 takes analog signals from the LRUs and converts them to digital signals for the ASIC. Also included are the 15 Vdc, 7.5 Vdc, + 5 Vdc and analog ground inputs from the PWB assembly A3. A total of 32 signals are sent to the ADC through the multiplexers A3U18 and A3U19. 2) The ASIC A3U21 samples individual ADC outputs individually by closing the respective channel on the multiplexers. To close a channel, the ASIC addresses and enables the various multiplexers through the multiplexer address bus lines MUXADR<3…0> (A3U21-113, -114, -115 and -116) and two multiplexer select lines MUXCS<1…0> (A3U21-111 and -112). The selected multiplexer channel sends its signal through the gain amplifier A3U27 (pins 3 and 6) to ADC voltage input 1 (VIN1) at A3U16-4. 3) The ASIC provides two programmable control lines (AD_OE* and ADSTB<0>) for ADC control. An active (low) A/D output enable (AD_OE*) signal from A3U21-118 causes signals read (RD*) at A3U16-21 and chip select (CS*) at A3U16-22 to go active (low). The result of the A/D conversion is sent to the data bus (AD_DATA<15…4>) where it is read by the ASIC. Once enabled, the start conversion (CONVST) input from A3U16-24 is pulsed by the A/D strobe 0 (ADSTB<0>) signal from A3U21-123 and the A/ D conversion begins. 4) Once the conversion is complete, the ADC transmits the analog signal in digital format over the data bus to the ASIC. The digital outputs (A3U16-8 through A3U16-13 and A3U16-15 through A3U16-20) are sent to the A/D data bus (AD_DATA<15…4>). The remaining data bus lines (AD_DATA<3…0>) are tied to digital ground (DIGGND1). 5) The end-of-conversion (EOC*) signal from A3U16-23 confirms correct voltage regulator operation. Correct voltage regulator operation is confirmed to the microprocessor through tri-state buffer A3U12-3. The EOC* signal is not used to poll the ADC. Open loop timing is used. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 68 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 6) The MODE (A3U16-7), STANDBY* (A3U16-2) and VDD (A3U161) inputs are all connected to a 5 Vdc power supply (REF5V). Three external resistors A3R140, A3R141 and A3R142 set the REF5V voltage signal. The REF5V signal output comes from the voltage regulator at A3U26-2. Diode A3D1 provides A3U26 with protection against reverse voltage during power-down. Capacitors A3C16, A3C53 and A3C54 filter the resultant voltage. 7) The VIN2 (A3U16-3), REF (A3U16-5) and AGND (A3U16-6) inputs are all connected to analog ground (ANAGND1). b Digital Signal Processor (DSP) 1) The 16-bit fixed point DSP (A3U17) is a single-chip microprocessor with three external interrupts, one output flag, and two serial ports. 2) The DSP clock input (CLKIN) from A3U17-42 receives an external 20 MHz clock signal (DSP_CLK) at A3U1-56 from the microprocessor. During normal operation, the CLKIN input cannot be halted, changed or operated below a specified frequency. The crystal (XTAL) input from A3U17-41 is not connected because an external clock is used. The clock output (CLKOUT) signal from A3U17-43 is not connected. 3) The reset (RESET*) input from A3U17-20 starts a master reset of the DSP. The reset signal to the microprocessor (A3U1-24) and ASIC (A3U21-75) must be held low during the power-up sequence. An active (low) boot memory select (BMS*) output from A3U17-39 indicates a correct boot memory interface through the middle byte of the data bus DSP_DATA<15…8>. When the reset signal is released and the chip is configured for booting, the memory map (MMAP) input at A3U17-17 is tied inactive (low) to DIGGND1 and the external bus request (BR*) input from A3U1718 transitions active (low) at the ASIC (A3U21-173), the boot loading sequence is performed. The DSP code is “booted” to the DSP from the microprocessor, through the DSP data bus and the ASIC. 4) External memory peripherals can gain control of external buses with an active (low) BR* signal and an active (low) bus grant (BG*) signal from A3U17-40. Bus grant and bus request (BG* and BR*) signals are used for handshaking during the DSP boot. a) Memory Expansion Port a1) The DSP address and data buses, and bus control signals are part of the memory expansion port set up as a master bus. The data memory (DMS*) interface is selected by an active (low) at A3U17-38. This signal results as an (HSEL*) output from the ASIC A3U21-176. Through the expansion port, the digital signal processor A3U17 is seen as a memory-mapped peripheral by the microprocessor A3U1. a2) The DSP address input signals DSPADR<7…0> provides an address location for the DSP data bus. The address inputs receive their signals from the ASIC A3U21. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 69 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 a3) The DSP data input/output (DSPDT<23…8>) signals from A3U17 allow bi-directional data transfer. The data is transferred by the ASIC A3U21, from or to the microprocessor A3U1. a4) The DSP data bus control read (RD*) pulses from A3U17-45 and write (WR*) pulses from A3U17-44, control the transfer of data from (or to) the microprocessor A3U1. The DSP read and write outputs are A3U21-175 (HRD*) and A3U21-174 (HWR*), respectively. b) Serial Ports b1) The DSP A3U17 has two synchronous serial ports (SPORT0 and SPORT1) for serial communications and multiprocessor communication. The serial port 0 multi-channel interface (SPORT<4…0>) can receive and transmit a 24 or 32 word, time-division multiplexed, serial bit stream. The SPORT<4…0> signals are interfaced to a not installed digital-to-analog converter (DAC). The DSP serial receive frame synchronization (RFS0) signal, SPORT<1>, receives an AD_OE* input from the ASIC A3U21-118. The DSP serial receiver (DR0) signal, SPORT<3>, receives a direct memory access (DMA) acknowledge (DMA_ACK) input from the ASIC A3U21-178. An active (high) DMA_ACK signal indicates a completed memory transfer. b2) Serial port 1 has two external interrupts (IRQ0* and IRQ1*) and the flag input/output (FI and FO) signals. The external IRQ0* signal, RFS1, is sent from the buffered data bus as DSP_INT* from A3U10-19. The IRQ1* signal, TFS1, is sent from the ASIC A3U21-120 as the ABSTB<1> signal. The FO (DT1) output from A3U12-15 is sent to the data bus as DSP_STAT. An active (high) indicates a software shutdown. The FI (DR1) input is tied to DIGGND1. b3) The IRQ2* signal (A3U17-19) receives a ABSTB<2> input from the ASIC A3U21-119. Subtask 24-23-34-870-020-A00 E. Test Connector A3J2 (1) Test connector A3J2 does not have a mating connector. It is used for board testing, microprocessor emulation and programming the on-board programmable memories. The test connector is also used to program EPLD A3U13 and flash EPROM A3U5. (2) Test bus JTAG<4…0> provides test data input (TDI), a test data output (TDO), a test clock (TCK), test mode select (TMS), and a controller test reset (TRST*) to the ASIC A3U21. (3) The global tri-state signal ASIC_TS* is sent from the test connector and sent to the ASIC as the signal GLBL_TS. The global tri-state pin tri-states all outputs except for the TDO. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 70 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 TASK 24-23-34-870-807-A 7. POWER SUPPLY/VOLTAGE REGULATOR PWB ASSEMBLY A4 DETAILED CIRCUIT DESCRIPTIONS Subtask 24-23-34-870-021-A00 A. General Description (1) Refer to Figure 2004. The PWB assembly A4 interfaces (through connector A4P1) with the ARINC interconnect PWB assembly A5 and connects to circuits [PMG power source, exciter field interface, servo valve interface, power ready relay and the +28 Vdc power sources (PSU28V and PSA5)]. (2) The PWB assembly A4 connects to the Interconnect PWB assembly A1, through connectors A4J1 and A1P3, and connects to the other PWBs within the GCU. PWB assembly A4 also outputs 15 Vdc (POS15V and NEG15V), +5 Vdc (POS5V), 15 Vdc power (PWR15V and PWRN15V) and 28 Vdc power (PWR28V) to power the other PWBs of the GCU. (3) The PWB assembly A4 performs the following functions: Servo Valve (SV) Coil Drive, SV Current Monitor, SV Switch Protection, Voltage Regulator (VR) Disable Protection, Shorted PMG Protection, Exciter Field Pulse-Width Modulation (PWM) Drive, Exciter Field (±) Volts Monitor, Exciter Field Current Monitor, Exciter Drive Protection, PMG Transformer Power, Hybrid Power, Power-Up Reset (PUR) DC Voltage Monitor, PMG Frequency Sensing, Power Ready Relay Control, GLC Control, GCR Relay Protection, and Built-In-Test (BIT). Subtask 24-23-34-870-022-A00 B. Servo Valve Interface (1) The servo valve in the IDG is a 28 Vdc current-controlled device with a coil resistance of 75 6 ohms at 70 °F (21 °C). The servo valve (SV) controls the IDG wobbler position, to regulate the rotor speed and output frequency of the generator. (2) The 11.72 kHz PWM input (PWM_2) signal varies its duty cycle from 0% to 100% to provide SV current regulation. (3) An active (high) SV switch enable (SVS_ENA) signal provided to the SV over-current control switch circuit indicates the SV switch is turned on. (4) An active (low) power-up reset (PU_RESET*) signal is provided to the SV overcurrent control switch circuit. The PU_RESET* signal holds the transistors A4Q2 and A4Q4 turned off and cuts off SV voltage from the drive circuit. (5) The +32 Vdc isolated power supply (ISOPS) is derived from PMG power and the transformer rectifier unit (TRU) on the PWB assembly A4. The ISOPS controls the SV drive circuit. (a) Servo Valve Current Regulation 1 The PWM input (PWM_2) from the DSP on PWB assembly A3 converts to a linear control signal and regulates the SV current within a specified range. The control current range at the servo valve coil (between the outputs SERVO_POS and SERVO_NEG) is from zero (0% duty cycle) to 100 7.5 mA (100% duty cycle). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 71 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 The SV current sense circuit measures commanded current, sensed by resistor A4R33, and not coil current. Bleed resistance causes coil current between the outputs SERVO_POS and SERVO_NEG to be lower than SV current. Bleed resistor A4R133 is in parallel with the SV coil to allow the software to discriminate between an open SV coil and a SV power supply failure. 3 The servo control signal, PWM_2, a 11.72 kHz fixed frequency with a 0% to 100% software-adjustable duty cycle, goes to Schmitt trigger inverter A4U18-5. Resistor A4R19 provides a pull-down of the pulsed waveform. On or off control is provided by the inverted square wave output from Schmitt trigger inverter A4U18-6 to the cathode (pin 2) of the internal LED of optoisolator A4U4. Opto-isolator A4U4 is a single channel logic gate with hysteresis. Resistor A4R20 provides POS5V power to the internal LED of opto-isolator A4U4. Resistor A4R21 bypasses leakage current from the internal LED to ensure opto-isolator A4U4 cannot turn on when output A4U18-6 is high. 4 The opto-isolator A4U4-7 sends a pulsed waveform (0 to 5 Vdc) to the noninverting input (pin 11) of the voltage comparator A4U5. Resistor A4R24, capacitor A4C2 and comparator A4U5 form a zero crossing detection circuit that has an output (A4U5-13) with the same frequency (11.72 kHz) as the input (A4U5-11) signal. Resistor A4R24 provides positive feedback for hysteresis and ensures a rapid output transition. Capacitor A4C2 connects across A4R24 to improve switching time. Pull-up resistor A4R25 holds the voltage follower input (A4U31-5) high so the output (A4U31-7) is also high. 5 When comparator output A4U5-13 transitions low (negative square wave pulse), it is sent to a two-pole low-pass active filter that has a corner frequency of 1.6 kHz. The active filter consists of a VCVS A4U2 and two low-pass RC circuits. The two low-pass RC circuits consist of resistors A4R26 and A4R27, feedback capacitor A4C3, and capacitor A4C4. 6 The output of the active filter A4U2-7 (voltage divided by resistors A4R28 and A4R29), low-pass filtered by RC circuit (resistor A4R28 and capacitor A4C5), provides a reference input to the VCVS A4U2-3. Capacitor A4C6 stabilizes the VCVS A4U2 negative feedback loop. Resistors A4R31 and A4R33 provide input voltage to output current conversion for the SV driver. Current-limiting resistor A4R30 ties the VCCS A4U2 to the gate of Nchannel MOSFET A4Q5. MOSFET A4Q5 controls the gate driving voltage across resistor A4R33 so it is equal to the reference voltage at A4U2-3. The voltage drop across resistor A4R33 connects to the SV current monitor circuit as the signal SVI. Maximum voltage across resistor A4R33 is 1 volt; therefore, maximum SV current is 100 mA. 7 Resistor A4R32 and capacitor A4C7 provide stability compensation for the closed-loop VCVS A4U2 drive circuit. The components provide instantaneous difference current. The components adjust the feedback voltage to meet the reference voltage. When the reference signal changes abruptly, the SV coil inductance prevents an instant change in load current. Diode A4D3 is a fly-back diode for the SV coil and provides protection against inductive feedback. The bi-directional TVS components A4VR13 and A4VR14 provide protection against chassis-referenced voltage spikes. Bleed resistor A4R133 is in place to discriminate between an open SV coil and a SV power supply fault. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 72 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (b) Servo Valve Overcurrent Protection 1 The power-up reset (PU_RESET*) signal goes to the cathode (pin 2) of the internal LED of opto-coupler A4U3. The signal PU_RESET* provides on or off control of opto-coupler A4U3. Resistor A4R8 provides POS5V power to the internal LED of opto-coupler A4U3. Resistor A4R9 bypasses leakage current from that LED to ensure that A4U3 cannot turn on when PU_RESET* is inactive (high). An active (low) PU_RESET* signal turns on the opto-coupler A4U3 to output an active (low) PUR_INHIBIT* signal to the non-inverting input (pin 12) of comparator A4U31. 2 The servo valve switch enable (SVS_ENA) signal goes to pin 3 of Schmitt trigger inverter A4U18. The resistor A4R162 provides a pull-down of the enable signal. On or off control is provided by the inverted output from A4U18-4 to the cathode (pin 3) of the internal LED of opto-coupler A4U3. Resistor A4R10 provides POS5V power to the internal LED of opto-coupler A4U3. Resistor A4R11 bypasses leakage current from that LED to ensure that A4U3 cannot turn on when output A4U18-4 is high. The output of optocoupler A4U3 (pin 6) is the servo drive enable (SV_ENABLE*) signal from A4U3-6. Pull-up resistor A4R12 forces the SV_ENABLE* output inactive (high) when SVS_ENA (A4U18-3) is inactive (low). 3 The NPN bi-polar transistor A4Q3 provides a bypass path to ISOGND for comparator A4U2-15. The trip reset (TRIP_RESET) signal is voltage divided by resistors A4R13 and A4R14 and connected to the SV_ENABLE* signal at the output of opto-isolator A4U3-6. The TRIP_RESET signal is seen as a voltage drop across resistor A4R14 and connects to the base of NPN transistor A4Q3-15. An active signal turns on transistor A4Q3 and pulls the A4U2-10 output to ground. The A4U2-16 output is forced high. The A4U31-12 input goes high and A4U31-10 output goes high. The high side of switch A4Q4 and MOSFET transistor A4Q2 turn on and deliver 32 Vdc to the SV circuit. 4 The SV_ENABLE* signal is sent through the voltage divider network resistors A4R187 and A4R186 to the base of NPN bi-polar transistor A4Q39. Transistor A4Q3 provides a bypass path to ISOGND for comparator A4U31-12 input. A low SV_ENABLE* signal bypasses the resistors A4R13 and A4R14 and turns on the MOSFET transistor A4Q2. The TRIP_RESET signal goes low and turns off NPN transistor A4Q3. 5 The ISOPS signal enters a current mirror circuit consisting of emitter control resistor network A4R1 (pins 1 and 16, and pins 2 and 15), matched bi-polar PNP transistors A4Q1 (pins 3, 4, 13 and 14, and pins 7 through 10), current-sensing resistor A4R2 and current control resistor network A4R1 (pins 3 and 14). 6 The matched bi-polar PNP transistors A4Q1 (pins 3, 4, 13 and 14, and pins 7 through 10), are biased by the 5.1 Vdc voltage drop across zener diode A4VR1, bi-polar PNP transistor A4Q1 (pins 1, 2, 15 and 16), and the resistor A4R3. The voltage drop across resistor network A4R1 pins (3 and 14) controls the amount of voltage that goes to the non-inverting input of comparator A4U2-12. The voltage drop across resistor network A4R1 (pins 4 and 13) is sent to the inverting input of A4U2-11. The two inputs are compared and, if the current to the servo drive is over 150 30 mA, comparator A4U2-15 is greater than A4U2-14, comparator A4U2-16 output goes low. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 73 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 7 Comparator A4U2-10 output is connected to a filtered voltage divider circuit to the inverting input of comparator A4U2-15. The filter, provided by the resistor A4R15 and storage capacitor A4C1, is referenced to ISOGND. The resistors A4R15 and A4R16 divide the voltage signal to A4U2-15. The noninverting input (pin 14) of comparator A4U2, tied to isolated 10 volts (ISO10V) through resistor network A4R1 (pins 6 and 11) and zener diode A4VR4, provides a 5.1 volt reference for the comparator inverting input A4U2-15. 8 An overcurrent condition (A4U2-15 is greater than A4U2-14), causes the comparator output A4U2-16 to go low. The A4U2-16 output connects, through diode A4D50, to the inverting input of comparator A4U2-11 and, through diode A4D2, to the non-inverting input of comparator A4U31-12. These diodes (latched low) force pins A4U2-11 and A4U31-12 low when A4U2-16 is low. The low signal from A4U31-12, compared to the reference voltage (2.5 Vdc) at A4U31-11, causes the output A4U31-10 to go low. The comparator output signal is fed through the voltage divider network resistors A4R183 and A4R182 to the base of NPN bi-polar transistor A4Q4. When A4U31-10 goes low, transistor A4Q4 turns off. The P-channel MOSFET A4Q2 also turns off and removes power from the servo coil. 9 An overcurrent condition causes the voltage at A4U2-16 to go low (ISOGND). This provides a path to ground from the internal cathode (A4U17-2) to turn on opto-coupler A4U17. Pin 7 of A4U17 is pulled low to signal ground (SIGGND), switched by inverter A4U18, and sent out as an active (high) overcurrent trip status (SV_OC_STS) signal. 10 If there is no overcurrent condition, the voltage at A4U2-16 goes high (the ISO10V signal ties to pin 16). This voltage is blocked by diodes A4D2 and A4D50 before being sent to the internal cathode (A4U17-2) to turn off optocoupler A4U17. The inactive pin 7 of A4U17 is held high by the POS5V signal and pull-up resistor A4R7, is switched by inverter A4U18, and is sent out as an inactive (low) overcurrent trip status SV_OC_STS signal. 11 The resistor A4R2 senses current delivered from the servo power supply and ties the ISOPS signal to the source of P-channel MOSFET transistor A4Q2. Resistors A4R2 and A4R6 tie the ISOPS input to the gate of A4Q2. Voltage divider resistors A4R6 and A4R17 and NPN transistor A4Q4 bias the voltage at gate A4Q2-1. The servo drive signal (SERVO_POS) output at the drain of P-channel MOSFET transistor A4Q2 connects the servo drive return (SERVO_NEG) at the cathode of diode A4D3. Subtask 24-23-34-870-023-A00 C. PMG Power (1) The PMG primary three-phase voltage of a nominal 104 Vac, line-line (L-L) for classic IDGs or 110 Vac, line-line (L-L) for EMM IDGs, come to the PWB assembly A4 for exciter field voltage rectification. Driven by the GCR_CMD signal, the PMG inputs are routed through the generator control relay (GCR). When the GCR_CMD signal is inactive (low), the GCR trips (opens) and disconnects the input signals. A tripped GCR causes the exciter field voltage to bypass through a resistor. The IDG is deexcited under shorted rotating diode faults. (2) A high-voltage (140 Vdc) six-diode, full-wave bridge rectifies the PMG primary threephase input power before being routed to the exciter field PWM control. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 74 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (3) The three-phase PMG inputs are diode ORed together, after the GCR, for shortedPMG (SPMG) fault detection. In the event of an open PMG phase or two PMG phases shorted together, the SPMG status (SPMG_STS) signal goes high to indicate a SPMG fault condition. (a) GCR Relay Protection 1 The three-phase PMG inputs (PMG_PHC, PMG_PHB, and PMG_PHA) are sent to the solid-state GCR A4K2. The GCR connects the PMG to the exciter field supply. An active (high) GCR command (GCR_CMD) signal is voltage divided by the resistors A4R110 and A4R111 before it is sent to the base of NPN bi-polar transistor A4Q19. Transistor A4Q19 turns on to provide a path to ground for the cathodes of diode A4D47 and the GCR control input circuit. The contacts in GCR A4K2 close and connect PMG line voltages to the six-diode high-voltage dc bridge rectifier and filter. The +5 Vdc power (POS5V) supply voltage is pulled to ground (SIGGND) through the current-limiting resistor A4R189, diode A4D47 and transistor A4Q19. 2 If the GCR_CMD signal is inactive (low), the GCR A4K2 contacts trip (open) and disconnect the PMG from the exciter field bridge rectifier. The GCR status is monitored by means of the exciter field positive [EX_FLD_(+)] voltage level. A tripped GCR causes the exciter field to bypass voltage through the diode A4D43 and resistor A4R125. Transistor A4Q19 turns off and removes the SIGGND path through diode A4D47. The +5 Vdc power supply voltage reroutes through the voltage divider network resistors A4R189 and A4R190. 3 The reduced voltage passes through diode A4D48 to the base of the bipolar NPN transistor A4Q3 to turn it on. When transistor A4Q3 turns on, it provides a path to SIGGND for the resistor A4R112 and capacitor A4C64, the voltage divider resistors A4R112 and A4R113, and the opto-isolator A4U21. The opto-isolator A4U21 contains an internal LED and a photodiode. These components provide isolation from the high dc voltage of the EXC_FLD_(+). When turned on, the LED causes the photodiode to output approximately 10 volts across resistor A4R114 to turn on N-channel MOSFET A4Q12. When MOSFET A4Q12 turns on, it causes the exciter field voltage to bypass across the current-limiting resistor A4R125 to isolation ground (ISOGND). (b) High Voltage DC Bridge and Filter 1 The three-phase PMG signals from the IDG pass through the GCR A4K2 when the relay energizes. The signals are then phase-to-phase filtered by the capacitors A4C32 through A4C34 before being full-wave rectified by the diodes A4D17 through A4D22. The rectified signal (140 Vdc with PMG voltage inputs of 104 Vac L-L) is limited to 170 Vdc by TVS A4VR7. The limited voltage is a safety against voltage generated during a shorted rotating diode (SRD) condition. Two voltage sharing resistors A4R126 and A4R127 are used across the two series-mounted storage capacitors A4C35 and A4C36 for the times when the PMG line-to-line voltage is minimal. 2 During an SRD condition, TVS A4VR7 clamps the field voltage to a nominal 170 Vdc. However, large currents (approximately 15A peak) flow until the GCR trips. After the GCR trips, the N-channel MOSFET A4Q12 turns on to provide a shorting path through the diode A4D43 bypass the back EMF energy that occurs under an SRD condition. Resistor A4R125 provides current-limiting for the shorted field. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 75 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (c) Shorted PMG Ripple Detector 1 After the three-phase PMG inputs pass through the GCR, they are diode ORed together for shorted-PMG (SPMG) fault monitoring. When two PMG phases are shorted together or an open PMG phase occurs, the ripple content of this ORed signal increases. This indicates a SPMG fault condition that results in a logic-high SPMG_STS signal. An active BIT stimulus (SPMG_STIM) signal simulates a fault condition. 2 The three PMG inputs (PMG_PHA, PMG_PHB, and PMG_PHC) pass through the GCR A4K2 and are ORed by diodes A4D16, A4D15 and A4D14. The ORed signal is voltage divided by resistors A4R115 through A4R117 and routed to the shorted PMG sense circuit. This signal is conditioned by the ripple filter components: resistors A4R163 and A4R121, capacitors A4C30 and A4C31, diode A4D11, and zener diode A4VR6. 3 If the PMG phases are all similar in amplitude, the ORed signal (mostly dc voltage) at resistor A4R163 is blocked by the coupling capacitor A4C30. Voltage comparator A4U5, which has a trip threshold of 1.43 Vdc, is prevented from tripping. The trip threshold at A4U5-9 is provided by the isolated 5 Vdc reference (ISO5V_REF) and the voltage divider resistors A4R118 and A4R119. Resistor A4R120 provides hysteresis for the comparator. Diode A4D13 blocks the opto-isolator A4U24-2 ground path through resistors A4R119 and A4R120. Opto-isolator A4U24 is turned off. The resistor A4R124 holds pin A4U24-7 high, and the output is switched by inverter A4U18 as the inactive (low) SPMG_STS signal. The SPMG_STS signal is sent to the microprocessor on the A3 PWB, through the input/ output port on the A2 PWB. 4 If a PMG phase is much greater or less than the other two phases (a phase shorted to ground or two phases are shorted to each other), then the ORed signal (mostly ac voltage) at resistor A4R163 is passed by the coupling capacitor A4C30. The ripple voltage, limited to 5.1 Vdc by the zener diode A4VR6, is rectified by the diode A4D11 and storage capacitor A4C31. If the voltage comparator A4U5-8 is greater than 1.43 Vdc, then the comparator A4U5-14 output goes low and turns on the opto-isolator A4U24. The low signal at A4U24-7 is switched by inverter A4U18 and results as a logic high signal to indicate an SPMG condition. 5 During BIT stimulus, an active (high) SPMG_STIM signal is sent through inverter A4U7 and exits as a logic-low signal. The internal LEDs cathode of opto-isolator A4U23 is pulled low to turn on A4U23. The base of PNP bipolar transistor A4Q6 is pulled low to turn on transistor A4Q6. An isolated 5 Vdc (ISO5V) signal is sent through blocking diode A4D9 to the inverting input of comparator A4U5-8. The comparator A4U5-14 output goes low and turns on opto-isolator A4U24. The low signal at A4U24-7 is inverted by A4U18 sent out as a logic high signal to simulate a SPMG condition. (d) Isolated Power Supply (ISOPS) Voltage Regulator 1 The ISOPS voltage level (21 Vdc to 30 Vdc) is derived from the ISOPS transformer-rectifier unit (TRU) diodes A4D36 through A4D41 and is dependent upon the PMG speed. A linear regulator consisting of voltage regulator A4U33, comparator A4U11, output pass-transistor A4Q11, and other discrete components, reduces the ISOPS voltage to 10 Vdc (ISO10V) and 5 Vdc (ISO5V). These voltages supply the electrically isolated components that control and monitor the EXC_FLD and SV signals. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 76 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 Voltage regulator A4U33, whose output voltage is set by the resistors A4R179 and A4R180, provides the ISO10V signal while the capacitor A4C25 provides energy storage. 3 The zener diode A4VR5 establishes a fixed 5.1 Vdc reference for the noninverting input of amplifier A4U11-12. The A4U11-12 output is routed to the base of NPN bi-polar transistor A4Q11. The amplifier output controls the transistor to maintain the ISO5V supply voltage at 5.1 Vdc 5%. The emitter of transistor A4Q11 outputs the ISO5V supply voltage. This voltage is supplied to the inverting input of amplifier A4U11-11. When A4U11-11 is less than A4U11-12, the output of A4U11-10 increases to turn on transistor A4Q11. When the voltage at A4U11-11 equals or is greater than A4U11-12, the output at A4U11-10 decreases to turn off transistor A4Q11. 4 The 5 Vdc reference A4U34 outputs a ISO5V_REF signal to provide a stable temperature reference for comparator circuits, bias circuits, and the servo valve circuit. Subtask 24-23-34-870-024-A00 D. Exciter Drive (1) The exciter field interface contains a two-wire circuit that includes the GCU source-toIDG exciter field (EXC_FLD_POS) and its return side (EXC_FLD_NEG). (2) The GCU voltage regulator uses pulse-width modulation (PWM) to control the exciter field current by modulating the exciter field coil voltage. Voltage regulator PWM is controlled by the MOSFET switch (N-channel power MOSFET and power rectifier assembly) which is located between the EXC_FLD_NEG circuit and the return side of the exciter field power source bridge rectifier, BRIDGE_RTN. An active (high) PWM_1 signal turns on the MOSFET switch. The switch is disabled by an overcurrent of greater than 7.5 A. (3) The current monitor circuit generates a signal proportional to the exciter field current (EXC_CUR), which routes to the PWB assembly A4 monitor section as the signal and to the overcurrent monitor. An overcurrent status (EXC_OC_STS) signal is routed to the PWB assembly A2 input/output section. (a) Exciter Field Pulse Width Modulation (PWM) Drive 1 The exciter field PWM drive function is implemented by the MOSFET switch A4U1 (with internal flyback diode and a current bypass resistor) and a bypass capacitor A4C13. 2 The exciter field interface includes the GCU source side to the IDG exciter field [EXC_FLD_(+)] and its return side [EXC_FLD_(-)]. These signals are sent through ferrite beads A4L1 and A4L2 for EMI filtering. The TVS diodes A4VR15 and A4VR16 provide transient protection to the EXC_FLD_POS and EXC_FLD_NEG outputs. 3 The 1,600 Hz pulse-width modulated PWM_1 signal is controlled by unsigned words from the DSP on PWB assembly A3 (refer to Subtask 2423-34-870-008-A00). The duty cycle of signal PWM_1 determines the exciter field dc load current. The maximum exciter field current is less than 4 amperes direct current (Adc). The current builds to a dc value over several cycles of MOSFET switching and maintains constant current levels until the system’s ac load changes. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 77 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 4 The twelve-bit saw-tooth PWM_1 signal, switched by Schmitt trigger inverter A4U18, and provided to the internal LED cathode (pin 3) of optocoupler A4U4. The alternating low pulses provide a path to ground for the LED to turn on opto-coupler A4U4. Alternating high pulses from A4U4-6 are provided to comparator A4U20-3. The voltage level at A4U20-3 is then compared to the 2 Vdc reference voltage (provided by resistors A4R62 and A4R63) at A4U20-2. If A4U20-3 is greater than pin 2, then comparator A4U20-1 output goes high. 5 The gate (A4U1-3) of N-channel Power MOSFET A4U1 turns on at a threshold of 3 1 Vdc. The comparator A4U20-1 output drives gate A4U13. The voltage is limited at the gate ( 16.5 Vdc) by internal bi-lateral zener diodes. 6 When the PWM_1 signal is low, the MOSFET switch A4U1 turns off and allows the internal flyback diode to maintain the inductor current from the exciter field at a minimum. The power flyback diode (pins 5 and 6) internal to A4U1 provides an inductive current feedback path. The bypass capacitor A4C13 acts as a clamp snubber and reduces EMI generated by the on/off characteristics of the flyback diode. 7 The MOSFET switch A4U1 turns on when the PWM_1 signal goes high. When MOSFET switch A4U1 turns on, current flow is removed from the flyback diode. Exciter field inductor current increases to its maximum through the BRIDGE_RTN output. The MOSFET switch A4U1 has an internal 0.1 ohm resistor. The resistor provides a proportional voltage signal for the exciter field current monitor to sense MOSFET drain current. (b) Exciter Field Current Sense 1 When the MOSFET switch A4U1 turns on, the peak voltage across its internal 0.1 ohm current sense resistor is proportional to the peak current through the exciter field load. This voltage is fed through the resistor A4R69 and sent to the non-inverting amplifier A4U20-12. A voltage gain of eight is provided by the resistors A4R68 and A4R70 and capacitor A4C14 (across resistor A4R70) filters the feedback signal. The amplified voltage is sent from A4U20-10. The peak voltage is held for A/D conversion by an ideal diode (voltage follower A4U20-5 and diode A4D7) and storage capacitor A4C17. Resistor A4R86 is a bleed resistor that provides a discharge path for A4C17. The peak voltage signal is applied to voltage follower A4U11-14 and exits at A4U11-16 as EXC_CUR for the PWB assembly A4 monitor section. (c) Exciter Drive Protection 1 Amplified voltage from A4U20-10 goes to the overcurrent sensing circuit. The MOSFET switch A4U1 is protected from overcurrent by the MOSFET gate drive disable circuit. The disable circuit consists of voltage comparators A4U20 and A4U5, NPN bi-polar transistor A4Q3, opto-isolator A4U24, and various discrete components. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 78 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 When MOSFET A4U1 drain current exceeds a peak of 7.5 amperes, the output voltage at comparator A4U20-10 is greater than 6.0 Vdc. This voltage is routed through voltage divider resistors A4R71 and A4R72. Resistors A4R71 and A4R72 reduce the input voltage to a voltage greater than 4.5 Vdc. The reduced voltage is filtered by capacitor A4C15 and sent to the inverting input of voltage comparator A4U5-4, then compared to the 4.5 Vdc reference A4U5-5. If the voltage at A4U5-4 is greater than the voltage at A4U5-5, the capacitor A4C16 discharges when comparator output A4U5-2 falls below 5.1 Vdc. The low output signal is sent to the inverting input of voltage comparator A4U5-6 and compared to the 5.1 Vdc reference A4U5-7 which causes the output (A4U5-1) to go high. This high output signal from A4U5-1 is sent through resistor A4R80 to the base of the NPN bi-polar transistor A4Q3. Transistor A4Q3 turns on and pulls the MOSFET switch A4U1 gate voltage to ground. When MOSFET switch A4U1 turns off, drain current goes to zero and causes the output voltage at A4U20-10 to drop to zero. The output at A4U5-2 goes high and charges the capacitor A4C16 to 5.1 Vdc (with the help of the power supply ISO10V, resistors A4R77, A4R178 and A4R78, and diode A4D6). These components compose the re-trigger delay to hold the MOSFET switch A4U1 turned off for a period of time before allowing it to turn on. After capacitor A4C16 reaches 5.1 Vdc, the output voltage at A4U5-1 goes low to turn off transistor A4Q3 and turn on the MOSFET switch A4U1. If the overcurrent fault condition is still present, the trip cycle repeats. If the overcurrent fault condition is gone, normal operation begins. 3 When MOSFET A4U1 gate voltage is pulled to ground, it turns off and the drain current goes to zero. When the drain current is zero, the output voltage at comparator A4U20-10 drops to zero volts. When the output voltage at A4U20-10 drops to zero volts, the output at voltage comparator A4U5-2 goes high and charges capacitor A4C16 to +5.1 Vdc in approximately 30 ms (with the help of the power supply ISO10V, resistors A4R77, A4R178 and A4R78, and diode A4D6). This is the re-trigger delay. The re-trigger delay holds MOSFET A4U1 turned off for a period of time before allowing it to turn on again. After capacitor A4C16 reaches +5.1 Vdc, the output voltage at A4U5-1 goes low which turns off transistor A4Q3 and turns on MOSFET A4U1. If the overcurrent fault condition is still present the trip cycle repeats. Of the overcurrent fault goes away, normal operation continues. 4 The active (low) power-up reset (PU_RESET*) signal disables the MOSFET switch A4U1 through the overcurrent protection circuit. When PU_RESET* is active (low), the output of opto-coupler A4U23-6 goes low to discharge the capacitor A4C16. Discharge of the capacitor simulates an overcurrent condition. When PU_RESET* is inactive, the output of optocoupler A4U23-6 goes open collector and does not affect normal operation. 5 A high, non-inverting input to voltage comparator A4U20-14 indicates an overcurrent condition. The output at A4U20-16 goes high and turns on the internal LED of opto-coupler A4U24. The output A4U24-6 is pulled to ground, switched by the Schmitt trigger inverter A4U18, and exits A4U18-8 as an active (high) exciter field overcurrent status (EXC_OC_STS) signal. When no overcurrent condition is sensed, the status signal is held inactive (low) by the pull-up resistor A4R87. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 79 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subtask 24-23-34-870-025-A00 E. PMG Power Supply (1) The GCU internal power supply section of the PWB assembly A4 is made up of the PMG power source circuit, and circuit to provide 15 Vdc, 5 Vdc, and 28 Vdc. These circuits are described below. (a) PMG Power Source 1 The PMG power source circuit provides input conditioning to the generator PMG output voltage of 104 Vac L-L (classic IDG) or 110 Vac L-L (EMM IDG) and the external 28 Vdc power supply for the generation of power supplies used throughout the GCU. 2 The PMG phase A, B, and C signals are sent to the step-down PMG transformer A4T1 from the generator’s PMG three-phase output. The secondary 1 winding output is approximately 30 Vdc after three-phase full wave bridge rectification. The secondary 2 winding output is approximately 30 Vdc after three-phase full wave rectification. The secondary 3 winding output is approximately 29 Vdc after three-phase full wave rectification. The secondary 4 winding two-phase output is approximately 5 Vrms. (b) 28 Volt Power Supply (PWR28V) TRU 1 The PWR28V supply voltage output from the PWR28V TRU (a combination of the PMG secondary #1 and the PMG secondary #2 TRUs), is diode ORed with the 28 Vdc aircraft voltage supply. The combined voltage is routed to the triple output hybrid power supply (dc-to-dc converter) A4U30 and other PWR28V loads within the GCU. 2 The PMG secondary #1 TRU is a delta configuration because of the high steady-state current demand. The maximum steady-state load current from this TRU is 2 amperes direct-current (Adc). 3 The PMG secondary #2 TRU is a wye configuration used only for start-up at low PMG voltage. The maximum steady-state load current from this TRU is 1 Adc. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 80 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 4 At low PMG frequency and voltages (input speed is less than 3500 rpm), the PMG secondary #2 TRU output is in series with the PMG secondary #1 TRU output. This effectively doubles the PWR28V output voltage level. As the PWR28V output level goes above 36 Vdc, the secondary #2 winding is switched from the series dc path by the P-channel MOSFET transistor A4Q14. The PWR28V output is sent to the secondary #1 winding through the diode A4D32. As PWR28V voltage level falls below 18 Vdc, the MOSFET transistor A4Q14 turns on and PMG secondary #2 voltage is put in dc series to supply PWR28V loads. a PMG Secondary #1 TRU 1) The reduced three-phase PMG signal (24.5 Vrms when the PMG output voltage is 110 Vrms) from the transformer A4T1 deltawound secondary #1 is three-phase full-wave bridge rectified by diodes A4D29 through A4D31 and A4D33 through A4D35. The TRU output voltage (24 Vdc to 32 Vdc when the input PMG phase voltage is between 50 to 64 Vrms) is sent to the secondary #1 TRU voltage level sense circuit as the signal TRU1 (+), through diode A4D32 as the PWR28V signal. The circuit has a maximum steady-state load current of 2 Adc. 2) The N-channel junction field-effect transistor (JFET) A4Q13 turns on at start-up while its gate voltage is at zero volts, conducting current through the resistor A4R174 and charging the capacitor A4C59 to 5.1 Vdc. The capacitor’s stored voltage is regulated by the zener diode A4VR10. This stored voltage is provided to comparator A4U26-3, the output A4U26-13 through the pull-up resistor A4R131, to the current-limit resistor A4R171, and the 1.23 Vdc zener diode A4VR11. 3) Regulated 1.23 Vdc is sent through resistor A4R172 to the noninverting input of comparator A4U26-11. The PWR28V signal is sent through the blocking diode A4D12 to the filter capacitor A4C63 and voltage divider resistors A4R128 and A4R129. The reduced signal is sent to voltage comparator A4U26-10. If the PWR28V signal at diode A4D12 is less than 17 Vdc, the comparator output transitions high. 4) A high output from the comparator A4U26 is sent through voltage divider resistors A4R132 and A4R173 to the base of NPN bi-polar transistor A4Q15. Transistor A4Q15 turns on. When A4Q15 turns on, a path is provided for power ground (PWRGND) through resistor A4R135 to the gate of P-channel MOSFET transistor A4Q14. A low gate signal turns on MOSFET transistor A4Q14 to provide secondary #2 voltage through diode A4D32 to the PWR28V output. b PMG Secondary #2 TRU 1) The reduced three-phase PMG signal (24.0 Vrms when the PMG output voltage is 110 Vrms) from the transformer A4T1 wyewound secondary #2 winding is three-phase full-wave bridge rectified by diodes A4D23 through A4D28. The TRU output voltage (24 Vdc to 32 Vdc when the input PMG phase voltage is between 50 to 64 Vrms) is sent through the diode A4D32 as a boost for the PWR28V signal from the secondary #1 TRU. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 81 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (c) Isolated Power Supply (ISOPS) TRU 1 The isolated power supply output from the ISOPS TRU (a combination of the PMG secondary #1 TRU voltage level sensing circuit and the PMG secondary #3 TRU) supplies the internal GCU power bus called ISOPS. This power bus supplies the servo valve driver and coil, the exciter field driver and other PWB assembly A4 loads. 2 The ISOPS power bus allows early start-up of the servo valve drive circuit at a PMG input speed of 2,500 rpm when PSU28V power is available. The ISOPS bus provides a minimum of 12 Vdc when the PMG has an input voltage of 26 Vrms (line to line). The maximum voltage the ISOPS TRU allows is 36 Vdc. 3 The secondary #1 TRU (TRU #1) output senses the output voltage of the secondary #3 TRU (TRU #3) because the voltage comparator A4U25 and the secondary #1 TRU are both referenced to power ground (PWRGND). Therefore the voltage of TRU #1 is directly proportional to the voltage of TRU #3. 4 When the TRU #1 output is greater than 19 Vdc, the relay A4K3 switches the TRU #3 bridge from a full-wave rectifier to a half-wave rectifier. This causes the ISOPS voltage across the capacitor A4C57 (load current at 200 mAdc) to ramp down from approximately 35 Vdc to 20 Vdc. Hysteresis by the comparator A4U25 prevents the ISOPS switching relay A4K3 from retriggering when there is a change of 1.2 Vdc at the TRU #1 output. 5 The auxiliary contacts of the ISOPS switch relay A4K3 route the POS5V signal to the indicator output, ISOPS_BIT, for relay status verification. a PMG Secondary #3 TRU 1) The reduced three-phase PMG signal (40.7 Vrms when the PMG output voltage is 110 Vrms) from the transformer A4T1 wyewound secondary #3 winding is three-phase bridge rectified by diodes A4D36 through A4D41. The full-wave or half-wave bridge configuration is controlled by the relay A4K3. The TRU #3 output voltage (steady-state dc voltage of 28 Vdc when the input PMG phase voltage is between 50 to 64 Vrms) is EMI filtered by capacitor A4C57 and becomes ISOPS output. The circuit is rated to supply a maximum steady-state load current of 250 mAdc. b PMG Secondary #1 TRU Voltage Level Sense Circuit 1) The TRU 1(+) signal from the PMG secondary #1 TRU is input through the blocking diode A4D46 and filtered by the capacitor A4C38. The TRU 1(+) signal voltage is divided by the resistors A4R142 and A4R143, and sent to the voltage comparator A4U254. The reduced signal at pin 4 is compared to the 2.5 Vdc reference voltage (PWR5V routed through voltage divider resistors A4R140 and A4R141) at A4U25-5. Hysteresis is provided to the voltage comparator by diode A4D45 and resistor A4R139. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 82 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2) If pin 4 is greater than pin 5, the output of comparator A4U25-2 goes low and turns off transistor A4Q16. When the transistor A4Q16 turns off, relay A4K3 turns off and the TRU #3 output is half wave rectified. The ISOPS voltage across capacitor A4C57 decreases from 35 Vdc to 20 Vdc. When the relay is turned off, diode A4D42 provides coil feedback protection. 3) If pin 4 is less than pin 5 [indicating the TRU 1(+) signal voltage is less than 19 Vdc], the output of comparator A4U25-2 transitions high and forward-biases the base of NPN bi-polar transistor A4Q16. The transistor A4Q16 turns on, and turns on relay A4K3 by providing a ground path from the PWR28V signal to PWRGND. This causes the TRU #3 output is be full-wave rectified, increasing the ISOPS voltage across capacitor A4C57 from 19 Vdc to 33 Vdc. (d) PMG Secondary #4 1 The PMG (+) and PMG (-) signals, output from the PMG secondary #4, provide frequency signals for the PMG frequency sense circuit on the A4 PWB. 2 The reduced three-phase PMG signal from the transformer A4T1 wyewound secondary #4 winding is a two-phase output (phases A and B). The two-phase output, used for PMG frequency sensing, provides a nominal 7.2-volt peak when the transformer’s input voltage is 110 Vrms. (e) 15-Volt (PWR15V) Power Supply 1 The PWR28V supply voltage is routed through the blocking diode A4D44, resistors A4R181 and A4R168, before it enters the linear voltage regulator A4U27-3. The 28 Vdc input is stepped-down to a 15 Vdc output referenced to PWRGND. Voltage is controlled at the regulator A4U27-1 by resistors A4R144 and A4R145. De-coupling capacitor A4C41 stabilizes the output voltage during transient conditions. Capacitor A4C28 improves transient response, while storage capacitor A4C43 filters the output supply voltage, PWR15V. 2 The regulator’s input at A4U27-3 and the PWR28V supply voltage routed through the resistor A4R154 are sent to the emitters (pins 14 and 16) of PNP bi-polar transistors A4Q6. The matched-pair transistor A4Q6 is in the current mirror configuration, which sources current to the gate of the Pchannel MOSFET transistor A4Q10. The MOSFET transistor A4Q10 is a transistor that conducts twice the current of regulator A4U27-3. (f) Negative 15-Volt (PWRN15V) Power Supply 1 The PWR15V supply voltage, routed through the switched-capacitor voltage inverter A4U29, generates a PWRN15V supply voltage (-14.3 Vavg at 25 kHz ripple voltage). Capacitors A4C56 and A4C49 hold the -15 Vdc output voltage during inverter A4U29 switching periods at a rate of 25 kHz. The NPN bi-polar transistor A4Q17 provides protection at pin 5 to prevent positive current flow. Positive current flow could latch inverter A4U29 and prevent its start-up. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 83 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (g) 5-Volt (PWR5V) Power Supply 1 The PWR15V supply voltage, through the +5 Vdc precision voltage reference A4U28, generates a PWR5V supply voltage. PWR5V is a precise, temperature-stable reference voltage for the PMG power supply comparator circuits referenced to PWRGND. The voltage reference A4U28 provides a minimum of 10 mA. (h) Triple Output Hybrid Power Supply 1 The triple output hybrid power supply (dc-to-dc converter) transforms the +28 Vdc bus voltage [PSU28V, or PMG rectified 28 Vdc power (PWR28V)] into three isolated voltages POS15V, POS5V, and NEG15V that reference SIGGND. The Inhibit circuit provides a means for disabling all dc-to-dc converter outputs when a ground signal is applied at the Inhibit input. a 28-Volt Input EMI Filter Circuit 1) The external 28 Vdc back-up power input (PSU28V), fed through diode A4D51 and ORed with the PWR28V supply voltage (PSA5), is the output from the PWR28V TRU (a combination of the PMG secondary #1 and the PMG secondary #2 TRUs). The 28 Vdc bus signal is EMI filtered by a differential-input filter of inductor A4L3 and capacitor A4C44, and limited for transient protection by TVS A4VR8. The TVS suppresses transient voltage spikes by conducting when the voltage across the line exceeds the zener avalanche rating of 40 volts. 2) The resultant voltage, fed through a common-mode input filter (inductor A4L7 and line-to-chassis ground capacitors A4C47 and A4C48), is the input for the triple-output hybrid power supply A4U30. 3) The 28 Vdc return (PSUGND) and (PSA5_RTN) circuits are EMI filtered by a differential-input filter (inductors A4L4 and A4L6 and capacitor A4C44). b Power Supply Inhibit Circuit 1) Power supply inhibit comparator A4U25 is set to enable the dc-todc converter A4U30. The dc-to-dc converter A4U30 sends a high PS_INHIBIT signal to A4U25-1 and releases the inhibit pin (A4U30-8). When the input power is not acceptable (less than 19 Vdc) the inhibit pin (A4U30-8) is active (low) and provides an undervoltage lockout by disabling the dc-to-dc converter. 2) A filtered voltage divider (resistors A4R146 and A4R151, and the capacitor A4C45) conditions the bus voltage sense signal that is fed to pin A4U25-10. The PWR5V signal is sent through resistor A4R147 as a reference voltage for comparator A4U25-11. Resistor A4R150 provides positive hysteresis. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 84 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 3) When the PSU28V signal is greater than 19 ±0.5 Vdc, pin A4U2513 goes low and provides an input to comparator A4U25-8. The ground reference at A4U25-8 is compared to the 2.5 Vdc voltage divider resistors A4R148 and A4R149 input at A4U25-9. The comparator A4U25-14 output is an active (high) through the pullup resistor A4R152 and storage capacitor A4C46. This input goes to comparator A4U25-7. Resistor A4R152 and capacitor A4C46 provide a 57 ms time delay to enable the dc-to-dc converter. The PWR15V signal at pin 7, compared to the PWR5V reference at pin 6, drives the output A4U25-1 high. Resistor A4R153 provides positive hysteresis. 4) A 2.0 Vdc hysteresis incorporated into the comparator A4U25 prevents erratic output (oscillation) as the threshold voltage is crossed. The dc-to-dc converter cannot be inhibited until the 28 Vdc bus voltage is less than 17.0 0.5 Vdc. 5) When the bus falls below 16.5 Vdc, pin A4U25-13 transitions open and sends a PWR5V signal to comparator A4U25-8. Voltage at A4U25-8 is compared to the 2.5 Vdc voltage divider resistors A4R148 and A4R149 input at A4U25-9 to pull the output at A4U25-14 low. The storage capacitor A4C46 discharges through the ground paths (A4U25-12 and A4U25-14) to drive the comparator input A4U25-7 low. The PWRGND at A4U25-7, compared to the PWR5V reference at A4U25-6, drives the output A4U25-1 low. The A4U25-1 output pulls the inhibit at A4U30-8 low. A low on pin A4U30-8 disables all three converter outputs and provides an undervoltage lockout. c Triple Output Switching DC-to-DC Converter 1) The triple-output dc-to-dc converter A4U30 is a switching regulator that uses continuous flyback conversion with a clock frequency of approximately 600 kHz. The dc-to-dc converter provides a maximum of 15 watts output power divided among three outputs (POS5V, POS15V, or NEG15V). The POS15V and NEG15V outputs are rated for five watts at a total current of 0.167 Adc. The POS5V output is rated for ten watts at a maximum current of 2.0 Adc. 2) The 28-volt bus signal is input to convert A4U30-1 where the isolated converter output voltages are rectified and filtered before being independently regulated and output. The three outputs (POS5V, NEG15V and POS15V) are filtered by capacitors A4C51, A4C53 and A4C55 and referenced to SIGGND. Subtask 24-23-34-870-026-A00 F. Power-Up Reset DC Voltage Monitor (1) The power-up reset dc voltage supply monitor circuit detects overvoltage or undervoltage fault conditions after a fixed time delay. The power OK (POK) opencollector output of A4U32-14 is held active (low) by an out-of-tolerance POS5V signal. The POS5V supply voltage level is monitored for a voltage within a tolerance of 5%. Resistors set the voltage tolerance range for the window adjustment (WA) pin (A4U32-4). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 85 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (2) The POS5V signal, through voltage divider network resistors A4R101 and A4R103, provides 2.5 Vdc to the quad supply and line monitor sense 1 (S1) input at A4U32-9. The voltage is monitored for overvoltage or undervoltage conditions. The other sense inputs (S2, S3, S4 and S4 Inverted) are tied to the 2.5 Vdc reference (A4U32-2). (3) The voltage reference input (VREF) at A4U32-2 is tied to SIGGND through resistors A4R102 and A4R104. The WA (pin 4), and resistors A4R102 and A4R104. These components control the fault thresholds of the supply monitor A4U32. The WA input provides a fault window of 2.375 to 2.625 Vdc. (4) Capacitor A4C23, which is connected to the undervoltage delay (UDLY) input at A4U32-13 sets a 50 s delay after POS5V goes out-of-range (below 4.75 Vdc). Capacitor A4C24, connected to the overvoltage delay (ODLY) input at A4U32-10, sets a 50 s time delay after POS5V goes above 5.25 Vdc. As the capacitors charge, A2U32 waits 50 s before latching the POK output at A4U32-14 active (low) which indicates that POS5V is out-of-tolerance (under/overvoltage). (5) An internal voltage follower operational amplifier (A4U32, pins 16 through 18) takes the 2.5 Vdc reference at pin 17 and outputs the CMP2.5V signal from pin 16. The CMP2.5V signal, through resistor A4R99 and capacitor A4C22, is provided to the line/ switch sense (LSS) at A4U32-15. The LSS input connects to an internal comparator with a reference voltage of 2.0 Vdc. This internal circuit indicates a voltage fault if the LSS input transitions from above or below 2.0 Vdc. The LSS input is discharged to ground when either the overvoltage fault (OFLT*) open-collector of A4U32-11 or the undervoltage fault (UFLT*) open-collector of A4U32-12 are active. (6) The capacitor A4C22 and resistor A4R99 establishes a time delay, used when a voltage fault has been removed (voltage within tolerances). This allows a delay of 20 ms before driving the POK output inactive (open). A minimum supply voltage of 3 Vdc is required at A4U32-1 before the POK signal is considered valid. (7) When the POK output A4U32-14 goes active (low), the POS15V signal (routed through pull-up resistor A4R105) and the gate of the P-channel JFET A4Q8 are both pulled to ground. As the gate of JFET A4Q8 falls below 3 Vdc, it turns off and removes the ground path (SIGGND) for the NEG15V power supply. The NEG15V supply voltage through resistor A4R107 to the gate of N-channel JFET A4Q9, turns on the JFET when the gate voltage is greater than -3 Vdc. This drives the PU_RESET* output active (low) by providing a path to SIGGND. (8) The PU_RESET* output, held low until the POK output A4U32-14 goes high (open collector), sends the POS15V signal through resistor A4R105 to the gate of JFET A4Q8. As the gate of A4Q8 rises above 3 Vdc, the JFET turns off and removes a ground path (SIGGND) to the gate of N-channel JFET A4Q9. The gate of A4Q9, pulled to -15Vdc, turns off the JFET when the gate voltage is less than -3 Vdc. The PU_RESET* output is driven inactive (high) when the POS5V supply voltage is sent through the pull-up resistor A4R106 and A4Q8 and A4Q9 are both off. (9) During BIT stimulus, the PUR_STIM signal is driven high and sent through currentlimiting resistor A4R98 and blocking diode A4D8 to the S1 sensing input (A4U32-9). This simulates an overvoltage condition that verifies the operation of the quad supply and line monitor A4U32. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 86 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subtask 24-23-34-870-027-A00 G. PMG Frequency Sense Circuit (1) The PMG frequency sense circuit receives a nominal 7 V peak input signal [PMG (+) to PMG (-)], for both inputs of the split-supply voltage comparator A4U35, from the PMG transformer A4T1 secondary #4. The comparator A4U35, resistor A4R96 and capacitor A4C21 are set up as a zero crossing detector circuit. The PMG (+) and (-) signals are sent through a signal conditioning circuit made up of resistors A4R91 and A4R95, and filter capacitor A4C20. The zero crossing detector monitors the PMG (+) and (-) signals and provides a square wave representation output (FREQ_IN_1) of the same fundamental input frequency. The line-to-line capacitor A4C20 provides a cleaner square wave output at A4U35-7. (2) The positive half of the IDG sine wave [PMG (+)] makes pin 2 of comparator A4U35 high with respect to pin 3. The negative half of the IDG sine wave [PMG (-)] makes pin 3 of comparator A4U35 high with respect to pin 2. The resultant output (pin 7) is a square wave, going high when pin 2 is higher than pin 3 and transitioning low when pin 3 is more positive than pin 2. (3) Resistor A4R96 accomplishes feedback of voltage to comparator A4U35. Capacitor A4C21 provides instantaneous feedback to offset the filter effect of A4C20. The POS5V supply voltage and pull-up resistor A4R97 provides a peak square wave output of 5 Vdc. Inverter A4U7 conditions the 5 Vdc. Series termination resistor A4R164 provides instantaneous current limiting for the inverted frequency (FREQ_IN_1) signal. This signal is sent to the ASIC in the A3 PWB I/O interface section. (4) During BIT stimulus (when PMG input is low), the comparator A4U35 inputs are pulled high by the resistors A4R92 through A4R94. The 1,600 Hz clock signal (FREQ_OUT_1) from PWB assembly A3 is sent through voltage divider resistors A4R89 and A4R90. This switches the base of the NPN bi-polar transistor A4Q18. When the transistor turns on, the comparator input A4U35-3 is pulled to SIGGND, which causes the output (A4U35-7) to go high. When the transistor turns off, the comparator input A4U35-3 goes slightly higher than A4U35-2 because of the lower voltage drop across resistor A4R92, which causes the output (A4U35-7) to go low. The inverter A4U7 outputs the simulated frequency signal back to the ASIC in the PWB assembly A3 I/O interface section. Subtask 24-23-34-870-028-A00 H. Power Ready Relay (1) The power ready relay (PRR) circuit connects and disconnects main generator power to the aircraft loads. The PRR signal causes a break-power transfer. (2) The power ready command (PR_CMD) signal mirrors the GLC solid-state relay (SSR) output PR_2A. The signal indicates that all parameters of voltage, frequency, and protection trips are within limits or are correct. (3) The GLC SSR output PR_2A is low (open). (a) GLC Control 1 The SSR switches voltage (PWR28V) to current at the GLC (PR_2A) output. The relay has over-current trip protection with a surge capability of 10A for 50 ms, and no-trip for PR_2A steady-state load current. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 87 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 The control and status pins on the SSR are tied to POS5V through the current-limiting resistors A4R67 and A4R36. When a logic high (PR_CMD) is applied to the base of the NPN bi-polar transistor A4Q20, through the voltage divider resistors A4R191 and A4R34, the transistor turns on. Transistor turn-on pulls the control pin of the GLC SSR A4U6-1 low to SIGGND. Current flow turns on the SSR. 3 When the SSR turns on, the supply voltage (PWR28V) at pin A4U6-12 is fed to the output at pin A4U6-9. The active (high) output provides a PR signal to the GLC. The PWR28V signal is limited for transient protection by TVS A4VR2. The TVS suppresses coil inductive feedback and transient voltage spikes by conducting when the voltage across the line exceeds the zener avalanche rating of 40 volts. 4 The PR trip/on status signals, PR2_TR_STS* and PR2_ON_STS, provide the state of the solid-state relay A4U6. The trip status output (PR2_TR_STS*), held high by POS5V when no trip is sensed, is internally pulled to SIGGND at pin A4U6-3 if the load current is high enough to cause the SSR to trip off. The trip status is sent to the microprocessor through the Data Bus Interface. 5 When the GLC PR signal goes active (high), the voltage (PWR28V) sent through the voltage divider resistors A4R37 and A4R38 is reduced to a voltage of approximately 5.6 Vdc. Capacitor A4C8 makes the opto-isolator A4U8 less sensitive to noise before turning on the internal LED of the optoisolator A4U8 and causing the output (A4U8-7) to reference SIGGND. The low output from A4U8-7, inverted by A4U7 and output as an active (high) PR2_ON_STS signal is sent to the microprocessor through the data bus interface. Resistor A4R161 provides a load for the output of the opto-isolator. Diode A4D10 provides reverse polarity protection for the A4U8 input. Subtask 24-23-34-870-029-A00 I. Monitors (1) The exciter field/servo drive and voltage monitor circuits use linear differential amplifiers to detect and isolate faults in the current and voltage sense circuits. (a) Exciter Field Current Monitor 1 The exciter field current sense signal (EXC_CUR), fed to the non-inverting input (pin 3) of linear differential amplifier A4U10 while the inverting input (pin 2) connects to ISOGND, is output as a SIGGND referenced fault monitor signal (EX_FLD_I_MON) at pin A4U10-6. 2 The EX_FLD_I_MON signal is then routed to the PWB assembly A3 I/O interface section as the analog input, ANALOG_15L (refer to Subtask 2423-34-870-008-A00). (b) Exciter Field (+) Voltage Monitor 1 The exciter field (+) voltage (EX_FLD_POS) signal is fed through the voltage divider network resistors A4R47, A4R48 and A4R49 and filtered by capacitor A4C11. The filtered signal is fed to the non-inverting input (pin 3) of voltage follower A4U11 and leaves at pin 1 as an approximate zero to + 6.7 Vdc signal. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 88 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 2 The signal is fed to the non-inverting input (pin 3) of linear differential amplifier A4U13, the inverting input (pin 2) is tied to ISOGND, and EX_FLD_POS_MON is output (pin 6) as a monitor signal referenced to SIGGND. 3 The EX_FLD_POS_MON signal is then routed to the PWB assembly A3 I/O interface section as the analog input, ANALOG_02L (refer to Subtask 2423-34-870-008-A00). (c) Exciter Field (-) Voltage Return Monitor 1 The exciter field (-) voltage return (EX_FLD_NEG) signal is fed through the voltage divider network resistors A4R50, A4R51 and A4R52 and filtered by capacitor A4C10. The filtered signal is fed to the non-inverting input (pin 5) of voltage follower A4U11 and leaves at pin 7 as an approximate zero to + 6.7 Vdc signal. 2 The signal is fed to the non-inverting input (pin 3) of linear differential amplifier A4U12, the inverting input (pin 2) is tied to ISOGND, and the signal EX_FLD_NEG_MON is output (pin 6) as a monitor signal referenced to SIGGND. 3 The EX_FLD_NEG_MON signal is then routed to the PWB assembly A3 I/O interface section as the analog input, ANALOG_04L (refer to Subtask 2423-34-870-008-A00). (d) Servo Valve Current Monitor 1 The servo valve current sensing circuit measures SV commanded current instead of SV coil current. The servo valve current sense (SV_I_SENSE) signal is low-pass filtered by resistor A4R53 and capacitor A4C12. The filtered signal is input to pin 3 of the non-inverting amplifier A4U31 for a gain of 11. The amplified signal is fed to the non-inverting input (pin 3) of linear differential amplifier A4U14, the inverting input (pin 2) is tied to ISOGND, and the SV_I_MON signal from A4U14-6 outputs as a fault monitor signal referenced to SIGGND. 2 The SV_I_MON signal is then routed to the PWB assembly A3 I/O interface section as the analog input, ANALOG_13L (refer to Subtask 24-23-34-870008-A00). (e) 28-Volt Power Monitor 1 The power 28 volt signal (PWR28V) is fed to the non-inverting input (pin 3) of linear differential amplifier A4U22, the inverting input (pin 2) is tied to PWRGND, and PWR28V_MON is output (pin 6) as a monitor signal referenced to SIGGND. The monitor signal has a reduced gain of 0.25 because the pin 6 output voltage is fed back through a gain reducing amplifier A4U19-9 to the reference input, REFA, at pin A4U22-5. 2 The PWR28V_MON signal is then routed to the PWB assembly A3 I/O interface section as the analog input, ANALOG_06L (refer to Subtask 2423-34-870-008-A00). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 89 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (f) 15-Volt Power Monitor 1 The isolated 5 volt signal (ISO5V) is fed to the non-inverting input (pin 3) of linear differential amplifier A4U15, the inverting input (pin 2) is tied to ISOGND, and ISO5V_MON is output (pin 6) as a monitor signal referenced to SIGGND. 2 The ISO5V_MON signal is then routed to the PWB assembly A3 I/O interface section as the analog input, ANALOG_12L (refer to Subtask 2423-34-870-008-A00). (g) Isolated 5-Volt Monitor 1 The isolated 5 volt signal (ISO5V) is fed to the non-inverting input (pin 3) of linear differential amplifier A4U15, the inverting input (pin 2) is tied to ISOGND, and ISO5V_MON is output (pin 6) as a monitor signal referenced to SIGGND. 2 The ISO5V_MON signal is then routed to the PWB assembly A3 I/O interface section as the analog input, ANALOG_12L (refer to Subtask 2423-34-870-008-A00). TASK 24-23-34-870-808-A 8. ARINC INTERCONNECT PWB ASSEMBLY A5 Subtask 24-23-34-870-030-A00 A. General Description (1) Refer to Figure 2005. The ARINC interconnect PWB assembly A5 provides routing of system interface signals to and from PWB assemblies A2 and A4. (2) The ARINC interconnect PWB assembly A5 for the GCU is a 6-layer circuit board. It contains no active circuit but provides the interconnection for the various analog and control signals. The two PWB assemblies plug directly into the connectors XA2P1 and XA4P1. (3) The PWB assembly A5 also contains an ARINC 600 connector (A5P1) located at the rear of the GCU. Signals from the aircraft and EPGS enter through the ARINC 600 connector. The signals include input/output power and drive signals, controller input/ output signals, and communication interface signals. Three polarizing pins are located between the A5P1B and A5P1C connector pins. The position of the polarizing pins determines the aircraft application on which the GCU can be used. (4) Refer to Figure 6 and Table 7 for GCU rear connector pin assignments. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 90 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 6 HE-242334-101893 Figure 6 GCU Rear Connector Pin Arrangement Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 91 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 7 Table 7 GCU Rear Connector Pin Arrangement GCU Signal Name (Hardware Name) Pin Number Low Oil Pressure (LOW_OIL*) AA4 Pin Programming Parity (PIN_PRG_PAR*) AA5 GLC Fault (S2_IN) AA6 Pin Programming E (PIN_PRG_E*) AA8 Not BTC Lockout (N_BTC_LKOUT*) AA9 Line CT Phase C (LINE_CT_PHC2) AA11 Line CT Phase B (LINE_CT_PHB2) AA12 Line CT Common (LINE_CT_COM2) AB11 Line CT Phase A (LINE_CT_PHA2) AB12 Open Cable Common (LINE_CT_COM1) AB14 Line CT Phase A1/Open Cable (LINE_CT_PHA1) AB15 Generator Control Switch +28Vdc Command (GCS_28V_CMD) AC1 Ground/Air Switch (GND_AIR_SW*) AC2 Bus Transfer Contactor Closed (BTC_CLOSED*) AC4 Spare10 – Fault Timer OR* (FTOR*) AC5 Underspeed (Disconnect Inhibit) UNDERSPEED* AC6 Pin Programming F (PIN_PRG_F) AC7 Fuel Cutoff (FUEL_CUTOFF*) AC8 Oil Temperature Output (OIL_TMP_OUT) AC9 Oil Temperature Input (OIL_TMP_IN) AC10 CHASSIS (Ref. Ground) AD10 Generator CT Phase A (GEN_CT_PHA) AD14 Generator CT Phase C (GEN_CT_PHC) AD15 Oil Temperature Common (OIL_TMP_COM) AD9 Pin Programming D (PIN_PRG_D*) AE2 Pin Programming C (PIN_PRG_C*) AE3 Generator Control Switch Off (GCS_OFF) AE4 Pin Programming B (PIN_PRG_B*) AE5 FADEC (A) ARINC 429 (-) (RX_429_NEG) AE7 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 92 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 7 GCU Rear Connector Pin Arrangement (Continued) GCU Signal Name (Hardware Name) Pin Number FADEC (A) ARINC 429 (+) (RX_429_POS) AE8 CHASSIS (Ref. Ground) AE9 Generator CT Common (GEN_CT_COM) AE14 Generator CT Phase B (GEN_CT_PHB) AE15 CHASSIS (Ref. Ground) AF6 SDAC 1 ARINC 429 (-) TX1_429_NEG AF7 SDAC 1 ARINC 429 (+) TX1_429_POS AF8 Generator Control Switch On (GCS_ON) AG2 Pin Programming A (PIN_PRG_A*) AG4 Power Ready to GCS (SYNC_D1) AG5 POR Phase A (POR_PHA) AG14 POR Phase C (POR_PHC) AG15 LRU Serial Link A (-) (LRU_SER_ANEG) AH6 SDAC 2 ARINC 429 (-) (TX2_429_NEG) AH8 POR Phase Neutral (POR_PHN) AH14 POR Phase B (POR_PHB) AH15 Disconnect Request (DISC_SW) AJ2 Fire Switch (FIRE_SW) AJ3 IDG Fault Lamp (IDG_WRN*) AJ4 LRU Serial Link A (+) (LRU_SER_APOS) AJ6 SDAC 2 ARINC 429 (+) (TX2_429_POS) AJ8 CHASSIS (Ref. Ground) AK6 CHASSIS (Ref. Ground) AK8 Spare Input 5 (SPARE_IN5) AK13 Spare Output 1 (SPARE_OUT1*) AK14 Spare Output 2 (SPARE_OUT2*) AK15 Spare Output 3 (SPARE_OUT3*) BG3 Galley Fault Lamp (GLY_SHD_2A*) BG6 Spare Output 4 (SPARE_OUT4*) BG7 Bus Synchronize Mode Code (B_SYNCMC*) BG8 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 93 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 7 GCU Rear Connector Pin Arrangement (Continued) GCU Signal Name (Hardware Name) Pin Number Power Ready to Generator Control Switch/ Generator Fault Light BG11 Serial Test Link (-) (TST_LNK_NEG) BH8 CHASSIS (Ref. Ground) BH10 Servo Valve (-) (SERVO_NEG) BH11 Spare Input 4 (SPARE_IN4) BJ3 Spare Input 3 (SPARE_IN3*) BJ4 Spare Input 2 (SPARE_IN2*) BJ5 Spare Input 1 (SPARE_IN1*) BJ6 Test Enable (TEST_EN*) BJ7 Serial Test Link (+) (TST_LNK_POS) BJ8 Power Ready to Generator Line Contactor Command (PR_2A) BJ10 Servo Valve (+) (SERVO_POS) BJ11 Test Enable Return (TEST_EN_RTN) BK7 SERIAL TEST LINK SHIELD BK8 CHASSIS (Safety Ground) C2 Power Supply Ground (PSUGND) C3 Backup +28 Vdc Power Supply (PSU28V) C4 PMG/Exciter Field Shield C7 CHASSIS (Ref. Ground) C8 PMG Phase C (PMG_PHC) C9 PMG Phase A(PMG_PHA) C10 PMG Phase B (PMG_PHB) C11 Exciter Field (+) (EX_FLD_POS) C12 Exciter Field (-) (EX_FLD_NEG) C13 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 94 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 TASK 24-23-34-870-809-A 9. LEADING PARTICULARS A. Refer to Table 8 for a list of leading particulars for the GCU. Table 8 Table 8 Leading Particulars Weight 8.73 pounds (lbs.) (3.96 kilograms [kg]) Dimensions 12.76 by 3.58 by 7.64 inches (in.) (32.41 by 9.09 by 19.4056 centimeters [cm]) Temperature Range -67 to 185 °F (-55 to 85 °C) Operating Voltage 18 to 32 Vdc Enclosure ARINC 600-3 MCU Power Dissipation 40 Watts Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 95 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DESCRIPTION AND OPERATION 24-23-34 Page 96 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 TESTING AND FAULT ISOLATION 10001000 TASK 24-23-34-700-801-A 1. GENERAL INFORMATION FOR TESTING Subtask 24-23-34-99F-010-A00 A. General Information (1) This section contains testing and fault isolation information for the GCU. Environmental conditions, pretesting check, test equipment, automatic test requirements, and fault isolation are described. NOTE: You can replace an item with its alpha-variant when permitted by the effect code for that item. For example, procedures that apply to item (10) also apply to the alpha-variant items (-10A, -10B, and -10C). (2) Refer to SPM 20-10-01. Subtask 24-23-34-94B-001-A00 B. Special Tools for Testing (1) Refer to Table 1001 for the special tools necessary to do the tests. Table 1001 Table 1001 Special Tools for Testing Tool Number and Name Source Use 600WXXXX, Test Executive Software Testek Incorporated (CAGE Code 06659) Test the GCU. 716WXXXX, Test Program Software Testek Incorporated (CAGE Code 06659) Test the GCU. 931030-P1 or 951009-PO, Interface Test Adapter Testek Incorporated (CAGE Code 06659) Test the GCU. AGETBD, A2, A3, A4 Fan-out Fixture Adapter (Optional) Hamilton Sundstrand (CAGE Code 99167) To troubleshoot the GCU while being tested with the test stand. Model TS1650, Universal Test Stand Testek Incorporated (CAGE Code 06659) Test the GCU. TE179512.bin Command Interpreter Software Testek Incorporated (CAGE Code 06659) Test the GCU. TE00246110, Buffer Converter and Diagnostic Software GCU Configuration File Testek Incorporated (CAGE Code 06659) Test the GCU. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1001 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 NOTE: Equivalent tools, fixtures, and equipment can be used if they agree with the requirements of ARINC Report 668. NOTE: To get a quotation for Ground Support Equipment, use the online order request website that follows: http://www.hamiltonsundstrand.com/gse. NOTE: You can get the full address and other information for vendors or suppliers listed in this table from the World Wide Web (www) at URL http://www.bpn.gov/bincs/begin_search.asp. Other CAGE Code sites are also available on the Web. Subtask 24-23-34-94C-001-A00 C. Test Equipment (1) Refer to Table 1002 for the test equipment necessary to do the tests. NOTE: See test stand setup for correct ITA used, refer to Figure 1001 and Figure 1002. Table 1002 Table 1002 Test Equipment Equipment Range Accuracy Use High Voltage AC Insulation Tester 100 to 3,000 VAC 0 to 5.00 milliamperes AC current To test the A5 printed wiring board insulation resistance. Megohmmeter 1 to 20,000 Megohms To measure the A5 printed wiring board insulation resistance. Milliohmmeter 1 micro-ohm to 50 milliohms To measure the A5 printed wiring board bonding resistance. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1002 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 TASK 24-23-34-700-802-A 2. ENVIRONMENTAL CONDITIONS CAUTION: ELECTROSTATIC DISCHARGE (ESDS) DEVICES ARE SUBJECT TO DAMAGE BY EXCESSIVE LEVELS OF VOLTAGE AND/OR CURRENT, JUST AS ARE THE MORE CONVENTIONAL SEMICONDUCTOR DEVICES SUCH AS BIPOLAR TRANSISTORS AND TTL LOGIC. HOWEVER, THE PRECAUTIONS USED TO PROTECT SEMICONDUCTORS ARE NOT SUFFICIENT FROM THE PROTECTION OF ESDS COMPONENTS. BECAUSE OF THE VERY HIGH RESISTANCE OF THE ESDS DEVICES, THESE COMPONENTS ARE SUSCEPTIBLE TO DAMAGE BY ELECTRICAL SOURCES WHICH CANNOT DELIVER ENOUGH ENERGY TO DAMAGE CONVENTIONAL SEMICONDUCTORS. THE LOW ENERGY SOURCE THAT MOST COMMONLY DESTROYS ESDS DEVICES IS THE HUMAN BODY, WHICH IN CONJUNCTION WITH NONCONDUCTIVE GARMENTS AND FLOOR COVERINGS, GENERATES AND RETAINS STATIC ELECTRICITY. CAUTION: IN ORDER TO ADEQUATELY PROTECT ESDS DEVICES, THE DEVICE AND EVERYTHING THAT CONTACTS IT MUST BE BROUGHT TO GROUND POTENTIAL BY PROVIDING A CONDUCTIVE SURFACE AND DISCHARGE PATHS. SPECIFICALLY, YOU MUST FOLLOW THESE PRECAUTIONS; 1) DE-ENERGIZE OR DISCONNECT ALL POWER AND SIGNAL SOURCES AND LOADS USED WITH THIS UNIT, 2) PUT THE UNIT ON A GROUNDED CONDUCTIVE WORK SURFACE, 3) GROUND THE REPAIR OPERATOR THROUGH A CONDUCTIVE WRIST STRAP OR OTHER DEVICE. USE A 470K OHM OR 1 MEG OHM SERIES RESISTOR TO PROTECT THE OPERATOR, 4) GROUND ANY TOOLS SUCH AS THE SOLDERING EQUIPMENT, WHICH WILL CONTACT THE UNIT. CONTACT WITH THE OPERATOR’S HAND PROVIDES A SUFFICIENT GROUND FOR THE TOOLS THAT ARE OTHERWISE ELECTRICALLY ISOLATED, 5) WHEN ESDS DEVICES AND ASSEMBLIES ARE NOT IN THE UNIT, THEY MUST BE ON A CONDUCTIVE WORK SURFACE OR IN CONDUCTIVE CONTAINERS. WHEN A DEVICE OR ASSEMBLY IS INSERTED IN OR REMOVED FROM A CONTAINER, THE OPERATOR MUST MAINTAIN CONTACT WITH THE CONDUCTIVE PORTION OF THE CONTAINER. DO NOT USE PLASTIC BAGS UNLESS THEY HAVE BEEN IMPREGNATED WITH A CONDUCTIVE MATERIAL, 6) DO NOT HANDLE THE ESDS DEVICES UNNECESSARILY OR REMOVE THEM FROM THEIR PACKAGES UNTIL THEY ARE ACTUALLY USED. A. Refer to SPM 20-10-01, REPAIR, when you handle ESDS devices. B. The ambient conditions of temperature, barometric pressure, and humidity that are normally found in an approved avionics maintenance facility must be kept during all GCU tests. TASK 24-23-34-700-803-A 3. TEST REQUIREMENTS SPECIFICATION A. The test requirements specification (TRS) is available for the GCU. A complete test requirements specification must include the defined drawings which are referenced within the specification. Table 1003 lists the applicable test requirements specification for each GCU configuration. To get the test requirements specification and the defined drawings, send a request to: Hamilton Sundstrand, 4747 Harrison Avenue, Rockford, IL 61108-7929, Attention: Data Management/151-6. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1003 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 TASK 24-23-34-700-804-A 4. TEST PROGRAM SOFTWARE A. The test program software is available for the GCU. Table 1003 shows the applicable test program software for each GCU configuration. To get the test program software send a request to: Hamilton Sundstrand, 4747 Harrison Avenue, Rockford, IL 61108-7929, Attention: Data Management/151-6. Table 1003 Table 1003 GCU Test Software Configuration Chart GCU FIRMWARE FIRMWARE PART NUMBER NUMBER NUMBER (FLIGHT DSP (FLIGHT AUX SOFTWARE) SOFTWARE) DOWNLOADABLE TEST TESTEK TEST TEST SOFTWARE REQUIREMENTS PROGRAM SPECIFICASET (TEST TION PROCEDURE) 1709225A 1713359 1713688 TE179512.bin Command Interpreter (CRC Number BC13) (5DSPBLK.bin DSP Test Code [CRC Number B8BA]) TRS1219 931030-P1 or 951009-P0 1709225B 1719306 1719304 TE179512.bin Command Interpreter (CRC Number BC13) (5DSPBLK.bin DSP Test Code [CRC Number B8BA]) TRS1219 931030-P1 or 951009-P0 TASK 24-23-34-700-805-A 5. TEST SOFTWARE CONFIGURATION INFORMATION A. Table 1003 lists the test requirements specification and test program software that relate to a specific GCU configuration. The figure includes the following: (1) The column heading - GCU PART NUMBER - includes the various GCU configurations by part number. (2) The column heading - FIRMWARE NUMBER (FLIGHT DSP AUX SOFTWARE) - is the number that is seen on the test stand display at the start of a test (if flight software for the digital signal processor (DSP) is loaded and an equipment identification request is initiated). (3) The number shown under the column heading - FIRMWARE NUMBER (FLIGHT SOFTWARE) - is the number that is seen on the test stand display at the start of a test (if flight software for the GCU is loaded and an equipment identification request is initiated). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1004 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (4) The column heading - DOWN-LOADABLE TEST SOFTWARE - lists the command interpreter and the DSP test code for a specific GCU configuration. CRC numbers are also shown. These numbers confirm the software has loaded correctly. (5) The column heading - TEST REQUIREMENTS SPECIFICATION AND DEFINED DRAWINGS - lists the test specification and defined drawings for a specific GCU configuration. Use these numbers when requesting a test specification. (6) The column heading - TESTEK TEST PROGRAM SET - lists the Testek test program set part number for a specific GCU configuration. Use this part number when requesting a test program set from Testek. TASK 24-23-34-700-806-A 6. PRETESTING CHECK A. Examine the GCU for contamination, corrosion, or other damage that can cause unsatisfactory performance. If the GCU has no apparent defects, proceed with testing. TASK 24-23-34-700-807-A 7. CYCLICAL REDUNDANCY CHECK NUMBERS A. The cyclical redundancy check (CRC) numbers are what the Buffer Converter and Diagnostic software displays to verify the correctness of the unit build configuration. The CRC numbers are shown in Table 1004. NOTE: CRC numbers are shown only at the time the appropriate code is downloaded. Table 1004 Table 1004 Cyclical Redundancy Check Numbers PART NUMBER FIRMWARE ASSEMBLY FIRMWARE ASSEMBLY NUMBER (FLIGHT DSP NUMBER (FLIGHT AUX SOFTWARE) SOFTWARE) DSP AUX CRC NUMBER FLIGHT CRC NUMBER 1709225A 1713359 1713688 97FD DB41 1709225B 1719306 1719304 F4DE 50B3 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1005 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 TASK 24-23-34-700-808-A 8. TESTING WARNING: ALL CIRCUITS NOT KNOWN TO BE SHUT OFF OR DISCONNECTED MUST BE CONSIDERED LIVE AND DANGEROUS AT ALL TIMES. PERSONNEL WORKING WITH ELECTRICITY SHALL HAVE ANOTHER PERSON SKILLED IN MODERN METHODS OF FIRST AID AND RESUSCITATION NEARBY. WARNING: REMOVE METALLIC RULERS, PENS, PENCILS, WATCHES, RINGS, AND OTHER ITEMS HAVING EXPOSED CONDUCTING MATERIAL WHEN WORKING ON ELECTRICAL EQUIPMENT TO PREVENT INJURY FROM ELECTRICAL SHOCK. PERSONNEL WORKING WITH ELECTRICITY SHALL HAVE ANOTHER PERSON SKILLED IN MODERN METHODS OF FIRST AID AND RESUSCITATION NEARBY. A. Install and connect the GCU to the Testek TS1650 universal test stand. Refer to the instructions in the Testek TS1650 Test Program Set Manual. Follow the instructions in Testek TS1650 Operation and Service Manual TS16500000.MNL to test a GCU. After you successfully complete the entire test procedure, the GCU may be returned to service. Test the GCU as follows: (1) Install the GCU interface test adapter (ITA) on the TS1650 test stand. Refer to Testek TS1650 Operation and Service Manual TS16500000.MNL (or equivalent). NOTE: All TS1650 test stands prior to part number 941002-P0, use the part number 931XXX series ITA. All TS1650 test stands after part number 941002-P0 and subsequent, use the part number 951XXX series ITA. (2) For TS1650 tests stands part number 941002-P0 and subsequent with 951XXX series ITAs, install the GCU in the mating connector on the left side of the ITA. (3) For TS1650 test stands with part numbers prior to 941002-P0 and 931XXX series ITAs, place the GCU on the test stand. Connect the harness assembly 931030-P1-1 (supplied with the ITA) to the ITA connectors J101 and J102, (refer to Figure 1001 and Figure 1002) and to the GCU connector. NOTE: Validate the test stand meter before the test. Refer to Testek TS1650 Operation and Service Manual TS16500000.MNL (or equivalent). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1006 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 1001 HE-242334-101894 Figure 1001 GCU Test Setup Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1007 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 1002 HE-242334-101895 Figure 1002 GCU Test Setup Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1008 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (4) The GCU NVM has BIT generated fault code messages and flight history information. The GCU test reads the NVM content and records the fault information. Then, record the GCU part number with build letter, serial number of the GCU and the flight software part number. This information is used later on, especially if the A3 PWB is changed during fault isolation. If the GCU fails any test, do the fault isolation procedure as necessary. NOTE: If the NVM is corrupted, remove and replace the NVM microcircuit A3U20 (250, IPL Figure 4). (a) Use the downloadable test software to get the fault data before the test. Refer to Table 1001. NOTE: The BCD software and the test executive software (refer to Table 1001) cannot operate at the same time. 1 Exit from the test executive if the program is open. 2 Double-click the “RRJ Download” icon (part of test program [refer to Table 1001]) and log-in to bring up the manual control window. 3 Double-click the “BCD” icon to open the Buffer Converter and Diagnostic Software. 4 Open the GCU configuration file (refer to Table 1001) to configure the BCD to work with the GCU. 5 From the BCD main screen, select the path FSI>>Connect Unit>>UUT Diagnostics to initiate GCU communications. 6 Select the RRJ Download Manual Control window and press “OFF” to turn the GCU on (the UUT POWER icon comes on). The BCD software must respond “Connection Successful.” NOTE: If power is not applied within 10 seconds, the BCD software displays a fault message. If this happens, clear the fault message by selecting “OK”, turn the GCU off, and begin from step 5. 7 From the BCD main screen, select the “Fault History” button to view the fault history screen. Save all the GCU fault records as follows: a Select the “Get All Fault Records” button. The BCD program continues to retrieve fault records until there are no more records to find or the user clicks on the “Stop” button. b Click on the “Log Buffer” button to store the buffered fault record information into a log file. c Select the A:drive and insert a formatted floppy disk into the A:drive. d Type a file name (RRJ GCU and the serial number). e Double-click on the “Save” button to transfer the file to the floppy disk. f Exit the fault history screen. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1009 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (b) Select the “SW ID” button and record the flight/DSP checksum and software (ID) numbers. NOTE: It is not necessary to record the boot checksum and software ID numbers. (5) The GCU test requires that the command interpreter and DSP aux test code be put into the GCU. Using Buffer Converter and Diagnostic software (or equivalent), overwrite the flight software with test code. NOTE: Download the DSP test code (refer to Table 1003) first, followed by command interpreter software (refer to Table 1003). (a) Download the DSP test code and command interpreter as follows: 1 Select the RRJ Download Manual Control window and press “OFF” to turn the GCU off (the UUT POWER icon goes off). 2 From the BCD main screen, select the path FSI>>Connect Unit>>Software Load to initiate GCU communications. 3 Select the RRJ Download Manual Control window and press “OFF” to turn the GCU on (the UUT POWER icon comes on). The window, “Connection Successful”, is displayed. Click “OK” to continue. NOTE: If power is not applied within 10 seconds, the BCD software displays a fault message. If this happens, clear the fault message by selecting “OK”, turn the GCU off, and begin from step 2. 4 From the BCD main screen, select the path FSI>>Load Mode>>Load From Fixed>>Aux Code. Select the DSP test code file (refer to Table 1003). The CRC number B8BA must be displayed. If correct CRC number is shown, select “Yes”. If not, reload DSP test code file. After download is complete, the window “Download Successful” is displayed. 5 Repeat steps 8.A.(5)(a)1 through 3. 6 From the BCD main screen, select the path FSI>>Load Mode>>Load From Fixed>>Test Code. Select the command interpreter test code (refer to Table 1003). The CRC number BC13 must be displayed. If correct CRC number is shown, select “Yes”. If not, reload command interpreter test code file. After download is complete, the window “Download Successful” is displayed. NOTE: The command interpreter takes several minutes to load. 7 Power down the GCU by selecting the RRJ Download Manual Control window and press “OFF” to turn off GCU off (the UUT POWER icon goes off). Press “QUIT” to exit the manual control window. 8 Exit the BCD program. (6) Start the test executive program (refer to Table 1001) by double-clicking the “TS1650” icon. (a) On the computer screen, select the applicable GCU test and test requirements specification from the menu. Make sure the selection agrees with the GCU being tested and Table 1003. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1010 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (b) Follow the computer screen prompts, enter the requested information, and run the test within the requirements of the applicable test requirement specification. (c) Exit the test executive program. (7) Restart the BCD program as follows: NOTE: The BCD software and test executive software (refer to Table 1001) cannot be running concurrently. (a) Exit the test executive program if the program is still open. (b) Double-click the “RRJ Download” icon (the file is part of the test program [refer to Table 1001]) to bring up the manual control window. (c) Double-click the “BCD” icon to open the BCD software. (d) Open the GCU configuration file (refer to Table 1001) to configure the BCD to work with the GCU. (8) After the GCU test is completed, the test code must be overwritten with flight software. Refer to the information recorded at the start of the test for the serial number, part number, flight DSP Aux software part number and flight software part number. Refer to Table 1003 for the flight DSP Aux software and flight software part numbers compatible with each GCU configuration. NOTE: Download the DSP Aux code (refer to Table 1004) first, followed by the flight code (refer to Table 1004). (a) Download the DSP Aux and flight software as follows: 1 Make sure the GCU is off. If not, select the RRJ Download Manual Control window and press “OFF” to turn the GCU off (the UUT POWER icon goes off). 2 From the BCD main screen, select the path FSI>>Connect Unit>>Software Load. 3 Select the RRJ Download Manual Control window and press “OFF” to turn the GCU on (the UUT POWER icon comes on). The window, “Connection Successful”, is displayed. Click “OK” to continue. NOTE: If power is not applied within 10 seconds, the BCD software displays a fault message. If this happens, clear the fault message by selecting “OK”, turn the GCU off, and begin from step 2. 4 From the BCD main screen, select the path FSI>>Load Mode>>Load From Fixed>>Aux Code. Select the DSP Aux file (refer to Table 1004). After download is complete, the window “Download Successful” is displayed. 5 Do steps 8.A.(8)(a)1 through 3 again. 6 From the BCD main screen, select the path FSI>>Load Mode>>Load From Fixed>>Flight Code (refer to Table 1004). After download is complete, the window “Download Successful” is displayed. NOTE: The flight software takes several minutes to load. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1011 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (9) Make sure that the software and hardware identification numbers as follows: (a) Make sure the GCU is off. If not, select the RRJ Download Manual Control window and press “OFF” to turn the GCU off (the UUT POWER icon goes off). (b) From the BCD main screen, select the path FSI>>Connect Unit>>UUT Diagnostics to initiate GCU communications. (c) Select the RRJ Download Manual Control window and press “OFF” to turn the GCU on (the UUT POWER icon comes on). The window, “Connection Successful”, is displayed. Click “OK” to continue. (d) Select the “SW ID” button and verify that the flight/DSP checksum and software ID numbers as the same as those recorded at the start of the test. (10) Clear the non-volatile memory (NVM) by selecting the “True Clear” button. (11) Power down the GCU by selecting the RRJ Download manual control window and press “OFF” to turn the GCU off (the UUT POWER icon goes off). Press “QUIT” to exit the manual control window. (12) Exit the BCD program. (13) At the completion of the test, do the test stand shutdown procedures. Refer to Testek TS1650 Operation and Service Manual TS16500000.MNL (or equivalent). (14) Remove the GCU from the ITA (refer to Figure 1001). (15) Or, remove the harness assembly (931030-P1-1) from the ITA connectors J101 and J102 (refer to Figure 1002) and from the GCU connector. TASK 24-23-34-810-801-A 9. FAULT ISOLATION A. If the acceptance test can be completed from start to finish without failure, the GCU can be returned to service. The GCU fault isolation procedures were prepared with the following presumptions: (1) The communication interface is functioning (2) The power supply is functioning (3) The A5 ARINC 600 PWB is maintaining interface integrity. B. Built-In Test (BIT) (1) SIGNATURE BIT (SIG-BIT) (a) SIG-BIT refers to reasonableness tests done continuously (may or may not be mode dependent). (b) SIG-BIT uses reasonableness checks along with cause and effect relationships to find out if a fault condition exists. (c) SIG-BIT begins to operate continually after control unit power up is complete. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1012 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (2) FAULT ISOLATION BIT (FIT) (a) FIT is executed when a fault condition is detected that results in a GC, AGC, EPC, BTC, or GCR being tripped. (b) FIT is based on failure probabilities of related circuitry in the GCU, interconnect wiring, and internal interfaces within the associated LRUs. (3) MAINTENANCE BITE (a) GROUND SELF TEST (GST) - Stimulation based test of input sense circuits of the GCU. (b) POWER UP INITIATED GST - refers to GST run automatically when power is applied to the GCU. (c) MANUALLY INITIATED GST - refers to GST run manually via the flight deck switches. TASK 24-23-34-700-809-A 10. A3 PWB REPLACEMENT A. The A3 PWB is the microprocessor board. This board contains the identifying characteristics of the GCU which include part number with build letter and serial number. If the A3 PWB is replaced during test or fault isolation, the replacement board must be configured with the necessary identifying characteristics. TASK 24-23-34-700-810-A 11. A5 PWB ASSEMBLY DIELECTRIC AND BONDING TESTS A. Dielectric Test Procedure B. Reworked test point circuits and all other disturbed test points are retested at full voltage. The remaining circuits are retested at 80 percent (%) of full voltage or 1000 Vrms, which ever is greater. C. Test is performed on chassis assembly with only the A5 PWB installed. The Unit Under Test (UUT) connectors and the A5 PWB itself should be dry, clean and free of contamination. NOTE: Make sure the UUT is not put on an Electrostatic Discharge (ESD) mat or any other device that is directly or indirectly connected to ground. D. Unless otherwise stated, the UUT will, at a minimum, be subjected to the following: (1) Dielectric Test (pin to pin) (a) Apply 1000 Vrms, 60 Hz, for one minute (applied and removed at 500 volts/sec), at 0.5 milli-amperes (mA) maximum between Test Point A and Test Point B of Table 1005. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1013 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1005 Test Point A Table 1005 Dielectric Test Points Test Point B Test Point B Test Point B All All All All P1-C9 P1-AA2 P1-AC12 P1-AH8 P1-C10 P1-AA3 P1-AC14 P1-AH14 P1-C11 P1-AA4 P1-AD9 P1-AJ1 P1-C12 P1-AA5 P1-AD10 P1-AJ2 P1-C13 P1-AA6 P1-AD14 P1-AJ3 P1-AA7 P1-AD15 P1-AJ4 P1-AA8 P1-AE1 P1-AJ5 P1-AA9 P1-AE2 P1-AJ6 P1-AA11 P1-AE3 P1-AJ8 P1-AA12 P1-AE4 P1-AK6 P1-AA13 P1-AE5 P1-AK7 P1-AA14 P1-AE7 P1-AK8 P1-AA15 P1-AE8 P1-AK11 P1-AB11 P1-AE9 P1-AK12 P1-AB12 P1-AE10 P1-AK13 P1-AB13 P1-AE14 P1-AK14 P1-AB14 P1-AE15 P1-AK15 P1-AB15 P1-AF6 P1-BG3 P1-AC1 P1-AF7 P1-BG4 P1-AC2 P1-AF8 P1-BG5 P1-AC3 P1-AF13 P1-BG6 P1-AC4 P1-AF14 P1-BG7 P1-AC5 P1-AG1 P1-BG8 P1-AC6 P1-AG2 P1-BG9 P1-AC7 P1-AG3 P1-BG10 P1-AC8 P1-AG4 P1-BG11 P1-AC9 P1-AG5 P1-BH8 P1-AC10 P1-AH6 P1-BH10 P1-C9 P1-BH11 P1-BK7 P1-AG14 P1-C10 P1-BJ3 P1-BK8 P1-AG15 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1014 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1005 Dielectric Test Points (Continued) Test Point A Test Point B Test Point B P1-C11 P1-BJ4 P1-C2 P1-C12 P1-BJ6 P1-C3 P1-C13 P1-BJ7 P1-C4 P1-BJ8 P1-C7 P1-BJ9 P1-E1 Test Point B P1-AH14 P1-BJ10 P1-BJ11 (b) The leakage current shall not be more than 2 milliamperes. (2) Bonding Resistance Test (pins to chassis) (a) Do a resistance check between Test Point C and Test Point D of Table 1006. Table 1006 Table 1006 Bonding Resistance Test Test Point C Chassis Test Point D Test Point D P1-AC12 P1-AK7 P1-AC14 P1-AK8 P1-AD10 P1-AK11 P1-AE9 P1-AK12 P1-AE10 P1-BH10 P1-AF6 P1-BK8 P1-AF13 P1-C2 P1-AF14 P1-C7 P1-AK6 (b) The resistance shall not be more than 5 milliohms. TASK 24-23-34-810-802-A 12. FAULT ISOLATION A. If the acceptance test can be completed from start to finish without failure, the GCU can be returned to service. The GCU fault isolation procedures were prepared with the following presumptions: (1) The communication interface is functioning (2) The power supply is functioning Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1015 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (3) The A5 ARINC 600 PWB is maintaining interface integrity. B. Built-In Test (BIT) (1) SIGNATURE BIT (SIG-BIT) (a) SIG-BIT refers to reasonableness tests done continuously (may or may not be mode dependent). (b) SIG-BIT uses reasonableness checks along with cause and effect relationships to find out if a fault condition exists. (c) SIG-BIT begins to operate continually after control unit power up is complete. (2) FAULT ISOLATION BIT (FIT) (a) FIT is executed when a fault condition is detected that results in a GC, AGC, EPC, BTC, or GCR being tripped. (b) FIT is based on failure probabilities of related circuitry in the GCU, interconnect wiring, and internal interfaces within the associated LRUs. (3) MAINTENANCE BITE (a) GROUND SELF TEST (GST) - Stimulation based test of input sense circuits of the GCU. (b) POWER UP INITIATED GST - refers to GST run automatically when power is applied to the GCU. (c) MANUALLY INITIATED GST - refers to GST run manually via the flight deck switches. TASK 24-23-34-810-803-A 13. USING FAULT ISOLATION CHARTS AND DATA A. Use of Fault Isolation - Test (1) The fault isolation process as provided in the test is summarized in Figure 1003. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1016 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 1003 HE-242334-101896 Figure 1003 Fault Isolation Flow Chart Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1017 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (2) The applicable test paragraphs are listed in Table 1007 for the GCU fault indicator. The GCU fault indicator is located on the front panel. Table 1007 Table 1007 Fault Isolation - Indicator Message Chart Indicator Message PTC TRIP Test Paragraph 8505 8670 (3) Test paragraph failures are provided in a chart for fault isolating the GCU (refer to Table 1008 through Table 1014). Test paragraph numbering in the charts is arranged in numerical order and is directly related to the test procedure. (a) Column 1 lists the test paragraph number. (b) Column 2 lists the printed wiring board(s) affected by the test. (c) Column 3 lists the applicable DESCRIPTION AND OPERATION section paragraph of the circuit tested for the applicable test paragraph failure. Also, the type signals applicable to the test point is indicated. (d) Column 4 lists the test name and the components tested. (e) Column 5 lists a schematic sheet reference. TASK 24-23-34-810-804-A 14. TEST STRUCTURE A. The test software implements the procedures found in the applicable TRS. The TRS is the source document for both the acceptance test procedure (ATP) and the CMM Testing and Fault Isolation. The GAPCU and the GCU share some common printed wiring board assemblies. Common PWB assemblies contain circuits that are both GAPCU-specific and GCU-specific in operation. When installed in their respective units on the aircraft, the GAPCU-specific components are not used during GCU operation and GCU-specific components are not used during GAPCU operation. B. The test has tests that make sure the tested unit operates correctly. It facilitates fault isolation of failed components to specific board(s), and may give further isolation to a group of components on a PWB that may have failed. Finally, it tests the repaired unit for the specified performance requirements to be met before it is reinstalled on the aircraft. C. There are four levels of test: (1) Subtest, (2) Function Test, (3) Object Test, and (4) Data Code Test. (1) Subtest is the highest level of test. This test can be done by itself or together with other subtests. (2) Function test is the second level of test. The function test targets specific circuit function. This test can be done by itself or together with other subtests. (3) Object test is the third level of test. The object test targets an attribute of the specific circuit function. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1018 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (4) Data code test is the final, pass-fail level of test. This test is done as part of an object test. Table 1008 Table 1008 Fault Isolation Chart (SUBTEST: Power Up - GCU) TEST PWB D&O NO. TEST NAME & COMPONENTS TESTED 8006 Wake Up Command Interpreter (CI) A3 Subtask 24-23-34-870017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34-870017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subtask 24-23-34-870018-A00, C.(2)(a) Flash Memory (NVM) A3U5 Figure 2003 (Sheet 5) Subtask 24-23-34-870018-A00, C.(2)(b) SRAM A3U3, A3U4 Figure 2003 (Sheet 5) Subtask 24-23-34-870019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) 8009 Fast Reset BIT Set 8010 Fast Reset BIT Cleared 8007 Walking BIT Test A3 SCHEMATIC REFERENCE Subtask 24-23-34-870018-A00, C.(2)(b) 8008 SRAM A3U3, A3U4 Figure 2003 (Sheet 5) Checker Test A3 Subtask 24-23-34-870018-A00, C.(2)(b) SRAM A3U3, A3U4 Figure 2003 (Sheet 5) 8015 Reset CI 8016 Check For No Failsafe Condition Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1019 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) TEST NO. PWB D&O 8101 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Register M1553BS1 - Pattern of A’s A3 Subtask 24-23-34870-019-A00, D.(1)(a)1 8102 ASIC A3U21 Figure 2003 (Sheet 7) Register M1553BS1 - Pattern of 5’s A3 Subtask 24-23-34870-019-A00, D.(1)(a)1 8103 ASIC A3U21 Figure 2003 (Sheet 7) ASIC DTI RAM Microprocessor Port BIST Enabled A3 Subtask 24-23-34870-019-A00, D.(1)(a)1 8104 ASIC A3U21 Figure 2003 (Sheet 7) ASIC DTI RAM DSP Port BIST Enabled A3 Subtask 24-23-34870-019-A00, D.(1)(a)1 8106 ASIC A3U21 Figure 2003 (Sheet 7) ASIC Fast A/D RAM DSP Port BIST Enabled A3 Subtask 24-23-34870-019-A00, D.(1)(a)1 8107 ASIC A3U21 Figure 2003 (Sheet 7) ASIC Fast A/D RAM DSP Port BIST Enabled A3 Subtask 24-23-34870-019-A00, D.(1)(a)1 8108 ASIC A3U21 Figure 2003 (Sheet 7) ASIC Slow A/D RAM A/D Port BIST Enabled A3 Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1020 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8109 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Slow A/D RAM Microprocessor Port BIST Enabled A3 Subtask 24-23-34870-019-A00, D.(1)(a)1 8110 ASIC A3U21 Figure 2003 (Sheet 7) After An Early Watchdog Trigger, Wake Up CI A3 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) 8112 Status Bits of Watchdog Failure A3 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Subtask 24-23-34870-019-A00, D.(1)(a)1 8113 ASIC A3U21 Figure 2003 (Sheet 5) Figure 2003 (Sheet 7) After A Late Watchdog Trigger, Wake Up CI A3 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1021 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8114 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Status Bits of Watchdog Failure A3 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Subtask 24-23-34870-019-A00, D.(1)(a)1 8115 ASIC A3U21 Figure 2003 (Sheet 5) Figure 2003 (Sheet 7) After a Non-ROM Fetch, Wake Up CI A3 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) 8116 Status Bits of Watchdog Failure A3 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Subtask 24-23-34870-019-A00, D.(1)(a)1 8117 ASIC A3U21 Figure 2003 (Sheet 5) Figure 2003 (Sheet 7) Verify Watchdog Clock A3 Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1022 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8120 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Write 2AAAH and Read Back D555H A2 A3 Subtask 24-23-34870-013-A00, I.(1)(c) I/O Port Latches A2U14, A2U15 Figure 2002 (Sheet 11) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) 8121 Figure 2003 (Sheet 5) Write 5555H and Read Back AAAAH A2 A3 Subtask 24-23-34870-013-A00, I.(1)(c) I/O Port Latches A2U14, A2U15 Figure 2002 (Sheet 6) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) 8125 Figure 2003 (Sheet 5) Common Discretes 1 A2 A3 Subtask 24-23-34Discretes 870-012-A00, H. (2)(b) Subtask 24-23-34870-012-A00, H. (2)(c) Figure 2002 (Sheet 25) Figure 2002 (Sheet 26) Subtask 24-23-34870-013-A00, I.(1)(c) I/O Port Latch A2U16 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) I/O Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 Figure 2002 (Sheet 12) Subtask 24-23-34870-017-A00, B. Figure 2003 (Sheet 3) Microprocessor A3U1 Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) Figure 2003 (Sheet 5) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1023 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8126 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Common 2 Discretes A2 A3 Subtask 24-23-34Discretes 870-012-A00, H.(2)(b) Figure 2002 (Sheet 24) Figure 2002 (Sheet 25) Figure 2002 (Sheet 26) Figure 2002 (Sheet 27) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) 8127 Figure 2003 (Sheet 5) Spare and Miscellaneous Discretes A2 A3 Subtask 24-23-34870-013-A00, I.(1)(a) Discretes Figure 2002 (Sheet 27) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) Figure 2003 (Sheet 5) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1024 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8128 SCHEMATIC REFERENCE Common Discretes 1 A2 Subtask 24-23-34Discretes 870-012-A00, H. (2)(b) Subtask 24-23-34870-012-A00, H. (2)(c) Figure 2002 (Sheet 25) Figure 2002 (Sheet 26) Subtask 24-23-34870-013-A00, I.(1)(c) I/O Port Latch A2U16 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34I/O Failsafe Buffer A2U38 870-013-A00, I.(1)(d)1 A3 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(a)1b Octal Buffer A2U67 Figure 2002 (Sheet 25) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) 8129 Figure 2003 (Sheet 5) Common 2 Discretes A2 Subtask 24-23-34Discretes 870-012-A00, H.(2)(b) Figure 2002 (Sheet 26) Figure 2002 (Sheet 27) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Octal Buffer A2U60, A2U70 Figure 2002 (Sheet 25) Figure 2002 (Sheet 27) Microprocessor A3U1 Figure 2003 (Sheet 3) --A3 Subtask 24-23-34870-017-A00, B. Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) Figure 2003 (Sheet 5) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1025 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8130 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Spare and Miscellaneous Discretes A2 A3 Subtask 24-23-34870-013-A00, I.(1)(a) Discretes Figure 2002 (Sheet 29) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-012-A00, H.(2)(c) Octal Buffer A2U73 Figure 2002 (Sheet 29) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) 8131 Figure 2003 (Sheet 5) Common Discretes 1 A2 A3 Subtask 24-23-34Discretes 870-012-A00, H.(2)(b) Figure 2002 (Sheet 24) Figure 2002 (Sheet 25) Figure 2002 (Sheet 26) Figure 2002 (Sheet 27) Subtask 24-23-34870-013-A00, I.(1)(c) I/O Port Latch A2U16 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) I/O Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(a)1b Octal Buffer A2U67 Figure 2002 (Sheet 25) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) Figure 2003 (Sheet 5) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1026 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8132 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Spare and Misc. Discretes A2 A3 Subtask 24-23-34870-013-A00, I.(1)(a) Discretes Figure 2002 (Sheet 29) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-012-A00, H.(2)(c) Octal Buffer A2U73 Figure 2002 (Sheet 29) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) 8133 Figure 2003 (Sheet 5) Common Discretes 1 A2 Subtask 24-23-34Discretes 870-012-A00, H.(2)(b) Figure 2002 (Sheet 24) Figure 2002 (Sheet 25) Figure 2002 (Sheet 26) Figure 2002 (Sheet 27) Subtask 24-23-34870-013-A00, I.(1)(c) I/O Port Latch A2U16 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) I/O Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 A3 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(a)1b Octal Buffer A2U67 Figure 2002 (Sheet 25) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) Figure 2003 (Sheet 5) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1027 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8134 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Spare and Misc. Discretes A2 A3 Subtask 24-23-34870-013-A00, I.(1)(a) Discretes Figure 2002 (Sheet 29) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-012-A00, H.(2)(c) Octal Buffer A2U73 Figure 2002 (Sheet 29) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34SRAM A3U3, A3U4 870-018-A00, C.(2)(b) 8135 Figure 2003 (Sheet 5) Analog_01L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(b) Positive 15V Supply A4U30 Figure 2004 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1028 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8136 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Analog_03L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(f) Negative 15V Supply A4U30 Figure 2004 (Sheet 8) 8137 Analog_05L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(f) Negative 15V Supply A4U30 Figure 2004 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1029 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8138 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Analog_07L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(b) Positive 15V Supply A4U30 Figure 2004 (Sheet 8) 8139 Analog_08L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(f) Negative 15V Supply A4U30 Figure 2004 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1030 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8140 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Analog_09L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(b) Positive 15V Supply A4U30 Figure 2004 (Sheet 8) 8141 Analog_11L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(f) Negative 15V Supply A4U30 Figure 2004 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1031 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8142 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Analog_14L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(b) Positive 15V Supply A4U30 Figure 2004 (Sheet 8) 8143 Analog_16L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(b) Positive 15V Supply A4U30 Figure 2004 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1032 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8144 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Analog_17L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(f) Negative 15V Supply A4U30 Figure 2004 (Sheet 8) 8145 Iso 5V Pwr Supply A3 Subtask 24-23-34870-019-A00, D.(1)(c) Multiplexer ANALOG_12L Figure 2003 (Sheet 8) A4 Subtask 24-23-34Voltage Regulator A4U33 870-023-A00, C.(3)(d) Figure 2004 (Sheet 5) Subtask 24-23-34Transistor A4Q11 870-023-A00, C.(3)(d) Figure 2004 (Sheet 5) Subtask 24-23-34870-029-A00, I.(1)(f) Figure 2004 (Sheet 12) Differential Amplifier A4U15 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1033 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8146 SCHEMATIC REFERENCE Analog_06L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(b) Power 28V TRU Figure 2004 (Sheet 7) Subtask 24-23-34870-029-A00, I.(1)(e) PWR28v_MON A4U22 Figure 2004 (Sheet 12) 8147 Analog_10L Channel A3 A4 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(e) 15V Voltage Regulator A4U27 Figure 2004 (Sheet 7) PWR15V_MON A4U16 Figure 2004 (Sheet 12) --- Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1034 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8150 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE SPMG Stim A2 A4 Subtask 24-23-34870-013-A00, I.(1)(b) I/O Port Input Buffer A2U12 Figure 2002 (Sheet 6) Subtask 24-23-34870-013-A00, I.(1)(d) I/O Port Failsafe Buffer A2U18 Figure 2002 (Sheet 6) Subtask 24-23-34870-013-A00, I.(1)(d) I/O Port Latch A2U15 Figure 2002 (Sheet 6) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 6) Subtask 24-23-34870-023-A00, C.(3)(c) SPMG Stimulus A4U7, A4U23, A4Q6 Figure 2004 (Sheet 5) Subtask 24-23-34SSGCR A4K2 870-023-A00, C.(3)(a) Figure 2004 (Sheet 5) Subtask 24-23-34870-024-A00, D.(3)(c) Figure 2004 (Sheet 5) 8151 SPMG Ripple Detector A4U5, A4U24 Verify SPMG Stim Reset A2 A4 Subtask 24-23-34870-013-A00, I.(1)(b) I/O Port Input Buffer A2U12 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) I/O Port Failsafe Buffer A2U18 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) I/O Port Latch A2U15 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-023-A00, C.(3)(c) SPMG Stimulus A4U7, A4U23, A4Q6 Figure 2004 (Sheet 5) Subtask 24-23-34SSGCR A4K2 870-023-A00, C.(3)(a) Figure 2004 (Sheet 5) Subtask 24-23-34870-024-A00, D.(3)(c) Figure 2004 (Sheet 5) SPMG Ripple Detector A4U5, A4U24 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1035 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1009 Fault Isolation Chart (SUBTEST: Stim Monitor - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8155 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE PMG Stim - Period A3 A4 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(a) PMG Transformer A4T1 Figure 2004 (Sheet 6) Subtask 24-23-34870-027-A00, G. PMG Frequency Sense A4Q18, A4U35, A4U7 Figure 2004 (Sheet 9) 8160 1553 Internal Data Wrap-Around Bus A A3 Subtask 24-23-34870-019-A00, D.(1)(a)1 8161 ASIC A3U21 Figure 2003 (Sheet 7) 1553 Internal Data Wrap-Around Bus B A3 Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1036 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1010 Table 1010 Fault Isolation Chart (SUBTEST: Power In - GCU/GAPCU) TEST NO. PWB D&O 8020 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Micro Doesn’t Turn Off At Minimum Voltage A4 Subtask 24-23-34870-025-A00, E.(1)(h) Hybrid Power Supply A4U30 Figure 2004 (Sheet 8) Subtask 24-23-34870-025-A00, E.(1)(h)1a EMI Filter A4L4-L6 Figure 2004 (Sheet 8) Subtask 24-23-34870-026-A00, F. 5V Power Supply Monitor A4U32 Figure 2004 (Sheet 9) Subtask 24-23-34870-025-A00, E.(1)(b)4a 28V TRU A4T1 8021 Figure 2004 (Sheet 7) Voltage At Which Micro Must Turn Off A4 Subtask 24-23-34870-025-A00, E.(1)(h) Hybrid Power Supply A4U30 Figure 2004 (Sheet 8) Subtask 24-23-34870-025-A00, E.(1)(h)1a EMI Filter A4L4-L6 Figure 2004 (Sheet 8) Subtask 24-23-34870-026-A00, F. 5V Power Supply Monitor A4U32 Figure 2004 (Sheet 9) Subtask 24-23-34870-025-A00, E.(1)(b)4a 28V TRU A4T1 8022 Figure 2004 (Sheet 7) Voltage At Which Micro Must Stay Off A4 Subtask 24-23-34870-025-A00, E.(1)(h) Hybrid Power Supply A4U30 Figure 2004 (Sheet 8) Subtask 24-23-34870-025-A00, E.(1)(h)1a EMI Filter A4L4-L6 Figure 2004 (Sheet 8) Subtask 24-23-34870-026-A00, F. 5V Power Supply Monitor A4U32 Figure 2004 (Sheet 9) Subtask 24-23-34870-025-A00, E.(1)(b)4a 28V TRU A4T1 Figure 2004 (Sheet 7) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1037 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1010 Fault Isolation Chart (SUBTEST: Power In - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8023 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Voltage At Which Micro Must Turn On A3 A4 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34870-017-A00, B.(1)(j) Differential Bus Transceiver A3U14 Figure 2003 (Sheet 4) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(h) Hybrid Power Supply A4U30 Figure 2004 (Sheet 8) Subtask 24-23-34870-025-A00, E.(1)(h)1a EMI Filter A4L4-L6 Figure 2004 (Sheet 8) Subtask 24-23-34870-026-A00, F. 5V Power Supply Monitor A4U32 Figure 2004 (Sheet 9) Subtask 24-23-34870-025-A00, E.(1)(b)4a 28V TRU A4T1 Figure 2004 (Sheet 7) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1038 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1010 Fault Isolation Chart (SUBTEST: Power In - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8024 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Micro Stays On At Minimum Input Voltage A3 A4 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34870-017-A00, B.(1)(j) Differential Bus Transceiver A3U14 Figure 2003 (Sheet 4) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-025-A00, E.(1)(h) Hybrid Power Supply A4U30 Figure 2004 (Sheet 8) Subtask 24-23-34870-025-A00, E.(1)(h)1a EMI Filter A4L4-L6 Figure 2004 (Sheet 8) Subtask 24-23-34870-026-A00, F. 5V Power Supply Monitor A4U32 Figure 2004 (Sheet 9) Subtask 24-23-34870-025-A00, E.(1)(b)4a 28V TRU A4T1 8025 Figure 2004 (Sheet 7) Check For Diode Functionality A4 Subtask 24-23-34870-025-A00, E.(1)(h)1a 8026 PSU28V Input Diodes A4VR20, A4D51, A4D52, A4VR8 Figure 2004 (Sheet 8) Minimum Voltage Micro Doesn’t Turn Off A4 Subtask 24-23-34870-025-A00, E.(1)(b)4a PMG Transformer A4T1, 28V TRU Supply Figure 2004 (Sheet 7) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1039 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) TEST NO. PWB D&O 8202 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE POR Phase A Frequency A2 A3 Subtask 24-23-34870-006-A00, B.(1)(a)1 A2AR1 ANALOG_01H Zero Crossing Detector Figure 2002 (Sheet 2) Subtask 24-23-34870-006-A00, B.(1)(a)1 A2AR4, Buffer A2U1 Figure 2002 (Sheet 2), Figure 2002 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 FREQ_IN_2 Figure 2003 (Sheet 7) 8211 Anti-Aliasing Filter [POR Phase A] A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A2AR1 ANALOG_01H Figure 2002 (Sheet 2) A3 Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1040 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8221 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Anti-Aliasing Filter [POR Phase B] A2AR2 ANALOG_02H Figure 2002 (Sheet 2) A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A3 Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) Fast MUX A3U18, A3U19 Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) 8230 Anti-Aliasing Filter [POR Phase C] A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A3 Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) A2AR3 ANALOG_03H Figure 2002 (Sheet 2) Fast MUX A3U18, A3U19 Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1041 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8235 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE In Phase Sequence A2 A3 Subtask 24-23-34870-006-A00, B.(1)(a)1 A2AR1 ANALOG_01H, A2AR2 ANALOG_02H, A2AR3 ANALOG _03H Figure 2002 (Sheet 2) Subtask 24-23-34870-006-A00, B.(1)(a)1 Zero Crossing Detector A2AR4, A2U1 Figure 2002 (Sheet 3) Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) 8244 Gen CT PHA AAF A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A3 Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) A2AR2 ANALOG_04H Figure 2002 (Sheet 3) Fast MUX A3U18, A3U19 Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1042 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8253 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Gen CT PHB AAF A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A3 Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) A2AR3 ANALOG_07H Figure 2002 (Sheet 2) Fast MUX A3U18, A3U19 Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) 8261 Gen CT PHC AAF A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A3 Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) A2AR1 ANALOG_010H Fast MUX A3U18, A3U19 Figure 2002 (Sheet 2) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1043 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8271 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Line CT PHA1 AAF A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A3 Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) A2AR3 ANALOG_05H Figure 2002 (Sheet 5) Fast MUX A3U18, A3U19 Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) 8279 Line CT PHA2 AAF A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A3 Subtask 24-23-34Flash Memory A3U5 870-018-A00, C.(2)(a) Subtask 24-23-34870-019-A00, D.(1)(c) A2AR1 ANALOG_06H Figure 2002 (Sheet 6) Figure 2003 (Sheet 5) Fast MUX (NVM) A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1044 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8291 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Line CT PHB1 AAF A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A3 Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) A2AR1 ANALOG_08H Figure 2002 (Sheet 5) Fast MUX A3U18, A3U19 Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) 8300 Line CT PHB2 AAF A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A3 Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) A2AR2 ANALOG_09H Figure 2002 (Sheet 6) Fast MUX A3U18, A3U19 Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1045 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8309 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Line CT PHC1 AAF A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A3 Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) A2AR2 ANALOG_11H Figure 2002 (Sheet 5) Fast MUX A3U18, A3U19 Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) 8319 Line CT PHC2 AAF A2 Subtask 24-23-34870-006-A00, B.(1)(a)1 A3 Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) A2AR3 ANALOG_12H Figure 2002 (Sheet 6) Fast MUX A3U18, A3U19 Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) 8322 Redundant PMG A3 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1046 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8870 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Oil Temp Low Gain Measurement A2 A3 Subtask 24-23-34870-008-A00, D.(2)(a)1 VCCS A2U2 Figure 2002 (Sheet 7) Subtask 24-23-34870-008-A00, D.(2)(a)1 Differential Amplifier A2AR5, A2AR6 Figure 2002 (Sheet 7) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34Amplifier A3U27 870-019-A00, D.(1)(d) Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) Fast MUX A3U19 Subtask 24-23-34Voltage Reference A2U22 870-019-A00, D.(1)(d) Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1047 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8871 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Oil Temp High Gain Measurement A2 A3 Subtask 24-23-34870-008-A00, D.(2)(a)1 VCCS A2U2 Figure 2002 (Sheet 7) Subtask 24-23-34870-008-A00, D.(2)(a)1 Differential Amplifier A2AR5, A2AR6 Figure 2002 (Sheet 7) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34Amplifier A3U27 870-019-A00, D.(1)(d) Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) Fast MUX A3U19 Subtask 24-23-34Voltage Reference A2U22 870-019-A00, D.(1)(d) Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1048 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8872 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Oil Temp High Gain Measurement A2 A3 Subtask 24-23-34870-008-A00, D.(2)(a)1 VCCS A2U2 Figure 2002 (Sheet 7) Subtask 24-23-34870-008-A00, D.(2)(a)1 Differential Amplifier A2AR5, A2AR6 Figure 2002 (Sheet 7) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34Amplifier A3U27 870-019-A00, D.(1)(d) Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) Fast MUX A3U19 Subtask 24-23-34Voltage Reference A2U22 870-019-A00, D.(1)(d) Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1049 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8883 SCHEMATIC REFERENCE Apply Load, Measure Output (ROLS) A2 Subtask 24-23-34870-025-A00, E.(1)(h)1b --- A3 Subtask 24-23-34870-017-A00, B. MOSFET A2Q1 Figure 2002 (Sheet 8) Differential Amplifier A2AR7 Figure 2002 (Sheet 8) Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34Amplifier A3U27 870-019-A00, D.(1)(d) Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) Fast MUX A3U18 Subtask 24-23-34Voltage Reference A2U22 870-019-A00, D.(1)(d) Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1050 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1011 Fault Isolation Chart (SUBTEST: Analog Input - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8889 SCHEMATIC REFERENCE Verify Voltage Interface (ROLS) A2 Subtask 24-23-34870-025-A00, E.(1)(h)1b --- A3 Subtask 24-23-34870-017-A00, B. MOSFET A2Q1 Figure 2002 (Sheet 8) Differential Amplifier A2AR7 Figure 2002 (Sheet 8) Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34Amplifier A3U27 870-019-A00, D.(1)(d) Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(c) Figure 2003 (Sheet 8) Fast MUX A3U18 Subtask 24-23-34Voltage Reference A2U22 870-019-A00, D.(1)(d) Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1051 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1012 Table 1012 Fault Isolation Chart (SUBTEST: Discrete Output - GCU) TEST PWB D&O NO. TEST NAME & COMPONENTS TESTED 8466 Verify UNDRSPD_ON* Monitor A2 A3 SCHEMATIC REFERENCE Subtask 24-23-34-870014-A00, J.(5)(a) Opto-coupler A2U24 Figure 2002 (Sheet 13) Subtask 24-23-34-870013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34-870013-A00, I.(1)(b) Input Buffer A2U13 Figure 2002 (Sheet 11) Subtask 24-23-34-870013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34-870013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34-870017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) 8467 UNDERSPEED* Low A2 Subtask 24-23-34-870014-A00, J.(5)(a) Switch A2U25 Figure 2002 (Sheet 13) Subtask 24-23-34-870013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34-870013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34-870013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1052 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1012 Fault Isolation Chart (SUBTEST: Discrete Output - GCU) (Continued) TEST PWB D&O NO. TEST NAME & COMPONENTS TESTED 8468 Verify UNDRSPD_ON* Monitor A2 A3 SCHEMATIC REFERENCE Subtask 24-23-34-870014-A00, J.(5)(a) Opto-coupler A2U24 Figure 2002 (Sheet 13) Subtask 24-23-34-870013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34-870013-A00, I.(1)(b) Input Buffer A2U13 Figure 2002 (Sheet 11) Subtask 24-23-34-870013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34-870013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34-870017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1053 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8577 SCHEMATIC REFERENCE PR13_STS Off A2 A4 Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U12 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Decoders A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34PR Relay Monitor A4U8 870-028-A00, H.(3)(a) 8578 Figure 2004 (Sheet 10) PR_3A* Low A2 Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latches A2U14, A2U15 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffers A2U17, A2U18 Figure 2002 (Sheet 11) A3 Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) A4 --- PR Relay A4K1 and drive circuit Figure 2004 (Sheet 10) 8582 PR13_STS On A2 A4 Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U12 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Decoders A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, J.(2)(c) Output Latch A2U15 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffers A2U17, A2U18 Figure 2002 (Sheet 11) PR Relay A4K1 and drive circuit Figure 2004 (Sheet 10) --- Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1054 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8585 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE PR_2A On With Surge Load A2 Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latches A2U14, A2U15 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffers A2U17, A2U18 Figure 2002 (Sheet 11) A3 Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) A4 Subtask 24-23-34GLC SSR A4U6 and drive circuit Figure 2004 (Sheet 10) 870-028-A00, H.(3)(a) 8586 Verify PR2_ON_STS High A2 A4 Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U12 Figure 2002 (Sheet 11) Subtask 24-23-34PR Relay Monitor A4U8, Inverter Figure 2004 (Sheet 10) 870-028-A00, H.(3)(a) A4U7 8593 Verify PR_2A Resets A2 A4 Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, J.(2)(c) Output Latch A2U15 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffers A2U17, A2U18 Figure 2002 (Sheet 11) Subtask 24-23-34870-028-A00, H. (4)(a) GLC SSR A4U6 and drive circuit Figure 2004 (Sheet 10) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1055 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8597 SCHEMATIC REFERENCE Verify NBPT Monitor A2 --- Switch A2U33 NBPT_D1*, NBPT_D2* Figure 2002 (Sheet 16) --- Monitor A2U34 NBPT_ON* Figure 2002 (Sheet 16) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U13 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) 8598 NBPT_D1* Low A2 A3 --- Switch A2U33 NBPT_D1* Figure 2002 (Sheet 16) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) 8600 Verify NBPT Monitor A2 --- Switch A2U33 NBPT_D1*, NBPT_D2* Figure 2002 (Sheet 16) --- Monitor A2U34 NBPT_ON* Figure 2002 (Sheet 16) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U13 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1056 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8676 SCHEMATIC REFERENCE Verify FTOR_ON* Monitor Inactive A2 Subtask 24-23-34870-014-A00, J. (5)(d)1b --Subtask 24-23-34870-013-A00, I.(1)(c) --- 8677 Switch A2U40 FTOR* Figure 2002 (Sheet 19) Monitor A2U34 FTOR_ON* Figure 2002 (Sheet 19) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Input Buffer A2U60 Figure 2002 (Sheet 24) FTOR* Low A2 A3 Subtask 24-23-34870-014-A00, J. (5)(d)1b FTOR* Switch A2U40 Figure 2002 (Sheet 19) Subtask 24-23-34870-013-A00, I.(1)(c) Decoders A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latches A2U14, A2U15 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffers A2U17, A2U18 Figure 2002 (Sheet 11) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) 8678 Verify FTOR_ON* Monitor Active A2 Switch A2U40 FTOR* Figure 2002 (Sheet 19) Monitor A2U34 FTOR_ON* Figure 2002 (Sheet 19) Subtask 24-23-34870-013-A00, I.(1)(c) Decoders A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, J.(2)(b) Input Buffer A2U70 Figure 2002 (Sheet 27) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34870-014-A00, J. (5)(d)1b --- Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1057 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8606 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE GLY_SHD_ON_STAT Off A2 Subtask 24-23-34870-014-A00, J.(5)(d) Relay A2K1 GLY_SHD_ON_STAT Figure 2002 (Sheet 18) Subtask 24-23-34870-014-A00, J.(5)(d) Monitor A2U29 Figure 2002 (Sheet 14) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-012-A00, H.(2)(c) Input Buffer A2U73 Figure 2002 (Sheet 29) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) 8607 GLY_SHD_1A* Low A2 A3 Subtask 24-23-34870-014-A00, J.(5)(d) Relay A2K1 GLY_SHD_1A* Figure 2002 (Sheet 18) Subtask 24-23-34870-013-A00, I.(1)(c) Decoders A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1058 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8610 SCHEMATIC REFERENCE GLY_SHD_ON_STAT On A2 Subtask 24-23-34870-014-A00, J.(5)(d) Monitor A2U29 GLY_SHD_ON_STAT Figure 2002 (Sheet 14) Subtask 24-23-34870-014-A00, J.(5)(d) Relay A2K1 GLY_SHD_ON_STAT Figure 2002 (Sheet 18) Subtask 24-23-34870-013-A00, I.(1)(c) Decoders A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-012-A00, H.(2)(c) Input Buffer A2U73 Figure 2002 (Sheet 29) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) 8614 Verify SPARE_OUT1* Monitor Active A2 --- Switch A2U45 SPARE_OUT1* Figure 2002 (Sheet 21) --- Monitor A2U46 SP_OUT1_ON* Figure 2002 (Sheet 21) Subtask 24-23-34870-013-A00, I.(1)(d) Output Latch A2U15 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U18 Figure 2002 (Sheet 11) Input Buffer A2U77 Figure 2002 (Sheet 31) Decoders A2U21, A2U22 Figure 2002 (Sheet 12) --Subtask 24-23-34870-013-A00, I.(1)(c) 8615 SPARE_OUT1* Low A2 A3 --- Switch A2U45 SPARE_OUT1* Figure 2002 (Sheet 21) Subtask 24-23-34870-013-A00, I.(1)(d) Output Latch A2U15, Failsafe Buffer A2U18 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1059 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8616 SCHEMATIC REFERENCE Verify SPARE_OUT1* Monitor Active A2 --- Switch A2U45 SPARE_OUT1* Figure 2002 (Sheet 21) --- Monitor A2U46 SP_OUT1_ON* Figure 2002 (Sheet 21) Subtask 24-23-34870-013-A00, I.(1)(d) Output Latch A2U15 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U18 Figure 2002 (Sheet 11) Input Buffer A2U77 Figure 2002 (Sheet 31) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) --Subtask 24-23-34870-013-A00, I.(1)(c) 8620 Verify SPARE_OUT2* Monitor Inactive A2 --- Switch A2U47 SPARE_OUT2* Figure 2002 (Sheet 21) --- Monitor A2U48 SP_OUT2_ON* Figure 2002 (Sheet 21) Output Latch A2U16 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(2)(c) Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 --Subtask 24-23-34870-013-A00, I.(1)(c) 8621 Figure 2002 (Sheet 12) Input Buffer A2U77 Figure 2002 (Sheet 31) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) SPARE_OUT2* Low A2 --Subtask 24-23-34870-013-A00, I.(2)(c) A3 Switch A2U47 SPARE_OUT2* Figure 2002 (Sheet 21) Output Latch A2U16 Figure 2002 (Sheet 12) Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1060 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8622 SCHEMATIC REFERENCE Verify SPARE_OUT2* Monitor Active A2 --- Switch A2U47 SPARE_OUT2* Figure 2002 (Sheet 21) --- Monitor A2U48 SP_OUT2_ON* Figure 2002 (Sheet 21) Output Latch A2U16 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(2)(c) Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 --Subtask 24-23-34870-013-A00, I.(1)(c) 8626 Figure 2002 (Sheet 12) Input Buffer A2U77 Figure 2002 (Sheet 31) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Verify SPARE_OUT3 Monitor Inactive A2 --- Switch A2U51 SPARE_OUT3 Figure 2002 (Sheet 22) --- Monitor A2U37 SP_OUT3_ON* Figure 2002 (Sheet 22) Output Latch A2U16 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(2)(c) Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U13 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) 8627 SPARE_OUT3 High A2 --Subtask 24-23-34870-013-A00, I.(2)(c) A3 Switch A2U51 SPARE_OUT3 Figure 2002 (Sheet 22) Output Latch A2U16 Figure 2002 (Sheet 12) Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1061 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8628 SCHEMATIC REFERENCE Verify SPARE_OUT3 Monitor Active A2 --- Switch A2U51 SPARE_OUT3 Figure 2002 (Sheet 22) --- Monitor A2U37 SP_OUT3_ON* Figure 2002 (Sheet 22) Output Latch A2U16 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(2)(c) Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U13 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) 8636 Verify SPARE_OUT4 Monitor Inactive A2 --- Switch A2U53 SPARE_OUT4 Figure 2002 (Sheet 22) --- Monitor A2U54 SP_OUT4_ON* Figure 2002 (Sheet 22) Output Latch A2U16 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(2)(c) Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U13 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) 8637 SPARE_OUT4 High A2 --Subtask 24-23-34870-013-A00, I.(2)(c) A3 Switch A2U53 SPARE_OUT4 Figure 2002 (Sheet 22) Output Latch A2U16 Figure 2002 (Sheet 12) Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1062 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8638 SCHEMATIC REFERENCE Verifier SPARE_OUT4 Monitor Active A2 --- Switch A2U53 SPARE_OUT4 Figure 2002 (Sheet 22) --- Monitor A2U54 SP_OUT4_ON* Figure 2002 (Sheet 22) Output Latch A2U16 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(2)(c) Failsafe Buffer A2U38 Subtask 24-23-34870-013-A00, I.(1)(d)1 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U13 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) 8647 Verify SYNC_ON* Monitor Inactive A2 --- Switch A2U27 SYNC_D1, SYNC_D2 Figure 2002 (Sheet 14) Subtask 24-23-34870-014-A00, J.(5)(d) Monitor A2U29 SYNC_ON* Figure 2002 (Sheet 14) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(b) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U13 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1063 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8648 SCHEMATIC REFERENCE SYNC_D2 High A2 A3 --- Switch A2U27 SYNC_D2 Figure 2002 (Sheet 14) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(b) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) 8650 Verify SYNC_ON* Monitor Active A2 --- Switch A2U27 SYNC_D1, SYNC_D2 Figure 2002 (Sheet 14) Subtask 24-23-34870-014-A00, J.(5)(d) Monitor A2U29 SYNC_ON* Figure 2002 (Sheet 14) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(b) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U13 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21, A2U22 Figure 2002 (Sheet 12) 8680 N_BTC_LKOUT* Low A2 Subtask 24-23-34870-014-A00, J.(5)(d) Relay A2K2 N_BTC_LKOUT* Figure 2002 (Sheet 20) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1064 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8681 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE BTC_LK High A2 Subtask 24-23-34870-014-A00, J.(5)(d) Relay A2K2 BTC_LK Figure 2002 (Sheet 20) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21 Figure 2002 (Sheet 12) Subtask 24-23-34870-012-A00, H.(2)(c) Input Buffer A2U73 Figure 2002 (Sheet 29) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) 8682 N_BTC_LKOUT* High A2 A3 Subtask 24-23-34870-014-A00, J.(5)(d) Relay A2K2 N_BTC_LKOUT* and drive circuit Figure 2002 (Sheet 20) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) 8683 BTC_LK Low A2 A3 Subtask 24-23-34870-014-A00, J.(5)(d) Relay A2K2 BTC_LK Figure 2002 (Sheet 20) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-012-A00, H.(2)(c) Input Buffer A2U73 Figure 2002 (Sheet 29) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1065 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O TEST NAME & COMPONENTS TESTED 8684 SCHEMATIC REFERENCE N_BTC_LKOUT* Low A2 A3 Subtask 24-23-34870-014-A00, J.(5)(d) Relay A2K2 N_BTC_LKOUT* and drive circuit Figure 2002 (Sheet 20) Subtask 24-23-34870-013-A00, I.(1)(a) Decoders A2U21 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) 8686 Verify DISC_LAMP* Monitor A2 --- Switch A2U31 DISC_LAMP* Figure 2002 (Sheet 15) --- Monitor A2U28 DISC_LMP_ON* Figure 2002 (Sheet 14) Subtask 24-23-34870-013-A00, I.(1)(c) Decoders A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-012-A00, H.(2)(c) Input Buffer A2U73 Figure 2002 (Sheet 29) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) 8687 DISC_LAMP* Low A2 A3 Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1066 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8688 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Verify DISC_LAMP* Monitor A2 Subtask 24-23-34870-013-A00, I.(1)(c) Decoders A2U21, A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) 8690 Verify IDG_WRN* Monitor A2 Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U12 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) 8691 IDG_WRN* Low A2 A3 Subtask 24-23-34870-014-A00, J.(5)(c) Switch A2U36 IDG_WRN* Figure 2002 (Sheet 17) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1067 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1013 Fault Isolation Chart (SUBTEST: Discrete Output - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8692 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Verify IDG_WRN_ON Monitor A2 Subtask 24-23-34870-014-A00, J.(5)(c) Switch A2U36 IDG_WRN* Figure 2002 (Sheet 17) Subtask 24-23-34870-014-A00, J.(5)(c) Monitor A2U37 IDG_WRN_ON* Figure 2002 (Sheet 17) Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U22 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U12 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U14 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U17 Figure 2002 (Sheet 11) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1068 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1014 Table 1014 Fault Isolation Chart (SUBTEST: Voltage Regulator - GCU/GAPCU) TEST NO. PWB D&O 8740 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Exciter (+) Monitor Test A2 A3 Subtask 24-23-34870-013-A00, I.(1)(a) Decoders A2U21 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, J.(2)(c) Output Latch A2U15 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U18 Figure 2002 (Sheet 11) Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) A4 Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subtask 24-23-34Solid State GCR A4K2 870-023-A00, C.(3)(a) Figure 2004 (Sheet 5) Subtask 24-23-34High Volt DC Bridge Rectifier 870-023-A00, C.(3)(b) A4D17 - A4D22 Figure 2004 (Sheet 5) Subtask 24-23-34Filter A4C32 - A4C34 870-023-A00, C.(3)(b) Figure 2004 (Sheet 5) Subtask 24-23-34Exciter Field Driver A4U1 870-024-A00, D.(3)(a) Figure 2004 (Sheet 6) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1069 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1014 Fault Isolation Chart (SUBTEST: Voltage Regulator - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8741 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Exciter (-) Monitor Test A3 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) A4 Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subtask 24-23-34Solid State GCR A4K2 870-023-A00, C.(3)(a) Figure 2004 (Sheet 5) Subtask 24-23-34High Volt DC Bridge Rectifier 870-023-A00, C.(3)(b) A4D17 - A4D22 Figure 2004 (Sheet 5) Subtask 24-23-34Filter A4C32 - A4C34 870-023-A00, C.(3)(b) Figure 2004 (Sheet 5) Subtask 24-23-34Exciter Field Driver A4U1 870-024-A00, D.(3)(a) Figure 2004 (Sheet 6) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1070 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1014 Fault Isolation Chart (SUBTEST: Voltage Regulator - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8744 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE I [Current] Monitor Check A3 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34Flash Memory (NVM) A3U5 870-018-A00, C.(2)(a) A4 Figure 2003 (Sheet 5) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4b DSP A3U17 Figure 2003 (Sheet 8) Subtask 24-23-34Solid State GCR A4K2 870-023-A00, C.(3)(a) Figure 2004 (Sheet 5) Subtask 24-23-34High Volt DC Bridge Rectifier 870-023-A00, C.(3)(b) A4D17 - A4D22 Figure 2004 (Sheet 5) Subtask 24-23-34Filter A4C32 - A4C34 870-023-A00, C.(3)(b) Figure 2004 (Sheet 5) Subtask 24-23-34Exciter Field Driver A4U1 870-024-A00, D.(3)(a) Figure 2004 (Sheet 6) Subtask 24-23-34Amplifier A4U20 870-024-A00, D.(3)(b) Figure 2004 (Sheet 6) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1071 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1014 Fault Isolation Chart (SUBTEST: Voltage Regulator - GCU/GAPCU) (Continued) TEST NO. PWB D&O 8745 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE Monitor OC Condition A2 A4 Subtask 24-23-34870-013-A00, I.(1)(a) Decoder A2U21 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(b) Input Buffer A2U12 Figure 2002 (Sheet 11) Subtask 24-23-34870-024-A00, D.(3)(c) Amplifier A4U5, A4U20 Figure 2004 (Sheet 6) Subtask 24-23-34870-024-A00, D.(3)(c) Transistor A4Q3 Figure 2004 (Sheet 6) Subtask 24-23-34870-024-A00, D.(3)(c) Opto-Isolator A4U24 Figure 2004 (Sheet 6) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1072 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1015 Table 1015 Fault Isolation Chart (SUBTEST: Servo Valve - GCU) TEST NO. PWB D&O 8776 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE 0% PWM, SVS_ENA On, PWM_2 On - No Output A2 Subtask 24-23-34870-013-A00, I.(1)(c) Decoder A2U21 Figure 2002 (Sheet 12) Subtask 24-23-34870-013-A00, I.(1)(c) Output Latch A2U15 Figure 2002 (Sheet 11) Subtask 24-23-34870-013-A00, I.(1)(d) Failsafe Buffer A2U18 Figure 2002 (Sheet 11) A3 Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) A4 Subtask 24-23-34870-022-A00, B. MOSFET A4Q2 Figure 2003 (Sheet 3) Inverter A4U18 Figure 2003 (Sheet 3) VCCS A4U2 Figure 2003 (Sheet 4) Resistor A4R28 Figure 2003 (Sheet 4) Capacitor A4C5 Figure 2003 (Sheet 4) 8777 0% PWM, SVS_ENA On, PWM_2 On -- SV_I_MON = 0 A3 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 A4 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-022-A00, B. MOSFET A4Q5 Figure 2004 (Sheet 4) Comparator A4U31 Figure 2004 (Sheet 12) Subtask 24-23-34870-029-A00, I.(1)(d) Differential Amplifier A4U14 Figure 2004 (Sheet 12) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1073 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1015 Fault Isolation Chart (SUBTEST: Servo Valve - GCU) (Continued) TEST NO. PWB D&O 8780 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE 50% PWM, SVS_ENA On, PWM_2 On - 50% Output A3 A4 Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-022-A00, B. MOSFET A4Q2 Figure 2004 (Sheet 3) Inverter A4U18 Figure 2004 (Sheet 3) VCCS A4U2 Figure 2004 (Sheet 4) Resistor A4R28 Figure 2004 (Sheet 4) Capacitor A4C5 Figure 2004 (Sheet 4) 8781 100% PWM, SVS_ENA On, PWM_2 On - 100% Output A3 A4 Subtask 24-23-34870-017-A00, B.(1)(h) Watchdog A3U13 Figure 2003 (Sheet 4) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-022-A00, B. MOSFET A4Q2 Figure 2004 (Sheet 3) Inverter A4U18 Figure 2004 (Sheet 3) VCCS A4U2 Figure 2004 (Sheet 4) Resistor A4R28 Figure 2004 (Sheet 4) Capacitor A4C5 Figure 2004 (Sheet 4) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1074 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 1015 Fault Isolation Chart (SUBTEST: Servo Valve - GCU) (Continued) TEST NO. PWB D&O 8782 TEST NAME & COMPONENTS TESTED SCHEMATIC REFERENCE 100% PWM, SVS_ENA On, PWM_2 On - SVI Monitor A3 A4 Subtask 24-23-34870-017-A00, B. Microprocessor A3U1 Figure 2003 (Sheet 3) Subtask 24-23-34870-019-A00, D.(1)(c) Fast MUX A3U18, A3U19 Figure 2003 (Sheet 8) Subtask 24-23-34Voltage Reference A3U15, 870-019-A00, D.(1)(d) A3U22 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(d)4a A/D A3U16, Gain Amplifier A3U27 Figure 2003 (Sheet 8) Subtask 24-23-34870-019-A00, D.(1)(a)1 ASIC A3U21 Figure 2003 (Sheet 7) Subtask 24-23-34870-022-A00, B. MOSFET A4Q5 Figure 2004 (Sheet 4) Comparator A4U31 Figure 2004 (Sheet 12) Subtask 24-23-34870-029-A00, I.(1)(d) Differential Amplifier A4U14 Figure 2004 (Sheet 12) Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1075 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. TESTING AND FAULT ISOLATION 24-23-34 Page 1076 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 SCHEMATICS AND WIRING DIAGRAMS 20002000 TASK 24-23-34-995-801-A 1. GENERAL A. This section contains the GCU electrical schematic diagrams. Schematics for printed wiring board (PWB) assemblies A1 through A5 are arranged sequentially. B. Schematics for the GCU are presented on multiple sheets. Circuits are tied together by circuit descriptions and connector designators located on the inputs and outputs of a circuit. When a schematic appears on multiple sheets, inter-sheet references for a PWB assembly may be found at the top or bottom of the schematic. TASK 24-23-34-995-802-A 2. USE OF SCHEMATICS A. Following circuits on the schematics involves tracing circuits on a PWB assembly from board to board or from a board to the rear connector. The following paragraphs give the procedure for tracing circuits on the schematics. B. Following Circuits Between PWB Assemblies (1) All PWB Assemblies A2 through A4 are interconnected through PWB Assembly A1. Figure 2001, Sheets 1 and 2 show a diagrammatic presentation of connector pin-to-pin connections for various circuit names. (2) Figure 2001, Sheets 6 through 8 show a tabular presentation of various circuit names and connector pin-to-pin interconnections. Proceed as follows: (a) Select a circuit name, for example: WD_RESET*. Go to Figure 2001, Sheet 2 or 3. Outputs go to connectors A2P1-8 and A3P2-3. (b) Go to Figure 2002 (Sheet 1), A2J1-8 or Figure 2003 (Sheet 1), A3J2-3, and follow the WD_RESET* line. C. Following Circuits on a PWB Assembly (1) Sheets 1 and 2 of PWB Assemblies A2 through A4 show the inputs for various circuits on a board. Use the example, WD_RESET*, and proceed as follows: (a) Go to Figure 2002 (Sheet 1), A2J1-8 or Figure 2003 (Sheet 1), A3J2-3, and follow the WD_RESET* line. (b) Trace the WD_RESET* line A2J1-8 to the COM_DIS1 circuit block. Go to Figure 2002 (Sheet 13), and follow the WD_RESET* line to A2U65 and A2U67. (c) Trace the WD_RESET* line A3J2-3 to the I/O INTERFACE circuit block. Go to Figure 2003 (Sheet 4), and follow the WD_RESET* line to A3U13. D. Following Circuits from Rear Connector to PWB Assembly (1) Figure 2005, Sheets 1 through 4 show the inputs for various circuits on PWB Assemblies A2 through A4. Select the example GCS_ON, and proceed as follows: (a) The GCS_ON input is received by rear connector P1, pin AG2. Follow the GCS_ON line to output connector XA2P1, pin 70. (b) Go to Figure 2002 (Sheet 2), and locate the P1, pin 70 input. Follow the GCS_ON line to the COM_DIS2 circuit block. (c) Go to Figure 2002 (Sheet 14), and locate the GCS_ON input. Follow the GCS_ON line to A2U65. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2001 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2001 HE-242334-101897 Figure 2001 (Sheet 1 of 6) Printed Wiring Board Assembly A1 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2002 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2001 HE-242334-101898 Figure 2001 (Sheet 2 of 6) Printed Wiring Board Assembly A1 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2003 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2001 HE-242334-101899 Figure 2001 (Sheet 3 of 6) Printed Wiring Board Assembly A1 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2004 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2001 HE-242334-101900 Figure 2001 (Sheet 4 of 6) Printed Wiring Board Assembly A1 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2005 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2001 HE-242334-101901 Figure 2001 (Sheet 5 of 6) Printed Wiring Board Assembly A1 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2006 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2001 HE-242334-101902 Figure 2001 (Sheet 6 of 6) Printed Wiring Board Assembly A1 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2007 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 J1 J1 J1 12 B_SYNCMC_I B_SYNCMC_I 23 10 TST_LNK_NEG TST_LNK_NEG 25 11 TST_LNK_POS TST_LNK_POS 26 P1 P1 P1 DISCRETE_OUT_3 GLY_SHD_CMD_I FTOR_CMD_I BTC_LK_TR_I BTC_LK_CL_I GLY_SHD_ON_STAT GLY_SHD_1A_I GLY_SHD_2B_I GLY_SHD_2A_I FTOR_ON_I FTOR_I N_BTC_LKOUT_I BTC_LK GLY_SHD_1A_I 30 GLY_SHD_2B_I 34 GLY_SHD_2A_I 32 FTOR_I 102 N_BTC_LKOUT_I 98 DISC_LAMP_I 59 NBPT_D1_I 64 NBPT_D2_I 65 IDG_WRN_I 73 P1 P1 P1 P1 P1 DISCRETE_OUT_2 IO_BLOCK J1 111 EXC_OC_STS J1 115 PR2_ON_STS J1 114 PR2_TR_STS_I J1 116 PR13_STS J1 95 ISOPS_BIT J1 110 SPMG_STS J1 112 SV_OC_STS J1 J1 J1 J1 J1 J1 J1 J1 J1 13 FAILSAFE1 59 PU_RESET_I 45 B_ADR_2 85 B_ADR_3 86 B_ADR_4 16 IO_WR1_I 15 IO_RD1_I EXC_OC_STS PR2_ON_STS PR2_TR_STS_I PR13_STS ISOPS_BIT SPMG_STS SV_OC_STS IDG_WRN_ON_I UNDRSPD_ON_I NBPT_ON_I SYNC_ON_I FAST_RST_I SP_OUT3_ON_I A7_BIT_STS_A SP_OUT4_ON_I A7_BIT_STS_B FAILSAFE1 PU_RESET_I B_ADDR_2 B_ADDR_3 B_ADDR_4 IO_WR1_I IO_RD1_I 77 A7_BIT_STS_A (GAPCU ONLY) 78 A7_BIT_STS_B (GAPCU ONLY) DISC_LMP_CMD_I NBPT_CMD_I IDG_WRN_CMD_I DATA_BUS<15..0> GLY_SHD_CMD_I IDG_WRN_CMD_I NBPT_CMD_I UNDRSPD_CMD_I DISC_LMP_CMD_I BTC_LK_CL_I BTC_LK_TR_I SYNC_CMD_I FTOR_CMD_I HI_RATE SPMG_STIM GCR_CMD PR_CMD PUR_STIM SV_ENA SP_OUT1_CMD_I SP_OUT2_CMD_I SP_OUT3_CMD_I SP_OUT4_CMD_I 120MA_CNTR_I 75MA_CNTR_I BIT_15V_CNT_I BIT_GND_CNT_I DIS_15V_CNT_I RD02062C_I RD020624_I RD020620_I DISC_LMP_ON_I DISC_LAMP_I NBPT_ON_I NBPT_D1_I NBPT_D2_I IDG_WRN_ON_I IDG_WRN_I DISCRETE_OUT_1 UNDRSPD_ON_I UNDERSPEED_I SYNC_D1 SYNC_D2 SYNC_ON_I FAST_RST_I UNDRSPD_CMD_I SYNC_CMD_I SP_OUT1_CMD_I SP_OUT2_CMD_I SP_OUT3_CMD_I SP_OUT4_CMD_I P1 P1 P1 SPARE_OUT4 SP_OUT4_ON_I P1 P1 112 P1 63 P1 108 P1 P1 P1 CTR_STRG3 CLOG_FILTER_I CTR_STRG1 110 CTR_STRG2 104 GLC_CLOSE_I P1 P1 P1 P1 COM_DIS1 P1 P1 P1 P1 P1 P1 P1 P1 105 BTC_CLOSED_I DIS_BIT_GND DIS_IN_15V BTC_CLOSED_I GND_AIR_SW_I FUEL_CUTOFF_I PIN_PRG_D_I PIN_PRG_E_I DIS_BIT_15V GCS_OFF PIN_PRG_F DISC_STS_I RD02062C_I GND_AIR_SW_I 99 FUEL_CUTOFF_I 68 PIN_PRG_D_I 58 PIN_PRG_E_I 107 GCS_OFF 100 PIN_PRG_F 69 DISC_STS_I OIL_TMP_COM 97 OIL_TMP_OUT 91 OIL_LVL_POS 50 OIL_LVL_NEG 71 SPARE_OUT1_I 39 SPARE_OUT2_I 38 SPARE_OUT3 36 SPARE_OUT4 37 GCR_CMD 73 PR_CMD 72 70 113 78 118 RX_429_POS RX_429_NEG OIL_TMP_IN OIL_TMP_COM OIL_TMP_OUT OIL_LVL_POS OIL_LVL_NEG 120MA_CNTR 75MA_CNTR RX_429_POS RX_429_NEG P1 P1 P1 P1 P1 DATA_BUS<15..0> WD_RESET_I WD_RESET* 8 LFM 9 121 J1 122 80 120 79 119 J1 J1 J1 J1 J1 J1 A B CD E F GH I J K LRU LRU LRU LRU LRU LRU LRU LRU 41 J1 J1 COMS_1 81 99 TX_INH 57 TXA 19 TXA_L 33 TXB 32 TXB_L 56 A429_TXA 18 A429_TXA_L HI_RATE LRU_SER_A4POS LRU_SER_A4NEG LRU_SER_A3POS LRU_SER_A3NEG LRU_SER_A2POS LRU_SER_A2NEG LRU_SER_A1POS LRU_SER_A1NEG TXINH TXA TXA_L TXB TXB_L 429_TXA 429_TXA_L P1 P1 P1 P1 P1 P1 P1 P1 P1 J1 J1 J1 J1 J1 OIL_IN OIL_OUT OIL_LVL LRU_TST_APOS LRU_TST_ANEG RXA RXA_L LRU_SER_APOS LRU_SER_ANEG RXB RXB_L TX1_429_POS TX1_429_NEG TX2_429_POS TX2_429_NEG A429_RXA A429_RXA_L ANALOG_13H 68 ANALOG_14H 24 ANALOG_15H 69 A429_RXA 55 A429_RXA_L 17 J1 J1 J1 J1 J1 LRU_TST_APOS 75 LRU_TST_ANEG 115 RXA 58 RXA_L 20 LRU_SER_APOS 74 LRU_SER_ANEG 114 RXB 35 RXB_L 34 TX1_429_POS 77 TX1_429_NEG 117 TX2_429_POS 76 TX2_429_NEG 116 P1 P1 J1 J1 P1 P1 J1 J1 P1 P1 P1 P1 L MN OP TO SHEET 2 HE-242334-101903 Figure 2002 (Sheet 1 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 _ SER A4POS _ SER A4NEG _ SER A3POS _ SER A3NEG _ SER A2POS _ SER A2NEG _ SER A1POS _ SER A1NEG P1 ANALOG_3 DATA_BUS<15..0> P1 103 OIL_TMP_IN 111 A429_REC 330_340_DIS DIS_BIT_GND DIS_IN_15V CTR_STRG3 CLOG_FILTER_I CTR_STRG1 CTR_STRG2 GLC_CLOSED_I RD020624_I 96 56 SYNC_D1 SYNC_D2 71 SV_ENA SP _ OUT1 _ ON _ I SPARE_OUT1_I SP_OUT2_ON_I SPARE_OUT2_I SPARE_OUT3 SP_OUT3_ON_I 101 SPMGP_STIM PUR_STIM SPARES_OUT UNDERSPEED_I P1 Page 2008 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 TO SHEET 1 A B CD E F GH I J K L MN O P COM_DIS2 P1 P1 P1 P1 67 61 62 66 PIN_PRG_C_I PIN_PRG_PAR_I LOW_OIL_I PIN_PRG_B_I P1 P1 P1 P1 70 109 27 28 GCS_ON PIN_PRG_A_I TEST_EN_I TEST_EN_RTN DIS_BIT_GND DIS_IN_15V PIN_PRG_C_I PIN_PRG_PAR_I LOW_OIL_I PIN_PRG_B_I DIS_BIT_15V GCS_ON PIN_PRG_A_I TEST_EN_I TEST_EN_RTN FTOR_ON_I RD020624_I DATA_BUS<15..0> LFM MISC_DIS P1 P1 P1 72 113 60 DISC_SW FIRE_SW S2_IN GLY_SHED_ON DISC_LMP_ON_I BTC_LK DIS_BIT_GND DIS_BIT_15V DIS_SW FIRE_SW S2_IN RD020620_I DATA_BUS<15..0> SPARE_IN P1 P1 P1 P1 P1 29 31 33 35 40 SPARE_IN1_I SPARE_IN2_I SPARE_IN3_I SPARE_IN4 SPARE_IN5 DIS_BIT_GND DIS_IN_15V SPARE_IN1_I SPARE_IN2_I SPARE_IN3_I DIS_BIT_15V SPARE_IN4 SPARE_IN5 SP_OUT1_ON_I SP_OUT2_ON_I RD020620_I DATA_BUS<15..0> P1 P1 P1 P1 P1 P1 P1 P1 48 89 47 88 49 90 7 8 P1 P1 P1 P1 P1 P1 P1 P1 52 93 51 92 53 94 11 12 P1 P1 P1 P1 P1 42 1 82 2 83 P1 P1 P1 P1 P1 P1 P1 P1 45 86 44 85 46 87 4 5 LINE_CT_PHA1 LINE_CT_PHB1 ANALOG_2 LINE_CT_PHC1 LINE_CT_COM1 LINE_CT_PHA2 LINE_CT_PHA1 LINE_CT_PHB1 LINE_CT_PHC1 LINE_CT_COM1 LINE_CT_PHA2 LINE_CT_PHB2 LINE_CT_PHC2 LINE_CT_COM2 J1 J1 J1 ANALOG_06H ANALOG_09H ANALOG_12H 61 21 23 J1 J1 J1 LINE_CT_PHC2 LINE_CT_COM2 POR_PHA POR_PHB POR_PHC POR_PHN ANALOG_1 POR_PHA POR_PHB POR_PHC POR_PHN GEN_CT_PHA GEN_CT_PHB GEN_CT_PHC GEN_CT_COM GEN_CT_PHA GEN_CT_PHB ANALOG_01H ANALOG_02H ANALOG_03H POR_A POR_B POR_C POR_FREQ GEN_PHA GEN_PHB GEN_PHC 100 101 102 54 103 J1 J1 J1 J1 J1 ANALOG_07H 62 J1 ANALOG_10H 22 J1 FREQ_IN_2 ANALOG_04H GEN_CT_PHC GEN_CT_COM 14 13 12 11 DIS_BIT POWER AND GND HIGHEST REF DES NOT USED REF DES 60 63 105 LINE_CT_PHB2 15 FILTER CAPS SPARES CHARTS TABLES ANALOG_05H ANALOG_08H ANALOG_11H 15 FILTER BIT_15V_CNT_I BIT_GND_CNT_I DIS_15V_CNT LINE_PHA1 LINE_PHB1 LINE_PHC1 LINE_PHA2 LINE_PHB2 LINE_PHC2 10 DIS_BIT_15V DIS_BIT_GND DIS_IN_15V 9 8 R490 R491 75 R493 75 R495 75 R497 75 15 7 75 R492 14 6 13 5 75 R494 12 4 11 3 75 R496 10 2 9 1 8 0 75 R498 R499 75 R501 75 R503 75 R505 75 75 R500 14 7 6 5 75 R502 4 75 R504 2 75 3 1 0 13 12 11 10 9 8 7 6 5 4 3 2 1 DATA_BUS<15..0> B_DATA<15..0> 0 B_DATA_15 B_DATA_14 B_DATA_13 B_DATA_12 B_DATA_11 B_DATA_10 B_DATA_9 B_DATA_8 B_DATA_7 B_DATA_6 B_DATA_5 B_DATA_4 B_DATA_3 B_DATA_2 B_DATA_1 B_DATA_0 94 93 92 91 90 89 88 87 53 52 51 50 49 48 47 46 J1 J1 J1 J1 J1 J1 J1 J1 J1 J1 J1 J1 J1 J1 J1 J1 HE-242334-101904 Figure 2002 (Sheet 2 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2009 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 C1 FB1 2 115 VRMS 1 POR_PHA\I BLM32A07 5909087 1 5 2 7 R1 R2 75K 75K 2000PF POS15V\G AR1 C2 1000PF 4 T1 3 TL074 1 2 11 3 2 ANAGND1 5 CHASSISGND POR_A\I NEG15V\G C3 FB2 2 115 VRMS 1 POR_PHB\I BLM32A07 5909087 1 5 2 7 R3 R4 75K 75K 2000PF POS15V\G AR2 C4 1000PF 4 T2 3 TL074 1 2 11 3 POR_B\I 2 ANAGND1 5 CHASSISGND NEG15V\G C5 R5 5909087 R24 75K 5 2 33.2K 1W 1 2 75K C6 1000PF 7 3 TL074 1 2 POR_C\I R8 3 2 FB4 POR_PHN\I POS15V\G AR3 1 BLM32A07 2000PF R6 10K ANAGND1 5 CHASSISGND BLM32A07 NEG15V\G 75PF POR ZEROCROSS POS15V\G AR4 B 3 5 8 R7 10K 2 S/B 6 POR INTERFACE POS5V\G C7 R9 1K 4 115 VRMS 2 11 1 4 T3 FB3 POR_PHC\I V+ 7 1 V- LM211 R10 4.99K U1 13 14 12 R11 POR_FREQ\I 75 NEG15V\G 2 DIGGND1 ANAGND1 HE-242334-101905 Figure 2002 (Sheet 3 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2010 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 1 ARMS FB5 1 2 BLM32A07 R12 C8 1 T4 R13 1 KELVIN_RES 5 2 7 3 75K 75K 2000PF C9 1000PF 100V 7 6 ANAGND1 R16 GEN_PHA\I NEG15V\G C10 1 R18 T5 R17 1 1 5 2 7 3 75K 2000PF R19 POS15V\G 4 KELVIN_RES 75K 5 C11 1000PF 5 CHASSISGND AR3 TL074 7 6 2 KELVIN_RES GEN_PHB\I NEG15V\G ANAGND1 FB7 1 ARMS 1 2 C12 R20 R21 1 KELVIN_RES 1 ARMS R22 T6 1 5 2 7 3 75K 2000PF R23 POS15V\G 4 1 KELVIN_RES 75K C13 1000PF 5 AR1 TL074 7 6 GEN_PHC\I 11 BLM32A07 GEN_CT_COM\I POS15V\G AR2 TL074 2 BLM32A07 GEN_CT_PHC\I 5 2 5 CHASSISGND FB6 1 R15 11 GEN_CT_PHB\I 1 ARMS 1 R14 11 KELVIN_RES 4 GEN_CT_PHA\I 2 5 CHASSISGND NEG15V\G ANAGND1 FB8 1 2 BLM32A07 CT SENSE HE-242334-101906 Figure 2002 (Sheet 4 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2011 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 FB11 C21 2 R31 1 2 3 11 75K 1 5 2 7 3 1 75K R39 T13 KELVIN_RES 2 2000PF R42 75K 10 5 3 8 9 LINE_PHB1\I C25 C26 1000PF 100V 1 AR1 TL074 2 ANAGND1 R41 1 10 NEG15V\G 2 R40 75K 5 CHASSISGND 1 KELVIN_RES POS15V\G 2000PF C24 1000PF 100V FB13 BLM32A07 R38 T12 KELVIN_RES 1 ARMS 2 ANAGND1 R37 R35 R36 LINE_CT_COM1\I LINE_PHA1\I C23 KELVIN_RES 1 8 NEG15V\G 1 1 ARMS AR3 TL074 9 7 2 BLM32A07 LINE_CT_PHC1\I POS15V\G 4 1 2000PF C22 1000PF 100V 5 CHASSISGND FB12 1 ARMS 75K 5 KELVIN_RES LINE_CT_PHB1\I 75K T11 1 1 R34 10 KELVIN_RES R32 R33 4 BLM32A07 11 1 POS15V\G AR2 TL074 4 1 ARMS 8 9 LINE_PHC1\I 11 LINE_CT_PHA1\I NEG15V\G 7 5 CHASSISGND 2 ANAGND1 FB14 1 2 BLM32A07 HE-242334-101907 Figure 2002 (Sheet 5 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2012 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 FB15 C27 2 R43 1 KELVIN_RES R45 R46 75K 75K 12 C28 1000PF 100V T14 1 5 2 3 KELVIN_RES 1 ARMS 1 NEG15V\G R49 R47 1 75K KELVIN_RES R48 1 2 3 1 75K R51 1 KELVIN_RES 1 ARMS T16 1 5 2 7 3 14 13 LINE_PHB2\I 2 ANAGND1 R53 1 POS15V\G AR2 TL074 NEG15V\G 2 R52 12 7 5 CHASSISGND KELVIN_RES 2000PF C30 1000PF 100V FB17 BLM32A07 LINE_CT_COM2\I C29 75K 5 KELVIN_RES 1 ARMS R50 T15 1 LINE_CT_PHC2\I 2 ANAGND1 2 BLM32A07 LINE_PHA2\I 4 LINE_CT_PHB2\I 14 13 7 5 CHASSISGND FB16 POS15V\G AR1 TL074 11 1 R44 2000PF 4 BLM32A07 11 1 5 CHASSISGND R54 C31 2000PF POS15V\G AR3 TL074 4 1 ARMS 75K 12 C32 1000PF 100V 14 13 LINE_PHC2\I 11 LINE_CT_PHA2\I NEG15V\G 2 ANAGND1 FB18 1 2 BLM32A07 HE-242334-101908 Figure 2002 (Sheet 6 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2013 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 PWR15V\G OIL TEMP U2 2 5 8 4 VIN TRIM OUT NRED GND R61 6 1K 0.1 AD586 POS15V\G C41 0.01UF NEG15V\G 3 PWRGND 3 AR5 PWRGND 7 R63 3 OIL_TMP_IN\I C 1K VR1 45V +VCC -VCC + 6 COMP 8 REFA REFB INA117 2 C42 0.47UF 5 1 R64 A IN SENSE 4 OUT OIL_IN\I 1K 5 CHASSISGND 2 ANAGND1 R67 1K 0.1 POS15V\G NEG15V\G AR6 OUT SENSE 7 R65 3 OIL_TMP_COM\I 1K R66 OIL_TMP_OUT\I +VCC -VCC C43 0.47UF + 6 COMP 8 REFA REFB INA117 2 5 1 OUT OIL_OUT\I C C 1K VR3 45V 2 ANAGND1 A VR2 45V A 4 3 PWRGND 5 CHASSISGND HE-242334-101909 Figure 2002 (Sheet 7 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2014 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 U75 LM317T R83 2 OIL_LVL_POS\I VOUT VIN 3 ADJ 1 2 PWR28V\G 1UH VR4 40V NEG15V\G POS15V\G 1 8.25 ROLS L1 150MA CURRENT LIMIT AR7 7 R68 5 CHASSISGND 3 1K 0.25W C44 0.47UF R69 OIL_LVL_NEG\I 1K 0.25W VR5 40V 2 5 1 +VCC + 6 COMP 8 REFA REFB INA117KU OUT OIL_LVL\I 2 POS15V\G 4 VR6 LT1004 1.235V + + - 11 AR8 TL074 NEG15V\G D R71 7 LT1214 C46 1000PF Q1 G 1K C47 0.01UF R75 16.5 POS5V\G R74 4.99K R73 75MA_CNTR\I 20K R81 1K 3 PWRGND R82 3.16K R72 PWRN15V\G 2 S C45 0.01UF 6 13 8 6 5 4 I149 AR9 3 1 CURRENT SOURCE R70 10K ANAGND1 4 PWR15V\G 5 CHASSISGND AV=1/4 4 -VCC 1 U3 2 499 6 5 4 3 PVG612 PWRGND R80 10.2 POS5V\G R79 4.99K R78 1 U4 2 120MA_CNTR\I 499 6 5 4 PVG612 3 PWRGND HE-242334-101910 Figure 2002 (Sheet 8 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2015 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 R92 T21 LRU_SER_A4POS\I 4 5 6 7 8 M21038/27-02 IN A4 XFMR LRU_SER_A4NEG\I IN R91 1 2 57.6 A3 XFMR LRU_SER_A3NEG\I IN 2 57.6 R95 3 A2 XFMR LRU_SER_A2NEG\I IN A1 XFMR LRU_SER_A1NEG\I IN R97 57.6 2 57.6 R99 3 57.6 4 5 6 7 8 M21038/27-02 IN R100 1 2 57.6 3 R101 R102 57.6 76.8 POS5V\G + LRU_TST_ANEG\I R98 1 T24 LRU_SER_A1POS\I OUT 57.6 R96 T23 4 5 6 7 8 M21038/27-02 IN LRU_TST_APOS\I R94 1 57.6 LRU_SER_A2POS\I OUT 57.6 4 5 6 7 8 M21038/27-02 IN R93 3 T22 LRU_SER_A3POS\I 76.8 C51 10UF T25 4 5 6 7 8 1 R103 10K R104 10K DIGGND1 TXINH\I TXA\I TXA_L\I TXB\I TXB_L\I 2 U5 1 3 1 4 18 19 20 5 CHANNEL A +5V RXENA_A BUS_A TXINH_A BUS_A_L TXA RXA RXA_L TXA_L GND_A 6 9 13 14 15 10 CHANNEL B +5V BUS_B RXENA_B BUS_B_L TXINH_B TXB RXB TXB_L RXB_L GND_B BUS A XFMR RXA\I 2 3 17 16 RXA_L\I T26 1 7 8 2 3 12 11 4 5 6 7 8 BUS B XFMR LRU_SER_APOS\I LRU_SER_ANEG\I RXB\I RXB_L\I NHI-1567 XCVR 1 DIGGND1 1 DIGGND1 INTER LRU HE-242334-101911 Figure 2002 (Sheet 9 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2016 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 D6 C U6 LM317T 3 PWR5V\G VIN VOUT 2 ADJ PWR15V\G R105 1 PWR15V\G A CMPD914 200 + C52 10UF C53 0.1UF R106 + C54 10UF PWRN15V\G + 402 C55 10UF R107 C56 0.1UF C57 0.1UF R108 10K 200 4950924 R109 3 POS5V\G U1 9 429_TXA\I 14 1K R110 4.99K 8 HCPL2232 U1 429_TXA_L\I 11 14 VCC VO GND 16 4 14 1 3 13 2 8 7 5 10 R111 4.99K R112 +5V DATA A CLK VREF SYNC DATA B DGND 9 7 6 11 5 12 8 +15V -15V OUT A OUT B CA CB AGND POS5V\G 8 6 5 14 16 5 V+ 13 S D IN GND V- 15 C59 470PF DG202B PWRN15V\G 3 PWRGND TX1_429_POS\I 2 OUT TX1_429_NEG\I C63 0.01UF C64 0.01UF 13 V+ 6 8 5 C60 75PF 4 PWR15V\G U9 PWR15V\G 6V OUT BLM32A07 VR12 HCPL2232 1K FB22 1 U9 VCC VO GND 2 BLM32A07 VR11 6V XMTR CH1 PWRGND U7 4 3 FB21 1 3 U8 PWRGND U7 1 2 C58 0.1UF NOT INSTALLED C62 75PF 7 S D IN GND V- 4 NOT INSTALLED C61 470PF DG202B PWRN15V\G 5 CHASSISGND 3 PWRGND PWR15V\G SPEED SELECT LOGIC R113 1 POS5V\G 1K 0.25W PWRGND 4 2 R114 4.99K 3 R115 10K U10 3 SFH6186 R116 10K HI_RATE\I PWR15V\G FB23 1 PWRN15V\G PWR5V\G 4950924 3 PWRGND ARINC 429 TRANSMIT XMTR CH2 U11 16 4 14 1 3 13 2 +5V DATA A CLK VREF SYNC DATA B DGND +15V -15V OUT A OUT B CA CB AGND 2 OUT TX2_429_POS\I BLM32A07 VR13 6V 9 7 6 11 5 12 8 FB24 1 VR14 6V U9 V+ 3 1 5 S D IN GND V- 13 C66 75PF 2 4 C65 470PF DG202B PWRN15V\G PWR15V\G U9 PWR15V\G 11 9 5 V+ 13 S D IN GND V- 10 4 DG202B C68 75PF 2 OUT TX2_429_NEG\I BLM32A07 C69 0.01UF C70 0.01UF NOT INSTALLED NOT INSTALLED 5 CHASSISGND C67 470PF 3 PWRGND PWRN15V\G 3 PWRGND Figure 2002 (Sheet 10 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2017 Jun 6/14 HE-242334-101912 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 DATA_BUS<15..0>\I IO U19 READBACK<15..0> INPUT BUFFERS OUTPUT LATCHES U12 EXC_OC_STS\I PR2_ON_STS\I PR2_TR_STS_I\I PR13_STS\I 244 A3 Y3 9 0 13 A2 Y2 7 1 15 A1 Y1 5 2 17 A0 Y0 3 3 0 VCC=POS5V;GND=DIGGND1 U12 SPMG_STS\I SV_OC_STS\I IDG_WRN_ON_I\I 8 Y3 12 4 6 A2 Y2 14 5 4 A1 Y1 16 6 2 A0 Y0 18 7 18 17 14 13 8 7 4 3 0 1 2 3 4 5 6 7 19 244 A3 1 2 U14 OE ISOPS_BIT\I 3 273 11 19 16 15 12 9 6 5 2 Q7 Q6 Q5 Q4 Q3 Q2 Q1 Q0 D7 D6 D5 D4 D3 D2 D1 D0 FAST_RST_I\I Y3 12 0 6 A2 Y2 14 1 4 A1 Y1 16 2 2 A0 Y0 18 3 SP_OUT3_ON_I\I A7_BIT_STS_A\I SP_OUT4_ON_I\I A7_BIT_STS_B\I 2 15 A1 Y1 5 2 3 17 A0 Y0 3 3 13 A2 Y2 7 15 A1 Y1 5 4 3 5 17 4 5 6 7 A0 8 9 VCC=POS5V;GND=DIGGND1 244 A3 Y3 13 A2 15 A1 17 A0 11 U15 U13 9 4 Y2 7 5 Y1 5 6 Y0 3 7 18 17 14 13 8 7 4 3 8 9 10 11 12 13 14 15 11 273 D7 D6 D5 D4 D3 D2 D1 D0 Q7 Q6 Q5 Q4 Q3 Q2 Q1 Q0 Y0 8 Y3 12 4 6 A2 Y2 14 5 6 4 A1 Y1 16 6 7 2 A0 Y0 18 7 8 240 A3 Y3 12 6 A2 Y2 14 4 A1 Y1 16 8 2 A0 Y0 18 9 1 U20 11 240 A3 Y3 9 13 A2 Y2 7 9 10 15 A1 Y1 5 10 11 17 A0 Y0 3 11 Y3 9 13 A2 Y2 7 15 A1 Y1 5 A0 Y0 3 U20 12 8 240 A3 Y3 12 12 13 6 A2 Y2 14 13 14 4 A1 Y1 16 14 15 2 A0 Y0 18 15 OE 1 12 13 POS5V\G 8 240 A3 Y3 12 6 A2 Y2 14 4 A1 Y1 16 2 A0 Y0 18 10K GLY_SHD_CMD_I\I IDG_WRN_CMD_I\I NBPT_CMD_I\I UNDRSPD_CMD_I\I DISC_LMP_CMD_I\I BTC_LK_CL_I\I BTC_LK_TR_I\I SYNC_CMD_I\I FTOR_CMD_I\I HI_RATE\I SPMG_STIM\I GCR_CMD\I PR_CMD\I SV_ENA\I SP_OUT1_CMD_I\I PUR_STIM\I OE 15 1 VCC=POS5V;GND=DIGGND1 A C B D E TO SHEET 12 Figure 2002 (Sheet 11 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2018 Jun 6/14 OUT OUT OUT OUT OUT OUT OUT OUT OUT OUT OUT OUT OUT OUT OUT OUT G F UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. READBACK U18 CL DIGGND1 19 19 R122 1 240 A3 OE 14 R121 4.99K OE 11 17 BUFFERS OE 8 19 16 15 12 9 6 5 2 1 POS5V\G 10 READBACK U19 240 A3 U18 19 R235 1K 1 U17 1 OE R234 1K 7 19 19 CL OE 11 Y2 9 1 8 1 0 A2 Y3 OE 244 A3 RDO2O638 9 13 240 A3 U13 SYNC_ON_I\I Y3 1 11 1 NBPT_ON_I\I 240 A3 OE OE OE UNDRSPD_ON_I\I 11 U17 11 RD02063C FAILSAFE BUFFERS 0 HE-242334-101913 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 TO SHEET 11 A B C D E F G PU_RESET_I\I R126 10K NOT INSTALLED U38 U16 1 DIGGND1 0 1 2 3 4 5 6 7 FOR 1700676 CONFIGURATIONS AND SUBSEQUENT ONLY 18 17 14 13 8 7 4 3 11 R123 75 0.25W R124 75 0.25W FAILSAFE1\I 273 D7 D6 D5 D4 D3 D2 D1 D0 Q7 Q6 Q5 Q4 Q3 Q2 Q1 Q0 19 16 15 12 9 6 5 2 11 240 A3 Y3 9 BIT_GND_CNT_I\I 13 A2 Y2 7 SP_OUT2_CMD_I\I 15 A1 Y1 5 SP_OUT3_CMD_I\I 17 A0 Y0 3 SP_OUT4_CMD_I\I OUT OUT OUT OUT OE CL 19 1 R125 1K PU_RESET_I\I R127 1K 1 U21 139 DEMUX Y3 DIGGND1 DECODERS 3 2 B_ADDR_2\I S1 S0 R130 POS5V\G 1 S1 S0 Y2 Y1 EN Y 0 DIGGND1 IO_RD1_I\I WR020620 8 Y3 12 120MA_CNTR_I\I 6 A2 Y2 14 75MA_CNTR_I\I 4 A1 Y1 16 BIT_15V_CNT_I\I 2 A0 Y0 18 DIS_15V_CNT_I\I OUT OUT OUT OUT OE 6 Y2 1 5 Y1 4 1 7 R131 1K 6 5 4 U22 139 DEMUX Y3 1 R129 10K 10K 3 2 R128 1K 240 A3 7 EN Y 0 U22 139 DEMUX Y3 U38 WR020630 C283 0.1UF 13 14 B_ADDR_3\I R132 1K S1 S0 Y2 Y1 RD02062C_I\I 10 RD020624_I\I 11 OUT OUT RD020628* RD020620_I\I 12 OUT 15 EN Y 0 9 U21 139 DEMUX Y3 B_ADDR_4\I POS5V\G R133 10K S1 S0 Y2 Y1 EN Y 0 9 10 11 12 15 13 14 IO_WR1_I\I HE-242334-101914 Figure 2002 (Sheet 12 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2019 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 MONITOR PWR28V\G POS5V\G R146 24.9K DEFAULT UNDERSPEED C76 0.1UF R147 10K U24 4 3 R145 10K PWR15V\G VCC VO GND 8 6 5 TP16 UNDRSPD_ON_I\I HCPL-073A POS5V\G 1 TP18 CMPD914 4 TP17 2 3 R141 UNDRSPD_CMD_I\I U25 1 SFH6186 1K D11 C R142 4.99K DIGGND1 A R143 10K U23 DRAIN IN SOURCE R144 4.99K D10 2 UNDERSPEED_I\I 3,4 C77 0.01UF 500V BSP75N 3 3 PWRGND CHASSISGND PWRGND SWITCH HE-242334-101915 Figure 2002 (Sheet 13 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2020 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 PWR15V\G SWITCH D12 SYNC_D1\I PWR28V\G R150 10K U26 1 1 R149 4.99K 4 TP14 2 3 R148 SYNC_CMD_I\I SFH6186 1K C80 0.01UF 500V R151 4.99K 2 IN 4 ST U27 BTS409L1 VBB OUT 5 SYNC_D2\I 1 1 R156 24.9K D140 R163 200 3 5 CHASSISGND D13 GND 1 TP15 SYNC 3 POS5V\G POS5V\G 5 CHASSISGND CMPD914 A C PWRGND PWR5V\G 1 3 R159 R161 PWR28V\G AR9 14 + 15 - 100K R160 100K + PWRGND 1 D14 R157 10K U29 C79 0.1UF 4 3 VCC VO GND 8 6 5 R158 10K TP13 SYNC_ON_I\I HCPL-073A + D15 16 A C LT1214 CMPD914 C78 4.7UF 3 MONITOR PWRGND DIGGND1 POS5V\G 13 140K PWR15V\G 4 R153 1K C81 0.01UF 500V R154 10K PWRN15V\G R152 10K R155 4.99K 3 PWRGND U28 4 3 U1 VCC VO GND 8 6 5 1 14 2 FAST_RST_I\I HCPL-073A FAST_RST 3 DIGGND1 PWRGND HE-24233-101916 Figure 2002 (Sheet 14 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2021 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 MONITOR PWR28V\G POS5V\G R171 24.9K DEFAULT C91 0.1UF 1 2 R170 10K VCC VO GND TP29 R167 4.99K DISC_LMP_CMD_I\I 1K D16 C TP30 U31 1 3 R166 SFH6186 DISC_LMP_ON_I\I CMPD914 4 2 TP25 DIGGND1 A R168 10K U30 1 8 7 5 HCPL-073A PWR15V\G POS5V\G R172 10K U28 IN DRAIN SOURCE R169 4.99K D17 2 DEFAULT 3,4 DISC_LAMP_I\I C92 0.01UF BSP75N 3 SWITCH PWRGND 3 CHASSISGND PWRGND HE-242334-101917 Figure 2002 (Sheet 15 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2022 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 MONITOR PWR28V\G POS5V\G R178 24.9K DEFAULT C93 0.1UF R179 10K U34 4 3 R177 10K PWR15V\G VCC VO GND 8 6 5 TP23 NBPT_ON_I\I D19 HCPL-073A DEFAULT POS5V\G 1 TP28 R174 4.99K 1K C TP24 U33 1 3 R173 NBPT_CMD_I\I D18 CMPD914 4 2 SFH6186 C94 0.01UF DIGGND1 A R175 10K U32 NBPT_D1_I\I IN DRAIN SOURCE R176 4.99K D20 2 CHASSISGND DEFAULT 3,4 NBPT_D2_I\I C95 0.01UF BSP75N SWITCH 3 PWRGND 3 CHASSISGND PWRGND HE-242334-101918 Figure 2002 (Sheet 16 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2023 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 MONITOR PWR28V\G POS5V\G R185 24.9K DEFAULT C96 0.1UF 1 2 R184 10K VCC VO GND 1 TP27 R181 4.99K IDG_WRN_CMD_I\I 1K CMPD914 C TP26 2 U36 1 3 SFH6186 IDG_WRN_ON_I\I D21 4 R180 TP22 DIGGND1 A R182 10K U35 8 7 5 HCPL-073A PWR15V\G POS5V\G R186 10K U37 R183 4.99K IN DRAIN SOURCE D22 2 DEFAULT 3,4 IDG_WRN_I\I C97 0.01UF BSP75N SWITCH CHASSISGND PWRGND PWRGND HE-242334-101919 Figure 2002 (Sheet 17 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2024 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 MONITOR PWR28V\G POS5V\G R195 10K U29 R193 4.99K 1 2 C101 0.01UF 500V VCC VO GND 8 7 5 OUT GLY_SHD_ON_STAT\I HCPL-073A 1 R194 24.9K DIGGND1 OUT GLY_SHD_1A_I\I K1 R506 10 0.25W POS5V\G 3 R191 R507 2 5 7 10 0.25W 6 4 8 1 U76 6 A 5 2 OUT GLY_SHD_2B_I\I OUT GLY_SHD_2A_I\I S114_26 PWRGND 499 R192 4.99K 3 1 D26 C C102 0.01UF 500V PWR28V\G CMPD914 C103 0.01UF 500V C104 0.01UF 500V 4 PVG612 GLY_SHD_CMD_I\I 5 CHASSISGND 3 PWRGND GALLEY SHED HE-242334-101920 Figure 2002 (Sheet 18 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2025 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 PWR28V\G MONITOR POS5V\G R201 24.9K DEFAULT C105 0.1UF 1 2 R200 10K VCC VO GND A R198 10K 1 TP21 4.99K 1K DIGGND1 CMPD914 C U40 TP20 2 1 3 R196 FTOR_CMD_I\I D27 4 R197 FTOR_ON_I\I IN DRAIN SOURCE SFH6186 R199 4.99K D30 2 DEFAULT C106 0.01UF 500V U39 TP19 8 7 5 HCPL-073A PWR15V\G POS5V\G R202 10K U34 3,4 BSP75N FTOR_I\I 3 3 PWRGND CHASSISGND PWRGND SWITCH HE-242334-101921 Figure 2002 (Sheet 19 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2026 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 POS5V\G R203 499 U41 1 R204 4.99K 6 5 2 4 PVG612 3 BTC_LK_CL_I\I PWRGND PWR28V\G A D28 C PWR28V\G CMPD914 K2 Y2 Y1 A3 A2 PSA5_RTN\G VR32 40V A1 B3 B2 B1 X1 X2 1 OUT N_BTC_LKOUT_I\I OUT BTC_LK\I R207 POS5V\G 10K C107 0.01UF 59578 DIGGND1 A POS5V\G D29 C PWR28V\G 5 CHASSISGND CMPD914 R205 499 1 R206 4.99K U42 2 4 PVG612 BTC_LK_TR_I\I 6 5 3 PWRGND HE-242334-101922 Figure 2002 (Sheet 20 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2027 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 MONITOR PWR28V\G POS5V\G R221 24.9K R222 10K U46 C111 0.1UF 4 3 R220 10K 8 6 5 VCC VO GND TP7 SP_OUT1_ON_I\I HCPL-073A PWR15V\G POS5V\G 10K 1 SFH6186 1K C U45 1 3 R216 SP_OUT1_CMD_I\I CMPD914 TP11 2 4.99K D36 4 R217 TP12 DIGGND1 A R218 U43 IN SPARE_OUT1_I\I 3,4 SOURCE R219 4.99K D40 2 DRAIN C112 0.01UF BSP75N SWITCH 3 3 PWRGND MONITOR PWRGND PWR28V\G CHASSISGND POS5V\G R228 24.9K R229 10K U48 C113 0.1UF 4 3 R227 10K VCC VO GND 8 6 5 TP9 SP_OUT2_ON_I\I HCPL-073A PWR15V\G A POS5V\G R225 1 TP8 R224 4.99K 1K CMPD914 C TP10 3 R223 SP_OUT2_CMD_I\I D37 4 2 SFH6186 DIGGND1 10K U44 U47 1 IN DRAIN SOURCE R226 4.99K D41 2 C114 0.01UF BSP75N SWITCH 3 SPARE_OUT2_I\I 3,4 3 PWRGND CHASSISGND PWRGND HE-242334-101923 Figure 2002 (Sheet 21 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2028 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 PWR15V\G SWITCH 1 1 R231 4.99K 4 TP6 2 3 R230 SP_OUT3_CMD_I\I PWR28V\G SFH6186 1K 2 IN 4 ST R233 4.99K U51 BTS409L1 VBB OUT GND 1 TP5 R232 10K U49 3 POS5V\G SPARE_OUT3\I 1 1 MONITOR POS5V\G CMPD914 A C PWRGND 3 C117 0.01UF R238 24.9K D142 R252 200 3 D42 5 5 CHASSISGND 1 D38 R239 C116 0.1UF 10K R240 10K U37 4 3 PWRGND VCC VO GND 8 6 5 TP1 SP_OUT3_ON_I\I HCPL-073A 3 DIGGND1 PWRGND PWR15V\G SWITCH R243 10K U52 1 R242 4.99K 1 4 TP3 2 3 R241 SP_OUT4_CMD_I\I SFH6186 1K R244 4.99K 2 IN 4 ST U53 BTS409L1 VBB OUT GND 1 TP4 PWR28V\G 3 POS5V\G SPARE_OUT4\I MONITOR 1 1 R253 200 3 D43 5 R249 24.9K D141 5 CHASSISGND CMPD914 A C PWRGND D39 1 R250 10K U54 C119 0.1UF 1 2 VCC VO GND 3 PWRGND C120 0.01UF POS5V\G 8 7 5 R251 10K TP2 SP_OUT4_ON_I\I HCPL-073A 3 PWRGND DIGGND1 HE-242334-101924 Figure 2002 (Sheet 22 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2029 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 POS5V\G PWR15V\G R261 499 1 R262 4.99K U55 6 5 2 4 OUT DIS_BIT_15V\I OUT DIS_BIT_GND\I OUT DIS_IN_15V\I PVG612 BIT_15V_CNT_I\I POS5V\G R263 499 1 R264 4.99K U56 6 5 2 4 PVG612 BIT_GND_CNT_I\I 3 PWRGND POS5V\G PWR15V\G R265 499 1 R266 4.99K U57 6 5 2 D46 4 PVG612 DIS_15V_CNT\I HE-242334-101925 Figure 2002 (Sheet 23 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2030 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 DIS_BIT_GND\I POS5V\G R275 10K U58 DIS_IN_15V\I CTR_STRG3\I R271 R272 4.99K 4.99K C C127 0.1UF D51 1 2 R274 4.99K A CMPD914 HCPL-073A R273 C126 0.01UF 8 7 5 VCC VO GND D52 A 1 DIGGND1 C CMPD914 10K 5 CHASSISGND POS5V\G R280 10K U58 R276 R277 4.99K 4.99K C CLOG_FILTER_I\I VR46 C129 0.1UF D53 A 8 6 5 VCC VO GND HCPL-073A CMPD914 R278 C128 0.01UF 40V 4 3 R279 4.99K A D54 1 DIGGND1 C CMPD914 10K POS5V\G 5 CHASSISGND CTR_STRG1\I R281 R282 4.99K 4.99K R285 10K U59 D55 C C131 0.1UF R284 4.99K A 4 3 8 6 5 VCC VO GND HCPL-073A CMPD914 R283 C130 0.01UF D56 A 1 U60 DIGGND1 C CMPD914 10K POS5V\G 5 CHASSISGND R286 R287 4.99K 4.99K C D57 C133 0.1UF R289 4.99K 1 2 A 8 7 5 VCC VO GND Y3 12 6 A2 Y2 14 9 4 A1 Y1 16 10 2 A0 Y0 18 11 8 OE HCPL-073A CMPD914 8 DATA_BUS<15..0>\I 1 1 CTR_STRG2\I R290 10K U46 IO 244 A3 R288 C132 0.01UF A D58 DIGGND1 C CMPD914 10K POS5V\G 5 CHASSISGND GLC_CLOSED_I\I U59 R291 R292 4.99K 4.99K C D59 C135 0.1UF A CMPD914 1 2 8 7 5 VCC VO GND R297 HCPL-073A R293 C134 0.01UF R294 4.99K 10K A D60 C U60 R295 10K 1 POS5V\G DIGGND1 CMPD914 10K R299 R298 10K 11 244 A3 Y3 9 12 13 A2 Y2 7 13 15 A1 Y1 5 14 17 A0 Y0 3 15 10K 19 5 CHASSISGND OE R296 RD020624_I\I 1K HE-242334-101926 Figure 2002 (Sheet 24 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2031 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 DIS_BIT_GND\I POS5V\G R310 10K U61 DIS_IN_15V\I R306 R307 4.99K 4.99K BTC_CLOSED_I\I C141 0.01UF D66 C C142 0.1UF 1 2 R309 4.99K A 8 7 5 VCC VO GND HCPL-073A CMPD914 R308 D67 A 10K 1 DIGGND1 C CMPD914 5 CHASSISGND U61 R311 R312 4.99K 4.99K GND_AIR_SW_I\I C C144 0.1UF D68 A 8 6 5 VCC VO GND HCPL-073A CMPD914 C143 0.01UF 4 3 R314 4.99K R313 A 10K D69 IO POS5V\G R315 10K 1 DIGGND1 C 8 244 A3 Y3 12 0 6 A2 Y2 14 1 4 A1 Y1 16 2 2 A0 Y0 18 3 CMPD914 OE POS5V\G R320 10K U62 R317 4.99K 4.99K C145 0.01UF D70 C R319 4.99K A 1 2 8 7 5 VCC VO GND HCPL-073A CMPD914 R318 D71 A 10K 1 U67 DIGGND1 C CMPD914 5 CHASSISGND POS5V\G R325 10K U63 R321 R322 4.99K 4.99K PIN_PRG_D_I\I C147 0.01UF D72 C C148 0.1UF R324 4.99K 1 2 A VCC VO GND 8 7 5 HCPL-073A CMPD914 R323 A 10K D73 11 244 A3 Y3 9 4 13 A2 Y2 7 5 15 A1 Y1 5 6 17 A0 Y0 3 7 OE 1 19 R316 FUEL_CUTOFF_I\I C146 0.1UF 1 5 CHASSISGND DATA_BUS<15..0>\I U67 DIGGND1 C CMPD914 POS5V\G 5 CHASSISGND U64 R326 R327 4.99K 4.99K PIN_PRG_E_I\I C149 0.01UF R330 10K C D74 C150 0.1UF A R329 4.99K 1 2 VCC VO GND HCPL-073A CMPD914 R328 10K A D75 C 8 7 5 1 DIGGND1 CMPD914 5 CHASSISGND A B C D E F TO SHEET 26 HE-242334-101927 Figure 2002 (Sheet 25 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2032 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 TO SHEET 25 A B NOT INSTALLED R331 A DIS_BIT_15V\I 10K R332 D76 CMPD914 C151 0.01UF 4.99K A D77 C C152 0.1UF 1 2 R334 4.99K 10K D79 POS5V\G 8 7 5 VCC VO GND OUT DIGGND1 D81 A C C CMPD914 CMPD914 R337 R338 PIN_PRG_F\I 4.99K WD_RESET_I\I 1 3 PWRGND A F HCPL-073A 5 CHASSISGND R336 E R335 10K U65 CMPD914 D NOT_INSTALLED C CMPD914 R333 GCS_OFF\I 4.99K D78 A NOT_INSTALLED C C 4.99K A D80 C POS5V\G R340 10K U66 CMPD914 C154 0.1UF C153 0.01UF 4 3 R339 4.99K 8 6 5 VCC VO GND HCPL-073A 5 CHASSISGND 1 3 DIGGND1 PWRGND POS5V\G R345 10K U62 R341 R342 4.99K 4.99K C DISC_STS_I\I D82 C156 0.1UF A CMPD914 C155 0.01UF R343 4.99K 4 3 8 6 5 VCC VO GND HCPL-073A R344 10K A D83 C 1 DIGGND1 CMPD914 5 CHASSISGND R346 RD02062C_I\I 1K COMMON DISCRETE 1 INPUTS HE-242334-101928 Figure 2002 (Sheet 26 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2033 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 DIS_BIT_GND\I POS5V\G DIS_IN_15V\I R355 10K U64 R351 R352 4.99K 4.99K PIN_PRG_C_I\I C162 0.1UF D91 C R354 4.99K 4 3 A 8 6 5 VCC VO GND HCPL-073A CMPD914 R353 C161 0.01UF D92 A 1 DIGGND1 C CMPD914 10K U70 5 CHASSISGND POS5V\G R360 10K U66 R356 R357 4.99K 4.99K D93 C PIN_PRG_PAR_I\I C164 0.1UF 1 2 R359 4.99K 8 7 5 A VCC VO GND HCPL-073A CMPD914 R358 C163 0.01UF A D94 1 DIGGND1 C DATA_BUS<15..0>\I 8 244 A3 Y3 12 0 6 A2 Y2 14 1 4 A1 Y1 16 2 2 A0 Y0 18 3 IO OE CMPD914 1 10K POS5V\G 5 CHASSISGND R361 R362 4.99K 4.99K C LOW_OIL_I\I C166 0.1UF D95 R364 4.99K 1 2 A 8 7 5 VCC VO GND HCPL-073A CMPD914 R363 C165 0.01UF VR51 40V R365 10K U48 A D96 1 DIGGND1 C U70 CMPD914 10K POS5V\G R366 R367 4.99K 4.99K PIN_PRG_B_I\I C167 0.01UF R370 10K U63 C D97 C168 0.1UF A R369 4.99K 4 3 8 6 5 VCC VO GND R368 10K A D98 C 9 4 A2 Y2 7 5 15 A1 Y1 5 6 17 A0 Y0 3 7 OE HCPL-073A CMPD914 Y3 13 1 19 5 CHASSISGND 11 244 A3 DIGGND1 CMPD914 5 CHASSISGND A B C D E F G TO SHEET 28 HE-242334-101929 Figure 2002 (Sheet 27 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2034 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 TO SHEET 27 A NOT INSTALLED R371 A DIS_BIT_15V\I 10K R372 B CMPD914 E F G CMPD914 R373 D100 A GCS_ON\I 4.99K D NOT INSTALLED C D101 A NOT INSTALLED C D99 C 4.99K POS5V\G C R375 10K U65 CMPD914 C170 0.1UF C169 0.01UF R374 4.99K 4 3 8 6 5 VCC VO GND HCPL-073A 5 CHASSISGND 1 3 DIGGND1 PWRGND POS5V\G R380 10K U68 R376 R377 4.99K 4.99K C PIN_PRG_A_I\I D102 C172 0.1UF R379 4.99K A 4 3 8 6 5 VCC VO GND HCPL-073A CMPD914 R378 C171 0.01UF A D103 1 DIGGND1 C CMPD914 10K POS5V\G PWR15V\G 5 CHASSISGND R381 4.99K PWR15V\G 1 2 R382 10K R383 10K U68 VCC VO GND R384 4.99K 8 7 5 1 U69 2 HCPL-073A R385 2K 6 5 4 PVG612 DIGGND1 DIGGND1 OUT LFM\I TEST_EN_I\I R386 R387 TEST_EN_RTN\I 200 200 C173 0.01UF 5 CHASSISGND FTOR_ON_I\I R389 RD020624_I\I 1K HE-242334-101930 Figure 2002 (Sheet 28 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2035 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 MICROCIRCUIT U73 GLY_SHED_ON\I DISC_LMP_ON_I\I POS5V\G R417 10K BTC_LK\I IO 8 244 A3 Y3 12 0 6 A2 Y2 14 1 4 A1 Y1 16 2 2 A0 Y0 18 3 DATA_BUS<15..0>\I OE 1 DIS_BIT_GND\I R401 A DIS_BIT_15V\I 10K R402 D106 D108 A C C MICROCIRCUIT CMPD914 CMPD914 R403 DIS_SW\I 4.99K 4.99K A D107 POS5V\G C R405 10K U71 CMPD914 C182 0.1UF C181 0.01UF 4 3 R404 4.99K VCC VO GND 8 6 5 R418 POS5V\G 10K HCPL-073A R406 10K A R407 1 3 D111 A C Y3 9 4 13 A2 Y2 7 5 15 A1 Y1 5 6 17 A0 Y0 3 7 OE C CMPD914 R408 FIRE_SW\I 4.99K 244 A3 DIGGND1 PWRGND CMPD914 11 19 5 CHASSISGND D109 U73 4.99K A D110 POS5V\G C U72 CMPD914 C184 0.1UF C183 0.01UF 4 3 R409 4.99K VCC VO GND R410 10K 8 6 5 HCPL-073A 5 CHASSISGND R411 10K A R412 D112 PWRGND A C CMPD914 4.99K 253P 5 CHASSISGND DIGGND1 D114 C CMPD914 R413 S2_IN\I VR56 40V 1 3 4.99K A D113 POS5V\G C R415 10K U71 CMPD914 C186 0.1UF C185 0.01UF R414 4.99K 1 2 VCC VO GND 8 7 5 HCPL-073A 1 3 5 CHASSISGND DIGGND1 PWRGND R416 RD020620_I\I 1K HE-242334-101931 Figure 2002 (Sheet 29 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2036 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 DIS_BIT_GND\I POS5V\G R430 10K U74 DIS_IN_15V\I R426 R427 4.99K 4.99K SPARE_IN1_I\I C C192 0.1UF D121 1 2 R429 4.99K A CMPD914 HCPL-073A R428 C191 0.01UF 8 7 5 VCC VO GND D122 A 1 DIGGND1 C CMPD914 10K 5 CHASSISGND POS5V\G R435 10K U74 SPARE_IN2_I\I R431 R432 4.99K 4.99K D123 C C194 0.1UF 4 3 R434 4.99K A 8 6 5 VCC VO GND HCPL-073A CMPD914 R433 C193 0.01UF A D124 C 1 DIGGND1 CMPD914 10K POS5V\G 5 CHASSISGND R440 10K U24 R436 R437 4.99K 4.99K SPARE_IN3_I\I C195 0.01UF C D125 CMPD914 C196 0.1UF A R439 4.99K 1 2 8 7 5 VCC VO GND HCPL-073A R438 10K A D126 C 1 DIGGND1 CMPD914 5 CHASSISGND A B C D TO SHEET 31 HE-242334-101932 Figure 2002 (Sheet 30 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2037 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 TO SHEET 30 A B C D U77 Y3 12 6 A2 Y2 14 9 4 A1 Y1 16 10 A DIS_BIT_15V\I 10K R442 D127 CMPD914 C 2 A0 Y0 18 11 CMPD914 R443 SPARE_IN4\I 4.99K D129 A C 4.99K A D128 OE POS5V\G C R445 10K U72 CMPD914 C198 0.1UF C197 0.01UF R444 4.99K 1 2 VCC VO GND 8 7 5 HCPL-073A 5 CHASSISGND 10K R447 A D130 PWRGND C CMPD914 C CMPD914 R448 SPARE_IN5\I 4.99K DIGGND1 D132 A 4.99K A D131 POS5V\G C C200 0.1UF C199 0.01UF R449 4.99K 4 3 VCC VO GND POS5V\G R450 10K U54 CMPD914 R451 8 6 5 10K 11 244 A3 Y3 9 12 13 A2 Y2 7 13 15 A1 Y1 5 14 17 A0 Y0 3 15 OE 19 R446 U77 1 3 DATA_BUS<15..0>\I 8 1 R441 IO 244 A3 8 HCPL-073A 5 CHASSISGND 3 PWRGND 1 DIGGND1 SP_OUT1_ON_I\I SP_OUT2_ON_I\I R452 RD020620_I\I 1K HE-242334-101933 Figure 2002 (Sheet 31 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2038 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 PWR15V\G PWR15V\G R466 10K R468 4.99K VR63 5.1V R467 249K PWRGND R465 AR10 5 8 3 B 3 2 S/B 1 V- LM211 3 6 4 10K V+ 7 PWRGND 10K D137 4 R462 10K 2 + - + PWRN15V\G PWRN15V\G A429_RXA\I VCC VO GND 8 6 5 OUT A429_RXA_L\I HCPL2232 R472 4.99K R469 10K 3 PWRGND 1 DIGGND1 R471 5 CHASSISGND 249K R464 10K 10K VR64 5.1V PWR15V\G 3 D139 PWRGND R470 10K AR11 5 8 R463 RX_429_NEG\I D138 OUT U78 4 3 PWRGND VR61 9V 8 7 5 HCPL2232 PWR15V\G 3 VCC VO GND 1 LT1214 13 3 RX_429_POS\I D136 1 2 PWR15V\G I91 AR9 R461 POS5V\G U78 PWRN15V\G 3 B 2 S/B 6 4 VR62 9V V+ 7 1 V- LM211 3 PWRGND PWRN15V\G 5 CHASSISGND HE-242334-101934 Figure 2002 (Sheet 32 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2039 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 C206 0.1UF C207 0.1UF C208 0.1UF C209 0.1UF C210 0.1UF C211 0.1UF C212 0.1UF C213 0.1UF C215 0.1UF C216 0.1UF 82 J1 27 J1 67 J1 108 PWR5V\G C276 0.1UF 2 1 ANAGND1 C218 0.1UF C229 0.1UF C230 0.1UF C240 0.1UF C221 0.1UF C231 0.1UF C241 0.1UF C222 0.1UF C232 0.1UF C242 0.1UF C223 0.1UF C233 0.1UF C243 0.1UF C224 0.1UF C234 0.1UF C244 0.1UF C225 0.1UF C235 0.1UF C245 0.1UF C226 0.1UF C236 0.1UF C246 0.1UF C227 0.1UF C237 0.1UF C247 0.1UF C238 0.1UF C248 0.1UF C282 0.1UF 1 J1 26 J1 66 J1 107 POS15V\G C249 0.1UF C250 0.1UF C256 0.1UF J1 25 J1 65 J1 106 J1 39 J1 120 C251 0.1UF C257 0.1UF C252 0.1UF C258 0.1UF 40 J1 80 J1 121 J1 38 J1 119 J1 41 J1 81 J1 122 C253 0.1UF C259 0.1UF C254 0.1UF C260 0.1UF C255 0.1UF C261 0.1UF C265 0.1UF C262 0.1UF C270 0.1UF 2 ANAGND1 NEG15V\G L6 1 2 PWR15V\G 1UH C263 0.1UF J1 DIGGND1 C264 0.1UF C266 0.1UF C267 0.1UF 3 P1 54 A2_UNUSED_PIN6 P1 24 A2_UNUSED_PIN5 P1 57 A2_UNUSED_PIN4 P1 95 A2_UNUSED_PIN3 P1 13 A2_UNUSED_PIN2 P1 16 A2_UNUSED_PIN1 J1 29 A2A5_SP2 J1 28 A2A5_SP1 J1 76 A2A7_SP1 J1 98 BOARD_SP12 J1 97 BOARD_SP11 J1 96 BOARD_SP10 J1 7 BOARD_SP9 J1 6 BOARD_SP8 J1 5 BOARD_SP7 J1 4 BOARD_SP6 J1 30 BOARD_SP5 J1 31 BOARD_SP4 3 P1 J1 109 BOARD_SP3 6 P1 J1 117 BOARD_SP2 9 P1 J1 74 BOARD_SP1 10 P1 J1 118 A2_UNUSED_PIN10 17 P1 J1 104 A2_UNUSED_PIN9 18 P1 J1 84 A2_UNUSED_PIN8 19 P1 J1 79 A2_UNUSED_PIN7 20 P1 J1 75 A2_UNUSED_PIN6 21 P1 J1 64 A2_UNUSED_PIN5 22 P1 J1 44 A2_UNUSED_PIN4 43 P1 J1 37 A2_UNUSED_PIN3 84 P1 J1 36 A2_UNUSED_PIN2 14 P1 J1 3 A2_UNUSED_PIN1 15 P1 J1 14 FREQ_OUT_1 55 P1 J1 1 VREF PWRGND R481 106 P1 4.99K C278 0.01UF NOT INSTALLED CHASSISGND CHASSIS CHASSISGND PSA5_RTN\G L7 POS15V\G 1UH C268 0.1UF C269 0.1UF C271 0.1UF C272 0.1UF 3 3 PWRGND 5 L9 AR8 4 5 14 6 6 AR8 TL074 7 10 AR8 9 TL074 8 12 13 AR9 TL074 12 14 11 + - + 10 LT1214 PWR28V\G 1UH C273 0.1UF C279 220UF 14 U1 PWRN15V\G 1UH PWR15V\G U1 L8 + GCS_28V_CMD PWR28V\G 13 C239 0.1UF C220 0.1UF 4 C228 0.1UF C219 0.1UF DIGGND1 11 C217 0.1UF C277 0.1UF 4 83 J1 4 J1 42 J1 POS5V\G 11 43 4 2 J1 11 J1 + C280 220UF + C274 0.1UF C275 0.1UF 1 DIGGND1 3 2 ANAGND1 NEG15V\G PWRGND PWRN15V\G C281 220UF 3 HE-242334-101935 PWRGND Figure 2002 (Sheet 33 of 34) Printed Wiring Board Assembly A2 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2040 Jun 6/14 U78 LM211 LM211 17 17 20 20 20 20 U8 U9 U11 U12 U13 U14 U15 HCPL-2232 DD-03182 DG202B DD-03182 74ACT244 74ACT244 74AC273 74AC273 5 5 5 6 6 6 6 24-23-34 U17 U18 U19 U20 U21 U22 74FCT240 74FCT240 74FCT240 74AC139 74AC139 HCPL-073A HCPL-073A HCPL-073A 74FCT240 HCPL-073A HCPL-073A HCPL-073A HCPL-073A HCPL-073A 6 6 6 6 6 6 7,16 7,8 7,9 8,9 8,10 6 10,12 10,14 10,16 12 12 UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. Subject to the EAR - See the Title, First, or Cover Page for more information. SCHEMATICS AND WIRING DIAGRAMS Page 2041 Jun 6/14 Figure 2002 (Sheet 34 of 34) Printed Wiring Board Assembly A2 Schematic R507 T26 TP30 C283 AR11 P1 FB24 L9 Q1 D142 J1 VR64 HIGHEST REFERENCE DESIGNATIONS U73 U78 K2 8 U72 U77 8 U71 74ACT244 20 U70 HCPL-2232 8 U68 16 20 U67 16 8 U66 U74 8 U65 HCPL-073A 8 U64 8 20 8 20 8 U63 16 14 8 U62 74ACT244 HCPL-073A 13 8 U61 15 74ACT244 13,14 20 U60 HCPL-073A HCPL-073A 13,14 8 U59 15,16 HCPL-073A 13,14 8 U58 74ACT244 HCPL-073A 13,14 8 HCPL-073A HCPL-073A 13 8 8 U54 15 HCPL-073A 13 8 20 U48 U46 U38 14 74ACT244 HCPL-073A 12 U34 HCPL-073A U37 8 U29 HCPL-073A 8 8 8 16 16 20 20 20 20 20 8 U28 U24 U16 74AC273 74FCT240 6 U7 1,6 5 U1 5 U5 74ACT14 NHI-1567 2,5,7,10 AR9 7 AR11 LT1214 7,4,17,18 9 2,8 5 7 2,8 4 1 1 POWER GROUND 7 PWR28VDC C187-C190 D1-D5 D31-D35 D61-D65 D105 C174-C180 C214 D23-D25 D47-D50 D104 R25-R30 FB10 R55-R60 L2-L5 FB19 C136-C140 C121-C125 D133-D135 C115 C82-C90 C33-C40 C108-C110 C71-C75 C14-C20 REFERENCE DESIGNATIONS NOT USED 5 10 5 10 5 5 10 5 10 5 5 5 5 5 5 10 5 5 5 5 5 10 5 5 5 5 R62 FB20 FB9 D115-D120 VR57-VR60 T17-T20 D82-D90 VR52-VR55 VR7-VR10 U50 D44,D45 VR33-VR45 R482-R489 R473-R480 R453-R460 D7-D9 VR15-VR31 R419-R425 R390-R400 R347-R350 C201-C205 VR47-VR50 R300-R305 R245-R248 R267-R270 R254-R260 C157-C160 R187-R190 R163-R165 R236,R237 R134-R140 R117-R120 R208-R215 R126 R84-R90 C118 C98-C100 R76, R77 C211 C242 C239 C241 C235 C232 C246 C228 C247 C227 C226 C225 C224 C223 C222 C248 C221 C220 C215 C213 C212 C282 C210 C206 C230 C233 C234 C216 5 C218 C243 C238 C237 C236 C229 C217 C244 C231 C263,C268,C277 C264,C269 C57,C58,C276 C208,C209 C219 C267,C272,C275 C266,C271,C274 C207 C255,C262 C252,C259 C254,C261 C253,C260 C265,C270 C251,C258 C250,C257 C249,C256 DECOUPLING CAPS 8 REFERENCE DESIGNATIONS NOT USED 9 13 4 4 8 8 13 PWR N15VDC 4 PWR15VDC 8 C48-C50 16 16 PWR5VDC C245 11 4 4 4 4 11 11 11 ANALOG GROUND 10 10 10 10 10 10 10 10 10 5 5,10 AR10 TL074 4 7 AR7 INA117 4 4,18 AR8 7 AR6 14 AR4 INA117 4 4 8 AR3 7 INA117 4 4 1 4 POS15VDC NEG15VDC AR1 POS5VDC MICROCIRCUIT POWER TABLE DIGITAL GROUND AR2 REF DES NUMBER AR5 TL074 LM211 2 TL074 2,3 TL074 2,3 PART NUMBER 2,3 SCHEMATIC PAGE NUMBER HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2002 HE-242334-101936 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2003 HE-242334-101937 Figure 2003 (Sheet 1 of 10) Printed Wiring Board Assembly A3 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2042 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2003 HE-242334-101938 Figure 2003 (Sheet 2 of 10) Printed Wiring Board Assembly A3 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2043 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2003 HE-242334-101939 Figure 2003 (Sheet 3 of 10) Printed Wiring Board Assembly A3 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2044 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2003 HE-242334-101940 Figure 2003 (Sheet 4 of 10) Printed Wiring Board Assembly A3 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2045 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2003 HE-242334-101941 Figure 2003 (Sheet 5 of 10) Printed Wiring Board Assembly A3 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2046 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2003 HE-242334-101942 Figure 2003 (Sheet 6 of 10) Printed Wiring Board Assembly A3 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2047 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2003 HE-242334-101943 Figure 2003 (Sheet 7 of 10) Printed Wiring Board Assembly A3 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2048 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2003 HE-242334-101944 NOTE: C52 NOT INSTALLED ON 771887B AND 771887C CONFIGURATIONS. Figure 2003 (Sheet 8 of 10) Printed Wiring Board Assembly A3 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2049 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2003 HE-242334-101945 Figure 2003 (Sheet 9 of 10) Printed Wiring Board Assembly A3 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2050 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2003 CONFIGURATIONS 771887B AND 771887C CONFIGURATION 771887D HE-242334-101946 Figure 2003 (Sheet 10 of 10) Printed Wiring Board Assembly A3 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2051 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101947 Figure 2004 (Sheet 1 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2052 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101948 Figure 2004 (Sheet 2 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2053 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101949 Figure 2004 (Sheet 3 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2054 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101950 Figure 2004 (Sheet 4 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2055 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101951 1700678C CONFIGURATION ONLY Figure 2004 (Sheet 5 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2056 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101952 Figure 2004 (Sheet 6 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2057 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 NOTE: 5914419-1 IS USED AT T1 FOR 1700678B AND 1700678C CONFIGURATIONS. Figure 2004 (Sheet 7 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2058 Jun 6/14 HE-242334-101953 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101954 Figure 2004 (Sheet 8 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2059 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101955 Figure 2004 (Sheet 9 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2060 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101956 Figure 2004 (Sheet 10 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2061 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101957 Figure 2004 (Sheet 11 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2062 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101958 Figure 2004 (Sheet 12 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2063 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2004 HE-242334-101959 Figure 2004 (Sheet 13 of 13) Printed Wiring Board Assembly A4 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2064 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 HE-242334-101960 Figure 2005 (Sheet 1 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2065 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 HE-242334-101961 Figure 2005 (Sheet 2 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2066 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 HE-242334-101962 Figure 2005 (Sheet 3 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2067 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 HE-242334-101963 Figure 2005 (Sheet 4 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2068 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 HE-242334-101964 Figure 2005 (Sheet 5 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2069 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 HE-242334-101965 Figure 2005 (Sheet 6 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2070 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 HE-242334-101966 Figure 2005 (Sheet 7 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2071 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 HE-242334-101967 Figure 2005 (Sheet 8 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2072 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 XA2P1 XA2P1 P1 AG5 P1 AJ5 P1 BG6 P1 BG5 P1 SYNC_D2 AA2 P1 AA1 P1 AC4 P1 AG4 P1 AE5 P1 AE3 P1 AE2 P1 AJ4 P1 AC7 P1 AA5 GLY_SHD_1A* GLY_SHD_2B* AG1 P1 AJ1 P1 AC2 P1 BJ7 P1 BK7 P1 BG8 P1 BJ6 P1 BJ5 P1 BJ4 P1 BJ3 P1 AK14 P1 AK15 P1 BG3 P1 BG7 P1 AJ2 P1 BJ8 P1 BH8 P1 BK8 XA2P1 XA2P1 30 XA2P1 32 XA2P1 34 XA2P1 64 NBPT_D2* (GAPCU ONLY) 65 XA2P1 NBPT_D1* BTC_CLOSE PIN_PRG_A* PIN_PRG_B* PIN_PRG_C* PIN_PRG_D* IDG_WRN* PIN_PRG_F PIN_PRG_PAR* CTR_STRG1 AE1 P1 111 (GAPCU ONLY) 71 GLY_SHD_2A* BG4 P1 P1 SYNC_D1 CTR_STRG2 CTR_STRG3 GND_AIR_SW* TEST_EN* TEST_EN_RTN B_SYNCMC* SPARE_IN1* SPARE_IN2* SPARE_IN3* SPARE_IN4 SPARE_OUT1* SPARE_OUT2* SPARE_OUT3* SPARE_OUT4* DISC_SW TST_LNK_POS TST_LNK_NEG XA2P1 103 XA2P1 109 XA2P1 66 XA2P1 67 XA2P1 68 XA2P1 73 XA2P1 100 XA2P1 61 XA2P1 108 XA2P1 110 XA2P1 112 XA2P1 105 XA2P1 27 XA2P1 28 XA2P1 23 XA2P1 29 XA2P1 31 XA2P1 33 XA2P1 35 XA2P1 39 XA2P1 38 XA2P1 36 XA2P1 37 XA2P1 72 XA2P1 26 XA2P1 25 XA2P1 TST LNK SHIELD 5 CHASSISGND P1 LRU_TST_APOS 75 (GAPCU ONLY) LRU_TST_ANEG 115 AJ7 P1 AH7 P1 AK7 XA2P1 (GAPCU ONLY) P1 XA2P1 XA2P1 LRU TST SHIELD 5 P1 CHASSISGND LRU_A1_POS AE11 (GAPCU ONLY) 79 (GAPCU ONLY) 119 LRU_A1_NEG P1 AE12 P1 AE10 P1 CHASSISGND LRU_A2_POS AF11 (GAPCU ONLY) LRU_A2_NEG (GAPCU ONLY) XA2P1 S2_IN AA6 P1 AC5 P1 AC6 P1 AA8 P1 AA7 P1 AA9 FTOR* UNDERSPEED* PIN_PRG_E* DISC_LAMP* BTC_LKOUT* XA2P1 60 XA2P1 102 XA2P1 101 XA2P1 58 XA2P1 59 XA2P1 98 XA2P1 P1 AF12 P1 AF13 P1 AH12 P1 AK12 80 XA2P1 120 XA2P1 P1 LRU_A3_POS (GAPCU ONLY) LRU_A3_NEG (GAPCU ONLY) 41 XA2P1 122 XA2P1 P1 AF7 P1 AF6 XA2P1 121 XA2P1 P1 P1 AH8 P1 AK8 77 XA2P1 117 XA2P1 P1 P1 AK6 XA2P1 78 XA2P1 118 XA2P1 C31 0.01UF FUEL_CUTOFF* CHASSISGND 99 XA2P1 P1 5 GCS_ON AG2 CHASSISGND 70 XA2P1 P1 C37 0.01UF 5 76 XA2P1 116 XA2P1 P1 5 GCS_OFF AE4 107 XA2P1 P1 CHASSISGND AE9 RX 429 SHIELD 5 C36 0.01UF TX2 429 SHIELD RX_429_NEG AE7 C29 0.01UF NOT INSTALLED CHASSISGND TX2_429_NEG RX_429_POS AE8 C30 0.01UF NOT INSTALLED TX1 429 SHIELD TX2_429_POS GCS_28V_CMD AC1 5 TX1_429_NEG CHASSISGND 5 CHASSISGND LRU_SER_APOS AJ6 P1 P1 5 AC8 5 AH6 XA2P1 CHASSISGND CHASSISGND P1 40 C38 0.01UF 5 P1 SPARE_IN5 AK13 5 TX1_429_POS CHASSISGND AJ8 106 5 CHASSISGND LRU A4 SHIELD AF8 XA2P1 C32 0.01UF CHASSISGND 81 DISC_STS* AG3 C39 0.01UF CHASSISGND P1 P1 C40 0.01UF 5 P1 XA2P1 LRU A3 SHIELD (GAPCU ONLY) AK11 113 5 LRU_A4_NEG P1 FIRE_SW AJ3 CHASSISGND CHASSISGND (GAPCU ONLY) AH11 69 5 CHASSISGND LRU_A4_POS AJ11 P1 XA2P1 C33 0.01UF 5 P1 CLOG_FILTER* AA3 XA2P1 CHASSISGND P1 63 5 LRU A2 SHIELD AJ12 XA2P1 CHASSISGND LRU A1 SHIELD 5 P1 62 C34 0.01UF 5 P1 LOW_OIL AA4 LRU_SER_ANEG 74 XA2P1 114 XA2P1 LRU SER SHIELD P1 GLC_CLOSED* AC3 104 XA2P1 C35 0.01UF 5 5 CHASSISGND CHASSISGND HE-242334-101968 Figure 2005 (Sheet 9 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2073 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 XA4P1 P1 C12 EX_FLD_POS C1 0.01UF NOT INSTALLED XA4P1 13 XA4P1 P1 C4 PSU28V 4 XA4P1 25 XA4P1 34 XA4P1 46 XA4P1 54 XA4P1 P1 5 BJ10 PR_2A CHASSISGND P1 P1 C13 EX_FLD_NEG C2 0.01UF NOT INSTALLED 15 XA4P1 35 XA4P1 36 XA4P1 56 XA4P1 5 BJ9 P1 BG11 P1 BG9 P1 BG10 PR_3A* PR_1B* PR_1A* C7 EXC/PMG SHIELD P1 BJ11 5 C10 PMG_PHA C3 0.01UF NOT INSTALLED 10 XA4P1 30 XA4P1 50 XA4P1 BG15 P1 BG14 XA4P1 18 XA4P1 62 XA4P1 P1 BH11 SERVO_NEG C7 0.01UF NOT INSTALLED 5 C11 C4 0.01UF NOT INSTALLED 11 XA4P1 31 XA4P1 51 XA4P1 19 XA4P1 39 XA4P1 20 XA4P1 40 XA4P1 P1 PMG_PHC C5 0.01UF NOT INSTALLED BE11 P1 BE12 P1 BC11 P1 BC12 P1 BD14 P1 BE15 P1 BD15 P1 BE14 P1 BB14 P1 BA15 P1 BA14 BH10 SERVO SHIELD P1 BB15 BE8 P1 BE7 P1 C1 P1 C5 EPA_PIN_E P1 BC10 EPA_PIN_F P1 BC9 EPB_PIN_E P1 BC8 EPB_PIN_F P1 BC7 P1 BC3 P1 BA3 P1 BE3 P1 BE4 P1 BC5 P1 BE5 P1 BA5 P1 BE6 P1 BE9 EPA_PHC EPB_PHA EPB_PHB P1 BA10 EPA_CT_PHA EPA_CT_PHB EPA_CT_PHC EPA_CT_COM EPB_CT_PHA EPB_CT_PHB EPB_CT_PHC EPA_PR_2A EPB_PR_2A EPB_CT_COM EPA_SYNC_D1 EPA_SYNC_D2 EPB_SYNC_D1 EPB_SYNC_D2 EPA_5VAC EPB_5VAC EPA_GLSH_1A* EPA_GLSH_2A* EPA_GLSH_2B* EPB_GLSH_1A* EPB_GLSH_2A* EPB_GLSH_2B* SPARE11 HIGHEST REFERENCE DESIGNATIONS C40 9 XA4P1 29 XA4P1 49 XA4P1 P1 BA9 P1 BA8 P1 BA7 EPA_NBPT_D1* P1 XA2P1 XA4P1 E1 NOTE 1 CHASSIS IS CONNECTED USING THE FOIL ON THE PWB ASSEMBLY AND MOUNTING HOLES. NOTE EACH MOUNTING HOLE SHOULD PROVIDE 4 VIA(S) BETWEEN LAYER 1 AND 4. NOTE 2 XA2P1 CONNECTOR 122 PINS 3 ROWS EPA_NBPT_D2* EPB_NBPT_D1* EPB_NBPT_D2* XA4P1 CONNECTOR 62 PINS 3 ROWS P1 ARINC-600 CONNECTOR TYPE 2 CHASSISGND C3 EPB_PR_3A* EPB_PHC 5 P1 EPA_PR_3A* 5 CHASSISGND 5 C9 P1 P1 EPA_PHB CHASSISGND CHASSISGND P1 BG13 XA4P1 5 P1 P1 EPA_PHA CHASSISGND CHASSISGND PMG_PHB BJ13 P1 5 P1 P1 XA4P1 C6 0.01UF NOT INSTALLED CHASSISGND BJ14 XA4P1 38 SERVO_POS P1 41 CHASSISGND P1 BJ15 21 61 PR_3B* P1 XA4P1 33 PSUGND P1 (SAFETY GND) C2 E1 5 XA4P1 26 XA4P1 NOTE: NOTE: 47 XA4P1 SAFETY GROUND IS VIA THE A6 ASSEMBLY AND MECHINCAL STANDOFF FROM THE ARINC600 CONNECTOR SHELL. E1 IS THE MECHINCAL BONDING STRAP (FLEX) MOUNTED TO THE CONTROLLER HOUSHING. 5 CHASSISGND SAFETYGROUND SEC-A 150 #22 FEMALE GAUGE PINS SEC-B 150 #22 FEMALE GAUGE PINS SEC-C 4 #20 MALE GAUGE PINS 4 #12 MALE GAUGE PINS 3 #16 MALE GAUGE PINS 2 # 8 MALE GAUGE PINS TOTAL OF 313 PINS NOTE 3 CHASSIS IS CONNECTED USING THE FOIL ON THE PWB ASSEMBLY AND MOUNTING HARDWARE. HE-242334-101969 Figure 2005 (Sheet 10 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2074 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 XA2P1 P1 POR_PHA AG14 XA2P1 42 XA2P1 P1 AC14 XA2P1 GEN CT SHIELD P1 C8 0.01UF P1 5 P1 CHASSISGND POR_PHB AH15 1 CHASSISGND LINE_CT_PHA1 AB15 48 XA2P1 89 XA2P1 C16 0.01UF XA2P1 C9 0.01UF P1 P1 82 PSA5 P1 CHASSISGND LINE_CT_PHB1 P1 2 XA2P1 83 XA2P1 C11 0.01UF 5 AD14 XA2P1 86 XA2P1 C12 0.01UF AC12 5 CHASSISGND GEN_CT_PHB AE15 P1 7 XA2P1 8 XA2P1 P1 87 XA2P1 XA2P1 5 XA2P1 XA2P1 A2UNUSED_PIN2 A2UNUSED_PIN4 A2UNUSED_PIN5 XA2P1 2 XA4P1 15 XA2P1 23 XA4P1 55 XA2P1 44 XA4P1 13 XA2P1 3 XA4P1 16 XA2P1 6 XA4P1 24 XA2P1 12 XA4P1 54 XA2P1 17 XA4P1 57 XA2P1 24 XA4P1 95 XA2P1 27 XA4P1 32 XA4P1 42 XA4P1 45 XA4P1 48 XA4P1 53 XA4P1 A4UNUSED_PIN1 A4UNUSED_PIN2 A4UNUSED_PIN3 A4UNUSED_PIN4 A4UNUSED_PIN5 A4UNUSED_PIN6 A4UNUSED_PIN7 A4UNUSED_PIN8 56 XA2P1 A4UNUSED_PIN9 A4UNUSED_PIN10 A4UNUSED_PIN11 P1 CHASSISGND 3 XA2P1 7 XA4P1 AD10 6 XA2P1 8 XA4P1 9 XA2P1 14 XA4P1 10 XA2P1 16 XA4P1 17 XA2P1 28 XA4P1 18 XA2P1 37 XA4P1 19 XA2P1 52 XA4P1 20 XA2P1 55 XA4P1 21 XA2P1 57 XA4P1 22 XA2P1 58 XA4P1 43 XA2P1 59 XA4P1 84 XA2P1 60 XA4P1 OIL TMP SHIELD 5 CHASSISGND LINE_CT_PHA2 AB12 52 XA2P1 93 XA2P1 91 XA2P1 C27 0.01UF P1 LINE_CT_PHB2 AA12 OIL_LVL_POS AB13 5 C21 0.01UF 4 A2UNUSED_PIN1 97 A2UNUSED_PIN6 CHASSISGND OIL_TMP_COM AD9 CHASSISGND OIL_LVL_NEG AA13 CHASSISGND P1 5 C15 0.01UF SPARE SHIELD 5 CHASSISGND GEN_CT_COM 14 C26 0.01UF C20 0.01UF XA2P1 XA4P1 XA2P1 5 P1 P1 46 96 C25 0.01UF XA2P1 C14 0.01UF AE14 CHASSISGND OIL_TMP_OUT AC9 XA2P1 5 CHASSISGND GEN_CT_PHC AD15 XA4P1 43 PSA5_RTN A2UNUSED_PIN3 CHASSISGND 44 C13 0.01UF P1 XA2P1 5 85 P1 XA2P1 90 XA4P1 5 P1 P1 49 OIL_TMP_IN AC10 CHASSISGND 45 XA2P1 C24 0.01UF 5 GEN_CT_PHA 12 1 22 5 CHASSISGND LINE_CT_COM1 AB14 POR SHIELD XA2P1 5 P1 C19 0.01UF CHASSISGND P1 XA2P1 C18 0.01UF P1 11 CHASSISGND CHASSISGND LINE_CT_PHC1 AA14 CHASSISGND AF14 XA2P1 88 5 5 P1 47 5 5 CHASSISGND POR_PHN AH14 LINE_CT_COM2 AB11 C23 0.01UF C17 0.01UF C10 0.01UF XA2P1 CHASSISGND AA15 XA2P1 XA2P1 94 5 5 5 53 C22 0.01UF P1 CHASSISGND POR_PHC AG15 LINE_CT_PHC2 AA11 5 51 XA2P1 92 XA2P1 50 XA2P1 C28 0.01UF 5 CHASSISGND 5 CHASSISGND 5 CHASSISGND 5 CHASSISGND 5 CHASSISGND HE-242334-101970 Figure 2005 (Sheet 11 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2075 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 P1 PIN NO XA2P1 PIN NO XA4P1 PIN NO LAYER TRACE WIRE SIZE SIZE 30 29 PR TO ECMU (SAME SIDE) PR_1A* PWRGND 28.5V 32.0V 5.0MA 20.0MA DC 0.0HZ BG10 38 2 .020 24 28 NOT PR TO ECMU PR_1B* PWRGND 28.5V 32.0V 10.0MA 20.0MA DC 0.0HZ BG9 62 5 .020 24 27 PR TO GCS (GEN FLT LT) PR_3B* PWRGND 28.5V 32.0V 30.0MA 100.0MA DC 0.0HZ BG11 18 5 .020 24 26 PR TO ECMU (OPP SIDE) PR_3A* PWRGND 28.5V 32.0V 5.0MA 20.0MA DC 0.0HZ BJ9 61 2 .020 24 25 PR TO GLC COMMAND PR_2A PWRGND 28.5V 32.0V 1.33A 2.73A DC 0.0HZ BJ10 21,41 2 BUS 24 SERVO VALVE SHIELD CHASSIS CHASSIS 0.0HZ BJ11 19,39 5 BUS 22 .15MIN 0.0HZ BH11 20,40 2 BUS 22 .15MIN 2 BUS 18 .25MIN .25MIN IMAX 2.73A FOR 20 SEC. 24 23 BH10 22 SERVO VALVE (+) SERVO_POS ISOGND 28.5V 32.0V 0.0MA 110.0MA DC 21 SERVO VALVE (-) SERVO_NEG ISOGND 28.5V 32.0V 0.0MA 110.0MA DC 1,6 CHASSIS CONNECTION SHIELD 20 19 18 47 PSU GROUND PSUGND PSUGND 28.5V 0.0V 1.25A 6.0A DC 0.0HZ C3 5,26 17 16 46 28VDC BACKUP PSU28V PSUGND 28.5V 32.0V 0.5A 6.0A DC 0.0HZ C4 4,25 5 BUS 22 .25MIN 13 PMG PHASE C PMG_PHC ISOGND 103.0VL-L 134.0VL-L 1.0A 3.0A AC 1600HZ C9 9,29,49 5 BUS 18 .35MIN IMAX 10.0A FAULT RATING 12 PMG PHASE B PMG_PHB ISOGND 103.0VL-L 134.0VL-L 1.0A 3.0A AC 1600HZ C11 11,31,51 5 BUS 18 .35MIN IMAX 10.0A FAULT RATING 11 PMG PHASE A PMG_PHA ISOGND 103.0VL-L 134.0VL-L 1.0A 3.0A AC 1600HZ C10 10,30,50 2 BUS 18 .35MIN IMAX 10.0A FAULT RATING 10 PMG/EXC SHIELD BUS 18 .45MIN IMAX 7.2A FOR 5 SEC. 15 14 CHASSIS C7 SHIELD 1,6 9 8 7 6 36,56 EXCITER FIELD - EX_FLD_NEG ISOGND 140V 140V 1.0A 3.0A SQ WAVE 1600HZ 15,35 C13 5 5 SHIELD 4 3 34,54 EXCITER FIELD + EX_FLD_POS ISOGND 140V 140V NOM VOLTS MAX VOLTS 1.0A 3.0A DC 0.0HZ SIGNAL FREQ P1 XA2P1 XA4P1 CHARAST (B.W.) PIN NO PIN NO PIN NO C12 13,33 2 BUS 18 TRACE WIRE SIZE SIZE .45MIN IMAX 7.2A FOR 5 SEC. 2 SYSTEM IO REFERENCE NAME A5 REFERENCE NAME REFERENCE GND NOM CURRENT MAX CURRENT ARINC NO LAYER COMMENTS PS/VR LINE I/O 1 HE-242334-101971 Figure 2005 (Sheet 12 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2076 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 P1 XA2P1 PIN NO PIN NO 34 XA4P1 PIN NO TRACE WIRE SIZE SIZE 5 .020 24 LAYER 60 59 58 57 GALLEY NOT SHED (ECMU) GLY_SHD_2B* PWRGND 28.5V 32.0V 10.0MA 20.0MA DC 0.0HZ BG4 56 GALLEY SHED (ECMU) GLY_SHD_1A* PWRGND 28.5V 32.0V 10.0MA 20.0MA DC 0.0HZ BG5 32 5 .020 24 55 GALLEY FAULT LIGHT GLY_SHD_2A* PWRGND 28.5V 32.0V 70.0MA 100.0MA DC 0.0HZ BG6 30 5 .020 24 SYNC WDW/PR TO GCS SYNC_D1 PWRGND 28.5V 32.0V 30.0MA 100.0MA DC 0.0HZ AG5 111 2 .020 24 51 LINE CTA COMMON LINE_CT_COM2 0.0V 0.0V 0.0MA 900MA AC 400HZ AB11 11,12 2 BUS 24 .25MIN 50 LINE CTA C2/LINE CTA C LINE_CT_PHC2 LINE_CT_COM2 0.5V 2.5V 261MA 900MA AC 400HZ AA11 53,94 5 BUS 24 .25MIN 49 LINE CTA B2/LINE CTA B LINE_CT_PHB2 LINE_CT_COM2 0.5V 2.5V 261MA 900MA AC 400HZ AA12 51,92 5 BUS 24 .25MIN LINE CTA A2/LINE CTA A LINE_CT_PHA2 LINE_CT_COM2 0.5V 2.5V 261MA 900MA AC 400HZ AB12 52,93 5 BUS 24 .25MIN 46 OPEN CABLE COMMON LINE_CT_COM1 0.0V 0.0V 0.0MA 900MA AC 400HZ AB14 7,8 5 BUS 24 .25MIN 45 LINE CTA C1 LINE_CT_PHC1 LINE_CT_COM1 0.5V 2.5V 261MA 900MA AC 400HZ AA14 49,90 2 BUS 24 .25MIN 44 LINE CTA B1 LINE_CT_PHB1 LINE_CT_COM1 0.5V 2.5V 261MA 900MA AC 400HZ AA15 47,88 2 BUS 24 .25MIN LINE CTA A1/OPN CABLE LINE_CT_PHA1 LINE_CT_COM1 0.5V 2.5V 261MA 900MA AC 400HZ AB15 48,89 2 BUS 24 .25MIN 41 GEN CTA COMMON GEN_CT_COM 0.0V 0.0V 0.0MA 900MA AC 400HZ AE14 4,5 2 BUS 24 .15MIN IMAX @ 5.0 SEC RATING 40 GEN CTA PHASE C GEN_CT_PHC GEN_CT_COM 0.5V 2.5V 231MA 900MA AC 400HZ AD15 46,87 5 BUS 24 .15MIN IMAX @ 5.0 SEC RATING 39 GEN CTA PHASE B GEN_CT_PHB GEN_CT_COM 0.5V 2.5V 231MA 900MA AC 400HZ AE15 44,85 5 BUS 24 .15MIN IMAX @ 5.0 SEC RATING 38 GEN CTA PHASE A GEN_CT_PHA GEN_CT_COM 0.5V 2.5V 231MA 900MA AC 400HZ AD14 45,86 5 BUS 24 .15MIN IMAX @ 5.0 SEC RATING 37 GEN CT SHIELD CHASSIS 35 POR NEUTRAL POR_PHN 0.0V 0.0V 2.0MA 6.0MA AC 400HZ AH14 2,83 5 .020 24 34 POR C VOLTAGE POR_PHC POR_PHN 115.0V 130.0V 2.0MA 6.0MA AC 400HZ AG15 82 2 .020 24 33 POR B VOLTAGE POR_PHB POR_PHN 115.0V 130.0V 2.0MA 6.0MA AC 400HZ AH15 1 2 .020 24 32 POR A VOLTAGE POR_PHA POR_PHN 115.0V 130.0V 2.0MA 6.0MA AC 400HZ AG14 42 2 .020 24 31 POR VOLTAGE SHIELD SIGNAL FREQ P1 XA2P1 XA4P1 TRACE WIRE CHARAST (B.W.) PIN NO PIN NO PIN NO SIZE SIZE 54 53 52 48 47 43 42 CHASSIS SHIELD 1,6 AC14 36 CHASSIS REFERENCE NAME GND 1,6 AF14 NOM VOLTS MAX VOLTS NOM CURRENT MAX CURRENT LAYER COMMENTS PS/VR NAME CHASSIS A5 REFERENCE ARINC NO SYSTEM IO REFERENCE I/O LINE HE-242334-101972 Figure 2005 (Sheet 13 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2077 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 P1 XA2P1 XA4P1 PIN NO PIN NO PIN NO LAYER TRACE WIRE SIZE SIZE 90 GLC CLOSED GLC_CLOSED* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AC3 104 2 .020 24 89 BTC CLOSED BTC_CLOSED* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AC4 103 2 .020 24 FUEL_CUTOFF* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AC8 99 2 .020 24 GND_AIR_SW* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AC2 105 2 .020 24 88 FUEL CUTOFF 87 86 85 GND/AIR 84 83 FIRE SWITCH FIRE_SW PWRGND 28.5V 32.0V 1.0MA 1.5MA DC 0.0HZ AJ3 113 2 .020 24 82 LOW OIL PRESSURE LOW_OIL* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AA4 62 5 .020 24 PIN_PRG_PAR* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AA5 61 5 .020 24 PIN_PRG_F PWRGND 28.5V 32.0V 1.0MA 1.5MA DC 0.0HZ AC7 100 2 .020 24 81 80 PIN PROG PARITY 79 PIN PROG F 78 PIN PROG E PIN_PRG_E* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AA8 58 5 .020 24 77 PIN PROG D PIN_PRG_D* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AE2 68 5 .020 24 76 PIN PROG C PIN_PRG_C* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AE3 67 5 .020 24 75 PIN PROG B PIN_PRG_B* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AE5 66 5 .020 24 74 PIN PROG A PIN_PRG_A* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AG4 109 2 .020 24 69 OIL IN TEMP OIL_TMP_IN OIL_TMP_COM 10.0V 10.0V 10.0MA 20.0MA DC 0.0HZ AC10 96 2 .020 22 68 OIL OUT TEMP OIL_TMP_OUT OIL_TMP_COM 10.0V 10.0V 10.0MA 20.0MA DC 0.0HZ AC9 97 2 .020 22 67 OIL TEMP COMMON OIL_TMP_COM 0.0V 10.0MA 20.0MA DC 0.0HZ AD9 56 5 PLANE 22 66 OIL TEMP SHIELD 73 72 71 70 0.0V CHASSIS CHASSIS 1,6 AD10 SHIELD CHASSIS CONNECTION 65 64 OIL LEVEL SOURCE OIL_LVL_POS PWRGND 0.5V 4.60V 0.0MA 120MA DC 0.0HZ AB13 91 5 BUS 24 63 OIL LEVEL COMMON OIL_LVL_NEG PWRGND 0.5V 4.60V 0.0A 120MA DC 0.0HZ AA13 50 2 BUS 24 A5 REFERENCE NAME REFERENCE GND SIGNAL FREQ P1 XA2P1 XA4P1 TRACE WIRE CHARAST (B.W.) PIN NO PIN NO PIN NO SIZE SIZE 62 SYSTEM IO REFERENCE NAME NOM VOLTS MAX VOLTS NOM CURRENT MAX CURRENT ARINC NO LAYER COMMENTS PS/VR LINE I/O 61 HE-242334-101973 Figure 2005 (Sheet 14 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2078 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 P1 XA2P1 XA4P1 PIN NO PIN NO PIN NO LAYER TRACE WIRE SIZE SIZE 120 119 118 117 116 115 114 113 SYNC_D2 AJ5 71 5 .020 N/A GAPCU ONLY 112 NBPT_D2* AA1 65 5 .020 N/A GAPCU ONLY 112 2 .020 24 111 110 CNTOR STRING 3 (IPT) CTR_STRG3 PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AJ1 109 CNTOR STRING 2 (IPT) CTR_STRG2 PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AG1 110 2 .020 24 108 CNTOR STRING 1 (IPT) CTR_STRG1 PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AE1 108 2 .020 24 105 GLC OPEN REQUEST S2_IN PWRGND 28.5V 32.0V 1.0MA 1.5MA DC 0.0HZ AA6 60 5 .020 24 104 NOT BTC LOCKOUT N_BTC_LKOUT* PWRGND 28.5V 32.0V 0.65A 1.5A DC 0.0HZ AA9 98 2 BUS 22/24 103 IDG OFF LIGHT DISC_LAMP* PWRGND 28.5V 32.0V 30.0MA 100.0MA DC 0.0HZ AA7 59 5 .020 24 102 IDG FAULT LIGHT IDG_WRN* PWRGND 28.5V 32.0V 30.0MA 100.0MA DC 0.0HZ AJ4 73 5 .020 24 107 106 101 IDG DISC STATUS SW DISC_STS* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AG3 69 5 .020 24 100 US (DISC INHIBIT) UNDERSPEED* PWRGND 28.5V 32.0V 40.0MA 100.0MA DC 0.0HZ AC6 101 2 .020 24 NBPT REQUEST (D) NBPT_D1* PWRGND 28.5V 32.0V 5.0MA 20.0MA DC 0.0HZ AA2 64 5 .020 24 97 CLOGGED FILTER CLOG_FILTER* PWRGND 15.0V 15.0V 1.0MA 1.5MA DC 0.0HZ AA3 63 5 .020 24 96 DISCONNECT REQUEST DISC_SW PWRGND 28.5V 32.0V 1.0MA 1.5MA DC 0.0HZ AJ2 72 5 .020 24 93 GCS OFF GCS_OFF PWRGND 28.5V 32.0V 1.0MA 1.5MA DC 0.0HZ AE4 107 2 .020 24 92 GCS ON GCS_ON PWRGND 28.5V 32.0V 1.0MA 1.5MA DC 0.0HZ AG2 70 5 .020 24 91 GCS +28V COMMAND GCS_28V_CMD PWRGND 28.5V 32.0V 2.0MA 3.0MA DC 0.0HZ AC1 106 2 .020 24 MAX VOLTS NOM CURRENT SIGNAL FREQ P1 XA2P1 XA4P1 TRACE WIRE CHARAST (B.W.) PIN NO PIN NO PIN NO SIZE SIZE 99 .15MIN 98 95 SYSTEM IO REFERENCE NAME A5 REFERENCE NAME REFERENCE GND NOM VOLTS MAX CURRENT ARINC NO LAYER COMMENTS PS/VR LINE I/O 94 HE-242334-101974 Figure 2005 (Sheet 15 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2079 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 P1 XA2P1 PIN NO PIN NO 150 XA4P1 PIN NO LAYER TRACE WIRE SIZE SIZE 43 PSA5 149 1,22 GAPCU ONLY 148 147 146 145 SDAC2 429 TX- TX2_429_NEG PWRGND 144 SDAC2 429 TX+ TX2_429_POS PWRGND 143 SDAC2 TX SHIELD CHASSIS CHASSIS 142 SDAC1 429 TX- TX1_429_NEG PWRGND 141 SDAC1 429 TX+ TX1_429_POS PWRGND + 5V - + 40V - AH8 116 2 .020 22/26 AJ8 76 5 .020 22/26 SHIELD 50.0MA 100.0MA AC 100.0KHZ AK8 + 5V - + 40V - 1,6 AF7 117 2 .020 22/26 AF8 77 5 .020 22/26 SHIELD 50.0MA 100.0MA AC 100.0KHZ 140 SDAC1 TX SHIELD CHASSIS CHASSIS AF6 139 FADEC (A) 429 RX(-) RX_429_NEG PWRGND AE7 118 2 .020 22/26 AE8 78 5 .020 22/26 + 5V - + 40V - 1,6 SHIELD 138 FADEC (A) 429 RX(+) RX_429_POS PWRGND 137 FADEC SHIELD CHASSIS CHASSIS 132 LRU 1553 A-(FRU/BITE) LRU_SER_ANEG 131 LRU 1553 A+(FRU/BITE) LRU_SER_APOS 130 LRU 1553 SHIELD CHASSIS CHASSIS SERIAL TEST LINK (-) TST_LNK_NEG DIGGND + 5V - + 5V - 1.0MA 150.0MA AC 19.2KHZ + 5V - + 5V - 1.0MA 150.0MA AC 19.2KHZ 50.0MA 100.0MA AC 100.0KHZ AE9 1,6 136 135 134 133 + 18VP-P - + 27VP-P - AH6 114 2 .020 24 AJ6 74 5 .020 24 5 .020 22 2 .020 22 SHIELD 300.0MA 500.0MA AC 1MHZ AK6 1,6 129 128 127 SERIAL TEST LINK (+) TST_LNK_POS DIGGND 126 SERIAL TEST LINK SHIELD CHASSIS CHASSIS 125 BSYNCMC B_SYNCMC* DIGGND 5.0V 5.25V 5.0V 5.0V NOM VOLTS MAX VOLTS 124 TEST ENABLE RETURN TEST_EN_RTN DIGGND 123 TEST ENABLE TEST_EN* DIGGND BH8 25 BJ8 26 BK8 1,6 1.0MA 1.5MA DC 0.0HZ BG8 23 5 .020 24 5.25V 1.0MA 1.5MA DC 0.0HZ BK7 28 2 .020 24 5.25V 1.0MA 1.5MA DC 0.0HZ BJ7 27 5 .020 24 TRACE WIRE SIZE SIZE 122 121 NAME A5 REFERENCE NAME REFERENCE GND NOM CURRENT MAX CURRENT SIGNAL CHARAST P1 XA2P1 XA4P1 PIN NO PIN NO PIN NO FREQ (B.W.) LAYER COMMENTS PS/VR SYSTEM IO REFERENCE ARINC NO I/O LINE HE-242334-101975 Figure 2005 (Sheet 16 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2080 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 P1 XA2P1 XA4P1 PIN NO PIN NO PIN NO TRACE WIRE SIZE SIZE 1,6 PLANE 22 22 LAYER 180 179 178 SPARE SHIELD 177 176 AE10 1,6 CHASSIS AK7 1,6 CHASSIS AF13 1,6 CHASSIS CHASSIS AK12 1,6 SPARE SHIELD CHASSIS CHASSIS AK11 1,6 SPARE SHIELD CHASSIS CHASSIS AC12 1,6 CHASSIS CHASSIS SPARE SHIELD CHASSIS SPARE SHIELD CHASSIS 175 SPARE SHIELD 174 173 172 43,84 59,60 171 21,22 57,58 170 19,20 52,55 169 17,18 28,37 168 9,10 14,16 C2 3,6 7,8 20.0MA AC5 102 2 .020 167 CHASSIS GROUND CHASSIS(SAFETY GND) CHASSIS AT ARINC DISTRIBUTION ASSY.(A6) 166 165 SPARE 10 FTOR* 28.5V 32.0V 5.0MA 164 SPARE 9 SPARE_OUT4* 28.5V 32.0V 30.0MA 100.0MA BG7 37 2 .020 163 SPARE 8 SPARE_OUT3* 28.5V 32.0V 30.0MA 100.0MA BG3 36 5 .020 162 SPARE 7 SPARE_OUT2* 28.5V 32.0V 30.0MA 100.0MA AK15 38 5 .020 161 SPARE 6 SPARE_OUT1* 28.5V 32.0V 30.0MA 100.0MA AK14 39 2 .020 160 SPARE 5 SPARE_IN5 28.5V 32.0V 1.0MA 1.5MA AK13 40 5 .020 159 SPARE 4 SPARE_IN4 28.5V 32.0V 1.0MA 1.5MA BJ3 35 2 .020 158 SPARE 3 SPARE_IN3* 15.0V 15.0V 1.0MA 1.5MA BJ4 33 2 .020 157 SPARE 2 SPARE_IN2* 15.0V 15.0V 1.0MA 1.5MA BJ5 31 2 .020 22 156 SPARE 1 SPARE_IN1* 15.0V 15.0V 1.0MA 1.5MA BJ6 29 2 .020 22 2 BUS 22 (SPARE EMI CAP) 155 154 153 PSA5_RTN 152 0.0V 0.0V 1.0A 5.0A DC 0.0HZ 55 44 14,15 2,23 INTERNAL BOARD TO BOARD CONNECTION NAME REFERENCE A5 NAME REFERENCE GND NOM VOLTS MAX VOLTS NOM CURRENT MAX CURRENT SIGNAL FREQ P1 CHARAST (B.W.) PIN NO PIN NO PIN NO PS/VR SYSTEM IO REFERENCE I/O NO ARINC 151 LINE XA2P1 XA4P1 LAYER TRACE WIRE SIZE SIZE COMMENTS HE-242334-102454 Figure 2005 (Sheet 17 of 18) Printed Wiring Board Assembly A5 Schematic Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2081 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2005 XA4P1 P1 PIN NO BA7 NOT ROUTED 212 EPB_NBPT_D1* BA8 NOT ROUTED 211 EPA_NBPT_D2* BA9 NOT ROUTED 210 EPA_NBPT_D1* BA10 NOT ROUTED 209 EPB_CT_COM BB15 NOT ROUTED 208 EPB_CT_PHC BA14 NOT ROUTED 207 EPB_CT_PHB BA15 NOT ROUTED 206 EPB_CT_PHA BB14 NOT ROUTED 205 EPA_CT_COM BE14 NOT ROUTED 204 EPA_CT_PHC BD15 NOT ROUTED 203 EPA_CT_PHB BE15 NOT ROUTED 202 EPA_CT_PHA BD14 NOT ROUTED 201 EPB_PIN_F BC12 NOT ROUTED 200 EPB_PIN_E BC11 NOT ROUTED 199 EPA_PIN_F BE12 NOT ROUTED 198 EPA_PIN_E BE11 NOT ROUTED 197 EPB_PHC BG13 NOT ROUTED 196 EPB_PHB BG14 NOT ROUTED 195 EPB_PHA BG15 NOT ROUTED 194 EPA_PHC BJ13 NOT ROUTED 193 EPA_PHB BJ14 NOT ROUTED 192 EPA_PHA BJ15 NOT ROUTED 191 A(ASSY. NO.)UNUSED_PIN11 53 NOT ROUTED 190 A(ASSY. NO.)UNUSED_PIN10 48 NOT ROUTED 189 A(ASSY. NO.)UNUSED_PIN9 45 NOT ROUTED 188 A(ASSY. NO.)UNUSED_PIN8 42 NOT ROUTED 187 A(ASSY. NO.)UNUSED_PIN7 32 NOT ROUTED 186 A(ASSY. NO.)UNUSED_PIN6 95 27 NOT ROUTED 185 A(ASSY. NO.)UNUSED_PIN5 57 24 NOT ROUTED 184 A(ASSY. NO.)UNUSED_PIN4 54 17 NOT ROUTED 183 A(ASSY. NO.)UNUSED_PIN3 24 12 NOT ROUTED 182 A(ASSY. NO.)UNUSED_PIN2 16 6 NOT ROUTED 181 A(ASSY. NO.)UNUSED_PIN1 13 3 NOT ROUTED B P1 PIN NO X(A2)P1 PIN NO X(A4)P1 PIN NO 121 NOT ROUTED GAPCU ONLY LRU_A4_NEG AH11 239 LRU_A4_POS AJ11 81 NOT ROUTED GAPCU ONLY 238 LRU_A3_NEG AH12 122 NOT ROUTED GAPCU ONLY 237 LRU_A3_POS AJ12 41 NOT ROUTED GAPCU ONLY 236 LRU_A2_NEG AF12 120 NOT ROUTED GAPCU ONLY 235 LRU_A2_POS AF11 80 NOT ROUTED GAPCU ONLY 234 LRU_A1_NEG AE12 119 NOT ROUTED GAPCU ONLY 233 LRU_A1_POS AE11 79 NOT ROUTED GAPCU ONLY 232 LRU_TST_ANEG AH7 115 NOT ROUTED GAPCU ONLY 231 LRU_TST_APOS AJ7 75 NOT ROUTED GAPCU ONLY 230 SPARE_11 BE9 NOT ROUTED GAPCU ONLY 229 EPB_GLSH_2B* BE6 NOT ROUTED 228 EPB_GLSH_2A* BA5 NOT ROUTED 227 EPB_GLSH_1A* BE5 NOT ROUTED 226 EPA_GLSH_2B* BC5 NOT ROUTED 225 EPA_GLSH_2A* BE4 NOT ROUTED 224 EPA GLSH_1A* BE3 NOT ROUTED 223 EPB_5VAC BA3 NOT ROUTED 222 EPA_5VAC BC3 NOT ROUTED 221 EPB_SYNC_D2 BC7 NOT ROUTED 220 EPB_SYNC D1 BC8 NOT ROUTED 219 EPA_SYNC_D2 BC9 NOT ROUTED 218 EPA_SYNC_D1 BC10 NOT ROUTED 217 EPB_PR_3A* BE7 NOT ROUTED 216 EPB_PR_2A C5 NOT ROUTED 215 EPA_PR_3A* BE8 NOT ROUTED 214 EPA_PR_2A C1 LINE NO P1 PIN NO SIGNAL REFERENCE NAME A COMMENTS NOT ROUTED X(A2)P1 PIN NO Subject to the EAR - See the Title, First, or Cover Page for more information. SCHEMATICS AND WIRING DIAGRAMS 24-23-34 Page 2082 Jun 6/14 COMMENTS ALL LISTED PIN NUMBERS ARE FOR EACH INDIVIDUAL BOARD ASSEMBLY, AND ARE NOT INTERCONNECTED WHAT IS REPRESENTED BY >(ASSY. NO.)< IS WERE THE SUBSTITUTE NUMBER IS INSERTED, FOR EXAMPLE: Figure 2005 (Sheet 18 of 18) Printed Wiring Board Assembly A5 Schematic X(A4)P1 PIN NO BETWEEN ASSEMBLY(S) AS THE COLUMNS IMPLY. B UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. PIN NO 230 PS/VR SIGNAL REFERENCE NAME I/O LINE NO XA4P1 PIN NO PS/VR EPB_NBPT_D2* XA2P1 PIN NO I/O 213 A6 ARINC A XA2P1 PIN NO A6 ARINC P1 PIN NO A2_UNUSED_PIN2 A4_UNUSED_PIN2 A2_UNUSED_PIN10 HE-242334-102455 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 DISASSEMBLY 30003000 TASK 24-23-34-000-801-A 1. GENERAL INFORMATION FOR DISASSEMBLY Subtask 24-23-34-99F-011-A00 A. General Information (1) This section has the procedures and illustrations necessary to disassemble the GCU. The item numbers in the procedures and illustrations are the same as those in the IPL. NOTE: You can replace an item with its alpha-variant when permitted by the effect code for that item. For example, procedures that apply to item (10) also apply to the alpha-variant items (-10A, -10B, and -10C). (2) Disassemble the GCU only to the level necessary to remove the defective parts. (3) If you see no signs of damage, corrosion, or contamination, do the test for the GCU to find out how much maintenance is necessary. Refer to TESTING AND FAULT ISOLATION. TASK 24-23-34-000-802-A 2. DISASSEMBLY OF THE GCU CAUTION: THE GCU CONTAINS ELECTROSTATIC DEVICES. DO NOT SUBJECT IT TO ELECTROSTATIC, ELECTROMAGNETIC, MAGNETIC, OR RADIOACTIVE FIELDS UNLESS PROTECTED BY A STATIC-SHIELDED CONTAINER. A. Remove the screws (20 and 30, IPL Figure 1) from the cover assembly (10) and chassis assembly (240). B. Use handle (140) and pull cover assembly (10) from chassis assembly (240). C. Remove the A1 through A4 printed wiring board (PWB) assemblies (50 through 80) as follows: (1) Remove screws (220 and 230) and bracket (210). (2) Remove A1 PWB assembly (50) from A2 and A4 PWB assemblies (60 and 80). (3) Use a 5/64-inch ball driver hex wrench to loosen the connector A3J1 (40, IPL Figure 4) jack screws. (4) Remove the A3 PWB assembly (70, IPL Figure 1) from the A1 PWB assembly (50). (5) Use a 3/32-inch ball driver hex wrench to loosen the A2 and A4 PWB assemblies (60 and 80) wedge-lock retainer fasteners. (6) Remove the A2 and A4 PWB assemblies (60 and 80) from the A5 PWB assembly (90). D. Remove the A5 PWB assembly (90) as follows: (1) Remove the screws (100). (2) Remove the nuts (120) and plate (110). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DISASSEMBLY 24-23-34 Page 3001 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (3) Remove flex print from studs (260) and A5 PWB assembly (90) from the chassis assembly (240). (4) Do not disassemble A5 PWB assembly (90) unless damaged. E. If damaged, remove the screws (150), handle (140), and serial-amendment plate (130). F. If damaged, remove the screws (170) and the identification plate (160). G. If damaged, remove the screws (190) and the support hooks (180). H. If damaged, remove the nut (300), flat washer (290), spacer (280), and screw (270) from the chassis assembly (240). I. If damaged, remove warning label (200). J. Do not remove self-clinching nuts (40 and 250) or studs (260). K. Do not remove or damage sponge rubber tape on inside of cover assembly (10). Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DISASSEMBLY 24-23-34 Page 3002 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 CLEANING 40004000 TASK 24-23-34-100-801-A 1. GENERAL INFORMATION FOR CLEANING Subtask 24-23-34-99F-012-A00 A. General Information (1) This section has the procedures and illustrations necessary to clean the GCU. The item numbers in the procedures and illustrations are the same as those in the IPL. NOTE: You can replace an item with its alpha-variant when permitted by the effect code for that item. For example, procedures that apply to item (10) also apply to the alpha-variant items (-10A, -10B, and -10C). (2) Refer to SPM 20-10-01, CLEANING, for general cleaning information. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. CLEANING 24-23-34 Page 4001 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. CLEANING 24-23-34 Page 4002 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 CHECK 50005000 TASK 24-23-34-210-801-A 1. GENERAL INFORMATION FOR CHECK Subtask 24-23-34-99F-013-A00 A. General Information (1) This section has the procedures and illustrations necessary to do the checks to the GCU and its detail parts. The item numbers in the procedures and illustrations are the same as those in the IPL. NOTE: You can replace an item with its alpha-variant when permitted by the effect code for that item. For example, procedures that apply to item (10) also apply to the alpha-variant items (-10A, -10B, and -10C). (2) Visually check all parts for obvious wear or damage. Specific check requirements are listed below. Refer to SPM 20-10-01, CHECK, for general check information. TASK 24-23-34-210-802-A 2. CHECK A. Visually check all parts for scratches, corrosion, nicks, cracks, foreign matter, breaks, or obvious wear. B. Check all threaded surfaces for cross-threading, stripping, chipping, or foreign matter. C. Check identification and serial number plates for legible printing. D. Check flex print for cracked or burned insulation or broken traces. E. Check the connectors for loose, corroded, or bent pins, and loose conductive material between pins. F. Check printed wiring boards for evidence of overheating, physical damage, shorts or cracks in the printed wiring, and signs of board deterioration. G. Check insulation for worn, burned, or broken wires. H. Check chassis-mounted components for displacement, damaged sleeving, shorted leads, and overheating. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. CHECK 24-23-34 Page 5001 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. CHECK 24-23-34 Page 5002 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 REPAIR 60006000 TASK 24-23-34-300-801-A 1. GENERAL INFORMATION FOR REPAIR Subtask 24-23-34-99F-014-A00 A. General Information (1) This section has the procedures and illustrations necessary to repair the GCU and its detail parts. The item numbers in the procedures and illustrations are the same as those in the IPL. NOTE: You can replace an item with its alpha-variant when permitted by the effect code for that item. For example, procedures that apply to item (10) also apply to the alpha-variant items (-10A, -10B, and -10C). (2) Refer to SPM 20-10-01. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. REPAIR 24-23-34 Page 6001 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. REPAIR 24-23-34 Page 6002 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 ASSEMBLY 70007000 TASK 24-23-34-400-801-A 1. GENERAL INFORMATION FOR ASSEMBLY Subtask 24-23-34-99F-015-A00 A. General Information (1) This section has the procedures and illustrations necessary to assemble the GCU. The item numbers in the procedures and illustrations are the same as those in the IPL. NOTE: You can replace an item with its alpha-variant when permitted by the effect code for that item. For example, procedures that apply to item (10) also apply to the alpha-variant items (-10A, -10B, and -10C). (2) Refer to SPM 20-10-01. Subtask 24-23-34-94A-001-A00 B. Materials for Assembly (1) Refer to Table 7001 for the materials necessary for the assembly procedures. Table 7001 Table 7001 Materials for Assembly Material Number and Name Source Use ASTM D770, Isopropyl Alcohol Commercially Available Clean threads of fasteners. Retaining Compound (Military Specification MIL-S-46163, Type II, Grade N - Loctite 242) Loctite Corporation (CAGE Code 05972) Apply to threads of fasteners. NOTE: Maintenance personnel must use the specified consumable material for the specified task. These consumable materials are known to agree with all of the design and qualification requirements. Only approved materials engineering personnel can make equivalent consumable material decisions. These materials are used at the risk of the organization who makes the decision. NOTE: You can get the full address and other information for vendors or suppliers listed in this table from the World Wide Web (www) at URL http:// www.bpn.gov/bincs/begin_search.asp. Other CAGE Code sites are also available on the Web. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. ASSEMBLY 24-23-34 Page 7001 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 TASK 24-23-34-400-802-A 2. ASSEMBLY OF THE GCU CAUTION: THE GCU CONTAINS ELECTROSTATIC DEVICES. DO NOT SUBJECT IT TO ELECTROSTATIC, ELECTROMAGNETIC, MAGNETIC, OR RADIOACTIVE FIELDS UNLESS PROTECTED BY A STATIC-SHIELDED CONTAINER. A. If removed, install the following parts: (1) Install warning label (200, IPL Figure 1) (refer to SPM 20-10-01, REPAIR). (2) Install the screws (170) and identification plate (160). Torque the screws (170) 8.0 to 11.0 pound-inches (1.0 to 1.2 Newton meters). (3) Apply Loctite retaining compound 242 to screws (150) as follows: WARNING: USE ISOPROPYL ALCOHOL, ASTM D770, CORRECTLY. ISOPROPYL ALCOHOL IS FLAMMABLE, EXPLOSIVE, AND A MILD POISON. IT CAN HAVE A BAD EFFECT ON YOUR HEALTH OR SAFETY. BEFORE YOU USE THE ALCOHOL, GET THE MATERIAL SAFETY DATA SHEET FROM THE MANUFACTURER OR SUPPLIER OF THE MATERIAL AND READ IT CAREFULLY. READ THE DETAILED WARNING, W0046SE, IN THE WARNING REGISTRY SPM 20-00-04. BEFORE YOU USE THE ALCOHOL, PUT ON CHEMICAL-SPLASH GOGGLES. MAKE SURE THAT YOU HAVE SUFFICIENT AIRFLOW TO KEEP THE ALCOHOL FUMES BELOW THE MATERIAL SAFETY DATA SHEET LIMIT. (a) Clean all threads of fasteners with clean isopropyl alcohol. Allow isopropyl alcohol to evaporate for a minimum of 5 minutes. WARNING: USE ANAEROBIC THREADLOCKING COMPOUND CORRECTLY. THE COMPOUND IS COMBUSTIBLE. IT CAN HAVE A BAD EFFECT ON YOUR HEALTH OR SAFETY. BEFORE YOU USE THE COMPOUND, GET THE MATERIAL SAFETY DATA SHEET FROM THE MANUFACTURER OR SUPPLIER OF THE MATERIAL AND READ IT CAREFULLY. READ THE DETAILED WARNING, W0069SE, IN THE WARNING REGISTRY SPM 20-00-04. BEFORE YOU USE THE COMPOUND, PUT ON SAFETY GLASSES OR GOGGLES AND NEOPRENE, RUBBER, OR BUTYL RUBBER GLOVES. (b) Apply Loctite retaining compound 242 to threads of screws (150). (4) Install the serial-amendment plate (130), handle (140), and screws (150). Torque the screws (150) 16.0 to 19.0 pound-inches (1.9 to 2.1 Newton meters). (5) Install the support hooks (180) and screws (190). Torque the screws (190) 8.0 to 11.0 pound-inches (1.0 to 1.2 Newton meters). NOTE: Make sure support hooks (180) are 0.040 inch (1.0160 mm) above or below the bottom edge of cover assembly (10). (6) Wipe off any excess compound. (7) Cure Loctite for 24 hours at room ambient temperature of 21 to 27 °C (70 to 80 °F). NOTE: Do not allow solvents to contact Loctite-coated assembled parts during first 8 hours of curing. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. ASSEMBLY 24-23-34 Page 7002 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 B. Install the A5 PWB assembly (90, IPL Figure 1) as follows: (1) Install the A5 PWB assembly (90) into the chassis assembly (240). WARNING: USE ISOPROPYL ALCOHOL, ASTM D770, CORRECTLY. ISOPROPYL ALCOHOL IS FLAMMABLE, EXPLOSIVE, AND A MILD POISON. IT CAN HAVE A BAD EFFECT ON YOUR HEALTH OR SAFETY. BEFORE YOU USE THE ALCOHOL, GET THE MATERIAL SAFETY DATA SHEET FROM THE MANUFACTURER OR SUPPLIER OF THE MATERIAL AND READ IT CAREFULLY. READ THE DETAILED WARNING, W0046SE, IN THE WARNING REGISTRY SPM 20-00-04. BEFORE YOU USE THE ALCOHOL, PUT ON CHEMICAL-SPLASH GOGGLES. MAKE SURE THAT YOU HAVE SUFFICIENT AIRFLOW TO KEEP THE ALCOHOL FUMES BELOW THE MATERIAL SAFETY DATA SHEET LIMIT. (2) Clean mating surfaces of chassis assembly (240) and plate (110) that contact the flex print and connector of A5 PWB assembly (90) with isopropyl alcohol. (3) Install the A5 PWB assembly flex print over studs (260), plate (110), and nuts (120). Torque the nuts (120) 9.0 to 12.0 pound-inches (1.1 to 1.3 N•m). (4) Position the A5 PWB assembly (90) connector locator lug flush to 0.010 inch (0.2540 millimeters) below the bottom of chassis assembly (240). (5) Install the screws (100) into the connector of A5 PWB assembly (90). Torque the screws (100) 8.0 to 11.0 pound-inches (1.0 to 1.2 N•m). C. Install the A1 through A4 printed wiring board (PWB) assemblies (50 through 80) as follows: (1) Install the screw (270), spacer (280), flat washer (290), and nut (300) in the chassis assembly (240). Torque the nut (300) 70.0 to 105.0 ounce-inches (0.50 to 0.74 N•m). (2) On all units, rest the chassis assembly (240) on its installed A5 PWB assembly (90) connector. (3) Install the A2 PWB assembly (60) in the chassis assembly (240). Insert into mating A5 PWB assembly (90) connector. NOTE: Make sure the A2 PWB assembly (60) is within the chassis assembly board guide. (4) Install the A3 PWB assembly (70) on the A1 PWB assembly (50) connector. Torque the connector (40, IPL Figure 4) jack screws to 25 ounce-inches (0.17 N•m). (5) Install the bracket (210, IPL Figure 1) and screw (220) on the A2 PWB assembly (60). (6) Install the A4 PWB assembly (80) on A1 PWB assembly (50) connector. (7) Install screw (230) to secure bracket (210) to A4 PWB assembly (80). Do not tighten. (8) Install the A3 PWB assembly (70) and A4 PWB assembly (80) in the chassis assembly (240). Insert into A5 PWB assembly (90) mating connectors. NOTE: Make sure the A3 and A4 PWB assemblies (70 and 80) are within the chassis assembly board guides. (9) Position the installed PWB assemblies so the gap between all the mating connectors is minimum. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. ASSEMBLY 24-23-34 Page 7003 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (10) Use a 3/32-inch ball driver hex wrench to tighten the A2 and A4 PWB assemblies (60 and 80) wedge-lock retainer screws (part of 380, IPL Figure 3 and part of 575, IPL Figure 5). Torque the screws 4.0 to 6.0 pound-inches (0.5 to 0.6 N•m). (11) Tighten the screw (220, IPL Figure 1). Torque the screw (220) 4.0 to 6.0 pound-inches (0.5 to 0.6 N•m). (12) Tighten the screw (230). Torque the screw (230) 8.0 to 11.0 pound-inches (1.0 to 1.2 N•m). D. Install the cover assembly (10) on chassis assembly (240). Secure with the screws (20 and 30). Torque the screws (20 and 30) 8.0 to 11.0 pound-inches (1.0 to 1.2 N•m). NOTE: Make sure sponge rubber pads inside cover assembly are in place and not damaged before installing cover. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. ASSEMBLY 24-23-34 Page 7004 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 FITS AND CLEARANCES 80008000 TASK 24-23-34-205-801-A 1. GENERAL INFORMATION FOR FITS AND CLEARANCES A. This section has the fits and clearances information for the GCU and its detail parts. The item numbers in the procedures and illustrations are the same as those in the IPL. NOTE: You can replace an item with its alpha-variant when permitted by the effect code for that item. For example, procedures that apply to item (10) also apply to the alpha-variant items (-10A, -10B, and -10C). TASK 24-23-34-205-802-A 2. TORQUE REQUIREMENTS NOTE: Refer to the INTRODUCTION and the REPAIR for the symbols used in the FITS AND CLEARANCES illustrations. A. Refer to Table 8001 for the torque requirements. NOTE: Metric torque values are shown in parentheses. Table 8001 Table 8001 Torque Requirements Name (IPL Figure-Item Number) Specified Torque Pound-inches (N•m) Screw Figure 1 - Item 20 8.0 to 11.0 (1.0 to 1.2 N•m) Screw Figure 1 - Item 30 8.0 to 11.0 (1.0 to 1.2 N•m) Screw Figure 1 - Item 100 8.0 to 11.0 (1.0 to 1.2 N•m) Nut Figure 1 - Item 120 9.0 to 12.0 (1.1 to 1.3 N•m) Screw Figure 1 - Item 150 16.0 to 19.0 (1.9 to 2.1 N•m) Screw Figure 1 - Item 170 8.0 to 11.0 (1.0 to 1.2 N•m) Screw Figure 1 - Item 190 8.0 to 11.0 (1.0 to 1.2 N•m) Screw Figure 1 - Item 220 4.0 to 6.0 (0.5 to 0.6 N•m) Screw Figure 1 - Item 230 8.0 to 11.0 (1.0 to 1.2 N•m) NOTE: Running Torque Pound-inches (N•m) If there is a running torque specified, add the measured running torque to the specified torque to get the final torque. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. FITS AND CLEARANCES 24-23-34 Page 8001 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table 8001 Torque Requirements (Continued) Name (IPL Figure-Item Number) Specified Torque Pound-inches (N•m) Nut Figure 1 - Item 300 70.0 to 105.0 ounce-inches (0.50 to 0.74 N•m) PWB Wedgelock Screw Figure 3 - Part of Item 380 4.0 to 6.0 (0.5 to 0.6 N•m) Connector Jack Screw Figure 4 - Part of Item 40 25 ounce-inches (0.17 N•m) PWB Wedgelock Screw Figure 5 - Part of Item 575 4.0 to 6.0 (0.5 to 0.6 N•m) NOTE: Running Torque Pound-inches (N•m) If there is a running torque specified, add the measured running torque to the specified torque to get the final torque. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. FITS AND CLEARANCES 24-23-34 Page 8002 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLE MATERIALS 90009000 TASK 24-23-34-940-801-A 1. SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLE MATERIALS Subtask 24-23-34-99F-016-A00 A. General Information (1) This section gives the special tools, fixtures, equipment, and consumable materials necessary to do maintenance procedures for the GCU. Subtask 24-23-34-94A-002-A00 B. Materials (1) Refer to Table 9001 for the materials necessary for the maintenance procedures. Table 9001 Table 9001 Materials Material Number and Name Source Use Antistatic Foam Molds Commercially Available To store the GCU. ASTM D770, Isopropyl Alcohol Commercially Available To clean the threads of fasteners. Conductive Plastic Bag Commercially Available To store the GCU. Fiberboard Box, Weather Resistant, Burst Strength 400 psi (2,758 kPa), ASTM Specification D118 (or equivalent) Commercially Available To store the GCU. Protective Cap (Electrically Conductive) 025-1157-001 and 025-1158-001 ITT Corporation (CAGE Code 71468) To protect electrical connector during storage. Retaining Compound (Military Specification MIL-S-46163, Type II, Grade N - Loctite 242) Loctite Corporation (CAGE Code 05972 To apply to the threads of fasteners. NOTE: Maintenance personnel must use the specified consumable material for the specified task. These consumable materials are known to agree with all of the design and qualification requirements. Only approved materials engineering personnel can make equivalent consumable material decisions. These materials are used at the risk of the organization who makes the decision. NOTE: You can get the full address and other information for vendors or suppliers listed in this table from the World Wide Web (www) at URL http://www.bpn.gov/bincs/begin_search.asp. Other CAGE Code sites are also available on the Web. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLE MATERIALS 24-23-34 Page 9001 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subtask 24-23-34-94B-002-A00 C. Special Tools (1) Refer to Table 9002 for the special tools necessary for the maintenance procedures. Table 9002 Table 9002 Special Tools Tool Number and Name Source Use 600WXXXX, Test Executive Software Testek Incorporated (CAGE Code 06659) To test the GCU. 716WXXXX, Test Program Software Testek Incorporated (CAGE Code 06659) To test the GCU. 931030-P1 or 951009-PO, Interface Test Adapter Testek Incorporated (CAGE Code 06659) To test the GCU. AGETBD, A2, A3, A4 Fan-out Fixture Adapter (Optional) Hamilton Sundstrand (CAGE Code 99167) To troubleshoot the GCU while being tested with the test stand. Model TS1650, Universal Test Stand Testek Incorporated (CAGE Code 06659) To test the GCU. TE179512.bin Command Interpreter Software Testek Incorporated (CAGE Code 06659) To test the GCU. TE00246110, Buffer Converter and Diagnostic Software GCU Configuration File Testek Incorporated (CAGE Code 06659) To test the GCU. NOTE: Equivalent tools, fixtures, and equipment can be used if they agree with the requirements of ARINC Report 668. NOTE: To get a quotation for Ground Support Equipment, use the online order request website that follows: http://www.hamiltonsundstrand.com/gse. NOTE: You can get the full address and other information for vendors or suppliers listed in this table from the World Wide Web (www) at URL http://www.bpn.gov/bincs/begin_search.asp. Other CAGE Code sites are also available on the Web. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLE MATERIALS 24-23-34 Page 9002 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subtask 24-23-34-94C-002-A00 D. Test Equipment (1) Refer to Table 9003 for the test equipment necessary for the maintenance procedures. Table 9003 Table 9003 Test Equipment Equipment Range Accuracy Use High Voltage AC Insulation Tester 100 to 3,000 VAC 0 to 5.00 milliamperes AC current To test the A5 printed wiring board insulation resistance. Megohmmeter 1 to 20,000 Megohms To measure the A5 printed wiring board insulation resistance. Milliohmmeter 1 micro-ohm to 50 milliohms To measure the A5 printed wiring board bonding resistance. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLE MATERIALS 24-23-34 Page 9003 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLE MATERIALS 24-23-34 Page 9004 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 ILLUSTRATED PARTS LIST 1000010000 TASK 24-23-34-950-801-A 1. ILLUSTRATED PARTS LIST INTRODUCTION Subtask 24-23-34-99F-017-A00 A. Illustrated Parts List (IPL) General Information (1) The Illustrated Parts List (IPL) shows the detail parts for each item identified on the Title Page. The IPL includes all of the parts that can be disassembled, repaired or replaced, and assembled again. (2) The part numbers identified in this Illustrated Parts List have been shown to comply with the applicable Federal Aviation Regulations and, when purchased from Hamilton Sundstrand, are FAA-approved under a Hamilton Sundstrand FAA Production Certificate (PC), Technical Standard Order (TSO), or Parts Manufacturer Approval (PMA) for use in the components listed. (3) This Illustrated Parts List does not constitute a grant of direct-ship authority, or otherwise confer FAA-approval under FAR 21.303 for parts and assemblies purchased directly from a listed vendor. Installation eligibility of all parts and assemblies purchased directly from a listed vendor must be supported by the vendor’s Parts Manufacturer Approval (PMA). (4) The items in this list are made or supplied by Hamilton Sundstrand, or by the suppliers shown in this list. Hamilton Sundstrand does not give approval for items that you get from suppliers who are not shown in this list. Approval from Hamilton Sundstrand is not necessary for government and industry standard parts. Subtask 24-23-34-99F-018-A00 B. Definitions for the Illustrated Parts List (1) The list that follows gives a list of the terms, their abbreviations (if applicable) and interpretations of how the terms are used in the DPL of this manual. Table IPL-10001 Definitions for the Illustrated Parts List Term Definition AS REQUIRED (AR) Shows that the actual quantity of a part is based on the decisions made as part of the maintenance process. ALTERNATE (ALT) Shows a part, subassembly, or assembly that fully meets the specifications for the function and structure of the initial part.These parts can have different overall dimensions, connections, installation or mounting provisions. These parts require a modification to install the part in a specific application. An alternate item is listed in the “Fig & Item” column with an item number that is different than the number of the part that it can replace. The alternate part is identified in the “Nomenclature” column as “(ALT TO ITEM XX)”. The primary part listing will show all alternate parts listed following the nomenclature of the primary part with all alternate part numbers and vendor codes. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. ILLUSTRATED PARTS LIST 24-23-34 Page 10001 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table IPL-10001 Definitions for the Illustrated Parts List (Continued) Term Definition Be Beryllium. See Hamilton Sundstrand Warnings Registry SPM 20-00-04 for hazards associated with this material. CAGE Commercial And Government Entity - This is a five character code that identifies the part manufacturers/suppliers. DELETED A deleted part, subassembly, assembly, or unit is one which has been removed from a specific application. The figure number, item number, and part number of a deleted part are retained in their respective columns. The EFF CODE and “UNITS PER ASSY” (UPA) column information is removed. The word “DELETED” is added to the “Nomenclature” column. The original nomenclature noun and modifier can follow in parenthesis; for example “DELETED (MCKT LINEAR)”. All other information will be removed from the nomenclature column. ESDS Electrostatic Discharge Sensitive. Keep the part away from electrostatic, electromagnetic, or radioactive fields unless protected by a static-shielded container. See the Hamilton Sundstrand Standard Practices Manual (SPM) applicable to this manual. FIG. Figure HS Hamilton Sundstrand - This is used as a prefix to a part number in the “Nomenclature” column. The part number that is adjacent to the “HS” is a Hamilton Sundstrand source control or specification control number. IDENT. AS Identify as. When a part number is either too long (exceeds fifteen characters) or is not compliant with ATA specifications (contains a slash or other symbols that are not recognized); such as M83248/1-905, the part number would be modified to M83248-1-905 in the part number column and the following would appear in the nomenclature column “IDENT. AS M83248/1-905”. MSD Moisture Sensitive Device. Keep the part away from extreme heat or humidity. Protect device in moisture-proof container. See the Hamilton Sundstrand Standard Practices Manual (SPM) applicable to this manual. NHA Next Higher Assembly NON-PROCURABLE (NP) Parts that have the abbreviation “(NP)” in the “NOMENCLATURE” column are not supplied by that part number. If you need the complete part identified as “(NP)”, order the next higher assembly (NHA). If a part is identified with an “(NP)”, and it has details that are not identified with “(NP)”, those details of the part can be supplied. OPN or RFL Preface to a reference part number used when the actual part number is overlength. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. ILLUSTRATED PARTS LIST 24-23-34 Page 10002 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Table IPL-10001 Definitions for the Illustrated Parts List (Continued) Term Definition OPTIONAL (OPT) Shows a choice of the parts, subassemblies, and assemblies that fully interchange. These parts are usually standard parts available from multiple sources and identified with different part numbers by the true manufacturer. The dimensions of the part can change, but the installation and mounting of the part does not require a rework or modification. An optional item is listed in the “Fig & Item” column as an alpha-variant and is identified in the “Nomenclature” column as “(OPT TO ITEM XX)” or “(VXXXXX) OPT”. The optional part is identified in the “Nomenclature” column as “(OPT TO ITEM XX)”. The primary part listing will show all alternate parts listed following the nomenclature of the primary part with all optional part numbers and vendor codes. PRE/POST SB Shows that the part was added or removed by a Service Bulletin. An item that was introduced by a Service Bulletin is identified in the “Nomenclature” column as “(POST SB XX)”. An item that was used prior to Service Bulletin accomplishment is identified in the “Nomenclature” column as “(PRE SB XX)”. REFER TO SB If an existing part is checked, inspected and/or modified by a Service Bulletin without resulting in a change to the part number, a note will appear in the nomenclature of that part to “(REFER TO SB XX)”. REPLACES/REPLACED (REPLS/ REPLD) Shows a choice of the parts, subassemblies, or assemblies that fully interchange (two-way). If usage is not otherwise restricted, the old part can be used on a new configuration, and a new part can be used on an old configuration. Old parts can be used until the old parts are gone. A replaced item is listed in the “Nomenclature” column as “(REPLD BY ITEM XX)”. The replacing item is listed in the “Fig & Item” column as an alpha-variant and identified in the “Nomenclature” column as “(REPLS ITEM XX)”. RF Reference SUPERSEDES/SUPERSEDED (SUPSDS/SUPSD) Shows that the parts, subassemblies, or assemblies cannot be fully interchanged or that a one-way interchange exists. The part identified as (SUPSD BY ITEM XX) is to be used only on the assemblies or units on which it was permitted prior to the supersedure, or as defined by a parts use note. The SUPERSEDED part will usually have restricted usage that is determined by a letter code in the EFF CODE column or by a parts use note in the NOMENCLATURE column. The superseding part is listed in the “Fig & Item” column as an alpha-variant and is identified in the “Nomenclature” column as (SUPSDS ITEM XX). A part that is limited to a one-way interchange can effect the use of other parts. Be sure to use other affected parts as directed by the effectivity codes and other maintenance instructions such as a Service Bulletin. The intent of the effectivity codes must be obeyed to assure the correct parts are used. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. ILLUSTRATED PARTS LIST 24-23-34 Page 10003 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Subtask 24-23-34-99F-019-A00 C. Illustrated Parts List (IPL) Organization (1) The IPL has these sections: • The Introduction, which tells how to use the IPL. It includes the Vendor List. It can also include a Configuration Change Summary, which shows the sequence and causes for the changes in the IPL. • The Equipment Designator Index (if applicable), which shows all of the electrical components in the sequence of their reference designators. It identifies each reference designator with a figure and item location. • The Numerical Index, which shows all of the parts in the sequence of their part numbers. It identifies each use of a part number with a figure and item location. • The Detailed Parts List, which shows all of the parts in their approximate disassembly sequence with illustrations. It also gives other information related to the use of each part. Subtask 24-23-34-99F-020-A00 D. Detailed Parts List (DPL) Organization (1) The “Fig & Item” (Figure and Item Number) columns give the item number for each part shown on the illustration. The item number can have a hyphen in front of it (-10), can be followed by a letter (10A), or can be shown with both (-10B). An item number with a hyphen in front of it is not shown on the illustration. An item number followed by a letter (10A) shows that the part on the illustration is equivalent to all parts that include the same item number (-10, -10B, or 10C). (2) The “Part Number” column gives the part numbers for each item. The types of numbers used in the “Part Number” column are shown below: • Hamilton Sundstrand Part Numbers - If a part is only available from Hamilton Sundstrand, the Hamilton Sundstrand Part number is shown in the “Part Number” column. • Vendor Part Numbers - If a part is not changed by Hamilton Sundstrand, the vendor’s part number is shown in the “Part Number” column. The vendor’s code is shown in the “Nomenclature” column after the letter “V”. The equivalent Hamilton Sundstrand part number is shown in the “Nomenclature” column after the letters “HS”. • Industrial Standard and Military Numbers - If a part has an industrial standard number or military standard number, that number is shown in the “Part Number” column. • RFN Numbers - “RFN” is used to divide the detail parts into smaller groups. Each RFN number refers to group of parts which is shown in detail on a different figure. This is done to make the parts list easier to use. You cannot procure parts by their “RFN” numbers. • RFL or OPN Numbers - Some vendor parts have “RFL” or “OPN” numbers in the “Part Number” column. “RFL” or “OPN” numbers are used when the correct vendor part number is too long to fit in the “Part Number” column. The correct vendor part number is in the “Nomenclature” column after the words “IDENT. AS”. You cannot procure parts by their “RFL” or “OPN” numbers. • When a series of letters is given in the “Part Number” column, the assembled parts shown on the illustration are not procurable as a subassembly. The part number shown last in a series of equivalent parts is the most recent part. • Part Numbers that are non-ATA-compliant are changed to become ATA-compliant and entered in the “Part Number” column. The correct non-ATA-compliant vendor part number is in the “Nomenclature” column after the words “IDENT. AS”. (3) The “Airline Part Number” column is used by the airline. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. ILLUSTRATED PARTS LIST 24-23-34 Page 10004 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (4) The “Nomenclature” column has the following types of information. • Assembly Sequence Indentation - The parts are indented to show which parts are installed in other parts. The level of indentation is shown by the number of dots at the left edge of the column. For example, the top assembly for a parts list figure is at the left margin. The names of its parts and subassemblies are indented by one dot. Subsequent subassemblies and parts are indented with more dots. Top Assembly . Detail Parts of the Top Assembly . Subassembly of the Top Assembly . Attaching Parts for the Subassembly . . Detail Parts of the Subassembly . . Subassemblies of the Subassembly • The part name is given in one or two parts. If just the name is given. It appears first. If the name and additional description is given, the name appears first, followed by a dash “-”, followed by the additional description. • A vendor code (a capital letter V followed by five numbers or a mixture of five numbers and letters). • A Hamilton Sundstrand Source/Specification Control Number. • A dimension or characteristic of an electronic component. All solid shim thicknesses are given in inches. An example is (0.010 THK) which represents a 0.010 inch thick solid shim. Metric equivalents are given in [ ]. • Equipment/Reference Designator(s). • A service bulletin number (with the capital letters SB in front of the number). • A note that has additional information about the use of a part. • The words “ATTACHING PARTS” tell that the items that follow are used to attach the item. The end of the “ATTACHING PARTS” are identified with the characters “------*-------” in the “Nomenclature” column. If there are the words “ATTACHING PARTS”, the “ATTACHING PARTS” for the item are shown first and the detailed breakdown of the item are shown after the end of “ATTACHING PARTS” characters “-------*-------”. • The words “PARTIAL BREAKDOWN FOLLOWS” tell that two or more detail parts of the subassembly are not listed. • The words “SERVICE USE” tell that the part was not used in the original equipment but can be used for in-service units. • The words “SERVICE EVALUATION PART” tell that the part is being used on a limited population of units and is not being supplied for the general population of units. • The words “CHANGE CODE”, followed by a number, show the sequence in which changes were made. The Configuration Change Summary (if supplied), in this IPL Introduction, tells about each change code number used. If the change code number has an asterisk (*) after it, then all of the items that have the same change code must be changed at the same time. The Configuration Change Summary tells about the change codes. It identifies each change by its change code number, tells you which assemblies changed by part number and/or mod data, identifies which engineering change (EC) caused the change, identifies which Service Bulletin (if any) has the change procedures and gives a brief description of the change. (5) The “Eff Code” column shows the differences between two or more configurations of an end item. When different parts are used, they are given the same code letter as the end item configuration. When no code letter is shown in the “Eff Code” column, the part can be used in all end item configurations. The “Eff Code” column uses a single letter to identify each configuration. The letters are capital A thru Z, but not I or O. The codes in the “Eff Code” column are unique to the IPL Figure in which they are shown. For example, an “A” used in Figure 1 may be applicable to PN XXXXXX-1 in Figure 1. In the same example, if an “A” is used in Figure 2, it may be applicable to PN XXXXX2 in Figure 2. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. ILLUSTRATED PARTS LIST 24-23-34 Page 10005 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 (6) The “UPA” (Units per Assembly) column shows the quantity of each part and subassembly shown in the IPL illustration. If there is a number shown in the “UPA” column, that quantity of the item is used in the location shown. An “RF” is used in the “UPA” column for the top assembly shown on a figure. The quantity of the assembly used is shown on the next higher assembly. If there is an “AR” in the “UPA” column, then the actual quantity of the item can vary. An example of when this would be used is for a shim that is selected during assembly. Subtask 24-23-34-99E-002-A00 E. Configuration Change Summary Table IPL-10002 Table IPL-10002 Configuration Change Summary Change Code Part Number - 1709225 2. VENDOR LIST NOTE: Mod Data Service Bulletin HS Reference (EC) Description Not Required - Basic Coverage. You can get the full address and other information for vendors or suppliers listed in this table from the World Wide Web (www) at URL http://www.bpn.gov/bincs/ begin_search.asp. Other CAGE Code sites are also available on the Web. CAGE Manufacturer 99167 Hamilton Sundstrand Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. ILLUSTRATED PARTS LIST 24-23-34 Page 10006 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 EQUIPMENT DESIGNATOR INDEX Equipment Designator AR1 AR10 AR11 AR2 AR3 AR4 AR5 AR6 AR7 AR8 AR9 C1 C1 C1 C10 C10 C10 C10 C10 C100 C101 C101 C102 C102 C103 C103 C104 C104 C105 C106 C107 C11 C11 C11 C11 C11 C111 C112 C113 C114 C115 C116 C117 C118 Fig - Item 3 3 3 3 3 3 3 3 3 3 3 3 4 5 3 4 5 6 6 5 3 5 3 5 3 5 3 5 3 3 3 3 4 5 6 6 3 3 3 3 3 3 3 3 - 125 120 120 125 125 120 205 205 205 125 190 25 10 35 25 10 80 50A 60 65 45 60 45 35 45 80 45 35 20 45 45 15 10 35 50A 60 20 45 20 45 55 20 45 55 Equipment Designator C119 C12 C12 C12 C12 C12 C120 C126 C127 C128 C129 C13 C13 C13 C13 C13 C130 C131 C132 C133 C134 C135 C14 C14 C14 C14 C141 C142 C143 C144 C145 C146 C147 C148 C149 C15 C15 C15 C150 C151 C152 C153 C154 C155 Fig - Item 3 3 4 5 6 6 3 3 3 3 3 3 4 5 6 6 3 3 3 3 3 3 4 5 6 6 3 3 3 3 3 3 3 3 3 4 6 6 3 3 3 3 3 3 - 20 25 10 35 50A 60 45 45 20 45 20 15 10 60 50A 60 45 20 45 20 45 20 10 20 50A 60 45 20 45 20 45 20 45 20 45 10 50A 60 20 45 20 45 20 45 Equipment Designator C156 C16 C16 C16 C16 C161 C162 C163 C164 C165 C166 C167 C168 C169 C17 C17 C17 C17 C170 C171 C172 C173 C18 C18 C18 C18 C181 C182 C183 C184 C185 C186 C19 C19 C19 C19 C191 C192 C193 C194 C195 C196 C197 C198 Fig - Item 3 4 5 6 6 3 3 3 3 3 3 3 3 3 4 5 6 6 3 3 3 3 4 5 6 6 3 3 3 3 3 3 4 5 6 6 3 3 3 3 3 3 3 3 - 20 10 5 50A 60 45 20 45 20 45 20 45 20 45 10 5 50A 60 20 45 20 45 10 35 50A 60 45 20 45 20 45 20 10 10 50A 60 45 20 45 20 45 20 45 20 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10007 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Equipment Designator C199 C2 C2 C2 C20 C20 C20 C20 C200 C206 C207 C208 C209 C21 C21 C21 C21 C21 C210 C211 C212 C213 C215 C216 C217 C218 C219 C22 C22 C22 C22 C22 C220 C221 C222 C223 C224 C225 C226 C227 C228 C229 C23 C23 C23 C23 Fig - Item 3 3 4 5 4 5 6 6 3 3 3 3 3 3 4 5 6 6 3 3 3 3 3 3 3 3 3 3 4 5 6 6 3 3 3 3 3 3 3 3 3 3 3 4 5 6 - 45 15 10 35 10 25 50A 60 20 20 20 20 20 25 10 15 50A 60 20 20 20 20 20 20 20 20 20 15 10 35 50A 60 20 20 20 20 20 20 20 20 20 20 25 10 25 50A Equipment Designator Fig - Item Equipment Designator Fig - Item C23 C230 C231 C232 C233 C234 C235 C236 C237 C238 C239 C24 C24 C24 C24 C24 C240 C241 C242 C243 C244 C245 C246 C247 C248 C249 C25 C25 C25 C25 C25 C250 C251 C252 C253 C254 C255 C256 C257 C258 C259 C26 C26 C26 C26 C26 6 3 3 3 3 3 3 3 3 3 3 3 4 5 6 6 3 3 3 3 3 3 3 3 3 3 3 4 5 6 6 3 3 3 3 3 3 3 3 3 3 3 4 5 6 6 C260 C261 C262 C263 C264 C265 C266 C267 C268 C269 C27 C27 C27 C27 C27 C270 C271 C272 C273 C274 C275 C276 C277 C279 C28 C28 C28 C28 C280 C281 C282 C283 C29 C29 C3 C3 C3 C30 C30 C31 C31 C31 C31 C32 C32 C32 3 3 3 3 3 3 3 3 3 3 3 4 5 6 6 3 3 3 3 3 3 3 3 3 3 5 6 6 3 3 3 3 3 5 3 4 5 3 5 3 5 6 6 3 4 5 - 60 20 20 20 20 20 20 20 20 20 20 15 10 35 50A 60 20 20 20 20 20 20 20 20 20 20 25 10 75 50A 60 20 20 20 20 20 20 20 20 20 20 15 10 35 50A 60 - 20 20 20 20 20 20 20 20 20 20 25 10 25 50A 60 20 20 20 20 20 20 20 20 40 15 35 50A 60 40 40 20 60 25 35 25 10 30 15 40 25 5 50A 60 15 10 60 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10008 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Equipment Designator C32 C32 C33 C33 C33 C33 C34 C34 C34 C34 C35 C35 C35 C35 C36 C36 C36 C36 C37 C37 C37 C37 C38 C38 C38 C38 C39 C39 C39 C39 C4 C4 C4 C40 C40 C40 C40 C41 C41 C41 C42 C42 C42 C42 C43 C43 Fig - Item 6 6 4 5 6 6 4 5 6 6 4 5 6 6 4 5 6 6 4 5 6 6 4 5 6 6 4 5 6 6 3 4 5 4 5 6 6 3 4 5 3 3 4 5 3 3 - 50A 60 10 60 50A 60 10 60 50A 60 10 55 50A 60 10 55 50A 60 10 60 50A 60 10 35 50A 60 10 35 50A 60 15 10 30 10 35 50A 60 45 10 80 30 30A 10 80 30 30A Equipment Designator C43 C43 C44 C44 C44 C44 C45 C45 C45 C46 C46 C47 C47 C48 C49 C49 C5 C5 C5 C50 C50 C51 C51 C51 C52 C52 C52 C53 C53 C53 C54 C54 C54 C55 C55 C55 C56 C56 C56 C57 C57 C57 C58 C58 C58 C59 Fig - Item 4 5 3 3 4 5 3 4 5 3 5 3 4 4 4 5 3 4 5 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 - 10 70 30 30A 10 50 45 10 35 15 80 45 20 20 20 45 25 10 30 20 35 50 20 35 50 25 35 20 20 35 50 10 35 50 10 35 20 10 45 20 30 50 20 30 60 5 Equipment Designator C59 C6 C6 C6 C60 C60 C61 C62 C63 C64 C65 C65 C66 C66 C67 C67 C68 C68 C69 C7 C7 C70 C71 C72 C73 C74 C75 C76 C76 C77 C77 C78 C78 C79 C79 C8 C8 C8 C8 C8 C80 C80 C81 C81 C82 C83 Fig - Item 5 3 4 5 3 5 3 3 5 5 3 5 3 5 3 5 3 5 5 3 4 5 5 5 5 5 5 3 5 3 5 3 5 3 5 3 4 5 6 6 3 5 3 5 5 5 - 80 15 10 60 10 70 5 10 35 5 5 35 10 35 5 35 10 35 35 10 10 35 35 35 35 35 35 20 35 45 35 35 35 20 35 25 10 25 50A 60 45 35 45 35 35 35 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10009 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Equipment Designator C84 C85 C86 C87 C88 C89 C9 C9 C9 C9 C9 C90 C91 C91 C92 C92 C93 C93 C94 C94 C95 C95 C96 C96 C97 C97 C98 C99 D1 D10 D10 D100 D102 D103 D106 D107 D108 D109 D11 D11 D110 D111 D112 D113 D114 D12 Fig - Item 5 5 5 5 5 5 3 4 5 6 6 5 3 5 3 5 3 5 3 5 3 5 3 5 3 5 5 5 4 3 5 3 3 3 3 3 3 3 3 5 3 3 3 3 3 3 - 35 35 35 35 35 35 15 10 25 50A 60 35 20 35 45 35 20 35 45 35 45 35 20 60 45 60 60 60 50 75 95 70 70 70 70 70 70 70 70 95 70 70 70 70 70 75 Equipment Designator Fig - Item Equipment Designator Fig - Item D12 D121 D122 D123 D124 D125 D126 D127 D128 D129 D13 D13 D130 D131 D132 D136 D137 D138 D139 D14 D14 D140 D141 D142 D15 D15 D16 D16 D17 D17 D18 D18 D19 D19 D2 D2 D20 D20 D21 D21 D22 D22 D23 D24 D25 D26 5 3 3 3 3 3 3 3 3 3 3 5 3 3 3 3 3 3 3 3 5 3 3 3 3 5 3 5 3 5 3 5 3 5 4 5 3 5 3 5 3 5 5 5 5 3 D26 D27 D27 D28 D28 D29 D29 D3 D30 D30 D31 D32 D33 D34 D35 D36 D36 D37 D37 D38 D38 D39 D39 D4 D40 D40 D41 D41 D42 D42 D43 D43 D44 D45 D46 D46 D47 D48 D49 D5 D50 D51 D51 D52 D52 D53 5 3 5 3 5 3 5 5 3 5 5 5 5 5 5 3 5 3 5 3 5 3 5 5 3 5 3 5 3 5 3 5 5 5 3 5 5 5 5 5 5 3 5 3 5 3 - 95 70 70 70 70 70 70 70 70 70 75 95 70 70 70 75 75 75 75 70 105 75 75 75 70 105 70 105 75 90 70 90 75 90 60 95 75 90 70 90 75 90 105 105 105 70 - 105 70 105 70 105 70 105 105 75 105 105 100 105 105 105 70 105 70 105 70 105 70 105 105 75 105 75 105 75 95 75 105 105 95 75 95 95 95 95 95 95 70 100 70 100 70 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10010 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Equipment Designator D54 D55 D56 D57 D58 D59 D6 D6 D60 D66 D67 D68 D69 D7 D70 D71 D72 D73 D74 D75 D77 D79 D8 D80 D81 D82 D83 D9 D91 D92 D93 D94 D95 D96 D97 D98 F1 FB1 FB11 FB12 FB13 FB14 FB15 FB16 FB17 FB18 Fig - Item 3 3 3 3 3 3 3 5 3 3 3 3 3 5 3 3 3 3 3 3 3 3 5 3 3 3 3 5 3 3 3 3 3 3 3 3 5 3 3 3 3 3 3 3 3 3 - 70 70 70 70 70 70 70 95 70 70 70 70 70 95 70 70 70 70 70 70 70 70 95 70 70 70 70 95 70 70 70 70 70 70 70 70 565 105 105 105 105 105 105 105 105 105 Equipment Designator FB2 FB21 FB22 FB23 FB24 FB3 FB4 FB5 FB6 FB7 FB8 G1 G2 G3 J1 J1 J1 K1 K1 K2 K2 K3 L1 L1 L2 L3 L4 L5 L6 L6 L7 L7 L8 L9 P1 P1 P1 P1 P1 P2 P3 Q1 Q1 Q1 Q10 Q11 Fig - Item 3 3 3 3 3 3 3 3 3 3 3 4 4 4 3 4 5 3 5 3 5 5 3 5 5 5 5 5 3 5 3 5 3 3 2 2 3 5 6 2 2 3 4 5 5 5 - 105 105 105 105 105 105 105 105 105 105 105 260 270 280 65 40 85 340 490 335 465 490 110 150 150 160 160 160 110 160 110 155 110 110 20 20A 65 85 160 30 10 345 340 540 530 525 Equipment Designator Q12 Q13 Q13 Q14 Q15 Q16 Q17 Q18 Q19 Q2 Q2 Q20 Q3 Q3 Q4 Q4 Q5 Q5 Q6 Q6 Q7 Q8 Q8 Q9 Q9 R1 R1 R1 R10 R10 R10 R100 R100 R100 R101 R101 R101 R102 R102 R102 R103 R103 R103 R104 R104 R104 Fig - Item 5 5 5 5 5 5 5 5 5 4 5 5 4 5 4 5 4 5 4 5 5 5 5 5 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 - 520 495 495A 530 525 525 525 525 525 340 530 525 340 535 350 525 350 515 340 540 525 510 510A 495 495A 295 330 280 280 300 385 315 330 355 315 330 300 320 330 385 285 320 300 285 320 300 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10011 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Equipment Designator R105 R105 R105 R106 R106 R106 R107 R107 R107 R108 R108 R108 R109 R109 R109 R11 R11 R110 R110 R110 R111 R111 R111 R112 R112 R112 R113 R113 R113 R114 R114 R114 R115 R115 R115 R116 R116 R116 R117 R117 R118 R118 R119 R119 R12 R12 Fig - Item 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 4 5 4 5 4 5 3 5 - 240 320 320 245 320 350 240 320 430 285 320 385 250 320 385 235 370 280 320 355 280 320 370 250 320 450 250 320 385 280 320 440 285 320 330 285 320 325 320 330 320 400 320 385 330 370 Equipment Designator Fig - Item Equipment Designator Fig - Item R120 R120 R121 R121 R121 R122 R122 R122 R123 R123 R123 R124 R124 R124 R125 R125 R125 R126 R126 R127 R127 R127 R128 R128 R128 R129 R129 R129 R13 R13 R13 R130 R130 R130 R131 R131 R131 R132 R132 R132 R133 R133 R133 R134 R134 R135 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 4 5 4 R135 R136 R136 R137 R137 R138 R138 R139 R139 R14 R14 R14 R140 R140 R141 R141 R141 R142 R142 R142 R143 R143 R143 R144 R144 R144 R145 R145 R145 R146 R146 R146 R147 R147 R147 R148 R148 R149 R149 R15 R15 R15 R150 R150 R151 R151 5 4 5 4 5 4 5 4 5 3 4 5 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 5 3 5 3 4 5 3 5 3 5 - 320 410 280 320 405 285 320 370 235 320 385 235 320 385 250 320 275 320 460 250 320 460 250 320 425 285 320 370 330 300 430 285 320 405 250 330 360 250 330 385 285 330 310 320 410 310 - 320 310 315 320 375 330 370 330 395 295 310 430 320 395 250 310 395 255 310 430 285 330 390 255 330 305 285 300 345 290 330 430 285 330 360 250 385 255 385 295 320 320 285 320 255 410 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10012 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Equipment Designator R152 R152 R153 R153 R154 R154 R155 R155 R156 R157 R158 R158 R159 R159 R16 R16 R16 R160 R160 R161 R161 R162 R163 R163 R164 R165 R166 R166 R167 R167 R168 R168 R169 R169 R17 R17 R17 R170 R170 R171 R171 R172 R172 R173 R173 R174 Fig - Item 3 5 3 5 3 5 3 5 3 3 3 5 3 5 3 4 5 3 5 3 5 5 3 5 5 5 3 5 3 5 3 5 3 5 3 4 5 3 5 3 5 3 5 3 5 3 - 285 435 250 445 285 270 280 315 290 285 285 385 305 385 330 320 420 300 355 300 385 385 240 355 285 370 250 360 255 385 285 270 255 315 330 320 320 285 315 290 370 285 355 250 410 255 Equipment Designator R174 R175 R175 R176 R176 R177 R177 R178 R178 R179 R179 R18 R18 R18 R180 R180 R181 R181 R182 R182 R183 R183 R184 R184 R185 R185 R186 R186 R187 R188 R189 R19 R19 R19 R190 R191 R191 R192 R192 R193 R193 R194 R195 R196 R197 R198 Fig - Item 5 3 5 3 5 3 5 3 5 3 5 3 4 5 3 5 3 5 3 5 3 5 3 5 3 5 3 5 5 5 5 3 4 5 5 3 5 3 5 3 5 3 3 3 3 3 - 290 285 320 255 365 285 355 290 440 285 345 295 310 385 250 295 255 270 285 370 255 385 285 385 290 355 285 430 430 385 360 295 310 385 360 270 370 280 385 280 385 290 285 250 255 285 Equipment Designator R199 R2 R2 R2 R20 R20 R20 R200 R201 R202 R203 R204 R205 R206 R207 R21 R21 R21 R216 R217 R218 R219 R22 R22 R22 R220 R221 R222 R223 R224 R225 R226 R227 R228 R229 R23 R23 R23 R230 R231 R232 R233 R235 R238 R239 R24 Fig - Item 3 3 4 5 3 4 5 3 3 3 3 3 3 3 3 3 4 5 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 - 255 295 330 340 330 320 360 285 290 285 270 280 270 280 285 330 320 385 250 255 285 255 295 320 385 285 290 285 250 255 285 255 285 290 285 295 320 395 250 255 285 255 250 290 285 325 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10013 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Equipment Designator R24 R24 R240 R241 R242 R243 R244 R246 R249 R25 R25 R250 R251 R252 R253 R26 R26 R261 R262 R263 R264 R265 R266 R27 R27 R271 R272 R273 R274 R275 R276 R277 R278 R279 R28 R28 R280 R281 R282 R283 R284 R285 R286 R287 R288 R289 Fig - Item 4 5 3 3 3 3 3 3 3 4 5 3 3 3 3 4 5 3 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 3 3 - 300 385 285 250 255 285 255 250 290 320 415 285 285 240 240 300 415 270 280 270 280 270 280 300 415 280 280 285 280 285 280 280 285 280 320 320 285 280 280 285 280 285 280 280 285 280 Equipment Designator Fig - Item Equipment Designator Fig - Item R29 R29 R290 R291 R292 R293 R294 R295 R296 R297 R298 R299 R3 R3 R3 R30 R30 R306 R307 R308 R309 R31 R31 R31 R310 R311 R312 R313 R314 R315 R316 R317 R318 R319 R32 R32 R320 R321 R322 R323 R324 R325 R326 R327 R328 R329 4 5 3 3 3 3 3 3 3 3 3 3 3 4 5 4 5 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 3 3 3 4 3 3 3 3 3 3 3 3 3 3 R33 R33 R33 R330 R332 R333 R334 R335 R336 R337 R338 R339 R34 R34 R34 R340 R341 R342 R343 R344 R345 R346 R35 R35 R351 R352 R353 R354 R355 R356 R357 R358 R359 R36 R36 R36 R360 R361 R362 R363 R364 R365 R366 R367 R368 R369 3 4 5 3 3 3 3 3 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 4 3 3 3 3 3 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 3 3 - 310 370 285 280 280 285 280 285 250 285 285 285 295 330 320 310 355 280 280 285 280 330 310 415 285 280 280 285 280 285 280 280 285 280 330 310 285 280 280 285 280 285 280 280 285 280 - 295 330 340 285 280 280 280 285 285 280 280 280 295 330 415 285 280 280 280 285 285 250 330 320 280 280 285 280 285 280 280 285 280 330 330 370 285 280 280 285 280 285 280 280 285 280 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10014 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Equipment Designator R37 R37 R37 R370 R372 R373 R374 R375 R376 R377 R378 R379 R38 R38 R38 R380 R381 R382 R383 R384 R385 R386 R387 R389 R39 R39 R39 R4 R4 R4 R40 R40 R40 R401 R402 R403 R404 R405 R406 R407 R408 R409 R41 R41 R41 R410 Fig - Item 3 4 5 3 3 3 3 3 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 3 3 4 5 3 4 5 3 4 5 3 3 3 3 3 3 3 3 3 3 4 5 3 - 295 330 320 285 280 280 280 285 280 280 285 280 295 330 295 285 280 285 285 280 275 240 240 250 330 320 385 295 330 320 330 330 370 285 280 280 280 285 285 280 280 280 295 330 370 285 Equipment Designator R411 R412 R413 R414 R415 R416 R417 R418 R42 R42 R42 R426 R427 R428 R429 R43 R43 R43 R430 R431 R432 R433 R434 R435 R436 R437 R438 R439 R44 R44 R44 R440 R441 R442 R443 R444 R445 R446 R447 R448 R449 R45 R45 R45 R450 R451 Fig - Item 3 3 3 3 3 3 3 3 3 4 5 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 3 3 3 4 5 3 3 - 285 280 280 280 285 250 285 285 295 330 385 280 280 285 280 330 300 370 285 280 280 285 280 285 280 280 285 280 330 300 385 285 285 280 280 280 285 285 280 280 280 295 300 385 285 285 Equipment Designator R452 R46 R46 R46 R461 R462 R463 R464 R465 R466 R467 R468 R469 R47 R47 R47 R470 R471 R472 R48 R48 R48 R481 R49 R49 R49 R490 R491 R492 R493 R494 R495 R496 R497 R498 R499 R5 R5 R5 R50 R50 R50 R500 R501 R502 R503 Fig - Item 3 3 4 5 3 3 3 3 3 3 3 3 3 3 4 5 3 3 3 3 4 5 3 3 4 5 3 3 3 3 3 3 3 3 3 3 3 4 5 3 4 5 3 3 3 3 - 250 295 300 370 285 285 285 285 285 285 310 280 285 330 300 335 285 310 280 330 300 335 280 295 300 320 235 235 235 235 235 235 235 235 235 235 295 330 370 295 300 335 235 235 235 235 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10015 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Equipment Designator R504 R505 R506 R507 R51 R51 R51 R52 R52 R52 R53 R53 R53 R54 R54 R54 R55 R55 R56 R56 R57 R57 R58 R58 R59 R59 R6 R6 R6 R60 R60 R61 R61 R61 R62 R62 R63 R63 R63 R64 R64 R64 R65 R65 R65 R66 Fig - Item 3 3 3 3 3 4 5 3 4 5 3 4 5 3 4 5 4 5 4 5 4 5 4 5 4 5 3 4 5 4 5 3 4 5 4 5 3 4 5 3 4 5 3 4 5 3 - 235 235 230 230 330 300 335 330 300 320 295 300 355 295 300 355 300 320 300 310 300 365 300 385 300 360 295 330 410 300 385 215 300 395 300 395 250 300 385 250 300 455 250 290 385 250 Equipment Designator Fig - Item Equipment Designator Fig - Item R66 R67 R67 R68 R68 R69 R69 R7 R7 R7 R70 R70 R71 R71 R72 R72 R73 R73 R74 R74 R75 R75 R76 R77 R78 R78 R79 R79 R8 R8 R8 R80 R80 R81 R81 R81 R82 R82 R82 R83 R83 R83 R84 R84 R85 R85 5 3 5 3 5 3 5 3 4 5 3 5 3 5 3 5 3 5 3 5 3 5 5 5 3 5 3 5 3 4 5 3 5 3 4 5 3 4 5 3 4 5 4 5 4 5 R86 R86 R87 R87 R88 R88 R89 R89 R9 R9 R9 R90 R90 R91 R91 R91 R92 R92 R92 R93 R93 R93 R94 R94 R94 R95 R95 R95 R96 R96 R96 R97 R97 R97 R98 R98 R98 R99 R99 R99 T1 T1 T1 T1 T11 T12 4 5 4 5 4 5 4 5 3 4 5 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 3 3 5 3 3 - 385 215 320 250 355 250 355 285 330 385 285 380 250 395 250 320 270 370 280 370 265 430 385 415 270 440 280 360 285 320 385 260 360 220 300 385 225 300 385 210 300 320 300 385 300 370 - 300 430 300 415 300 385 300 355 250 320 370 300 415 315 300 385 320 300 450 315 300 415 315 300 415 315 300 385 315 300 415 315 310 370 315 330 360 315 330 430 370 370A 370B 545 375 375 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10016 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Equipment Designator T13 T14 T15 T16 T2 T2 T2 T21 T22 T23 T24 T25 T25 T26 T26 T3 T3 T3 T4 T5 T6 U1 U1 U1 U10 U10 U10 U11 U11 U11 U12 U12 U12 U13 U13 U13 U14 U14 U14 U15 U15 U15 U16 U16 U16 U17 Fig - Item 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 - 375 375 375 375 370 370A 370B 360 360 360 360 365 365A 365 365A 370 370A 370B 375 375 375 150 240 500 185 150 265 115 140 250 135 120 265 135 80 265 145 90 265 145 160 265 145 110 265 165 Equipment Designator U17 U17 U18 U18 U18 U19 U19 U19 U2 U2 U2 U20 U20 U20 U21 U21 U21 U22 U22 U22 U23 U23 U23 U24 U24 U24 U25 U25 U25 U26 U26 U26 U27 U27 U27 U27 U28 U28 U29 U29 U3 U3 U3 U30 U30 U31 Fig - Item 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 4 5 3 3 4 5 3 5 3 5 3 4 5 3 5 3 - 210 230 165 190 205 165 190 200 155 120 250 165 250 255 140 220 240 140 170 265 185 100 235 175 130 230 355 130 165 185 180 165 350 350A 200 210 175 170 175 220 180 230 230 185 175 355 Equipment Designator U31 U32 U32 U33 U33 U34 U34 U35 U35 U36 U37 U38 U39 U4 U4 U4 U40 U41 U42 U43 U44 U45 U46 U47 U48 U49 U5 U5 U5 U5 U51 U51 U52 U53 U53 U54 U55 U56 U57 U58 U59 U6 U6 U60 U61 U62 Fig - Item 5 3 5 3 5 3 5 3 5 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 3 3 3 3 5 3 3 3 - 255 185 215 355 210 175 170 185 225 355 175 165 185 180 230 260 355 180 180 185 185 355 175 355 175 185 200 200A 70 165 350 350A 185 350 350A 175 180 180 180 175 175 160 245 135 175 175 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10017 Jun 15/15 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Equipment Designator U63 U64 U65 U66 U67 U68 U69 U7 U7 U7 U70 U71 U72 U73 U74 U75 U76 U77 U78 U8 U8 Fig - Item 3 3 3 3 3 3 3 3 4 5 3 3 3 3 3 3 3 3 3 3 4 - 175 175 175 175 135 175 180 195 120 205 135 175 175 135 175 160 180 135 195 115 120 Equipment Designator Fig - Item U8 U9 U9 U9 VR1 VR1 VR10 VR11 VR11 VR12 VR12 VR13 VR14 VR14 VR15 VR16 VR17 VR18 VR19 VR2 VR2 5 3 4 5 3 5 5 3 5 3 5 3 3 5 5 5 5 5 5 3 5 - 230 130 150 230 100 110 110 85 115 85 145 85 85 140 125 125 125 125 125 100 120 Equipment Designator Fig - Item VR20 VR3 VR32 VR4 VR46 VR5 VR5 VR51 VR56 VR6 VR6 VR61 VR62 VR63 VR64 VR8 VR9 XA2P1 XA4P1 5 3 3 3 3 3 5 3 3 3 5 3 3 3 3 5 5 6 6 - 135 100 95 95 95 95 110 95 95 170 110 90 90 80 80 130 145 150 140 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. EQUIPMENT DESIGNATOR INDEX 24-23-34 Page 10018 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 NUMERICAL INDEX Airline Part Number Part Number Fig - Item CCR07CG104FS CDR31BP220BJWS CDR31BP471BJWS CDR31BP750BKWS CDR31BX472BKWS CDR32BP102BJUR CDR32BP331BKUR CDR32BP681BKUR CDR33BP152BKUR CDR33BP202BJUR CDR33BP202BJUR CDR33BX104AKUS CDR33BX104AKUS CDR33BX104AKUS CDR35BX104BKUR CDR35BX474AKUS JANTX1N5418 MS21043-04 MS21043-06 MS24693C17 MS24693C26 MS24693C28 MS24693C6 MS35338-135 MS35338-135 MS35338-136 MS51957-120 MS51957-14 MS51957-14 MS51957-14 MS51957-28 MS51957-28 MS51957-28 MS51957-28 MS51957-30 MS51957-30 MS51957-30 MS51957-33 MS51957-45 M21038-27-02 M21038-27-26 M39003-01-6213 M39006-22-0620 M39006-25-0248 5 4 3 3 5 3 5 5 5 3 5 3 4 5 5 3 5 1 1 3 1 1 1 6 6 6 6 1 5 6 1 1 1 1 5 5 5 6 1 3 3 3 5 3 - 5 25 5 10 10 15 15 20 25 25 30 20 10 35 40 30 90 300 120 385 30 190 270 30 80 110 70 220 505 20 100 170 20 230 180 470 550 100 150 360 365 35 45 40 Total Req. 4 1 4 5 1 13 1 1 5 12 3 113 44 54 1 3 6 1 2 4 2 4 1 3 7 4 7 1 2 3 6 2 4 1 2 2 2 4 2 4 2 1 2 3 Airline Part Number Part Number Fig - Item M39006-25-0248 M39006-30-0660 M45938-7-3 M45938-7-3 M63540-1-13C NAS1149CN616R NAS1149CN616R NAS1149CN616R NAS1149CN616R NAS1149CN632R NAS43DD0-12FC NAS620C4L NAS620C4L NAS622CT2 NAS662C2R3 NAS671C6 NAS671C6 RWR81S8R25FS RWR89S1R00FR RWR89S1000FM 1700678C 1700678C 1702531 1702532 1702532 1702641-1 1703290 1703290 1705126 1705126 1705126A 1705126A 1705126B 1705126B 1705127 1705291 1706299 1707474 1707474 1708554 1709225 1709225A 1709225B 1711592-1 5 5 1 1 1 5 5 5 6 1 1 6 6 1 5 5 5 3 5 5 1 5 2 1 2 1 6 6 1 3 1 3 1 3 3 1 4 1 6 5 1 1 1 1 - 50 55 250 40 260 185 475 555 120 290 280 40 90 180 580 195 485 210 270 275 80 1 40 50 1 130 50 60A 60 1 60A 1A 60B 1B 390 310 360 90 1 585 1 1A 1B 160 Total Req. 2 2 2 12 2 4 4 2 4 1 1 3 7 2 4 2 2 1 3 1 1 RF 1 1 RF 1 1 1 RF 1 RF 1 RF 1 1 1 1 RF 1 RF RF RF 1 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. NUMERICAL INDEX 24-23-34 Page 10019 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Part Number Fig - Item 1713359 1713688 1719304 1719306 1723146-1 4950924 4950987 4950987 4950987 4950987 4951007 4951009 4951061-6 5P4818-041-0046 5903285-2 5907454-14 5907454-7 5907457-1 5907471-15 5907471-15 5907473-2 5907473-2 5907473-3 5909087 5909135-19 5909152-2 5909152-5 5909208-1 5909208-126 5909208-49 5909208-49 5909512-6 5909517-1 5909517-2 5909623-2 5909632-2 5909632-2 5909632-4 5909632-6 5909632-7 5909632-7 5909632-9 5909876-1 5909880-2 5909882-1 5909882-2 5909904-7 5910060-2 1 1 1 1 3 3 3 5 6 6 5 3 3 5 5 4 5 3 2 6 2 6 2 3 5 4 5 3 3 3 5 2 6 6 6 3 4 5 5 3 5 4 5 5 5 5 5 5 - 320A 310A 310B 320B 350A 115 45 60 50A 60 525 105 60 125A 150 40 85 65 10 140 20 150 20A 370 65 290 280 215 225 220 365 30 190 180 170 50 20 70 75 55 80 30 165 170 495 495A 500 190 Total Req. 1 1 1 1 3 2 48 12 31 9 20 1 2 1 2 2 1 1 1 1 1 3 1 1 1 2 1 1 2 1 3 3 147 4 6 2 1 2 6 2 3 2 2 2 1 2 Airline Part Number Part Number Fig - Item 5910060-2 5910060-2 5910201 5910275-5 5910275-5 5910329-1 5910419-1 5910541-1 5910548-1 5910548-1 5910548-1 5910552-1 5910563-2 5910567-13 5910567-13 5910567-2 5910567-2 5910567-3 5910567-4 5910567-4 5910567-9 5910567-9 5910568-1 5910568-1 5910580-1 5910608-2 5910608-2 5910608-2 5910639-1 5910639-1 5910639-1 5910641-1 5910641-126 5910641-126 5910641-155 5910641-155 5910641-193 5910641-215 5910641-231 5910641-234 5910641-251 5910641-260 5910641-260 5910641-318 5910641-335 5910641-356 5910641-414 5 5 5 3 5 3 1 4 3 4 5 3 4 3 5 3 4 4 3 4 3 4 3 4 4 3 4 5 3 4 5 3 3 5 3 5 3 5 5 5 5 3 5 5 5 5 5 - 480 560 175 380 575 375 140 90 125 100 200 130 110 150 205 135 120 130 140 140 145 150 155 160 170 160 180 210 70 50 95 230 240 285 245 290 250 295 300 305 310 255 315 320 325 330 335 Total Req. 2 2 1 1 1 9 1 1 4 1 1 1 1 1 2 7 4 2 2 1 3 2 1 1 1 2 1 2 73 1 17 2 7 1 1 1 35 2 3 1 2 20 4 16 1 2 4 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. NUMERICAL INDEX 24-23-34 Page 10020 Jun 15/15 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Part Number Fig - Item 5910641-85 5910654-1 5910654-2 5910658-1 5910659-1 5910659-2 5910662-1 5910662-5 5910662-5 5910691-6 5910695-1 5910698-11 5910698-12 5910698-13 5910700-1 5910751-2 5910835-1 5910868-134 5910868-164 5910868-164 5910868-164 5910868-193 5910868-193 5910868-222 5910868-222 5910868-260 5910868-260 5910868-268 5910868-274 5910868-289 5910868-289 5910868-289 5910868-304 5910868-306 5910868-327 5910868-327 5910868-341 5910868-347 5910868-356 5910868-364 5910868-369 5910868-373 5910868-385 5910868-385 5910868-399 5910868-399 3 5 5 5 4 4 5 3 5 4 5 5 3 3 5 5 3 5 3 4 5 4 5 3 5 3 5 5 5 3 4 5 5 5 3 5 5 5 5 5 5 3 3 5 3 5 - 235 510 510A 215 340 350 515 345 520 190 220 340 260 265 155 530 370A 345 270 310 350 320 355 275 360 280 370 375 380 285 330 385 390 395 290 400 405 410 415 420 425 295 300 430 305 435 Total Req. 19 1 1 1 4 2 1 1 1 2 1 2 1 1 1 3 3 2 8 12 1 44 13 1 10 101 22 1 1 114 29 44 1 7 11 1 2 5 11 1 1 24 2 10 1 1 Airline Part Number Part Number Fig - Item 5910868-423 5910868-452 5910868-481 5910868-85 5910932-2 5910932-2 5910936-1 5910936-2 5910944-13 5910944-13 5910944-2 5910991-1 5910994-1 5910994-1 5911059-3 5911059-4 5911059-5 5911094-1 5911147-1 5911147-1 5911438-1 5911452-1 5911452-1 5911452-4 5911481-2 5911482-2 5911490-2 5911495-4 5911577-19 5911577-19 5911577-2 5911577-20 5911577-21 5911577-25 5911577-25 5911577-4 5911577-4 5911591-193 5911591-339 5911591-385 5911591-74 5911591-86 5911591-97 5911593-2 5911595-1 5911596-1 3 5 5 4 4 5 5 3 3 5 5 4 3 5 4 4 4 3 3 5 6 3 5 5 4 4 5 5 3 5 3 5 5 3 5 3 5 5 3 5 3 3 5 3 3 5 - 310 440 445 300 60 100 105 75 80 110 145 200 120 225 260 270 280 165 170 115 160 175 230 235 210 220 240 245 95 120 85 125 135 100 130 90 140 455 325 460 315 320 450 180 185 250 Total Req. 2 3 1 44 1 3 25 20 2 4 2 1 3 1 1 1 1 5 1 1 1 20 5 1 1 1 1 1 6 1 4 5 1 3 1 2 1 1 1 2 10 2 2 9 11 2 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. NUMERICAL INDEX 24-23-34 Page 10021 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Part Number Fig - Item 5911596-2 5911596-2 5911699-1 5911699-1 5911700-1 5911728-2 5911837-1 5911837-2 5911839-1 5911839-1 5911840-4 5911901-1 5911903-1 5911904-1 5912345-3 5912547-1 5912795-4 5913435-1 5914419-1 5914427-1 5915870-1 3 5 3 5 3 6 5 5 3 5 6 3 5 3 4 6 5 3 5 5 3 - 190 255 195 260 110 200 535 540 340 490 130 350 160 330 230 210 565 355 545 465 370B Total Req. 1 2 2 1 5 5 1 2 1 2 4 3 4 18 2 2 1 7 1 1 3 Airline Part Number Part Number Fig - Item 5915884-1 5915972-2 5916078-3 59578 5962-9206103HMX 768187-2 768187-5 768187-7 768187-7 768318 768319A 768320 769485 771541 771887E 771887E 771888-1 772058 772919 772924 3 3 3 3 3 4 4 3 5 6 1 1 1 5 1 4 1 1 4 4 - 365A 30A 200A 335 200 240 250 205 265 10 240 10 110 570 70 1 200 210 80 70 Total Req. 2 3 1 1 1 1 1 3 7 1 1 1 1 1 1 RF 1 1 1 1 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. NUMERICAL INDEX 24-23-34 Page 10022 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 DETAILED PARTS LIST IPL Figure 1 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10023 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 HE-242334-102456 IPL Figure 1 Generator Control Unit Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10024 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Fig. & Item Part Number 1 1 1709225 1-1RF - 1A 1709225A - 1B 1709225B 1-1ARF 1-1BRF 10 768320 1-101 20 MS51957-28 30 MS24693C26 1-204 1-302 40 M45938-7-3 50 1702532 1-4012 1-501 60 1705126 1-601 - 60A 1705126A - 60B 1705126B 1-60A1 1-60B1 70 771887E 1-701 80 1700678C 1-801 90 1707474 1-901 100 MS51957-28 110 769485 120 MS21043-06 1-1006 1-1101 1-1202 130 1702641-1 140 5910419-1 1-1301 1-1401 150 MS51957-45 1-1502 Eff Code 1234567 Nomenclature UNIT-GENERATOR CONTROL (ESDS) SUPSD BY ITEM 1A UNIT-GENERATOR CONTROL (ESDS) SUPSDS ITEM 1 SUPERSEDED BY ITEM -1B PRE SB 1709225-24-1 UNIT-GENERATOR CONTROL (ESDS) SUPERSEDES ITEM -1A POST SB 1709225-24-1 .ASSEMBLY-COVER-INSEPARABLE (ATTACHING PARTS) .SCREW-MACHINE-PAN HEAD .SCREW-MACHINE-FLAT HEAD –––***––– . .NUT-SELF-LOCKING-SELF-CLINCHING .ASSEMBLY-PRINTED WIRING BOARD-A1 (ESDS) FOR DETAILS SEE IPL FIGURE 2 .ASSEMBLY-PRINTED WIRING BOARD-A2 (ESDS) FOR DETAILS SEE IPL FIGURE 3 .ASSEMBLY-PRINTED WIRING BOARD-A2 (ESDS) FOR DETAILS SEE IPL FIGURE 3 .ASSEMBLY-PRINTED WIRING BOARD-A2 (ESDS) FOR DETAILS SEE IPL FIGURE 3 .ASSEMBLY-PRINTED WIRING BOARD-A3 (ESDS) FOR DETAILS SEE IPL FIGURE 4 .ASSEMBLY-PRINTED WIRING BOARD-A4 (ESDS) FOR DETAILS SEE IPL FIGURE 5 .ASSEMBLY-PRINTED WIRING BOARD-A5 (ESDS) FOR DETAILS SEE IPL FIGURE 6 (ATTACHING PARTS) .SCREW-MACHINE-PAN HEAD .PLATE-CLAMP .NUT-SELF-LOCKING –––***––– .PLATE-SERIAL-AMENDMENT .HANDLE-OVAL (ATTACHING PARTS) .SCREW-MACHINE-PAN HEAD –––***––– Upa A RF B RF C RF 1 4 2 12 1 1 1 1 1 1 1 6 1 2 A 1 1 2 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10025 Sep 29/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Fig. & Item Part Number 1 160 1711592-1 1-1601 170 MS51957-28 180 NAS622CT2 1-1702 1-1802 190 MS24693C28 200 771888-1 210 772058 1-1904 1-2001 1-2101 220 MS51957-14 230 MS51957-28 - 240 250 260 270 280 290 300 310 1-2201 1-2301 768319A M45938-7-3 M63540-1-13C MS24693C6 NAS43DD0-12FC NAS1149CN632R MS21043-04 1705291 - 310A 1713688 - 310B 1719304 - 320A 1713359 - 320B 1719306 1-2401 1-2502 1-2602 1-2701 1-2801 1-3001 1-3101 1-310A1 1-310B1 1-320A1 1-320B1 1-2901 Eff Code 1234567 Nomenclature .PLATE-IDENTIFICATION (ATTACHING PARTS) .SCREW-MACHINE-PAN HEAD –––***––– .HOOK-SUPPORT (ATTACHING PARTS) .SCREW-MACHINE-FLAT HEAD –––***––– .LABEL-WARNING .BRACKET (ATTACHING PARTS) .SCREW-MACHINE-PAN HEAD .SCREW-MACHINE-PAN HEAD –––***––– .ASSEMBLY-CHASSIS-INSEPARABLE . .NUT-SELF-LOCKING-SELF-CLINCHING . .STUD-SELF-CLINCHING . .SCREW-MACHINE-FLAT HEAD . .SPACER . .WASHER-FLAT . .NUT-SELF-LOCKING .FIRMWARE-FLIGHT CODE SUPSD BY ITEM -310A .FIRMWARE-FLIGHT CODE SUPSDS ITEM -310 SUPERSEDED BY ITEM -310B PRE SB 1709225-24-1 .FIRMWARE-FLIGHT CODE SUPERSEDES ITEM -310A POST SB 1709225-24-1 .FIRMWARE-DSP SUPSDS ITEM -320 SUPERSEDED BY ITEM -320B PRE SB 1709225-24-1 .FIRMWARE-DSP SUPERSEDES ITEM -320A POST SB 1709225-24-1 Upa 1 2 2 4 1 1 1 1 A 1 2 2 1 1 1 1 1 B 1 C 1 B 1 C 1 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10026 Sep 29/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10027 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 IPL Figure 2 HE-242334-102457 IPL Figure 2 Printed Wiring Board Assembly A1 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10028 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Fig. & Item Part Number 2 1 1702532 2-1RF 10 5907471-15 2-101 Airline Part Number Eff Code 1234567 Nomenclature ASSEMBLY-PRINTED WIRING BOARD-A1 FOR NHA SEE IPL FIGURE 1 .CONNECTOR-PRINTED WIRING BOARD P3 .CONDUCTOR-PRINTED WIRING BOARD P1 REPLD BY ITEM -20A .CONNECTOR-PRINTED WIRING BOARD P1 REPLS ITEM 20 .CONNECTOR-PRINTED WIRING BOARD P2 .ASSEMBLY-PRINTED WIRING BOARD-A1 (NP) Upa RF 1 2-10 20 5907473-2 2-201 1 2-20 - 20A 5907473-3 2-20A1 1 2-20A 30 5909512-6 2-301 1 2-30 40 1702531 2-401 1 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10029 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10030 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 1 HE-242334-102458 IPL Figure 3 (Sheet 1 of 4) Printed Wiring Board Assembly A2 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10031 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 1 HE-242334-102459 IPL Figure 3 (Sheet 2 of 4) Printed Wiring Board Assembly A2 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10032 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 1 HE-242334-102460 IPL Figure 3 (Sheet 3 of 4) Printed Wiring Board Assembly A2 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10033 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 1 HE-242334-102461 IPL Figure 3 (Sheet 4 of 4) Printed Wiring Board Assembly A2 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10034 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Fig. & Item Part Number 3 1 1705126 3-1RF - 1A 1705126A - 1B 1705126B 3-1ARF 3-1BRF 5 CDR31BP471BJWS 3-54 ASSEMBLY-PRINTED WIRING BOARD-A2 (ESDS) FOR NHA SEE IPL FIGURE 1 ASSEMBLY-PRINTED WIRING BOARD-A2 (ESDS) FOR NHA SEE IPL FIGURE 1 ASSEMBLY-PRINTED WIRING BOARD-A2 (ESDS) FOR NHA SEE IPL FIGURE 1 .CAPACITOR-470 PF ±5% 100V C59 C61 C65 C67 .CAPACITOR-75 PF ±10% 100V C7 C60 C62 C66 C68 .CAPACITOR-1000 PF ±5%-100V C2 C4 C6 C9 C11 C13 C22 C24 C26 C28 C30 C32 C46 .CAPACITOR-0.1 µF ±10% 50V C53 C56 C57 C58 C76 C79 C91 C93 C96 C105 C111 C113 C116 C119 C127 C129 C131 C133 C135 C142 C144 C146 C148 C150 C152 C154 C156 C162 C164 C166 C168 C170 C172 C182 C184 C186 C192 C194 C196 C198 C200 C206 C207 C208 C209 C210 C211 C212 C213 C215 C216 C217 C218 C219 C220 C221 C222 C223 C224 C225 C226 C227 C228 C229 C230 C231 C232 C233 C234 C235 C236 C237 C238 C239 C240 C241 C242 C243 C244 C245 C246 C247 C248 C249 C250 C251 C252 C253 C254 C255 C256 C257 C258 C259 C260 C261 C262 C263 C264 C265 C266 C267 C268 C269 C270 C271 C272 C273 C274 C275 C276 C277 C282 .CAPACITOR-2000 PF ±10% 100V C1 C3 C5 C8 C10 C12 C21 C23 C25 C27 C29 C31 .CAPACITOR-0.47 µF ±10% 50V REPLACED BY ITEM -30A C42 C43 C44 .CAPACITOR-CERAMIC-X7R-SMT REPLACES ITEM 30 C42 C43 C44 .CAPACITOR-4.7 µF ±5% 50V C78 .CAPACITOR-220 µF ±10% 75V C279 C280 C281 3-5 10 CDR31BP750BKWS 3-105 3-5 3-10 15 CDR32BP102BJUR 3-1513 25 CDR33BP202BJUR 3-2512 3-303 30A 5915972-2 3-30A3 3-351 3-20 3-20 3-20 3-20 3-20 3-20 3-20 3-20 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-20 3-20 3-20 3- 20 3-20 3-20 3-25 C RF 4 5 13 3-25 3-25 3-25 3-25 3-25 113 3- 3- 3-25 RF 3- 3-20 3-25 B 3- 3-20 3-30A 35 M39003-01-6213 3-15 3-20 3-30 - 3-15 3-20 3-25 RF 3-15 3-20 3-20 3-15 3-20 25 30 CDR35BX474AKUS 3-15 20 3-25 A 3-10 3-15 3-20 3-20 3-10 3-15 3-15 3-20 20 3-15 Upa 3-5 3-10 3-15 3-15 15 3-20113 3-5 3-10 3-15 20 CDR33BX104AKUS Eff Code 1234567 Nomenclature 12 3- 3-25 3-30 A,B 3 C 3 3-30 3-30A 3-30A 1 3-35 40 M39006-25-0248 3-403 3-40 3-40 3 3-40 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10035 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Fig. & Item Part Number 3 45 4950987 3-4548 Airline Part Number .CAPACITOR-0.01 µF ±10% 500V C41 C45 C47 C77 C80 C81 C92 C94 C95 C97 C101 C102 C103 C104 C106 C107 C112 C114 C117 C120 C126 C128 C130 C132 C134 C141 C143 C145 C147 C149 C151 C153 C155 C161 C163 C165 C167 C169 C171 C173 C181 C183 C185 C191 C193 C195 C197 C199 .CAPACITOR-10 µF ±10% 35V C51 C52 C54 C55 .CAPACITOR-1.0 µF ±10% 50V C115 C118 .CAPACITOR-100 µF ±10% 50V C283 .CONNECTOR-PRINTED WIRING BOARD J1 P1 .DIODE D6 D11 D14 D15 D16 D18 D21 D26 D27 D28 D29 D36 D37 D38 D39 D51 D52 D53 D54 D55 D56 D57 D58 D59 D60 D66 D67 D68 D69 D70 D71 D72 D73 D74 D75 D77 D79 D80 D81 D82 D83 D91 D92 D93 D94 D95 D96 D97 D98 D100 D102 D103 D106 D107 D108 D109 D110 D111 D112 D113 D114 D121 D122 D123 D124 D125 D126 D127 D128 D129 D130 D131 D132 .DIODE D10 D12 D13 D17 D19 D20 D22 D30 D40 D41 D42 D43 D46 D136 D137 D138 D139 D140 D141 D142 .DIODE-ZENER-5.1V VR63 VR64 .DIODE VR11 VR12 VR13 VR14 .DIODE VR61 VR62 .DIODE VR4 VR5 VR32 VR46 VR51 VR56 .DIODE VR1 VR2 VR3 .INDUCTOR-FERRITE-BEAD FB1 FB2 FB3 FB4 FB5 FB6 FB7 FB8 FB11 FB12 FB13 FB14 FB15 FB16 FB17 FB18 FB21 FB22 FB23 FB24 .INDUCTOR-RF CHOKE (ESDS) L1 L6 L7 L8 L9 .MICROCIRCUIT (ESDS) U8 U11 3-45 3-45 3-45 45 45 3-504 3-552 3-601 3-45 3-45 3-45 3-45 3-45 3-45 3-45 3-45 3-45 3-45 3-45 3-45 3-45 3-45 3-45 3- 3-45 3- 3-45 3-45 3-45 3-45 3- 45 3-45 3-45 3-45 3-45 3-45 3- 45 3-45 3-45 3-45 3-45 3-45 3- 45 3-45 3-45 3-50 48 3-45 3-45 3-50 Upa 3- 45 3-55 60 4951061-6 3-45 3-45 3-50 55 5909632-7 3-45 3-45 3-45 50 5909632-2 Eff Code 1234567 Nomenclature 4 3-50 2 3-55 1 3-60 65 5907457-1 3-652 3-65 70 5910639-1 3-7073 3-70 75 5910936-2 3-7520 3-70 90 5911577-4 3-854 3-902 95 5911577-19 3-956 3-1003 3-10520 3-70 3-70 3-70 3-70 3-70 3- 3-70 3-70 3-70 3-70 3-70 3- 70 3-70 3-70 3-70 3-70 3-70 3-70 3-70 3- 70 3-70 3-70 3-70 3-70 3-70 3-70 3-70 3- 70 3-70 3-70 3-70 3-70 3-70 3-70 3-70 3- 70 3-70 3-70 3-1105 3-1152 3-70 3-70 70 3-70 3-70 3-70 3-70 3-70 70 3-70 3-70 3-70 3-70 3-70 3-75 3-75 3-75 3-70 3-70 3-70 3-75 3-70 3-70 70 3-75 3-75 3-75 3-75 3-80 3-80 3-85 3-85 3-90 3-90 3-75 3-75 3-85 3-75 3- 3-75 3-95 3-95 3-105 3-105 3-105 3-105 3-105 2 6 3 3-105 3-105 3-105 3-105 3- 3-105 3-105 3-105 3-105 3-105 3-105 3-110 20 3- 3-105 3-115 4 3-95 105 3-110 2 3-100 3-105 3-110 20 3- 3-85 3-95 3-100 3- 3- 3-75 3-75 3- 3-70 3-75 3-75 3-75 3-95 3-70 105 3-110 115 4950924 3-70 73 3- 3-70 3-105 110 5911700-1 3-70 3-70 3-100 105 4951009 3-70 3-70 3-95 100 5911577-25 3-70 3-70 75 85 5911577-2 3-70 70 75 3-802 3-70 70 3-75 80 5910944-13 2 3-65 5 3-110 2 3-115 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10036 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Fig. & Item Part Number 3 120 5910994-1 3-1203 Airline Part Number .MICROCIRCUIT-DIFFERENTIAL COMPARATOR (ESDS) AR4 AR10 AR11 .MICROCIRCUIT-JFET OPERATIONAL AMPLIFIER (ESDS) AR1 AR2 AR3 AR8 .MICROCIRCUIT-QUAD SPST ANALOG SWITCH (ESDS) U9 .MICROCIRCUIT-DIGITAL CMOS (ESDS) U12 U13 U60 U67 U70 U73 U77 .MICROCIRCUIT-DIGITAL CMOS (ESDS) U21 U22 .MICROCIRCUIT-DIGITAL CMOS (ESDS) U14 U15 U16 .MICROCIRCUIT-DIGITAL CMOS (ESDS) U1 .MICROCIRCUIT-PRECISION 5V REFERENCE (ESDS) U2 .MICROCIRCUIT-VOLTAGE REGULATOR (ESDS) U6 U75 .MICROCIRCUIT-LINE DRIVER-OCTAL BUFFER (ESDS) U17 U18 U19 U20 U38 .MICROCIRCUIT (ESDS) VR6 .MICROCIRCUIT-OPTO-COUPLER (ESDS) U24 U28 U29 U34 U37 U46 U48 U54 U58 U59 U61 U62 U63 U64 U65 U66 U68 U71 U72 U74 .MICROCIRCUIT (ESDS) U3 U4 U41 U42 U55 U56 U57 U69 U76 .MICROCIRCUIT-OPTO-COUPLER (ESDS) U10 U23 U26 U30 U32 U35 U39 U43 U44 U49 U52 .MICROCIRCUIT-OPERATIONAL AMPLIFIER (ESDS) AR9 3-120 125 5910548-1 3-1254 3-120 3-125 130 5910552-1 3-1301 Eff Code 1234567 Nomenclature 3-125 Upa 3 3-120 3-125 4 3-125 1 3-130 135 5910567-2 3-1357 3-135 140 5910567-4 3-1402 3-135 3-140 145 5910567-9 3-1453 3-1501 3-135 3-135 3-135 3-135 2 3-140 3-145 150 5910567-13 3-135 7 3-145 3 3-145 1 3-150 155 5910568-1 3-1551 1 3-155 160 5910608-2 3-1602 3-160 165 5911094-1 3-1655 3-160 3-165 170 5911147-1 3-1701 2 3-165 3-165 3-165 5 3-165 1 3-170 175 5911452-1 3-17520 3-175 180 5911593-2 3-1809 3-175 3-175 175 3-175 3-175 3-175 3-175 3-175 3-180 3-180 3-180 3-180 3-175 3-175 3-175 3-180 3- 3- 3-180 9 3- 3-180 3-185 3-1901 3-175 3-175 185 190 5911596-2 3-175 3-175 3-180 3-18511 3-175 3-175 180 185 5911595-1 3-175 175 20 3-185 3-185 3-185 3-185 3-185 3-185 3-185 3-185 11 3- 3-185 1 3-190 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10037 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Fig. & Item Part Number 3 195 5911699-1 3-1952 .MICROCIRCUIT-OPTO-COUPLER (ESDS) U7 U78 .MICROCIRCUIT A (ESDS) U5 .TRANSCEIVER - 1553 B (ESDS) U5 .MICROCIRCUIT (ESDS) AR5 AR6 AR7 .RESISTOR-8.25 OHM ±1% 1W R83 .RESISTOR-1K OHM ±0.1% 1/8W R61 R67 .RESISTOR-3.16K OHM ±0.1% 1/8W R81 .RESISTOR-20K OHM ±0.1% 1/8W R82 .RESISTOR-10 OHM ±1% 1/4W R506 R507 .RESISTOR-75 OHM ±1% 1/4W R11 R123 R124 R490 R491 R492 R493 R494 R495 R496 R497 R498 R499 R500 R501 R502 R503 R504 R505 .RESISTOR-220 OHM ±1% 1/4W R105 R107 R163 R252 R253 R386 R387 .RESISTOR-402 OHM ±1% 1/4W R106 .RESISTOR-1K OHM ±1% 1/4W R9 R63 R64 R65 R66 R68 R69 R71 R72 R109 R112 R113 R125 R127 R128 R131 R132 R141 R148 R153 R166 R173 R180 R196 R216 R223 R230 R235 R241 R246 R296 R346 R389 R416 R452 .RESISTOR-4.99K OHM ±1% 1/4W R142 R144 R149 R151 R167 R169 R174 R176 R181 R183 R197 R199 R217 R219 R224 R226 R231 R233 R242 R244 .RESISTOR-10.2 OHM ±0.5% 1W R80 .RESISTOR-16.5 OHM ±0.5% 1W R75 .RESISTOR-499 OHM ±1% 1/8W R73 R78 R191 R203 R205 R261 R263 R265 .RESISTOR-2K OHM ±1% 1/10W R385 3-195 200 5962-9206103HMX 3-2001 Eff Code 1234567 Nomenclature Upa 2 3-195 1 3-200 - 200A 5916078-3 3-200A1 1 3-200A 205 768187-7 3-2053 3-205 210 RWR81S8R25FS 3-2101 3-205 3 3-205 1 3-210 215 5909208-1 3-2152 3-215 220 5909208-49 3-2201 2 3-215 1 3-220 225 5909208-126 3-2251 1 3-225 230 5910641-1 3-2302 3-230 235 5910641-85 3-23519 3-235 240 5910641-126 3-2407 3-235 3-235 3-235 3-235 3-235 3-235 3-235 3-235 3- 3-235 3-235 3-235 3-235 3-235 3- 235 3-235 3-240 3-240 3-240 19 3- 235 240 3-2451 3-235 235 3-240 245 5910641-155 2 3-230 3-240 7 3- 3-240 1 3-245 250 5910641-193 3-25035 3-250 250 255 5910641-260 3-25520 3-250 3-250 3-2601 3-250 3-250 3-250 3-250 3-250 3-250 3-250 3-250 3- 3-250 3-250 3-250 3-250 3-250 3- 250 3-250 3-250 3-250 3-250 3-250 3- 250 3-250 3-250 3-250 3-250 3-250 3- 250 3-250 3-250 3-250 3-255 3-255 3-255 35 3- 250 3-255 260 5910698-12 3-250 3-255 20 3- 255 3-255 3-255 3-255 3-255 3-255 3- 255 3-255 3-255 3-255 3-255 3-255 3- 255 3-255 3-255 1 3-260 265 5910698-13 3-2651 1 3-265 270 5910868-164 3-2708 3-270 -270 275 5910868-222 3-2751 3-270 3-270 3-270 3-270 3-270 8 3 3-270 1 3-275 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10038 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Fig. & Item Part Number 3 280 5910868-260 3-280101 Airline Part Number .RESISTOR-4.99K OHM ±1% 1/10W R10 R74 R79 R110 R111 R114 R121 R155 R192 R193 R204 R206 R262 R264 R266 R271 R272 R274 R276 R277 R279 R281 R282 R284 R286 R287 R289 R291 R292 R294 R306 R307 R309 R311 R312 R314 R316 R317 R319 R321 R322 R324 R326 R327 R329 R332 R333 R334 R337 R338 R339 R341 R342 R343 R351 R352 R354 R356 R357 R359 R361 R362 R364 R366 R367 R369 R372 R373 R374 R376 R377 R379 R381 R384 R402 R403 R404 R407 R408 R409 R412 R413 R414 R426 R427 R429 R431 R432 R434 R436 R437 R439 R442 R443 R444 R447 R448 R449 R468 R472 R481 .RESISTOR-10K ±1%-.125 R7 R8 R70 R103 R104 R108 R115 R116 R122 R129 R130 R133 R143 R145 R147 R150 R152 R154 R157 R158 R168 R170 R172 R175 R177 R179 R182 R184 R186 R195 R198 R200 R202 R207 R218 R220 R222 R225 R227 R229 R232 R239 R240 R243 R250 R251 R273 R275 R278 R280 R283 R285 R288 R290 R293 R295 R297 R298 R299 R308 R310 R313 R315 R318 R320 R323 R325 R328 R330 R335 R336 R340 R344 R345 R353 R355 R358 R360 R363 R365 R368 R370 R375 R378 R380 R382 R383 R401 R405 R406 R410 R411 R415 R417 R418 R428 R430 R433 R435 R438 R440 R441 R445 R446 R450 R451 R461 R462 R463 R464 R465 R466 R469 R470 .RESISTOR-24.9K OHM ±1% 1/4W R146 R156 R171 R178 R185 R194 R201 R221 R228 R238 R249 .RESISTOR-75K OHM ±1% 1/8W R1 R2 R3 R4 R5 R6 R14 R15 R18 R19 R22 R23 R33 R34 R37 R38 R41 R42 R45 R46 R49 R50 R53 R54 .RESISTOR-100K OHM ±1% 1/10W R160 R161 .RESISTOR-140K OHM ±1% 1/4W R159 .RESISTOR-249K OHM ±1% 1/10W R467 R471 3-280 285 5910868-289 3-285114 3-280 3-29011 3-3002 3-280 3-280 3-280 3- 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-280 3- 280 3-280 3-280 3-280 3-280 3-285 3-285 3-285 3-285 3-285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3- 285 3-285 3-285 3-285 3-285 3-285 3-290 3-295 3-3051 3-290 3-290 3-295 3-290 3-290 3-295 3-290 3-290 3-295 3-295 101 114 3- 285 3-290 Upa 3- 3-280 11 3- 3-290 3-295 3-295 24 3- 295 3-295 3-295 3-295 3-295 3-295 3-295 3- 295 3-295 3-295 3-295 3-295 3-295 3-295 3- 295 3-295 3-300 305 5910868-399 3-280 3-280 3-295 300 5910868-385 3-280 3-280 290 3-29524 3-280 280 3-290 295 5910868-373 3-280 280 3-285 290 5910868-327 Eff Code 1234567 Nomenclature 2 3-300 1 3-305 310 5910868-423 3-3102 3-310 2 3-310 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10039 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Fig. & Item Part Number 3 315 5911591-74 3-31510 .RESISTOR-57.6 OHM ±1% 1W R91 R93 R94 R95 R96 R97 R98 R99 R100 R101 .RESISTOR-76.8 OHM ±1% 1W R92 R102 .RESISTOR-33.2K OHM ±1% 1W R24 .RESISTOR-CURRENT SENSE 1 OHM ±1% 1/2W (ESDS) R12 R13 R16 R17 R20 R21 R31 R32 R35 R36 R39 R40 R43 R44 R47 R48 R51 R52 .RELAY K2 .RELAY-DPDT (ESDS) K1 .SEMICONDUCTOR-MOSFET (ESDS) Q1 .TRANSISTOR-SMART SWITCH (ESDS) U27 U51 U53 REPLACED BY ITEM -350A .TRANSISTOR-SMART SWITCH (ESDS) U27 U51 U53 REPLACES ITEM 350 .TRANSISTOR-SMART SWITCH (ESDS) U25 U31 U33 U36 U40 U45 U47 .TRANSFORMER-PULSE T21 T22 T23 T24 .TRANSFORMER-PULSE A T25 T26 .TRANSFORMER-PULSE B T25 T26 .TRANSFORMER-AUDIO A T1 T2 T3 .TRANSFORMER-AUDIO T1 T2 T3 REPLD BY ITEM -370B .TRANSFORMER-AUDIO T1 T2 T3 REPLS ITEM -370A .TRANSFORMER-SIGNAL T4 T5 T6 T11 T12 T13 T14 T15 T16 3-315 315 320 5911591-86 3-3202 3-315 3-3251 3-315 3-315 3-315 3-315 3-315 3-315 Upa 10 3- 3-315 3-320 325 5911591-339 Eff Code 1234567 Nomenclature 2 3-320 1 3-325 330 5911904-1 3-33018 3-330 335 59578 3-3351 3-330 3-330 330 3-330 3-330 3-330 330 3-330 3-330 3-330 3-330 3-330 3-330 3-330 3-330 3-330 3-330 18 3- 3- 1 3-335 340 5911839-1 3-3401 1 3-340 345 5910662-5 3-3451 1 3-345 350 5911901-1 3-3503 3-350 - 350A 1723146-1 3-350A3 3-350 3-350A 355 5913435-1 3-3557 365 M21038-27-26 - 365A 5915884-1 3-3604 3-3652 3-365A2 3-355 3-360 3-360 3-365 3-365 3-365A 370 5909087 3-3703 3-370 - 370A 5910835-1 - 370B 5915870-1 375 5910329-1 3-370A3 3-370B3 3-3759 3-350 3-350A 3-355 360 M21038-27-02 3 3-350A 3-355 3-360 3-355 3-355 3-355 7 3-355 4 3-360 2 2 3-365A 3-370 3-370A 3-370A 3-370B 3-370B 3-370B 3-375 3 3-370 3-370A 3-375 3 3-375 3-375 3-375 3-375 3-375 3-375 3 3 9 3- 375 380 5910275-5 3-3801 385 MS24693C17 390 1705127 3-3901 3-3854 .RETAINER-PRINTED WIRING BOARD (ATTACHING PARTS) .SCREW-MACHINE-FLAT HEAD –––***––– .ASSEMBLY-PRINTED WIRING BOARD-A2 (NP) 1 4 1 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10040 Jun 15/15 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2 20 10 130 250 290 10 120 150 10 120 150 70 10 20 10 10 230 90 60 10 40 30 10 140 230 220 10 190 240 10 20 10 110 260 20 190 270 10 20 10 10 170 280 80 10 120 10 210 10 50 10 ELECTROSTATIC DISCHARGE SENSITIVE (ESDS) 160 180 10 100 10 200 25 HE-242334-102462-A IPL Figure 4 (Sheet 1 of 2) Printed Wiring Board Assembly A3 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10041 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 2 HE-242334-102463 IPL Figure 4 (Sheet 2 of 2) Printed Wiring Board Assembly A3 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10042 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Fig. & Item Part Number 4 1 771887E 4-1RF 10 CDR33BX104AKUS 4-1044 ASSEMBLY-PRINTED WIRING BOARD-A3 (ESDS) FOR NHA SEE IPL FIGURE 1 .CAPACITOR-0.1 µF ±10% 50V C1 C2 C3 C4 C5 C6 C7 C8 C9 C10 C11 C12 C13 C14 C15 C16 C17 C18 C19 C20 C21 C22 C23 C24 C25 C26 C27 C32 C33 C34 C35 C36 C37 C38 C39 C40 C41 C42 C43 C44 C45 C54 C55 C56 .CAPACITOR-10 µF ±10% 35V C47 C48 C49 C50 C51 C53 .CAPACITOR-22 pF ±5% 100V C52 .CAPACITOR-47 µF ±10% 20V C57 C58 .CONNECTOR-PRINTED WIRING BOARD J1 .DIODE D1 .DIODE D2 .ASSEMBLY-FIRMWARE-BOOT (ESDS) U5 .ASSEMBLY-FIRMWARE-WATCHDOG (ESDS) U13 .MICROCIRCUIT-DIFFERENTIAL BUS TRANSCEIVER (ESDS) U14 .MICROCIRCUIT-JFET OPERATIONAL AMPLIFIER (ESDS) U23 .MICROCIRCUIT-ANALOG TO DIGITAL CONVERTER (ESDS) U16 .MICROCIRCUIT-DIGITAL CMOS (ESDS) U2 U7 U8 U12 .MICROCIRCUIT-DIGITAL CMOS (ESDS) U24 U25 .MICROCIRCUIT-DIGITAL CMOS (ESDS) U11 4-10 20 5909632-2 4-206 4-10 4-251 4-10 4-10 4-10 4-10 4-10 4-10 4-10 10 4-10 4-10 4-10 4-10 4-10 4-10 4-10 4- 4-10 4-10 4-10 4-10 4-10 4-10 4-10 4- 10 4-10 4-10 4-10 4-10 4-10 4-10 4-10 4- 10 4-10 4-10 4-10 4-10 4-10 4-10 4-10 4- 10 4-10 4-10 4-20 4-20 4-20 4-20 Upa RF 44 4- 10 4-20 25 CDR31BP220BJWS Eff Code 1234567 Nomenclature 6 4-20 1 4-25 30 5909632-9 4-302 4-30 40 5907454-14 4-401 2 4-30 1 4-40 50 5910639-1 4-501 1 4-50 60 5910932-2 4-601 1 4-60 70 772924 4-701 1 4-70 80 772919 4-801 1 4-80 90 5910541-1 4-901 1 4-90 100 5910548-1 4-1001 1 4-100 110 5910563-2 4-1101 1 4-110 120 5910567-2 4-1204 4-120 130 5910567-3 4-1302 4-130 140 5910567-4 4-1401 4-120 4-120 4 4-120 2 4-130 1 4-140 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10043 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Fig. & Item Part Number 4 150 5910567-9 4-1502 Airline Part Number .MICROCIRCUIT-DIGITAL CMOS (ESDS) U9 U10 .MICROCIRCUIT-PRECISION 5V REFERENCE (ESDS) U15 .MICROCIRCUIT-HIGH-SPEED ANALOG SWITCH (ESDS) U22 .MICROCIRCUIT-VOLTAGE REGULATOR (ESDS) U26 .MICROCIRCUIT-ANALOG MULTIPLEXER (ESDS) U18 U19 .MICROCIRCUIT (ESDS) U27 .MICROCIRCUIT-DIGITAL SIGNAL PROCESSOR (ESDS) (MSD) U17 .MICROCIRCUIT-ASIC (ESDS) (MSD) U21 .MICROCIRCUIT-STATIC RAM (ESDS) U3 U4 .MICROCIRCUIT (ESDS) U1 .MICROCIRCUIT (ESDS) U20 .OSCILLATOR-CRYSTAL (ESDS) G1 .OSCILLATOR-CRYSTAL (ESDS) G2 .OSCILLATOR-CRYSTAL (ESDS) G3 .RESISTOR-NETWORK 3.9K OHM ±2% 1/10W R65 4-150 160 5910568-1 4-1601 Eff Code 1234567 Nomenclature Upa 2 4-150 1 4-160 170 5910580-1 4-1701 1 4-170 180 5910608-2 4-1801 1 4-180 190 5910691-6 4-1902 4-190 200 5910991-1 4-2001 2 4-190 1 4-200 210 5911481-2 4-2101 1 4-210 220 5911482-2 4-2201 1 4-220 230 5912345-3 4-2302 4-230 240 768187-2 4-2401 2 4-230 1 4-240 250 768187-5 4-2501 1 4-250 260 5911059-3 4-2601 1 4-260 270 5911059-4 4-2701 1 4-270 280 5911059-5 4-2801 1 4-280 290 5909152-2 4-2901 1 4-290 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10044 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Fig. & Item Part Number 4 300 5910868-85 4-30044 Airline Part Number .RESISTOR-75 OHM ±1% 1/10W R10 R13 R24 R26 R27 R43 R44 R45 R46 R47 R48 R49 R50 R51 R52 R53 R54 R55 R56 R57 R58 R59 R60 R61 R62 R63 R64 R81 R82 R83 R84 R85 R86 R87 R88 R89 R90 R91 R92 R93 R94 R95 R96 R145 .RESISTOR-499 OHM ±1% 1/10W R14 R18 R19 R29 R30 R31 R32 R97 R135 R136 R141 R142 .RESISTOR-1K OHM ±1% 1/10W R8 R9 R15 R16 R17 R20 R21 R22 R23 R25 R28 R35 R39 R103 R104 R105 R106 R107 R108 R109 R110 R111 R112 R113 R114 R115 R116 R117 R118 R119 R120 R121 R122 R123 R124 R125 R126 R127 R128 R129 R130 R134 R137 R140 .RESISTOR-10K OHM ±1% 1/10W R1 R2 R3 R4 R5 R6 R7 R33 R34 R36 R37 R38 R40 R41 R42 R98 R99 R100 R101 R102 R131 R132 R133 R138 R139 R143 R144 R146 R147 .TRANSISTOR (ESDS) Q1 Q2 Q3 Q6 .TRANSISTOR (ESDS) Q4 Q5 .ASSEMBLY-PRINTED WIRING BOARD-A3 (NP) 4-300 4-31012 4-300 4-300 4-300 4-300 4-300 4- 4-300 4-300 4-300 4-300 4-300 4- 300 4-300 4-300 4-300 4-300 4-300 4-300 4- 300 4-300 4-300 4-300 4-300 4-300 4-300 4- 300 4-300 4-300 4-300 4-300 4-300 4-300 4- 4-310 4-3502 4-3601 4-320 4-310 4-310 4-310 4-320 4-320 44 4- 4-320 4-320 4-310 4-320 4-320 4-320 4-320 4-320 4-320 4-320 4-320 4-320 4-320 320 4-320 4-320 4-320 4-320 4-320 320 4-320 4-320 4-320 4-320 4-320 330 4-330 330 4-330 4-330 4-330 4-330 4-330 4-330 330 4-330 330 4-330 4-340 4-340 4-330 4-320 4-320 4-330 4-330 4-330 4-330 4-320 4-330 4-330 4-330 4- 4- 4-320 4-330 4-330 4- 4-320 4-320 44 4- 4-320 4-320 320 4-330 12 4- 4-310 4-320 4-320 4-310 320 4-350 360 1706299 4-310 4-320 4-320 4-340 350 5910659-2 4-310 4-310 4-330 4-3404 Upa 4-300 320 340 5910659-1 4-300 4-300 320 4-33029 4-300 4-300 4-320 330 5910868-289 4-300 4-300 310 4-32044 4-300 300 4-310 320 5910868-193 4-300 300 300 310 5910868-164 Eff Code 1234567 Nomenclature 4- 4- 4-330 4-330 4-330 4-330 29 4- 4- 4- 4- 4 4-340 2 4-350 1 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10045 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10046 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 3 HE-242334-102464 IPL Figure 5 (Sheet 1 of 6) Printed Wiring Board Assembly A4 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10047 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 3 HE-242334-102465 IPL Figure 5 (Sheet 2 of 6) Printed Wiring Board Assembly A4 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10048 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 3 570 545 65 460 150 105 105 105 105 105 160 105 505 530 500 520 185 565 185 190 105 505 100 195 180 105 55 B 275 515 55 100 530 125 125 135 120 210 175 85 140 155 125 130 70 105 80 175 (REF) SECTION B-B B ELECTROSTATIC DISCHARGE SENSITIVE (ESDS) IPL Figure 5 (Sheet 3 of 6) Printed Wiring Board Assembly A4 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10049 Jun 6/14 PRIMARY SIDE HE-242334-102466-A HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 3 550 555 560 310 370 325 550 555 560 330 410 25 295 320 370 320 385 385 35 60 385 335 385 25 35 320 60 305 355 35 405 385 345 435 385 390 60 35 430 395 385 440 385 585 35 ELECTROSTATIC DISCHARGE SENSITIVE (ESDS) 575 SECONDARY SIDE IPL Figure 5 (Sheet 4 of 6) Printed Wiring Board Assembly A4 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10050 Jun 6/14 425 290 360 35 430 35 410 365 320 450 HE-242334-102467-A HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 3 HE-242334-102468 IPL Figure 5 (Sheet 5 of 6) Printed Wiring Board Assembly A4 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10051 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 3 HE-242334-102469 IPL Figure 5 (Sheet 6 of 6) Printed Wiring Board Assembly A4 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. 24-23-34 DETAILED PARTS LIST Page 10052 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Fig. & Item Part Number 5 1 1700678C 5-1RF 5 CCR07CG104FS 5-54 ASSEMBLY-PRINTED WIRING BOARD-A4 (ESDS) FOR NHA SEE IPL FIGURE 1 .CAPACITOR-0.1 µF ±10% 50V C16 C17 C31 C64 .CAPACITOR-4700 PF ±10% 100V C19 .CAPACITOR-330 PF ±10% 100V C21 .CAPACITOR-680 PF ±10% 100V C14 .CAPACITOR-1500 PF ±10% 100V C8 C9 C20 C23 C27 .CAPACITOR-2000 PF ±10% 100V C3 C4 C5 .CAPACITOR-0.1 µF ±10% 50V C1 C2 C11 C12 C18 C22 C24 C26 C28 C29 C38 C39 C40 C45 C50 C51 C52 C53 C54 C55 C63 C65 C66 C67 C68 C69 C70 C71 C72 C73 C74 C75 C76 C77 C78 C79 C80 C81 C82 C83 C84 C85 C86 C87 C88 C89 C90 C91 C92 C93 C94 C95 C102 C104 .CAPACITOR-0.1 µF ±10% 100V C30 .CAPACITOR-110 µF ±10% 75V C49 C56 .CAPACITOR-220 µF ±10% 75V C44 C57 .CAPACITOR-56 µF ±10% 125V C35 C36 .CAPACITOR-0.1 µF ±10% 50V C6 C13 C32 C33 C34 C37 C58 C96 C97 C98 C99 C101 .CAPACITOR-0.5 µF ±10% 200V C100 .CAPACITOR-4.75 µF ±10% 50V C43 C60 .CAPACITOR-22 µF ±10% 20V C25 .CAPACITOR-1.0 µF ±10% 50V C10 C41 C42 C46 C59 C103 .CONNECTOR-PRINTED WIRING BOARD J1 P1 .DIODE D17 D18 D19 D20 D21 D22 .DIODE D2 D5 D6 D7 D8 D9 D10 D11 D12 D13 D42 D45 D46 D47 D48 D49 D50 5-5 10 CDR31BX472BKWS 5-101 Eff Code 1234567 Nomenclature 5-5 5-5 Upa RF 4 5-5 1 5-10 15 CDR32BP331BKUR 5-151 1 5-15 20 CDR32BP681BKUR 5-201 1 5-20 25 CDR33BP152BKUR 5-255 30 CDR33BP202BJUR 5-303 35 CDR33BX104AKUS 5-3554 40 CDR35BX104BKUR 5-401 5-25 5-25 5-30 5-30 5-35 5-35 5-25 5-25 5 5-25 3 5-30 5-35 5-35 5-35 5-35 5-35 5-35 35 5-35 5-35 5-35 5-35 5-35 5-35 5-35 5- 35 5-35 5-35 5-35 5-35 5-35 5-35 5-35 5- 35 5-35 5-35 5-35 5-35 5-35 5-35 5-35 5- 35 5-35 5-35 5-35 5-35 5-35 5-35 5-35 5- 35 5-35 5-35 5-35 5-35 5-35 5-35 5-35 5- 35 5-35 5-35 5-35 5-35 54 5- 5-35 1 5-40 45 M39006-22-0620 5-452 50 M39006-25-0248 5-502 55 M39006-30-0660 5-552 60 4950987 5-6012 5-45 5-45 5-50 5-50 5-55 5-55 5-60 5-60 60 65 5909135-19 5-651 5-60 5-60 5-60 5-60 5-60 5-60 5-60 5-60 2 2 2 12 5- 5-60 1 5-65 70 5909632-4 5-702 5-70 75 5909632-6 5-751 2 5-70 1 5-75 80 5909632-7 5-806 5-80 85 5907454-7 5-852 5-85 90 JANTX1N5418 5-906 5-80 5-9517 5-90 5-95 5-95 5-80 5-80 6 5-80 2 5-85 5-90 95 5910639-1 5-80 5-95 5-95 5-90 5-95 5-95 5-90 5-95 5-95 5-95 5-90 5-95 5-95 6 5-90 5-95 5-95 5-95 5-95 17 5-95 5-95 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10053 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Fig. & Item Part Number 5 100 5910932-2 5-1003 .DIODE D32 D51 D52 .DIODE D3 D4 D14 D15 D16 D23 D24 D25 D26 D27 D28 D29 D30 D31 D33 D34 D35 D36 D37 D38 D39 D40 D41 D43 D44 .DIODE-ZENER-5.1V VR1 VR5 VR6 VR10 .DIODE (ESDS) VR11 .DIODE-ZENER-40V VR2 .DIODE-ZENER-170V VR15 VR16 VR17 VR18 VR19 DELETED (DIODE) .DIODE-ZENER-45V VR8 .DIODE-ZENER-58V VR20 .DIODE-ZENER-9V VR14 .DIODE-ZENER-10V VR9 VR12 .BEAD-FERRITE-RING L1 L2 .INDUCTOR-POWER (ESDS) L7 .INDUCTOR-HIGH CURRENT (ESDS) L3 L4 L5 L6 .MICROCIRCUIT-VOLTAGE COMPARATOR (ESDS) U5 U25 U26 .MICROCIRCUIT-VOLTAGE REFERENCE (ESDS) U28 U34 .MICROCIRCUIT-HYBRID POWER SUPPLY (ESDS) U30 (ATTACHING PARTS) .SCREW-MACHINE-PAN HEAD .WASHER-FLAT .WASHER-LOCKING-SQUARE .NUT-SELF-LOCKING –––***––– 5-100 105 5910936-1 5-10525 5-100 5-105 110 5910944-13 5-1104 5-1151 Upa 3 5-100 5-105 5-105 5-105 5-105 5-105 5-105 105 5-105 5-105 5-105 5-105 5-105 5-105 5- 5-105 5-105 5-105 5-105 5-105 5-105 5- 105 5-105 5-105 5-105 5-110 5-110 25 5- 105 5-110 115 5911147-1 Eff Code 1234567 Nomenclature 4 5-110 1 5-115 120 5911577-19 5-1201 1 5-120 125 5911577-20 5-1255 5-125 - 125A 5P4818-041-0046 130 5911577-25 5-125A 5-1301 5-125 5-125 5-125 5 5-125 1 5-130 135 5911577-21 5-1351 1 5-135 140 5911577-4 5-1401 1 5-140 145 5910944-2 5-1452 5-145 150 5903285-2 5-1502 5-150 155 5910700-1 5-1551 2 5-145 2 5-150 1 5-155 160 5911903-1 5-1604 5-160 165 5909876-1 5-1653 5-165 170 5909880-2 5-1702 5-170 175 5910201 5-1751 5-160 5-160 5-165 4 5-160 3 5-165 2 5-170 1 5-175 180 185 190 195 MS51957-30 NAS1149CN616R 5910060-2 NAS671C6 5-1802 5-1902 5-1952 5-1854 2 4 2 2 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10054 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Fig. & Item Part Number 5 200 5910548-1 5-2001 Eff Code 1234567 Nomenclature .MICROCIRCUIT-JFET OPERATIONAL AMPLIFIER (ESDS) U19 .MICROCIRCUIT-DIGITAL CMOS (ESDS) U7 U18 .MICROCIRCUIT-VOLTAGE REGULATOR (ESDS) U27 U33 .MICROCIRCUIT (ESDS) U32 .MICROCIRCUIT-VOLTAGE CONVERTER (ESDS) U29 .MICROCIRCUIT-DIFFERENTIAL COMPARATOR (ESDS) U35 .MICROCIRCUIT-OPTO-COUPLER (ESDS) U3 U8 U9 U17 U24 .MICROCIRCUIT-OPTO-COUPLER (ESDS) U23 .MICROCIRCUIT-OPTO-COUPLER (ESDS) U21 .MICROCIRCUIT-SOLID STATE RELAY (ESDS) U6 .MICROCIRCUIT-OPERATIONAL AMPLIFIER (ESDS) U2 U11 .MICROCIRCUIT-OPERATIONAL AMPLIFIER (ESDS) U20 U31 .MICROCIRCUIT-OPTO-COUPLER (ESDS) U4 .MICROCIRCUIT (ESDS) U10 U12 U13 U14 U15 U16 U22 .RESISTOR-1 OHM ±1% 3W R154 R168 R181 .RESISTOR-100 OHM ±1% 3W R125 .RESISTOR-NETWORK 10K OHMS ±2% 0.19W R1 Upa 1 5-200 205 5910567-13 5-2052 5-205 210 5910608-2 5-2102 5-205 5-210 215 5910658-1 5-2151 2 2 5-210 1 5-215 220 5910695-1 5-2201 1 5-220 225 5910994-1 5-2251 1 5-225 230 5911452-1 5-2305 5-230 235 5911452-4 5-2351 5-230 5-230 5-230 5 5-230 1 5-235 240 5911490-2 5-2401 1 5-240 245 5911495-4 5-2451 1 5-245 250 5911596-1 5-2502 5-250 255 5911596-2 5-2552 5-250 5-255 260 5911699-1 5-2601 2 2 5-255 1 5-260 265 768187-7 5-2657 5-265 270 RWR89S1R00FR 5-2703 5-270 275 RWR89S1000FM 5-2751 5-265 5-265 5-270 5-265 5-265 5-265 7 5-265 3 5-270 1 5-275 280 5909152-5 5-2801 1 5-280 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10055 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Fig. & Item Part Number 5 285 5910641-126 5-2851 Airline Part Number Eff Code 1234567 Nomenclature .RESISTOR-220 OHM ±1% 1/4W R164 .RESISTOR-402 OHM ±1% 1/4W R174 .RESISTOR-1.69K OHM ±1% 1/4W R38 R180 .RESISTOR-2.49K OHM ±1% 1/4W R101 R103 R104 .RESISTOR-2.67K OHM ±1% 1/4W R144 .RESISTOR-4.02K OHM ±1% 1/4W (ESDS) R56 R133 .RESISTOR-4.99K OHM ±1% 1/4W R136 R155 R169 R170 .RESISTOR-20K OHM ±1% 1/4W R3 R4 R15 R17 R28 R37 R49 R52 R55 R67 R72 R83 R105 R135 R150 R175 .RESISTOR-3.01K OHM ±1% 1/4W R116 .RESISTOR-49.9K OHM ±1% 1/4W R115 R117 .RESISTOR-200K OHM ±1% 1/4W R47 R48 R50 R51 .RESISTOR-10K OHM ±1% 1W R2 R33 .RESISTOR-243 OHM ±1% 1/8W R145 R179 .RESISTOR-499 OHMS ±1% 1/10W R106 .RESISTOR-1K OHM ±1% 1/8W R30 R53 R54 R68 R69 R89 R100 R110 R160 R163 R172 R177 R185 .RESISTOR-2K OHM ±1% 1/10W R20 R59 R79 R80 R98 R131 R147 R166 R189 R190 .RESISTOR-3.16K OHM ±1% 1/8W R57 R176 .RESISTOR-4.99K OHM ±1% 1/10W R5 R9 R11 R12 R29 R36 R40 R41 R43 R46 R73 R74 R85 R97 R111 R122 R129 R138 R165 R171 R182 R191 .RESISTOR-6.04K OHM ±1% 1/4W R137 .RESISTOR-6.98K OHM ±1% 1/10W (ESDS) R70 Upa 1 5-285 290 5910641-155 5-2901 1 5-290 295 5910641-215 5-2952 5-295 300 5910641-231 5-3003 5-300 305 5910641-234 5-3051 2 5-295 5-300 3 5-300 1 5-305 310 5910641-251 5-3102 5-310 315 5910641-260 5-3154 5-310 5-315 320 5910641-318 5-32016 5-320 320 5-3251 5-315 5-320 5-315 5-320 5-320 5-320 5-320 4 5-315 5-320 5-320 5-320 5-320 5-320 5-320 16 5- 5-320 5- 5-320 320 325 5910641-335 2 1 5-325 330 5910641-356 5-3302 5-330 335 5910641-414 5-3354 5-335 340 5910698-11 5-3402 5-335 5-340 345 5910868-134 5-3452 5-3501 5-335 4 5-335 2 5-340 5-345 350 5910868-164 2 5-330 2 5-345 1 5-350 355 5910868-193 5-35513 5-355 355 360 5910868-222 5-36010 5-355 5-355 5-360 360 365 5909208-49 5-3652 5-37022 5-360 375 5910868-268 5-3751 5-355 5-355 5-355 5-360 5-360 5-360 5-355 13 5- 5-355 5-355 5-355 5-360 5-360 5- 10 5-360 2 5-365 5-370 370 5-355 5-360 5-365 370 5910868-260 5-355 5-370 5-370 370 5-370 370 5-370 5-370 5-370 5-370 5-370 5-370 5-370 5-370 5-370 5-370 5-370 5-370 5-370 5-370 5-370 22 5- 5- 5- 1 5-375 380 5910868-274 5-3801 1 5-380 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10056 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Fig. & Item Part Number 5 385 5910868-289 5-38544 .RESISTOR-10K OHM ±1% 1/10W R7 R8 R10 R18 R19 R21 R22 R24 R39 R42 R44 R45 R58 R60 R63 R65 R66 R76 R81 R82 R84 R88 R91 R95 R102 R108 R109 R113 R119 R123 R124 R132 R148 R149 R158 R159 R161 R162 R167 R183 R184 R188 R192 R193 .RESISTOR-14.3K OHM ±1% 1/8W R143 .RESISTOR-15K OHM ±1% 1/10W R23 R61 R62 R71 R139 R140 R141 .RESISTOR-24.9K OHM ±1% 1/4W R118 .RESISTOR-34.8K OHM ±1% 1/8W R121 R130 .RESISTOR-40.2K OHM ±1% 1/10W R6 R120 R134 R151 R173 .RESISTOR-49.9K OHM ±1% 1/10W R25 R26 R27 R31 R34 R77 R87 R90 R93 R94 R96 .RESISTOR-60.4K OHM ±1% 1/10W R16 .RESISTOR-68.1K OHM ±1% 1/8W R128 .RESISTOR-100K OHM ±1% 1/10W R13 R14 R75 R86 R99 R107 R142 R146 R186 R187 .RESISTOR-140K OHM ±1% 1/8W R152 .RESISTOR-499K OHM ±1% 1/10W (ESDS) R78 R114 R178 .RESISTOR-1M OHM ±1% 1/10W R153 .RESISTOR-100 OHM ±1% 1W R92 R112 .RESISTOR-1K OHM ±1% 1W R64 .RESISTOR-100K OHM ±1% 1W (ESDS) R126 R127 .RELAY-SOLID STATE (ESDS) K2 (ATTACHING PARTS) .SCREW-MACHINE-PAN HEAD .WASHER-FLAT .WASHER-LOCKING-SQUARE 5-385 390 5910868-304 5-3901 Eff Code 1234567 Nomenclature 5-385 5-385 5-385 5-385 5-385 5-385 385 5-385 5-385 5-385 5-385 5-385 5-385 385 5-385 5-385 5-385 5-385 5-385 5-385 385 5-385 5-385 5-385 5-385 5-385 Upa 44 5- 5- 5- 5- 385 5-385 5-385 5-385 5-385 5-385 5- 385 5-385 5-385 5-385 5-385 5-385 5- 385 5-385 5-385 5-385 5-385 1 5-390 395 5910868-306 5-3957 5-395 400 5910868-327 5-4001 5-395 5-395 5-395 5-395 5-395 7 5-395 1 5-400 405 5910868-341 5-4052 5-405 410 5910868-347 5-4105 5-410 415 5910868-356 5-41511 5-410 5-415 415 420 5910868-364 5-4201 5-410 5-415 5-415 2 5-405 5-415 5-415 5-410 5-415 5 5-410 5-415 5-415 5-415 11 5- 5-415 1 5-420 425 5910868-369 5-4251 1 5-425 430 5910868-385 5-43010 5-430 5-4351 5-430 5-430 430 435 5910868-399 5-430 5-430 5-430 5-430 5-430 10 5- 5-430 1 5-435 440 5910868-452 5-4403 5-440 445 5910868-481 5-4451 5-440 3 5-440 1 5-445 450 5911591-97 5-4502 5-450 455 5911591-193 5-4551 2 5-450 1 5-455 460 5911591-385 5-4602 5-460 465 5914427-1 5-4651 2 5-460 1 5-465 470 MS51957-30 475 NAS1149CN616R 480 5910060-2 5-4702 5-4754 5-4802 2 4 2 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10057 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Fig. & Item Part Number 5 485 NAS671C6 5-4852 490 5911839-1 5-4902 Airline Part Number .NUT-SELF-LOCKING –––***––– .RELAY-DPDT (ESDS) K1 K3 .SEMICONDUCTOR-JFET (ESDS) Q9 Q13 REPLD BY ITEM -495A .SEMICONDUCTOR-JFET (ESDS) Q9 Q13 REPLS ITEM 495 .DEVICE-SEMICONDUCTOR-MOSFET-NCHANNEL U1 (ATTACHING PARTS) .SCREW-MACHINE-PAN HEAD –––***––– .SEMICONDUCTOR-JFET-P-CHANNEL (ESDS) Q8 REPLD BY ITEM -510A .SEMICONDUCTOR-JFET-P-CHANNEL (ESDS) Q8 REPLS ITEM 510 .SEMICONDUCTOR-MOSFET (ESDS) Q5 .SEMICONDUCTOR-MOSFET (ESDS) Q12 .TRANSISTOR (ESDS) Q4 Q7 Q11 Q15 Q16 Q17 Q18 Q19 Q20 .TRANSISTOR-MOSFET (ESDS) Q2 Q10 Q14 .TRANSISTOR (ESDS) Q3 .TRANSISTOR (ESDS) Q1 Q6 .TRANSFORMER T1 (ATTACHING PARTS) .SCREW-MACHINE-PAN HEAD 5-490 495 5909882-1 5-4952 5-495A2 5-5001 2 2 2 5-495 5-495A 500 5909904-7 Upa 5-490 5-495 - 495A 5909882-2 Eff Code 1234567 Nomenclature 2 5-495A 1 5-500 505 MS51957-14 510 5910654-1 5-5052 5-5101 2 1 5-510 - 510A 5910654-2 5-510A1 1 5-510A 515 5910662-1 5-5151 1 5-515 520 5910662-5 5-5201 1 5-520 525 4951007 5-5259 5-525 525 530 5910751-2 5-5303 5-5351 5-525 5-525 5-525 5-525 5-525 5- 5-525 5-530 535 5911837-1 5-525 9 5-530 3 5-530 1 5-535 540 5911837-2 5-5402 5-540 545 5914419-1 5-5451 2 5-540 1 5-545 550 MS51957-30 5-5502 2 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10058 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Fig. & Item Part Number 5 555 NAS1149CN616R 560 5910060-2 5-5552 5-5602 565 5912795-4 5-5651 Airline Part Number Eff Code 1234567 Nomenclature .WASHER-FLAT .WASHER-LOCKING-SQUARE –––***––– .FUSE-2A F1 .PLATE-INSEPARABLE ASSEMBLY .RETAINER-PRINTED WIRING BOARD (ATTACHING PARTS) .SCREW-MACHINE-FLAT HEAD –––***––– .ASSEMBLY-PRINTED WIRING BOARD-A4 (NP) Upa 2 2 1 5-565 570 771541 575 5910275-5 5-5701 5-5751 580 NAS662C2R3 5-5804 585 1708554 5-5851 1 1 4 1 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10059 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10060 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 IPL Figure 6 130 (4X) 10 160 (P1) 30 40 20 150 (XA2P1) DETAIL B 120 110 60A (A5) 100 140 (XA4P1) 90 DETAIL A 80 70 HE-242334-102482-A IPL Figure 6 (Sheet 1 of 2) Printed Wiring Board Assembly A5 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10061 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Figure 0 50A (C8 - C28, C31 - C40) 60A (REF) 170 160 (REF) 170 200 180 180 200 190 190 200 210 DETAIL B DETAIL A HE-242334-102483-A IPL Figure 6 (Sheet 2 of 2) Printed Wiring Board Assembly A5 Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10062 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 Airline Part Number Fig. & Item Part Number 6 1 1707474 6-1RF 10 768318 6-101 20 MS51957-14 30 MS35338-135 40 NAS620C4L 6-203 6-303 6-403 - 50 1703290 50A 4950987 6-50 6-50A31 ASSEMBLY-PRINTED WIRING BOARD-A5 FOR NHA SEE IPL FIGURE 1 .ASSEMBLY-BRACKET-MOUNTING (ATTACHING PARTS) .SCREW-MACHINE-PAN HEAD .WASHER-LOCKING .WASHER-FLAT –––***––– DELETED (WIRING-PRINTED-RIGID FLEX) .CAPACITOR-0.01 µF ±10% 500V C8 C9 C10 C11 C12 C13 C14 C15 C16 C17 C18 C19 C20 C21 C22 C23 C24 C25 C26 C27 C28 C31 C32 C33 C34 C35 C36 C37 C38 C39 C40 DELETED (CAPACITOR) C8 C9 C10 C11 C12 C13 C14 C15 C16 C17 C18 C19 C20 C21 C22 C23 C24 C25 C26 C27 C28 C31 C32 C33 C34 C35 C36 C37 C38 C39 C40 .WIRING-PRINTED-RIGID FLEX-A5 (ATTACHING PARTS) .SCREW-MACHINE-PAN HEAD .WASHER-LOCKING .WASHER-FLAT .SCREW-MACHINE-PAN HEAD .WASHER-LOCKING .WASHER-FLAT .STANDOFF-ROUND –––***––– .CONNECTOR-PRINTED WIRING BOARD XA4P1 .CONNECTOR-PRINTED WIRING BOARD XA2P1 .CONNECTOR-ELECTRICAL RECEPTACLE P1 . .CONTACT-SOCKET . .CONTACT-PIN . .CONTACT-PIN . .CONTACT-PIN . .ADAPTER-PIN 6-50A - 60 4950987 6-60 6-50A 6-60A1 70 80 90 100 110 120 130 MS51957-120 MS35338-135 NAS620C4L MS51957-33 MS35338-136 NAS1149CN616R 5911840-4 6-707 6-807 6-907 6-1004 6-1104 6-1204 6-1304 140 5907471-15 6-1401 6-50A 6-50A 6-50A 6-50A 6-50A 50A 6-50A 6-50A 6-50A 6-50A 6-50A 6-50A 6- 6-50A 6-50A 6-50A 6-50A 6-50A 6-50A 6- 50A 6-50A 6-50A 6-50A 6-50A 6-50A 6-50A 6- 50A 6-50A 6-50A 6-60 6-60 6-60 6-60 6-60 6-60 Upa RF 1 3 3 3 31 6- 50A 6-60 60A 1703290 Eff Code 1234567 Nomenclature 6-60 60 6-60 6-60 6-60 6-60 6-60 6-60 6-60 6- 60 6-60 6-60 6-60 6-60 6-60 6-60 6-60 6- 60 6-60 6-60 6-60 6-60 6-60 6-60 6- 1 7 7 7 4 4 4 4 1 6-140 150 5907473-2 6-1501 1 6-150 160 5911438-1 6-1601 1 6-160 170 180 190 200 210 5909623-2 5909517-2 5909517-1 5911728-2 5912547-1 6-170147 6-1803 6-1903 6-2005 6-2102 147 3 3 5 2 - ITEM NOT ILLUSTRATED Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10063 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 THIS PAGE INTENTIONALLY LEFT BLANK Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. DETAILED PARTS LIST 24-23-34 Page 10064 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 STORAGE 1500015000 TASK 24-23-34-550-801-A 1. GENERAL INFORMATON FOR STORAGE CAUTION: UNPACKED STORAGE IS NOT RECOMMENDED. CAUTION: UNUSUAL ENVIRONMENTAL CONDITIONS CAN DECREASE THE STORAGE LIFE OF THE GCU. Subtask 24-23-34-99F-021-A00 A. General Information (1) This section has the procedures and illustrations necessary for storage of the GCU. The item numbers in the procedures and illustrations are the same as those in the IPL. NOTE: You can replace an item with its alpha-variant when permitted by the effect code for that item. For example, procedures that apply to item (10) also apply to the alpha-variant items (-10A, -10B, and -10C). Subtask 24-23-34-94A-003-A00 B. Materials for Storage (1) Refer to Table 15001 for the materials necessary for the storage procedures. NOTE: There is no limit to the time that you can keep a GCU when you follow the procedures listed below. When a GCU has been stored for more than 3 years, Hamilton Sundstrand recommends that the unit be examined for corrosion and that the GCU test be done to make sure that the unit is serviceable. Table 15001 Table 15001 Materials for Storage Material Number and Name Source Use Antistatic Foam Molds Commercially Available Storage of the GCU. Conductive Plastic Bag Commercially Available Storage of the GCU. Fiberboard Box, Weather Resistant, Burst Strength 400 psi (2,758 kPa), ASTM Specification D118 (or equivalent) Commercially Available Storage of the GCU. Protective Cap (Electrically Conductive) 025-1157-001 and 025-1158-001 ITT Corporation (CAGE Code 71468) Protect electrical connector during storage. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. STORAGE 24-23-34 Page 15001 Jun 6/14 HAMILTON SUNDSTRAND CORPORATION, A UTC AEROSPACE SYSTEMS COMPANY COMPONENT MAINTENANCE MANUAL 1709225 NOTE: Maintenance personnel must use the specified consumable material for the specified task. These consumable materials are known to agree with all of the design and qualification requirements. Only approved materials engineering personnel can make equivalent consumable material decisions. These materials are used at the risk of the organization who makes the decision. NOTE: You can get the full address and other information for vendors or suppliers listed in this table from the World Wide Web (www) at URL http://www.bpn.gov/bincs/begin_search.asp. Other CAGE Code sites are also available on the Web. TASK 24-23-34-550-802-A 2. PREPARATION FOR STORAGE A. Prepare the GCU for storage as follows: CAUTION: THE GCU CONTAINS ELECTROSTATIC DEVICES. DO NOT SUBJECT IT TO ELECTROSTATIC, ELECTROMAGNETIC, MAGNETIC, OR RADIOACTIVE FIELDS UNLESS PROTECTED BY A STATIC-SHIELDED CONTAINER. (1) Install the conductive dust caps on the rear electrical connector of the GCU. (2) Put the GCU in a conductive waterproof plastic bag. (3) Seal the open end of the plastic bag. WARNING: DO NOT GET FOAM MOLDS HOT OR BURN THEM. IT WILL CAUSE TOXIC GASES. (4) Make sure the bottom antistatic foam mold is in the fiberboard box. (5) Put the GCU in the bottom foam mold. (6) Put the top antistatic foam mold on top of the GCU. (7) Seal the fiberboard box. (8) Mark the GCU part number and any other data required by ATA Specification 300 on the container. CAUTION: DO NOT LET THE STORAGE TEMPERATURE DECREASE TO LESS THAN -55 °C (-67 °F) OR INCREASE TO MORE THAN +74 °C (+165 °F). KEEP HUMIDITY UNDER 95 PERCENT. (9) Keep the GCU in a clean, dry area, away from vibration and shock. Subject to the EAR - See the Title, First, or Cover Page for more information. UTC AEROSPACE SYSTEMS PROPRIETARY - Subject to the restriction on the title or cover page. STORAGE 24-23-34 Page 15002 Jun 6/14
