GOODRICH AEROSTRUCTURES
CAGE Code 51563
Goodrich Aerostructures
850 Lagoon Drive
Chula Vista, California 91910−2098
Phone: +1−800−735−7899
Email: 24−7@goodrich.com
TRANSMITTAL LETTER
HIGHLIGHTS
TO: COMPONENT MAINTENANCE MANUAL DISTRIBUTION
CONCERNING: Revision No. 33, Dated April 15, 2019
MANUAL UPDATE INSTRUCTIONS
This is a complete reissue of the manual. Discard the old manual upon receipt of this reissued manual.
Chapter/Section/Subject
Page
Description of Change
Title Page
TL−1
Added title and RDN
Description and Operation
1
Revised conversion
Repair 2
6007
Replaced obsolete primer with new primer
and its’ manufacturer (CV17–2912)
Repair 3
6007
Revised measurement values
Repair 4
6016 — 6018
Revised measurement conversion
Repair 6
6002, 6004
Revised measurement values
Repair 7
6005
6012
6031
Revised text (CV18–0167)
6008, 6011 — 6012,
6019
Revised measurement values
7004 — 7005
Revised measurement values
Introduction
10001
Added Note (CV18–2641 Rev A)
Numerical Index
10008
Revised text (CV18–0167)
Figure 1
10028
Added superseded part (CV17–2745)
10029
Revised nomenclature
10052
Updated illustration to add forward arrow
10054
Revised illustration
Assembly
Illustrated Parts List:
Figure 5
Page HL−1
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
CAGE Code 51563
Goodrich Aerostructures
850 Lagoon Drive
Chula Vista, California 91910−2098
Phone: +1−800−735−7899
Email: 24−7@goodrich.com
Chapter/Section/Subject
Page
Description of Change
10058
Revised nomenclature
Page HL−2
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
CAGE Code 51563
Goodrich Aerostructures
850 Lagoon Drive
Chula Vista, California 91910−2098
Phone: +1−800−735−7899
Email: 24−7@goodrich.com
COMPONENT MAINTENANCE MANUAL
WITH ILLUSTRATED PARTS LIST
INLET COWL
ASSEMBLY
PART NUMBERS
277−1100−505
277−1100−507
RDN 117
TRANSMITTAL OF TECHNICAL DATA (EAR)
THESE COMMODITIES, TECHNOLOGY, OR SOFTWARE ARE CONTROLLED BY THE U.S. EXPORT
ADMINISTRATION REGULATIONS (EAR). DIVERSION CONTRARY TO U.S. LAW IS PROHIBITED
ECCN: 9E991
Page TL−1
71−11−09
Original Issue Oct 01/1993
Rev 33 Apr 15/2019
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
GOODRICH AEROSTRUCTURES
CAGE Code 51563
Goodrich Aerostructures
850 Lagoon Drive
Chula Vista, California 91910−2098
Phone: +1−800−735−7899
Email: 24−7@goodrich.com
Goodrich Aerostructures Group Proprietary Information
The information contained in this document is Goodrich proprietary information and is
disclosed in confidence. It is the property of Goodrich and shall not be used, disclosed
to others or reproduced without the express written consent of Goodrich, including, but
without limitation, it is not to be used in the creation, manufacture, development, or
derivation of any repairs, modifications, spare parts, design, or configuration changes or
to obtain FAA or any other government or regulatory approval to do so. If consent is
given for reproduction in whole or in part, this notice and the notice set forth on each
page of this document shall appear in any such reproduction in whole or in part. The
information contained in this document may also be controlled by the U.S. export control
laws. Unauthorized export or re−export is prohibited.
Copyright License:
Customer is authorized to copy these materials for its own use only, provided that all
copyright notices, proprietary legends, confidential markings, and other restrictive
notices appearing on the original materials are preserved on all such copies.
Caution Regarding Use of Materials:
It is customer’s sole responsibility to ascertain and ensure that all materials are current
and appropriate for the use to which they are put and Goodrich assumes no
responsibility whatsoever in that regard. Customer agrees to indemnify and save
harmless Goodrich against all claims and liability of whatever nature, including those of
third parties (including contractors and vendors to customer) where and by whomsoever
brought, resulting from customer’s use of materials or other information, consultation,
assistance, or training furnished or any other performance in connection with this
agreement by Goodrich or from the manufacture, sale, delivery, resale of any product by
customer. In no event shall Goodrich be liable for any special, incidental, indirect or
consequential or punitive damages.
Page TL−2
71−11−09
Original Issue Oct 01/1993
Rev 33 Apr 15/2019
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
RECORD OF REVISIONS
REV.
NO.
ISSUE DATE
Initial
DATE
INSERTED
REV.
NO.
ISSUE DATE
Oct 01/93
25
Oct 01/10
1
Jan 01/94
26
Apr 01/11
2
Apr 15/94
27
Oct 01/11
3
Apr 01/99
28
Apr 01/12
4
Oct 01/99
29
Oct 01/13
5
Apr 01/00
30
Oct 01/14
6
Oct 01/00
31
Dec 01/15
7
Apr 01/01
32
Oct 01/16
8
Oct 01/01
33
Apr 15/19
9
Oct 01/02
10
Apr 01/03
11
Oct 01/03
12
Apr 01/04
13
Oct 01/04
14
Apr 01/05
15
Oct 01/05
16
Apr 01/06
17
Oct 01/06
18
Apr 01/07
19
Oct 01/07
20
Apr 01/08
21
Oct 01/08
22
Apr 01/09
23
Oct 01/09
24
Apr 01/10
BY
DATE
INSERTED
BY
RETAIN THIS RECORD IN THE FRONT OF MANUAL OR CHAPTER. ON RECEIPT OF REVISIONS,
INSERT REVISED PAGES IN THE MANUAL AND ENTER REVISION NUMBER, DATE INSERTED,
AND INITIALS.
Page ROR−1
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
Page ROR−2
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
RECORD OF TEMPORARY REVISIONS
TEMPORARY
REV. NO.
ISSUE DATE
DATE
INSERTED/
INSERTED BY
DATE
REMOVED/
REMOVED BY
DATE
INCORP.
Page RTR−1
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
Page RTR−2
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
SERVICE BULLETIN LIST
SERVICE BULLETIN /
REVISION NUMBER
DATE
INCORPORATED
ISSUE DATE OR NO EFFECT
23−001
Apr 01/00
23−002
Apr 01/99
30−001
Apr 01/00
30−005
Apr 01/01
71−015
Apr 01/99
71−021
Apr 01/00
71–041
Oct 01/14
71–042
Oct 01/14
71–043
Oct 01/14
TITLE
Page SBL−1
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
Page SBL−2
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
LIST OF EFFECTIVE PAGES
SECTION
PAGE
DATE
TRANSMITTAL LETTER HL−1
HL−2
Apr 15/2019
Apr 15/2019
Title Page
Legal Notice
TL−1
TL−2
Apr 15/2019
Apr 15/2019
Record of Revisions
ROR−1
ROR−2
Apr 15/2019
BLANK
RECORD OF
TEMPORARY
REVISIONS
RTR−1
RTR−2
Apr 15/2019
BLANK
SERVICE BULLETIN
LIST
SBL−1
SBL−2
Apr 15/2019
BLANK
EFFECTIVE PAGES
LEP−1
LEP−2
LEP−3
LEP−4
Apr 15/2019
Apr 15/2019
Apr 15/2019
Apr 15/2019
CONTENTS
TOC−1
TOC−2
Apr 15/2019
BLANK
Introduction
INTRO−1
INTRO−2
INTRO−3
INTRO−4
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Description and
Operation
1
2
Apr 15/2019
Oct 01/2016
Disassembly
3001
3002
3003
3004
Oct 01/2016
Oct 01/2016
Oct 01/2016
BLANK
Cleaning
4001
4002
4003
4004
Oct 01/2016
Oct 01/2016
Oct 01/2016
BLANK
5001
Oct 01/2016
SECTION
PAGE
DATE
5002
Oct 01/2016
6001
6002
Oct 01/2016
BLANK
Repair No. 1 Stencil And 6001
Marking Replacement
6002
6003
6004
6005
6006
6007
6008
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
BLANK
Repair No. 2 Leading
Edge Protector Repair
6001
6002
6003
6004
6005
6006
6007
6008
6009
6010
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Apr 15/2019
Apr 15/2019
Oct 01/2016
Oct 01/2016
Repair No. 3 Repair Of
Inlet Cowl Outer Barrel
Frame Structure
6001
6002
6003
6004
6005
6006
6007
6008
6009
6010
6011
6012
6013
6014
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Apr 15/2019
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
BLANK
Repair No. 4 Non−
Autoclave Outer Barrel
Frame Structure
6001
6002
6003
Oct 01/2016
Oct 01/2016
Oct 01/2016
Repair General
Check
Page LEP−1
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
LIST OF EFFECTIVE PAGES
SECTION
PAGE
DATE
6004
6005
6006
6007
6008
6009
6010
6011
6012
6013
6014
6015
6016
6017
6018
6019
6020
6021
6022
6023
6024
6025
6026
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Apr 15/2019
Apr 15/2019
Apr 15/2019
Apr 15/2019
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
BLANK
Repair No. 5 Insulation 6001
Blanket Inner Barrel
6002
Acoustic Panel Backskin 6003
Replacement
6004
6005
6006
6007
6008
6009
6010
6011
6012
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
BLANK
Repair No. 6 Replace
6001
Single Lip Skin Segment 6002
6003
6004
6005
6006
Oct 01/2016
Apr 15/2019
Oct 01/2016
Apr 15/2019
Oct 01/2016
Oct 01/2016
SECTION
PAGE
DATE
6007
6008
Oct 01/2016
Oct 01/2016
Repair No. 7 −
6001
REPLACE INLET COWL 6002
INNER BARREL
6003
6004
6005
6006
6007
6008
6009
6010
6011
6012
6013
6014
6015
6016
6017
6018
6019
6020
6021
6022
6023
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6025
6026
6027
6028
6029
6030
6031
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6033
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6036
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6038
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6040
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Apr 15/2019
Apr 15/2019
Oct 01/2016
Apr 15/2019
Oct 01/2016
Oct 01/2016
Apr 15/2019
Apr 15/2019
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Apr 15/2019
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Apr 15/2019
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Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Page LEP−2
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
LIST OF EFFECTIVE PAGES
SECTION
PAGE
DATE
6041
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6043
6044
6045
6046
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
BLANK
7001
7002
7003
7004
7005
7006
7007
7008
Oct 01/2016
Oct 01/2016
Oct 01/2016
Apr 15/2019
Apr 15/2019
Oct 01/2016
Apr 15/2019
BLANK
Fits and Clearances
8001
8002
Oct 01/2016
Oct 01/2016
Special Tools, Fixtures
and Equipment
9001
9002
9003
9004
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Introduction
10001
10002
10003
10004
10005
10006
10007
10008
10009
10010
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BLANK
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Apr 15/2019
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Oct 01/2016
Assembly (Includes
Storage)
SECTION
Figure 2
Figure 3
Numeric Index
Figure 1
Figure 4
Figure 5
Figure 6
PAGE
DATE
10020
10021
10022
10023
10024
10025
10026
10027
10028
10029
10030
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10047
10048
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10050
10051
10052
10053
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10055
10056
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10062
Oct 01/2016
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Oct 01/2016
Apr 15/2019
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Oct 01/2016
Apr 15/2019
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Oct 01/2016
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Oct 01/2016
BLANK
Page LEP−3
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
LIST OF EFFECTIVE PAGES
SECTION
PAGE
DATE
10063
10064
10065
Apr 15/2019
Apr 15/2019
BLANK
SECTION
PAGE
DATE
Page LEP−4
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
TABLE OF CONTENTS
SUBJECT TITLE
PAGE
INTRODUCTION
DESCRIPTION AND OPERATION
TESTING AND FAULT ISOLATION
SCHEMATICS AND WIRING DIAGRAMS
DISASSEMBLY
CLEANING
CHECK
REPAIR GENERAL
REPAIR NO. 1 STENCIL AND MARKING REPLACEMENT
REPAIR NO. 2 LEADING EDGE PROTECTOR REPAIR
REPAIR NO. 3 REPAIR OF INLET COWL OUTER BARREL FRAME STRUCTURE
REPAIR NO. 4 NON−AUTOCLAVE OUTER BARREL FRAME STRUCTURE
REPAIR NO. 5 INSULATION BLANKET INNER BARREL ACOUSTIC PANEL BACKSKIN
REPLACEMENT
REPAIR NO. 6 REPLACE SINGLE LIP SKIN SEGMENT
REPAIR NO. 7 – REPLACE INLET COWL INNER BARREL
ASSEMBLY
FITS AND CLEARANCES
SPECIAL TOOLS, FIXTURES, AND EQUIPMENT
ILLUSTRATED PARTS LIST
SPECIAL PROCEDURES
REMOVAL
INSTALLATION
SERVICING
STORAGE
REWORK
INTRO−1
1
N/A
N/A
3001
4001
5001
6001
6001
6001
6001
6001
6001
6001
6001
7001
8001
9001
10001
N/A
N/A
N/A
N/A
N/A
N/A
Page TOC−1
71−11−09
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
Page TOC−2
71−11−09
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*/530%6$5*0/
TASK 71−11−09−800−801
1.
Introduction
A.
This manual gives maintenance instructions and Illustrated Parts List for the Inlet Cowl
Assembly, Part Number 277−1100. Dash number applications are found by going to Figure 1
of the Illustrated Parts List.
B.
Cautions, Warnings and Dangers
NOTICE!!
Carefully read and obey all CAUTION and WARNING statements in this manual. Refer
to the descriptions of these statements that follow:
− A "CAUTION" statement is given to prevent damage to equipment.
− A "WARNING" statement is given to prevent personal injury or illness
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL SAFETY
INSTRUCTIONS FOR THE CHEMICALS. THESE INCLUDE MANUFACTURER’S
INSTRUCTIONS, THE MATERIAL SAFETY DATA SHEET (MSDS), AND
GOVERNMENT REGULATIONS. CHEMICALS MAY CAUSE INJURY TO YOU OR
MAKE YOU SICK WHEN SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS
GIVES INSTRUCTIONS ON HOW TO SAFELY USE, KEEP, AND DISCARD
CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER ON HOW TO SAFELY
USE, KEEP, AND DISCARD CHEMICALS.
CADMIUM − Obey the warnings below before you touch or do maintenance on parts that are cadmium
plated. The Occupational, Safety, and Health Administration (OSHA) sets mandatory limits on exposure
to cadmium dust (29 CFR 1910.1027).
WARNING:
DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT IS SWALLOWED CAN
CAUSE KIDNEY OR REPRODUCTIVE SYSTEM DISEASE. AFTER YOU TOUCH
CADMIUM PLATED PARTS, WASH YOUR HANDS BEFORE YOU EAT OR SMOKE.
GET SAFETY INSTRUCTIONS FROM YOUR EMPLOYER. OBEY GOVERNMENT
AND OSHA REGULATIONS WHEN YOU DISCARD PARTS THAT CONTAIN
CADMIUM.
WARNING:
DO NOT INHALE CADMIUM PARTICLES, FUMES, OR DUST. THESE PARTICLES,
FUMES, OR DUST CAN CAUSE LUNG OR KIDNEY DISEASE. IF MAINTENANCE
PROCEDURES CREATE CADMIUM PARTICLES, FUMES, OR DUST, TELL YOUR
EMPLOYER TO SUPPLY RESPIRATORS, VENTILATION, AND/OR PROCEDURES
TO PREVENT EXPOSURE TO PERSONNEL.
The Occupational, Safety, and Health Administration (OSHA) has an applicable DANGER warning (29
CFR 1910.1027 (m)(3)(ii)) as follows:
DANGER:
CONTAINS CADMIUM. CANCER HAZARD. AVOID CREATING DUST. CAN CAUSE
LUNG AND KIDNEY DISEASE.
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*/530%6$5*0/
ASBESTOS − Obey the warning below before you touch or do maintenance on parts that contain
asbestos. Some old assembly components may contain asbestos. The Occupational, Safety, and
Health Administration (OSHA) sets mandatory limits on exposure to asbestos dust (29 CFR 1910.1001).
WARNING:
DO NOT BREATHE ASBESTOS DUST. THIS DUST CONTAINS ASBESTOS FIBERS
THAT CAN CAUSE CANCER AND LUNG DISEASE. DO NOT USE COMPRESSED
AIR TO CLEAN PARTS OR ASSEMBLIES THAT POSSIBLY CONTAIN ASBESTOS
DUST. IF MAINTENANCE PROCEDURES EXPOSE PERSONNEL TO ASBESTOS
DUST, TELL YOUR EMPLOYER TO SUPPLY RESPIRATORS, VENTILATION,
AND/OR PROCEDURES TO PREVENT EXPOSURE TO PERSONNEL. OBEY
GOVERNMENT AND OSHA REGULATIONS WHEN YOU DISCARD PARTS THAT
CONTAIN ASBESTOS.
The Occupational, Safety, and Health Administration (OSHA) has an applicable DANGER warning (29
CFR 1910.1001 (j)(4)(ii)) as follows:
DANGER:
CONTAINS ASBESTOS FIBERS. AVOID CREATING DUST. CANCER AND LUNG
DISEASE HAZARD.
BERYLLIUM or BERYLLIUM COPPER ALLOYS − Obey the warning below before you touch or do
maintenance on parts that contain beryllium. Bronze bearings and bushings may contain beryllium or
beryllium copper alloys. The Occupational, Safety, and Health Administration (OSHA) sets mandatory
limits on exposure to dust or fumes from beryllium or beryllium copper alloys (29 CFR 1910.1000).
WARNING:
DO NOT BREATHE BERYLLIUM PARTICLES OR DUST. THESE PARTICLES OR
DUST CAN CAUSE CANCER OR LUNG DISEASE. IF MAINTENANCE
PROCEDURES MAKE BERYLLIUM PARTICLES OR DUST, TELL YOUR EMPLOYER
TO SUPPLY RESPIRATORS, VENTILATION, AND/OR PROCEDURES TO PREVENT
EXPOSURE TO PERSONNEL. OBEY GOVERNMENT AND OSHA REGULATIONS
WHEN YOU DISCARD PARTS THAT CONTAIN BERYLLIUM. READ AND OBEY THE
NEWEST APPLICABLE MATERIAL SAFETY DATA SHEET (MSDS) THAT IS
AVAILABLE FROM BRUSH WELLMAN INC. (REFER TO THE ADDRESS BELOW).
The newest MSDS for beryllium is available from:
Brush Wellman Inc. Product Stewardship
Department 14710 W. Portage River S. Road
Elmore, Ohio 43416−9502 USA
Tel.: (800) 862−4118 Fax: (419)
862−4414 www.brushwellman.com
CERAMIC FIBERS − Obey the warning below before you do maintenance on parts that contain ceramic
fibers. Heat resistant cloth and foil covered heat shields and thermal blankets may contain ceramic
fibers. The Occupational, Safety, and Health Administration (OSHA) and the Refractory Ceramic Fibers
Coalition (RCFC) have a voluntary personnel protection program (PSP 2002, Feb. 11, 2002). This
program gives limits on personnel exposure to ceramic fibers.
Page INTRO−2
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*/530%6$5*0/
WARNING:
DO NOT BREATHE CERAMIC FIBER DUST. THIS DUST CONTAINS CERAMIC
FIBERS THAT MAY CAUSE CANCER. DO NOT USE COMPRESSED AIR TO CLEAN
PARTS OR ASSEMBLIES THAT POSSIBLY CONTAIN CERAMIC FIBERS. IF
MAINTENANCE PROCEDURES EXPOSE PERSONNEL TO CERAMIC FIBERS,
TELL YOUR EMPLOYER TO SUPPLY RESPIRATORS, VENTILATION, AND/OR
PROCEDURES TO PREVENT EXPOSURE TO PERSONNEL. OBEY GOVERNMENT
AND OSHA REGULATIONS WHEN YOU DISCARD PARTS THAT CONTAIN
CERAMIC FIBERS. READ AND OBEY THE NEWEST APPLICABLE MATERIAL
SAFETY DATA SHEET (MSDS).
CHROMATES (HEXAVALENT CHROMIUM) − Obey the warnings below before you touch or do
maintenance on parts that contain hexavalent chromium. Stainless steel parts often contain hexavalent
chromium. The Occupational Safety and Health Administration (OSHA) sets mandatory limits on
exposure to chromium dust (29 CFR 1910.1000).
WARNING:
DO NOT GET HEXAVALENT CHROMIUM ON YOUR SKIN. REPEATED SKIN
CONTACT CAN CAUSE DERMATITIS AND SKIN ULCERS. DIRECT EYE CONTACT
WITH HEXAVALENT CHROMATE DUSTS CAN CAUSE EYE DAMAGE. AFTER YOU
TOUCH HEXAVALENT CHROMIUM PARTS. CLEAN YOUR HANDS BEFORE YOU
EAT OR SMOKE. GET SAFETY INSTRUCTIONS FROM YOUR EMPLOYER. OBEY
GOVERNMENT AND OSHA REGULATIONS WHEN YOU DISCARD PARTS THAT
CONTAIN HEXAVALENT CHROMIUM.
WARNING:
DO NOT BREATHE HEXAVALENT CHROMIUM PARTICLES, FUMES OR DUST.
THESE PARTICLES, FUMES OR DUST CAN CAUSE CANCER OR LUNG DISEASE.
IF MAINTENANCE PROCEDURES MAKE HEXAVALENT CHROMIUM PARTICLES,
FUMES OR DUST, TELL YOUR EMPLOYER TO SUPPLY RESPIRATORS,
VENTILATION AND/OR PROCEDURES TO PREVENT EXPOSURE TO
PERSONNEL.
CRYSTALLINE SILICA (Quartz) − Obey the warning below before you touch or do maintenance on
parts that contain crystalline silica. Primers, sealants, static conditioners, and fillers may contain
crystalline silica. The Occupational, Safety, and Health Administration (OSHA) sets limits on exposure to
crystalline silica dust (29 CFR 1910.1000 Table Z−3).
WARNING:
DO NOT BREATHE CRYSTALLINE SILICA PARTICLES OR DUST. THESE
PARTICLES OR DUST CAN CAUSE SILICOSIS AND OTHER LUNG DISEASE. IF
MAINTENANCE PROCEDURES MAKE CRYSTALLINE SILICA PARTICLES OR
DUST, TELL YOUR EMPLOYER TO SUPPLY RESPIRATORS, VENTILATION
AND/OR PROCEDURES TO PREVENT EXPOSURE TO PERSONNEL.
LEAD − Obey the warnings below before you touch or do maintenance on parts that contain lead.
Soldered components and high temperature dry lubricants may contain lead. The Occupational, Safety,
and Health Administration (OSHA) sets limits on exposure to lead (29 CFR 1910.1025).
Page INTRO−3
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*/530%6$5*0/
WARNING:
DO NOT GET LEAD IN YOUR MOUTH. LEAD THAT IS SWALLOWED CAN CAUSE
REPRODUCTIVE OR BLOOD SYSTEM DISEASE. AFTER YOU TOUCH LEAD
PARTS, CLEAN YOUR HANDS BEFORE YOU EAT OR SMOKE. GET SAFETY
INSTRUCTIONS FROM YOUR EMPLOYER. OBEY GOVERNMENT AND OSHA
REGULATIONS WHEY YOU DISCARD PARTS THAT CONTAIN LEAD.
WARNING:
DO NOT BREATHE LEAD PARTICLES, FUMES OR DUST. THESE PARTICLES,
FUMES OR DUST CAN CAUSE REPRODUCTIVE OR BLOOD SYSTEM DISEASE. IF
MAINTENANCE PROCEDURES MAKE LEAD PARTICLES, FUMES OR DUST, TELL
YOUR EMPLOYER TO SUPPLY RESPIRATORS, VENTILATION AND/OR
PROCEDURES TO PREVENT EXPOSURE TO PERSONNEL.
Page INTRO−4
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
%&4$3*15*0/"/%01&3"5*0/
TASK 71−11−09−870−801
1.
Description and Operation (See Figure 1)
A.
The inlet cowl assembly directs the air inlet flow to the engine fan section. This assembly has
two−section composite graphite outer barrel around an inner barrel. The inner barrel has three
aluminum alloy, bonded−honeycomb, acoustic−panel assemblies. A titanium bulkhead aft of
the inlet cowl serves as a fireshield between the inlet cowl and the engine fan case. The inlet
cowl lip, attached to both outer and inner barrels, separates the airstream to provide a smooth
airflow to the fan and over the nacelle external surface.
B.
Three access panels located on the aft bulkhead of the inlet assembly, two access panels on
the upper outer barrel, and one access door on the inner barrel give access to internal
components. These components are the anti−ice ducting for the lip assembly, an electrical
harness and electrical connector, and an interphone jack.
C.
Externally, two hoist points are located on the top of the cowl for attachment of a hand sling
and a grounding receptacle located in the anti−ice air exit duct.
D.
Bleed air from the engine is routed through the anti−ice shutoff and regulating valve, the
ducting and the three outlet nozzle to the inlet cowl leading edge. The airflow is in a clockwise
direction. the anti−ice air flows out of the Inlet Cowl through the exhaust duct at the bottom of
the Inlet Cowl.
E.
Pertinent Data. (See Table 1)
Diameter:
122.8 in. (3119 mm)
Length:
64 in. (1626 mm)
Weight:
552 lb (250 kg)
Pertinent Data
Table 1
Page 1
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
%&4$3*15*0/"/%01&3"5*0/
ANTI−ICE
ACCESS DOOR
ATTACH
RING
ATTACH
BOLT HOLE
INDEX PIN
PRESSURE
RELIEF DOOR
INDEX PIN
CEC−006−00
INTERPHONE AND
GROUND JACKS
FIGURE 1 INLET COWL ASSEMBLY
Page 2
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
%*4"44&.#-:
TASK 71−11−09−040−801
1.
Disassembly
General
Disassemble the inlet cowl only to the extent necessary to do required maintenance. Refer to
the Check section to determine the condition of components or most probable cause of
malfunction.
A.
Disassembly Tools (See Table 301)
DESCRIPTION
DESIGNATION
MANUFACTURE
Wrench, spanner
RSE 1243
V51563
Rohr Inc.
DBA Goodrich Aerostructures 850
Lagoon Dr Chula Vista, CA 91910
(619) 691−2006
www.parts.asg.goodrich.com
Screwdriver
Commercially Available
Disassembly Tools
Table 301
B.
Disassembly Procedures
CAUTION:
(1)
(2)
(3)
PROTECT THE HARNESS ASSEMBLY CONNECTORS FROM DAMAGE
DURING REMOVAL.
Electrical Installation (See IPL Figure 2)
(a)
Remove bolts (90) and clamps (100).
(b)
Remove bolt (120), nuts (70, 170 and 180), washers (60, 130, 140 and 150),
connector (80) and ground jack wire assembly (10).
(c)
Remove screws (30), plate (50) and retainer (40).
Upper Outer Barrel Access Panels (See IPL Figure 3)
(a)
Remove screws (30) and access panel (40).
(b)
Remove screws (30) and access panel (50).
Anti−ice Supply Tube Assembly (See IPL Figure 1)
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
%*4"44&.#-:
(a)
(b)
(c)
(4)
(6)
1)
Remove the bolts (230), washers (240) and retainer (330).
2)
Remove the screws (180), nut (340), seal (350), back up seal (360), two face
seals (370), face seal (380) and tube assembly (390).
Post SB 30−001 Pre SB 30−005
1)
Remove the bolts (230), washers (240) and retainer (330).
2)
Remove the screws (180), nut (340), packing seal (355), face seal (385) and
tube assembly (390).
Post SB 30−005
1)
Remove the bolts (230), washers (240) and retainer (330).
2)
Remove the screws (180), nut (340), packing seal assembly (387) and tube
assembly (390).
Exhaust Duct Assembly (See IPL Figure 1)
(a)
(5)
Pre SB 30−001
Remove bolts (200 and 210), washers (250) and duct assembly (400).
Pressure Relief Door Assembly (See IPL Figure 3)
(a)
Remove bolt (70), nut (100), washers (80), pin (280), sleeves (−275), springs (−
285) and door assembly (150).
(b)
Remove pins (60), collars (90), strip (110) and bracket (120).
(c)
Remove bolts (75), shims (130 and 140) and hinge half (370).
(d)
Door Assembly (150)
1)
Remove pins (210), nuts (240), washers (220) and latch (250).
2)
Remove bolt (160), nut (180), washer (170) and lanyard (190).
3)
Remove pins (200), collars (230) and bracket (260).
4)
Remove pins (300), collars (330), spacer (310) and hinge half (390) from
splice (400).
Lower Outer Barrel (See IPL Figure 4)
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COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
%*4"44&.#-:
(7)
(a)
Remove nuts (120), screws (130) and clips (110).
(b)
Remove Screws (290, 300) and plate (280).
Inner Barrel Assembly (See IPL Figure 5)
(a)
(8)
Remove screws (10), nuts (20) and pin (30).
Lip Assembly (See IPL Figure 6)
(a)
Remove bolts (40), washers (50) and nozzle assembly (60).
Page 3003
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
$-&"/*/(
TASK 71−11−09−100−801
1.
Cleaning
A.
Cleaning Materials.
NOTE:
YOU CAN USE ALTERNATIVE MATERIALS WITH THE SAME
PROPERTIES TO REPLACE THE ITEMS SHOWN IN TABLE 401.
DESCRIPTION
DESIGNATION
MANUFACTURER
Blanket, Heat
0°−250°F (−17,8°−121,1°C)
10W/Sq. In. (10W/645 Sq.
mm)
V61426
Atacs Products, Inc.
850 South Cambridge Street
Seattle, WA 98108−4748
Phone: (206) 433−9000
www.atacs.com
Cheesecloth
Commercially Available
Cloth, Breather
RC3000−10
V0F451
Richmond Aircraft Products, Inc.
13503 Pulmice St
Norwalk, CA 90650−5250
Phone: (562) 404−2440
www.richmondaircraft.com
Cloth, Lint−Free
Cotton
Commercially Available
Fabric, Fiberglass
Type 181
Commercially Available
Film, Parting
Nonporous
V0F451
Richmond Aircraft Products, Inc.
Solvent
Isopropyl Alcohol 99 percent
pure or
Commercially Available
MIBK/MEK Blend (60% Methyl V5E821
Isobutyl Ketone/40% Methyl
Univar U.S.A., Inc.
Ethyl Ketone or
532 E. Emaus Street
Middletown, PA 17057−2200
Phone: (717) 944−7471
www.univarusa.com
Turco 6646
V71410
Henkel Corporation
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
$-&"/*/(
DESCRIPTION
DESIGNATION
MANUFACTURER
Cleaning Materials
Table 401
B.
Cleaning Procedures.
WARNING:
(1)
Remove the unwanted material with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 401)
NOTE:
C.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
PARTS MUST BE FREE OF CORROSION, DIRT, GREASE, OIL, AND
OTHER UNWANTED MATERIALS.
Cleaning Procedures − Hydraulic Decontamination.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(1)
Open up the contaminated area.
(2)
Saturate cheesecloth with the solvent and apply to the contaminated surface.
(3)
Cover the saturated cheesecloth and contaminated surface with a plastic sheet to
reduce evaporation. Keep covered for approximately four hours.
(4)
Remove the cheesecloth. Remove the solvent with a clean lint−free cloth before the
solvent becomes dry.
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
$-&"/*/(
WARNING:
(5)
(6)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Do a test for the presence of Skydrol as follows:
(a)
Apply one layer of fiberglass cloth and one layer of breather cloth on the cleaned
area.
(b)
Cover breather cloth with nonporous parting film, heat blanket, three layers of
fiberglass cloth, a layer of breather cloth and a vacuum bag. Pull 20−in. HG (0,69
Kg/sq.cm) vacuum.
(c)
Increase temperature to 150°−160°F (66°−71°C). Maintain temperature for 60
minutes.
(d)
Remove vacuum bag, breather cloth, fiberglass cloth, heat blanket, nonporous
parting film, breather cloth and fiberglass cloth.
(e)
Inspect for evidence of Skydrol on breather cloth. If Skydrol remains, repeat Steps
1.C.(2) to 1.C.(5).
Bake dry at 150°−160°F (66°−71°C) for 60 minutes.
Page 4003
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COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
$)&$,
TASK 71−11−09−200−801
1.
Check
General.
Do a check of parts in accordance with the general instructions and data specified in this
section.
A.
Nondestructive Check Data. (See Table 501.)
IPL
FIG./ITEM
NOMEN−
CLATURE
METHOD
INSTRUCTIONS
REQUIREMENTS AND
DISPOSITION
All
Screws and
bolts
Visual
Do a check for corrosion,
wear, or stripped or
crossed threads.
Replace if defective.
Remove corrosion.
*Flourescent
Penetrant
Do a check for cracks at
thread roots.
No cracks allowed.
Replace if defective.
Visual
Do a check for burrs,
corrosion, wear, stripped
or crossed threads.
Replace if defective.
*Flourescent
Penetrant
Do a check for cracks.
No cracks allowed.
Replace if defective.
All
Nuts
2−10
Wire assembly
Visual
Do a check for
discoloration due to
excessive heat, and for
broken, loose or frayed
wires.
Replace and/or repair as
required.
2−80
Connectors
Visual
Do a check for damage to
shell or threads, and
loose, bent or missing
connector pins.
Replace and/or tighten
defective or loose parts.
1−390
Anti−ice tube
assembly
Visual
Do a check for dents,
holes and cracks.
Do a check of seals for
leakage.
Replace defective tubes.
Tighten packing nut or
replace seals if leak
persists.
Do a check for scratches,
cracks or cuts.
No cracks allowed.
Replace defective parts.
Borescope
1−350,
360,
370
380
Seals
Visual
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
$)&$,
IPL
FIG./ITEM
NOMEN−
CLATURE
METHOD
INSTRUCTIONS
REQUIREMENTS AND
DISPOSITION
All
Pins
Visual
Do a check for cracks,
corrosion or wear.
No cracks, wear or
distortion allowed.
Replace defective parts.
1−400
Exhaust duct
assembly
Visual
Do a check for dents,
holes and cracks. Check
seals and gaskets for
leakage.
Replace and/or repair
defective parts.
1−480,
490,
500
Aft bulkhead
panel assy,
access
Visual
Do a check for cracks and
punctures, loose or
missing fasteners.
No cracks and/or
punctures allowed.
Replace all loose or
missing fasteners.
Bulkhead assy
forward
Visual,
borescope
Do a check for cracks and
loose or missing
fasteners.
No cracks allowed.
Replace all loose and/or
missing fasteners.
Brackets
Visual
Do a check for cracks,
wear and distortion. Do a
check for loose or missing
fasteners.
Replace defective parts.
Tighten and/or replace
loose or missing
fasteners.
*Fluorescent
Penetrant
Do a check for cracks.
No cracks allowed.
Replace defective parts.
All
* See GE Standard Practices Manual, GEK 9250
Nondestructive Check Data
Table 501
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3(&/&3"TASK 71−11−09−300−801
1.
Repair General
TASK 71−11−09−300−801
2.
Removed
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Document Part No. 277−1100
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/045&/$*-"/%."3,*/(3&1-"$&.&/5
TASK 71−11−09−300−802
1.
Repair No. 1
TASK 71−11−09−300−802
2.
General
A.
For all inlet cowl access doors, the actual markings are to be centered on the external
surfaces of the doors. All other markings are placed immediately adjacent to the items on the
inlet cowl for which stenciling is required.
B.
All letters and numerical figures are to be black in order to contrast with the surrounding
surface of the inlet cowl. Lines and letters are to be centered under the top line of each
marking. Letters are to be No. 3 Alternate Gothic style. Space height between lines is to be
the same as the letter height.
TASK 71−11−09−300−802
3.
Repair Instructions
A.
Remove the old stencil. (See Figure 601.)
CAUTION:
(1)
Lightly sand off the old stencil message using abrasive aluminum oxide paper (See
Table 602).
NOTE:
(2)
B.
SEE REPAIR NO. 2 SURFACE FINISH REPAIR−COMPOSITE AS
NECESSARY.
Polish area with rubbing compound.
WARNING:
(3)
DO NOT DAMAGE THE BASE FINISH.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Remove the unwanted material with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 602)
Prepare and apply new stencil.
(1)
Cut the stencil. (See Table 601)
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/045&/$*-"/%."3,*/(3&1-"$&.&/5
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(2)
Locate the stencil on the cowl and spray paint through stencil (See Figure 601).
(3)
Allow paint to dry.
NOTE:
DRYING TIME:
DUST FREE...........30 MINUTES MAX
TACK FREE............3 HOURS MAX
DRY THROUGH..........6 HOURS MAX
TASK 71−11−09−300−802
4.
Marking
A.
Marking Locations.
NOTE:
ITEM NUMBERS REFER TO FIGURE 601.
ITEM NO.
LETTER HEIGHT
MARKING
1
1/4
INSPECTION ACCESS
2
1/4
UPPER CENTER
3
1/4
LOWER LEFT
4
1/2
HOIST POINT
5
1/4
ANTI−ICE DUCT ACCESS
6
1/4
UPPER LEFT
7
1/2
NO STEP
8
1/2
PHONE JACK
9
1/4
LOWER RIGHT
Page 6002
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COMPONENT MAINTENANCE MANUAL
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3&1"*3/045&/$*-"/%."3,*/(3&1-"$&.&/5
ITEM NO.
LETTER HEIGHT
MARKING
10
1/2
GROUND JACK
Marking Locations
Table 601
TASK 71−11−09−300−802
5.
Material and Equipment
NOTE:
YOU CAN USE ALTERNATIVE MATERIALS WITH THE SAME PROPERTIES TO
REPLACE THE ITEMS SHOWN IN TABLE 602.
DESCRIPTION
DESIGNATION
MANUFACTURER
Cloth, Lint−Free
Cotton
Commercially Available
Compound, Rubbing
Commercially Available
Flat Black
Flat 3121
V9D157
Pro Line Paint Company
2646 Main Street
San Diego, CA 92113
619−231−2313
Paper, Abrasive
400, 600 Grit Aluminum Oxide
Commercially Available
Spatula
Metal or Plastic
Commercially Available
Solvent
Isopropyl Alcohol 99 percent
pure or
Commercially Available
MIBK/MEK Blend (60% Methyl V5E821
Isobutyl Ketone/40% Methyl
Univar U.S.A., Inc.
Ethyl Ketone or
532 E. Emaus Street
Middletown, PA 17057−2200
Phone: (717) 944−7471
www.univarusa.com
Tape, Teflon
Turco 6646
V71410
Henkel Corporation
32100 Stephenson Hwy.
Madison Heights, MI 48071
Phone: (248) 583−9300
www.aerospace.henkel.com
2−In. (50.8 mm) Wide
Commercially Available
Page 6003
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COMPONENT MAINTENANCE MANUAL
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3&1"*3/045&/$*-"/%."3,*/(3&1-"$&.&/5
DESCRIPTION
DESIGNATION
MANUFACTURER
Template
Commercially Available
Topcoat, Epoxy −
Temperature control
Flat 463−3−8, Flat Black
V0KXA5
Akzo Nobel Aerospace Coatings
East Water St.
Waukegan, IL 60085−5563
Phone: (847) 625−4200
Fax: (847) 625−3200
www.anac.com
Repair Materials and Equipment
Table 602
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3&1"*3/045&/$*-"/%."3,*/(3&1-"$&.&/5
7
4
1
6
1
9
C2C−1060−01
FIGURE 601 ENGINE INLET COWL MARKING LOCATIONS
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3&1"*3/045&/$*-"/%."3,*/(3&1-"$&.&/5
1
2
4
5
1
3
8
10
C2C−1061−01
FIGURE 601 ENGINE INLET COWL MARKING LOCATIONS
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PHONE
JACK
0.38
2.75
3.20
(0.25)
0.25
2 PL
4.05
GROUND
JACK
1.25
DIAGRAM OF MARKING FOR
PHONE JACK AND GROUND JACK
SCALE: NONE
C2C−1094−00
0.50
TYP
FIGURE 601 ENGINE INLET COWL MARKING LOCATIONS
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THIS PAGE INTENTIONALLY LEFT BLANK
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Apr 15/2019
GOODRICH AEROSTRUCTURES
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Document Part No. 277−1100
3&1"*3/0-&"%*/(&%(&1305&$5033&1"*3
TASK 71−11−09−300−803
1.
Repair No. 2
TASK 71−11−09−300−803
2.
General
A.
This repair installs edge protectors which are 18−inch (457 mm) in length.
B.
For larger areas, butt splice two sections together. For smaller areas, cut the length to size.
C.
If there is damage to the composite surfaces, refer to CF6−80E1 A330 Structural Repair
Manual Section 54−10−00.
TASK 71−11−09−300−803
3.
Repair Instructions
A.
Surface Preparation
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
(1)
Use a putty knife and remove all aerodynamic sealant between the lip skin and the outer
barrel panel in the damaged area.
(2)
Make sure there is a minimum gap 0.040−inch (1.02 mm) between the lip skin trailing
edge and the outer barrel leading edge (See Figure 601).
(3)
If the gap is less than 0.040−inch (1.02 mm), proceed as follows:
CAUTION:
(a)
DO NOT CUT INTO LIP SKIN ASSEMBLY BELOW THE OUTER
BARREL LEADING EDGE.
Grind or cut the outer barrel leading edge. Maintain a minimum 2D edge distance
around fasteners.
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3&1"*3/0-&"%*/(&%(&1305&$5033&1"*3
WARNING:
(4)
Remove the unwanted material with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 601)
(5)
Mask the area 1.0−inch (25.4 mm) around the repair area with Teflon tape (See Table
601).
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
(6)
Use 240−grit abrasive paper (See Table 601) and rough the repair area between the
tape and the lip skin.
(7)
Use 240−grit abrasive paper and break the corner of the outer barrel leading edge to a
0.020−inch (0.51 mm) radius (See Figure 601).
WARNING:
(8)
B.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Remove the unwanted material with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 601)
Repair Material Preparation
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Document Part No. 277−1100
3&1"*3/0-&"%*/(&%(&1305&$5033&1"*3
(1)
Cut the edge protector(s) to fit the repair edge. Butt the edge protector(s) to the outer
barrel leading edge and gently bend to form around the contour.
(2)
Use 400−grit abrasive paper (See Table 601) and rough the mating surface of the edge
protector (See Table 601).
WARNING:
(3)
Remove the unwanted material with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 601)
(4)
Use 0.063−inch (1.60 mm) thick Aluminum sheet (See Table 601) and make 1.0−inch
(25.4 mm) wide x 40.0−inch (1016.0 mm) long strips.
NOTE:
(5)
C.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
THE STRIPS WILL BE USED TO CLAMP THE EDGE PROTECTORS
TO THE OUTER BARREL WHILE THE ADHESIVE CURES. MAKE A
SUFFICIENT NUMBER OF STRIPS TO COVER ALL OF THE EDGE
PROTECTOR(S).
Cover the mating side of the aluminum strips with Teflon tape (See Figure 602).
Edge Protector Bonding
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(1)
Mix the adhesive (See Table 601). Refer to the instructions of the manufacturer.
(2)
Apply the adhesive to the repair surface and the mating surface of the edge protector(s).
Refer to the instructions of the manufacturer.
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Document Part No. 277−1100
3&1"*3/0-&"%*/(&%(&1305&$5033&1"*3
(3)
Butt the edge protector(s) to the leading edge of the outer barrel (See Figure 602).
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(4)
Remove excess adhesive with a clean cotton cloth moist with solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 601)
(5)
Put the aluminum strips over the edge protector(s) and apply Teflon tape axially over the
aluminum strips (See Figure 602).
(6)
Put a cargo strap around the inlet cowl and over the aluminum strips. Lightly snug the
cargo strap to the inlet cowl (See Figure 602).
(7)
Use a putty knife and push the edge lip of the edge protector aft against the outer barrel
leading edge.
CAUTION:
DO NOT OVER TIGHTEN THE CARGO STRAP. DAMAGE TO THE INLET
COWL CAN OCCUR.
(8)
Tighten the cargo strap against the inlet cowl.
(9)
Dry the adhesive. Refer to the instructions of the manufacturer.
(10) Remove the cargo strap, aluminum strip(s) and Teflon tape.
D.
Surface Finish Application
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Document Part No. 277−1100
3&1"*3/0-&"%*/(&%(&1305&$5033&1"*3
WARNING:
(1)
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
Use 240−grit abrasive paper and remove the excess adhesive to make an aerodynamic
surface. Use 400−grit abrasive paper and rough the surface of the edge protector(s).
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(2)
Fill the gap between the edge protector(s) and lip skin with the sealant. Use the sealant
to fill any area around the edge protector(s) not filled by adhesive. Refer to the
instructions of the manufacturer.
(3)
Use a putty knife and form the sealant to make an aerodynamic surface.
WARNING:
(4)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Mix the epoxy primer (See Table 601). Refer to the instructions of the manufacturer.
Page 6005
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0-&"%*/(&%(&1305&$5033&1"*3
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(5)
Remove the unwanted material with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 601)
(6)
Mask the repair area and the lip skin prevent over spray on the surrounding surface.
(7)
Apply one coat of the epoxy primer to the masked repair area. Refer to the instructions
of the manufacturer.
NOTE:
A COAT OF EPOXY PRIMER SHALL BE 0.0005 TO 0.001−INCH
(0.013 TO 0.025 MM) THICK.
(8)
Dry the primer. Refer to the instructions of the manufacturer.
(9)
Apply the anti−static and top coat. Refer to the requirements of the Airline Manufacturer.
(10) Remove all masking materials.
TASK 71−11−09−300−803
4.
Repair Materials and Equipment
NOTE:
YOU CAN USE ALTERNATIVE MATERIALS WITH THE SAME PROPERTIES TO
REPLACE THE ITEMS SHOWN IN TABLE 601.
DESCRIPTION
DESIGNATION
MANUFACTURER
Adhesive, Epoxy Paste
EA934NA
V33564
Henkel Corporation
2850 Willow Pass Rd.
P.O. Box 312
Baypoint, CA 94565−0031
Phone: (800) 257−7522
www.aerospace.henkel.com
Cloth
Lint−Free, Cotton
Commercially Available
Knife
Putty
Commercially Available
Page 6006
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0-&"%*/(&%(&1305&$5033&1"*3
DESCRIPTION
DESIGNATION
MANUFACTURER
Lamp, Heat
75°−200°F (25°−95°C)
Commercially Available
Paper, Abrasive
240−Grit, Silicon Carbide
Commercially Available
Paper, Abrasive
400−Grit, Aluminum Oxide
Commercially Available
Primer, Epoxy Base Curing
Solution Reducer
EEAY051
or
02Y040A
V83574
PRC−DeSoto International, Inc. DBA
PPG Aerospace Div
ASC−Los Angeles
24811 Avenue Rockefeller Valencia,
CA 91355−3468
P.O. Box 1800
Phone: (661) 678−4209
www.ppgaerospace.com
Protector, Edge
S700E1474−2
V51563
Goodrich Corporation
850 Lagoon Drive
Chula Vista, CA 91910−2098
Sealant
DC 93−006 (Two Part)
Sealant and Catalyst
V5D028
Dow Corning Corporation
3901 South Saginaw Road
Midland, MI 48686
Phone: (989) 496−4400
www.dowcorning.com
Sheet, Aluminum
0.063−inch (1.60 mm)
CLAD 2024−T3
Commercially Available
Solvent
Isopropyl Alcohol 99 percent
pure or
Commercially Available
MIBK/MEK Blend (60% Methyl V5E821
Isobutyl Ketone/40% Methyl
Univar U.S.A., Inc.
Ethyl Ketone or
532 E. Emaus Street
Middletown, PA 17057−2200
Phone: (717) 944−7471
www.univarusa.com
Page 6007
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Apr 15/2019
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COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0-&"%*/(&%(&1305&$5033&1"*3
DESCRIPTION
DESIGNATION
MANUFACTURER
Turco 6646
V71410
Henkel Corporation
32100 Stephenson Hwy
Madison Heights, MI 48071
Phone: (248) 583−9300
www.aerospace.henkel.com
Spatula
Metal or Plastic
Commercially Available
Strap
Cargo
Commercially Available
Tape, Masking
2.0−inch (50.8 mm)
Commercially Available
Tape, Teflon
1.0−inch (25.4 mm)
Commercially Available
Template
Commercially Available
Repair Materials and Equipment
Table 601
Page 6008
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Document Part No. 277−1100
3&1"*3/0-&"%*/(&%(&1305&$5033&1"*3
1.0 IN.
(25.4 mm)
TEFLON TAPE
1.0 IN.
(25.4 mm)
LIPSKIN
OUTER
BARREL
0.040 IN.
(1.016 mm)
MINIMUM
GAP
BREAK CORNER
0.020 IN.
(0.508 mm)
RADIUS
REMOVE ALL
AERODYNAMIC
SEALANT
MCC−094−00
PREPARATION FOR INSTALLATION OF OUTER BARREL EDGE PROTECTOR STRIP FIGURE 601
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COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0-&"%*/(&%(&1305&$5033&1"*3
CARGO STRAP (ALL AROUND INLET)
METAL CLAMPING STRIP
TEFLON TAPE
STRIPS OF TEFLON
TAPE (TYPICAL)
(AXIAL DIRECTION)
EDGE PROTECTOR
P/N − S700E1474−2
OUTER BARREL
LIPSKIN
1.0 in. WIDE TEFLON TAPE
CEC−007−00
EA9394
BOTH FAYING
SURFACES
PREPARATION FOR INSTALLATION OF OUTER BARREL EDGE PROTECTOR STRIP FIGURE 601
Page 6010
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1"*30'*/-&5$08-065&3#"33&-'3".&4536$563&
TASK 71−11−09−300−804
1.
Repair No. 3
TASK 71−11−09−300−804
2.
General
A.
This repair assumes the outer barrel panel has been removed.
B.
This repair describes a single frame repairs. All three frames may be repaired and the
moisture barrier is recommended on all three frames.
C.
Repair to frame caps uses precured flat laminations of unidirectional carbon tape. The basic
element is a fiberglass cloth sandwiched between two layers of 0.005−inch thick unidirectional
carbon−epoxy tape. The glass stops the carbon tape from splitting when laminates are
pushed into the contour.
TASK 71−11−09−300−804
3.
Repair Instructions
A.
Inspect damage area. (See Figure 601)
(1)
B.
Determine the extent of the damage.
Remove all damage. (See Figure 601)
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
(1)
Cut out damaged area of frame to the length required to accomplish required repairs.
(2)
Cut away or remove damaged or disbonded part of aluminum honeycomb core. Sand off
adhesive fillets and remove adhesive down to original fiberglass layer. Fiberglass layer
must not be damaged. If damaged, you must replace the layer.
(3)
Taper ends off frame caps 45 degrees toward outer surface at the cut off line. Smooth
edges of cut off using 180−grit or finer abrasive paper. Sand outer surface of frame cap
six inches beyond cut off using 180−grit abrasive paper. Sand surfaces to smooth matte
finish for bonding.
Page 6001
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1"*30'*/-&5$08-065&3#"33&-'3".&4536$563&
WARNING:
(4)
C.
Remove the unwanted material with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 601)
Remove moisture from the repair area.
NOTE:
DO THIS PROCEDURE IF THERE IS EVIDENCE OF MOISTURE IN
THE REPAIR AREA.
(1)
Put five plies of fiberglass fabric bleeder cloth above and all around the repair area.
(2)
Put a sheet of silicone rubber above the fiberglass fabric.
(3)
Put a heat blanket above the sheet of silicone rubber.
(4)
Put two plies of breather cloth above the heat blanket.
(5)
Put a sheet of 4 mil nylon bagging film above the repair area. The sheet must be 2.0 in.
(51 mm) larger than the repair area all around.
(6)
Put the vacuum probes under the nylon bagging film. Seal the probes to the bagging film
with tacky tape bag sealant. Seal the edges of the bagging film to the structure with the
sealant.
(7)
Connect the vacuum hose to the vacuum source. Connect the heat blanket to an
electrical source.
(8)
Apply a steady vacuum pressure of 22 in. of mercury (74, 5 kPa) and heat the area for
two hours at 150° to 170°F (66° to 77°C).
NOTE:
(9)
D.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
REPEAT STEPS C.(1) THROUGH C.(8) UNTIL THERE IS NO
EVIDENCE OF MOISTURE OR OTHER CONTAMINATION.
Disconnect the heat blanket and the vacuum source. Remove the bagging material.
Trim repair core plug. (See Table 601 for core material)
Page 6002
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1"*30'*/-&5$08-065&3#"33&-'3".&4536$563&
(1)
E.
Trim aluminum honeycomb repair core plug to length of the cutout for a close fit.
Make frame cap repair element.
WARNING:
(1)
Lay out two graphite tapes with fiber in the lengthwise direction and one prepreg glass
fabric strip at least 2 in. (50.8 mm) longer and the same width as the removed cap
material for each ‘cap repair element’.
(2)
Lay up two graphite tapes with one prepreg glass fabric strip sandwiched in between,
i.e., tape−glass−tape, for each cap repair element. (Two cap repair elements are
required for each frame repair).
(3)
Vacuum bag and place both repair elements (tape−glass−tape) flat in autoclave and
cure at 70 psi (482.6 kPa) and 345°−355°F (173.9°−179.4°C) for 120−180 minutes.
NOTE:
F.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
IF TOOLING IS AVAILABLE, INDIVIDUAL GRAPHITE TAPES (4 PER
FRAME REPAIR) CAN BE CURED TO THE OUTER BARREL
RADIUS AND WOULD NOT REQUIRE THE GLASS FABRIC.
Prepare fiberglass fill plies.
WARNING:
(1)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Use prepreg glass fabric and cut sufficient plies to provide a level surface between the
aluminum honeycomb repair core plug and the original frame cap surface. (See Figure
602)
Page 6003
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1"*30'*/-&5$08-065&3#"33&-'3".&4536$563&
G.
(2)
Lay up the required number of plies. Bag and apply vacuum at 22 in. of mercury (74.5
kPa). Put into autoclave while under vacuum. Apply 40 to 50 psi (275.8−344.7 kPa)
positive pressure. When autoclave pressure reaches 15 psi (103.4 kPa), vent the
vacuum bag to the atmosphere.
(3)
Heat to 240° to 260°F (115° to 127°C) at a rate of 2° to 8°F (1° to 5°C) per minute. Keep
at temperature for 90 to 105 minutes. Cool down to 160°F (71°C) before you release the
autoclave pressure.
Install aluminum honeycomb repair core plug.
WARNING:
(1)
Use foaming adhesive in accordance with manufacturer’s instructions.
(2)
Apply foaming adhesive at the mating areas of the original honeycomb.
WARNING:
H.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(3)
Apply supported film adhesive between core plug and outer barrel.
(4)
Insert repair core plug.
(5)
Apply one or more plies of supported film adhesive on open honeycomb cells.
Install pre−cured fill plies. (See Figure 602)
(1)
Cut and fit the pre−cured fiberglass fill plies to the area.
Page 6004
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1"*30'*/-&5$08-065&3#"33&-'3".&4536$563&
I.
(2)
Make sure the fill plies will be flush with the outer frame cap outer surface. Use abrasive
paper to sand down to the correct thickness, if necessary.
(3)
Fit the fill plies into position.
Install repair elements. (See Figure 602)
WARNING:
(1)
Place supported film adhesive over the entire repair length including at least one inch
(25.4 mm) beyond the cut off line at each end.
(2)
Place the first cap repair element in the location shown with the one inch (25.4 mm)
overlap at each end.
WARNING:
J.
K.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(3)
Place another layer of supported film adhesive between the first and second cap repair
elements.
(4)
Install the second cap repair element with length as shown.
Prepare repair elements and fill plies for curing.
(1)
Vacuum bag repair area for autoclave cure.
(2)
Install adequate tooling to stabilize the outer barrel panel during the cure cycle.
Cure repair parts.
Page 6005
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1"*30'*/-&5$08-065&3#"33&-'3".&4536$563&
L.
(1)
Load into autoclave and apply a minimum of 10 inches (250 mm) of mercury (33.9 kPa)
vacuum.
(2)
Apply 35 psig (241.3 kPa) pressure before autoclave temperature reaches 200°F
(93.3°C).
(3)
Vent bag to atmosphere when autoclave pressure records 15 to 20 psig (103.4 to 137.9
kPa).
(4)
Heat at 1° to 10°F (0.5° to 5.5°C) per minute.
(5)
Cure at 345° to 365°F (174° to 185°C) for 120 minutes at 35 psig (241.3 kPa).
(6)
Remove vacuum bag and materials.
Inspect the repair.
(1)
M.
Do an inspection and a tap test of the repair area to make sure the requirements of this
repair are done.
Install fiberglass fabric moisture barrier over complete repair area as well as any remaining
undamaged frames. (See Figure 603)
(1)
Place a sheet of fiberglass on a sheet of nonporous parting film that is large enough to
cover the frame and extend at least 0.5 inch (12.7 mm) on each side of the frame.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(2)
Cover with another sheet of nonporous parting film after coating with adhesive. Use a
roller to thoroughly soak fiberglass fabric with adhesive, to remove trapped air and to
remove excessive adhesive.
(3)
Fit fiberglass fabric sheet over complete frame, tucking in the corner at the core to outer
skin joint on both sides of the frame.
(4)
Cover the fiberglass fabric sheet with a sheet of porous parting film approximately 2
inches (50.8 mm) larger than the fiberglass. Cover the parting film with three layers of
bleeder cloth.
Page 6006
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1"*30'*/-&5$08-065&3#"33&-'3".&4536$563&
(5)
Cover the entire porous parting film with a vacuum bag approximately 2 inches (50.8
mm) larger, place a vacuum connector under the bag and seal edges with bag sealant.
Apply 20 inches (508 mm) of mercury (67.7 kPa) vacuum inside bag.
(6)
Use heat lamps and cure at approximately 150°F (65.5°C) for 1 hour.
(7)
Remove vacuum bag and materials.
N.
Inspect for integrity of sealing against moisture around complete repair area.
TASK 71−11−09−300−804
4.
Repair Materials and Equipment
NOTE:
YOU CAN USE ALTERNATIVE MATERIALS WITH THE SAME PROPERTIES TO
REPLACE THE ITEMS SHOWN IN TABLE 601. .
DESCRIPTION
DESIGNATION
MANUFACTURER
Adhesive, Foaming
FM410−1
V0V7G8
Cytec Industries Inc.
5 Garret Mountain Plz
West Paterson, NJ 07242−3317
Adhesive
EA9396 A/B
V33564
Henkel Corporation
2850 Willow Pass Rd.
P.O. Box 312
Baypoint, CA 94565−0031
Phone: (800) 257−7522
www.aerospace.henkel.com
Adhesive, Epoxy Film
EA9689
V33564
Henkel Corporation
Blanket, Heat
0°−250°F 10W/Sq.In
(−18°−121°C 10W/
(645 mm sq)
V61426
Atacs Products, Inc.
850 South Cambridge Street
Seattle, WA 98108−4748
Phone: (206) 433−9000
www.atacs.com
Brush
Nylon Bristle
Commercially Available
Cloth, Bleeder
Fiberglass
Commercially Available
Page 6007
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1"*30'*/-&5$08-065&3#"33&-'3".&4536$563&
DESCRIPTION
DESIGNATION
MANUFACTURER
Cloth, Breather
RC3000−10
V0F451
Richmond Aircraft Products, Inc.
13503 Pulmice St
Norwalk, CA 90650−5250
Phone: (562) 404−2440
www.richmondaircraft.com
Cloth, Lint−Free
Cotton
Commercially Available
Clothing, Protective
Commercially Available
Connector, Vacuum
1/8−In. (3,2 mm)
Diameter
Commercially Available
Container
Metal or Plastic
Commercially Available
Cover, Container
Metal or Plastic
Commercially Available
Fabric, Fiberglass
Type 181
Commercially Available
Film, Bagging
4 Mil (0.1 mm) Nylon
V0F451
Richmond Aircraft Products, Inc
Film, Parting
Non−Pourous, Porous
V0F451
Richmond Aircraft Products, Inc.
Gauge, Vacuum
0−20−In.−Of−Mercury
(0 to 67.7 kPa)
Commercially Available
Glasses, Safety
Commercially Available
Gloves
Neoprene or Polyvinyl
Chloride
Commercially Available
Graphite Tape
AS−4/3501−5A
2 in. (50.8 mm) wide
V0CZA6
Hercules Aerospace Co.
5000 S 8400 W
P.O. Box 98
Magna, UT 84044−0098
Honeycomb Core
0.842 height x 2 wide
(1/8 hex cell x
0.0020 Thick) 5052
or 5056 Al alloy
foil, Non−perforated,
Core density 8.1 lb/
cu. ft.
V0WL95 Alcore, Inc.
1502 Quarry Drive
Edgewood, MD 21040−1047
Phone (410) 676−7100
www.alcore.com
Page 6008
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1"*30'*/-&5$08-065&3#"33&-'3".&4536$563&
DESCRIPTION
DESIGNATION
MANUFACTURER
Honeycomb Core
0.842 height x 2 wide
(1/8 hex cell x
0.0020 Thick) 5052
or 5056 Al alloy
foil, Non−perforated,
Core density 8.1 lb/
cu. ft.
V52331
Hexcel Corporation
11711 Dublin Blvd
Dublin, CA 94568−2832
Phone: (203) 696−0666
Fax: (203) 316−5139
www.hexcel.com
Hose, Vacuum
1/8−In. (3.2 mm)
Diameter
Commercially Available
Knife, Utility
Commercially Available
Lamp, Heat
180°−200°F
(82.2°−93.3°C)
Commercially Available
Mask, Dust
Regulatory Agency
Approved
Commercially Available
Paper, Abrasive
159, 320−Grit
Aluminum Oxide
Commercially Available
Prepreg Glass Fabric
CYCOM 985−1/120
V0V7G8
Cytec Industries Inc.
5 Garret Mountain Plz
West Paterson, NJ 07242−3317
phone: (973) 357−3100
www.cytec.com
Probe, Temperature
0° − 250°F
(−17.8° − 121°C)
Commercially Available
Pump, Vacuum
0−30 In.−of−Mercury
(0−101.6 kPa)
Commercially Available
Roller
Steel or Plastic
2−Inch (50.8 mm) Dia
Commercially Available
Rubber, Sheet
0.062−0.125−Inch
(1.6−3.2 mm)
Silicone
V85471
Boyd Corporation
13885 Ramona Avenue
Chino, CA 91710−5426
www.boydcorp.com
Page 6009
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1"*30'*/-&5$08-065&3#"33&-'3".&4536$563&
DESCRIPTION
DESIGNATION
MANUFACTURER
Sealant, Bag
Tacky Tape
V53309
Schnee−Morehead
Chemicals, Inc.
111 North Nursery Road
P.O. Box 1305
Irving, TX 75060−3153
Solvent
Isopropyl Alcohol 99 Percent
Pure
or
Commercially Available
MIBK/MEK Blend (60% Methyl
Isobutyl Ketone/40% Methyl
Ethyl Ketone)
or
V5E821
Univar U.S.A., Inc.
532 E. Emaus Street
Middletown, PA 17057−2200
Phone: (717) 944−7471
www.univarusa.com
Turco 6646
V71410
Henkel Corporation
32100 Stephenson Hwy.
Madison Heights, MI 48071
Phone: (248) 583−9300
www.aerospace.henkel.com
Repair Materials and Equipment
Table 601
Page 6010
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Document Part No. 277−1100
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DAMAGE
A
A
24 INCH MAX.
CUTOUT
CUTOUT
INNER CAP (4)
INNER BARRIER
CORE
OUTER BARRIER
OUTER BARREL SKIN
SIDE VIEW
SECTION A−A
C2C−081−00
FIGURE 601 FRAME DAMAGE CLEAN UP
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GLASS CLOTH DUST COVER
B
B
.075 .075 1.0
INCH INCH INCH
GLASS
CLOTH
DUST
COVER
CAP REPAIR
ELEMENT (2)
TOP VIEW
INNER CAP
(4)
GLASS
FILL PLIES
INNER BARRIER
CORE REPAIR PLUG
CORE
OUTER BARRIER
OUTER BARREL SKIN
SIDE VIEW
SECTION B−B
C2C−082−00
FIGURE 602 INSTALLATION OF REPAIR PLIES
Page 6012
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Document Part No. 277−1100
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HEAT BLANKET
BREATHER CLOTH (2)
BREATHER CLOTH (2)
NONPOROUS PARTING
FILM
BLEEDER CLOTH (3)
VACUUM BAG
VACUUM
HOSE
POROUS PARTING
FILM
CAP REPAIR ELEMENT (2)
GLASS
CLOTH
DUST
COVER
BAG SEAL
GLASS
CLOTH
FILL
PLIES
CORE REPAIR
PLUG
TEMPERATURE
PROBE
OUTER BARRIER
C2C−083−00
FIGURE 603 HEAT BLANKET INSTALLATION
Page 6013
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
Page 6014
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
TASK 71−11−09−300−805
1.
Repair No. 4
TASK 71−11−09−300−805
2.
General
A.
This repair applies to frame damage up to 60−inches (1524 mm) in length.
B.
This repair applies to outer barrel panels that you have removed from the inlet cowl.
C.
This repair gives a single or multiple frame repairs. All three frames can be repaired at one
time. We recommend that you apply the moisture barrier on all three frames, whether you
repair them or not.
D.
This repair replaces a section of carbon tape cap element and damaged core with
replacement core and five (5) plies of graphite fabric.
TASK 71−11−09−300−805
3.
Repair Instructions
A.
Examine damage area (See Figure 601)
(1)
Install adequate fixture(s) to stabilize outer barrel panel.
(2)
Visually examine and do a tap test on all frames to determine the extent of damage. Put
marks on the panel where you will cut out the damaged frame.
NOTE:
(3)
ENSURE THE MAXIMUM LENGTH OF DAMAGE DOES NOT
EXCEED 60−INCHES (1524 MM) FOR ANY ONE FRAME. IF
DAMAGE EXCEEDS THIS LIMIT, CONTACT YOUR LOCAL
REPRESENTATIVE FROM GOODRICH AEROSTRUCTURES,
FORMALLY ROHR, FOR DISPOSITION.
Determine the distance from the marks to apply tape according to the following formula:
(See Figure 602)
(a)
Add 1−inch (25.4 mm) from the marks for first repair ply.
(b)
Add 0.75−inch (19.05 mm) more from the marks for each additional repair ply,
including the fiberglass moisture barrier.
(c)
Add 2−inches (50.8 mm) more from the marks.
(4)
Apply 2−inch (50.8 mm) wide teflon tape around the repair area at the distance you
found in step A.(3).
(5)
Make lay−up templates for the ply lay−ups. See figure 602 for the dimensions of each
ply lay−up.
Page 6001
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COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
B.
Remove all damage (See Figure 601)
WARNING:
(1)
Cut out the section of the damaged frame as necessary.
(2)
Cut away and remove the damaged or disbonded part of the aluminum honeycomb
core. Remove the adhesive on the graphite fabric under the core to a smooth finish. Use
180−grit or finer abrasive paper. Be careful that you do not damage the fibers of the
graphite fabric.
(3)
Taper the ends of the cut frame caps to 45 degrees at the cut off line. Make the edges of
frame cut off areas smooth with 180−grit or finer abrasive paper. Remove the outer
surface of the frame cap 6.0−inches (152.4 mm) beyond the cut off line. Use 180−grit or
finer abrasive paper. Make the surfaces smooth to a matte finish for bonding. (See
Figure 601)
WARNING:
(4)
C.
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Remove the unwanted material with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 601)
Remove moisture from the repair area
NOTE:
DO THE FOLLOWING PROCEDURE IF THERE IS EVIDENCE OF
MOISTURE IN THE REPAIR AREA.
(1)
Put five plies of the fiberglass fabric bleeder cloth above and all around the repair area.
(2)
Put a sheet of silicone rubber above the fiberglass fabric.
Page 6002
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GOODRICH AEROSTRUCTURES
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Document Part No. 277−1100
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(3)
Put a heat blanket above the silicone rubber.
(4)
Put two plies of breather cloth above the heat blanket.
(5)
Put a sheet of 4−mil nylon bagging film above repair area. The sheet must be 2.0−
inches (50.8 mm) larger than the repair area all around.
(6)
Put the vacuum probes under the nylon bagging film. Seal the probes to the bagging film
with tacky tape bag sealant. Seal the edges of the bagging film to the structure with bag
sealant.
(7)
Connect the vacuum hose to the vacuum source. Connect the heat blanket to an
electrical source.
(8)
Apply a steady vacuum pressure of 22−inches of mercury (74.53 kPa) and heat the area
at 150° to 170°F (66° to 77°C) for two hours.
NOTE:
(9)
D.
Disconnect the heat blanket and the vacuum source. Remove bag sealant, vacuum
hose, heat probe, bagging film, breather cloth, rubber sheet, and bleeder cloth.
Cut repair core plug
(1)
E.
REPEAT STEPS C.(1) THROUGH C.(8) UNTIL THERE IS NO SIGN
OF MOISTURE OR OTHER CONTAMINATION.
Cut the aluminum honeycomb repair core plug to the same length and height of the cut
out section. The repair core must be cut so that the ribbon direction matches that of the
remaining core.
Prepare the graphite fabric and the fiberglass fabric
NOTE:
DETERMINE THE WARP DIRECTION AND LAY−UP OF THE OUTER
BARREL PANEL. THIS DATA CAN BE FOUND IN THE SRM.
(1)
Cut a sheet of graphite fabric large enough so that you can cut all repair plies and fill
plies from it.
(2)
Cut a sheet of the fiberglass fabric large enough that you can cut the moisture barrier
from it.
Page 6003
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
WARNING:
(3)
Mix the epoxy composite repair adhesive. Refer to the instructions of the manufacturer.
WARNING:
F.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(4)
Put a sheet of graphite fabric on a sheet of nonporous parting film. Use a brush or
spatula to apply a layer of adhesive on the fabric. Put another sheet of nonporous
parting film on the fabric. Apply adhesive with a spatula and soak the sheet thoroughly.
Use the spatula to remove air trapped in the fabric.
(5)
Prepare the fiberglass fabric by repeating step E.(4).
Prepare the repair area for the aluminum honeycomb core plug (See Figure 602)
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(1)
Mix the structural paste adhesive. Refer to the instructions of the manufacturer.
(2)
Apply structual paste adhesive at the areas that touched the original honeycomb and at
the inner surface of the outer barrel. Refer to the instructions of the manufacturer.
Page 6004
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
G.
Install core plug with the ribbon direction matching that of the remaining core (See Figure 602)
WARNING:
H.
I.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(1)
Apply structural paste adhesive. Refer to the instructions of the manufacturer.
(2)
Use a brush to coat the ends and sides of the repair plug with the adhesive.
(3)
Install the repair core plug with the ribbon direction matching that of the remaining core.
Cut the repair and fill plies (See Figure 602)
(1)
Cut the five repair plies and fill plies from the prepared graphite fabric with the templates
made in step A.(5). Make sure the warp direction of the fill plies match that of each
repair ply.
(2)
Remove bottom ply of nonporous parting film from first graphite fill ply. Install the fill ply
on top of the honeycomb core. Remove all wrinkles and trapped air from the fill ply with
a brush. Remove the nonporous parting film from top of fill ply.
(3)
Repeat step H.(2) for the remaining graphite fill plies. Make sure the top fill ply is flush
with the outer frame cap outer surface. Remove all wrinkles and trapped air from top fill
ply with a brush. Remove the nonporous parting film from top ply.
Install Graphite Fabric repair elements (See Figure 602)
Page 6005
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
WARNING:
J.
K.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(1)
Remove the nonporous parting film from the bottom of repair ply No. 1. Install the repair
ply on the frame cap surface with the cut out and fill plies in the center. Remove all
wrinkles and trapped air from the repair ply with a brush. Remove the nonporous parting
film from the top of the graphite repair ply.
(2)
Remove the nonporous parting film from the bottom of the subsequent repair ply. Install
the repair ply with the previous repair ply in the center. Remove all wrinkles and trapped
air with a brush. Remove the nonporous parting film from the top of the repair ply.
(3)
Repeat step I.(2) for all five (5) repair plies.
Install the fiberglass fabric as a moisture barrier over complete repair area (See Figure 603)
(1)
Cut the moisture barrier from the prepared fiberglass fabric. Make sure it is large enough
to cover the frame(s) being repaired and any adjacent frames. Make sure it extends at
least 0.5−inch (12.7 mm) on each side of all frame(s) covered.
(2)
Remove the nonporous parting film from bottom of the fiberglass ply. Put the fiberglass
ply over the repair area. Remove wrinkles and trapped air with a brush. Remove the
nonporous parting film from the top of the fiberglass ply.
Prepare repair area for curing (See Figure 604)
NOTE:
ONE SHEET OF BLEEDER PLY IS NECESSARY FOR EACH
REPAIR LAYER.
NOTE:
IF THE REPAIR AREA IS LARGER THAN 36−INCHES (914.4 MM),
TWO VACUUM CONNECTIONS AT OPPOSITE CORNERS OF THE
BAG ARE NECESSARY. THIS IS TO MAKE SURE THERE IS
CORRECT VACUUM PRESSURE OVER THE REPAIR AREA.
NOTE:
INSULATION CAN POSSIBLY BE NECESSARY AROUND THE
OUTSIDE SURFACE OF THE OUTER BARREL. THIS IS TO KEEP
THE TEMPERATURE EVEN AND CONSTANT, WHICH IS
NECESSARY FOR CORRECT BONDING.
Page 6006
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
L.
M.
(1)
Put a sheet of porous parting film over the moisture barrier. Make sure the parting film is
approximately 2−inches (50.8 mm) larger all around than the moisture barrier. Put six
layers of bleeder cloth over the parting film. Put a sheet of nonporous parting film over
the bleeder cloth. Put a silicone rubber sheet over the parting film.
(2)
Put one ply of breather cloth over the rubber sheet. Put a heat blanket over the breather
cloth. Put two plies of breather cloth over the heat blanket. Put a vacuum bag on the
heat blanket and rubber sheet. Make sure the vacuum bag is approximately 2−inches
(50.8 mm) larger all around than the heat blanket and rubber sheet. Put a minimum of
three temperature probes at the edge of the bond area. Put a vacuum connector under
the vacuum bag. Seal the edges of the vacuum bag with bag sealant.
Cure repair plies
(1)
Apply 22−inches of mercury (74.50 kPa) pressure inside the vacuum bag. Turn on the
heat blanket and raise temperature of the repair area to 190° to 210°F (88° to 99°C) for
220 minutes.
(2)
After the repair cools down to a minimum of 100°F (37.8°C), remove the bag sealant,
vacuum bag, heat blanket, rubber sheet, bleeder cloth, breather plies, and parting film.
Examine repair
(1)
N.
Do a visual inspection and a tap test of the repair to check for disbonds and voids.
Prepare surface for painting
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
CAUTION:
USE OF PAINT REMOVER COMPOUNDS ON GRAPHITE/ARAMID/EPOXY
STRUCTURES IS PROHIBITED. THE COMPOUNDS ATTACK THE EPOXY
BONDING ADHESIVE IN THE STRUCTURE AND WILL DEGRADE THE
INTEGRITY OF THE PARENT COMPOSITE MATERIALS.
Page 6007
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
CAUTION:
(1)
Air−wet the surface of the moisture barrier. Rub all around edge of the moisture barrier
to a featheredge with 180−grit or finer abrasive paper. Make sure the surface is smooth
enough to paint.
(2)
Rub graphite/aramid/epoxy structures with 180−grit or finer abrasive paper to a smooth,
dull matte finish with all gloss removed.
(3)
Remove surface finishes and filler material from areas to be painted. Rub the material
from rivet heads to a featheredge of a minimum blend ratio of 10 to 1.
WARNING:
O.
DO NOT CUT OR BREAK FIBERS FROM EXPOSED GRAPHITE PLY.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(4)
Remove the unwanted material with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 601)
(5)
Put a cover around the repair area to protect adjacent surfaces from paint over−spray.
Apply the epoxy primer (green)
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(1)
Mix the green epoxy primer base and converter. Use thinner as necessary to get the
correct spray consistency. Refer to the instructions of the manufacturer.
(2)
Apply a cross coat of primer 0.0005 − 0.0007−inches (0.5 − 0.7 mil) thick. Refer to the
instructions of the manufacturer.
Page 6008
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
P.
(3)
Dry the paint. Refer to the instructions of the manufacturer.
(4)
Remove the cover from around the repair area.
Do water break test
NOTE:
CAUTION:
Q.
THIS PROCEDURE WILL MAKE SURE NO CONTAMINATION
EXISTS ON THE SURFACES TO BE BONDED. DO THIS TEST
WHEN THE SURFACES ARE CLEAN.
BE CAREFUL WHEN EXPOSING WATER TO A SURFACE ADJACENT TO
HONEYCOMB MATERIAL. IF WATER BECOMES CAUGHT IN THE
HONEYCOMB, IT WILL BE NECESSARY TO REMOVE THE WATER
BEFORE PROCEEDING WITH THE REPAIR.
(1)
Fill a clean polyethylene bottle that has a small spray nozzle with a sufficient amount of
distilled water for the test.
(2)
Spray the water on the clean surface until a thin layer of water is on all the surface.
(3)
If the surface is clean, there will be an unbroken layer of water for 30 seconds. If the
surface has contamination, the water will separate into sections or beads.
(4)
If you find the surface has contamination, repeat the cleaning procedure and do another
water break test.
(5)
After you do a successful water break test, clean the water off the surface with a clean
dry cloth.
(6)
Force air−dry the area at 150°F (65.5°C) for 30 minutes. Let the area cool to ambient
temperature before you continue with the repair.
(7)
If moisture exists in the honeycomb panel after the end of water break test, remove the
moisture from the honeycomb panel. Refer to step C. of this repair.
Prepare surface for ablative material
NOTE:
APPLY ABLATIVE MATERIAL TO THE INNER SURFACE OF THE
OUTER BARREL. MAKE SURE IT IS ON THE REPAIR AND ALL
ADJACENT AREAS. (SEE FIGURE 605).
Page 6009
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
CAUTION:
TO PREVENT CONTAMINATION OF OTHER REPAIR FACILITIES BY
SILICONE MATERIALS, MAKE SURE THE REPAIR FACILITY FOR THIS
REPAIR IS ISOLATED. ANY REPAIR FACILITIES THAT APPLIES THE
MATERIALS USED IN THIS REPAIR AND/OR ANY RELATED SILICONE
MATERIALS MUST BE IDENTIFIED "RESERVED FOR SILICONE
APPLICATION ONLY".
(1)
Remove the unwanted material with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 601)
WARNING:
(2)
R.
DO NOT POINT COMPRESSED AIR IN THE DIRECTION OF PERSONNEL.
THIS CAN CAUSE INJURY TO THE EYES OR BLINDNESS. THIS CAN
CAUSE LOOSE PARTICLES TO BECOME EMBEDDED UNDER THE
SKIN.
Blow air throughout the repaired area and around adjacent surfaces to make sure the
surface is fully clean. Air must be dry, oil−free, compressed air at 30 psi maximum
(206.8 kPa). Clean surfaces with dry cotton clothes as necessary.
NOTE:
THE SURFACE MUST BE PRIMED WITHIN 12 HOURS OF SURFACE
PREPARATION. SURFACES THAT HAVE EXCEEDED THE 12−
HOUR LIMITATION MUST BE RE−CLEANED PER STEP Q.
NOTE:
USE LINT−FREE GLOVES WHEN YOU TOUCH THE PARTS.
Prime surface for adhesion
Page 6010
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
WARNING:
(1)
Put a small quantity of RTV prime coat into a polyethylene container. Visually examine
the primer. Satisfactory siliocne primer will be clear. Unsatisfactory primer will be cloudy.
NOTE:
(2)
S.
NEVER PUT RTV PRIME COAT BACK INTO ITS ORIGINAL
CONTAINER. DISCARD UNUSED PRIMER IN AN APPROVED
WASTE CONTAINER.
Apply a very thin layer of RTV prime coat to the prepared surface. If you use red RTV
prime coat, you can make an estimate of the layer thickness by its color: the thicker the
primer, the darker the red color. Too thick a layer is chalky. Remove too thick primer with
a clean cotton cloth.
NOTE:
(3)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
IF YOU REMOVED PRIMER BECAUSE IT WAS TOO THICK, IT IS
POSSIBLE THAT YOU DO NOT NEED TO APPLY MORE PRIMER.
MAKE SURE THE ENTIRE SURFACE IS WET WITHOUT RUNS OR
PUDDLES. MAKE SURE THE PRIMER IS NOT CHALKY.
RDry the primer. Refer to the instructions of the manufacturer.
Apply ablative material (See Figure 605)
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(1)
Mix ablative material. Refer to the instructions of the manufacturer.
(2)
Initial equipment adjustments are:
Page 6011
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
(a)
Spray pot pressure; 25 ± 5 psi (172.3 ± 34.4 kPa).
(b)
Atomization pressure; 30 ± 10 psi (206.8 ± 68.9 kPa).
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(3)
Put Heptane solvent through the fluid hose and spray gun immediately before the
ablative material. This prevents the equipment from becoming clogged at start up.
(4)
Apply a test pattern spray on a test sheet. The distance from the nozzle to the substrate
must be 8−12−inches (203.2−304.8 mm). The spray material must be smooth and flat
on the paper. If the material does not apply correctly, adjust the spray gun equipment.
For example, adjust the fluid needle to change the wetness of the material. Adjust the
spray pattern to change the width of the fan pattern.
(5)
Once you have correctly adjusted the spray pattern, apply the ablative material as
follows: Apply the first layer approximately 0.005 − 0.010−inches (0.127 − 0.254 mm)
thick. Apply subsequent layers 0.020 − 0.030−inches (0.508 − 0.762 mm) thick. Let the
solvent dry between layers for approximately 2 to 3 minutes or until the material has a
matte finish when seen from a 45 degree angle. Drying time can vary with weather
conditions and material thickness. Apply the layers with an approximately 50 percent
overlap. Each layer must be applied without stopping. The total thickness of all layers
must be between 0.500 ± 0.030−inches (12.7 mm ± 0.762 mm).
(6)
Let the layers cure at 75°± 5°F (23.9°± 2.8°C), at a relative humidity of 30%, for 48
hours minimum. For a faster cure, let the layers cure for 8 hours at 75°± 5°F (23.9°±
2.8°C) followed by 10 hours at 120° to 150°F (48.8° to 65.6°C).
(7)
Carefully remove the teflon tape from around the repair area.
Page 6012
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
WARNING:
(8)
T.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Clean the repair area with a clean, lint−free cloth and the solvent. Remove the solvent
with a clean lint−free cloth before the solvent becomes dry.
Apply the sealant. (See Figure 606)
WARNING:
(1)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Apply RTV prime coat by brush to the panel adjacent to the edge of the ablative
material. Let dry for a minimum of 60 minutes. Refer to the instructions of the
manufacturer.
NOTE:
APPLY THE SEALANT IN 24 HOURS AFTER THE PRIMER HAS
DRIED. IF MORE THAN 24 HOUR, CLEAN THE SURFACE WITH
THE SOLVENT, DRY THE SURFACE WITH A CLEAN CLOTH, AND
APPLY THE PRIMER AGAIN.
(2)
Mix the silicone sealant. Refer to the instructions of the manufacturer.
(3)
Apply the sealant to the edges you can see of the ablative material. Refer to the
instructions of the manufacturer.
NOTE:
DISTILLED WATER OR A SOLUTION OF ISOPROPYL ALCOHOL IN
DISTILLED WATER CAN BE USED TO MAKE SURE THE TOOLS
MOVE FREELY AND TO MAKE THE EDGES OF THE SEALANT
SMOOTH.
Page 6013
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
U.
(4)
Make the edges of the sealant around the ablative material smooth. Use a non−metallic
scraper or spatula. (See Figure 606)
(5)
Dry the sealant before you apply the ablative material topcoat. Refer to the instructions
of the manufacturer.
Apply the ablative material topcoat
WARNING:
(1)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Mix the ablative material topcoat part "A" by itself for 30 minutes in an explosive proof
container. After you mix part "A" slowly add the applicable amount of part "B". Refer to
the instructions of the manufacturer.
NOTE:
THE LIFE OF THE ABLATIVE MATERIAL TOPCOAT IS 60 MINUTES
AT 50° TO 90°F (9.99° TO 32.22°C) IN A CLOSED CONTAINER. FOR
SPRAY APPLICATIONS, USE THE FLUID NEEDLE TO ADJUST THE
WETNESS OF THE MATERIAL. THE NOZZLE TO SUBSTRATE
DISTANCE MUST BE 8 − 12−INCHES (203.2 − 304.8 MM). APPLY
THE MATERIAL IN MULTIPLE COATS AS NECESSARY TO
PREVENT RUNS, SAGS, AND PUDDLES. THE FIRST COAT MUST
BE 0.005−INCHES (0.127 MM) THICK. APPLY SUBSEQUENT
COATS 0.005 − 0.010−INCHES (0.127 − 0.254 MM) THICK. WAIT 2
TO 3 MINUTES BETWEEN COATS FOR SOLVENT TO DRY. AVOID
LONG DELAYS IN EXCESS OF 6 MINUTES BETWEEN COATS.
SPRAY POT PRESSURE MUST BE 20 ± 3 PSI (137.8 ± 20.6 KPA)
AND ATOMIZING SPRAY GUN PRESSURE MUST BE 40 ± 3 PSI
(275.7 ± 20.6 KPA).
(2)
Apply a layer of ablative material topcoat 0.015 − 0.020−inches (0.381 − 0.508 mm)
thick on the ablative material. Refer to the instructions of the manufacturer.
(3)
Dry the topcoat. Refer to the instructions of the manufacturer.
(4)
Visually examine the repair to make sure you did all of the requirements of this repair
procedure.
TASK 71−11−09−300−805
Page 6014
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
CAUTION:
4.
WHEN YOU REMOVE THE PANEL FROM THE SUPPORT FIXTURE(S), DO NOT
LET THE PANEL BEND TOO MUCH. THIS COULD CAUSE DAMAGE TO THE
ABLATIVE MATERIAL.
Materials and Equipment
NOTE:
YOU CAN USE ALTERNATIVE EQUIPMENT WITH THE SAME PRECISION TO
REPLACE THE ITEMS SHOWN IN TABLE 601.
NOTE:
YOU CAN USE ALTERNATIVE MATERIALS WITH THE SAME PROPERTIES TO
REPLACE THE ITEMS SHOWN IN TABLE 601.
DESCRIPTION
DESIGNATION
MANUFACTURER
Adhesive, Epoxy Composite
Repair
EA9390 (Two Part)
V33564
Henkel Corporation
2850 Willow Pass Rd.
P.O. Box 312
Baypoint, CA 94565−0031
Phone: (800) 257−7522
www.aerospace.henkel.com
Adhesive, Structural Paste
EA9394 (Two Part)
V33564
Henkel Corporation
Blanket, Heat
0°−250°F 5W/Sq.In
(−18°−121°C5said tW/
(645 mm sq)
V61426
Atacs Products, Inc.
850 South Cambridge Street
Seattle, WA 98108−4748
Phone: (206) 433−9000
www.atacs.com
Brush
Nylon Bristle
Commercially Available
Cloth
Lint−Free, Cotton
Commercially Available
Cloth, Bleeder
Fiberglass
Commercially Available
Cloth, Breather
RC3000−10
V0F451
Richmond Aircraft Products, Inc.
13503 Pulmice St
Norwalk, CA 90650−5250
Phone: (562) 404−2440
www.richmondaircraft.com
Clothing, Protective
Commercially Available
Page 6015
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
DESCRIPTION
DESIGNATION
MANUFACTURER
Cloth, Wipe
Cheesecloth
Commercially Available
Connector, Vacuum
1/8−In. (3,2 mm)
Diameter
Commercially Available
Container w/cover
Polyethylene Mixing Cups
Commercially Available
Fabric, Fiberglass
Type 181
Commercially Available
Fabric, Carbon
AH370−5H
V2B975
Hexcel Corp
1913 N King St
Seguin, TX 78155−2197
Phone: (830) 401−8130
www.hexcel.com
Film, Bagging
4 Mil (0.1 mm) Nylon
V0F451
Richmond Aircraft Products, Inc
Film, Parting
Non−Pourous, Porous
V0F451
Richmond Aircraft Products, Inc.
Gauge, Vacuum
0−30−In.−Of−Mercury
(0 to 101.6 kPa)
Commercially Available
Glasses, Safety
Commercially Available
Gloves
Neoprene or Polyvinyl
Chloride
Commercially Available
Honeycomb Core
1.0 height x 2 wide
(1/8 hex cell x
0.0020 Thick) 5052
or 5056 Al alloy
foil, Non−perforated,
Core density 8.1 lb/
Cu. Ft. RMS026,
Type 1 Grade 2
V0WL95
Alcore, Inc.
1502 Quarry Drive
Edgewood, MD 21040−1047
Phone (410) 676−7100
www.alcore.com
Page 6016
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
DESCRIPTION
DESIGNATION
MANUFACTURER
Honeycomb Core
1.0 height x 2 wide
(1/8 hex cell x
0.0020 Thick) 5052
or 5056 Al alloy
foil, Non−perforated,
Core density 8.1 lb/
Cu. Ft. RMS026,
Type 1 Grade 2
V52331
Hexcel Corporation
11711 Dublin Blvd
Dublin, CA 94568−2832
Phone: (203) 696−0666
Fax: (203) 316−5139
www.hexcel.com
Hoses
3/8−inch (9.5 mm) Diameter
Nylon or Teflon Lined
Commercially Available
Hose, Vacuum
1/8−In. (3.2 mm) Diameter
Commercially Available
Knife, Utility
Commercially Available
Lamp, Heat
180° − 200°F
(82.2° − 93.3°C)
Commercially Available
Mask, Dust
Regulatory Agency
Approved
Commercially Available
Material, Ablative
MI−15 Type I
Lockheed Martin
Thermal Protection Products
P.O. Box 29304
New Orleans, LA 70189
Material, Ablative
MI−15 Topcoat
Lockheed Martin
Thermal Protection Products
Pad, Abrasive
Scotchbrite
V52152
Minnesota Mining and
Manufacturing Co.
Industrial Tape and
Specialties Division
3M Center
St. Paul, MN 55144−1000)
Paper, Abrasive
180−320−Grit
Silicone Carbide
Commercially Available
Paper
Kraft
Commercially Available
Page 6017
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
DESCRIPTION
DESIGNATION
MANUFACTURER
Pressure Pot
Binks, 15 gal
(56.8 L) with
dual regulator
V07334
ITW Industrial Finishing
DBA Binks Devilbiss
195 Internationale Blvd.
Glendale Heights, IL 60139
Primer, Epoxy
Green 10−P4−2 Base EC−117
Converter TR−19 thinner
V0KXA5
Akzo Nobel Aerospace
Coatings
East Water St.
Waukegan, IL 60085−5563
Phone: (847) 625−4200
Fax: (847) 625−3200
www.anac.com
Prime Coat, RTV
DOW CORNING®PR−1200
V5D028
Dow Corning Corporation
3901 South Saginaw Road
Midland, MI 48686
Phone: (989) 496−4400
www.dowcorning.com
Probe, Temperature
0° − 250°F
(−17.8° − 121°C)
Commercially Available
Pump, Vacuum
0−30 In.−of−Mercury
(0−101.6 kPa)
Commercially Available
Rubber, Sheet
0.062−0.125−Inch
(1.6−3.2 mm) Silicone
V85471
Boyd Corporation
13885 Ramona Avenue
Chino, CA 91710−5426
www.boydcorp.com
Scraper
Plastic
Commercially Available
Sealant
RTV 88/9910
V01139
Momentive Performance Materials
Inc. (704) 992−4107
187 Danbury Road
Wilton, CT 06897−4122
Page 6018
71−11−09
Printed in U.S.A.
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
DESCRIPTION
DESIGNATION
MANUFACTURER
Sealant, Bag
Tacky Tape
V53309 Schnee−Morehead
Chemicals, Inc.
111 North Nursery Road
P.O. Box 1305
Irving, TX 75060−3153
Sealant, Silicone Paste,
Gray
DC 93−006−6 (Two Part) Sealant
and Catalyst
V5D028
Dow Corning Corporation
Solvent
Isopropyl Alcohol 99 Percent Pure
or
Commercially Available
MIBK/MEK Blend (60% Methyl
Isobutyl Ketone/40% Methyl Ethyl
Ketone)
or
V5E821
Univar U.S.A., Inc.
532 E. Emaus Street
Middletown, PA 17057−2200
Phone: (717) 944−7471
www.univarusa.com
Turco 6646
V71410
Henkel Corporation
32100 Stephenson Hwy.
Madison Heights, MI 48071
Phone: (248) 583−9300
www.aerospace.henkel.com
Solvent
Heptane
Commercially Available
Spatula
Metal or Plastic
Commercially Available
Spray Bottle
Polyethylene
Commercially Available
Spray Gun
Binks Model 7 Nozzle, Fluid No. 36 V07334
Needle, Fluid No. 36SS Air Cap
ITW Industrial Finishing
No. 36SD
Tape, Masking
1 or 2−Inch Wide (25.4 or 50.8
mm)
Commercially Available
Tape, Teflon
1 or 2−Inch Wide (25.4 or 50.8
mm)
Commercially Available
Water
Distilled or Deionized
Commercially Available
Repair Materials and Equipment
Table 601
Page 6019
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
*/$)."9
&9*45*/(065&3
(3"1)*5&'"#3*$
%"."(&"3&"
"
"
'3".&$"1$65
0''-*/&
&9*45*/(
'3".&
$"1
'3".&$"1$65
0''-*/&
*//&3'3".&$"1
5"1&1-*&4
¡
065&3
#"33&4,*/
$03&
4*%&7*&8
4&$5*0/"¦"
.$$¦¦
FIGURE 601 FRAME DAMAGE CLEAN UP
Page 6020
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
*/$)
5:1
.0*4563&#"33*&3
#
#
*/$)
5:1
*/$)
5:1
*/$)
5:1
(3"1)*5&
3&1"*3
1-: 5017*&8
.0*4563&
#"33*&3
(3"1)*5&'*--&31-*&4
$03&3&1"*31-6(
"%)&4*7&
$03&
(3"1)*5&
3&1"*3
1-: *//&3#"33*&3
&9*45*/('3".&$"1
065&3#"33*&3
065&3#"33&-4,*/
4*%&7*&8
4&$5*0/#¦#
.$$¦¦
FIGURE 602 CORE PLUG
Page 6021
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
&95&/%*/$)
#&:0/%&/%0'3&1"*3
*/$)."91-$4
$*3$6.'&3&/5*"-
.0*4563&
#"33*&3
#0550.
$&/5&3-*/&
'*#&3(-"44#3&"5)&3$-05)
(3"1)*5&3&1"*31-:4
.0*4563&
#"33*&3
#-&&%&3$-05)
4*-*$0/&36##&34)&&5
7"$66.#"(
1030641"35*/(
'*-.
7"$66.)04&
#"(4&".$$¦¦
FIGURE 603 MOISTURE BARRIER
Page 6022
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
1030641"35*/('*-.
)&"5
#-"/,&5
.0*4563&
#"33*&3
#-&&%&3$-05)1-*&4
'*#&3(-"44'"#3*$
#3&"5)&31*-&4 /0/1030641"35*/('*-.
4*-*$0/&36##&34)&&5
7"$$6.#"(
7"$66.
$0//&$503
7"$66.
$0//&$503
5&.1&3"563&
130#&
.*/*.6.
#"(
4&"-
(3"1)*5&
'*--&31-:
)0/&:$0.#$03&
3&1"*31-6(
(3"1)*5&3&1"*3
1-*&4 .$$¦¦
FIGURE 604 HEAT BLANKET INSTALLATION
Page 6023
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
357'*--&54&""--"306/%
5:1
&/%0'(3"1)*5&
'"#3*$1-:
-":¦613&1"*3
"
"
1-:
(3"1)*5&'"#3*$
-":¦613&1"*3
5:1*$"-
.*¦"#-"5*7&
$0"5*/(
5:1
5:1
5:1
357'*--&54&""--"306/%
065&3#"33&-'3".&5:1
065&3#"33&-1"/&7*&8"¦"
&91"/%&%7*&8
.$$¦¦
FIGURE 605 ABLATIVE MATERIAL APPLICATION
Page 6024
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0/0/¦"650$-"7&065&3#"33&-'3".&4536$563&
1-"45*$4$3"1&3
.*¦
501$0"5
3&1"*3"#-"5*7&
$0"5*/( .*¦5:1&*
3574&"-"/5
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FIGURE 606 RTV SEALANT INSTALLATION
Page 6025
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
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TASK 71−11−09−300−806
1.
Repair No. 5
TASK 71−11−09−300−806
2.
General Information
A.
This repair assumes the outer barrel panel(s) has been removed.
B.
This repair applies to the insulation blanket bonded to the backskin of the inner barrel
assembly to be removed from the inlet cowl.
TASK 71−11−09−300−806
3.
Repair Instructions
A.
Remove Bonded Insulation Blanket (See Figure 601)
(1)
Install adequate fixture(s) to stabilize inner barrel.
CAUTION:
(2)
BE CAREFUL NOT TO DAMAGE COMPOSITE STRUCTURE WHEN
REMOVING INSULATION BLANKET.
Use a rounded edge spatula to loosen edges of insulation blanket from inner barrel
structure. Carefully remove insulation blanket from structure.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
CAUTION:
BE CAREFUL NOT TO OVERSOAK COMPOSITE SURFACE WITH
SOLVENT.
CAUTION:
DO NOT PULL OFF EXCESS BOND MATERIAL OR DAMAGE TO
STRUCTURE CAN OCCUR. BE CAREFUL NOT TO DAMAGE
COMPOSITE WHEN SCRAPING SURFACE OF STRUCTURE.
(3)
Apply the solvent to bond material residue and allow to soak for approximately 3
minutes. Use a rounded edge spatula or equivalent to carefully remove softened excess
bond material from barrel surfaces. Use a clean, lint−free cloth to dry surface
completely.
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(4) Remove the bond residue with a clean, lint−free cloth and the aviation solvent. Remove
the solvent with a clean lint−free cloth before the solvent becomes dry.
(5)
B.
Make sure that all bond residue is removed, surface is clean, and that there is no
damage to composite structure.
Inner Barrel Surface Preparation
(1)
Lightly abrade faying surface of the inner barrel backskin with 150 to 240−grit abrasive
paper. Do not damage graphite fibers when abrading composite material; remove
surface gloss only. Use a vacuum to remove debris.
WARNING:
(2)
C.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Clean faying and adjacent surfaces with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. Force air dry surface
for 30 minutes minimum at 150° − 180°F (65.6° − 82.2°C). (See Table 601)
NOTE:
DURING BONDING PROCESS WEAR CLEAN, LINT−FREE GLOVES
WHEN HANDLING CLEANED PARTS AND ADHESIVE MATERIAL.
NOTE:
APPLY THE PRIMER IN 12 HOURS AFTER THE SURFACE IS
PREPARED. IF MORE THAN 12 HOURS, REFER TO STEP B TO
CLEAN THE SURFACE AGAIN
Prime Faying Surfaces for Bonding
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GOODRICH AEROSTRUCTURES
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Document Part No. 277−1100
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3&1-"$&.&/5
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
CAUTION:
(1)
(2)
(3)
D.
TO PREVENT CONTAMINATION OF OTHER REPAIR FACILITIES BY
SILICONE MATERIALS, MAKE SURE THE REPAIR FACILITY FOR THIS
REPAIR IS ISOLATED. ANY REPAIR FACILITIES THAT APPLIES THE
MATERIALS USED IN THIS REPAIR AND/OR ANY RELATED SILICONE
MATERIALS MUST BE IDENTIFIED "RESERVED FOR SILICONE
APPLICATION ONLY".
Put a small quantity of the RTV prime coat into a polyethylene container.
NOTE:
VISUALLY EXAMINE THE PRIMER. SATISFACTORY RTV PRIME
COAT WILL BE CLEAR. UNSATISFACTORY PRIMER WILL BE
CLOUDY.
NOTE:
NEVER PUT RTV PRIME COAT BACK INTO ITS ORIGINAL
CONTAINER. DISCARD UNUSED PRIMER IN AN APPROVED
WASTE CONTAINER.
Apply a thin layer of RTV prime coat to the prepared surface with a clean, lint−free cloth.
Refer to the instructions of the manufacturer.
NOTE:
IF YOU USE RED RTV PRIME COAT, YOU CAN MAKE AN
ESTIMATE OF THE LAYER THICKNESS BY ITS COLOR: THE
THICKER THE PRIMER, THE DARKER THE RED COLOR. TOO
THICK A LAYER IS CHALKY. REMOVE TOO THICK PRIMER WITH
A CLEAN, LINT−FREE CLOTH.
NOTE:
IF YOU REMOVED PRIMER BECAUSE IT WAS TOO THICK, IT IS
POSSIBLE THAT YOU DO NOT NEED TO APPLY MORE PRIMER.
MAKE SURE THE ENTIRE SURFACE IS WET WITHOUT RUNS OR
PUDDLES. MAKE SURE THE PRIMER IS NOT CHALKY.
Dry the primer. Refer to the instructions of the manufacturer.
Silicone Sealant Faying Surface Application (See Figure 601 and 603)
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NOTE:
APPLY THE SEALANT IN 24 HOURS AFTER THE PRIMER HAS
DRIED. IF MORE THAN 24 HOURS, CLEAN THE SURFACE WITH
THE SOLVENT, DRY THE SURFACE WITH A CLEAN CLOTH, AND
APPLY THE PRIMER AGAIN.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(1)
Mix the silicone sealant paste. Refer to the instructions of the manufacturer.
(2)
Apply the silicone sealant paste to the faying surfaces within 24 hours of the RTV prime
coat application. Each faying surface shall have 0.010 − 0.015 in (0.25 − 0.38 mm) of
adhesive for a total bondline thickness of 0.020 − 0.030 in (0.51 − 0.76 mm). Apply the
silicone sealant paste with a serrated tool to control the application thickness. Squeeze
out is acceptable but not required.
(3)
NOTE:
THE LOCAL ABSENCE OF ADHESIVE, WHERE THE TEETH OF
THE SERRATED TOOL MAKE CONTACT WITH THE SURFACE, IS
ACCEPTABLE. THE AREA SHALL BE NO WIDER THAN THE
TOOTH, WHICH IS APPROXIMATELY 0.031 (0.78 MM) OF AN INCH
OR LESS.
NOTE:
DEMINERALIZED WATER, DEMINERALIZED ICE WATER OR A
SOLUTION OF ISOPROPYL ALCOHOL IN DEMINERALIZED WATER
CAN BE USED TO MAKE SURE THE TOOLS MOVE FREELY AND
TO MAKE THE EDGES OF THE SEALANT SMOOTH.
Bond insulation blanket to the inner barrel backskin surface within five to ten minutes
after the sealant application.
(a)
Put the insulation blanket on the inner barrel backskin surface, between the radials
located at 300°30’ and 350°30’. Make sure the aft edge of the insulation blanket is
4.4 inches (111.76 mm) from the aft edge of the inner barrel and 1.00 in. (25.4
mm) overlap at the edge of the closure.
(b)
Assemble items in such a manner to prevent air entrapment between the bonding
surfaces.
Page 6004
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GOODRICH AEROSTRUCTURES
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Document Part No. 277−1100
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(c) Use a roller to press the insulation blanket on the inner barrel and remove any air
trapped in the bondline.
CAUTION:
(4)
DO NOT LIFT OR DELAMINATE THE EDGES OF THE BONDED HEAT
SHIELD UNTIL FULL CURE IS ATTAINED.
Cure the repair area as follows:
Apply mechanical pressure and cure at 75° F +/− 15° F for a minimum of 24 hours
before the part is handled.
or
(a)
(5)
Use the vaccum bag process and cure the repair area at 110° F +/− 10° F for a
minimum of two hours before the part is handled. (Refer to the GE SPM 70−46−
03, Vaccum Bagging of Thermosetting Composite Repairs).
Dry the sealant prior to handling. Refer to the instructions of the manufacturer.
NOTE:
E.
RECOMMENDED RELATIVE HUMIDITY IS 50% OR GREATER
DURING THE CURE. RELATIVE HUMIDITY LESS THAN 50% WILL
REQUIRE LONGER CURE TIMES.
Prime Edge Seal Surfaces for Bonding (See Figure 602)
WARNING:
(1)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Put a small quantity of silicone primer into a polyethylene container.
NOTE:
VISUALLY EXAMINE THE PRIMER. SATISFACTORY RTV PRIME
COAT WILL BE CLEAR. UNSATISFACTORY PRIMER WILL BE
CLOUDY.
NOTE:
NEVER PUT RTV PRIME COAT BACK INTO ITS ORIGINAL
CONTAINER. DISCARD UNUSED PRIMER IN AN APPROVED
WASTE CONTAINER.
Page 6005
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Printed in U.S.A.
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0*/46-"5*0/#-"/,&5*//&3#"33&-"$0645*$1"/&-#"$,4,*/
3&1-"$&.&/5
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(2)
(3)
F.
Apply a thin layer of silicone primer to the prepared surface with a clean, lint−free cloth.
Refer to the instructions of the manufacturer.
NOTE:
IF YOU USE RED RTV PRIME COAT, YOU CAN MAKE AN
ESTIMATE OF THE LAYER THICKNESS BY ITS COLOR: THE
THICKER THE PRIMER, THE DARKER THE RED COLOR. TOO
THICK A LAYER IS CHALKY. REMOVE TOO THICK PRIMER WITH
A CLEAN, LINT−FREE CLOTH.
NOTE:
IF YOU REMOVED PRIMER BECAUSE IT WAS TOO THICK, IT IS
POSSIBLE THAT YOU DO NOT NEED TO APPLY MORE PRIMER.
MAKE SURE THE ENTIRE SURFACE IS WET WITHOUT RUNS OR
PUDDLES. MAKE SURE THE PRIMER IS NOT CHALKY.
Dry the primer. Refer to the instructions of the manufacturer.
Silicone Sealant Edge Seal Application (See Figure 603)
NOTE:
WARNING:
(1)
APPLY THE SEALANT IN 24 HOURS AFTER THE PRIMER HAS
DRIED. IF MORE THAN 24 HOURS, CLEAN THE SURFACE WITH
THE SOLVENT, DRY THE SURFACE WITH A CLEAN CLOTH, AND
APPLY THE PRIMER AGAIN.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Mix silicone sealant paste. Refer to the instructions of the manufacturer.
Page 6006
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Oct 01/2016
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COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
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(2) Fillet seal the edge of the insulation blanket.
(3)
Apply the silicone sealant paste to the faying surfaces. The silicone sealant paste shall
be applied to form a bead that is 0.125 − 0.375−inch (3.18 − 9.53 mm) wide. The
silicone sealant paste shall be 0.090 − 0.150−inch (2.29 − 3.81 mm) thick at the center
of the seam, feathered out to the edges from the center of the bead.
CAUTION:
DO NOT LIFT OR DELAMINATE THE EDGES OF THE BONDED HEAT
SHIELD UNTIL FULL CURE IS ATTAINED.
(4) Dry the silicone sealant paste. Refer to the instructions of the manufacturer.
TASK 71−11−09−300−806
4.
Material and Equipment
NOTE:
YOU CAN USE ALTERNATIVE MATERIALS WITH THE SAME PROPERTIES TO
REPLACE THE ITEMS SHOWN IN TABLE 601.
DESCRIPTION
DESIGNATION
MANUFACTURER
Clothing, Protective
Commercially Available
Containers, W/Covers
Polyethylene
Mixing Cups
Commercially Available
Gauge, Vacuum
0−30−In.−of−Mercury
(0−01.6 kPa)
Commercially Available
Gloves, Fabric
JOH Contamination Control
V8M556
Plasco Gloves Inc
1919 Commerce Rd
Springfield, OH 45501
Mask, Dus
Regulatory Agency Approved
Commercially Available
Paper, Abrasive
150−240 Grit Silicone Carbide
Commercially Available
Prime Coat, RTV
DOW CORNING®PR−1200
V5D028
Dow Corning Corporation
3901 South Saginaw Road
Midland, MI 48686
Phone: (989) 496−4400
www.dowcorning.com
Roller
Plastic or Rubber 2−In. (50,8
mm) Dia
Commercially Available
Scraper, Plastic
Serrated Edge
Commercially Available
Page 6007
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
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3&1-"$&.&/5
DESCRIPTION
DESIGNATION
MANUFACTURER
Sealant, Silicone Paste, Red
DC 90−006−2 Sealant and
Catalyst
V5D028
Dow Corning Corporation
Solvent, Aviation
SkyKleen 1000
V1CHP6
Solutia Inc.
Specialty Chemicals Division
575 Maryville Center Drive
St. Louis, MO 63166−6760
Phone: (314) 674−6661
Solvent
Isopropyl Alcohol 99 Percent
Pure
Commercially Available
MIBK/MEK Blend (60% Methyl
Isobutyl Ketone/40% Methyl
Ethyl Ketone
or
V5E821
Univar U.S.A., Inc.
532 E. Emaus Street
Middletown, PA 17057−2200
Phone: (717) 944−7471
www.univarusa.com
Turco 6646
V71410
Henkel Corporation
32100 Stephenson Hwy.
Madison Heights, MI 48071
Phone: (248) 583−9300
www.aerospace.henkel.com
Spatual
Rounded Edge
Commercially Available
Water
Demineralized
Commercially Available
Repair Materials and Equipment
Table 601
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Document Part No. 277−1100
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INLET STA
141.200
INLET STA
16.886
PANEL SPLIT
INLET RADIAL 355
INLET RADIAL
350 30’
INLET RADIAL 325 30’
NEW
INSULATION
BLANKET
A
A
B
B
INLET RADIAL 300 30’
CEC−102−00
INNER
BARREL
BACKSKIN
FIGURE 601 INSULATION BLANKET ON INNER BARREL BACKSKIN LOOKING INBOARD
Page 6009
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
REPAIR NO. 5 INSULATION BLANKET INNER BARREL ACOUSTIC PANEL BACKSKIN
REPLACEMENT
NEW INSULATION
INSTALLATION
EXISTING
PANEL CLOSURE
PLY LAY−UP
1.00 INCH
(25.4 mm)
OVERLAP
INNER
BARREL
PANEL
SILICONE
SEALANT FILLET
A−A
FWD EDGE
OF PANEL
AIR WETTED
SURFACE
NAC STA
141.200
4.40 INCH
(111.76 mm)
NEW INSULATION
INSTALLATION
SILICONE
SEALANT FILLET
AFT
PANEL
EDGE
AIR WETTED
SURFACE
CEC−103−00
INNER
BARREL
BACKSKIN
B−B
FIGURE 602 INSULATION BLANKET EDGE DETAILS
Page 6010
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Document Part No. 277−1100
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3&1-"$&.&/5
PLASTIC SCRAPER
NEW
INSULATION
BLANKET
SEALANT
45°
CEC−104−00
INNER BARREL
BACKSKIN
FIGURE 603 SILICONE SEALANT FILLET SEAL APPLICATION
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1-"$&4*/(-&-*14,*/4&(.&/5
TASK 71−11−09−300−807
1.
Repair No. 6
TASK 71−11−09−300−807
2.
General Information
A.
Do the repair by access through the Aft bulkhead access panels or by removal of the outer
barrel half.
B.
If the access through the Aft Bulkhead in not sufficient, remove the outer barrel panel(s).
TASK 71−11−09−300−807
3.
Repair instructions
A.
Remove the NAS1079D6 rivets with 0.185−inch (4.69 mm)(No. 13) diameter drill that attach
the damaged lip skin segment to the adjacent lip segments. (Ref. SRM 54−04−01)
B.
Remove the collars, bolts and pins that attach the damaged lip skin segment to the outer cap
angle of the forward bulkhead assembly.
C.
Remove the collars and pins that attach the damaged lip skin segment to the inner cap angle
of the forward bulkhead assembly.
D.
Remove the damaged lip skin segment from the inlet cowl assembly.
E.
Make a mark of the position of the shims and fillers for the installation of the new lip skin
segment.
F.
Remove the splice plates from the inlet cowl assembly.
G.
Trim The New Lip Skin Segment
H.
(1)
Put the new lip skin segment on the inlet cowl and attach with a clamp.
(2)
Make a mark for the trim lines on the new lip skin segment at the splice plates. make
sure there is a 0.030 to 0.120−inch (0.762 to 3.048 mm) gap at the two splice locations.
(3)
Remove the new lip skin segment and trim to marked lines.
Make Rivet Holes In New Lip Skin Segment (See Figure 601)
(1)
Cover the holes in the anti−ice spray tube with masking tape to prevent the entry of
metal chips and unwanted material into the tube.
(2)
Put the new splice plates on each side of the lip skin segments that remain on the inlet
cowl.
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Document Part No. 277−1100
3&1"*3/03&1-"$&4*/(-&-*14,*/4&(.&/5
(3)
Use the rivet holes in the lip skin segments as a template. Use a 0.189−inch (4.800 mm)
diameter (No. 12) drill to make the holes in the new splice plates for the NAS1097D6
rivets.
(4)
Install temporary fasteners to attach the new splice plates on the lip skin segments.
(5)
Layout the rivet holes in the new splice plates and lip skin segment to align with the rivet
holes made in paragraph ‘C’.
(6)
Use a 0.205−inch (5.22 mm) diameter (No. 5) drill to make the holes through the new lip
skin segment and splice plate for the CR3552−6−3 rivets. Install temporary fasteners.
NOTE:
TOTAL NUMBER OF RIVETS CAN CHANGE FROM SPLICE PLATE
TO SPLICE PLATE.
(7)
Use the fastener holes in the inner and outer cap angles of the forward bulkhead as a
template for the rivet holes in the new lip skin segment. Use a 0.166−inch (4.21 mm)
diameter (No. 19) drill to make the holes.
(8)
Countersink the rivet holes on the new lip skin segment where the lip skin attaches to
the inner cap angle for the HL633−5 pins. (Ref. SRM 54−04−09)
(9)
Countersink the rivet holes on the new lip skin segment where the lip skin attaches to
the outer cap angle for the HL41−5 pins. (Ref. SRM 54−04−09)
(10) Countersink the rivet holes on the new lip segment where the lip skin attaches to the
splice plates for rivets CR3552−6−3. (Ref. SRM 54−04−10)
(11) Remove the new lip skin segment and new splice plates, remove rough edges from
around the holes.
(12) Remove unwanted material from inner area of the inlet cowl lip.
Page 6002
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1-"$&4*/(-&-*14,*/4&(.&/5
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(13) Clean the new lip skin, splice plates and lip skin area with a clean lint−free cloth and
solvent. Remove the solvent with a clean lint−free cloth before the solvent becomes dry.
(See Table 601)
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(14) Apply chemical conversion coating to the cut edges of the new lip skin segment and all
the new rivet holes. Allow chemical conversion costing to dry. (Ref. SRM 54−02−03)
I.
Install the new splice plates and new lip skin segment on the inlet cowl. (See Figure 601)
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(1)
Mix the epoxy primer. Refer to the instructions of the manufacturer.
(2)
Put the new splice plates on the lip skin segments on the inlet cowl and attach with
NAS1097D6 rivets made moist with epoxy primer. (See Table 601)
(3)
Remove the masking tape from the anti−ice spray tube. (See Table 601)
Page 6003
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1-"$&4*/(-&-*14,*/4&(.&/5
CAUTION:
(4)
Put the new lip skin segment in position on the inlet cowl assembly and install temporary
fasteners.
WARNING:
J.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(5)
Install the CR3552−6−3 rivets made moist with the epoxy primer where the new lip skin
segment is attached at the splice plates. Remove the unwanted rivet stems. (See Table
601)
(6)
Install the pins and collars that attach the new lip skin segment to the inner cap angle of
the forward bulkhead assembly. (See Table 601)
(7)
Install the pins, bolts and collars that attach the new lip skin segment to the outer cap
angle of the forward bulkhead assembly. (See Table 601)
Close access
(1)
K.
DO NOT PRELOAD THE NEW LIP SKIN SEGMENT. NO MORE THAN TEN
(10) LBS OF FORCE MUST BE NECESSARY TO POSITION THE NEW LIP
SKIN SEGMENT AGAINST THE INLET COWL BARREL ASSEMBLY
WHEN ONE SIDE IS ATTACHED WITH A CLAMP.
Install the access panels on the aft bulkhead and the outer barrel panel(s) if the panel(s)
where removed.
Apply Aerodynamic Sealant to the Inlet Cowl Lip Skin Area
(1)
Remove the remaining sealant from the lip skin repair area.
(2)
Taper the ends of the sealant that stays for a minimum of 1.00−inch (2.54 mm) overlap
with new sealant.
(3)
abrade the ends of the sealant that stays to have a better bond with the new sealant.
Page 6004
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1-"$&4*/(-&-*14,*/4&(.&/5
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(4)
Remove the unwanted material with a clean lint−free cloth and solvent. Remove the
solvent with a clean lint−free cloth before the solvent becomes dry. (See Table 601)
(5)
Put masking tape on the two side of the gap where the sealant is applied. (See Table
601)
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(6)
Mix the sealant. Refer to the instructions of the manufacturer.
(7)
Put the sealant in the gap, push the sealant into the area and smooth with a spatula.
The sealant must flush to the surface or 0.010−inch (0.254 mm) below the surface.
NOTE:
DO NOT LET THE SEALANT TO BE ABOVE THE SURFACE.
(8) Dry the sealant. Refer to the instructions of the manufacturer. Remove masking tape.
TASK 71−11−09−300−807
4.
Material and Equipment
NOTE:
YOU CAN USE ALTERNATIVE MATERIALS WITH THE SAME PROPERTIES TO
REPLACE THE ITEMS SHOWN IN TABLE 601.
Page 6005
71−11−09
Printed in U.S.A.
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1-"$&4*/(-&-*14,*/4&(.&/5
DESCRIPTION
DESIGNATION
MANUFACTURER
Coating, Chemical
Conversion
Alodine 1000L
V71410
Henkel Corporation
32100 Stephenson Hwy.
Madison Heights, MI 48071
Phone: (248) 583−9300
www.aerospace.henkel.com
Cloth
Lint−Free, Cotton
Commercially Available
Gloves
Neoprene or Polyvinyl
Chloride
Commercially Available
Hi−Lok Pin Hi−Lok Collar
HL633−5−4, −5, −6
HL41−5−3, −4
V73197
Hi−Shear Corporation
2600 Skypark Dr
Torrance, CA 90505
Phone: (310) 326−8110
Primer, Epoxy
Yellow
10P20−13 Base
EC−213 Curing Solution
TR−144 or TR−49 Thinner
V0KXA5
Akzo Nobel Aerospace Coatings
Respirator
Regulatory Agency Approved
Commercially Available
Rivet, Blind Coutersink
CR3552−6−3
V05693
Cherry Textron Inc
1224 E. Warner St.
Santa Ana, CA 92705−5484
Phone: (714) 545−5511
www.cherryaerospace.com
Rivet, Solid Shank
NAS1097D6
Commercially Available
Solvent
Isopropyl Alcohol
99 Percent Pure
or
Commercially Available
MIBK/MEK Blend (60%
Methyl Isobutyl Ketone/
40% Methyl Ethyl Ketone)
or
V5E821
Univar U.S.A., Inc.
532 E. Emaus Street
Middletown, PA 17057−2200
Phone: (717) 944−7471
www.univarusa.com
Page 6006
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1-"$&4*/(-&-*14,*/4&(.&/5
DESCRIPTION
DESIGNATION
MANUFACTURER
Solvent
Turco 6646
V71410
Henkel Corporation
Tape, Masking
2−inch (50.8 mm) Wide
Commercially Available
Sealant, Silicone
DOW CORNING® 93−006−1/−
6
or DC93−006RF−1/−6 (ALT)
Grey
V5D028
Dow Corning Corporation
3901 South Saginaw Road
Midland, MI 48686
Phone: (989) 496−4400
www.dowcorning.com
Repair Materials and Equipment
Table 601
Page 6007
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/03&1-"$&4*/(-&-*14,*/4&(.&/5
FIGURE 601 REPLACE DAMAGED LIP SKIN SEGMENT
Page 6008
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&TASK 71−11−09−300−810
Repair No. 7
1.
Repair Instructions
A.
This repair provides instructions to remove and replace damaged inlet cowl acoustic panel
segments. Carefully dismantle and remove the inlet cowl (277−1100) from the aircraft at the
engine attach interface using proper ground handling equipment/tools (RSE1021 and
RSE1236) and appropriate ground transportation and restraints. Remove and keep the
2750308−30 bolt, 277−1011−501 spacer, VN936NP8 washer and NAS1805−8 nuts for
installation. Refer to A330 CF6−80E1 AMM and CMM 71−11−09 Disassembly section for
additional removal instructions. Refer to A330 CF6−80E1 SRM 54−10−00 Structural
Identification and A330 CF6−80E1 CMM 71−11−09 Illustrated Parts List for inlet cowl parts
identification. See Figures 901 and 902, Special Tools, Fixtures and Equipment.
NOTE:
B.
TO MAINTAIN CORRECT ALIGNMENT OF INLET COWL, THE INNER
BARREL, WHICH IS THE PRIMARY STRUCTURE, MUST BE REPLACED
ONE SEGMENT AT A TIME USING SUITABLE SHOP TOOLING AIDS AND
THE INLET COWL ATTACH RING/FAN CASE INTERFACE PLANE TOOL.
SEE FIGURE 610.
Prepare the inlet cowl assembly for inner barrel replacement. See Figure 601.
(1)
(2)
Use inlet cowl sling RSE1236 (See Figure 902, Special Tools, Fixtures and Equipment)
or equivalent tool to rotate the inlet cowl to the vertical position and place it facedown
with the inlet lip on a padded surface.
(a)
Disconnect chain to separate front and rear harnesses on the sling and use two
cranes to control rotation.
(b)
Position lead−shot bags or sandbags where the lip skin of the inlet cowl is to be
placed face−down.
(c)
The inlet cowl attach ring at the aft end should be in a horizontal position to
provide access to the interior surface area of the inner barrel.
Make a shop aid alignment tool and install it at the inlet cowl attach ring/fan case
interface plane.
(a)
Use suitable bolts, nuts and washers to match existing hole sizes in each of the
three attach ring segments.
(b)
Torque fasteners per SRM and Industry Standard requirements. See Figure 610.
Page 6001
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Printed in U.S.A.
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&CAUTION:
(3)
Check the perimeter of attach ring and shop aid tool interface for gaps. Use a 0.002 inch
(0,0508 mm) thick feeler gauge and record the size and location of gaps that exist.
CAUTION:
(4)
2.
TO PREVENT STRUCTURE MISALIGNMENT DURING REWORK, DO NOT
MOVE OR SHIFT THE INLET COWL UNTIL THE WORK IS COMPLETE.
TO PREVENT DISTORTION OF THE SHOP AID INTERFACE PLANE
TOOL AND PREVENT DAMAGE TO THE INLET COWL INTERFACING
STRUCTURE, DO NOT PLACE ANY LOAD ON THE TOOL.
Remove the shop aid tool from the inlet cowl assembly. Keep it for later use.
Replace the inlet cowl inner barrel lower acoustic panel assembly.
A.
Remove the lower outer barrel assembly (277−1130) to get access to inner barrel assembly.
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
CAUTION:
REMOVE THE SURFACE FINISH ONLY. DO NOT TAPER OR BREAK THE
GRAPHITE FIBERS FROM THE TOP SURFACE OF THE OUTER SKIN
PLY.
(1)
Remove the surface finish to expose the heads of rivets which attach the lower outer
barrel assembly to the forward bulkhead and to the splice plates at radials 90 and 270
degrees. Use 150−grit or finer silicon carbide abrasive paper. See Table 601.
NOTE:
SURFACE PRIMER TOP COAT IS GRAY, MIDDLE COAT IS BLACK,
AND FIRST COAT IS YELLOW.
NOTE:
REFER TO THE A330 CF6−80E1 SRM 54−04−01 FASTENER
REMOVAL AND INSTALLATION.
Page 6002
71−11−09
Printed in U.S.A.
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
CAUTION:
MAKE SURE NOT TO DAMAGE THE OUTER BARREL DURING THE
FASTENER SURFACE REMOVAL PROCESS.
CAUTION:
DO NOT ALLOW BLIND RIVETS TO SPIN IN COMPOSITE SKIN WHEN
YOU DRILL THEM OUT. REFER TO THE A330 CF6−80E1 SRM 54−04−01
FASTENER REMOVAL AND INSTALLATION.
(2)
Remove the anti−ice duct overboard discharge access panel to get access to the inside
of the outer barrel. Keep the attach hardware for installation. See Figure 606.
(3)
Drill out CR3522−5 rivets which attach the lower outer barrel assembly to the forward
bulkhead. Use a 0.1570−inch diameter No. 22 drill for the CR3522−5 blind rivets.
(4)
Drill out rivets which attach lower outer barrel assembly to the splice plate at radial 90
degree and at radial 270 degree. Use No. 22 drill for CR3522−5 blind rivets.
(5)
Drill out MS21141U05 blind rivets which attach aft bulkhead webs to lower outer frame
using No. 5/32−inch drill.
(6)
Drill out MS20427M5 blind rivets which attach left and right bulkhead stiffener splice
angles to upper outer barrel and to upper outer frame. Drill out MS20427M5 blind rivets
which attach splice angles to upper outer frame and to aft bulkhead web using No. 22
drill. See Figures 608 and 609.
(7)
Drill out MS20427M5 rivets which attach left and right frame splice plates to upper outer
frame using No. 22 drill.
Page 6003
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Printed in U.S.A.
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&(8)
NOTE:
COVER ANY OPENINGS IN FORWARD BULKHEAD OF THE INLET
COWL TO PREVENT ENTRANCE OF FOREIGN MATTER AND TO
MAKE THE INLET COWL VERMIN−PROOF.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
CAUTION:
BE CAREFUL NOT TO DAMAGE THE OUTER GRAPHITE
FABRIC/STRUCTURE WHEN YOU REMOVE THE SEALANT AND FILLER
MATERIAL.
(9)
B.
Remove the lower outer barrel segment (277−1130) from inlet cowl assembly. Leave
splice plates attached to outer barrel panel assembly, where practicable. Place lower
outer barrel segment with forward end down on a smooth flat surface and keep it for
installation.
Remove all sealant and filler material between inlet lip skin and outer barrel lower half.
Smooth the surface with 150−grit abrasive paper. Vacuum and remove remaining
sanding debris with a cloth moistened with solvent. Wipe dry before solvent evaporates.
Remove aft bulkhead lower sections. See Figure 607.
NOTE:
REFER TO THE A330 CF6−80E1 SRM 54−04−01, FASTENER REMOVAL
AND INSTALLATION.
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
(1)
Remove MS21141U05 blind rivets which attach lower web sections to lower inner frame
(Ref 277−1100). Use a No. 5/32−inch drill. See Figure 607.
(2)
Remove aft bulkhead lower web sections and keep them for installation.
Page 6004
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&(3)
C.
Remove all sharp edges and burrs from structure assembly after fastener removal in
accordance with A330 CF6−80E1 SRM 54−02−01 Damage Clean−up.
Remove the lower engine attach ring segment with brackets attached. Remove the HL930−6
Pins and HL585DU( )AW Collars that attach to the Aft Engine Attach Brackets to the Aft Ring.
Retain Lower Engine Attach Ring Segment and Aft Engine Attach Brackets for reinstallation.
(Ref 277−1123 and 277−1124). See Figures 603 and 604.
(1)
Remove collars and fastener pins which attach two lower attach ring splices to upper
and lower attach ring segments and to inner barrel acoustic panel Assemblies.
(2)
Remove splice angles which attach upper and lower attach ring segments. Remove
splice angles and aft ring segments and keep for installation.
NOTE:
(3)
D.
TAP THE SPLICES LIGHTLY TO RELEASE FROM CURED LIQUID
SHIM UNDER FILLERS.
Remove collars, fasteners pins, and rivets which attach lower segment of attach ring,
brackets and shims to inner barrel lower acoustic panel assembly. Remove attach ring
lower segment, attach ring brackets and shims as a unit. Tap brackets lightly to release
from cured liquid shim under fillers. Use 150−grit abrasive paper to remove gloss from
exposed surface of liquid shim and leave with a dull matte finish. Keep the attach ring,
brackets, and fillers for installation.
NOTE:
A FILLER MAY BE INSTALLED BETWEEN THE ATTACH RING AND
THE ACOUSTIC PANEL AFT LAND. KEEP THE FILLERS FOR
INSTALLATION WITH THE ATTACH RING OR REPLACE FILLERS.
NOTE:
MEASURE AND RECORD GAPS AROUND THE ENTIRE PANEL
BEFORE YOU REMOVE THE DAMAGED PANEL.
Remove the damaged inner barrel lower acoustic panel assembly (277−1121) from the inlet
cowl.
(1)
Remove collars, sleeves, pins, rivets, outer splices, shims and inner splices, which
attach inner barrel lower acoustic panel to inner barrel upper acoustic panels. Keep the
pins and sleeves for use for fit up of replacement panel or replace fasteners if damaged
during the fastener removal process.
(2)
Remove collars and pins which attach inner barrel lower acoustic panel to forward
bulkhead assembly. See Figure 605.
Page 6005
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&-
E.
(3)
Move the inner barrel lower acoustic panel aft and outboard to remove from inlet cowl.
Rotate right side of panel as required to clear upper right attach ring segment.
Determine if the damaged inner barrel is repairable. Keep the part for repair or scrap the
segment if it is not repairable.
(4)
Use 150−grit aluminum oxide abrasive paper and remove sealant and cured liquid shim
from faying surfaces of inner barrel upper acoustic panels, inner barrel outer splices,
inner splices, shims and angle splices for aft bulkhead inner frames. Keep the hardware
for installation.
Make a template of the damage area. Trim the replacement inner barrel lower acoustic panel
to fit the inlet cowl assembly. Record the fastener locations from the interfacing structure.
NOTE:
(1)
MEASURE THE AREA WHERE THE INNER BARREL LOWER ACOUSTIC
PANEL IS TO BE INSTALLED. USE A TRANSFER TEMPLATE AND
TRANSFER THE TRIM DIMENSIONS TO THE NEW INNER BARREL
SEGMENT AND TRIM TO FIT.
Put the replacement inner barrel lower acoustic panel between inner barrel upper panels
and temporarily secure in place using shop aids to ensure gaps are properly maintained.
Check aerodynamic smoothness steps and gaps in accordance A330 CF6−80E1 SRM
54−07−00 for compliance. Install aft bulkhead inner frame splice angles on panels with
pins and sleeves retained from removal procedure. Use temporary fasteners through
free legs of aft bulkhead inner frames on panels and splice angles. Clamp splice angles
to free leg of aft bulkhead lower inner frame on the lower acoustic panel.
NOTE:
THE FORWARD END OF THE REPLACEMENT PANEL WILL REST
INSIDE THE TRAILING EDGE OF THE INLET LIP UNTIL IT IS
TRIMMED FOR BUTT SPLICE ATTACHMENT TO THE FORWARD
BULKHEAD ANGLES.
(2)
Make sure the aft corners of the panel match the aft corners of the upper panels and do
not extend beyond the aft vertical surfaces of the upper attach ring segments See Figure
605.
(3)
Install the shop aid alignment tool on inlet cowl attach ring upper segments. Use two
NAS567−45 bolts, AN960C716 washers, and AN315−7R nuts in each segment of attach
ring. Torque NAS567−45 bolts to 270 to 300 lb−in (30,5 to 33,9 N.m). Use NAS566−45
bolts, AN960D616 washers, and AN315−6R nuts in remaining holes. Torque NAS566−
45 bolts 96 to 114 lb−in (10,8 to 12,9 N.m). See Figure 610.
Page 6006
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&CAUTION:
(4)
Hold the forward land of panel firmly against inner surface of the inlet lip. Make sure the
gap between aft corners of panel and face of shop aid tool interface plane is 00.060 to
0.120 inch (1,524 to 3,048 mm) and gap at center of panel is based on previous
measurements.
NOTE:
F.
MISMATCH ALIGNMENT AND GAP AT INNER BARREL FORWARD AND
AFT EDGES ARE CRITICAL FOR AERODYNAMIC SMOOTHNESS
REQUIREMENTS OF INLET COWL ASSEMBLY. REFER TO THE A330
CF6−80E1 SRM 54−07−00 FOR AERODYNAMIC SMOOTHNESS
REQUIREMENTS.
THE THICKNESS OF THE FORWARD LAND OF PANEL WHICH
EXTENDS OVER INLET LIP CAUSES THE CENTER OF THE AFT
EDGE OF THE PANEL TO BE MOVED 0.102 INCH (2,591 MM) FROM
THE INTERFACE PLANE WHEN THE AFT BULKHEAD INNER
FRAMES OF THE PANELS ARE ALIGNED AT THE SPLICE POINTS.
THE CENTER OF THE FORWARD EDGE OF PANEL IS ALSO
MOVED FORWARD.
(5)
Hold the forward land of panel firmly against the inner surface of the inlet lip. Mark a line
on the inlet lip at the forward edge of the panel. Mark reference lines at the center of the
panel and lip and at four equally spaced points between the center and corners of panel.
(6)
Remove the shop aid tool from the attach ring upper segments. Remove the splice
angles from the aft bulkhead inner frames and remove the replacement inner barrel
panel from the inlet cowl assembly.
(7)
Measure the distance the forward land extends over inlet lip at center mark and at each
reference point on each side out to corner.
(8)
Make a fairing strip straight edge from aluminum stock. Place the fairing strip on the
inner surface of the forward land of the replacement panel, align forward edge of strip
with measurements at corners, center and intermediate points and clamp to land. Mark
forward edge trim line for inner barrel along forward edge of fairing strip.
(9)
Remove the fairing strip and trim the inner barrel forward land to the trim line mark.
Smooth the edge of the land and break sharp corners.
Install the replacement inner barrel lower acoustic panel assembly (277−1120) to the inlet
cowl assembly (277−1100).
Page 6007
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&(1)
Put the replacement inner barrel lower panel centered between the upper panels. Install
the inner splices on the panels using the pins and collars which were removed from the
original installation. Install the aft bulkhead inner frame splice angles on the aft bulkhead
inner frames of panels using fasteners which were removed from the original installation.
Insert the fasteners through the panel, frames, and splice angles. Use temporary
fasteners through the splice angles and the free legs of the frames. See Figures 603,
604 and 605.
CAUTION:
LIMIT THE TORQUE OF HI−LOK COLLARS TO 19−23 IN−LBS FOR 5/32
INCH COLLARS AND 26−30 IN−LBS FOR 3/16 INCH COLLARS. IF HI−
LOK NUT DOES NOT SNAP OFF, CAREFULLY REMOVE THE NUT
PORTION OF THE COLLAR PER INDUSTRY STANDARD PRACTICES.
(2)
Install the shop aid alignment tool on the inlet cowl attach ring upper segments and
torque the bolts. See Figure 610.
(3)
Install the lower attach angle (and filler if used on original installation) on the shop aid
alignment tool. Use two NAS567−45 bolts, AN960C716 washers, and AN315−7R nuts.
Torque the NAS567−45 bolts 270 to 300 lb−in (30,5 to 33,9 N.m). Use NAS566−45
bolts, AN960D616 washers, and AN315−6R nuts in the remaining holes. Torque the
NAS566−45 bolts 90 to 114 lb−in (10,2 to 12,9 N.m).
NOTE:
REMOVE SCREWS, NUTS AND INDEX PIN (277−1125) FROM THE
LOWER ATTACH RING SEGMENT IF IT INTERFERES WITH
INSTALLATION OF THE ATTACH RING SEGMENT. KEEP THE
HARDWARE FOR INSTALLATION.
(4)
Hold forward land of panel firmly against forward bulkhead angles and aft land firmly
against lower attach ring. Make sure the gap between forward edge of panel forward
land and inlet lip is 0.060 to 0.120 inch (1,524 mm to 3.048 mm). Make sure the gap
between aft edge of aft land of panel and face of shop aid alignment tool is 0.010 to
0.070 inch (0,254 to 1,778 mm). Insert the “GO” pin of through ring of shop aid
alignment tool to get correct position of panel aft land and to hold land in contact with
attach ring segment. See Figure 610.
(5)
Install inner splices, outer splices and shims. Use pins and collars removed from original
installation through panels splices, and shims. Use temporary fasteners through outer
splices, aft bulkhead land, and attach ring segment Use temporary fasteners through
panels inner splices, outer splices, forward land, and forward bulkhead angles.
Page 6008
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
(6)
Use a 0.1890−inch (4,801 mm) diameter (No. 12) drill and back−drill Hi−Lok holes in
lower attach ring segment (and filler between attach ring and panel land if it existed on
original assembly) through aft land of panel. Work outboard from center of panel and
install temporary fasteners. Countersink inner skin of panel for rivets in accordance with
A330 CF6−80E1 SRM 54−04−09 and SRM 54−04−01.
(7)
Install attach ring splices on panels with temporary fasteners through the panels and
upper attach ring segments.
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
(8)
Use 0.1910−inch (4,851 mm) diameter (No. 11) drill and back−drill existing pin holes in
splices through panel. Install temporary fasteners.
(9)
Use a No.11 or 19 drill and back−drill existing pin holes in forward bulkhead angles
through forward land of panel. Install temporary fasteners in holes.
(10) Use a 0.1910−inch (4,851 mm) diameter (No. 11) drill and back−drill existing pin holes in
splices through outer skin of panel. Drill mating pin holes in splices through inner skin of
panel and core. Align holes through inner skin, outer skin, and core.
(11) Use a No. 16 drill and back−drill existing rivet holes in splices through outer skin only at
aft end of panel.
(12) Check for gaps between shims under attach brackets, attach ring splices and the outer
skin of panel. If gap exceeds 0.030 inch (0,762 mm), use additional laminated shims to
close gap. Peel fillers to the thickness required.
Page 6009
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&(13) Remove the shop aid alignment tool, lower attach ring, inner barrel lower panel, splices,
fillers, and angle splices. Deburr rivet and pin holes, and clean drill chips from structure.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(14) Treat exposed untreated reworked surfaces of panel with chemical conversion coating
and prime with epoxy primer. See Table 601.
G.
Install replacement inner barrel lower acoustic panel assembly.
(1)
Put the replacement panel between panels and install inner splices, outer splices, shims
and aft bulkhead lower inner frame angle splices. Use temporary pins, and collars which
were removed from original structure. Use other temporary fasteners through angle
splices and free legs of aft bulkhead inner frames on panels. Install temporary fasteners
through forward land of panel and forward bulkhead angles. Install temporary fasteners
through outer splices at forward ends of panels.
(2)
Install shop aid alignment tool and torque bolts. Install lower attach ring segment (and
filler between attach ring and panel land if it existed on original assembly) on the shop
aid alignment tool. Position attach ring splices and install temporary fasteners through
attach ring segments, splices, attach brackets, and aft land of panel.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(3)
Use epoxy primer and wet−install new pins through the forward land of the inner barrel
panel and forward bulkhead assembly. Install collars on the pins.
(4)
Use epoxy primer and wet−install new fasteners through panels, inner splices, outer
splices. Install pins and collars.
Page 6010
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&(5)
Install rivets through splices and outer skin of panels.
(6)
Remove the attach ring splices and lower attach ring segment from the panel and shop
aid alignment tool.
WARNING:
(7)
Clean mating surfaces of splices shims, lower attach ring segment attach brackets and
panels with solvent. Wipe dry before solvent evaporates. Brush or spray surfaces which
will contact liquid shim with polyvinyl alcohol to serve as a release agent. Apply polyvinyl
alcohol to all surfaces of bolts, washers, and nuts used to attach lower ring segment to
shop aid alignment tool. Apply masking tape to surfaces adjacent to liquid shim areas to
protect surfaces from excess liquid shim squeeze−out.
WARNING:
(8)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Mix one part−by−weight (pbw) of Part B epoxy adhesive catalyst with three pbw of Part
A epoxy adhesive base in a stainless steel container.
NOTE:
(9)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
THE USEFUL LIFE OF AN EIGHT−OUNCE MIX OF LIQUID SHIM IS
1.5 HOURS AT ROOM TEMPERATURE, 65°F TO 75°F (18,3°C TO
23,8°C).
Use a brush and apply liquid shim mix to the mating surfaces of the attach ring segment
panels, brackets, splices and shims and existing cured liquid shim surfaces.
Page 6011
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&(10) Put the attach ring segment on panel with shims in place under brackets and attach to
shop aid alignment tool with NAS567−45 and NAS566−45 bolts. Position splices on
panels and install temporary fasteners (clecos) through panels. Clamp splices to shop
aid alignment tool and legs of attach ring segments.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(11) Remove excess liquid shim with clean wipers dampened with solvent. Remove masking
tape. Cure liquid shim 24 hours at room temperature, 65°F to 75°F (18,3°C to23,8°C),
or two hours at 150°F to 200°F (65,5°C to 93,3°C).
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(12) Insert HL930 pins through panel, shims, and attach brackets and install HL585 collars.
Wet−install pins with epoxy primer. See Figures 603, 604, and paragraph 1.C.
(13) Insert pins through panels, and attach ring splices, and install collars. Wet−install the
pins with epoxy primer.
(14) Wet−install pins with epoxy primer rivets through aft land of panel and lower attach ring
segment.
(15) Remove shop aid alignment tool and install rivets through attach ring segments and
attach ring splices.
(16) Install index pin, bolts, and nuts on lower attach ring segment, if it was removed.
Page 6012
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(17) Mix 100 pbw of sealant base with 12 pbw of sealant catalyst in a stainless steel
container. See Table 601.
NOTE:
THE SEALANT MIXTURE IS USABLE FOR TWO HOURS AT ROOM
TEMPERATURE, 70°F TO 80°F (21,1°C TO 26,6°C).
(18) Scuff sand the epoxy primer on the outer skin of panels and outer splices along edges of
splices. Use 320−grit abrasive paper. Clean skins and splices with wiper moistened with
solvent. Wipe dry before solvent evaporates.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(19) Apply a filler of sealant mix along edges of outer splices and between joints of splices.
Cure the sealant for 24 hours at room temperature.
H.
Install the aft bulkhead lower panels to the inner frame on the inner barrel lower acoustic
panel. See Figure 607.
(1)
Install the lower outer barrel assembly on the inlet cowl with temporary fasteners
through the right splice plate, the left splice plate, forward bulkhead, and upper sections
of the aft bulkhead of the inner barrel assembly.
(2)
Install the lower sections of the aft bulkhead webs on the lower outer barrel with
temporary fasteners through the aft bulkhead outer frame (which was left installed on
the outer barrel).
(3)
Clamp the aft bulkhead webs to the leg of the aft bulkhead lower inner frame.
Page 6013
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&WARNING:
(4)
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
Drill the MS21141 blind fastener holes in the aft bulkhead webs through the leg of lower
inner frame of the panel using a 5/32−inch diameter drill.
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
(5)
Use a 0.194−inch (4,928 mm) diameter (No. 10) drill for the screw holes at the ends of
webs and at the starter duct bracket.
(6)
Remove the aft bulkhead webs from the inlet cowl assembly.
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
(7)
Drill attach rivet holes in the inner frame for nutplates using 0.098−inch (2,489 mm)
diameter (No. 40) drill.
(8)
Remove burrs from rivet and screw holes in the inner frame and install nutplates with
rivets. Remove all drill chips and other debris from inside of the inlet cowl inner and the
outer barrels. Remove protective covers from the forward bulkhead.
(9)
Position the aft bulkhead lower web sections and reinstall MS21141U05 blind rivets
through the webs and the aft bulkhead lower outer frame. Use the same production type
fasteners at intersection of radial stiffener angles.
Page 6014
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&NOTE:
INSTALLATION OF RIVETS BETWEEN THE LOWER ACCESS
DOORS AND THE UPPER ENDS OF LOWER OUTER FRAME MAY
BE DEFERRED IF THE UPPER LEFT AND/OR UPPER RIGHT INNER
BARREL PANELS WILL BE REPLACED.
(10) Install HL48−5 pins and HL86−5 collars through webs and aft bulkhead inner frame and
at intersection of radial stiffener angles.
I.
Complete the installation of the lower outer barrel.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(1)
Wet−install fasteners through the forward land of the lower outer barrel assembly and
inlet cowl forward bulkhead angles, using polyamide epoxy primer. See Table 601.
(2)
Wet−install rivets through the lower outer barrel assembly and splice plates, using
polyamide epoxy primer.
NOTE:
WARNING:
(3)
INSTALLATION OF RIVETS MAY BE DEFERRED IF THE UPPER
LEFT AND/OR UPPER RIGHT INNER BARREL PANELS WILL BE
REPLACED.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Wet−install CR3522−5 blind rivets through upper outer barrel, splice angles, and upper
outer frame. Install blind rivets through aft bulkhead upper and lower webs and aft
bulkhead upper and lower outer frames. See Figure 609.
Page 6015
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&-
3.
(4)
Install CR3522−5 blind rivets through aft bulkhead upper outer frame and outer frame
splice plates. See Figure 608.
(5)
Repair surface finish of inlet cowl outer barrel in accordance with instructions in A330
CF6−80E1 SRM 54−10−00, Repair No.1.
Replace the inlet cowl inner barrel upper left acoustic panel assembly.
A.
Remove the outer barrel upper assembly to get access to the upper left panel of the inner
barrel assembly.
CAUTION:
(1)
REMOVE SURFACE FINISH ONLY. DO NOT TAPER OR BREAK
GRAPHITE FIBERS FROM THE TOP SURFACE OF THE OUTER SKIN
PLY.
Remove surface finish to expose heads of rivets which attach the upper outer barrel
assembly to the inlet cowl forward bulkhead. Remove surface finish from rivets which
attach the splice plates to the lower outer barrel assembly at the 90 and 270 inlet cowl
radials. Use 150−grit or finer silicon carbide abrasive paper. See Table 601.
NOTE:
SURFACE PRIMER TOP COAT IS GRAY, THE MIDDLE COAT IS
BLACK, AND FIRST COAT IS YELLOW.
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
CAUTION:
DO NOT ALLOW BLIND RIVETS TO SPIN IN THE COMPOSITE SKIN
WHEN DRILLING OUT.
(2)
Drill out rivets which attach upper outer barrel assembly to inlet cowl forward bulkhead.
Use 0.1570−inch (3,988 mm) diameter (No. 22) drill for CR3522−5 blind rivets.
(3)
Drill out rivets which attach splice plates to lower outer barrel.
(4)
Drill out fasteners which attach aft bulkhead webs to aft bulkhead upper outer frame.
(5)
Remove HL48−5 pins and HL86−5 collars and MS21141U05 blind rivets which attach
aft bulkhead webs and stiffeners to aft bulkhead upper outer frame. See Figure 607.
Page 6016
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&WARNING:
(6)
B.
C.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Remove all filler material applies between inlet lip and outer barrel upper half and
between outer barrel upper and lower Halves. Smooth surface with 150−grit abrasive
paper. Remove sanding debris with a cloth wiper moistened with solvent. Wipe dry
before solvent evaporates.
Remove aft bulkhead upper left sections.
NOTE:
DISCONNECT THE ANTI−ICE DUCT (277−1150) ATTACHMENT AND
COMPONENT PARTS (AS REQUIRED) AT AFT BULKHEAD AND KEEP
THE HARDWARE FOR INSTALLATION.
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
(1)
Remove HL48−5 pins and HL86−5 collars which attach aft bulkhead upper left web
sections to aft bulkhead upper left inner frame. See Figure 607.
(2)
Remove HL48−5 pins and HL86−5 collars and MS21141U05 blind rivets which attach
stiffener angles to aft bulkhead webs and aft bulkhead upper left inner frame.
(3)
Remove aft bulkhead upper left web sections and Keep the for installation.
Remove attachment ring upper left segment with brackets attached.
(1)
Remove collars and pins which attach splices to upper and lower attach ring segments
and to inner barrel acoustic panel assemblies.
(2)
Remove rivets which attach upper and lower left attach ring splices to lower and upper
attach ring segments. Remove splices and keep them for installation.
Page 6017
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&NOTE:
(3)
Remove collars, pins, and rivets which attach upper left segment of attach ring, brackets
and shims to lower inner barrel acoustic panel assembly. Remove attach ring upper left
segment, brackets and shims as a unit and keep for installation. Tap brackets lightly to
release from cured liquid shim under fillers. Use 150−grit abrasive paper to remove
gloss from exposed surface of cured liquid shim and leave with a dull matte finish. Keep
the attach ring, brackets, and fillers for installation.
NOTE:
D.
E.
TAP THE SPLICES LIGHTLY TO RELEASE FROM CURED LIQUID
SHIM UNDER FILLERS.
A FILLER MAY BE INSTALLED BETWEEN THE ATTACH RING AND
THE ACOUSTIC PANEL AFT LAND. YOU MUST KEEP THE FILLER
FOR INSTALLATION WITH THE ATTACH RING.
Remove upper left acoustic panel assembly from inlet cowl inner barrel.
(1)
Remove collars, pins, rivets, outer splices, shims and inner splices which attach inner
barrel acoustic panel to inner barrel acoustic panels. Keep the pins and collars for use in
fitting replacement panel.
(2)
Remove collars and pins which attach inner barrel upper left acoustic panel to forward
bulkhead assembly.
(3)
Move the inner barrel panel aft as required to remove from inlet cowl inner barrel
assembly. Rotate lower side of panel to clear lower attach ring segment.
(4)
Use 150−grit aluminum oxide abrasive paper and remove sealant and cured liquid shim
from faying surfaces of inner barrel panels inner barrel outer splices, inner barrel inner
splices and shims. Keep the splices and shims for installation.
Trim the replacement inner barrel upper left acoustic panel to fit existing inlet cowl assembly.
(1)
Put the replacement inner barrel upper left panel between the inner barrel upper right
panel and the inner barrel lower panel.
NOTE:
(2)
THE FORWARD END OF THE REPLACEMENT PANEL REQUIRES
FINAL TRIM AND WILL REST INSIDE THE TRAILING EDGE OF THE
INLET LIP UNTIL IT IS TRIMMED FOR BUTT−SPLICE
ATTACHMENT TO THE FORWARD BULKHEAD ANGLES.
Make sure the aft corners of panel match aft corners of panels and do not extend
beyond aft vertical surfaces of upper right and lower attach ring segments.
Page 6018
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&(3)
Install the shop aid alignment tool on the inlet cowl attach ring upper right and lower
segments. Use two NAS567−45 bolts, AN960C716 washers, and AN315−7R nuts in
each segment of attach ring. Torque NAS567−45 bolts to 270 to 300 lb−in (30,5 to 33,9
N.m). Use NAS566−45 bolts, AN960D616 washers, and AN315−6R nuts in remaining
holes. Torque NAS566−45 bolts to 96 to 114 lb−in (10,8 to 12,9 N.m).
WARNING:
F.
MISMATCH ALIGNMENT AND GAP AT INNER BARREL FORWARD AND
AFT EDGES ARE CRITICAL FOR AERODYNAMIC SMOOTHNESS
REQUIREMENTS OF THE INLET COWL ASSEMBLY.
(4)
Hold the forward land of the panel firmly against the inner surface of the inlet lip. Make
sure the gap between the aft corners of the panel and face of the shop aid alignment
tool interface plane tool is 0.060 to 0.120 inch (1,524 to 3,048 mm) and gap at center of
panel is correct in accordance with previous measurement records.
(5)
Hold the forward land of the panel firmly against the inner surface of the inlet lip and
mark a line on the inlet lip at the forward edge of the panel. Mark reference lines at the
center of the panel and lip and at four equally spaced points between the center and
each corner of the panel.
(6)
Remove the shop aid alignment tool from the attach ring upper right and lower
segments. Remove the splice angles from the aft bulkhead inner frames and remove the
replacement inner barrel panel from the inlet cowl.
(7)
Measure the distance the inner barrel land extends over the inlet lip at the center mark
and at each reference point on each side out to the corner. Subtract 0.13 inch (3,3 mm)
from the center measurement and transfer to the center reference line on the inside of
forward land of the replacement inner barrel panel. Subtract 0.10 inch (0,254 mm) from
measurement at next reference line out from center on each side and transfer to inner
barrel forward land. Subtract 0.08 inch (2,032 mm), 0.05 inch (1,270 mm) and 0.025
inch (0,635 mm) progressively from measurements at remaining reference lines and
transfer to inner barrel forward land at appropriate location. At each corner measure and
transfer the dimensions to the inner barrel forward land as required.
(8)
Make a fairing strip straight−edge from aluminum stock. Place fairing strip on inner
surface of inner barrel forward land, align forward edge of strip with transferred
measurements at corners, center, and intermediate points and clamp to land. Mark the
forward edge trim line for the inner barrel along the forward edge of the fairing strip.
(9)
Remove fairing strip and trim inner barrel forward land to trim line mark. Smooth the
edge of the land and break sharp corners.
Fit the replacement inner barrel upper left acoustic panel assembly (277−1120) to the inlet
cowl assembly (277−1100).
Page 6019
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&(1)
Position the replacement inner barrel panel centered between the panels.
(2)
Remove fairing strip and trim inner barrel forward land to the trim line mark. Smooth the
edge of the land and break sharp corners.
(3)
Install shop aid alignment tool on inlet cowl attach ring upper segments and torque bolts.
(4)
Install upper left attach ring (and filler if used on original installation) on shop aid
alignment tool. Use two NAS567−45 bolts, AN960C716 washers, and AN315−7R nuts.
Torque NAS567−45 bolts to 270 to 300 lb−in (30,5 to 33,9 N.m). Use NAS566−45 bolts,
AN960D616 washers, and AN315−6R nuts in remaining holes. Torque NAS566−45
bolts to 96 to 114 lb−in (10,8 to 12,9 N.m).
(5)
Hold forward land of panel firmly against forward bulkhead angles and aft land firmly
against upper left attach ring. Make sure the gap between forward edge of panel forward
land and inlet lip is 0.060 to 0.120 inch (1,524 to 3,048 mm). Make sure the gap
between aft edge of aft land of panel) and face of shop aid alignment tool is 0.010 to
0.070 inch (0,254 to 1,778 mm). Insert the "GO" pin of shop aid alignment tool through
ring of tool to get the correct position of panel aft land, and to hold land in contact with
attach ring segment.
(6)
Install inner splices, outer splices, and shims. Use pins and collars (which were removed
from original installation) through panels , splices, and shims. Use temporary fasteners
through outer splices, aft bulkhead land, and attach ring segment. Use temporary
fasteners through panels inner splices, outer splices, forward land, and forward
bulkhead angles.
WARNING:
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
(7)
Use 0.1890−inch (4,801 mm) diameter (No. 12) drill and back−drill rivet holes in upper
left attach ring segment (and filler between attach ring and panel land if it existed on
original assembly) through aft land of panel. Work outboard from center of panel and
install temporary fasteners. Countersink inner skin of panel for rivets in accordance with
A330 CF6−80E1 SRM 54−04−09 and SRM 54−04−01.
(8)
Install attach ring splices on panels with temporary fasteners through panels, upper right
attach ring segment and lower attach ring segment.
Page 6020
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&WARNING:
(9)
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
Use 0.1910−inch (4,851 mm) diameter (No. 11) drill and back−drill existing pin holes in
splice through panel. Install temporary fasteners.
(10) Use No. 11 and 19 drill and back−drill existing pin holes in forward bulkhead angles
through forward land of panel. Install temporary fasteners in holes.
(11) Use 0.1910−inch (4,851 mm) diameter (No. 11) drill and back−drill existing pin holes in
splices through outer skin of panel. Drill mating pin holes in splices through inner skin of
panel and core. Align holes through inner skin, outer skin, and core.
(12)
Use a 5/32−inch drill and back−drill existing rivet holes through the outer skin only at
the aft end of the panel.
(13) Check for gaps between shims under attach brackets, attach ring splices, and the outer
skin of panel. If gap exceeds 0.030 inch (0,762 mm), use additional laminated shims to
close gap. Peel fillers to thickness required.
(14) Remove shop aid alignment tool, upper left attach ring, inner barrel lower panel, splices,
fillers, and angle splices. Deburr rivet and pin holes, and clean drill chips from structure.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(15) Treat exposed, untreated or reworked surfaces of the panel with chemical conversion
coating and prime with epoxy primer. See Table 601.
G.
Install replacement inner barrel upper left acoustic panel assembly.
Page 6021
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&(1)
Put the replacement panel between existing panels and install inner splices, and outer
splices, shims. Use temporary pins and collars which were removed from original
structure. Install temporary fasteners through forward land of panel and forward
bulkhead angles. Install temporary fasteners through outer splices at forward ends of
panels.
(2)
Install the shop aid alignment tool and torque bolts. Install upper left attach ring segment
and filler between attach ring and panel land if it existed on original assembly on shop
aid alignment tool. Position attach ring splices and install temporary fasteners through
attach ring segments, splices, attach brackets and aft land of the panel.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(3)
Use epoxy primer and wet−install new pins through forward land of inner barrel panel
and forward bulkhead assembly. Install collars on pins.
(4)
Use epoxy primer and wet−install new pins through panels, inner splices and outer
splices. Install pins and collars.
(5)
Install rivets through splices and outer skin of panels.
(6)
Remove attach ring splices, upper left attach ring segment, and filler if used on the
original installation from panel and shop aid alignment tool.
Page 6022
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&WARNING:
(7)
Clean mating surfaces of splices, shims , upper left attach ring segment, attach
brackets, and panels with solvent. Wipe dry before solvent evaporates. Brush or spray
surfaces which will contact liquid shim with polyvinyl alcohol to serve as a release agent.
Apply polyvinyl alcohol to all surfaces of bolts, washers, and nuts used to attach upper
left ring segment to the shop aid alignment tool. Apply masking tape to surfaces
adjacent to liquid shim areas to protect surfaces from excess liquid shim squeeze−out.
WARNING:
(8)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Mix in a stainless steel container one pbw of Part B epoxy adhesive catalyst with three
pbw of Part A epoxy adhesive base. Useful life of eight ounce mix of liquid shim is 1.5
hours at room temperature, 65°F to 75°F (18,3°C to 23,8°C). See Table 601.
WARNING:
(9)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Brush apply liquid shim mix to mating surfaces of attach ring, panels, brackets, splices,
shims and existing cured liquid shim surfaces.
Page 6023
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(10) Put the attach ring on panel with shims in place under brackets and attach to shop aid
alignment tool with NAS567−45 and NAS566−45 bolts. Position splices on panels and
install temporary fasteners through panels. clamp splices to shop aid alignment tool and
legs of attach rings.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(11) Remove excess liquid shim with clean wipers dampened with solvent. Remove masking
tape. Cure liquid shim 24 hours at room temperature, 65°F to 75°F (18,3°C to 23,8°C) or
two hours at 150°F to 200°F (65,5°C to 93,3°C).
(12) Insert pins through panel, shims, and attach brackets and install collars. Wet−install pins
with epoxy primer.
(13) Insert pins through panels, and attach ring splices, and install collars. Wet−install pins
with epoxy primer.
(14) Wet−install with epoxy primer rivets through aft land of panel and lower attach ring
segment.
(15) Remove the shop aid alignment tool and install rivets through attach rings and attach
ring splices.
Page 6024
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(16) Install index pin, bolts and nuts on attach ring if they were removed.
(17) Mix 100 pbw of sealant base with 12 pbw of sealant catalyst in a metal container. See
Table 601.
NOTE:
THE SEALANT MIXTURE IS USABLE FOR TWO HOURS AT ROOM
TEMPERATURE, 70°F TO 80°F (21,1°C TO 26,6°C).
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(18) Scuff−sand with 320−grit abrasive paper and epoxy primer on outer skin of panels and
outer splices along edges of splices. Clean skins and splices with wiper moistened with
solvent. Wipe dry before solvent evaporates.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(19) Apply a fillet of sealant mix along edges of outer splices and between joints of splices.
Cure sealant 24 hours at room temperature.
Page 6025
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&H.
Install aft bulkhead upper left panels to aft bulkhead inner frame on upper left inner barrel
panel. See Figure 607.
(1)
Install outer barrel upper assembly on inlet cowl with temporary fasteners through right
splice plate, left splice plate, forward bulkhead, and upper right section of aft bulkhead.
(2)
Install upper left sections of aft bulkhead webs on outer barrel upper assembly with
temporary fasteners through aft bulkhead outer frame (which was left installed on outer
barrel).
(3)
Clamp aft bulkhead webs to leg of aft bulkhead upper left inner frame.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(4)
Drill the MS21141U05 blind fastener holes in aft bulkhead webs through leg of upper left
inner frame, using 5/32−inch diameter drill.
(5)
Remove Aft Bulkhead Webs from Inlet Cowl Assembly.
(6)
Drill attach rivet holes in aft bulkhead inner frame for nutplates using 0.098−inch (2,489
mm) diameter (No. 40) drill. Debur rivet and screw holes in aft bulkhead inner frame and
install nutplates with rivets. Remove all drill chips and other debris from the inside of
inlet cowl and outer barrels. Remove protective covers from the forward bulkhead.
WARNING:
(7)
WEAR APPLICABLE PERSONAL PROTECTIVE EQUIPMENT (PPE)
WHEN YOU DO THIS TASK. BEFORE YOU USE PPE, READ,
UNDERSTAND AND OBEY ALL INSTRUCTIONS FOR ITS USE. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, YOUR EMPLOYER AND GOVERNMENT
REGULATIONS. YOU CAN GET INJURED IF YOU DO NOT USE PPE. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON WHICH PPE IS
NECESSARY.
Position aft bulkhead upper left web sections and install MS21141U05 blind fasteners
through the webs, aft bulkhead upper and lower outer frames. Use same production
type fasteners at intersections of radial stiffener angles.
Page 6026
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Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&(8)
I.
Install new HL48−5 pins and HL86−5 collars through webs and aft bulkhead inner frame
and at intersection of radial stiffener angles.
Complete the installation of upper outer barrel.
NOTE:
IF YOU ALSO WILL REPLACE THE INNER BARREL UPPER RIGHT
ACOUSTIC PANEL ASSEMBLY, YOU MAY WAIT TO DO THESE
PROCEDURES UNTIL AFTER YOU REPLACE THE UPPER RIGHT
ACOUSTIC PANEL ASSEMBLY.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(1)
Wet−install rivets through forward land of upper outer barrel assembly and inlet cowl
forward bulkhead angles, using polyamide epoxy primer. See Table 601.
(2)
Wet−install rivets through lower outer barrel assembly and splice plates using polyamide
epoxy primer.
(3)
Wet−install CR3522−5 blind rivets through upper outer barrel, splice angles, and aft
bulkhead upper outer frame. Install blind rivets through aft bulkhead upper and lower
webs and aft bulkhead upper and lower outer frames. See to Figure 609.
(4)
Install CR3522−5 blind rivets through aft bulkhead upper outer frame, and outer frame
splice plates. See Figure 608.
(5)
Repair the surface finish of inlet cowl outer barrel in accordance with instructions in the
A330 CF6−80E1 SRM 54−10−00, Repair No.1.
Page 6027
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&WARNING:
(6)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Apply aerodynamic silicone sealant to inlet cowl outer barrel.
WARNING:
(a)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY
ALL SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, THE MATERIAL SAFETY DATA SHEET (MSDS),
AND GOVERNMENT REGULATIONS. CHEMICALS MAY CAUSE
INJURY TO YOU OR MAKE YOU SICK WHEN SAFETY
INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR
EMPLOYER ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS.
Clean the surfaces in and around gaps between the upper and lower outer barrel
panels at the 90 degree and 270 degree radials and at the aft edge of the inlet lip
with a cloth moistened with solvent. Wipe the cleaned area dry before the solvent
evaporates.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY
ALL SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, THE MATERIAL SAFETY DATA SHEET (MSDS),
AND GOVERNMENT REGULATIONS. CHEMICALS MAY CAUSE
INJURY TO YOU OR MAKE YOU SICK WHEN SAFETY
INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR
EMPLOYER ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS.
(b)
Mask around gaps to protect surfaces from excess sealant.
(c)
Apply RTV prime coat to metal surfaces in gaps. See Table 601.
Page 6028
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&WARNING:
(d)
Mix one pbw of silicone sealant catalyst with ten pbw of silicone sealant base.
NOTE:
(e)
THE SEALANT MIX IS USABLE FOR TWO HOURS AT ROOM
TEMPERATURE.
Apply sealant mixture with plastic spatula to fill gaps around inlet lip and between
upper and lower outer barrel panels flush with air−wetted surfaces. Work trapped
air from sealant in gaps with spatula.
WARNING:
J.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY
ALL SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, THE MATERIAL SAFETY DATA SHEET (MSDS),
AND GOVERNMENT REGULATIONS. CHEMICALS MAY CAUSE
INJURY TO YOU OR MAKE YOU SICK WHEN SAFETY
INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR
EMPLOYER ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS.
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY
ALL SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, THE MATERIAL SAFETY DATA SHEET (MSDS),
AND GOVERNMENT REGULATIONS. CHEMICALS MAY CAUSE
INJURY TO YOU OR MAKE YOU SICK WHEN SAFETY
INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR
EMPLOYER ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS.
(f)
Remove masking tape and fair sealant head with spatula to form an
aerodynamically smooth surface. Clean excess sealant from adjacent surfaces
with cotton wiper moistened with solvent.
(g)
Cure the sealant for 48 hours at room temperature.
Replace the inlet cowl inner barrel upper right acoustic panel assembly.
(1)
Replace the inner barrel upper right acoustic panel assembly. Use the instructions given
in step 2.D.
Page 6029
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&K.
4.
Return the inlet cowl assembly to serviceable status or storage status, whichever existed prior
to inner barrel replacement.
(1)
Install hoist plates on inlet cowl upper outer barrel.
(2)
Attach the front sling to inlet cowl front hoist plates and rear sling to aft hoist plates. Use
the inlet cowl sling RSE1236. See Figure 902.
(3)
Lift inlet cowl from the lip−down position on the padded work surface and rotate to the
horizontal position.
(4)
Place inlet cowl on the RSE1021 inlet cowl dolly. See Figure 901
Materials and Equipment.
NOTE:
YOU CAN USE ALTERNATIVE EQUIPMENT AND MATERIALS WITH THE
SAME PRECISION TO REPLACE THE ITEMS SHOWN IN TABLE 601.
DESCRIPTION
DESIGNATION
MANUFACTURER
Agent, Wetting
Calsoft LAS 99
McKesson Chemical Corp
Agent, Wetting
Alternate
Surfactant Activol 1357
Harry Miller Corp
Aluminum Stock
Bare, 2024−T42 or −T3
0.025 in. (0.64 mm),
0.028 in. (0.71 mm),
0.036 in. (0.91 mm), and
0.050 in. 1.27 mm) Thick
Commercially Available
Bolt
NAS566−45
NAS567−45
2750308−30
Commercially Available
Coating, Chemical
Conversion
Alodine 1000L or equivalent
V71410
Henkel Corporation
32100 Stephenson Hwy.
Madison Heights, MI 48071
Phone: (248) 583−9300
www.aerospace.henkel.com
Cloth, Lint−Free
Cotton
Commercially Available
Container
Stainless Steel
Commercially Available
Page 6030
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&DESCRIPTION
DESIGNATION
MANUFACTURER
Dolly, Inlet Cowl Work
Stand
RSE1021
Rohr Industries
Drill
Size No.:
5/32 in.,
11,
12,
16
Commercially Available
Pin, Hi−Lok
HL48−5
Hi−Shear
Collar, Hi−Lok
HL86−5
Hi−Shear
Pin, Hi−Lok−HL930−6 and Collar, Hi−Lok
HL585DU( )AW
Nut
NAS1805−8
AN3156R
Commercially Available
Paper, Abrasive
Aluminum Oxide 150, 320−Grit
Commercially Available
Paper, Abrasive
150−Grit Silicon Carbide
Commercially Available
Prime Coat, RTV
DOW CORNING® PR−1200
V5D028
Dow Corning Corporation
3901 South Saginaw Road
Midland, MI 48686
Phone: (989) 496−4400
www.dowcorning.com
Primer, epoxy − Fluid
Resistant
Base 10P4−2 (Green)
Converter EC−117
Thinner TR−19
Retarder Thinner TR−20
V0KXA5
Akzo Nobel Aerospace Coatings
East Water St.
Waukegan, IL 60085−5563
Phone: (847) 625−4200
Fax: (847) 625−3200
www.anac.com
Primer, epoxy − Fluid
Resistant
Lead and Cadmium Free
Base 10P4−3
Converter EC−117
Thinner TR−19
Retarder Thinner TR−20
V0KXA5
Akzo Nobel Aerospace Coatings
Rivet
MS20426AD5−( )
MS20427M5
Commercially Available
Page 6031
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&DESCRIPTION
DESIGNATION
MANUFACTURER
Rivet, Blind
CR3522PR−5
CR3522−6
V05693
Cherry Textron Inc
1224 E. Warner St.
Santa Ana, CA 92705−5484
Phone: (714) 545−5511
www.cherryaerospace.com
Rivet, Blind
MS21141−5
Commercially Available
Sealant,
Silicone Paste,
Gray
DC 93−006−6 (Two Part)
Sealant and Catalyst
V5D028
Dow Corning Corporation
3901 South Saginaw Road
Midland, MI 48686
Phone: (989) 496−4400
www.dowcorning.com
Adhesive,
Epoxy Paste
EA934NA
V33564
Henkel Corporation
2850 Willow Pass Rd.
P.O. Box 312
Bay Point, CA 94565−0031
Phone: (925) 458−8000
www.aerospace.henkel.com
Shop Aid Alignment Tool,
Engine Attach Flange
Not Applicable
Develop locally
Sling, Inlet Cowl
RSE1236
Rohr Industries
Solvent
Isopropyl Alcohol 99 percent
pure
or
Commercially Available
MIBK/MEK Blend
(60% Methyl Isobutyl
Ketone/40% Methyl Ethyl
Ketone)
or
V5E821
Univar U.S.A., Inc.
532 E. Emaus Street
Middletown, PA 17057−2200
Phone: (717) 944−7471
www.univarusa.com
Turco 6646
V71410
Henkel Corporation
Spacer
277−1011−501
Commercially Available
Spatula
Plastic
Commercially Available
Page 6032
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&DESCRIPTION
DESIGNATION
MANUFACTURER
Tape
Masking
Commercially Available
Washer
AN960C10L
AN960C716
AN960D616
VN936NP8
Commercially Available
Repair Materials and Equipment
Table 601
Page 6033
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&-
INLET COWL
ASSY (277−1100)
OUTER BARREL
ASSY (277−1130)
AFT BULKHEAD
ASSY (277−1140)
FIGURE 609
CEC−120−00
INLET RADIAL 270
(90O RADIAL OPP.)
INNER BARREL
ASSY (277−1120)
FIGURE 604 AND
FIGURE 605
O
FIGURE 601 INLET COWL ASSEMBLY (277−1100)
Page 6034
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&AFT FRAME
(277−1122)
C
C
AFT ENGINE
ATTACH FITTING
(277−1123)
CEC−121−00
INNER BARREL
ACOUSTIC PANEL
(277−1120)
FIGURE 602 INLET COWL INNER BARREL ASSEMBLY AND ENGINE ATTACH BRACKETS (277−1120 AND 277−1123)
Page 6035
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&-
J
AFT ENGINE ATTACH
RING (277−1124)
INSULATION
BLANKET
INSULATION
BLANKET
(277D1101)
G
L
F
INNER BARREL
SPLICE TYPICAL
(3 PLACES)
(277−1120)
o
o
o
RDL114 , 236 , & 355
CEC−122−00
H
D
FIGURE 603 (SHEET 1) INLET COWL INNER BARREL CONFIGURATION (277−1120)
Page 6036
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&SPLICE STRAP
(277−1120)
SPLICE STRAP
(277−1120)
HL633−6 PIN
HL585DU6AW
COLLAR TYP
SPLICE STRAP
(277−1120)
H
ENGINE ATTACH
RING (277−1124)
AFT FRAME
(277−1122)
SPLICE STRAP
(277−1120)
HL633−6 PIN
HL585DU6AW
COLLAR TYP
SPLICE STRAP
(277−1120)
HL633−6 PIN
HL585DU6AW
COLLAR TYP
SPLICE STRAP
(277−1120)
AFT FRAME
(277−1122)
G
SPLICE STRAP
(277−1120)
M
HL633−6 PIN
HL585DU6AW
COLLAR TYP
SPLICE STRAP
(277−1124)
M
AFT FRAME
(277−1122)
ENGINE ATTACH
RING (277−1120)
BRACKET
(277−1123) TYP
F
HL633−6 PIN
HL585DU6AW
COLLAR TYP
SPLICE STRAP
(277−1120)
HL633−6 PIN
HL585DU6AW
COLLAR TYP
INLET COWL
(273−1100) TYP
CEC−123−00
ENGINE ATTACH
RING (277−1124)
FIGURE 603 (SHEET 2) INNER BARREL ASSEMBLY SPLICE DEFINITION (277−1120) (INLET RADIALS 114°, 236° AND 355°)
Page 6037
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&-
NAC STA
141.200
INLET COWEL ENGINE
ATTACH BRACKET
(277−1123 TYP)
HL930−6 PIN
HL585DU( )AW
TYP
MS20426 AD5
RIVET TYP
HL930−5 PIN
HL585DU5AW
ENGINE ATTACH
RING (277−1124)
CEC−124−00
AFT FRAME
(277−1122)
J
FIGURE 603 (SHEET 3) INNER BARREL ASSEMBLY
Page 6038
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&AFT ENGINE ATTACH
FITTING (277−1123)
HL41DU−6−( ) PIN
HL97DU ( ) AW COLLAR
SPLICE ANGLE
(277−1120)
HL930−6−( ) AW PIN
HL585 DU ( ) AW COLLAR
AFT ENGINE ATTACH
RING (277−1124)
AFT ENGINE ATTACH AT
RDL 15O AND 195 O
K
CEC−125−00
BRACKET TYPICAL
(277−1123)
FIGURE 604 LOWER INNER BARREL ASSEMBLY
Page 6039
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&INNER BARREL
SEGMENT
(277−1120)
INNER BARREL SPICE@
236 DEGREE RDL
HL633−( ) PIN WITH
HL585DU−( ) AW
COLLAR
LIP SKIN
ASSEMBLY
(277−1110)
HL930−( ) PIN WITH
HL585DU−( ) AW
COLLAR
L
2.19
OUTER SPLICE
STRAP (277−1120)
(1.272 CONST)
.180
.030
LL
2X
.130
.015
INNER BARREL
PANEL (277−1120)
CEC−126−00
INNER BARREL
STRAP (277−1120)
M
FIGURE 605 INNER BARREL SPLICE AT FORWARD BULKHEAD
Page 6040
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
CEC−127−00
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&-
FIGURE 606 INNER BARREL ASSEMBLY
Page 6041
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&-
MS21141
BLIND
FASTENER
HL48 PIN
HL86 COLLAR
MS21141
BLIND
FASTENER
M13701−02−2
UPPER INNER FRAME
NAS6303U4
NAS1149D0332
M13701−02−3
HL48 PIN
HL86 COLLAR
M13701−02−2
MS21141
BLIND
FASTENER
LOWER
OUTER
FRAME
CEC−128−00
277−1140
FIGURE 607 AFT BULKHEAD
Page 6042
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&-
277−1131
OUTER BARREL
277−1131
OUTER BARREL
MS20427M5
BLIND RIVETS
AFT FRAME
SPLICE STRAP
A
8X .74
1.02
.56
.050 + .030
A
3.12
277−1141 OUTER
AFT BHD FRAME
2X .45 + .03
FWD
SPLIT LINE
AFT FRAME
SPLICE STRAP
AFT OUTER
FRAME
LL
NAC STA 137.11
NAC STA
137.240
CEC−129−00
MS20427M5
BLIND RIVETS
VIEW A−A
FIGURE 608 AFT OUTER FRAME SPLICE STRAPS
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&AFT OUTER
FRAME
277−1110
LIP SKIN
1.98
60 EQ SPACES
STAGGERED
2.06
A
SPLICE
277−1130−501
A
1.21 .44 .77
CR3522−5
BLIND RIVETS
277−1130−505
OUTER BARREL
MS20427M5
RIVETS
VIEW LOOKING INBOARD
AFT FRAME
SPLICE STRAP
277−1130
277−1130−505
SPLICE
1.62
SPLICE
1.55
AFT
BULKHEAD
FORWARD
BULKHEAD
AFT
OUTER
FRAME
SECTION A−A
TYPICAL OUTER BARREL SPLICE
CEC−130−00
FWD
FIGURE 609 OUTER BARREL SPLICE TYPICAL
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
CEC−106−00
3&1"*3/0 o 3&1-"$&*/-&5$08-*//&3#"33&-
FIGURE 610 SHOP AID ALIGNMENT TOOL ENGINE ATTACH FLANGE
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
"44&.#-: */$-6%&44503"(&
TASK 71−11−09−500−801
1.
Assembly (Includes Storage)
A.
Assembly Materials and Equipment (See Table 701)
NOTE:
YOU CAN USE ALTERNATIVE EQUIPMENT WITH THE SAME PRECISION
TO REPLACE THE ITEMS SHOWN IN TABLE 701.
NOTE:
YOU CAN USE ALTERNATIVE MATERIALS WITH THE SAME
PROPERTIES TO REPLACE THE ITEMS SHOWN TABLE 701.
DESCRIPTION
DESIGNATION
MANUFACTURER
Anti−Seize, Copper Based
LOCTITE® C5−A®
V33564
Henkel Corporation
2850 Willow Pass Rd.
P.O. Box 312
Baypoint, CA 94565−0031
Phone: (800) 257−7522
www.aerospace.henkel.com
Cloth
Lint−free, Cotton
Commercially Available
Screwdriver
Standard
Commercially Available
Solvent
Isopropyl Alcohol 99 Percent
Pure
or
Commercially Available
MIBK/MEK Blend (60%
Methyl Isobutyl Ketone/40%
Methyl Ethyl Ketone)
or
V5E821
Univar U.S.A., Inc.
532 E. Emaus Street
Middletown, PA 17057−2200
Phone: (717) 944−7471
www.univarusa.com
Turco 6646
V71410
Henkel Corporation
32100 Stephenson Hwy.
Madison Heights, MI 48071
Phone: (248) 583−9300
www.aerospace.henkel.com
RSE 1243
Tool drawings provided by
Goodrich, upon request
Locally Manufactured
Wrench, Spanner
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
"44&.#-: */$-6%&44503"(&
Assembly Materials and Equipment
Table 701
B.
Assembly Procedures
WARNING:
(1)
THE INLET COWL WEIGHS APPROXIMATELY 552 LBS (250 KG). MAKE
SURE THE COWL IS ADEQUATELY SUPPORTED DURING
DISASSEMBLY TO AVOID INJURY TO PERSONNEL.
Lip Assembly (See IPL Figure 6)
WARNING:
(a)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY
ALL SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE
MANUFACTURER, THE MATERIAL SAFETY DATA SHEET (MSDS),
AND GOVERNMENT REGULATIONS. CHEMICALS MAY CAUSE
INJURY TO YOU OR MAKE YOU SICK WHEN SAFETY
INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR
EMPLOYER ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS.
Clean the threads of the bolts (40) with a clean lint−free cloth and the solvent.
Remove the solvent with a clean lint−free cloth before the solvent becomes dry.
WARNING:
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
(2)
Apply a small amount of anti−seize compound to threads of bolts (40). Remove excess
compound with a clean dry cotton cloth. Refer to the instructions of the manufacturer.
(3)
Install the nozzle assembly (60) with bolts (40) and washers (50).
(4)
Torque bolts (40) to 20−25 lb−in. (2.3−2.8 Nm).
(5)
Inner Barrel Assembly (See IPL Figure 5)
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"44&.#-: */$-6%&44503"(&
(6)
(7)
(a)
Install pins (30) with screws (10) and nuts (20).
(b)
Torque nuts (20) to 12−15 lb−in (1.4−1.7 Nm).
Lower Outer Barrel (See IPL Figure 4)
(a)
Install clips (70) with screws (50) and nuts (60).
(b)
Torque nuts (60) to 1.7−2.3 lb−in (0.2−0.3 Nm).
Pressure Relief Door Assembly (See IPL Figure 3)
(a)
Install hinge half (390) on splice (400) with spacer (310), pins (300) and collars
(330).
(b)
Install bracket (260) with pins (200) and collars (230).
(c)
Install lanyard (190) with bolt (160), nut (180) and washer (170).
(d)
Torque nut (180) to 12−15 lb−in. (1.4−1.7 Nm).
(e)
Install latch (250) with pins (210), nuts (240) and washers (220).
(f)
Torque nuts (240) to 12−15 lb−in. (1.4−1.7 Nm).
(g)
Install hinge half (370) with shims (130 and 140) and bolts (75).
(h)
Torque bolts (75) to 20−25 lb−in. (2.3−2.8 Nm).
(i)
Install bracket (120) with strip (110), pins (60) and collars (90).
(j)
Install door assembly (150) with pin (280), sleeves (−275), springs (−285), bolt
(70), nut (100) and washers (80).
NOTE:
(k)
(8)
Torque nut (100) to 12−15 lb−in. (1.4−1.7 Nm).
Peening of Hinges
(a)
(9)
INSTALL THE SPRINGS TO FORCE THE DOOR OPEN WHEN
UNLATCHED.
Peening of hinges (both extruded and formed) shall be sufficient to resist a push−
out force, applied to the hinge pin of 20 pounds.
Exhaust Duct Assembly (See IPL Figure 1)
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Document Part No. 277−1100
"44&.#-: */$-6%&44503"(&
(a)
Install duct assembly (400) with bolts (200 and 210), washers (250).
(b)
Torque bolts (200 and 210) to 20−25 lb−in. (2.3−2.8 Nm).
(10) Anti−ice Supply Tube Assembly (See IPL Figure 1)
(a)
(b)
(c)
Pre SB 30−001
1)
Install the nut (340), seal (350), back up seal (360), two face seals (370) and
face seal (380) on the tube assembly (390).
2)
Move the tube assembly (390), seal (350), back up seal (360), two face
seals (370) and face seal (380) into the swirl−tube coupling. Loosely engage
the nut (340) on the swirl−tube coupling.
3)
Attach the tube assembly (390) to the inlet cowl aft bulkhead with the screws
(180). Torque the screws (180) to 55 − 70 lb−in. (6.2 − 7.9 Nm).
4)
Tighten the nut (340) with the RSE 1243 wrench. Torque the nut (340) to
120 − 240 lb−in. (1.35 − 2.71 daNm). See Special Tools, Figure 903.
5)
Install the retainer (330) with washers (240) and bolts (230). Torque the bolts
(230) to 12 − 15 lb−in. (1.4 − 1.7 Nm).
Post SB 30−001 Pre SB 30−005
1)
Install the nut (340), packing seal (355) and face seal (385) on the tube
assembly (390).
2)
Move the tube assembly (390), packing seal (355) and face seal (385) into
the swirl−tube coupling. Loosely engage the nut (340) on the swirl−tube
coupling.
3)
Attach the tube assembly (390) to the inlet cowl aft bulkhead with the screws
(180). Torque the screws (180) to 55 − 70 lb−in. (6.2 − 7.9 Nm).
4)
Tighten the nut (340) with the RSE 1243 wrench. Torque the nut (340) to
360 − 480 lb−in. (4.1 − 5.4 daNm). See Special Tools, Figure 903.
5)
Install the retainer (330) with washers (240) and bolts (230). Torque the bolts
(230) to 12 − 15 lb−in. (1.4 − 1.7 Nm).
Post SB 30−005
1)
Install the nut (340) and the packing seal assembly (387) on the tube
assembly (390).
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
"44&.#-: */$-6%&44503"(&
2)
Move the tube assembly (390) and packing seal assembly (387) into the
swirl−tube coupling. Loosely engage the nut (340) on the swirl−tube
coupling.
3)
Attach the tube assembly (390) to the inlet cowl aft bulkhead with the screws
(180). Torque the screws (180) to 55 − 70 lb−in. (6.2 − 7.9 Nm).
4)
Tighten the nut (340) with the RSE 1243 wrench. Torque the nut (340) to
360 − 480 lb−in. (4.1 − 5.4 daNm). See Special Tools, Figure 903.
5)
Install the retainer (330) with washers (240) and bolts (230). Torque the bolts
(230) to 12 − 15 lb−in. (1.4 − 1.7 Nm).
(11) Upper Outer Barrel Access Panels (See IPL Figure 3)
(a)
Install access panel (50) with screws (30).
(b)
Torque screws (30) to 20−25 lb−in. (2.3−2.8 Nm).
(c)
Install access panel (40) with screws (30).
(d)
Torque screws (30) to 20−25 lb−in. (2.3−2.8 Nm).
(12) Electrical Installation (See IPL Figure 2)
(a)
Install jack end of wire harness assembly (10) with plate (50), retainer (40) and
screws (30).
(b)
Torque screws (30) to 7−9 lb−in. (0.8−1.0 Nm).
(c)
Install ground jack wire assembly (10) with connector (80), bolt (120), nuts (70,
170 and 180), washers (60, 130, 140 and 150).
(d)
Torque nuts (70, 170 and 180) to 20−25 lb−in. (2.3−2.8 Nm).
(e)
Install clamps (100) with bolts (90).
(f)
Torque bolts (90) to 20−25 lb−in. (2.3−2.8 Nm).
TASK 71−11−09−500−801
2.
Storage After Assembly
A.
Apply a layer of the protective coating to the inlet cowl lip skin. (SeeTable 702)
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
"44&.#-: */$-6%&44503"(&
NOTE:
YOU MUST REMOVE THE TEMPORARY PROTECTIVE COATING
BEFORE THE OPERATION OF THE AIRCRAFT ENGINE. REMOVE
THE PROTECTIVE COATING FROM THE COMPONENT SURFACE.
REFER TO THE INSTRUCTIONS OF THE MANUFACTURER.
(1)
Clean the inlet cowl lip skin. Make sure the lip skin is dry and free of dirt, chips, oil,
grease, or other unwanted materials. Refer to Cleaning Section.
(2)
Make a mask onall painted surfaces, inner barrel, and electrical connectors of the inlet
cowl.Use the masking tape and kraft paper.
WARNING:
(3)
BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND
DISCARD CHEMICALS. GET INSTRUCTIONS FROM YOUR EMPLOYER
ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS.
Apply the protective coating to the inlet cowl lip skin.Refer to the instructions of the
manufacturer.
B.
Put the covers on the open ends of the pneumatic ducts.
C.
Put the covers on the open ends of the electrical plugs. Use the polyethylene sheets and
adhesive tape.
D.
Put the unit in a clean, dry area.
CAUTION:
(1)
E.
DO NOT PUT TARPAULIN TYPE COVERS DIRECTLY ON THE INLET.
THE MOVEMENT OF THE COVER AGAINST THE ALUMINUM SURFACE
CAN CAUSE DAMAGE THROUGH THE OXIDE COATING OF THE
COMPONENT. THE MOISTURE FROM THE RAIN, OR CONDENSATION
FROM THE TEMPERATURE CHANGES BETWEEN THE COVER AND
INLET CAN CAUSE CORROSION ON THE ALUMINUM.
When the inlet is in an open area where the temperature changes, put the inlet in a
shipping container. Use tarpaulin covers on the shipping container.
Storage Materials. (See Table 702.)
NOTE:
YOU CAN USE ALTERNATIVE MATERIALS WITH THE SAME
PROPERTIES TO REPLACE THE ITEMS SHOWN TABLE 702.
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
"44&.#-: */$-6%&44503"(&
DESCRIPTION
DESIGNATION
MANUFACTURER/SUPPLIER
Coating, Protective
Spraylat
1074 B1 (basecoat)
SC 1090 (topcoat−white)
V87354
Spraylat Corporation
143 Sparks Ave
Pelham, NY 10803−1810
(914) 699−3030
www.spraylat.com
Cover, Tarpaulin
Cloth, Plastic, or Rubber
Commercially Available
Paper, Kraft
Commercially Available
Polyethylene Sheet
L−P−378, Type I
Commercially available
Tape, Adhesive
Cloth−backed PPP−T−60, Type IV
Class 1
Commercially available
Tape, Masking
Commercially available
Storage Materials
Table 702 dif
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
'*54"/%$-&"3"/$&4
TASK 71−11−09−220−801
1.
Fits and Clearances
A.
Torque Values (See Table 801)
NOTE:
FASTENERS TIGHTENED FROM THE HEAD END MUST BE TIGHTENED
TO THE HIGH VALUE OF THE TORQUE RANGE.
IPL FIGURE AND
ITEM NUMBER
ITEM
NOMENCLATURE
TORQUE VALUE
POUND−INCHES
TORQUE VALUE
NEWTON−METER
1−
180
Screw
50 − 70
5.7 − 7.9
−
190
Bolt
50 − 70
5.7 − 7.9
−
200
Bolt
20 − 25
2.3 − 2.8
−
210
Bolt
20 − 25
2.3 − 2.8
−
220
Bolt
20 − 25
2.3 − 2.8
−
230
Bolt
12 − 15
1.4 − 1.7
−
340
Nut
120 − 240
13.6 −27.1
2−
30
Screw
7−9
0.8 − 1.0
−
70
Nut
20 − 25
2.3 − 2.8
−
90
Bolt
20 − 25
2.3 − 2.8
−
110
Screw
7−9
0.8 − 1.0
−
120
Bolt
20 − 25
2.3 − 2.8
−
160
Nut
7−9
0.8 − 1.0
−
170
Nut
20 − 25
2.3 − 2.8
−
180
Nut
20 − 25
2.3 − 2.
3−
30
Screw
20 − 25
2.3 − 2.
−
70
Bolt
12 − 15
1.4 − 1.7
−
75
Bolt
20 − 25
2.3 − 2.8
−
100
Nut
12 − 15
1.4 − 1.7
−
160
Bolt
12 − 15
1.4 − 1.7
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
'*54"/%$-&"3"/$&4
IPL FIGURE AND
ITEM NUMBER
ITEM
NOMENCLATURE
TORQUE VALUE
POUND−INCHES
TORQUE VALUE
NEWTON−METER
−
180
Nut
12 − 15
1.4 − 1.7
−
240
Nut
12 − 15
1.4 − 1.7
4−
50
Screw
1.7 − 2.3
0.2 − 0.3
−
60
Nut
1.7 − 2.3
0.2 − 0.3
5−
10
Screw
12 − 15
1.4 − 1.7
−
20
Nut
12 − 15
1.4 − 1.7
6−
40
Bolt
20 − 2
2.3 − 2.8
Torque Values
Table 801
Page 8002
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
41&$*"-500-4 '*9563&4"/%&26*1.&/5
TASK 71−11−09−940−801
1.
Special Tools, Fixtures and Equipment
NOTE:
YOU CAN USE ALTERNATIVE EQUIPMENT WITH THE SAME PRECISION TO
REPLACE THE ITEMS SHOWN IN TABLE 901.
NOMENCLATURE
USAGE
Inlet Cowl Dolly,
RSE1021
To be used for storage, transport and as a work support fixture.
(See Figure 901)
Inlet Cowl Sling,
RSE1236
To be used for lifting and shop handling.
(See Figure 902)
Wrench, Spanner − Anti−Ice
Duct Seal Nut
RSE1243
To be used to torque the seal nut for the Anti−Ice Duct (See
Figure 903)
Special Tools, Fixtures and Equipment
Table 901
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
41&$*"-500-4 '*9563&4"/%&26*1.&/5
INLET COWL
CEC−012−00
DOLLY
FIGURE 901 INLET COWL DOLLY
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
41&$*"-500-4 '*9563&4"/%&26*1.&/5
SLING
INLET COWL
C2C−002−00
FIGURE 902 INLET COWL SLING
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
41&$*"-500-4 '*9563&4"/%&26*1.&/5
SEAL NUT
RSE1243
CEC−082−00
FIGURE 903 ANTI−ICE DUCT SEAL NUT SPANNER WRENCH
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
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Page 10001
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
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71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
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Page 10003
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
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Page 10004
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
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Page 10005
71−11−09
Printed in U.S.A.
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Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
Page 10006
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
NUMERICAL INDEX
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Page 10007
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
NUMERICAL INDEX
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Page 10008
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
NUMERICAL INDEX
PART NUMBER
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Page 10009
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
NUMERICAL INDEX
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Page 10010
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
NUMERICAL INDEX
PART NUMBER
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Page 10011
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
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Page 10012
71−11−09
Printed in U.S.A.
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
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Page 10013
71−11−09
Printed in U.S.A.
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
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Page 10014
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
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Page 10015
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Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
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Page 10016
71−11−09
Printed in U.S.A.
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
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220
255
220
255
220
255
500
220
255
220 220 220
255 255 255
U
120
320
220
255
220
255
135
220
255
520
510
220
255
490
120
320
120
320
120
310
120
310
315
220 220
255 255
220 220
255 255
220
255
CEM−185−00
INLET COWL ASSEMBLY FIGURE 1
IPL FIGURE 1 (SHEET 6 OF 11)
Page 10017
71−11−09
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
160
165
160 160
165 165
7111090107−00
150
152
INLET COWL ASSEMBLY FIGURE 1
IPL FIGURE 1 (SHEET 7 OF 11)
Page 10018
71−11−09
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
270
Y
387
150
385
380
355
AB
Z
370
150
160 170
160 150 170
150
360 350 340
AC
AB
270
280 270
270
270
280 270
AA
150
390
180
CEM−195−01
270
INLET COWL ASSEMBLY FIGURE 1
IPL FIGURE 1 (SHEET 8 OF 11)
Page 10019
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
AC
AD
230
240
330
200
250
410
430
400
460
420
210
295
315
317
120
210
295
315
317
470
CEC−084−00
210
315
317
INLET COWL ASSEMBLY FIGURE 1
IPL FIGURE 1 (SHEET 9 OF 11)
Page 10020
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
532
35 (24 LOCATIONS)
530
REF
UPR OUTER
BARREL ASSY
LWR OUTER
BARREL ASSY
REF
540
532
AE
AJ
CEC−085−01
542
INLET COWL ASSEMBLY FIGURE 1
IPL FIGURE 1 (SHEET 10 OF 11)
Page 10021
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
AJ
190
(4 PL)
AG
AK
AJ
AK
AG
AH
190
(4 PL)
AG
AK
AH
AK
AJ
AK
580
AK
REF UPPER
PANEL OUTER
AF
570
600
590
F
W
D
AK
AH
TYPICAL 6 PLACES
CEM−023−04
REF LOWER
PANEL OUTER
580
INLET COWL ASSEMBLY FIGURE 1
IPL FIGURE 1 (SHEET 11 OF 11)
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
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NUMBER
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UNITS
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Page 10023
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
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Page 10024
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
¦"
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UNITS
EFF PER
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Page 10025
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
AIRLINE
PART
NO.
NOMENCLATURE
1234567
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EFF PER
CODE ASSY
/"46
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8"4)&3
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#$
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3'
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− ITEM NOT ILLUSTRATED
Page 10026
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
AIRLINE
PART
NO.
NOMENCLATURE
1234567
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EFF PER
CODE ASSY
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Page 10027
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
AIRLINE
PART
NO.
NOMENCLATURE
1234567
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CODE ASSY
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Page 10028
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
AIRLINE
PART
NO.
NOMENCLATURE
1234567
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EFF PER
CODE ASSY
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Page 10029
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
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NO.
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UNITS
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Page 10030
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
Page 10031
71−11−09
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
B
A
90
A
100
(2 PLACES)
C
170
A
140
140
10
140
180
120
(BULKHEAD)
150
140
B
CEM−187−01
ELECTRICAL INSTALLATION FIGURE 2
IPL FIGURE 2 (SHEET 1 OF 2)
Page 10032
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
300
80
40
60
50
10
60
70
30
(4 PLACES)
30
(4 PLACES)
C
CEM−188−01
ELECTRICAL INSTALLATION FIGURE 2
IPL FIGURE 2 (SHEET 2 OF 2)
Page 10033
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
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71−11−09
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
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PART
NUMBER
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Page 10035
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
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NUMBER
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Page 10036
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
A
C
C
B
A
40
30
410
A
D
A
10
20
B
CEM−200−04
30
50
INLET COWL OUTER BARREL ASSEMBLY (UPR) FIGURE 3
IPL FIGURE 3 (SHEET 1 OF 2)
Page 10038
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
D
400
110
60
90
300
330
75
310
270
320
350
140
70
80
120
80
100
190
210
220
240
250
130
150
200
230
260
290
330
270
340
270
340
370
300
330
160
170
180
390
270
320
350
CEM−201−00
280
INLET COWL OUTER BARREL ASSEMBLY (UPR) FIGURE 3
IPL FIGURE 3 (SHEET 2 OF 2)
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GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
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UNITS
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Page 10041
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
AIRLINE
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NO.
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Page 10042
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
AIRLINE
PART
NO.
NOMENCLATURE
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UNITS
EFF PER
CODE ASSY
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Page 10043
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
C
360
C
B
A
A
A
C
E
D
A
A
120
B
110
B
80
100
C
60
70
10
130
30
20
CEM−202−02
50
110
INLET COWL OUTER BARREL ASSEMBLY (LWR) FIGURE 4
IPL FIGURE 4 (SHEET 1 OF 3)
Page 10044
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
140
150
150
210
160
170
210
210
230
190
180
260
(22 PLCS)
D
220
CONFIG 1
250
19 PLCS
200
270
D
240
CEM−246−00
CONFIG 2
D
CONFIG 3
INLET COWL OUTER BARREL ASSEMBLY (LWR) FIGURE 4
IPL FIGURE 4 (SHEET 2 OF 3)
Page 10045
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
310
330
350
350
340
320
REF
E
290
300
300
CEM−247−00
280
INLET COWL OUTER BARREL ASSEMBLY (LWR) FIGURE 4
IPL FIGURE 4 (SHEET 3 OF 3)
Page 10046
71−11−09
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
¦
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"$#¦
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AIRLINE
PART
NO.
NOMENCLATURE
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UNITS
EFF PER
CODE ASSY
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-83 '*(63&
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Page 10047
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
AIRLINE
PART
NO.
NOMENCLATURE
1234567
UNITS
EFF PER
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Page 10048
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
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NO.
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Page 10049
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
AIRLINE
PART
NO.
NOMENCLATURE
1234567
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CODE ASSY
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Page 10050
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
Page 10051
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
A
A
A
A
A
A
A
A
A
G
A
A
D
A
A
E
A
A
A
A
F
150
A
D
A
A
A
140
B
B
C
C
A
F
E
A
D
C
A
C
A
C
A TO C
C
170
B
C
180
200
B
170
190
200
160
180
200
A 210
B 220
C 230
CEM−203−04
180
200
240
250
INLET COWL INNER BARREL ASSEMBLY FIGURE 5
IPL FIGURE 5 (SHEET 1 OF 5)
Page 10052
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
D
70
90
60
90
70
90
110
20
30
F
E
10
50
106
108
90
CEM−204−01
40
80
INLET COWL INNER BARREL ASSEMBLY FIGURE 5
IPL FIGURE 5 (SHEET 2 OF 5)
Page 10053
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
G
ENGINE ATTACH
RING (277−1124)
INSULATION
BLANKET
INSULATION
BLANKET
(277D1101)
F
E
INNER BARREL
SPLICE TYPICAL
(3 PLACES)
(277−1120)
o
o
o
RDL114 , 236 , & 355
CEM−252−01
K
A
INLET COWL INNER BARREL ASSEMBLY FIGURE 5
IPL FIGURE 5 (SHEET 3 OF 5)
Page 10054
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Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
94
92
H
60
90
104
102
110
(REF)
J
60
90
96
98
110
(REF)
K
60
90
CEC−101−00
110
(REF)
INLET COWL INNER BARREL ASSEMBLY FIGURE 5
IPL FIGURE 5 (SHEET 4 OF 5)
Page 10055
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
NAC STA
141.200
L
CEC−100−00
42
44
82
84
INLET COWL INNER BARREL ASSEMBLY FIGURE 5
IPL FIGURE 5 (SHEET 5 OF 5)
Page 10056
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Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
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NUMBER
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UNITS
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Page 10057
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
AIRLINE
PART
NO.
NOMENCLATURE
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UNITS
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Page 10058
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
PART
NUMBER
AIRLINE
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Page 10059
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
H
180
80
190
H
A B
220
F
E
210
C
200
A TO E
D
DETAILS
100 A, B,C, E
120 D
DETAILS
130 A
140 B
150 C
160 D
170 E
CEM−205−02
90
INLET COWL LIP ASSEMBLY FIGURE 6
IPL FIGURE 6 (SHEET 1 OF 2)
Page 10060
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
10
240
260
(4 LOCATIONS)
G
20
40
50
20
60
70
10
30
250
(7 LOCATIONS)
F
270
H
280
(2 LOCATIONS)
G
280
(2 LOCATIONS)
CEM−206−03
270
260
(14 LOCATIONS)
INLET COWL LIP ASSEMBLY FIGURE 6
IPL FIGURE 6 (SHEET 2 OF 2)
Page 10061
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Oct 01/2016
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
Page 10062
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
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Page 10063
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
*--6453"5&%1"354-*45
FIG.&
ITEM
NO.
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Page 10064
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019
GOODRICH AEROSTRUCTURES
COMPONENT MAINTENANCE MANUAL
Document Part No. 277−1100
THIS PAGE INTENTIONALLY LEFT BLANK
Page 10065
71−11−09
Printed in U.S.A.
Rohr, Inc., operating as Goodrich Aerostructures. U.S. Export Classification: EAR 9E991
Goodrich Proprietary − This document is subject to the controls and restrictions on the title page.
Apr 15/2019