767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS D622T001-9-01 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-1 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS (AWLs) D622T001-9-01 JUNE 2019 This document has EAR data with an Export Control Classification Number (ECCN) of 9E991. Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). 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. Boeing claims copyright in each page of this document on to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by the Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact the Boeing Company, P.O. Box 3707, Seattle WA 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the red-white-blue Boeing livery are all trademarks owned by The Boeing Company; no trademark license is granted in connection with this document unless provided in writing by Boeing. COMPILED AND PUBLISHED BY: MAINTENANCE PROGRAMS ENGINEERING BOEING COMMERCIAL AIRPLANE GROUP SEATTLE, WASHINGTON JUN 2019
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AIRWORTHINESS LIMITATIONS (AWLs) JUNE 2019...The following 13 767-200SF SSIs, that had 767-200SF listed under the Airplane/Engine Applicability for a similar SSI on another airplane
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ils Page 1.0-1
)
E991.Export ort license may be required before it is used for
sponsibility to abide by all export laws.
Boeing cla right in this document as a compilation and/or collective work. This the information it contains is governed by contract with Boeing. F 07, 717, 727, 737, 747, 757, 767, 777, 787, BBJ, DC-8,
DC-9, D trademark license is granted in connection with this
JUN 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
JUNE 2019This document has EAR data with an Export Control Classification Number (ECCN) of 9
of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An expdevelopment, production or use by foreign persons from specific countries. The controller of this data has the individual re
ims copyright in each page of this document on to the extent that the page contains copyrightable subject matter. Boeing also claims copy document includes proprietary information owned by the Boeing Company and/or one or more third parties. Treatment of the document andor more information, contact the Boeing Company, P.O. Box 3707, Seattle WA 98124. Boeing, the Boeing signature, the Boeing symbol, 7C-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the red-white-blue Boeing livery are all trademarks owned by The Boeing Company; no
document unless provided in writing by Boeing.
COMPILED AND PUBLISHED BY:MAINTENANCE PROGRAMS ENGINEERINGBOEING COMMERCIAL AIRPLANE GROUP
SEATTLE, WASHINGTON
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D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
F EFFECTIVE PAGES ........................................................................................................................................
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
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JULY 201
Original R
This revis
Please s
NOVEMB
Revised uirements for operators that have incorporated Service B
DECEMB
Added a 26.21 (Amendment 26-6).
FEBRUA
Revised n of the main landing gear full-scale fatigue tests and anal
OCTOBE
Revised
Added S the -200SF and -300BCF to the table of Airworthi
Added Ite g SSI Items affected by this new note: 57-10-I01A, 57-DECEMB
Revised
JUN 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
REVISIONS
4
elease
ion contains no technical changes.
ee the 767 MPD Section 9, D622T001-9 for historical Revision Log information.
ER 2014
Subsection B. Airworthiness Limitations - Structural Inspections to add a paragraph which addresses special inspection requlletin 767-23-0228.
ER 2014
new Section D. AWLs - Structural Limit of Validity (LOV) as required by Title 14 Code of Federal Regulations (CFR) Section
RY 2015
Structural Safe Life Parts section by reformatting for clarification and updating the 767-400ER life limits based on completioysis.
R 2015
SSI 52-30-I02A to reflect changes made to the DTR Check Form requirements.
SI 57-10-I03B - Rear Spar Lower Chord and Skin - Wing Center Section - Hidden Locations - BBL 49.5, 62.05 and 73.0 forness Limitations - Structural Inspections in Section B.
m 5 to the Table Notes for the Airworthiness Limitations - Structural Inspections Table and added a footnote to the followin10-I02C, 57-10-I03A, 57-10-I03B, 57-10-I03C, 57-10-I20A, 57-10-I24A, 57-20-I12C, 57-20-I15J, and 57-20-I16K.ER 2015
Section D. AWLs - Structural Limit of Validity (LOV) to add applicability for the 767-300BCF.
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JULY
Dele ction 9/AWL/CMR/SCI documents. Submittal sign
Revi tank fasteners to point to the 767 Special Compliance Item
Revi rential Skin and Stringer Splice - BS 434 for the 767-
Revi ded #5 Inboard Flap Support to the title for clari
Revi all aircraft and added #5 Inboard Flap Support to the title
Revi els and added #5 Inboard Flap Support to the title for c
Revi ed #5 Inboard Flap Support to the title for clarification.
Dele
Revi ed #5 Inboard Flap Support to the title for clarification.JULY
Revi
Revi h grace period of change incorporation.
Revi dix A being added to the document to define the base hold, to be 3,000 flight cycles, 24 months or 9,000 fligh ting instructions. The manager of the FAA Oversight Offic al of Excess Sealant When Inspecting to add excess seal to the beginning of phrase “Structural Inspections “ rega
Revi
Rem s. This is to clarify that all 200SF and 300BCF ALIs are i
Rem
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BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
2016
ted the FAA Approval signature column from the Revision Log to improve the layout and provide consistency across all Seatures will no longer be included in the Revision Log.
sed front matter under “REMOVAL OF EXCESS SEALANT WHEN INSPECTING” to update the reference to sealant of fuel s/Airworthiness Limitations document, D622T001-9-04.
sed the Airworthiness Limitations - Structural Inspections Table in Section B by adding SSI 53-30-I08A - Fuselage Circumfe300F, L/N 1108 and on.
sed SSI 57-53-I03I.2 to combine SSI/DTR Forms and their requirements into one SSI/DTR Form to cover all aircraft and adfication.
sed SSI 57-53-I03J.1 to combine with SSI 57-53-I03J.2 DTR Form and their requirements into one SSI/DTR Form to coverfor clarification and removed Flag Note <2>.
sed SSI 57-53-I03J.2 to combine SSI/DTR Forms and their requirements into one SSI/DTR Form to cover all airplane modlarification.
sed SSI 57-53-I03K to combine SSI/DTR Forms and their requirements into one SSI/DTR Form to cover all aircraft and add
ted SSI 57-53-I03L.1 and 57-53-I03L.2 as those requirements are now covered in SSI 57-53-I03L.
sed SSI 57-53-I03L to combine SSI/DTR Forms and their requirements into one SSI/DTR Form to cover all aircraft and add 2018
sed document header from 767 to 767-200/300/300F/400ER to list all derivatives.
sed Section A. Scope to add requirement for document to be used in its entirety. Added guidelines that provides a 24 mont
sed Section B reference document names for consistency within this document. Revised to address the inclusion of Appenline inspection program. Revised Threshold section to clarify A-Check and C-check inspection interval, after reaching thres
t hours for the C-check, and 300 flight cycles or 900 flight hours for the A-check. Revised structural inspection results repore, the Transport Airplane Directorate, and the FAA have been removed from the list of required recipients. Revised Removant removal instructions and added a table with detailed descriptions table for Excess Sealant. Added the word “Fuselage”rding the Airworthiness Limitations document for the 767-300BCF.
sed definition of 767-300, 767-300ER from “300” to “300 PASS”, for clarity.
oved the two notes stating that some ALIs for the 767-200SF and 767-300BCF do not have corresponding DTR check formncluded in the DTR Check Form Document.
oved "No DTR Check Form" notes from ALIs table to clarify that all ALIs are included in the DTR Check Form Document.
(Continued on next page
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Revised 52-30-I0552-30-I0752-30-I09
Revised lumn.
Revised ble 767 Non-Destructive Testing Manual:52-30-I0252-30-I0752-30-I0752-30-I0752-30-I0752-30-I07
Fuselage o other existing SSIs. As a result, updates have been maThe upda53-30-I2453-30-I2453-10-I0853-10-I0853-30-I24
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8, Continued
the following SSIs to include the intercostal numbers for the inspection area:BBB
SSI 52-30-I07B to correct an error in the July 2016 revision of this document by adding 300F to the Type and Threshold co
the following SSIs to remove the Flagnote <2> as inspection procedures for these items have been published in the applicaAABCEF
137 SSIs to make clarifications.
e following 6 new SSIs:A all 767 modelsA all 767 modelsB all 767 models except 767-300F/53-30-I29/53-60-I31 all 767 modelsA all 767 modelsB 767-300 Passenger
he following 3 SSIs: 767-200SF item SF8A 767-200SF item SF8BF
frame inspections for the 767-200SF and 767-300BCF were reorganized and simplified such that 5 SSIs were merged intde to the SSI number and the Airplane/Engine Applicability of some of these SSIs. ted 767-200SF fuselage frame inspection SSIs are the following:A/53-30-I24B/53-50-I01A/53-50-I02A/53-60-I08A 767-200SF A/53-30-I24B/53-60-I08A 767-200SF B 767-200SF and 767-300BCF item BCF3C/53-30-I24C/53-60-I08C 767-200SF and 767-300BCF item BCF5C/53-60-I08C 767-200SF and 767-300BCF item BCF6
(Continued on next page)
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The 53-353-353-153-153-3
The r airplane model, were separated into their own line item D622T001-DTR document. 53-353-353-353-553-553-553-553-553-553-653-653-653-6
The
Of th : The 53-353-353-353-353-353-5
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2018, Continued
53, Continued
updated 767-300BCF fuselage frame inspection SSIs are the following:0-I24A/53-30-I24B/53-50-I01A /53-50-I02A /53-60-I08A 767-300BCF item BCF10-I24A/53-30-I24B 767-300BCF item BCF2/BCF40-I08B 767-200SF and 767-300BCF item BCF30-I08C/53-30-I24C/53-60-I08C 767-200SF and 767-300BCF item BCF50-I24C/53-60-I08C 767-200SF and 767-300BCF item BCF6
following 13 767-200SF SSIs, that had 767-200SF listed under the Airplane/Engine Applicability for a similar SSI on anothe. This was done to clarify the difference between the DTR Check Form for the 767-200SF and the other 767 models in the 0-I14A0-I14C0-I14D0-I06A0-I06B0-I06C0-I06D0-I06E0-I06F0-I06B0-I06C0-I06D0-I10 767-200SF item SF2
threshold for SSI 53-60-I06B (767-200SF item) was changed from 40,000 cycles to 50,000 cycles.
e 137 SSIs that were revised for clarifications, the following SSIs were changed more significantly than minor clarificationsairplane model applicability was changed for the following 6 SSIs:0-I04A RHS 767-300BCF 0-I19AD0-I19AD10-I19AF0-I19AF10-I19
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
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8, Continued
ontinued
the following 13 SSIs to change the inspection region:B 767-200SF item SF5DEFC 767-200 C 767-200SF 767-300BCF item BCF2 767-200SF item SF2CABD
the following SSIs to add or update required Flagnotes in the Airplane/Engine Applicability:C/53-30-I04C/53-60-I04C D/53-30-I04D/53-60-I05DABACA Line numbers 1- 757A Line numbers 758 and onA 767-200SF ADEFADAD 767-300 PassengerD 767-400ERA/53-50-I03/53-60-I03 767-200SFA B
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
2018, Continued
53, Continued
sed the following SSIs to add or update required Flagnotes (continued):0-I28C 0-I28D 0-I28E 0-I28F 0-I06 0-I13C0-I14B0-I06B 767-300BCF and All Passenger0-I06B 767-200SF0-I06C 0-I06D/53-30-I14D 0-I14D 0-I06D 0-I06E/53-30-I14E0-I06E 0-I10C 0-I14F0-I27A 767-300 Passenger0-I27A 767-400ER0-I27B0-I27C0-I29A 0-I29B 0-I29C 0-I29D 0-I30A 0-I01C
sed the following SSIs to remove Flagnote.0-I05/53-30-I08/53-30-I21/53-50-I03/53-60-I03/53-60-I04/53-60-I24/53-60-I330-I01A0-I01B0-I01D0-I01E0-I15/53-80-I16/53-80-I17
sed the following SSIs to add Flagnote <2> in the Airplane/Engine Applicability Column:0-I01 7R40-I01 40000-I01 80C
sed the following SSIs to remove the Flagnote <2> as inspection procedures for these items have been published in the ap0-I01a 0-I02/I03a 5240-I03b 5240-I04a 80C (400E)0-I04c 80C (400E)0-I04e 80C (400E)0-I05 7R40-I05 40000-I05 80A0-I05 80C (Except 400E)0-I05a 80C (400E)0-I06a 80C (400E)0-I06c 80C (400E)0-I06d 80C (400E)0-I09a/I07/I08/I12 80C (400E)0-I10 5240-I10b 80C (400E)0-I12b 80C (400E)0-I13 7R40-I13 40000-I13 80A0-I13 80C0-I13a 80C (400E)
(Continued on next page)
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Revised ble 767 Non-Destructive Testing Manual, Continue54-50-I1354-50-I1454-50-I1654-50-I1654-50-I1754-50-I1754-50-I1754-50-I17
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8, Continued
ontinued
the following SSIs to remove the Flagnote <2> as inspection procedures for these items have been published in the applicad:e 80C (400E) 80C (400E)a 80C (400E)e 80C (400E)a 80C (400E)c 80C (400E)e 80C (400E)f 80C (400E)
2 SSIs to clarify the titles.
180 SSIs to clarify the titles.
23 SSIs to clarify the zones.
the following SSIs to clarify the data in the Airplane/Engine Applicability Column (as described):A 200ER/300ER with center section fuel, with stage length < 8 hoursA 200ER/300ER with center section fuel, with stage length ≥ 8 hoursB 200ER/300ER with center section fuel, with stage length < 8 hoursB 200ER/300ER with center section fuel, with stage length ≥ 8 hoursC 200ER/300ER with center section fuel, with stage length < 8 hoursC 200ER/300ER with center section fuel, with stage length ≥ 8 hours all except 200SF and 300BCF with stage length < 8 hours all except 200SF and 300BCF with stage length ≥ 8 hoursY all except 400ER
the following SSIs to replace Flagnote <5> with Flagnote <6> in the Type and Threshold Column, to correct the inspection A 200SF & 300BCFB 200SF & 300BCFC 200SF & 300BCFJ 200SF & 300BCFK 200SF & 300BCF
(Continued on next page)
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ATA
Revi57-257-2
Revi
Adde
Revi 8 hours.
Revi airplanes with stage length > 8 hours.
Revi to differentiate it from bolt shank inspections.
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
2018, Continued
57, Continued
sed the following SSIs to add Flagnote <6> in the Type and Threshold Column, to correct the inspection threshold:0-I15K 200SF & 300BCF0-I16L 200SF & 300BCF
sed SSI 57-10-I02 for the 400ER to be applicable to airplanes with stage length < 8 hours.
d SSI 57-10-I02 for the 400ER with stage length ≥ 8 hours.
sed SSI 57-20-I15E to remove 400ER effectivity for airplanes with stage length < 8 hours and airplanes with stage length ≥
sed the two SSIs for 57-20-I27 to combine SSI 57-20-I27 "for airplanes with stage length < 8 hours" with SSI 57-20-I27 "for
sed SSI # for SSI 57-53-I03F - Inboard Flap Box Support No. 3/6 - Flap Attachment Bolts, IFS 251.25 to SSI 57-53-I03F.1
sed SSI # for SSI 57-53-I03F - Inboard Flap Support No. 3/6 - Flap Attachment Bolts - Shank Location to SSI 57-53-I03F.2
sed the threshold for SSI 57-10-I08 to correct a typographical error from 70,000 flight hours to 80,000 flight hours.
sed the following SSIs to add Flagnote <2> in the Airplane/Engine Applicability Column:0-I07 400ER, and all airplane types L/N 922 and later
sed the following SSIs to remove the Flagnote <2> as inspection procedures for these items have been published in the ap0-I02B 400ER with stage length < 8 hours0-I02B 400ER with stage length ≥ 8 hours0-I25 400ER with stage length < 8 hours0-I25 400ER with stage length ≥ 8 hours0-I15F 400ER with stage length < 8 hours0-I15F 400ER with stage length ≥ 8 hours3-I02A.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-9213-I02A.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-9213-I02B 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 922 and Later and 400ER3-I02D.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-9213-I02E 200, 200SF, 300BCF, 300F, 300 PASS L/N 922 and later and 400ER3-I02G.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-9213-I02I ALL3-I02J.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-9213-I02J.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-9213-I02L.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-9213-I02L.3 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-9213-I02M.1 200, 200SF, 300BCF, 300F, 300 PASS L/N 922 and later and 400ER3-I03E.1 200, 200SF, 300BCF, 300F, 300 PASS L/N 922 and later and 400ER
(Continued on next page)
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the following SSIs to revise the threshold from 80,000 flight hours to 70,000 flight hours in the Type and Threshold Columnents, including a grace period for the 300BCF:C 300BCFD 200SFK 200SF and 300BCFL 200SF and 300BCF
(Continued on next page)
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Revi lumn, to reflect the 200SF & 300BCF fatigue requ57-157-157-157-257-2
Revi
Revi
Adde
AddeJUN
Revi
Revi
ATA Revi en published in the applicable 767 Non-Destructive Test
ATA Revi 4/53-30-I29/53-60-I31, 53-30-I19AB (300BCF, 300F, and 3-60-I27C (300 PASS and 400E), and 53-80-I01C (Line plicable 767 Non-Destructive Testing Manual.
Revi he applicable 767 Non-Destructive Testing Manual.
Revi move the Flagnote <4> as inspection procedures for thes
Revi
Revi ord and Splice Stringers in the structures baseline insp
Revi nd Splice Stringers to the structures baseline insp
Revi
Revi
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2018, Continued
57, Continued
sed the following SSIs to revise the threshold from 50,000 flight cycles to 25,000 flight cycles in the Type and Threshold Coirements, including a grace period for the 300BCF:0-I03A 200SF and 300BCF0-I03B 200SF and 300BCF0-I03C 200SF and 300BCF0-I15J 200SF and 300BCF0-I16K 200SF and 300BCF
sed Flagnote <1> description to reflect that this Flagnote is no longer being used.
sed Flagnote <3> and <4> description to be consistent with Flagnote <2>.
d Flagnote <6>.
d Appendix A to provide information related to AD 2014-14-04 paragraph (g) requirements.E 2019
sed A. Scope to update guidelines that provides a 24 month grace period of change incorporation.
sed the structural inspection requirements when reaching threshold for clarity.
52sed SSIs 52-30-I05A and 52-30-I09A (300F) to remove the Flagnote <2> as inspection procedures for these items have being Manual.
53sed SSIs 53-10-I06A, 53-10-I10A, 53-10-I10B, 53-10-I14A, 53-10-I32A, 53-10-I32B (All 767 models except 300F), 53-10-I3400E), 53-30-I19AC (300BCF, 300F, and 400E), 53-50-I29A, 53-50-I29B (300 PASS), 53-60-I27B (300 PASS and 400E), 5 numbers 424 and on) to remove the Flagnote <2> as inspection procedures for these items have been published in the ap
sed SSI 53-60-I10C (300F) to remove the Flagnote <3> as inspection procedures for these items have been published in t
sed SSIs 53-30-I01 (200SF), 53-30-I14A (200SF), 53-60-I06C (300BCF), 53-60-I10 (300BCF), and 53-60-I10 (200SF) to ree items have been published in the applicable 767 Non-Destructive Testing Manual.
sed Appendix A to change the applicability for MPD Item 53-550-91 from "300, 300BCF, 400ER" to "300, 300BCF, 400E".
sed Appendix A to change MPD Item 53-618-00 to Internal - Detailed: Wing Center Section Lower Surface At Rear Spar Chection requirements.
sed Appendix A to add MPD Item 53-618-91 Internal - Detailed: Wing Center Section Lower Surface At Rear Spar Chord aection requirements.
sed Appendix A to change the applicability for MPD Item 53-710-92 from "ALL" to "200, 300, 300BCF, 400E".
sed Appendix A to change the applicability for MPD Item 53-710-93 from "300, 300BCF, 400ER" to "300, 300BCF, 400E".(Continued on next page)
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Added S f (80C (400E), ≥ 8 Hours), 54-50-I13g (80C (400E), < rs).
Revised lagnote <2> as inspection procedures for these items hav
ATA 57
Revised ility Column.
Revised hold Column.
Revised
Revised
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SSIs 54-50-I01e (80C (400E)), 54-50-I18 (80C (400E), < 8 Hours), and 54-50-I18 (80C (400E), ≥ 8 Hours) to remove the Fe been published in the applicable 767 Non-Destructive Testing Manual.
SSIs 57-20-I16F (400E, < 8 Hours) and 57-20-I16F (400E, ≥ 8 Hours) to add Flagnote <2> in the Airplane/Engine Applicab
the threshold for SSI 57-53-I03K to include 25,000 Cycles after SB 767-27A0176 was accomplished in the Type and Thres
Appendix A front matter for clarity.
Appendix A to remove the special note for MPD Item 57-416-91 requiring the removal of sealant.
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LIST OF EFFECTIVE PAGES767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
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his program was developed in accordance with the guidelines of MSG-3 and partially satisfies the requiremen
ccidental and environmental damage detection opportunity for all SSIs, and in some cases, fatigue damage d
nspection threshold is reached. The supplemental structural inspections listed in this “Airworthiness Limitation
eceive adequate fatigue damage detection opportunity from the initial baseline structural program that is listed
f this document. The inspections shown in this section and Appendix A are to be accomplished in conjunction
tructural maintenance program found in Section 2 of the MPD.
he supplemental structural inspection program uses the Damage Tolerance Rating (DTR) system to determin
ecessary to provide adequate fatigue damage detection. The DTR system defines a required DTR (a numeri
SI. DTR Check Forms which define the inspection options and the required DTR are contained in Document
HRESHOLD
he certifying authority (FAA Oversight Office) requires designation of all SSIs into two categories. These two
Type 2. Type 1 structure requires the implementation threshold to be established by crack growth analysis. Ty
implementation threshold established by fatigue analysis (supported by test evidence) and allows for the future
sufficient data from the initial inspections statistically support an increased threshold. See Document D622T00
and Type 2 categories.
The inspections are to be done on the basis of the threshold specified in the AWL - Structural Inspections table
DTR Check Forms contained in Document D622T001-DTR.
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Initia s accumulated regardless of what the
airfra the same flight cycles and flight hours
as th able/rotable/expendables) or installing
used may be different than the airframe. The
oper
Altho ble Structural Component, which may
be a
The items are sensitive to flight length and
iden rs and flight cycles to determine the
impl
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
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l inspection (threshold) and intervals are measured in flight cycles or flight hours that a particular SSI detail ha
me as a whole has accumulated. Most SSI details have never been replaced and therefore have accumulated
e airframe. Some SSI details are replaced, such as when installing Removable Structural Components (repair
structural parts as a repair. In these cases the SSI details have accumulated flight cycles and flight hours that
ator must account for this in determining when inspections must be done.
ugh intended for repairs, FAA AC 120-93 Appendix 7, provides a method for determining the age of a Remova
pplied to the baseline structure.
Airworthiness Limitations - Structural Inspections table defines the inspection implementation threshold. Some
tified by “FLS” (Flight Length Sensitive) in the Threshold column of the table. FLS Items require both flight hou
ementation threshold. Refer to Figure 1, shown on the next page, to determine the threshold for FLS Items.
14
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IONS
CURVE
2
3 Threshold Curve. Note that the shaded area
d -400ER Passenger aircraft.
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767-200/300/300F/400ER AIRWORTHINESS LIMITAT
FIGURE 1. FLIGHT LENGTH SENSITIVE (FLS) THRESHOLD
Instructions for the use of the Flight Length Sensitive (FLS) Threshold Curve:
1. Determine, for each airplane, the accumulated flight cycles and flight hours.
. Enter the FLS Threshold Curve at the appropriate flight cycles and flight hours and plot point.
. The initial supplemental inspection must be accomplished before crossing into the shaded area on the FLS
for the -200, -200SF, -300 Passenger, and -300BCF aircraft is different from that for the -300F Freighter an
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In ad f an FAA approved Corrosion
Prev
The s that must be used upon the airplane
reac 14 CFR § 25.571 Damage Tolerance
Req
As s al Inspection intervals in the Operator's
base
Whe ted to -300BCF aircraft after 10,000
cycle ger converted to -300BCF aircraft
befo tion interval described in Appendix A as
"S 1 eck inspection interval described in
Appe es first. This means that any operator
who interval must reduce their Structures A-
chec t the Title 14 CFR § 25.571 damage
toler thiness Limitations listed in this
docu eline Structural Inspection Program
defin erval could result in additional structure
not m ss Limitations are to be accomplished
in co
767
Cert ulletin. After incorporation of the
Boei and 767-300BCF. Refer to Section C
of th1 Onl
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dition to the thresholds described above, a calendar threshold of 20 years applies unless an initial inspection o
ention and Control Program (CPCP) has occurred, constituting CPCP implementation.
information contained in Appendix A provides operators with the Baseline Structures and Zonal Inspection task
hing the fatigue threshold. This must be done in order to ensure the maintenance program complies with Title
uirements.
uch, when reaching the threshold the inspection must be the lesser of: 1) the FAA approved Structural and Zon
line inspection program or 2) the inspection intervals contained in Appendix A.
n reaching the threshold of 50,000 flight cycles (-200, -200SF1 and -300 Passenger or -300 Passenger conver
s or more as a -300 Passenger) or 40,000 flight cycles (-300F Freighter or -400ER Passenger or -300 Passen
re 10,000 cycles as a -300 Passenger) or the FLS curve, whichever comes first, the Structures A-check inspec
A" must be no greater than 300 flight cycles or 900 flight hours whichever comes first, and the Structures C-ch
ndix A as “S 1C” must be no greater than 3,000 flight cycles or 24 months or 9,000 flight hours, whichever com
has escalated their structures inspection program by increasing the Structures A-check or C-check inspection
k or C-check inspection interval to within these limits when they reach the threshold. The reason for this is tha
ance evaluation takes credit for the baseline Structures Inspection Program defined in Appendix A. The Airwor
ment are supplemental structural inspections of the SSIs for which the required DTR is not satisfied by the bas
ed in Appendix A. Any continued escalation beyond the baseline Structures A-check or C-check inspection int
eeting the required DTR which was the basis of certification. The inspections contained within the Airworthine
njunction with, and not as a substitute for, the existing Structures Inspection Program found in Appendix A.
PASSENGER-TO-FREIGHTER CONVERSION AIRPLANES
ain 767 airplanes are modified from passenger model airplanes to a freighter configuration via Boeing service b
ng passenger-to-freighter service bulletin, these 767-200 and 767-300 airplanes are designated as 767-200SF
is chapter for additional data related to 767-200SF and 767-300BCF structural safe life parts.
y one -200SF exists, and it was modified after 14,900 cycles as a Passenger aircraft.
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IONS
age accrued as a passenger and then a
ine the threshold for these items.
C re identified by “Mod Date Sensitive” in the
T
I
1
2
3 curve.
I
1
2
3 urve.
N re applicable to converted airplane variable
7-300BCF, the operator must refer to
s Supplement," Revision New or later.
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767-200/300/300F/400ER AIRWORTHINESS LIMITAT
Certain 767-300BCF supplemental inspection thresholds are calculated based on the summation of fatigue dam
freighter. These are identified by “Combined Threshold” in the Threshold column. Refer to Figure 2 to determ
ertain 767-300BCF supplemental inspection thresholds are calculated from the date of modification. These a
hreshold column. Refer to Figure 3 to determine the threshold for these items.
nstructions for the use of the Combined Life Threshold curve:
. Determine, for each airplane, the accumulated flight cycles prior to BCF modification.
. Enter the threshold curve at the appropriate flight cycles as 300ER.
. The initial supplemental inspection must be accomplished before crossing the 300BCF Combined Threshold
nstructions for the use of the Mod Date Sensitive curve:
. Determine, for each airplane, the accumulated flight cycles prior to BCF modification.
. Enter the threshold curve at the appropriate flight cycles as 300ER.
. The initial supplemental inspection must be accomplished before crossing the 300BCF Mod Date Sensitive c
ote: The 767-300BCF Airworthiness Limitations - Fuselage Structural Inspections contained in this section a
numbers VN191 thru VN197. For the Airworthiness limitations - Fuselage Structural inspections of all other 76
document D622T200-01 "767-300BCF Instructions for Continued Airworthiness - Airworthiness Limitation Item
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45000 50000
oubler
anel)er Row
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FIGURE 2. Combined Passenger and Freighter Life Threshold
Combined Threshold
25000
30000
35000
40000
45000
50000
55000
0 5000 10000 15000 20000 25000 30000 35000 40000
Flights as 300ER (Cycles)
Com
bine
d Th
resh
old
(Cyc
les)
53-30-I01 BCF2 Section 43 Crown SK/STR at Aft Edge External D53-30-I01 BCF10 Crown Stringer STA 654+110 to STA 78653-30-I04D BCF1 Inner Skin at Lower Fastener Row S-26L Lap53-30-I04A BCF2 Outer Skin at Upper Fastener row S-8L Lap (L2 P53-30-I04B STR 8R Lap BS 434 - 654+22 Inner Skin at Lower Fastn
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IONS
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767-200/300/300F/400ER AIRWORTHINESS LIMITAT
FIGURE 3. Mod Date Sensitive Structure
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REP
A re with an average flight length (flight
hour of the form (see Document D622T001-
DTR the FAA Oversight Office.
SPE
For o apply. After incorporation of
SB 7 incorporated into the aircraft
main
REP
All c anes using the Discrepant Structure
Rep ins the same information may be used).
REM
1. e following:
• e a metal blade or knife. Check to make
• plication.
• de the fuel tank removal and application,
• the fuel tank.
• s document, D622T001-9-04.
2. ns at, or prior to, the listed thresholds:
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EAT INSPECTION INTERVAL
peat inspection interval for the fatigue inspection of an SSI is established from its DTR Check Form. Airplanes
s per landing) equal to or more than 8 hours must use the DTR Check Form labeled "767 > 8 hours" at the top
for DTR Check Forms). Revision to the required DTR or the DTR curve is not allowed without approval from
CIAL STRUCTURAL INSPECTIONS
perators that incorporate the SATCOM retrofit, given in SB 767-23-0228, supplemental structural inspections
67-23-0228, prior to returning the aircraft to service the supplemental inspections in SB 767-23-0228 shall be
tenance program.
ORTING RESULTS OF STRUCTURAL INSPECTIONS
racks found during these inspections shall be reported within ten (10) days directly to Boeing Commercial Airpl
ort Form. Refer to Document D622T001-DTR for the required report form (any suitable alternative which conta
OVAL OF EXCESS SEALANT WHEN INSPECTING
In areas where the DTR Check Forms, or the MPD Items listed in Paragraph 2, require sealant removal, use th
Refer to AMM 51-31-01 for general sealant removal and application, and the use of proper tools. Do not ussure that surface scratching or scoring damage to the part did not occur.
Refer to AMM 28-11-00 (Task 28-11-00-308-013) for sealant (BMS 5-45) inside the fuel tank removal and ap
Refer to AMM 28-11-00 (Task 28-11-00-308-060) for secondary fuel barrier sealant (BMS 5-81, Type II) outsion the wing center section.
If sealant is removed inside the fuel tank for inspection, care must be taken to remove any sealant debris in
Sealant of fuel tank fasteners must comply with the 767 Special Compliance Items/Airworthiness Limitation
The following MPD Items require sealant to be removed, or limited, to accomplish the baseline visual inspectio
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SCRIPTION OF SEALANT REMOVAL AT AREAS ERE INSPECTIONS NEED TO BE PERFORMED
neral Notes
ny sealant that is removed does not need to be pplied except where indicated.
o not remove fillet seals along the edges of parts ess where indicated.
1. WSeSu
r to inspection of the splice stringers L-6 and L-10 the wing sealant removal is required:
t all locations, remove fastener cap seals on the nger horizontal flange surfaces. Replace fastener cap ls after inspections.
t all locations, ensure that the fillet seals that overlap o the stringer horizontal flanges do not extend past centerline of the nearest fastener row.
t the intersection with the external beams at BL 9.5 BL 62, remove the fillet seals that overlap onto the
face of the stringer horizontal flanges.
2. WSec
BodAttaLow
r to inspection of the side-of-body rib web at the er plus chord, the following sealant removal is uired:
t the rib web to lower plus chord attachment, remove fillet seal overlap onto the vertical surface of the rib .
imit fastener cap seals on the rib web along the lower s chord to 0.4 inches from the edge of the fastener d or collar.
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767-200/300/300F/400ER AIRWORTHINESS LIMITAT
EXCESS SEALANT TABLE
ITEM AIRPLANE APPLICABILITY
MPD ITEM NO. THRESHOLD
INSTALLATION DRAWING DEWHGe
1. Area
2. Dunl
NUMBER TITLE
ing - Center ction - Lower rface Splice Stringers
400ER 57-416-0025,000 FC or 80,000 FH, whichever comes first
111T4000 Lower Panel Instl and Assy - Wing, Center Section
Priofollo
1. Astrisea
2. Aontthe
3. Aandsur
ing - Center tion - Side of
y Rib Web - at chment to the er Plus Chord
ALL models with Wing Center Section Fuel
57-526-0025,000 FC or 80,000 FH, whichever comes first
112T5000 Rib Instl - Wing, BBL 97.42
Priolowreq
1. Atheweb
2. Lpluhea
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3. WingSection
Spar Low
inspection of the rear spar lower chord the g sealant must be removed:
locations, remove any fillet sealant which onto the horizontal and vertical flanges of the rd.
external fittings at BL 49.5, BL 62.05 and BL 73 the fastener cap seals on the horizontal and flanges of the spar chord. Replace fastener cap ter the inspection.
other locations limit the fastener cap seals on the al spar chord flange to 0.150 inches from the the collars.
other locations limit the fastener cap seals on the spar chord flange to 0.25 inches from the edge of rs or fastener heads.
4. WingSectionSkin adRear Sp
Ch
inspection of the lower skin adjacent to rear spar ord at the hidden locations at BL 49.5, BL 62.05
73.0, remove any fillet sealant extending more 8 inches from the edge of the spar chord onto r skin as described in 767 NDT Manual, Part 6,
4, Paragraph 3B.
5. WingSection
Spar Lowat W
Attac
inspection of the rear spar lower chord between nd WBL 97.9, and between LBL 11 and RBL 11, sealant on the fastener cap seals of the rear spar ord vertical flange such that at least 0.40 inches
chord surface is visible between the fastener
IT
IPTION OF SEALANT REMOVAL AT AREAS INSPECTIONS NEED TO BE PERFORMED
l Notes
ealant that is removed does not need to be d except where indicated.
t remove fillet seals along the edges of parts here indicated.
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767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
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- Center - Rear er Chord
200ER and 300ER with center section
fuel57-420-00
25,000 FC or 80,000 FH, whichever comes first
111T1000Rear Spar Assembly and Installation - Wing, Center
Section
Prior to followin
1. At all overlapsspar cho
2. At theremovevertical seals af
3. At all horizontedge of
4. At all vertical the colla
- Center - Lower jacent to ar Lower ord
200ER and 300ER with center section
fuel and flight length < 8 hours
57-420-00 FLS 111T4000 Lower Panel Instl and Assy - Wing, Center Section
Prior to lower chand BL than 0.1the lowe57-10-0
- Center - Rear er Chord eb
hment
400ER with flight length < 8 hours 57-422-00
25,000 FC or 80,000 FH whichever comes first
111T1000 Rear Spar Assy and Instl - Wing, Center Section
Prior to BL 62 aremovelower chof spar rows.
EXCESS SEALANT TABLE
EM AIRPLANE APPLICABILITY
MPD ITEM NO. THRESHOLD
INSTALLATION DRAWING DESCRWHEREGenera
1. Any sreapplie
2. Do nounless w
NUMBER TITLE
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IONS
OutSu
StriL-B
r to inspection of the lower surface splice stringers and L-10, ensure that fillet seal overlap onto the nger horizontal flange does not extend past the terline of the nearest fastener row.
OuSpa
Betat
r to inspection of the rear spar lower chord, the wing sealant removal is required:
emove the fillet seal overlaps onto the surfaces of spar chord vertical and horizontal flanges.
nsure that the fastener cap seals on the horizontal r chord flange do not extend more than 0.150 inches the edge of the collars.
nsure that the fastener cap seals on the vertical spar rd flange do not extend more than 0.25 inches from edge of the collars or fastener heads.
SCRIPTION OF SEALANT REMOVAL AT AREAS ERE INSPECTIONS NEED TO BE PERFORMED
neral Notes
ny sealant that is removed does not need to be pplied except where indicated.
o not remove fillet seals along the edges of parts ess where indicated.
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BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
6. Wing - board - Lower rface Splice
Stringers - ngers L-6 and 10 - Side-of-ody to Rib 3
ALL except 200SF, 300BCF 57-516-00
25,000 FC or 80,000 FH whichever comes first
112T4000 Panel Installation - Inspar, Wing, Lower
PrioL-6stricen
7. Wing - tboard - Rear r Lower Chord and Skin - ween Fairing Side-of-Body and Rib 3
ALL except 200SF and 300BCF
57-522-00
57-524-00
25,000 FC or 80,000 FH whichever comes first
112T1000
112T4000
Rear Spar Instl - Wing
Panel Installation - Inspar, Wing, Lower
Priofollo
1. Rthe
2. Espafrom
3. Echothe
EXCESS SEALANT TABLE
ITEM AIRPLANE APPLICABILITY
MPD ITEM NO. THRESHOLD
INSTALLATION DRAWING DEWHGe
1. Area
2. Dunl
NUMBER TITLE
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8. WOutboar
Spar Lowat Ext
Hidden
inspection of the front spar lower chord, the g sealant removal is required:
ternal stiffeners and auxiliary track ribs, between d Rib 31, ensure that the fillet seal overlap onto chord horizontal flange does not extend past the e of the nearest fastener row.
ternal stiffeners between Rib 9 and Rib 14, and Rib 24 and Rib 31, ensure that fillet seal overlap spar chord vertical flange does not extend past erline of the nearest fastener row.
ternal stiffeners between Rib 14 and Rib 24, that the fillet seal on the front spar chord vertical oes not extend more than 0.125 inches below ner collars on the lower fastener row.
9. WOutboar
Spar Low
inspection of the front spar lower chord between d Rib 10, ensure that the fillet seal overlap onto chord horizontal and vertical flanges does not ast the centerline of the nearest fastener row.
IT
IPTION OF SEALANT REMOVAL AT AREAS INSPECTIONS NEED TO BE PERFORMED
l Notes
ealant that is removed does not need to be d except where indicated.
t remove fillet seals along the edges of parts here indicated.
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767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
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EXPORT CONTROLLED - EAR ECCN: 9E991
ing - d - Front er Chord
ernally Details
400ER with flight length < 8 hours 57-530-00 FLS 112T2000 Front Spar Instl - Wing
Prior to followin
1. At exRib 9 anthe sparcenterlin
2. At exbetweenonto thethe cent
3. At exensure flange dthe faste
ing - d - Front er Chord
ALL except 400ER, 200SF and 300BCF
57-530-00 FLS 112T2000 Front Spar Instl - Wing
Prior to Rib 9 anthe sparextend p
EXCESS SEALANT TABLE
EM AIRPLANE APPLICABILITY
MPD ITEM NO. THRESHOLD
INSTALLATION DRAWING DESCRWHEREGenera
1. Any sreapplie
2. Do nounless w
NUMBER TITLE
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IONS
OuSpa- H
r to inspection of the front spar lower chord, between s 14 and Ribs 24, at hidden details common to ernal stiffeners and aux track ribs, the following lant removal is required:
nsure that the fillet seal overlap onto the spar chord izontal flange does not extend past the centerline of nearest fastener row.
nsure that fillet sealant overlap on the spar chord tical flange does not extend more than 0.125 inches ow the edge of the fastener collars on the lower tener row.
OuSpa
r to inspection of the rear spar lower chord, between 6 and Rib 8, the following sealant removal is uired:
nsure that the fillet seal overlap onto the spar chord izontal flange does not extend more than 0.125 es aft of the edge of the fastener collars in the aft
tener row.
nsure that the fillet seal overlap onto the spar chord tical flange does not extend past the centerline of the rest fastener row.
SCRIPTION OF SEALANT REMOVAL AT AREAS ERE INSPECTIONS NEED TO BE PERFORMED
neral Notes
ny sealant that is removed does not need to be pplied except where indicated.
o not remove fillet seals along the edges of parts ess where indicated.
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BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
10. Wing - tboard - Front r Lower Chord idden Details
400ER with stage length < 8 hours 57-538-00 FLS 112T2000 Front Spar Instl - Wing
inspection of the rear spar lower chord, between d Rib 6 and between Rib 8 and Rib 11, the
g sealant removal is required:
re that the fillet seal overlap onto the horizontal rd flange does not extend past the centerline of
rest fastener row.
re that the fillet seal overlap onto the spar chord flange does not extend more than 0.125 inches e edge of the fastener collars on the lower row.
13. WOutboa
Spar Low- Hidde
inspection of the rear spar lower chord, between d Rib 11 at external stiffeners, the following removal is required:
re that the fillet seal overlap onto the spar chord al flange does not extend past the centerline of rest fastener row.
re that the fillet seal and fastener cap seals on chord vertical flange does not extend more than ches below the edge of the fastener collars on r fastener row.
IT
IPTION OF SEALANT REMOVAL AT AREAS INSPECTIONS NEED TO BE PERFORMED
l Notes
ealant that is removed does not need to be d except where indicated.
t remove fillet seals along the edges of parts here indicated.
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
n Details400ER 57-538-00 FLS 112T1000 Rear Spar Instl - Wing
Prior to Rib 3 ansealant
1. Ensuhorizontthe nea
2. Ensuthe spar0.125 inthe lowe
EXCESS SEALANT TABLE
EM AIRPLANE APPLICABILITY
MPD ITEM NO. THRESHOLD
INSTALLATION DRAWING DESCRWHEREGenera
1. Any sreapplie
2. Do nounless w
NUMBER TITLE
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details Page 1.0-34
IONS
OutSu
St
r to inspection of the lower surface splice stringer L-the following sealant removal is required:
etween Rib 7 and Rib 20, ensure that fillet seal rlap onto the splice stringer horizontal flange does extend past the centerline of the nearest fastener .
nder the nacelle fairing, remove fastener cap seals the stringer horizontal flanges. Replace fastener cap ls after inspection.
nder the nacelle fairing, remove fillet seal overlap on splice stringer horizontal flanges.
15. SePa
Strin5 - T
r to inspection of the lower surface stringer L-1, L-2 L-5, the following sealant removal is required:
ure that the fillet seal overlap onto the stringer izontal attach flange does not extend past the terline of the nearest fastener row.
SCRIPTION OF SEALANT REMOVAL AT AREAS ERE INSPECTIONS NEED TO BE PERFORMED
neral Notes
ny sealant that is removed does not need to be pplied except where indicated.
o not remove fillet seals along the edges of parts ess where indicated.
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D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
14. Wing - board - Lower rface Splice
Stringers - ringers L-10
ALL except 200SF and 300BCF 57-540-00
25,000 FC or 80,000 FH whichever comes first
112T4000 Panel Installation - Inspar, Wing, Lower
Prio10
1. Bovenotrow
2. Uon sea
3. Uthe
Wing - Center ction - Lower nel - Typical gers 1, 2, and ypical Details
ALL 53-830-0025,000 FC or
80,000 FH whichever comes first
111T4000 Lower Panel Instl and Assy - Wing, Center Section
Prioand
Enshorcen
EXCESS SEALANT TABLE
ITEM AIRPLANE APPLICABILITY
MPD ITEM NO. THRESHOLD
INSTALLATION DRAWING DEWHGe
1. Area
2. Dunl
NUMBER TITLE
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The imitation supplemental inspection
requ ability, Type and Threshold.
Ther e there is more than one listing for a
give Airplane/engine applicability is listed
as fo
ALL .
PASS s per Landing) less than 8 hours.
200
200S
300 P s per Landing) equal to or more than 8 hours.
300B
300F
400E
4000
7R4
80A
80C
524
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
following pages, included in the Airworthiness Limitations - Structural Inspections table, list the Airworthiness L
irements. Each item is listed by SSI Number, DTR Check Form Title, Inspection Zone, Airplane/Engine Applic
e are corresponding DTR Check Forms (in Document D622T001-DTR) for each item listed in the table. Wher
n SSI Number, the DTR Check Form Title is the unique identifier along with the Airplane/Engine Applicability.
llows
= All Airplanes PASS (-ER ONLY) = Passenger Airplanes, Extended Range Only
2-30-I02A Standard Cargo Door Forward and Aft - Applicable to 767 Airplanes with Standard (70x69) Cargo Doors - 8 Places (At Beams #1, #2, #3, and #4 between Door Sta 184.4 and 189.6 and between Door Sta 208.4 & 213.6)
821, 82230
2-30-I05A Latch Cam Support Frame Fitting - Forward large Cargo Door - Fitting Lug Bore 821
2-30-I05B Latch frame inner chord - Forward large Cargo Door - Latch Frame Inner Chord at Splice to Latch Frame Support Fitting in the area common to intercostal #6
821
2-30-I05C Outer Skin - Forward large Cargo Door - Outer Skin at attachment to main hinge segments at forward and aft ends of the door
821
2-30-I07A Latch Cam Support Fitting - Main Deck Cargo Door - Fitting Lug Bore 838
N 2019
NS
ils Page 1.0-37
52-30 200SFBCF, 300F
Type 130,000 Cycles (300F)
44,900 Cycles (200SF)Mod Date Sensitive (300BCF)
52-30 200SFBCF, 300F
Type 1 44,900 Cycles (200SF)
Mod Date Sensitive (300BCF)30,000 Cycles (300F)
52-30 200SFBCF, 300F
Type 250,000 Cycles (200SF)
Mod Date Sensitive (300BCF)40,000 Cycles (300F)
52-30 200SFBCF, 300F
Type 144,900 Cycles (200SF)
Mod Date Sensitive (300BCF)30,000 Cycles (300F)
52-30 300F Type 240,000 Cycles
52-30 300F Type 130,000 Cycles
52-30 300F Type 130,000 Cycles
53-10 ALL Type 250,000 Cycles (200, 300 PASS,
300BCF)40,000 Cycles (300F, 400E)
SS
PLANE/NGINE ICABILITY TYPE AND THRESHOLD
JUN 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
-I07B Latch Frame Inner Chord - Main Deck Cargo Door - Latch Frame Inner Chord at Splice to Latch Frame Support Fitting in the area common to intercostal #11
838300
-I07C Outer Skin - Main Deck Cargo Door - Outer Skin at attachment to main hinge segments at forward and aft ends of the door
-I09A Latch Cam Support Fitting - Aft large Cargo Door - Fitting Lug Bore 822
-I09B Latch Frame Inner Chord - Aft large Cargo Door - Latch Frame Inner Chord at Splice to Latch Frame Support Fitting in the area common to intercostal #6
822
-I09C Outer Skin - Aft large Cargo Door - Outer Skin at attachment to main hinge segments at forward and aft ends of the door
822
-I06A Outflow Valve Cutout DoublerBS 400 to BS 410, S-35L to S-36L
Note: Only applicable to aircraft configured at delivery with the subject structure.
5 200SF, 300BCF Type 250,000 Cycles (200SF, 300BCF)
SAIRPLANE/
ENGINE PPLICABILITY TYPE AND THRESHOLD
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
3-10-I07A3-30-I04A3-60-I05A
Skin Longitudinal Lap Splices - Upper Row - Crown and Upper Lobe, Sections 41, 43 and 46
Inspection requirements are altered for the following locations:1) 767-300BCF: S-8L STA 654+22 to 654+110 and S-8R, STA 434 to 654+22. See additional entries for SSI # 53-30-I04A. 2) 767-200BCF: S-2R 654+22 to 654+110. No inspection required. 3) L/N 1-1068 (except 300F): S-2R STA 368 to 434. Must inspect per SB 767-53A0260.4) L/N 1069 and on (767-300 only): S-2R STA 368 to 434. Inspect lap splice upper skin at upper fastener row externally using HFEC inspection per 767 NDT manual Part 6, 51-00-01. Threshold: 43,000 flight cycles. Repeat interval: 9,000 flight cycles.
220, 230, 250
3-10-I07B3-30-I04B3-60-I05B
Skin Longitudinal Lap Splices - Lower Row - Crown and Upper Lobe, Sections 41, 43 and 46
Inspection requirements are altered for the following locations:1) 300BCF: S-8R, STA 434 to 654+22; S-8L, STA 654+22 to 654+110. See additional entries for SSI # 53-30-I04B.2) 200SF: S-8R, STA 434 to 676. See additional entry for SSI # 53-30-I04B.3) 300BCF: S-2R, STA 654+22 to 654+110. No inspection required.
220, 230, 250
3-10-I07C3-30-I04C3-60-I05C
Skin Longitudinal Lap Splices - Upper Row - Bilge and Lower Lobe, Sections 41, 43 and 46
Not applicable to 300BCF and 200SF, S-37R, STA 368 to 434. No inspection required at these locations.
100
3-10-I07D3-30-I04D3-60-I05D
Skin Longitudinal Lap Splices - Lower Row - Bilge and Lower Lobe, Sections 41, 43 and 46
Inspection requirements are altered for the following locations:1) 300BCF: STA 434 to 654+110, S-26L. See additional entry for SSI # 53-30-I04D BCF1.2) 200SF: STA 434 to 676, S-26L. See additional entry for BCF1 SSI # 53-30-I04D.
100
3-10-I08B3-30-I24B
Frames - Above S-20For 200 Pass: From BS 246 to BS 786, S-20L to S-20RFor 300 Pass: From BS 246 to BS 654, S-20L to S-20RFor 300F and 400E: From BS 246 to BS 434, S-20L to S-20R
220, 230 A
3-10-I08B BCF3 Frames - Above S-20BS 246 to BS 412
220, 230
AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTION
SSI # DTR CHECK FORM TITLEINSPECTION
ZONE A
L 2018
NS
ils Page 1.0-39
53-1053-3053-60
L Except F, 300BCF
Type 250,000 Cycles (200, 300 PASS)
40,000 Cycles (300F, 400E)53-1053-3053-60
F, 300BCF Type 250,000 Cycles (200SF, 300BCF)
53-10 ALL Type 250,000 Cycles
(200, 300 PASS)40,000 Cycles
(200SF, 300BCF, 300F, 400E)53-10 ALL Type 2
50,000 Cycles (200, 300 PASS)
40,000 Cycles (200SF, 300BCF, 300F, 400E)
53-10 ALL Type 250,000 Cycles
(200, 200SF, 300BCF,300 PASS)
40,000 Cycles (300F, 400E)
53-10 ALL Type 250,000 Cycles
(200, 200SF, 300BCF, 300 PASS)
40,000 Cycles (300F, 400E)
SS
PLANE/NGINE ICABILITY TYPE AND THRESHOLD
JUN 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
-I08C-I24C-I08C
Frames - S-20 and BelowBS 246 to BS 786 and BS 1065 to BS 1582
100 AL200S
-I08C-I24C-I08C
BCF5 Frames - S-20 and BelowBS 246 to BS 786 and BS 1065 to BS 1582For additional inspections required at locations with partially visible frame structure, see entry for BCF6 SSI # 53-30-I24C / 53-60-I08C.
100 200S
-I10A Forward Passenger Entry/Service Door Cutout- Edge Frame - Inner Chord Door STA 76.3, S-7 to S-12 and S-19 to S-23Door STA 123.7, S-8 to S-12 and S-19 to S-23
119, 221, 222, 223, 224
-I10B Forward Passenger Entry/Service Door Cutout- Upper Main Sill - Inner Chord BS 287 to Door STA 89
221, 222
-I12 Main Equipment Center Access Door CutoutBS 303 - BS 325, LBL 13.1 - RBL 13.1
119
-I13 Forward Equipment Bay Access Door Cutout - BS 144.5 - BS 163.2. LBL 9 - RBL 9 113, 114
3-10-I16 Window #2 Cutout Structure - EF POST 211, 212
3-10-I18A Nose Landing Gear Wheel Well - Canted Bulkhead Details - Outer Chord Typical Locations Between S-32L & S-32R
113, 114
3-10-I18B Nose Landing Gear Wheel Well - Canted Bulkhead Details - Outer Chord Hidden Locations L/RBL 10.60 & L/RBL 25.00
113, 114
AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTION
SSI # DTR CHECK FORM TITLEINSPECTION
ZONE A
N 2019
NS
ils Page 1.0-41
53-10 ALL Type 150,000 Cycles
(200, 300 PASS)40,000 Cycles
(200SF, 300BCF, 300F, 400E)53-10 ALL Type 1
50,000 Cycles (200, 200SF, 300BCF,
300 PASS)40,000 Cycles (300F, 400E)
53-10 ALL<2>
Type 150,000 Cycles
(200, 300 PASS)40,000 Cycles
(200SF, 300BCF, 300F, 400E)53-10 ALL
/N 1-757<2>
Type 150,000 Cycles
(200, 300 PASS)40,000 Cycles
(200SF, 300BCF, 300F) 53-10 ALL
758 and on<2>
Type 150,000 Cycles (200, 300 PASS)
40,000 Cycles (300F, 400E)
53-10 ALL Type 150,000 Cycles
(200, 200SF, 300BCF, 300 PASS)
40,000 Cycles (300F, 400E)
SS
PLANE/NGINE ICABILITY TYPE AND THRESHOLD
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
-I20A Nose Landing Gear Wheel Well - BL25 Side Panel Details - Vertical Beams & Panel Web from BS 180.5 to BS 276
117, 118
-I20B Nose Landing Gear Wheel Well - Trunnion Support Fitting at Top Panel Beam Attachment. BS 276, BL 30, WL 181 to WL 187
117, 118
-I20C Nose Landing Gear Wheel Well - Trunnion Support Fitting at Strap Attachment BS 276, BL 30, WL 165 to WL 169
117, 118
-I21A Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - WL 159 Beam & Bulkhead Web from LBL 27 to LBL 23, LBL 10.0 to RBL 10.0, RBL 23 to RBL 27Applicable to 767 Line Numbers 1 - 757.For Line Numbers 758 and on: See additional entries for SSI # 53-10-I21A and 53-10-I21E.
119L
-I21A Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - WL 159 Beam & Bulkhead Web from LBL 10.0 to RBL 10.0Applicable to 767 Line Numbers 758 and on.For Line Numbers 1-757: See additional entry for SSI # 53-10-I21A.
119L/N
-I21B Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - Outer Chord Typical Locations between S-24L and S-24R
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
3-10-I21C Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - Outer Chord - Stringer Splices between S-24L and S-24R
119
3-10-I21D Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - Outer Chord Hidden Locations at S-36L, S-36R and S-27R
119
3-10-I21E Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - WL 159 Beam and Bulkhead Web LBL 27 to LBL 23 and RBL 23 to RBL 27Applicable to 767 Line Numbers 758 and on.For Line Numbers 1-757: See entry for SSI # 53-10-I21A.
119
3-10-I32A T.C.A.S. Antenna Cutout DoublerBS 368 to BS 390, S-1L to S-1R
Note: Only applicable to aircraft configured at delivery with the subject structure.
223, 224
3-10-I32B T.C.A.S. Antenna Cutout DoublerBS 390 to BS 412, S-39L to S-39R
Note: Only applicable to aircraft configured at delivery with the subject structure.Not applicable to 767-200SF or 767-300BCF airplanes with external service panel doubler installed between BS 368 and BS 434.
123, 124
3-10-I33B BCF2 - Section 41 External Skin Doubler first fastener common to skin and doubler between BS 368 and BS 434 at S-38L
121
3-10-I33E BCF5 - Section 41 Service Panel Cutout Structure BS 390 to BS 412; BL 0 toRBL 13.65
121
AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTION
SSI # DTR CHECK FORM TITLEINSPECTION
ZONE A
N 2019
NS
ils Page 1.0-43
53-1053-3053-60
ALL Type 250,000 Cycles (200, 200SF, 300
PASS, 300BCF)40,000 Cycles (300F, 400E)
53-3053-5053-60
ALL t where noted
for and 300BCF
Type 250,000 Cycles
(200, 200SF, 300BCF, 300 PASS)
40,000 Cycles (300F, 400E)
53-30 00BCF<4>
Type 250,000 Cycles
53-30 00BCF<4>
Type 1Combined Threshold
53-30 00BCF<4>
Type 250,000 Cycles
53-30 00BCF<4>
Type 250,000 Cycles
53-30 00BCF Type 250,000 Cycles
53-30 00BCF Type 2Combined Threshold
53-30 200SF<4>
Type 250,000 Cycles
53-30 200SF<4>
Type 230,000 Cycles
SS
PLANE/NGINE ICABILITY TYPE AND THRESHOLD
JUN 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
-I34-I29-I31
Pressurized Door CutoutsForward and aft lower corners of door cutoutsApplicable to Forward Passenger Entry/Service Doors, Mid Passenger Entry/Service Doors, Aft Passenger Entry/Service Doors, Bulk Cargo Door, Forward Main Cargo Door, Aft Main Cargo Door, Forward Large Cargo Door, Aft Large Cargo Door, and Main Deck Cargo Door
Fuselage Crown Stringers - BS 654 to BS 1395, S-8L to S-8RNot applicable to:1) 200SF: from BS 676 to 786 at stringers S-2R and S-3R, from BS 742 to 786 at stringers S-1R to S-5L. See additional entry for SSI # 53-30-I01, SF10.2) 300BCF: from BS 654+110 to 786 at stringers S-4L to S-4R. See additional entry for SSI # 53-30-I01, BCF10.
230, 240, 250Excep
200SF
-I01 BCF1 - Crown Doubler, BS 654+28 to 654+115, S-6L to S-8L and S-6R to S-8R 231, 232 3
3-30-I04A Skin Longitudinal Lap Splices - Upper Row - Crown and Upper Lobe, Section 43 Applicable to S-8R, STA 434 to 654 + 22.
230
3-30-I04A BCF2 Skin Longitudinal Lap Splices - Upper Row - Upper LobeApplicable to S-8L, STA 654 + 22 to 654 + 110.
230
3-30-I04B Skin Longitudinal Lap Splices - Lower Row - Crown and Upper Lobe, Section 43Applicable to S-8L, STA 654 + 22 to 654 + 110.
230
3-30-I04B Skin Longitudinal Lap Splices - Lower Row - Crown and Upper Lobe, Section 43200SF: Applicable to S-8R, STA 434 to 676.300BCF: Applicable to S-8R, STA 434 to 654+22.
230
3-30-I04D BCF1 - Skin Longitudinal Lap Splices - Lower Row - Bilge S-26L MDCD and L2 Panel200SF: Applicable to S-26L, STA 434 to 676.300BCF: Applicable to S-26L, STA 434 to 654+110.
100
3-30-I05 Circumferential Splice in the Body CrownApplicable to BS 786 S-7L to S-7R.
240
AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTION
SSI # DTR CHECK FORM TITLEINSPECTION
ZONE A
N 2019
NS
ils Page 1.0-45
53-3053-3053-3053-5053-6053-60
200 Type 150,000 Cycles
53-3053-3053-3053-5053-6053-60
F, 300 PASS, Type 150,000 Cycles
53-3053-3053-3053-5053-6053-60
300Fpt as noted
Type 140,000 Cycles
53-3053-3053-3053-5053-6053-6053-6053-60
400E Type 140,000 Cycles
53-3053-50
300F070 and on<3>
Type 140,000 Cycles
53-3053-50
300F070 and on
Type 140,000 Cycles
53-30 300F108 and on
Type 140,000 Cycle
SS
PLANE/NGINE ICABILITY TYPE AND THRESHOLD
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
-I05-I21-I27-I03-I03-I26
Fuselage Circumferential Splices in the Body Crown 230, 240, 250
-I05-I21-I27-I03-I03-I26
Fuselage Circumferential Splices in the Body Crown
Note: For 767-300BCF, STA 654+22, see additional entry for SSI # 53-30-I27
230, 240, 250 300BC
-I05-I21-I27-I03-I03-I26
Fuselage Circumferential Splices in the Body Crown
Not applicable to 767-300F Line Numbers 1070 and on, BS 786 and BS 1065. See additional entries for SSI # 53-30-I05A / 53-50-I03A and 53-30-I05B / 53-50-I03B
230, 240, 250Exce
-I05-I08-I21-I03-I03-I04-I24-I33
Fuselage Circumferential Splices in the Body Crown 230, 240, 250
-I05A-I03A
Fuselage Circumferential Splices In the Body Crown - BS 1065 and BS 785.9, S-4L/R to S-5L/R
230, 240, 250L/N 1
-I05B-I03B
Fuselage Circumferential Splices In the Body Crown - BS 1065 and BS 785.9, S-13L to S-13R
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
3-30-I24A3-50-I01A3-50-I02A3-60-I08A
Frames - Above S-20For 200 PASS: From BS 786 to BS 1582, S-20L to S-20R.For 300 PASS: From BS 654 to BS 1582, S-20L to S-20R.For 300F and 400E: From BS 434 to BS 1582, S-20L to S20R.
230, 240, 250 A
3-30-I24A3-30-I24B3-60-I08A
Frames - (Partially Visible) - Above S-20BS 434 to BS 786 and BS 1065 to BS 1582For additional frame inspection requirements, see entry for 200SF SSI # 53-30-I24A / 53-30-I24B / 53-50-I01A / 53-50-I02A / 53-60-I08A.
230, 240, 250
3-30-I24A3-30-I24B3-50-I01A3-50-I02A3-60-I08A
BCF1 Frames - Above S-20BS 434 to BS 1582For additional inspections required at locations with partially visible frame structure, see entry for BCF2 SSI # 53-30-I24A / 53-30-I24B.
231, 232
3-30-I24A3-30-I24B3-50-I01A3-50-I02A3-60-I08A
Frames - Above S-20BS 434 to BS 1582For additional inspections required at locations with partially visible frame structure, see entry for 200SF SSI # 53-30-I24A / 53-30-I24B / 53-60-I08A.
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
-I10 BCF2 - Bulk Cargo Door Cutout - Aft Edge Frame BS 1461 Inner ChordS-22L to S-22.5L
161, 163 3
-I10 SF2 - Bulk Cargo Door Cutout - Aft Edge Frame BS 1461 Inner ChordS-20L to S-22.5L
161, 163
-I10A Bulk Cargo Door Cutout - Edge Frames Inner Chord200SF and 300BCF: See entries for SSI # 53-60-I10 for additional inspections at BS 1461, S-22L to S-22.5L
161, 163
-I10B Bulk Cargo Door Cutout - Frame Splice - Aft Edge Frame, BS 1461 Inner Chord at S-26 161
-I10C Bulk Cargo Door Cutout - Upper Main Sill Inner Chord - BS 1458 to BS 1464 161
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
3-60-I27C Type I Emergency Exit Door Cutout - Lower Main Sill - Inner Chord, BS 1131 to BS 1175
251, 252
3-60-I29A Aft Large Cargo Door Cutout - Edge Frame - Inner Chord, BS 1344Between S-24R and S-26R
154
3-60-I29B Aft Large Cargo Door Cutout - Edge Frame - Inner Chord, BS 1344Between S-24R and S-26R
154
3-60-I29C Aft Large Cargo Door Cutout - Upper Main Sill - Inner Chord, BS 1219 154
3-60-I29D Aft Large Cargo Door Cutout - Lower Main Sill - Inner Chord, BS 1342 to BS 1348 154, 156
3-60-I30A Aft Large Cargo Door Cutout - Latch Backup Fitting - Latch 12 156
3-80-I01A Aft Pressure Bulkhead - Circumferential Attachment of Web to Y-RingFor Line Numbers 1 to 423, equivalent inspections are included in Service Bulletins. See applicable Service Bulletins for inspection requirements.
165, 166, 251, 252, 253, 254
3-80-I01B BS 1582 Pressure Bulkhead - Radial Web Lap Splices - BS 1582 (Fwd Web)For Line Numbers 1 to 423, equivalent inspections are included in Service Bulletins. See applicable Service Bulletins for inspection requirements.
311, 312
3-80-I01C BS 1582 Pressure Bulkhead - Radial Web Lap Splices - BS 1582 (Aft Web)For Line Numbers 1 to 423, equivalent inspections are included in Service Bulletins. See applicable Service Bulletins for inspection requirements.
311, 312
3-80-I01D BS 1582 Pressure Bulkhead - Circumferential Tear Strap Splices - BS 1582 (Fwd Tear Strap)For Line Numbers 1 to 423, equivalent inspections are included in Service Bulletins. See applicable Service Bulletins for inspection requirements.
311, 312
AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTION
SSI # DTR CHECK FORM TITLEINSPECTION
ZONE A
N 2019
NS
ils Page 1.0-57
53-80 ALL 424 & on
Type 250,000 Cycles
(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)
53-80 200SF Type 150,000 Cycles
53-80 BCF, 300FPASS
Type 150,000 Cycles
(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)
53-80 200SF Type 138,600 Cycles
53-80 BCF, 300FPASS
Type 150,000 Cycles
(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)
53-8053-8053-80
ALL 710 & on
Type 125,000 Cycles
53-80 ALL Type 125,000 Cycles
54-50 7R4<2>
Type 250,000 Cycles
54-50 4000<2>
Type 225,000 Cycles
54-50 80A Type 250,000 Cycles
54-50 xcept 400E)<2>
Type 250,000 Cycles (200, 300 PASS)
40,000 Cycles (300F)
SS
PLANE/NGINE ICABILITY TYPE AND THRESHOLD
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
-I01E BS 1582 Pressure Bulkhead - Circumferential Tear Strap Splices - BS 1582 (Aft Tear Strap)For Line Numbers 1 to 423, equivalent inspections are included in Service Bulletins. See applicable Service Bulletins for inspection requirements.
BS 1809.5 Bulkhead Outboard ChordFor Line Numbers 1 to 709: Inspect per Service Bulletin 767-53A0078, Revision 6 or later.
313, 314L/N
-I25 Horizontal Stabilizer Fitting Hinge Pins - BS 1809, BL 41.5Note: For Line Numbers 1 to 98: If terminating action per Service Bulletin 767-55-0005 has been accomplished, the inspection threshold is 25,000 cycles from accomplishment of terminating action.
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
7-10-I01 Skin at Typical Stringer - Wing Center Section, Lower Surface at External Lower Beams (BBL 9.5 and BBL 62.0)
133, 134
7-10-I01A Wing Center Section Wet Bay - Upper and Lower Surfaces, Front and Rear Spar, Spanwise Beams and Access Door Cutouts, Lower Surface Beams, Side of Body Ribs, Splices, Lower Surface Access Hole Cutout and Adjacent Stringers, and Drain
133,134
7-10-I01B Wing Center Section - Upper and Lower Surfaces, Rear Spar, Beams and Access Door Cutouts, Lower Surface Beams, Side of Body Ribs, Splices, Lower Surface Access Hole Cutout and Adjacent Stringers, and Drain
133, 134
-10-I01C.1 Typical Stringer - Wing Center Section - Typical - In Areas of Attach Fasteners Between Left and Right WBL 97.9
133, 134
-10-I01C.2 Typical Stringer and Skin - Wing Center Section - Lower Surface - Stringers 1, 2 and 5 at External Beams (BL 9.5 and BL 62)
133, 134,135, 136
7-10-I02 Splice Stringer - Wing Center Section at Stringer 6 and 10 133, 134
7-10-I02 Splice Stringer - Wing Center Section at Stringer 6 and 10 133, 134
7-10-I02 Splice Stringer - Wing Center Section at Stringer 6 and 10 133, 134
7-10-I02A Front Spar Lower Chord and Skin - Wing Center Section at Radius Fillers 133, 134 A
7-10-I02A Front Spar Lower Chord and Skin - Wing Center Section at Radius Fillers 133, 134 A
7-10-I02B Skin at Front Spar Lower Chord - Wing Center Section at Underwing Longeron 193, 194
7-10-I02B Skin at Front Spar Lower Chord - Wing Center Section at Underwing Longeron 193, 194
AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTION
SSI # DTR CHECK FORM TITLEINSPECTION
ZONE A
L 2018
NS
ils Page 1.0-67
57-10 00BCF Type 150,000 Cycles/70,000 Flt. Hrs.
<5>57-10 200SF Type 1
50,000 Cycles/70,000 Flt. Hrs.
57-10 PASS ER, 300ER) enter section
fuel 8 Hours
Type 125,000 Cycles/80,000 Flt. Hrs.
57-10 PASS ER, 300ER)enter section
fuel 8 Hours
Type 125,000 Cycles/80,000 Flt. Hrs.
57-10 300F Type 125,000 Cycles/80,000 Flt. Hrs.
57-10 400E 8 Hours
Type 125,000 Cycles/80,000 Flt. Hrs.
57-10 400E 8 Hours
Type 125,000 Cycles/80,000 Flt. Hrs.
57-10 200SF00BCF
Type 125,000 Cycles/70,000 Flt. Hrs.
<6>57-10 PASS
ER, 300ER)enter section
fuel 8 Hours
Type 125,000 Cycles/80,000 Flt. Hrs.
SS
PLANE/NGINE ICABILITY TYPE AND THRESHOLD
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
-I02C Wing Center Section - Lower Surface Splice Stringers L-6 and L-10 in Areas of Attach Fasteners Between Left and Right WBL 97.9
133, 134 3
-I02D Wing Center Section - Lower Surface Splice Stringers L-6 and L-10 in Areas of Attach Fasteners Between Left and Right WBL 97.9
133, 134
-I03A Rear Spar Lower Chord - Wing Center Section - Typical - BBL 23.0 to Inboard Edge of Terminal Fitting
133, 134(200
with c
<-I03A Rear Spar Lower Chord - Wing Center Section - Typical - BBL 23.0 to Inboard Edge of
Terminal Fitting133, 134
(200with c
>-I03A Rear Spar Lower Chord - Wing Center Section - Typical - BBL 23.0 to Inboard Edge of
Terminal Fitting133, 134
-I03A Rear Spar Lower Chord - Wing Center Section - Inboard Edge of Left Terminal Fitting to Inboard Edge of Right Terminal Fitting
133, 134<
-I03A Rear Spar Lower Chord - Wing Center Section - Inboard Edge of Left Terminal Fitting to Inboard Edge of Right Terminal Fitting
133, 134>
-I03A Rear Spar Lower Chord - Wing Center Section - Typical - BBL 23.0 to Inboard Edge of Terminal Fitting
133, 1343
-I03B Rear Spar Lower Chord - Wing Center Section - Hidden Locations - BBL 49.5, 62.05 and 73.0
<2> res are validated, published in the appropriate manual,
<3> ocedures are validated, published in the appropriate
<4> icable inspection procedures are validated, published
<5> curs later, not to exceed 50,000 total Flight Cycles and
<6> curs later, not to exceed 25,000 total Flight Cycles and
SAIRPLANE/
ENGINE PPLICABILITY TYPE AND THRESHOLD
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
7-54-I03A Load Distribution Plates, Flange around Outboard Upper Lug 552, 652
7-54-I03B Load Distribution Plates, Flange around Outboard Lower Lug 552, 652
7-54-I03C Load Distribution Plates, Flange around Inboard Lug. 552, 652
7-54-I03D Load Distribution Plates, Flange except in the Lug areas covered by SSI 57-54-I03A, 57-54-I03B and 57-54-I03C
552, 652
7-54-I04 Main Landing Gear Beam, Outboard Pin 552, 652
7-54-I13 Main Landing Gear Forward Trunnion Support - Side Load Fitting - Side Load Fitting to Strap Inboard Fastener Row
551, 651
7-54-I14 Main Landing Gear Forward Trunnion Support - Side Load Strap - First Fastener Row Either Side of Trunnion
551, 651
This flagnote is no longer being used.
No 767 airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedu and accepted by the FAA.
No 767-300F airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection pr manual, and accepted by the FAA.
No 767-300BCF and 767-200SF airplane may be operated beyond the stated threshold (or operational limit) until the appl in the appropriate manual, and accepted by the FAA.
Threshold is 50,000 Flight Cycles / 70,000 Flight Hours or 8,000 Flight Hours after conversion to 767-300BCF, whichever oc78,000 total Flight Hours.
Threshold is 25,000 Flight Cycles / 70,000 Flight Hours or 8,000 Flight Hours after conversion to 767-300BCF, whichever oc78,000 total Flight Hours.
AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTION
SSI # DTR CHECK FORM TITLEINSPECTION
ZONE A
L 2018
NS
ils Page 1.0-93
C. AIRW
LIFE LIMIT
80,000 Landings *
70,000 Landings *
90,000 Landings *
80,000 Landings **
50,000 Landings **
62,000 Landings **
90,000 Landings **
80,000 Landings **
50,000 Landings **
36,800 Landings **
31,800 Landings **
50,000 Landings **
16,175 Landings **
se Landing Gear Component
airplanes.
LIFE LIMIT TO INCORPORATION
9,000 Landings
18,000 Landings
30,000 Landings
FEB 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
ORTHINESS LIMITATIONS - STRUCTURAL SAFE LIFE PARTS
ITEM767-200, 767-200SF Nose Landing Gear
767-200, 767-200SF Main Landing Gear
767-200, 767-200SF Main Landing Gear Support Structure
767-300, 767-300BCF, 767-300F Nose Landing Gear
767-300, 767-300BCF, 767-300F Main Landing Gear
767-300, 767-300BCF, 767-300F Main Landing Gear Support Structure
767-300, 767-300BCF, 767-300F Main Landing Gear Retract Actuator Fitting and Pin
767-400ER Nose Landing Gear
767-400ER Main Landing Gear
767-400ER Main Landing Gear Inner Cylinder 161T7120
767-400ER Main Landing Gear Outer Cylinder 161T7110
NOTE: Service Letter 767-SL-32-092 (Latest Revision) and its reference Boeing Drawing 160T0002, 767 Main and No Interchangeability List, identify the 767 landing gear and support structure safe-life (life limited) parts. * These values are based on completed fatigue tests and incorporation of the following Service Bulletins on applicable** These values are based on completed fatigue tests and analysis.
SERVICE BULLETIN NUMBER DESCRIPTION PRIOR
767-32-44 MLG Upper Spindle-Drag Strut, Part # 161T6007
767-32-45 MLG Outer Cylinder Assembly, Part # 161T1110
767-32-46 MLG Upper Bulkhead-Shock Strut, Part # 16T1161
15
details Page 1.0-94
IONS
e:
LIFE LIMIT30,000 Landings ***
30,000 Landings ***
50,000 Landings ***
FE
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
The following data is applicable to the Rolls-Royce RB211-524H engine mounts for use on the 767-300 airplan
ITEM767-300 Front Mount Pylon Mounting Bracket
767-300 Front Mount Center Thrust Link And Associated Hardware
767-300 Rear Mount Pylon Bracket
*** These values are based on completed Safe-Life testing and analysis.
B 2015
NS
ils Page 1.0-95
D. AWL
This ndment 26-6). This regulation requires
the e ce program that corresponds to the
perio strated that widespread fatigue damage
will n Sections 121.1115 and 129.115 for
the 7
HOUR LOV
0,000
0,000
DEC 2
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
s - STRUCTURAL LIMIT OF VALIDITY (LOV)
section provides the Limit of Validity (LOV) in accordance with the requirements of Title 14 CFR § 26.21 (Ame
stablishment of an airplane level limit of validity of the engineering data that supports the structural maintenan
d of time, stated as a number of total accumulated flight cycles or flight hours or both, during which it is demon
ot occur in the airplane. The LOVs listed in the following table support operator compliance with Title 14 CFR
67.
LIMIT OF VALIDITY
MODEL FLIGHT CYCLE LOV FLIGHT
767-200*767-300** 75,000 18
767-300F767-400ER 60,000 18
* 767-200 LOV applies to 767-200SF**767-300 LOV applies to 767-300BCF
015
details Page 1.0-96
IONS
BL
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
THIS PAGE INTENTIONALLY LEFT BLANK
ANK
NS
ils Page A.0-1
A. SCOP
This the airplane reaching the fatigue
thres mage Tolerance Requirements.
As s and Zonal Inspection interval in the
Ope
The ment.
JUN 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
APPENDIX A – STRUCTURES BASELINE REQUIREMENTS
E
appendix provides operators with the Baseline Structures and Zonal Inspection tasks that must be used upon
hold. This must be done in order to ensure the maintenance program complies with Title 14 CFR § 25.571 Da
uch, when reaching the threshold the inspection interval must be the lesser of: 1) the FAA approved Structural
rator baseline inspection program or 2) the inspection interval contained in this appendix.
structures A-check and C-check interval, when reaching threshold, is defined in Section B of the baseline docu
19
ls Page A.0-2
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D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for detaiEXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
THIS PAGE INTENTIONALLY LEFT BLANK
NS
ils Page A.1-1
B. STRU
MPD INUMB INTERVAL APPLICA-
BILITY ENG
52-40 3000 FC18 MO ALL ALL
52-40 3000 FC18 MO ALL ALL
52-41 3000 FC18 MO ALL ALL
52-41 12000 FC72 MO
PASS200SF
300BCFALL
52-41 3000 FC18 MO
PASS200SF
300BCFALL
52-41 3000 FC18 MO
ALLNOTE ALL
52-42 3000 FC18 MO
ALLNOTE ALL
52-42 12000 FC72 MO 300F ALL
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
CTURES BASELINE INSPECTION REQUIREMENTS
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
2-00 EXTERNAL - GENERAL VISUAL: Bulk Cargo Compartment DoorBulk cargo compartment door external surface, frame, hinges, and stops.
6-00EXTERNAL - GENERAL VISUAL: Forward Cargo Compartment DoorLarge forward cargo door external surface and frame including hinges, latches, and fittings.Standard (70x69) Forward Cargo Door external surface and frames including hooks and door stops.
0-00EXTERNAL - GENERAL VISUAL: Aft Cargo DoorLarge Aft Cargo Door external surface and frame including hinges, latches, and fittings.Standard (70x69) Aft Cargo Door external surface and frames including hooks and door stops.
2-00INTERNAL - GENERAL VISUAL: Entry & Galley Service DoorsEntry and galley service doors internal beams and frames.
ACCESS NOTE: Passenger airplanes: Zone and access defined by each operator's door configuration.
6-00EXTERNAL - GENERAL VISUAL: Entry & Galley Service DoorsEntry and galley service door external surface, frame, latches, and continuous stops.
ACCESS NOTE: Passenger airplanes: Zone and access defined by each operator's door configuration.
8-00EXTERNAL - GENERAL VISUAL: Overwing Emergency Exit HatchOverwing emergency hatch external surface, frame, latch and stops.
AIRPLANE NOTE: Airplanes with overwing escape hatch configurations, including deactivated hatches.
2-00EXTERNAL - GENERAL VISUAL: Emergency Exit DoorEmergency exit door external surface, frame, latch, and stops.
AIRPLANE NOTE: Airplanes with emergency exit door.
4-00 INTERNAL - GENERAL VISUAL: Crew Entry DoorCrew entry door internal beams and frames.
18
details Page A.1-2
IONS
5 3000 FC18 MO 300F ALL
5 3000 FC18 MO
200SF300F
300BCFALL
5 24000 FH72 MO ALL ALL
5 24000 FH72 MO
ALLNOTE ALL
5 24000 FH72 MO
ALLNOTE ALL
5 24000 FH72 MO
ALLNOTE ALL
5 24000 FH72 MO
ALLNOTE ALL
5 24000 FH72 MO
ALLNOTE ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
2-428-00 EXTERNAL - GENERAL VISUAL: Crew Entry DoorCrew entry door external surface, frame, latches, and continuous stops.
2-430-00 EXTERNAL - GENERAL VISUAL: Main Deck Cargo DoorMain deck cargo door external surface and frame including hinges, latches, and fittings.
2-800-00INTERNAL - ZONAL (GV): Bulk Cargo Compartment DoorPerform internal general visual inspection of zone.
CPC NOTE: Corrosion Prevention and Control Basic Task required.
2-806-00
INTERNAL - ZONAL (GV): Forward Cargo Compartment DoorPerform internal general visual inspection of zone.
CPC NOTE: Corrosion Prevention and Control Basic Task required.AIRPLANE NOTE: Airplanes with large forward cargo door.
2-808-00
INTERNAL - ZONAL (GV): Forward Cargo Compartment DoorPerform internal general visual inspection of zone.
CPC NOTE: Corrosion Prevention and Control Basic Task required.AIRPLANE NOTE: Airplanes with standard forward cargo door.
2-812-00
INTERNAL - ZONAL (GV): Aft Cargo Compartment DoorPerform internal general visual inspection of zone.
CPC NOTE: Corrosion Prevention and Control Basic Task required.AIRPLANE NOTE: Applicable to airplanes with Standard (70 x 69) Aft Cargo Door.
2-814-00
INTERNAL - ZONAL (GV): Aft Cargo Compartment DoorPerform internal general visual inspection of zone.
CPC NOTE: Corrosion Prevention and Control Basic Task required.AIRPLANE NOTE: Airplanes with large aft cargo door.
2-824-00
INTERNAL - ZONAL (GV): Overwing Emergency Exit Hatches - Left / RightPerform internal general visual inspection of the zones.
CPC NOTE: Corrosion Prevention and Control Basic Task required.AIRPLANE NOTE: Dual overwing emergency exit configuration.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
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ils Page A.1-3
52-82
24000 FH72 MO
200200SFNOTE
ALL
52-83 24000 FH72 MO
300NOTE ALL
52-84 24000 FH72 MO
200SF300F
300BCFALL
52-84 24000 FH72 MO
300400ENOTE
ALL
53-40NOT
, areas of llations) and S 1C ALL ALL
53-40NOT S 1A ALL ALL
53-40 S 1C ALLNOTE ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
6-00
INTERNAL - ZONAL (GV): Overwing Emergency Exit Hatches - Left / RightPerform internal general visual inspection of zone.CPC NOTE: Corrosion Prevention and Control Basic Task required.
AIRPLANE NOTE: 767-200 Airplanes with single overwing emergency exit configuration and 200SF airplanes withdeactivated single overwing emergency exit configuration.
2-00
INTERNAL - ZONAL (GV): Overwing Emergency Exit Hatches - Left / RightPerform internal general visual inspection of zone.
CPC NOTE: Corrosion Prevention and Control Basic Task required.AIRPLANE NOTE: 767-300 Airplanes with single overwing emergency exit configuration.
0-00INTERNAL - ZONAL (GV): Main Deck Cargo Compartment DoorPerform internal general visual inspection of zone.
CPC NOTE: Corrosion Prevention and Control Basic Task required.
8-00
INTERNAL - ZONAL (GV): Emergency Exit Door - Left / RightPerform internal general visual inspection of the zone.
CPC NOTE: Corrosion Prevention and Control Basic Task required.AIRPLANE NOTE: 767-300 and 767-400ER airplanes with emergency exit doors.ACCESS NOTE: Remove emergency door lining/insulation.
0-91E
EXTERNAL - GENERAL VISUAL: Lower Half Of Fuselage - ExteriorBody external skin between Body Station (BS) 132.5 and BS 1582 in major zone 100 with attention to: skin splicesattachments to BS 955.1 bulkhead, and areas within 12 inches of all cutouts (doors, hatches and equipment instaall antenna locations.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-800-00.
6-91E
EXTERNAL - GENERAL VISUAL: Door Stops, Sills, and FramesDoor stops, sills, frames, and body external skin within 22 inches around door cutouts.
ACCESS NOTE: According to each operator's door configuration. Not applicable to deactivated doors.NOTE: This inspection can be accomplished concurrently with MPD item number 53-406-00.
8-00EXTERNAL - DETAILED: Large Forward Cargo Door HingesLarge forward cargo door hinges.
AIRPLANE NOTE: Airplanes with large forward cargo door.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-4
IONS
5 including door S 1C ALL ALL
5 S 4C ALL ALL
5 168.5/188.5 S 2C ALL ALL
5 S 1C ALL ALL
5 orward S 4C ALL ALL
5 s, nose landing S 1C ALL ALL
5 the gear S 4C ALL ALL
5 bulkhead and S 4C ALL ALL
5 nd frames from S 4C ALL ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
3-412-00EXTERNAL - DETAILED: Door Stops and CutoutsDoor stops (if installed) and visible adjacent cutout structure within aircraft contour at all cargo door locations sills and frame chords.
3-414-00 INTERNAL - DETAILED: Body Station 132.5 BulkheadBody Station (BS) 132.5 Bulkhead.
3-416-91NOTE
INTERNAL - GENERAL VISUAL: Fuselage Lower LobeControl cabin floor beams, aft side of Body Station (BS) 132.5 bulkhead, and entire forward side of canted BSbulkhead.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-416-00.
3-416-92NOTE
INTERNAL - GENERAL VISUAL: Structure Forward of Nose Landing Gear Wheel WellForward access door outer frame, hinges, latch, and stops.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-804-00.
3-418-00INTERNAL - DETAILED: Forward Equip Bay Access Door CutoutBody skin, doubler, frames, adjacent to the access door cutout including fittings and back up structures, and fequipment bay access door internal structure.
3-428-91NOTE
INTERNAL - GENERAL VISUAL: Nose Landing Gear Wheel Well StructureNose landing gear wheel well flat pressure panels with attention to areas of attachments to: frames and beamgear trunnion and actuator attach fittings.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-806-00.
3-430-00INTERNAL - GENERAL VISUAL: Area Outboard & Above Nose Wheel WellFuselage lower lobe interior body floor beams and nose landing gear wheel well flat pressure panels includingtrunnion fitting, the aft lock link fitting, the drag brace fitting, and the actuator support beam fitting.
3-432-00INTERNAL - DETAILED: Bulkhead and Nose Landing Gear Wheel WellBody skin, bulkhead and nose landing gear wheel well side panel at intersection of the Body Station (BS) 287the aft end of the nose landing gear wheel well side panel.
3-440-00INTERNAL - GENERAL VISUAL: Fuselage Lower Lobe InteriorFuselage lower lobe interior floor beams, seat tracks, Body Station (BS) 287 bulkhead, body skin, stringers, athe lower surface of the cabin floor to Stringer S-36.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
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ils Page A.1-5
53-44e door
S 4C ALL ALL
53-44 S 1C ALL ALL
53-44 aft of the ne (LBL) 40 S 4C ALL ALL
53-44 S 4C ALL ALL
53-45NOT
ng, body floor on the
(Right).
S 4C ALL ALL
53-45NOT
door
(Right),
S 4C ALLNOTE ALL
53-45NOT
of the main
ection is S 4C
200SF300F
300BCFALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
2-00
INTERNAL - DETAILED: Forward Entry / Service Door CutoutsBody skin, doubler, stringers, frames and lower sill within 22 inches forward and aft of the forward entry and serviccutouts between stringer S-20 to stringer S-23.
NOTE: This inspection also applies to the crew entry door on 767-300F.
4-00 INTERNAL - GENERAL VISUAL: Main Equipment Center Access DoorMain equipment center access door outer frame, stops, and latch.
6-00INTERNAL - DETAILED: Main Equipment CenterBody skin, stringers, and frames, from stringer S-36L to stringer S-36R and from 10 inches forward and 10 inchesmain equipment center access door and lower portion of Body Station (BS) 287 bulkhead between Left Buttock Liand Right Buttock Line (RBL) 40.
8-00 INTERNAL - GENERAL VISUAL: Main Equipment Center Access DoorMain equipment center access door internal structure.
2-91E
INTERNAL - GENERAL VISUAL: Forward Cargo CompartmentFuselage lower lobe interior structure, Body Station (BS) 355 to BS 738.5, between stringer S-20 and S-32 includiskin, stringers, skin splices, stringer splices and frames from lower surface of cabin floor to upper surface of cargoleft and right hand sides of the airplane.
NOTE: This inspection can be accomplished concurrently with MPD item numbers 53-452-00 (Left) and 53-454-00
2-92E
INTERNAL - DETAILED: Mid-Cabin Entry/Service Door CutoutsBody skin, doubler, stringers, frames and lower sill within 22 inches forward and aft of the mid-cabin entry/service cutouts between stringer S-20 and S-23.
AIRPLANE NOTE: Airplanes with mid cabin doors.NOTE: This inspection can be accomplished concurrently with MPD item number 53-452-00 (Left) and 53-454-00except detailed inspection is required.
2-93E
INTERNAL - DETAILED: Main Deck Cargo Door CutoutBody skin, doubler, stringers, frames, intercostals, fittings and lower sill within 14 inches forward and 22 inches aftdeck cargo door cutout between stringer S-20 and S-23.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-452-00, except detailed insprequired.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-6
IONS
5 ent door cutout.
inspection is S 4C ALL ALL
5 S 2C ALL ALL
5 S 4C ALL ALL
5
argo floor to in sill.
onfigurations of -32L to S-33L. er, access for
e heat
S 4C ALL ALL
5 on extensions. S 4C ALL ALL
5 . S 4C ALL ALL
5 S 4C ALL ALL
5 ertical stiffeners S 4C ALL ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
3-454-91NOTE
INTERNAL - DETAILED: Forward Cargo Compartment Door CutoutBody skin, doubler, stringers and intercostals within 22 inches forward and aft of the forward cargo compartm
NOTE: This inspection can be accomplished concurrently with MPD item number 53-454-00, except detailed required.
3-456-00 INTERNAL - DETAILED: Forward Cargo Compartment Door CutoutForward cargo door cutout lower main sill upper and lower surface.
3-458-00 INTERNAL - DETAILED: Forward Cargo Compartment Door CutoutEdge frames of the forward cargo compartment door cutout.
3-460-00
INTERNAL - DETAILED: Body Below Forward Cargo Compartment FloorLower lobe interior body skin, stringers, keel beam extension, roller trays, and frames from upper surface of cButtock Line (BL) 0.0, including area within 22 inches of the forward cargo compartment door cutout lower ma
ACCESS NOTE: No permanently attached structure is to be removed to accomplish this inspection. Several celectronics bay cooling skin heat exchangers have been installed between Body Station (BS) 434 and 522, SThese heat exchangers cover various structures in this area. As an alternative to removal of the heat exchangthis inspection may be gained by removing the lower plenum and by loosening and lifting the lower edge of thexchanger. Viewing aids will be required if using this technique.
3-474-91NOTE
INTERNAL - GENERAL VISUAL: Area Aft of Forward Cargo CompartmentFuselage lower lobe interior, Body Station (BS) 738.5 to BS 785.9, stringer S-20 tostringer S-35, body floor beams, body skin, bulkheads, stringers, frames, and overwing and underwing longer
NOTE: This inspection can be accomplished concurrently with MPD item number 53-474-00.
3-478-00 INTERNAL - DETAILED: Keel Beam Extension 738.5 - 785.9Keel beam extension chords and body skin, stringers, and frames between stringer S-35L and stringer S-35R
3-480-00 INTERNAL - DETAILED: Body Station 785.9 Bulkhead Inner ChordBody Station (BS) 785.9 bulkhead inner chord between stringers S-20 and stringer S-21.
3-482-00INTERNAL - GENERAL VISUAL: Front Spar Bulkhead Below FloorWing front spar bulkhead and side of body splice, including area of attachment of body skin to front spar and vin area of lower front spar chord.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-7
53-49 ng: body skin/ S 4C ALL ALL
53-49NOT
l Well
from the
0 or
S 4C ALL ALL
53-50 wer surface S 1C ALL ALL
53-50 g stringer S 1C ALL ALL
53-5065 pport fitting S 4C ALL ALL
53-51NOT
body S 1C ALL ALL
53-52 een S 1C
300300BCF
300F400E
ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
6-00INTERNAL - DETAILED: Wing Center Section Upper SurfaceStructure below floor between Body Station (BS) 786 and BS 955.1 and wing center section upper surface includiskin. Body frames and BS 786 and BS 955.1 bulkheads, forward and aft sides. Side of body splice chord. BS 786stringer circumferential splice.
6-91 E
INTERNAL - GENERAL VISUAL: Structure above Wing Center Section Upper Skin and Main Landing Gear WheePressure DeckLongitudinal floor beams, cargo tracks, intercostals, horizontal shear webs and cargo floor fitting support structureupper surface of the cabin floor to the lower surface of the cabin floor, Body Station (BS) 785.9 to 1065.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-824-00, 53-826-00, 53-834-053-836-00.
2-00INTERNAL - GENERAL VISUAL: Keel Beam & Wing Center SectionKeel beam webs including shear web at Body Station (BS) 863, Stiffeners, and chords; and wing center section loand body bulkheads at BS 785.9 and BS 955.1.
4-00INTERNAL - DETAILED: Wing Center Section Tension FittingTension fitting installation on the wing center section lower surface at Buttock Line (BL) 0 from the rear spar to winS-1L.
8-00
INTERNAL - DETAILED: Below Floor Structure - Body Station 955 to 1065Structure below floor between Body Station (BS) 955 and BS 1065 including: floor beams; body frames and BS 10bulkhead, forward and aft sides; pressure deck; BS 1065 skin/stringer circumferential splice; main landing gear suattachment at BS 1043.
ACCESS NOTE: Cabin equipment from BS 955 to BS 1065.
8-91E
INTERNAL - GENERAL VISUAL: Left / Right Main Wheel WellMain landing gear wheel well structure with attention to wing rear spar. Body bulkhead at Body Station (BS) 1065,frames, keel beam, pressure deck, main landing gear beam support fitting at BS 1043, overwing longeron.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-838-00.
0-00INTERNAL - DETAILED: Transverse BeamsTransverse beam lower chords at Body Station (BS) 999 between Buttock Line (BL) 22 and BL 33, BS 1021 betwBL 0 and BL 69, and BS 1043 between BL 0 and BL 42.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-8
IONS
5 nd Wing Buttock S 1C ALL ALL
5 043 between S 1C 200200SF ALL
5 S 1C ALL ALL
5 S 4C ALL ALL
5 surface of cabin S 4C ALL ALL
5 lices and Body
8-00 (Right).
S 4C ALL ALL
5or cutouts
inspection is
S 4C
300300BCF
400ENOTE
ALL
5 including, body argo floor on left S 4C ALL ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
3-524-00INTERNAL - DETAILED: Rear Spar Bulkhead At Wheel WellBody Station (BS) 955.1 rear spar bulkhead and wing rear spar terminal fitting between Buttock line (BL) 62 aLine (WBL) 97.9 including spar web adjacent to fitting, rear spar lower chord splice and overwing longeron.
3-526-00INTERNAL - DETAILED: Transverse Beams At Main Wheel WellsTransverse beam lower chords at Body Station (BS) 1021 between Buttock Line (BL) 20 and BL 69 and BS 1BL 0 and BL 14.
3-528-00 INTERNAL - DETAILED: Rear Spar At Keel BeamWing rear spar at Buttock Line (BL) 0 in area of attachment to the keel beam.
3-540-91NOTE
INTERNAL - GENERAL VISUAL: Keel Beam - Aft SectionKeel beam chords, webs, stiffeners, Body Station (BS) 955.1 to BS 1081, and body bulkhead at BS 1081.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-540-00.
3-542-00INTERNAL - GENERAL VISUAL: Body Forward of Aft Cargo CompartmentFloor beams, seat tracks; body skin, stringers, frames, splices & Body Station (BS) 1065 bulkhead from lowerfloor to stringer S-32.
3-544-91NOTE
INTERNAL - DETAILED: Body Forward of Aft Cargo CompartmentButtock Line (BL) 26 and BL 47 intercostals; keel beam extension chords and body skin, stringers, frames, spStation (BS) 1065 bulkhead outer chord between stringer S-32L and stringer S-32R.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-544-00 (Left) and 53-54
3-550-91NOTE
INTERNAL - DETAILED: Emergency Exit Door CutoutBody skin, doubler, stringers, frames, and lower sill within 22 inches forward and aft of the emergency exit dobetween stringer S-20 and stringer S-23.
AIRPLANE NOTE: Airplanes with Type I emergency exit doors.NOTE: This inspection can be accomplished concurrently with MPD item number 53-550-00, except detailed required.
3-552-91NOTE
INTERNAL - GENERAL VISUAL: Aft Cargo CompartmentFuselage lower lobe interior structure, Body Station (BS) 1088.7 to BS 1404, between stringer S-20 and S-32skin, stringers, skin splices, stringer splices and frames from lower surface of cabin floor to upper surface of cand right hand sides of the airplane.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-552-00.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
N 2019
NS
ils Page A.1-9
53-55NOT
nt door
ection is S 4C ALL ALL
53-55 S 2C ALL ALL
53-55 S 4C ALL ALL
53-55f cargo floor
S 4C ALL ALL
53-57NOT
ing body and right S 4C ALL ALL
53-57NOT
mpartment
ection is S 4C ALL ALL
53-57 S 2C ALL ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
2-92E
INTERNAL - DETAILED: Aft Cargo CompartmentBody skin, doubler, stringers, intercostals and frames within 22 inches forward and aft of the aft cargo compartmecutout.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-552-00, except detailed insprequired.
4-00 INTERNAL - DETAILED: Aft Cargo Compartment Door CutoutAft cargo door cutout lower main sill upper and lower surface.
6-00 INTERNAL - DETAILED: Aft Cargo Compartment Door CutoutEdge frames of the aft cargo compartment door cutout.
8-00
INTERNAL - DETAILED: Body Below Aft Cargo Compartment FloorLower lobe interior, body skin, stringers, roller trays, skin splices, stringer splices and frames from upper surface oto Buttock Line (BL) 0.0 including area within 22 inches of the aft cargo compartment door cutout lower main sill.
ACCESS NOTE: No permanently attached structure is to be removed to accomplish this inspection.
2-91E
INTERNAL - GENERAL VISUAL: Bulk Cargo CompartmentFuselage lower lobe interior structure, Body Station (BS) 1404 to BS 1540, between stringer S-20 and S-32 includskin, stringers, skin splices, and frames from lower surface of cabin floor to upper surface of cargo floor on the lefthand sides of the airplane.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-572-00.
2-92E
INTERNAL - DETAILED: Bulk Cargo Compartment Door CutoutBody skin, doubler, stringers, intercostals, frames, and upper sill within 22 inches forward and aft of bulk cargo codoor cutout.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-572-00, except detailed insprequired.
4-00 INTERNAL - DETAILED: Bulk Cargo Door Lower SillBulk cargo door cutout lower sill upper surface.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-10
IONS
5 aft entry and S 4CPASS200SF
300BCFALL
5cluding skins, ulk cargo
6-00 (Right).
S 4C ALL ALL
5 S 4C ALL ALL
5me from stringer
pection.S 4C ALL ALL
5 and BS 955.1. S 2C ALL ALL
5 S 2C ALL ALL
5 dy splice, wing ard edge of S 2C ALL ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
3-582-00INTERNAL - DETAILED: Aft Entry / Service Door CutoutsLower lobe interior body skin, doubler, stringers, frames, and lower sill within 22 inches forward and aft of theservice door cutouts between stringer S-20 and stringer S-23.
3-584-91NOTE
INTERNAL - DETAILED: Bulk Cargo Compartment Below FloorLower lobe interior body skin from Body Station (BS) 1404 to BS 1540, between stringer S-32L and S-32R, instringers, and frames from upper surface of cargo floor to BL 0, with attention to area within 22 inches of the bcompartment door cutout lower main sill.
NOTE: This inspection can be accomplished concurrently with MPD item numbers 53-584-00 (Left) and 53-58
3-588-91NOTE
INTERNAL - GENERAL VISUAL: Fuselage Lower Lobe InteriorFuselage lower lobe interior structure, Body Station (BS) 1540 to BS 1629, betweenstringer S-20 and stringer S-28, including forward side of pressure dome.
ACCESS NOTE: Waste tank removal is recommended in order to facilitateinspection.NOTE: This inspection can be accomplished concurrently with MPD item number 53-588-00.
3-592-91NOTE
INTERNAL - DETAILED: Body Below Floor - Rear Pressure DomeBody skin, stringers, frames, Body Station (BS) 1582 skin/stringer splice, and forward side of the pressure doS-28 to Buttock Line (BL) 0.
ACCESS NOTE: Waste and potable water tank removal, if installed, is recommended in order to facilitate insNOTE: This inspection can be accomplished concurrently with MPD item number 53-592-00.
3-602-00 INTERNAL - GENERAL VISUAL: Upper Wing / Side Of Body SpliceWing upper surface and side of body splice normally covered by the fairing between Body Station (BS) 785.9
3-606-00 INTERNAL - DETAILED: Overwing LongeronOverwing longeron in areas of attachments at Body Station (BS) 859.5, BS 883.5 and BS 911.
3-614-00INTERNAL - GENERAL VISUAL: Wing Lower Surface Buttock Line 62 - Fairing EdgeLower wing surface between Buttock Line (BL) 62 and outboard edge of wing/body fairing including side of bofront spar splice, bulkhead at Body Station (BS) 785.9 and body skin normally covered by the fairing from forwfairing to BS 955.1 and the portion of the outboard wing lower panel normally concealed by the fairings.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-11
53-61 0L. S 1C ALL ALL
53-61 e (BL) 62.0 S 1C ALL ALL
53-61 k Line S 1C ALL ALL
53-62 S 1C ALL ALL
53-62 S 1C ALL ALL
53-63 to aft edge S 2C ALL ALL
53-63NOT S 1C ALL ALL
53-64NOT
in major f all cutouts S 1C ALL ALL
53-64NOT S 1A ALL ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUN 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
6-00 INTERNAL - DETAILED: Lower Side of Body Splice PlatesSide of body splice plates in areas of attachment to the lower wing surface between the rear spar and stringer S-1
8-00INTERNAL - DETAILED: Wing Center Section Lower Surface At Rear Spar Chord and Splice StringersLower external wing surface at the rear spar chord and splice stringer L-6 and splice stringer L-10 from Buttock Linto outboard edge of wing/body fairing.
8-91INTERNAL - DETAILED: Wing Center Section Lower Surface At Rear Spar Chord and Splice StringersLower external wing surface at the rear spar chord and splice stringer L-6 and splice stringer L-10 from Left Buttoc(LBL) 62.0 to Right Buttock Line (RBL) 62.0.
2-00 INTERNAL - DETAILED: Buttock Line 70 Underwing Longeron FittingButtock Line (BL) 70 underwing longeron fitting installation.
4-00INTERNAL - GENERAL VISUAL: Wing-to-body FairingBody skin and outboard wing upper panel normally covered by the wing/body fairing from Body Station (BS) 955.1of fairing.
4-91 E
INTERNAL - GENERAL VISUAL: Wing To Body Fairings - Aft Left / RightSupport structure for inboard flap mechanisms.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-870-00.
2-91E
EXTERNAL - GENERAL VISUAL: Upper Half of Fuselage - ExteriorControl cabin windshields, cabin windows and body external skin between Body Station (BS) 132.5 and BS 1582 zone 200 with attention to: skin splices, areas of attachments to BS 955.1 bulkhead, and areas within 12 inches o(doors, hatches, windows and equipment installations) and all antenna locations.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-872-00.
8-91E
EXTERNAL - GENERAL VISUAL: Deactivated Door CutoutsBody external skin within 22 inches around deactivated door cutouts.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-648-00.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
19
details Page A.1-12
IONS
5e, and
kpit window. S 1C ALL ALL
5e panel,
inspection is
S 4C NOTE ALL ALL
5 S 2C ALL ALL
5
inger S-12, ills within
ers only). S 4C ALL ALL
5touts.
inspection is
S 4C ALL ALL
5ar web, Body
trough not S 4C
200SF300F
300BCFALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
3-650-00
EXTERNAL - DETAILED: Door Stops And CutoutsDoor stops and visible adjacent cut-out structure within aircraft contour at all door locations (cabin entry/servicemergency) including section 41 access doors and visible adjacent support and cutout structure at No. 2 Coc
ACCESS NOTE: Zone and Access defined by each airplanes door configuration.
3-654-91NOTE
INTERNAL - DETAILED: Control Cabin Windshield StructureControl cabin windshields and visible portions of window posts and sills after accessed.
INTERVAL NOTE: This task should also be performed at windshield and window replacement.ACCESS NOTE: Removal of readily removed sidewall panels required. Removal of overhead dripshield, glarwindows, or permanently attached wall panels not required to accomplish intent of inspection.NOTE: This inspection can be accomplished concurrently with MPD item number 53-654-00, except detailed required.
3-656-00 INTERNAL - GENERAL VISUAL: Control Cabin Floor StructureControl cabin floor structure.
3-662-91NOTE
INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior StructureFuselage upper lobe interior structure, Body Station (BS) 243.5/246 to BS 434, between stringer S-20 and strincluding lap joints, circumferential joints, window forgings, bonded tear straps, stringer splices, frames and s22 inches of doors, door cutout structure, and horizontal shear web.
ACCESS NOTE: Outboard equipment, sidewall panels and movable ceiling panels to be removed (for freightRemoval of rigid barrier, fittings, and drain trough not required (for freighters only).NOTE: This inspection can be accomplished concurrently with MPD item number 53-662-00.
3-662-92NOTE
INTERNAL - DETAILED: Forward Entry and Service Door CutoutsBody skin, doubler, stringers, frames, and upper sill within 22 inches of the forward entry and service door cu
ACCESS NOTE: Outboard equipment, sidewall panels and movable ceiling panels.NOTE: This inspection also applies to the crew entry door on 767-300F.NOTE: This inspection can be accomplished concurrently with MPD item number 53-662-00, except detailed required.
3-670-91NOTE
INTERNAL - GENERAL VISUAL: Cargo Floor Structure - Shear WebRigid cargo barrier attachment structure to fuselage and floor from stringer S-9 to the floor and horizontal sheStation (BS) 266 to BS 412.
ACCESS NOTE: Cargo compartment floor panel removal required. Removal of rigid barrier, fittings, and drainrequired.NOTE: This inspection can be accomplished concurrently with MPD item number 53-670-00.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-13
53-67
Line (BL) nt structure
00F, and
S 4C ALLNOTE ALL
53-68NOT
(Right).
S 4C ALL ALL
53-68 S 2C200SF300F
300BCFALL
53-68NOT
r cutouts.
ection is
S 4C ALLNOTE ALL
53-69NOT
of the main
ection is
S 4C200SF300F
300BCFALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
8-00
INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior StructureFuselage upper lobe interior structure, Body Station (BS) 243.5/246 to BS 434, between stringer S-12 and Buttock0.0, including lap joints, circumferential joints, bonded tear straps, stringer splices, and rigid cargo barrier attachmeto fuselage from BL 0 to stringer S-9.
AIRPLANE NOTE: Inspection is applicable to all aircraft. However, rigid cargo barrier is installed only on 200SF, 3300BCF.
2-91E
INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe InteriorFuselage upper lobe interior structure, including the main deck floor structure, BodyStation (BS) 434 to BS 785.9, between stringer S-12 and stringer S-20, includinglap joints, circumferential joints, window forgings, bonded tear straps, stringersplices, frame and sills within 22 inches of doors, door cutout structure.
ACCESS NOTE: Outboard equipment and sidewall panels.NOTE: This inspection can be accomplished concurrently with MPD item number 53-682-00 (Left) and 53-692-00
6-00 INTERNAL - DETAILED: Main Deck Cargo Door Cutout SillMain deck cargo door cutout lower sill upper surface.
8-91E
INTERNAL - DETAILED: Mid Entry / Service Door CutoutsBody skin, doubler, stringers, frames, intercostals, and upper sill within 22 inches of the mid entry and service doo
AIRPLANE NOTE: Airplanes with mid cabin doors.ACCESS NOTE: Outboard equipment, sidewall panels and moveable ceiling panels.NOTE: This inspection can be accomplished concurrently with MPD item number 53-688-00, except detailed insprequired.
0-91E
INTERNAL - DETAILED: Main Deck Cargo Door CutoutBody skin, doubler, stringers, frames, intercostals, fittings and upper sill within 14 inches forward and 22 inches aftdeck cargo door cutout.
ACCESS NOTE: Outboard equipment, sidewall panels, and movable ceiling panels.NOTE: This inspection can be accomplished concurrently with MPD item number 53-690-00, except detailed insprequired.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-14
IONS
5e forward cargo
inspection is
S 4C ALL ALL
5 k Line (BL) 0.0, S 4C ALL ALL
5 ck Line (BL) 0.0, S 4C ALL ALL
5
per surface of r straps,
el interface, and 5. S 4C ALL ALL
5 ger S-12R, in and stringer .
S 4C ALL ALL
5including lap nches of doors,
4-00 (Right).
S 4C ALL ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
3-692-91NOTE
INTERNAL - DETAILED: Fuselage Upper Lobe Interior Near Forward Cargo DoorBody skin, doubler, stringers, intercostals, fittings, frames, and upper sill within 22 inches forward and aft of thcompartment door cutout from stringer S-17 to stringer S-20.
ACCESS NOTE: Outboard seat sets. Carpet risers and grilles from body sta 456 to sta 654.NOTE: This inspection can be accomplished concurrently with MPD item number 53-690-00, except detailed required.
3-698-00INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe InteriorFuselage upper lobe interior structure Body Station (BS) 434 to BS 785.9, between stringer S-12L and Buttocincluding lap joints, circumferential joints, frames, bonded tear straps, stringer splices.
3-700-00INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe InteriorFuselage upper lobe interior structure, Body Station (BS) 434 to BS 785.9, between stringer S-12R and Buttoincluding lap joints, circumferential joints, frames, bonded tear straps, stringer splices.
3-704-91NOTE
INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior StructureFuselage upper lobe interior structure, Body Station (BS) 785.9 to BS 1065, between stringer S-12 and the upthe pressure deck/wing center section, including lap joints, circumferential joints, window forgings, bonded teastringer splices, frames and sills within 22 inches of doors and escape hatches, stub beam to wing upper panhatch cutout structure, and body window forgings in areas of attach fasteners between BS 785.9 and BS 106
ACCESS NOTE: Cabin equipment and sidewall panels from BS 785 to BS 1065.NOTE: This inspection can be accomplished concurrently with MPD item number 53-704-00.
3-706-00INTERNAL - GENERAL VISUAL: Cabin Above Ceiling Body Station 785-1065Fuselage upper lobe interior structure, Body Station (BS) 785.9 to BS 1065, between stringer S-12L and strinincluding lap joints, circumferential joints, bonded tear straps, stringer splices. Body bulkhead and adjacent sksplices at BS 785.9, BS 955, and BS 1065 (forward and aft sides) between stringer S-12L and stringer S-12R
3-710-91NOTE
INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe InteriorFuselage upper lobe interior structure, Body Station (BS) 1065 to BS 1636, between stringer S-20 and S-12, joints, circumferential joints, window forgings, bonded tear straps, stringer splices, frames and sills within 22 iforward side of BS 1582 aft pressure bulkhead, and door cutout structure.
NOTE: This inspection can be accomplished concurrently with MPD item numbers 53-710-00 (Left) and 53-71
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-15
53-71NOT
service
(Right), S 4C
200300
300BCF400E
ALL
53-71NOT
exit door
(Right),
S 4C
300300BCF
400ENOTE
ALL
53-71NOT
go
ection is
S 4C ALL ALL
53-72-12R, 82 aft S 4C ALL ALL
53-72 d Right S 2C ALL ALL
53-72 d. S 2C ALL ALL
53-73 S 2C ALL ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUN 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
0-92E
INTERNAL - DETAILED: Fuselage Upper Lobe InteriorBody skin, doubler, stringers, intercostals, frames, fittings, and upper sill within 22 inches of the aft cabin entry anddoor cutouts.
NOTE: This inspection can be accomplished concurrently with MPD item numbers 53-710-00 (Left) and 53-714-00except detailed inspection is required.
0-93E
INTERNAL - DETAILED: Fuselage Upper Lobe InteriorBody skin, doubler, stringers, intercostals, frames, stops, fittings, and upper sill within 22 inches of the emergencycutouts.
AIRPLANE NOTE: airplanes with Type I emergency exit doors.NOTE: This inspection can be accomplished concurrently with MPD item numbers 53-710-00 (Left) and 53-714-00except detailed inspection is required.
4-91E
INTERNAL - DETAILED: Fuselage Upper Lobe InteriorBody skin, doubler, stringers, intercostals, frames, fittings and upper sill within 22 inches forward and aft of aft carcompartment door cutout from stringer S-17 to stringer S-20.
ACCESS NOTE: Seat sets, carpet riser, grilles Body Station (BS) 1253 to BS 1417.NOTE: This inspection can be accomplished concurrently with MPD item number 53-714-00, except detailed insprequired.
0-00
INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior StructureFuselage upper lobe interior structure, Body Station (BS) 1065 to BS 1636, between stringer S-12L and stringer Sincluding lap splices, circumferential joints, frames, bonded tear straps, stringer splices, and forward side of BS 15pressure bulkhead.
ACCESS NOTE: Ceiling panels from BS 1065 to BS 1636.
6-00INTERNAL - DETAILED: Forward and Aft Sides of Body Station 1702 - 1725.5 BulkheadsForward and aft sides of Body Station (BS) 1702 and BS 1725.5 bulkheads between Left Buttock Line (LBL) 15 anButtock Line (RBL) 15.
8-00 INTERNAL - DETAILED: Horizontal Stabilizer Trim Actuator SupportHorizontal stabilizer trim actuator support fitting in area of lugs and attachment to Body Station (BS) 1702 bulkhea
0-00 EXTERNAL - GENERAL VISUAL: Exterior Section 48, Left / Right SideExterior of section 48, Body Station (BS) 1582 through BS 1832/1843.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
19
details Page A.1-16
IONS
5 rrosion, S 2C ALL ALL
5 S 4C ALL ALL
5 vot pin, the S 2C ALL ALL
5 S 2C ALL ALL
5
ing fittings
S 4C ALL 80A80C
5
ing fittings
S 4C ALL 40007R4
5 ing fittings. S 12C ALL ALL
5 S 1A ALL
40007R480A80C
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
3-732-00INTERNAL - DETAILED: Aft Pressure Bulkhead - Body Station 1582Aft pressure bulkhead, Body Station (BS) 1582, aft surface for damage; dents, scratches, nicks, gouges or coincluding cracks at splices, doublers, and around all cutouts.
3-734-00 INTERNAL - SPECIAL DETAILED: Vertical Stabilizer Attach BoltVertical stabilizer attach bolts (14 bolts in zone 311/312 and 2 bolts in zone 313/314).
3-746-00INTERNAL - DETAILED: Horizontal Stabilizer Pivot FittingsHorizontal stabilizer pivot fittings in areas of attachment to the Body Station (BS) 1809.5 bulkhead, lugs for pibackup fittings, and the pivot nut lockwire.
3-748-00 INTERNAL - DETAILED: Body Longerons At Horizontal Stabilizer CutoutBody upper and lower longerons adjacent to the horizontal stabilizer cutout.
4-400-00
INTERNAL - GENERAL VISUAL: Power Plant Strut (GE Configuration)Power Plant strut, including pylon skin, spars, struts, braces, attach fittings, lugs, pins, engine cowlings and w(GE configuration).Task notes:1) Inspect visible structure with pylon in place.2) Engine removal not required for this inspection.3) Service Bulletin reference: Service Bulletin 767-54-0052.
4-402-00
INTERNAL - GENERAL VISUAL: Power Plant Strut (P&W Configuration)Power Plant strut, including pylon skin, spars, struts, braces, attach fittings, lugs, pins, engine cowlings and w(P&W configuration).Task notes:1) Inspect visible structure with pylon in place.2) Engine removal not required for this inspection.3) Service Bulletin reference: Service Bulletin 767-54-0052.
4-404-00INTERNAL - GENERAL VISUAL: Power Plant StrutPower Plant strut, including pylon skin, spars, struts, braces, attach fittings, lugs, pins, engine cowlings, and wTask Note: Inspect all fittings, including wing fittings with pylon dropped.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-17
54-40 S 1C ALL
40007R480A80C
54-41 S 2C ALL
40007R480A80C
54-41 itting and S 1C ALL 524
54-41unt fittings, ENG CNG
<1> ALL 524
54-41 ENG CNG<1> ALL 524
54-41
ittings
S 4C ALL 524
54-42 S 1A ALL 524
54-42 S 3C ALL
40007R480A80C
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
8-00 EXTERNAL - GENERAL VISUAL: No. 1 / 2 Nacelle StrutNacelle strut skin and aft strut fairing including areas of attachment to: bulkhead and frames. Spars and stringers.
0-00 EXTERNAL - DETAILED: Nacelle Strut No. 1 / 2Nacelle strut skin (under side strut fairing) in area of attachment to the strut mid bulkhead and spar.
2-00INTERNAL - DETAILED: Strut 1 / 2 Lower Spar and Engine MountsLower spar chords, webs, thrust plate and forward and aft engine mount bulkheads. Diagonal brace, strut attach fassociated fuse pins. Forward and aft engine mount fittings, links, and attach bolts.
4-00
INTERNAL - DETAILED: Strut 1 / 2Lower spar chords and thrust plate. Diagonal brace, strut attach fittings and fuse pins. Forward and aft engine molinks, and attach bolts (including dye penetrant inspection of attach bolts).
ACCESS NOTE: At engine removal.
6-00INTERNAL - GENERAL VISUAL: Strut 1 / 2Forward and aft engine mount bulkheads.
ACCESS NOTE: At engine removal.
8-00
INTERNAL - GENERAL VISUAL: Power Plant Strut (RR Configuration)Power Plant strut, including pylon skin, spars, struts, braces, attach fittings, lugs, pins, engine cowlings and wing f(RR configuration).Task Notes:1) Inspect visible structure with pylon in place.2) Engine removal not required for this inspection.3) Service Bulletin reference: Service Bulletin 767-54-0052.
2-00 EXTERNAL - GENERAL VISUAL: Strut 1 / 2Visible external portions of strut.
4-00 INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Forward Upper SparNacelle strut forward upper spar, upper link and upper link attach fitting.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-18
IONS
5 S 3C ALL
40007R480A80C
5 ward engine S 3C ALL
40007R480A80C
5 S 1C ALL 524
5not incorporated
S 1C ALLNOTE 524
5ich have
S 2C ALLNOTE 524
5d upper s prior to line S 1C ALL
NOTE
4000 7R4 80A80C
5 able to 80A and
0C engines only.
S 1C ALL
4000 7R4 80A80C
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
AIRPLANE NOTE: SB 767-54-0082. This task is applicable to airplanes line numbers 702 and on or those whincorporated this service bulletin.
4-436-00INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Mid-spar Fitting Nacelle strut outboard mid-spar fitting forwartang.AIRPLANE NOTE: SB 767-54-0080 (P&W) and SB 767-54-0081 (GE). This task is applicable to airplanenumber 665 (GE) and 664 (P&W) which have not incorporated this service bulletin.
4-438-00
INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Upper LinkNacelle strut upper link forward attach fitting and upper link including the forward attach lug.
ACCESS NOTE: Access Panel 431ET applicable to 7R4 and 4000 engines only. Access Panel 432ET applic80C engines only.Access Panel 441ET applicable to 7R4 and 4000 engines only. Access Panel 442ET applicable to 80A and 8
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-19
54-44bers 665
S 3C ALLNOTE
4000 7R4 80A80C
54-44 e mount S 1C ALL 524
54-44 l brace, S 1C ALL 524
54-44 S 2C ALL
4000 7R4 80A80C
54-44 S 2C ALL
4000 7R4 80A80C
54-45ut attach
corporated S 1C ALL
NOTE 524
54-45ut attach
ave S 1C ALL
NOTE 524
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
AIRPLANE NOTE: SB 767-54-0080 (P&W) and SB 767-54-0081 (GE). This task is applicable to airplanes line numand on (GE) and 664 and on (P&W) or those which have incorporated this service bulletin.
2-00INTERNAL - DETAILED: Strut 1 / 2 Torque BoxUpper spar chords, webs, stiffeners, and backup chords. Lower spar chords and webs. Thrust plate, forward enginbulkhead, and aft upper spar fitting and fuse pins.
4-00INTERNAL - GENERAL VISUAL: Strut 1 / 2 Aft Torque BoxSide skin stiffeners and backup chords, mid bulkhead, aft engine mount bulkhead, and aft strut bulkhead, diagonastrut attach fittings and fuse pins, side link and strut attach fittings.
6-00 INTERNAL - GENERAL VISUAL: Nacelle Strut - Mid & Aft Torque BoxNacelle strut mid and aft torque box stiffeners, spars, frames, bulkheads, and fittings.
8-00 INTERNAL - DETAILED: Strut No. 1 / 2 Aft Engine Mount BulkheadNacelle strut No. 1 and No. 2 aft engine mount support bulkhead.
0-00
INTERNAL - DETAILED: Strut 1 / 2 Aft Torque BoxAft strut bulkhead, diagonal brace, strut attach fitting and fuse pins. Aft upper spar fitting, fuse pins, lug area of strfitting, side links and side load fittings.
AIRPLANE NOTE: SB 767-54-0082. This task is applicable to airplanes prior to line number 702 which have not inthis service bulletin.
2-00
INTERNAL - DETAILED: Strut 1 / 2 Aft Torque BoxAft strut bulkhead, diagonal brace, strut attach fitting and fuse pins. Aft upper spar fitting, fuse pins, lug area of strfitting, side links and side load fittings, strut attach fitting.
AIRPLANE NOTE: SB 767-54-0082. This task is applicable to airplanes line numbers 702 and on or those which hincorporated this service bulletin.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-20
IONS
5iagonal brace
r to line number S 2C ALL
NOTE
4000 7R4 80A80C
5iagonal brace
numbers 665 S 3C ALL
NOTE
4000 7R4 80A80C
5ttings (wing and
r to line number S 1C ALL
NOTE
4000 7R4 80A80C
5ttings (wing and
numbers 665 S 3C ALL
NOTE
4000 7R4 80A80C
5 S 1C ALL ALL
5 nt to nacelle S 1C ALL ALL
5
al inspection.
S 1C ALL 7R4
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
AIRPLANE NOTE: SB 767-54-0080 (P&W) and SB 767-54-0081 (GE). This task is applicable to airplanes prio665 (GE) and 664 (P&W) which have not incorporated this service bulletin.
AIRPLANE NOTE: SB 767-54-0080 (P&W) and SB 767-54-0081 (GE). This task is applicable to airplanes lineand on (GE) and 664 and on (P&W) or those which have incorporated this service bulletin.
4-462-00
INTERNAL - DETAILED: Left / Right Nacelle Strut Mid Spar FittingNacelle strut mid spar fittings (wing and strut), side load links, side link attach fittings, diagonal brace attach fistrut) and aft torque box bulkhead.
AIRPLANE NOTE: SB 767-54-0080 (P&W) and SB 767-54-0081 (GE). This task is applicable to airplanes prio665 (GE) and 664 (P&W) which have not incorporated this service bulletin.
4-464-00
INTERNAL - DETAILED: Left / Right Nacelle Strut Mid Spar FittingNacelle strut mid spar fittings (wing and strut), side load links, side link attach fittings, diagonal brace attach fistrut) and aft torque box bulkhead.
AIRPLANE NOTE: SB767-54-0080 (P&W) and SB767-54-0081 (GE). This task is applicable to airplanes lineand on (GE) and 664 and on (P&W) or those which have incorporated this service bulletin.
4-466-00 INTERNAL - GENERAL VISUAL: Left / Right Nacelle Strut / Wing Lower SurfaceWing lower inspar surface including nacelle fairing supports including nacelle support fittings.
4-468-00INTERNAL - DETAILED: Left / Right Nacelle Strut / Wing Lower SurfaceWing lower inspar skin at splice stringers L-6, L-10, and L-15, front and rear spar chords, and in areas adjacestrut attach fittings and nacelle fairing attach angles.
4-804-00
INTERNAL - ZONAL (GV): Underwing Fairing - Strut 1 / 2Perform internal general visual inspection of zones. (EZAP <2>)CPC NOTE: Corrosion Prevention and Control Basic Task required
INTERVAL NOTE: The EZAP inspection requirement with interval 24000 FH or 72 MO is satisfied by this zon
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-21
54-81
spection.
S 1C ALL 80
54-82spection.
S 1C ALL 4000
54-83 S 1C ALL 524
55-40 4.5 S 4C ALL ALL
55-41 the S 4C ALL ALL
55-41NOT
(fin sta. attachment posts to S 2C ALL ALL
55-41NOT
ttings S 2C ALL ALL
55-41NOT
tabilizer tip S 4C ALL ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
6-00
INTERNAL - ZONAL (GV): Underwing Fairing - Strut 1 / 2Perform internal general visual inspection of zones. (EZAP <2>)CPC NOTE: Corrosion Prevention and Control Basic Task required.
INTERVAL NOTE: The EZAP inspection requirement with interval 24000 FH or 72 MO is satisfied by this zonal in
8-00INTERNAL - ZONAL (GV): Underwing Fairing - Strut 1 / 2Perform internal general visual inspection of zones. (EZAP <2>)
INTERVAL NOTE: The EZAP inspection requirement with interval 24000 FH or 72 MO is satisfied by this zonal in
8-00EXTERNAL - ZONAL (GV): Strut No. 1 / 2Perform external general visual inspection of the zone (including fairings).CPC NOTE: Corrosion Prevention & Control Basic Task required.
6-00INTERNAL - DETAILED: Vertical Stabilizer Fixed Leading EdgeBody skin within vertical stabilizer fixed leading edge in area of attachment to Body Station (BS) 1629 and BS 165bulkheads and stringers S-2L and S-2R, and vertical stabilizer fin-to-body fittings on forward side of front spar.
0-00INTERNAL - GENERAL VISUAL: Vertical Stabilizer Front Spar To Rear SparVertical stabilizer left and right surfaces, front and rear spars, and inspar ribs between rib 10 (Fin Station 225) andstabilizer tip rib including spar webs.
0-91 E
INTERNAL - GENERAL VISUAL: Vertical Stabilizer - Front Spar To Rear SparVertical stabilizer left and right surfaces, front and rear spars, and inspar ribs between the fin-body deck and rib 10225) including front and rear spar webs, rear spar chords, stringer S-6, fin-body deck around cutouts and areas ofto body frames at Body Station 1654, 1678, 1702, and 1725, rib webs around cutouts, rib shear ties, and rib attachfront and rear spars.
NOTE: This inspection can be accomplished concurrently with MPD item number 55-816-00.
0-92 E
INTERNAL - GENERAL VISUAL: Vertical Stabilizer - Rear Spar To Trailing EdgeRudder actuator support fittings, vertical stabilizer rear spar, trailing edge support ribs, and rudder hinge support fibetween top of body and Rudder Station 18 and between Rudder Station 106 and Station 181.
NOTE: This inspection can be accomplished concurrently with MPD item number 55-820-00.
0-93 E
INTERNAL - GENERAL VISUAL: Vertical Stabilizer - Rear Spar To Trailing EdgeVertical stabilizer rear spar, trailing edge support ribs, and rudder hinge support fittings between top of body and sexcept between Rudder Station 106 and Station 181 and at Rudder Station 18.
NOTE: This inspection can be accomplished concurrently with MPD item number 55-820-00.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-22
IONS
5 S 2C ALL ALL
5 rib 1 (Fin Station S 1C ALL ALL
5 S 2C ALL ALL
5 fin-to-body S 1C ALL ALL
5 o Body Station S 2C ALL ALL
5 S 4C ALL ALL
5 06 and Station S 1C ALL ALL
5 S 1C ALL ALL
5 106 and 181. S 2C ALL ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
5-412-00 INTERNAL - DETAILED: Vertical Stabilizer Fin-to-Body FittingsVertical stabilizer fin-to-body fittings at front and rear spars and stringers S-4 and S-8.
5-414-00EXTERNAL - GENERAL VISUAL: Left and Right Vertical Stabilizer Inspar StructureVertical stabilizer surfaces between top of body and rib 10 (Fin Station 225), including areas of attachment to 16), spar chords and stringer S-6.
5-416-00 EXTERNAL - GENERAL VISUAL: Vertical Stabilizer Front Spar To Rear SparVertical stabilizer left and right surfaces from rib 10 (Fin Station 225) to the stabilizer tip rib.
5-418-00EXTERNAL - DETAILED: Vertical Stabilizer Inspar StructureVertical stabilizer left and right surfaces from top of body to rib 1 (Fin Station 16) in areas of attachment to thefittings at front and rear spar chords and stringers S-4 and S-8.
5-420-00INTERNAL - GENERAL VISUAL: Vertical Stabilizer Trailing EdgeVertical stabilizer fin-to-body fitting and body skin within vertical stabilizer trailing edge in area of attachment t(BS) 1725.5 bulkhead and stringers S-2L and S-2R.
5-422-00 INTERNAL - GENERAL VISUAL: RudderRudder interior.
5-422-91 NOTE
EXTERNAL - GENERAL VISUAL: RudderRudder external structure including areas of attach fasteners through the front spar between Rudder Station 1181.
NOTE: This inspection can be accomplished concurrently with MPD item number 55-824-00.
5-424-00 EXTERNAL - DETAILED: RudderRudder spar, hinge, and actuator attach fittings between Rudder Stations 106 and 181.
5-426-00 EXTERNAL - DETAILED: RudderRudder spar and hinge fittings between Rudder Station 0 and top of rudder except between Rudder Stations
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-23
55-42 Testing
S 4C ALL ALL
55-43 S 4C ALL ALL
55-43 and 3R free flanges S 2C ALL ALL
55-43NOT
ft and right
S 1C ALL ALL
55-43NOT
and 3R r free S 2C ALL ALL
55-43NOT
ion to the S 2C ALL ALL
55-43NOT
attention to S 2C ALL ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
8-00
EXTERNAL - SPECIAL DETAILED: RudderRudder spar and adjacent structure between Rudder Stations 106 and 181.
The NDI method(s) necessary to accomplish the intent of this inspection are contained in the 767 Non-DestructiveManual, D634T301. The inspection procedure is contained in part 4, subjects 55-40-01, 55-40-02, and 55-40-03.
0-00 INTERNAL - GENERAL VISUAL: Vertical Stabilizer TipVertical stabilizer tip and upper side of stabilizer tip rib.
4-00INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Center SectionHorizontal stabilizer center section upper and lower surfaces, front and rear spars and inspar ribs between ribs 3Lincluding: rib webs around cutouts. Rib shear ties. Rib attach posts to front and rear spars. Attachment of stringer to the upper and lower chords of rib 2.
4-91 E
EXTERNAL - GENERAL VISUAL: Horizontal Stabilizer Center SectionHorizontal stabilizer center section upper and lower surfaces and front and rear spars between inboard edge of lestab./body fairings, including:The chordwise splice at rib 2. Upper spanwise splice at stringer S-3. Rear spar web.Pivot and jackscrew fittings.
NOTE: This inspection can be accomplished concurrently with MPD item number 55-830-00.
4-92 E
INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Center SectionHorizontal stabilizer center section upper and lower surfaces. Front and rear spars and inspar ribs between ribs 3Lincluding rib webs around cutouts, rib shear ties, rib attach posts to front and rear spars, and attachment of stringeflanges to the upper and lower chords of rib 2.
NOTE: This inspection can be accomplished concurrently with MPD item number 55-828-00.
6-91E
INTERNAL - GENERAL VISUAL: Areas Aft of Pressure Bulkhead To Body Station 1725.5Body internal surface, stringers, frames and bulkhead between Body Station (BS) 1582 and BS 1725.5 with attentbody upper and lower longeron backup fittings forward of the horizontal stabilizer cutout at BS 1725.5.
NOTE: This inspection can be accomplished concurrently with MPD item number 55-800-00.
8-91E
INTERNAL - GENERAL VISUAL: Fuselage Areas Aft of Body Station 1725.5Body internal surface, stringers, frames and bulkheads between Body Station (BS) 1725.5 and BS 1832/1843 withbulkhead at BS 1809.5.
NOTE: This inspection can be accomplished concurrently with MPD item number 55-804-00.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-24
IONS
5 luding front and S 4C ALL ALL
5 ing front and d rear spars.
S 4C ALL ALL
5 attachment to S 1C ALL ALL
5 S 2C ALL ALL
5 splice stringer S 1C ALL ALL
5 en outboard S 4C ALL ALL
5 vator hinge S 2C ALL ALL
5 S 4C ALL ALL
5 pt between S 2C ALL ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
5-454-00INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Front To Rear Spar Left & RightHorizontal stabilizer upper and lower surfaces, front and rear spars and inspar ribs between ribs 8 and 17 increar spar webs, rib webs, rib shear ties, and rib attach posts to front and rear spars.
5-456-00INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Outboard Section Left and RightHorizontal stabilizer upper and lower surfaces front and rear spars and inspar ribs between ribs 3 and 8 includrear spar webs, rear spar upper chord, rib webs around cutouts, rib shear ties, and rib attach posts to front an
5-458-00EXTERNAL - GENERAL VISUAL: Horizontal Stabilizer Upper Outboard Surface Left and RightHorizontal stabilizer upper surface from outboard edge of stabilizer / body fairing to rib 17, including areas of spar chords and stringer S-3 from edge of fairing to rib 8.
5-460-00 EXTERNAL - GENERAL VISUAL: Horizontal Stabilizer Lower Outboard Surface Left and RightHorizontal stabilizer lower surface from outboard edge of stabilizer / body fairing to rib 17.
5-462-00EXTERNAL - DETAILED: Horizontal Stabilizer Upper Outboard Surface Left and RightHorizontal stabilizer upper skin in area of attach fasteners through upper rear spar chord and upper spanwiseS-3 from outboard edge of stabilizer / body fairing to rib 5.
5-464-00INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Trailing Edge Left and RightHorizontal stabilizer rear spar, trailing edge panels and support ribs, and elevator hinge support fittings betweedge of stabilizer/body fairing and rib 17 except between stabilizer Rear Spar Stations 104.1 and 177.6.
5-466-00INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Trailing Edge Right and LeftElevator actuator support fittings, horizontal stabilizer rear spar, trailing edge panels and support ribs, and elesupport fittings between stabilizer rear spar stations 104.1 and 177.6.
5-470-00 INTERNAL - GENERAL VISUAL: Left / Right Elevator InteriorElevator interior.
5-474-00EXTERNAL - DETAILED: Elevator Spar & Hinge Fittings Left and RightElevator spar and hinge fittings between Elevator Station 51.8 and horizontal stabilizer Buttock Line 317 exceElevator Stations 139.3 and 212.7.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-25
55-47 9.3 and S 1C ALL ALL
55-48 S 1C ALL ALL
55-48 Testing
S 4C ALL ALL
55-48 S 4C ALL ALL
55-49 g areas of S 2C ALL ALL
55-49 er and S 1C ALL ALL
55-49 t rib 2 S 1C ALL ALL
55-49 iring. S 1C ALL ALL
57-40s, and lower
S 1C ALL NOTE ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
8-00EXTERNAL - GENERAL VISUAL: Left / Right Elevator - Inboard / OutboardElevator external structure including areas of attach fasteners through the front spar between Elevator Stations 13212.7 and the elevator interconnect fitting.
0-00 EXTERNAL - DETAILED: Left / Right Elevator - OutboardElevator spar, hinge, and actuator attach fittings between Elevator Stations 139.3 and 212.7.
4-00
EXTERNAL - SPECIAL DETAILED: Elevator Spar & Adjacent Structure Left and RightElevator spar and adjacent structure between Elevator Stations 139.3 and 212.7.
The NDI method(s) necessary to accomplish the intent of this inspection are contained in the 767 Non-DestructiveManual, D634T301. The inspection procedure is contained in part 4, subjects 55-20-01, 55-20-02, and 55-20-03.
6-00 INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Tip Left and RightHorizontal stabilizer tip and outboard side of rib 17.
0-00INTERNAL - DETAILED: Horizontal Stabilizer Center SectionHorizontal stabilizer rear spar upper chord and skin between rear spar and stringer S-1, from rib 2 to rib 3, includinattach fasteners.
2-00EXTERNAL - DETAILED: Horizontal Stabilizer Jackscrew FittingHorizontal stabilizer jackscrew fitting lug area at cross brace fitting and at attachment of fitting to the stabilizer upplower front spar chords, and upper and lower skin attach straps.
4-00EXTERNAL - DETAILED: Horizontal Stabilizer Pivot FittingsHorizontal stabilizer pivot fitting lug and areas of attachment to stabilizer spar and upper and lower splice plates aincluding areas of the splice plates aft of the spar.
6-00 EXTERNAL - DETAILED: Horizontal Stabilizer Center Section Rear SparHorizontal stabilizer rear spar upper chord and adjacent skin between rib 1 and inboard edge of stabilizer / body fa
0-00
INTERNAL - GENERAL VISUAL: Wing Center Section Left and RightWing center section upper and lower surfaces, front and rear spars, spanwise beams, side of body ribs and splicesurface beams including lower surface access hole cutout and adjacent stringers.
AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-26
IONS
5right Wing
S 1C ALL NOTE ALL
5 S 1C ALL NOTE ALL
5web and lower
S 1C ALL NOTE ALL
5 Wing Buttock
S 1C ALL NOTE ALL
5r spar terminal
S 1C ALLNOTE ALL
5 of the front
S 1C ALL NOTE ALL
5s and lower
S 1C ALL NOTE ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
7-402-00
INTERNAL - DETAILED: Wing Center Section Lower Surface SpliceWing center section lower surface splice stringers L-6 and L-10 in areas of attach fasteners between left and Buttock Line (WBL) 97.9.
AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank.
7-404-00INTERNAL - DETAILED: Wing Center Section Rear Spar ChordWing center section rear spar lower chord between left and right Wing Buttock Line (WBL) 97.9.
AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank.
7-406-00
INTERNAL - DETAILED: Wing Center Section Side of Body SpliceLower left and right Wing Buttock Line (WBL) 97.9 side of body splice chord in areas of attachment to the rib wing surface between the wing rear spar and stringer L-10.
AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank.
7-408-00
INTERNAL - DETAILED: Wing Center Section Rear Spar WebLeft and right wing center section rear spar web in areas of attach fasteners between buttock line (BL) 62 andLine (WBL) 97.9 and between Left Buttock Line (LBL) 11 and Right Buttock Line (RBL) 11.
AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank.
7-410-00
INTERNAL - DETAILED: Wing Center Section Side of Body Rib WebLeft and right Wing Buttock Line (WBL) 97.9 side of body rib web surrounding cutouts, and attachments to reafitting and lower rib chord between the rear spar and spanwise beam #1.
AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank.
7-412-00
INTERNAL - DETAILED: Wing Center Section Lower Surface Buttock Line 70Wing center section lower surface left and right Buttock Line (BL) 70 underwing longeron backup structure aftspar.
AIRPLANE NOTE: For airplanes without four-bay center section fuel tank.
7-414-00
INTERNAL - GENERAL VISUAL: Wing Center Section Fuel Tank Dry Bay AreaWing center section dry bay upper and lower surface, front spar, spanwise beam, side of body ribs and splicesurface beams including lower surface access hole cutout, adjacent stringers, and drain.
AIRPLANE NOTE: Airplanes with two-bay center section fuel tank.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-27
57-41
Wing
is document S 4C ALL NOTE ALL
57-41NOT
er surface
S 4C ALL NOTE ALL
57-41r spar
S 4C ALL NOTE ALL
57-42 is document S 4C ALL NOTE ALL
57-42
ne (WBL)
is document S 4C ALL NOTE ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUN 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
6-00
INTERNAL - DETAILED: Wing Center Section Fuel Tank Wet BayWing center section lower surface splice stringers L-6 and L-10 in areas of attach fasteners between left and rightButtock Line (WBL) 97.9.
SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of thfor sealant limits and threshold values.
AIRPLANE NOTE: For airplanes with two-bay or four-bay center section fuel tank.
6-91 E
INTERNAL - GENERAL VISUAL: Wing Center SectionWing center section wet bay upper and lower surfaces, rear spar, span wise beams and access door cutouts, lowbeams, side of body ribs, splices and drain.
AIRPLANE NOTE: Airplanes with 2-BAY or 4-BAY center section fuel tank.
NOTE: This inspection can be accomplished concurrently with MPD item number 53-830-00.
8-00
INTERNAL - DETAILED: Wing Center Section Fuel Tank Wet BayLeft and right Wing Buttock Line (WBL) 97.9 side of body rib web and lower chord cutouts, and attachments to reaterminal fitting and lower rib chord between the rear spar and spanwise beam no. 2.
AIRPLANE NOTE: For airplanes with two-bay or four-bay center section fuel tank.
0-00
INTERNAL - DETAILED: Wing Center Section Fuel Tank Wet BayWing center section rear spar lower chord and skin between left and right Wing Buttock Line (WBL) 97.9.
SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of thfor sealant limits and threshold values.
AIRPLANE NOTE: For airplanes with two-bay or four-bay center section fuel tank.
2-00
INTERNAL - DETAILED: Left and Right Wing Center Section Fuel Tank Wet Bay Wing center section rear spar web in areas of attach fasteners between Buttock Line (BL) 62 and Wing Buttock Li97.9 and between Left Buttock Line (LBL) 11 and Right Buttock Line (RBL) 11.
SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of thfor sealant limits and threshold values.
AIRPLANE NOTE: For airplanes with two-bay or four-bay center section fuel tank.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
19
details Page A.1-28
IONS
5er wing surface
S 4C ALL NOTE ALL
5 of the front
S 4C ALL NOTE ALL
5 at Body Station 1.
S 1C ALL ALL
5 S 1C ALL ALL
5 S 1C ALL ALL
5 spar and the S 1C ALL ALL
5 slat tracks, and
12-00 and S 2C ALL ALL
5 S 1A ALL ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
7-424-00
INTERNAL - DETAILED: Left and Right Wing Center Section Fuel Tank Wet Bay Lower Wing Buttock Line (WBL) 97.9 side of body splice chords in areas of attachment to the rib web and lowbetween the wing rear spar and stringer L-10.
AIRPLANE NOTE: For airplanes with two-bay or four-bay center section fuel tank.
7-426-00
INTERNAL - DETAILED: Wing Center Section Lower Surface Buttock Line 70Wing center section lower surface left and right Buttock Line (BL) 70 underwing longeron backup structure aftspar.
AIRPLANE NOTE: Airplanes with four-bay center section fuel tank.
7-458-00INTERNAL - GENERAL VISUAL: Wing Center Section Lower SurfaceWing center section lower surface including the area surrounding the access hole cutout, front spar bulkhead(BS) 785.9, Keel beam and wing lower surface beam at Buttock Line (BL) 62 between BS 785.9 and BS 955.
7-460-00 EXTERNAL - GENERAL VISUAL: Inboard Flap Support Structure - Left / RightInboard flap inboard support and mechanism.
7-470-00INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Upper LinkNacelle strut upper link and upper link to wing attach fitting including the area of attachment to the wing front upper and lower wing skin projections.
7-470-91 NOTE
INTERNAL - GENERAL VISUAL: Right and Left Wing Leading Edge To Front SparRight and left wing leading edge panels and ribs, support structure for slats and actuators, main and auxiliarywing front spar and skin including the side of body splice at WBL 97.9.
NOTE: This inspection can be accomplished concurrently with MPD item number 57-802-00, 57-802-01, 57-857-812-01.
7-504-00 EXTERNAL - GENERAL VISUAL: Left / Right Wing Inspar Lower Surface, ExteriorWing lower surface between wing/body fairings and Wing Buttock Line (WBL) 929.1/rib 36.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-29
57-50 airings at S 1C ALL ALL
57-50 as of attach ar. Main S 2C ALL ALL
57-51 S 1C ALL ALL
57-51 and 20 and /body between rib
S 1C ALL ALL
57-51 S 2C ALL ALL
57-51is document
S 4C ALL ALL
57-51NOT
cluding ar spars S 4C ALL ALL
57-51 S 4C ALL ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
6-00EXTERNAL - GENERAL VISUAL: Left / Right Wing Inspar Lower SurfaceWing lower surface between wing/body fairings and Wing Buttock Line (WBL) 929.1/rib 36 including areas under fmain landing gear forward trunnion, and ribs 7, 17 and 24.
8-00EXTERNAL - GENERAL VISUAL: Left / Right Wing Inspar Upper SurfaceWing inspar upper surface between wing/body fairing and Wing Buttock Line (WBL) 929.1/rib 36 (tip) including arefasteners at: nacelle support at front spar (WBL 310). Main landing gear beam outboard fitting (WS 394) at rear splanding gear forward trunnion fitting (WS 308) at rear spar.
0-00 EXTERNAL - DETAILED: Left / Right Wing Inspar Upper SurfaceWing upper surface in the area of the nacelle strut fitting attachments at Wing Buttock Line (WBL) 310.
2-00
EXTERNAL - DETAILED: Left / Right Wing Inspar Lower SurfaceWing lower surface surrounding fuel access plate cutouts between wing/body fairing and rib 3 and between ribs 7in the following areas of attachments: main landing gear beam outboard support fitting. Rear spar chord from wingfairing to Wing Station (WS) 590.2 (rib 16). Spanwise splice stringer L-6 between wing/body fairing and rib 3, and 8 and rib 14. Spanwise splice stringer L-10, from rib 7 to rib 20. Front spar chord from rib 7 to rib 24.
4-00 EXTERNAL - DETAILED: Left / Right Wing Inspar Upper SurfaceWing upper surface in areas of attachment to rear spar upper chord between ribs 5 and 21.
6-00
INTERNAL - DETAILED: Left / Right Wing Lower Surface Spanwise SpliceWing lower surface spanwise splice stringers L-6 and L-10 between Wing Buttock Line (WBL) 97.9 and rib 3.
SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of thfor sealant limits and threshold values.
6-91 E
INTERNAL - GENERAL VISUAL: Center Auxiliary Tank - Left / Right WingLeft and right wing upper and lower surfaces, front and rear spars, and inspar ribs between WBL 97.9 and rib 3 incavity drain adjacent to the side of body rib, wing rib access cutouts in ribs 1 and 2, rib attach posts to front and reand lower surface splice stringer L-15.
NOTE: This inspection can be accomplished concurrently with MPD item number 57-834-00.
8-00 INTERNAL - DETAILED: Left / Right Wing Lower Surface Access Hole CutoutsWing lower surface access hole cutouts and adjacent stringers.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-30
IONS
5 ringers between S 4C ALL ALL
5of this document
S 4C ALL ALL
5of this document
S 4C ALL ALL
5nding cutouts
of this document S 4C ALL ALL
5
and rib 31 8, 10, 17, and
of this document
S 4C ALL ALL
5 308.1. S 4C ALL ALL
5 . S 4C ALL ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
7-520-00INTERNAL - DETAILED: Left / Right Wing Lower Surface / Side of Body RibWing Buttock Line (WBL) 97.9 side of body rib lower chord in areas of attachment to the lower surface and stthe rear spar and stringer L-10.
7-522-00
INTERNAL - DETAILED: Left / Right Wing Rear Spar Web & Lower ChordWing rear spar web and lower chord between Wing Buttock Line (WBL) 97.9 and rib 1.
SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B for sealant limits and threshold values.
7-524-00
INTERNAL - DETAILED: Left / Right Wing Rear Spar Lower Chord & Rib 1 & 3Wing rear spar lower chord between rib 1 and rib 3.
SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B for sealant limits and threshold values.
7-526-00
INTERNAL - DETAILED: Left / Right Wing Side of Body Rib WebWing Buttock Line (WBL) 97.9 side of body rib web in areas of rib attach fasteners and reinforcements surroubetween rear spar and spanwise beam no. 1.
SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B for sealant limits and threshold values.
7-530-00
INTERNAL - GENERAL VISUAL: Left / Right Wing Main TankWing upper and lower surfaces, front and rear spars, spanwise dry bay barrier, and inspar ribs between rib 3 including: cavity drain adjacent to rib 3. Wing rib access cutouts in ribs 4, 5, and 9. Rib shear ties at ribs 4, 7, 24. Rib attach posts to front and rear spars.
SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B for sealant limits and threshold values.
7-532-00 INTERNAL - DETAILED: Left / Right MLG Trunnion Backup StructureWing main landing gear forward trunnion support backup structure forward of rear spar at Wing Station (WS)
7-534-00 INTERNAL - DETAILED: Left / Right MLG Beam Backup StructureWing main landing gear beam outboard support backup structure forward of rear spar adjacent to ribs 7 and 8
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-31
57-53 uttock Line S 4C ALL ALL
57-53e in Section
S 4C ALL ALL
57-54s 9 and 11.
e in Section S 4C ALL ALL
57-54 S 4C ALL ALL
57-54 S 1C ALL ALL
57-54NOT
and rib 9. S 1C ALL ALL
57-54 S 1C ALL ALL
57-54 S 1C ALL ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
6-00INTERNAL - DETAILED: Left / Right Wing Nacelle Strut Support BackupWing nacelle strut support backup structure forward of the rear spar adjacent to stringers L-5 and L-6 and Wing B(WBL) 310.
8-00
INTERNAL - DETAILED: Left / Right Wing Lower Spar ChordsLower spar chords as follows: front spar chord between ribs 14 and 24, rear spar chord between ribs 3 and 11.
SPECIAL NOTE: This MPD task requires removal of sealant prior to inspection. Refer to the Excess Sealant TablB of this document for sealant limits and threshold values.
0-00
INTERNAL - DETAILED: Left / Right Wing Lower Spanwise Splice StringersLower surface spanwise splice stringers; L-6 between ribs 8 and 14, L-10 between ribs 7 and 20, L-15 between rib
SPECIAL NOTE: This MPD task requires removal of sealant prior to inspection. Refer to the Excess Sealant TablB of this document for sealant limits and threshold values.
2-00 INTERNAL - DETAILED: Left / Right Wing Lower Surface Access Hole CutoutsLower surface access hole cutouts and adjacent stringers between ribs 7 and 20.
4-00 INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Backup StructureNacelle strut support backup structure aft of the front spar between ribs 8 and 9.
4-91 E
INTERNAL - GENERAL VISUAL: Dry Bay - Inboard Left / Right WingLeft and right wing upper & lower surfaces, front spar & the spanwise dry bay barrier and inspar ribs between rib 6
NOTE: This inspection can be accomplished concurrently with MPD item number 57-838-00.
6-00 INTERNAL - DETAILED: Left / Right Wing Spanwise Splice Stringer L-15Lower surface spanwise splice stringer L-15 between ribs 8 and 9.
8-00 INTERNAL - DETAILED: Left / Right Wing Front Spar Lower Chord, Rib 7&9Front spar lower chord between ribs 7 and 9.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-32
IONS
5nd).
S 1C NOTE
ALL NOTE ALL
5 S 4C ALL ALL
5 cluding access S 4C ALL ALL
5 075) and Wing S 4C ALL ALL
5 rib 36 including S 4C 400E ALL
5 S 4C ALL NOTE ALL
5inspection).
a inside of S 4C 400E ALL
5 outboard end of sembly, upper nd actuator;
S 1C ALL ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
7-550-00
INTERNAL - GENERAL VISUAL: Left / Right Wing Inboard Dry BayWing lower surface, Wing Station (WS) 314.3 to (WS) 404.4 front spar to aft dry bay barrier (leveling compou
INTERVAL NOTE: Or 15 months, whichever comes first.
AIRPLANE NOTE: Applicable to airplanes prior to line number 260.
7-552-00 INTERNAL - DETAILED: Left / Right Trailing Edge Flap Support Backup StructureWing trailing edge flap support backup structure forward of rear spar at ribs 17 and 24.
7-552-91 NOTE
INTERNAL - GENERAL VISUAL: Surge Tank - Left / Right WingLeft and right wing upper and lower surfaces. Front and rear spars, and inspar ribs between ribs 31 and 34 inhole cutouts, and rib attach posts to front and rear spars.
NOTE: This inspection can be accomplished concurrently with MPD item number 57-842-00.
7-554-00INTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Dry BayLeft/right wing upper and lower surfaces, front and rear spars, and inspar ribs between rib 34 (Wing Station 1Buttock Line 929 including access hole cutout and rib attach posts to front and rear spars.
7-556-00INTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Dry BayWing upper and lower surfaces, front and rear spars, and inspar ribs between rib 34 (Wing Station 1075) andaccess hole cutout and rib attach post to front and rear spars.
7-558-00INTERNAL - GENERAL VISUAL: Left / Right Wing Tip and Outboard Side of Wing Buttock Line 929 RibWing tip and outboard side of Wing Buttock Line (WBL) 929 rib.
AIRPLANE NOTE: Applicable to ALL airplanes except 400E.
7-560-00
INTERNAL - SPECIAL DETAILED: Wing Tip Rib & Outboard Side of Rib 36 Left and RightRaked wing tip rib, rib attachment to skin and attach bolts (wing tip rib to rib 36 attachment bolts) (Borescope
NOTE: Use illuminated borescope. Inspect raked wing tip rib, attachment to skin, attach bolts and general areraked wing tip. Insert borescope through holes in rib 36 and raked wing tip rib.
7-564-00
INTERNAL - GENERAL VISUAL: Left / Right Wing Trailing Edge Support Structure & Rear SparWing Trailing Edge (TE) support structure and wing rear spar and skin from Wing Buttock Line (WBL) 97.9 toinboard aileron including: main landing gear beam and support structure; lower stabilizer beam/strut/brace asstabilizer beam/strut/brace (-400 only) support structure for main landing gear drag brace, forward trunnion, asupport structure for inboard aileron, flap, and # 5, # 6, # 7, and # 8 spoilers including actuator supports.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-33
57-56 S 2C ALL ALL
57-56 S 1A ALL ALL
57-57 n of main S 5A ALL ALL
57-57 S 4C ALL ALL
57-57NOT
surface in S 1C ALL ALL
57-58 S 2C ALL ALL
57-58 S 4C ALL NOTE ALL
57-58 S 1A ALL ALL
57-59 tock Line S 2C ALL ALL
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
6-00 INTERNAL - DETAILED: Left / Right Upper Wing / Side of Body SpliceWing upper surface side of body splice at the rear spar including the kick fitting.
8-00 EXTERNAL - GENERAL VISUAL: Left / Right Wing Trailing EdgeWing trailing edge.
0-00EXTERNAL - GENERAL VISUAL: Left / Right Main Gear Drag Brace & MLG BeamMain landing gear drag brace support fitting attached to wing rear spar at Wing Station (WS) 220 and visible portiolanding gear beam.
8-00 INTERNAL - GENERAL VISUAL: Left / Right Wing Inboard Trailing EdgeInboard trailing edge flap box except in area of outboard support structure.
8-91 E
EXTERNAL - GENERAL VISUAL: Inboard Trailing Edge Flap - Left / Right WingLeft and right wing inboard trailing edge flap including linkage, support fittings, support beam, and main flap lowerarea of flap outboard support.
NOTE: This inspection can be accomplished concurrently with MPD item number 57-850-00.
0-00 INTERNAL - GENERAL VISUAL: Left / Right Wing Inboard Trailing EdgeWing inboard flap box in area of outboard support structure.
4-00INTERNAL - SPECIAL DETAILED: Left / Right Wing Inboard Trailing Edge Flap BoxWing inboard trailing edge flap to support No. 3 / 6 beam attach bolts - re-torque.
AIRPLANE NOTE: Applicable to line numbers 922 and on, and all 400E airplanes.
6-00 EXTERNAL - GENERAL VISUAL: Left / Right Wing Inboard Trailing Edge FlapWing inboard trailing edge flap.
6-00INTERNAL - GENERAL VISUAL: Wing Trailing Edge Support Structure / Rear Spar Left and RightWing trailing edge support structure and wing rear spar and skin from outboard end of inboard aileron to Wing But(WBL) 929.1/ rib 36 including support structure for outboard aileron, flap and spoilers including actuator supports.
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-34
IONS
5 n wing STA. S 1C ALL ALL
5 S 4C ALL ALL
5 S 2C ALL ALL
5vice bulletin
S 4C ALL NOTE ALL
5 S 1A ALL ALL
5 nd rib, and flap aft regardless of S 1C ALL ALL
5ing attach fitting, nd links. S 2C 400E
NOTE ALL
5 S 1C ALL ALL
MN INTERVAL APPLICA-
BILITY ENG
JU
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991
767-200/300/300F/400ER AIRWORTHINESS LIMITAT
7-596-91 NOTE
INTERNAL - GENERAL VISUAL: Rear Spar To Wing Trailing Edge - Left / Right WingLeft and right wing rear spar and skin in area of outboard aileron actuator and hinge support structure betwee1006.7 and STA. 1031.7.
NOTE: This inspection can be accomplished concurrently with MPD item number 57-854-00.
7-598-00 INTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Trailing Edge Flap BoxOutboard trailing edge flap box except in area of support structure.
7-600-00 INTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Trailing Edge Flap BoxWing outboard trailing edge flap box in area of support structure.
7-602-00
INTERNAL - SPECIAL DETAILED: Left / Right Wing Outboard Trailing Edge Flap BoxWing outboard trailing edge flap to support beam attach bolts - re-torque.
AIRPLANE NOTE: This task is applicable to airplanes line numbers 1 through 710 that have incorporated ser767-27A0155, and to all airplanes line number 711 and on.
7-604-00 EXTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Trailing Edge FlapWing outboard trailing edge flap.
7-606-00EXTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Trailing Edge FlapWing outboard trailing edge flap including linkage, support fittings, support beam, outboard auxiliary support alower surface in areas of flap supports. For Airplanes which are line numbers 922 and later, and all 400E aircrline number, also inspect the inboard auxiliary support and rib.
7-616-00
INTERNAL - GENERAL VISUAL: Left / Right Wing Inboard Trailing Edge FlapWing inboard trailing edge flap support mechanism No. 3 / 6 including actuator support rib assembly, underwaft flap drive, flap box attachment fasteners, reaction ring, drive arm, fuse pins, flap support pins, all beams a
AIRPLANE NOTE: Applicable to all 400E airplanes and applicable to all airplanes L/N 883 and later.
7-616-91 NOTE
INTERNAL - GENERAL VISUAL: Left/Right Wing Inboard Flap - Outboard Flap SupportLeft and right wing inboard TE flap, outboard support linkage.
NOTE: This inspection can be accomplished concurrently with MPD item number 57-860-00.
PD ITEM UMBER INSPECTION LEVEL and TASK DESCRIPTION
L 2018
NS
ils Page A.1-35
57-61 ing tension s, all beams S 2C 400E ALL
57-61NOT S 1C ALL ALL
57-61NOT S 1C ALL ALL
57-68 S 4C ALL NOTE ALL
71-60 and aft S 1C ALL
4000 7R4 80A80C
71-60 and aft ENG CNG
<1> ALL
4000 7R4 80A80C
<1
<2
ocedure" (EZAP) with guidance from Advisory Circular on of combustible materials; 2) detect EWIS component ntenance programs.
This appendix includes definitions of other terms related C 25-27.
MPD INUMB INTERVAL APPLICA-
BILITY ENG
JUL 20
767-200/300/300F/400ER AIRWORTHINESS LIMITATIO
D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta
EXPORT CONTROLLED - EAR ECCN: 9E991
8-00INTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Trailing Edge FlapWing outboard trailing edge flap support mechanism No. 1 / 8 and No. 2 / 7 including rear spar fitting, rear spar fittbolts, flap box attachment fasteners, reaction ring and doubler, drive arm, swivel fitting, fuse pins, flap support pinand links.
8-91 E
INTERNAL - GENERAL VISUAL: Inboard Flap Support Fairing - Left / Right Outboard FlapLeft and right wing outboard TE flap, inboard support linkage.
NOTE: This inspection can be accomplished concurrently with MPD item number 57-862-00.
8-92 E
INTERNAL - GENERAL VISUAL: Outboard Flap Support Fairing - Left / Right Outboard FlapLeft and right wing outboard TE flap, outboard support linkage.
NOTE: This inspection can be accomplished concurrently with MPD item number 57-864-00.
6-00INTERNAL - DETAILED: Side of Body Rib Lower Chord Cutouts Left and RightArea surrounding side of body rib lower chord cutouts from rear spar to spanwise beam No. 2.
AIRPLANE NOTE: Airplanes with two-bay or four-bay center section fuel tank.
0-00INTERNAL - DETAILED: No. 1 / 2 Power PlantForward engine mount bulkhead fitting, visible portion of diagonal brace attach fitting at aft end of firewall, forwardengine mounts, links, and attachments.
2-00
INTERNAL - GENERAL VISUAL: No. 1 / 2 Power PlantForward engine mount bulkhead fitting, visible portion of diagonal brace attach fitting at aft end of firewall, forwardengine mounts, links, attachments, and strut lower surface (firewall).
ACCESS NOTE: At engine removal.
> Engine Change
>
To comply with 14 CFR 26.11(b), an analysis was conducted for each maintenance zone using an "Enhanced Zonal Analysis Pr(AC) 25-27. The objective of the EZAP analysis was to identify maintenance and inspection tasks to: 1) minimize the accumulatidefects; and 3) detect EWIS installation discrepancies that may not be reliably detected by inspections contained in existing mai
The term "EWIS" is defined in the 767 Maintenance Review Board Report (MRBR), D622T001-MRBR, Appendix D, Definitions. to EZAP tasks such as: "Power Feeder Wiring" and "Combustible Materials". For all other definitions related to EZAP, refer to A
TEM ER INSPECTION LEVEL and TASK DESCRIPTION
18
details Page A.1-36
IONS
BL
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991