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Commercial Airplanes 767 Requirements Bulletin ALERT Number: 767-53A0278 RB Original Issue: June 30, 2017 ATA System: 5350 SUBJECT: FUSELAGE - Section 45 - Overwing Hatch Door Surround Structure - Edge Frame Inner Chord Inspection Above Stub Beam Fitting Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET Copyright © 2017 Boeing.
Unpublished Work. All Rights Reserved.
Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.
Original Issue: June 30, 2017 767-53A0278 RB 1 of 48
2.0
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 30, 2017 767-53A0278 RB 2 of 48 REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT
BLANK PAGE
Table of Contents
1 . E F F E C T I V I T Y5
A. Airplanes5
B . S p a r e s A f f e c t e d6
2. CONCURRENT REQUIREMENTS6
3 . C O M P L I A N C E6
4. APPROVAL ................................................ 1 2
5. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 3 A. General Information ......................................... 1 3 B. Work Instructions ........................................... 1 4 FIGURE 1: LEFT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION [Group 1] . 19 FIGURE 2: LEFT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION [Group 2 ] ................................................ 2 4 FIGURE 3: RIGHT SIDE - STA 859.5 AND 883.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION [Group 1] . 30 FIGURE 4: RIGHT SIDE - STA 859.5, 883.5 AND 903.5 - AREA FROM FRAME WEB TO STUB BEAM FITTING AND ABOVE THE FRAME TO STUB BEAM JOINT - DETAILED INSPECTION [Group 2 ] ................................................ 3 5 FIGURE 5: LEFT SIDE - AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB FILLER - FRAME INNER CHORD - SURFACE HFEC INSPECTION ............ 4 1 FIGURE 6: RIGHT SIDE - AREA FROM FRAME WEB TO STUB BEAM FITTING COMMON TO A MRB FILLER - FRAME INNER CHORD - SURFACE HFEC INSPECTION ............ 4 5 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 30, 2017 767-53A0278 RB 3 of 48 REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 30, 2017 767-53A0278 RB 4 of 48 REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT
BLANK PAGE
Commercial Airplanes 767 Requirements Bulletin ALERT Number: 767-53A0278 RB Original Issue: June 30, 2017 ATA System: 5350 SUBJECT: FUSELAGE - Section 45 - Overwing Hatch Door Surround Structure - Edge Frame Inner Chord Inspection Above Stub Beam Fitting
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. THIS IS AN ENHANCED REQUIRED FOR COMPLIANCE DOCUMENT. THE BOEING
PROCESSES USED TO CREATE THE SERVICE BULLETIN (SB) AND THE REQUIREMENTS BULLETIN (RB) ENSURE THAT THE INFORMATION BETWEEN "RC START" AND "RC END" IN THE SB ARE IDENTICAL TO THE INFORMATION IN THE SAME SECTIONS (COMPLIANCE, WORK INSTRUCTIONS…) OF THE RB WHICH THE SB REFERS TO AS THE RELATED DOCUMENT.
1. EFFECTIVITY A. Airplanes Service Bulletin 767-53A0278 and Requirements Bulletin 767-53A0278 RB are applicable to 767-200 and 767-300 Airplanes, line numbers 1-120, 272, 569, 602, 617-618, 642, 668, 834, 843, and 882, in 2 Groups.
DESCRIPTIONCONFIGURATIONGROUP 767-200 and 767-300 airplanes, line numbers 1-70, 72-78, 80, 82-100, 102-106, 108-112, 114-120, 272, 569, 618 and 642 delivered with one Type III overwing exit door.
-1 767-200 and 767-300 airplanes.1 767-200 airplane changed to the 767-200SF (Special Freighter) configuration and 767-300 airplane changed to the 767-300BCF (Boeing Converted Freighter) configuration.
2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 30, 2017 767-53A0278 RB 5 of 48
DESCRIPTIONCONFIGURATIONGROUP 767-200 and 767-300 airplanes, line numbers 71, 79, 81, 101, 107, 113, 602, 617, 668, 834, 843 and 882 delivered with two Type III overwing exit door.
-2 767-200 and 767-300 airplanes.1 767-300 airplanes changed to the 767-300BCF (Boeing Converted Freighter) configuration.
2 B. Spares Affected None.
2. CONCURRENT REQUIREMENTS None.
3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Requirements Bulletin 767-53A0278 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 767-53A0278 RB mandatory.
Accomplish the required actions, based on the applicable conditions in Tables 1 through 4, in accordance with the Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION numbers for that CONDITION number or OPTION number.
Logic diagrams showing compliance tasks and compliance times are included as an aid in APPENDIX A, APPENDIX B, APPENDIX C and APPENDIX D of Service Bulletin 767-53A0278.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 30, 2017 767-53A0278 RB 6 of 48 REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT
Group 1, Configuration 1:
Table 1: Station (STA) 859.5 and 883.5 - Detailed Inspection for any Material Review Board (MRB) filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner chord Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 24 months or 3,000 flight cycles after the original issue date of Requirements Bulletin 767- 53A0278 RB, whichever occurs first.
Before 37,500 total flight cycles.
Do a detailed inspection for any MRB filler installed in the area from the frame web to the stub beam fitting on the left and right side at STA
859.5 and 883.5. (a) All Airplanes.
--No further action required at this frame location.
CONDITION 1: NO MRB
FILLER INSTALLED OR
MRB FILLER INSTALLED
DOES NOT EXTEND
ABOVE THE FRAME TO STUB BEAM JOINT.
-Before further flight.Do a surface HFEC inspection around the end fastener common to each MRB filler for any crack in the frame inner chord.
(b) CONDITION 2: MRB
FILLER INSTALLED AND
EXTENDS ABOVE THE
FRAME TO STUB BEAM JOINT.
-Before further flight.ACTION 1: Contact The Boeing Company for repair instructions and do the repair.
CONDITION 3: ANY CRACK FOUND.
6,000 flight cycles.-ACTION 2: Repeat the surface HFEC inspection around the end fastener for any crack in the frame inner chord, at each unrepaired frame location common to a MRB filler.
(b) 6,000 flight cycles.-Repeat the surface HFEC inspection around the end fastener for any crack in the frame inner chord, at each frame location common to a MRB filler. (b) CONDITION 4: NO CRACK FOUND.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 30, 2017 767-53A0278 RB 7 of 48 REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT
Group 1, Configuration 1:
Table 1: Station (STA) 859.5 and 883.5 - Detailed Inspection for any Material Review Board (MRB) filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner chord Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition
(a) A structural MRB filler is installed during production integration in addition to a laminated shim when the gap between the frame web and the stub beam support fitting could not be filled to within 0.005 inches by the shim installation.
(b) It is not necessary to do the surface HFEC inspection in accordance with Requirements Bulletin 767- 53A0278 RB in areas where existing repairs approved by the Boeing Organization Designation Authorization (ODA) via FAA form 8100-9 or installed in accordance with Boeing Service Bulletin 767-53A0209 covers the affected inspection area. Damage Tolerance Inspections specified in the approval for existing repairs must continue. Inspection outside each repaired region must continue as instructed in accordance with Requirements Bulletin 767-53A0278 RB.
Group 1, Configuration 2:
Table 2: Station (STA) 859.5 and 883.5 - Detailed Inspection for any Material Review Board (MRB) filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner chord Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 24 months or 3,000 flight cycles after the original issue date of Requirements Bulletin 767- 53A0278 RB, whichever occurs first.
Before 30,000 total flight cycles.
Do a detailed inspection for any MRB filler installed in the area from the frame web to the stub beam fitting on the left and right side at STA
859.5 and 883.5. (a) All Airplanes.
--No further action required at this frame location.
CONDITION 1: NO MRB
FILLER INSTALLED OR
MRB FILLER INSTALLED
DOES NOT EXTEND
ABOVE THE FRAME TO STUB BEAM JOINT.
-Before further flight.Do a surface HFEC inspection around the end fastener common to each MRB filler for any crack in the frame inner chord.
(b) CONDITION 2: MRB
FILLER INSTALLED AND
EXTENDS ABOVE THE
FRAME TO STUB BEAM JOINT.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 30, 2017 767-53A0278 RB 8 of 48 REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT
Group 1, Configuration 2:
Table 2: Station (STA) 859.5 and 883.5 - Detailed Inspection for any Material Review Board (MRB) filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner chord Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.ACTION 1: Contact The Boeing Company for repair instructions and do the repair.
CONDITION 3: ANY CRACK FOUND.
6,000 flight cycles.-ACTION 2: Repeat the surface HFEC inspection around the end fastener for any crack in the frame inner chord, at each unrepaired frame location common to a MRB filler.
(b) 6,000 flight cycles.-Repeat the surface HFEC inspection around the end fastener for any crack in the frame inner chord, at each frame location common to a MRB filler. (b) CONDITION 4: NO CRACK FOUND.
(a) A structural MRB filler is installed during production integration in addition to a laminated shim when the gap between the frame web and the stub beam support fitting could not be filled to within 0.005 inches by the shim installation.
(b) It is not necessary to do the surface HFEC inspection in accordance with Requirements Bulletin 767- 53A0278 RB in areas where existing repairs approved by the Boeing Organization Designation Authorization (ODA) via FAA form 8100-9 or installed in accordance with Boeing Service Bulletin 767-53A0209 covers the affected inspection area. Damage Tolerance Inspections specified in the approval for existing repairs must continue. Inspection outside each repaired region must continue as instructed in accordance with Requirements Bulletin 767-53A0278 RB.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 30, 2017 767-53A0278 RB 9 of 48 REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT
Group 2, Configuration 1:
Table 3: Station (STA) 859.5, 883.5, and 903.5 - Detailed Inspection for any Material Review Board (MRB) filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner chord Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 24 months or 3,000 flight cycles after the original issue date of Requirements Bulletin 767- 53A0278 RB, whichever occurs first.
Before 37,500 total flight cycles.
Do a detailed inspection for any MRB filler installed in the area from the frame web to the stub beam fitting on the left and right side at STA
859.5, 883.5 and 903.5.
(a) All Airplanes.
--No further action required at this frame location.
CONDITION 1: NO MRB
FILLER INSTALLED OR
MRB FILLER INSTALLED
DOES NOT EXTEND
ABOVE THE FRAME TO STUB BEAM JOINT.
-Before further flight.Do a surface HFEC inspection around the end fastener common to each MRB filler for any crack in the frame inner chord.
(b) CONDITION 2: MRB
FILLER INSTALLED AND
EXTENDS ABOVE THE
FRAME TO STUB BEAM JOINT.
-Before further flight.ACTION 1: Contact The Boeing Company for repair instructions and do the repair.
CONDITION 3: ANY CRACK FOUND.
6,000 flight cycles.-ACTION 2: Repeat the surface HFEC inspection around the end fastener for any crack in the frame inner chord, at each unrepaired frame location common to a MRB filler.
(b) 6,000 flight cycles.-Repeat the surface HFEC inspection around the end fastener for any crack in the frame inner chord, at each frame location common to a MRB filler. (b) CONDITION 4: NO CRACK FOUND.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 30, 2017 767-53A0278 RB 10 of 48 REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT
Group 2, Configuration 1:
Table 3: Station (STA) 859.5, 883.5, and 903.5 - Detailed Inspection for any Material Review Board (MRB) filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner chord Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition
(a) A structural MRB filler is installed during production integration in addition to a laminated shim when the gap between the frame web and the stub beam support fitting could not be filled to within 0.005 inches by the shim installation.
(b) It is not necessary to do the surface HFEC inspection in accordance with Requirements Bulletin 767- 53A0278 RB in areas where existing repairs approved by the Boeing Organization Designation Authorization (ODA) via FAA form 8100-9 or installed in accordance with Boeing Service Bulletin 767-53A0209 covers the affected inspection area. Damage Tolerance Inspections specified in the approval for existing repairs must continue. Inspection outside each repaired region must continue as instructed in accordance with Requirements Bulletin 767-53A0278 RB.
Group 2, Configuration 2:
Table 4: Station (STA) 859.5, 883.5, and 903.5 - Detailed Inspection for any Material Review Board (MRB) filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner chord Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Within 24 months or 3,000 flight cycles after the original issue date of Requirements Bulletin 767- 53A0278 RB, whichever occurs first.
Before 30,000 total flight cycles.
Do a detailed inspection for any MRB filler in installed the area from the frame web to the stub beam fitting on the left and right side at STA
859.5, 883.5 and 903.5.
(a) All Airplanes.
--No further action required at this frame location.
CONDITION 1: NO MRB
FILLER INSTALLED OR
MRB FILLER INSTALLED
DOES NOT EXTEND
ABOVE THE FRAME TO STUB BEAM JOINT.
-Before further flight.Do a surface HFEC inspection around the end fastener common to each MRB filler for any crack in the frame inner chord.
(b) CONDITION 2: MRB
FILLER INSTALLED AND
EXTENDS ABOVE THE
FRAME TO STUB BEAM JOINT.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 30, 2017 767-53A0278 RB 11 of 48 REQUIREMENTS BULLETIN 767-53A0278
ALERTALERT
Group 2, Configuration 2:
Table 4: Station (STA) 859.5, 883.5, and 903.5 - Detailed Inspection for any Material Review Board (MRB) filler installed in the area from the frame web to the stub beam fitting - Surface High Frequency Eddy Current (HFEC) inspection around the end fastener common to each MRB filler for any crack in the frame inner chord Repeat Interval (Not to Exceed) Compliance Time (Whichever Occurs Later) ActionCondition -Before further flight.ACTION 1: Contact The Boeing Company for repair instructions and do the repair.
CONDITION 3: ANY CRACK FOUND.
6,000 flight cycles.-ACTION 2: Repeat the surface HFEC inspection around the end fastener for any crack in the frame inner chord, at each unrepaired frame location common to a MRB filler.
(b) 6,000 flight cycles.-Repeat the surface HFEC inspection around the end fastener for any crack in the frame inner chord, at each frame location common to a MRB filler. (b) CONDITION 4: NO CRACK FOUND.
(a) A structural MRB filler is installed during production integration in addition to a laminated shim when the gap between the frame web and the stub beam support fitting could not be filled to within 0.005 inches by the shim installation.
(b) It is not necessary to do the surface HFEC inspection in accordance with Requirements Bulletin 767- 53A0278 RB in areas where existing repairs approved by the Boeing Organization Designation Authorization (ODA) via FAA form 8100-9 or installed in accordance with Boeing Service Bulletin 767-53A0209 covers the affected inspection area. Damage Tolerance Inspections specified in the approval for existing repairs must continue. Inspection outside each repaired region must continue as instructed in accordance with Requirements Bulletin 767-53A0278 RB.
4. APPROVAL This Requirements Bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this document comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This document and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this Requirements Bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this Requirements Bulletin.
Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details.
Original Issue: June 30, 2017 767-53A0278 RB 12 of 48 REQUIREMENTS BULLETIN 767-53A0278