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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)

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D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for deta

EXPORT CONTROLLED - EAR ECCN: 9E991

767-200/300/300F/400ERAIRWORTHINESS LIMITATIONS (AWLs

D622T001-9-01

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BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for EXPORT CONTROLLED - EAR ECCN: 9E991

767-200/300/300F/400ER AIRWORTHINESS LIMITAT

THIS PAGE INTENTIONALLY LEFT BLANK

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REVIS .............................................................. 1.0-5

LIST O ............................................................ 1.0-18

A. SC ............................................................ 1.0-19

B. AIR ............................................................ 1.0-20

C. AIR ............................................................ 1.0-93

D. AW ............................................................ 1.0-95

APPE ..............................................................A.0-1

A. S ..............................................................A.0-1

B. S ..............................................................A.1-1

JUN 20




TABLE OF CONTENTS

IONS ....................................................................................................................................................................

F EFFECTIVE PAGES ........................................................................................................................................

OPE.......................................................................................................................................................................

WORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS..........................................................................

WORTHINESS LIMITATIONS - STRUCTURAL SAFE LIFE PARTS ...................................................................

LS - STRUCTURAL LIMIT OF VALIDITY (LOV)...................................................................................................

NDIX A – STRUCTURES BASELINE REQUIREMENTS......................................................................................

COPE...................................................................................................................................................................

TRUCTURES BASELINE INSPECTION REQUIREMENTS ...............................................................................

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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




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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IONS

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

JU
D622T001-9-01


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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JULY 201

ATA 52

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

ATA 53

Revised

Added th53-10-I0653-10-I3253-10-I3253-10-I3453-50-I2953-50-I29

Deleted t53-30-I0153-30-I0153-60-I29

Fuselage o other existing SSIs. As a result, updates have been maThe upda53-30-I2453-30-I2453-10-I0853-10-I0853-30-I24

JUN 20




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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ATA

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


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JULY 201

ATA 53, C

Revised 53-10-I1053-30-I0153-30-I1953-30-I1953-30-I1953-50-I0653-50-I0653-60-I1053-60-I1053-60-I1053-60-I2953-60-I2953-60-I29

Revised 53-10-I0753-10-I0753-10-I1053-10-I1053-10-I1453-10-I2053-10-I2153-10-I2153-30-I1453-30-I1953-30-I1953-30-I1953-30-I1953-30-I1953-30-I2053-30-I2253-30-I2253-30-I2753-30-I2853-30-I2853-30-I28

JUN 20




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


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ATA

Revi53-353-353-353-353-553-553-553-653-653-653-653-353-653-653-653-653-653-653-653-653-653-653-653-653-653-653-8

Revi53-353-853-853-853-853-8

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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


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JULY 201

ATA 54

Revised

Revised

Revised 54-50-I0154-50-I0154-50-I0154-50-I0154-50-I0354-50-I0454-50-I0454-50-I1754-50-I1754-50-I17

Revised 54-50-I0154-50-I0454-50-I0454-50-I0654-50-I0654-50-I0654-50-I0654-50-I1054-50-I1054-50-I1454-50-I1454-50-I1754-50-I1754-50-I1854-50-I18

JUN 20




8, Continued

20 SSIs to clarify the title.

59 SSIs to clarify the notes.

the following SSIs to change the recommended inspection interval: JT9D PW4000 CF6-80C (Except 400E)c CF6-80C (400E) ≥ 8 Hoursb 524c CF6-80C (400E) ≥ 8 Hourse CF6-80C (400E) < 8 Hourse CF6-80C (400E) ≥ 8 Hourse CF6-80C (400E) < 8 Hoursf CF6-80C (400E) < 8 Hours

the following SSIs to change the recommended inspection type:c CF6-80C (400E) ≥ 8 Hoursc CF6-80C (400E) ≥ 8 Hourse CF6-80C (400E) ≥ 8 Hours JT9D PW4000 CF6-80A CF6-80C (Except 400E)b CF6-80C (400E) < 8 Hoursb CF6-80C (400E) ≥ 8 Hours CF6-80C (400E) < 8 Hours CF6-80C (400E) ≥ 8 Hourse CF6-80C (400E) ≥ 8 Hoursf CF6-80C (400E) < 8 Hours CF6-80C (400E) < 8 Hours CF6-80C (400E) ≥ 8 Hours


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ATA

Adde54-554-554-554-554-554-554-554-5

Revi54-554-554-5

Revi plicable 767 Non-Destructive Testing Manual:54-554-554-554-554-554-554-554-554-554-554-554-554-554-554-554-554-554-554-554-554-554-554-5

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2018, Continued

54, Continued

d the following SSIs:0-I01d 80C (400E) < 8 Hours0-I01d 80C (400E) ≥ 8 Hours0-I01e 80C (400E) 0-I13f 80C (400E) < 8 Hours0-I13f 80C (400E) ≥ 8 Hours0-I16f 80C (400E)0-I17g CF6-80C (400E) < 8 Hours0-I17g CF6-80C (400E) ≥ 8 Hours

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)


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ATA 54, C

Revised ble 767 Non-Destructive Testing Manual, Continue54-50-I1354-50-I1454-50-I1654-50-I1654-50-I1754-50-I1754-50-I1754-50-I17

ATA 55

Revised

ATA 57

Revised

Revised

Revised 57-10-I0357-10-I0357-10-I0357-10-I0357-10-I0357-10-I0357-10-I2457-10-I2457-53-I04

Revised threshold:57-10-I0357-10-I0357-10-I0357-20-I1557-20-I16

JUN 20




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


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Revi57-257-2

Revi

Adde

Revi 8 hours.

Revi airplanes with stage length > 8 hours.

Revi to differentiate it from bolt shank inspections.

Revi to differentiate it from SSI 57-53-I03F.1

Revi

Revi57-2

Revi plicable 767 Non-Destructive Testing Manual:57-157-157-157-157-257-257-557-557-557-557-557-557-557-557-557-557-557-557-5

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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


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ATA 57, C

Revised ble 767 Non-Destructive Testing Manual (continue

57-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-53-I0457-54-I1357-54-I14

Revised , to reflect the 200SF & 300BCF fatigue requirem57-10-I1657-10-I1657-20-I1557-20-I16

JUN 20




8, Continued

ontinued

the following SSIs to remove the Flagnote <2> as inspection procedures for these items have been published in the applicad):

A.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921B.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-882B.3 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-882D.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-882E.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921E.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921E.3 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921F.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921F.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921H 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921I ALLK.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921N.1 200, 200SF, 300BCF, 300F, 300 PASS L/N 922 and later and 400ERP ALLQ.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921Q.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921S ALLT ALLAA 200, 200SF, 300BCF, 300F, 300 PASS L/N 922 and later and 400ER 400ER 400ER

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


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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)

N 2019

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JUNE 20

ATA 54

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

JUN 20




19, Continued

SIs 54-50-I01f (80C (400E), < 8 Hours), 54-50-I01f (80C (400E), ≥ 8 Hours), 54-50-I04f (80C (400E), < 8 Hours), 54-50-I04 8 Hours), 54-50-I13g (80C (400E), ≥ 8 Hours), 54-50-I17h (80C (400E), < 8 Hours), and 54-50-I17h (80C (400E), ≥ 8 Hou

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.

19

Section P ate Section Page Date

Page 1.0-18

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1.01.01.01.01.01.01.01.01.01.0 11.0 11.0 11.0 11.0 11.0 11.0 11.0 11.0 11.0 11.0 21.0 21.0 21.0 21.0 21.0 21.0 21.0 21.0 21.0 21.0 31.0 31.0 31.0 31.0 31.0 31.0 31.0 31.0 31.0 3

UL 2018UL 2018UL 2018UL 2018UL 2018UL 2018UL 2018

N 2019UL 2018UL 2018UL 2018UL 2018UL 2018UL 2018UL 2018UL 2018BLANK

JUN 201

age Date Section Page Date Section Page Date Section Page D

D622T001-9-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details


LIST OF EFFECTIVE PAGES767-200/300/300F/400ER AIRWORTHINESS LIMITATIO

1 JUN 20192 BLANK3 JUN 20194 BLANK5 JUN 20196 JUN 20197 JUN 20198 JUN 20199 JUN 20190 JUN 20191 JUN 20192 JUN 20193 JUN 20194 JUN 20195 JUN 20196 JUN 20197 JUN 20198 JUN 20199 JUN 20190 JUL 20181 JUL 20142 JUL 20143 JUN 20194 JUL 20185 JUL 20146 JUL 20147 JUL 20188 JUL 20189 JUL 20180 JUL 20181 JUL 20182 JUL 20183 JUL 20184 JUL 20185 JUL 20186 JUN 20197 JUN 20198 JUL 20189 JUN 2019

1.0 40 JUN 20191.0 41 JUL 20181.0 42 JUN 20191.0 43 JUN 20191.0 44 JUN 20191.0 45 JUL 20181.0 46 JUN 20191.0 47 JUN 20191.0 48 JUL 20181.0 49 JUL 20181.0 50 JUL 20181.0 51 JUL 20181.0 52 JUL 20181.0 53 JUN 20191.0 54 JUN 20191.0 55 JUN 20191.0 56 JUN 20191.0 57 JUL 20181.0 58 JUN 20191.0 59 JUN 20191.0 60 JUL 20181.0 61 JUL 20181.0 62 JUL 20181.0 63 JUN 20191.0 64 JUN 20191.0 65 JUL 20181.0 66 JUL 20181.0 67 JUL 20181.0 68 JUL 20181.0 69 JUL 20181.0 70 JUL 20181.0 71 JUL 20181.0 72 JUL 20181.0 73 JUL 20181.0 74 JUL 20181.0 75 JUL 20181.0 76 JUN 20191.0 77 JUL 20181.0 78 JUL 2018

1.0 79 JUL 20181.0 80 JUL 20181.0 81 JUL 20181.0 82 JUL 20181.0 83 JUN 20191.0 84 JUL 20181.0 85 JUL 20181.0 86 JUL 20181.0 87 JUL 20181.0 88 JUL 20181.0 89 JUL 20181.0 90 JUL 20181.0 91 JUL 20181.0 92 JUL 20181.0 93 FEB 20151.0 94 FEB 20151.0 95 DEC 20151.0 96 BLANKA.0 1 JUN 2019A.0 2 BLANKA.1 1 JUL 2018A.1 2 JUL 2018A.1 3 JUL 2018A.1 4 JUL 2018A.1 5 JUL 2018A.1 6 JUL 2018A.1 7 JUL 2018A.1 8 JUN 2019A.1 9 JUL 2018A.1 10 JUL 2018A.1 11 JUN 2019A.1 12 JUL 2018A.1 13 JUL 2018A.1 14 JUL 2018A.1 15 JUN 2019A.1 16 JUL 2018A.1 17 JUL 2018A.1 18 JUL 2018A.1 19 JUL 2018

A.1 20 JA.1 21 JA.1 22 JA.1 23 JA.1 24 JA.1 25 JA.1 26 JA.1 27 JUA.1 28 JA.1 29 JA.1 30 JA.1 31 JA.1 32 JA.1 33 JA.1 34 JA.1 35 JA.1 36

9

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A. SCO

The ctivities with the U.S. Federal Aviation

Adm e Model 767 Type Certificate Data

Shee

This of Federal Regulations (CFR) § 43.16

and s document must be used in its entirety

at a combined.

Whe ight responsibility for the type certificate

of th te of the 767 is the FAA Boeing Aviation

Safe

AIRW

The

If the the FAA Oversight Office must be

used

CHA

With aintenance program to incorporate all

the c

JUN 20




PE

scheduled maintenance requirements described in this document result from Model 767 airplane certification a

inistration (FAA). Accordingly, this FAA approved Airworthiness Limitations document is cross-referenced in th

t. These maintenance actions are mandatory.

Airworthiness Limitations document is FAA approved and specifies maintenance required under Title 14 Code

§ 91.403 unless an alternative program has been FAA Oversight Office approved. The Airworthiness Limitation

specific revision level, and maintenance requirements and limitations from different revision levels shall not be

re used in this document, the term “FAA Oversight Office” is defined as the FAA office that currently has overs

e Boeing model 767. At the time of publication, the FAA office with oversight responsibility for the type certifica

ty Oversight Office (BASOO).

ORTHINESS LIMITATIONS

Airworthiness Limitations may only be revised with the approval of the FAA Oversight Office.

inspections cannot be accomplished due to repairs and/or modifications, an alternate inspection approved by

.

NGE INCORPORATION

in 24 months after the release date of the June 2019 version of this document, operators should revise their m

hanges contained in this document, including Appendix A.

19

details Page 1.0-20

IONS

B. A

and contained in Section 2 of the

M m for all Structural Significant Items (SSIs).

T ts of Title 14 CFR § 25.571 by providing

a etection opportunity until the supplemental

i s” document are for those SSIs that do not

r in Section 2 of the MPD and in Appendix A

o with and not as a substitute for the existing

s

T e the inspections (and repeat intervals)

n cal value) that must be achieved for each

S D622T001-DTR.

T

T categories are referred to as Type 1 and

pe 2 structure is allowed to have the

escalation of the inspection threshold when

1-DTR for a detailed definition of Type 1

and repeat inspections determined from

JU
D622T001-9-01


IRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS

The Structural Inspection Program approved in Section 3 of the 767 Maintenance Review Board (MRB) Report

aintenance Planning Document (MPD) D622T001 describes an initial baseline structural maintenance progra

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.

L 2018

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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




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

details Page 1.0-22

IONS

CURVE

2

3 Threshold Curve. Note that the shaded area

d -400ER Passenger aircraft.

JU
D622T001-9-01


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

L 2014

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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

JUN 20




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.

19

details Page 1.0-24

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.

JU
D622T001-9-01


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

L 2018

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45000 50000

oubler

anel)er Row

JUL 20




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

14

details Page 1.0-26

IONS

JU
D622T001-9-01


FIGURE 3. Mod Date Sensitive Structure

L 2014

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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:

JUL 20




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

18

details Page 1.0-28

IONS

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.

JU
D622T001-9-01


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

L 2018

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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.

JUL 20




- 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.


EM AIRPLANE APPLICABILITY


INSTALLATION DRAWING DESCRWHEREGenera

1. Any sreapplie

2. Do nounless w

NUMBER TITLE

18

details Page 1.0-30

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.


neral Notes



JU
D622T001-9-01


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


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


112T1000

112T4000

Rear Spar Instl - Wing

Panel Installation - Inspar, Wing, Lower

Priofollo

1. Rthe

2. Espafrom

3. Echothe





1. Area

2. Dunl

NUMBER TITLE

L 2018

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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


l Notes



JUL 20




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





1. Any sreapplie

2. Do nounless w

NUMBER TITLE

18

details Page 1.0-32

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.


neral Notes



JU
D622T001-9-01


10. Wing - tboard - Front r Lower Chord idden Details

400ER with stage length < 8 hours 57-538-00 FLS 112T2000 Front Spar Instl - Wing

PrioRibextsea

1. Ehorthe

2. Everbelfas

11. Wing - tboard - Rear r Lower Chord

400ER 57-538-00 FLS 112T1000 Rear Spar Instl - Wing

PrioRibreq

1. Ehorinchfas

2. Evernea





1. Area

2. Dunl

NUMBER TITLE

L 2018

NS

ils Page 1.0-33

12. WOutboa

Spar Low

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


l Notes



JUL 20




ing - rd - Rear er Chord

400ER with stage length > 8 hours 57-538-00 FLS 112T1000 Rear Spar Instl - Wing

Prior to Rib 3 anfollowin

1. Ensuspar chothe nea

2. Ensuvertical below thfastener

ing - rd - Rear er Chord

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





1. Any sreapplie

2. Do nounless w

NUMBER TITLE

18

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.


neral Notes



JU
D622T001-9-01


14. Wing - board - Lower rface Splice

Stringers - ringers L-10

ALL except 200SF and 300BCF 57-540-00


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





1. Area

2. Dunl

NUMBER TITLE

L 2018

NS

ils Page 1.0-35

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




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

= Passenger Airplanes < 8 HOURS = Airplanes with cumulative stage length (Flight Hour

= 767-200, -200ER

F = 767-200 Special Freighter

ASS = 767-300, -300ER > 8 HOURS = Airplanes with cumulative stage length (Flight Hour

CF = 767-300 Boeing Converted Freighter

= All 767-300 Freighters

= 767-400ER

= P&W PW4052, PW4056, PW4060, PW4062

= P&W JT9D-7R4D and -7R4E

= GE CF6-80A

= GE CF6-80C

= RR RB211-524H

18

details Page 1.0-36

IONS

SAIRPLANE/

ENGINE PPLICABILITY TYPE AND THRESHOLD

2 ALL Type 150,000 Cycles

(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)

2 400E Type 140,000 Cycles

5 200, 200SF0BCF, 300 PASS

400E

Type 1 50,000 Cycles

(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (400E)5 ALL Type 2

50,000 Cycles (200, 300 PASS)

40,000 Cycles (300BCF, 300F, 400E)

5 ALL Type 1 37,500 Cycles

(200, 300 PASS)30,000 Cycles

(300BCF, 300F, 400E)5 ALL Type 1

37,500 Cycles (200, 300 PASS)

30,000 Cycles (300BCF, 300F, 400E)

5 200SF300BCF, 300F

Type 2 40,000 Cycles (300F)

50,000 Cycles (200SF)Mod Date Sensitive (300BCF)

JU
D622T001-9-01


AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTION

SSI # DTR CHECK FORM TITLEINSPECTION

ZONE A7-40-I01A Stabilizer Trim Actuator - Lower Gimbal Lug Assy BS 1708.5, WL 239.9 311, 312

7-40-I01B Stabilizer Trim Actuator - Lower Gimbal Plate Assy BS 1708.5, WL 239.9, BL 0.0 311, 312

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)


52-30 200SFBCF, 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




-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

838300

-I07E MDCD Outer Skin Lap Splice - Upper row (upper skin) - Intercostal #5 838300

-I07F MDCD Outer Skin Lap Splice - Lower row (lower skin) - Intercostal #5 838300

-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.

123

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS

I # DTR CHECK FORM TITLEINSPECTION

ZONE

AIRE

APPL

19

details Page 1.0-38

IONS

555

ALL Type 250,000 Cycles

(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)

555

ALL Type 250,000 Cycles

(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)

555

ALL<2>

Type 250,000 Cycles

(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E) 555

ALL<2>

Type 250,000 Cycles

(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)

55

LL Except 200SF, 300BCF

Type 250,000 Cycles (200, 300 PASS)

40,000 Cycles (300F, 400E)

5 200SF, 300BCF Type 250,000 Cycles (200SF, 300BCF)

SAIRPLANE/


JU
D622T001-9-01


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



ZONE A

L 2018

NS

ils Page 1.0-39

53-1053-3053-60

L Except F, 300BCF


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)


(200, 200SF, 300BCF,300 PASS)

40,000 Cycles (300F, 400E)


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)

SS


JUN 20




-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



ZONE

AIRE

APPL

19

details Page 1.0-40

IONS


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)

SAIRPLANE/


JU
D622T001-9-01


3-10-I14A Window #1 Cutout Structure - AB POST 211, 212

3-10-I14B Window #1 Cutout Structure - BD SILL 211, 212

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



ZONE A

N 2019

NS

ils Page 1.0-41


(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>


40,000 Cycles (300F, 400E)


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)

SS


JUL 20




-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

119



ZONE

AIRE

APPL

18

details Page 1.0-42

IONS


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)5 ALL Type 1

50,000 Cycles (200, 200SF, 300BCF,

300 PASS)40,000 Cycles (300F, 400E)

5 ALLL/N 758 and on


40,000 Cycles (300F, 400E)

5 ALL Type 250,000 Cycles (200, 200SF, 300

PASS, 300BCF)40,000 Cycles (300F, 400E)

5 ALLExcept 300F

Type 250,000 Cycles (200, 200SF, 300

PASS, 300BCF)40,000 Cycles (400E)

5 200SF, 300BCF<4>

Type 250,000 Cycles

5 200SF, 300BCF<4>


Mod Date Sensitive (300BCF)

SAIRPLANE/


JU
D622T001-9-01


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


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



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


JUN 20




-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

122, 124, 154, 156, 161, 163, 221, 222, 231, 232, 251, 252

-I01-I01-I01

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

-I01 BCF2 - Crown Doubler Aft Edge Circumferential Crack - BS 654+115, S-7L to S-7R 231, 232 3

-I01 BCF3 - Circumferential Splice - Upper Crown - BS 654+22 233, 234 3

-I01 BCF5 - Crown Skin Doubler - Longitudinal Crack in Skin at forward corners - BS 654+22, S-8L and S-8R

231, 232 3

-I01 BCF9 - Fuselage Crown Skin - BS 654+115 to 786, S-4L to 4R 231, 232 3

-I01 BCF10 - Fuselage Crown Stringers - BS 654+110 to 786, S-4L to 4R 230 3

-I01 SF1 - Crown Skin Doubler - RHS Edge of Crown Skin Doubler at RBL 9 233, 234

-I01 SF2 - Crown Skin Doubler - Aft Edge BS 742 233, 234



ZONE

AIRE

APPL

19

details Page 1.0-44

IONS

5 200SF Type 250,000 Cycles

5 200SF<4>

Type 250,000 Cycles


5 200SF<4>

Type 237,500 Cycles

5 200SF<4>

Type 225,000 Cycles

5 300BCF Type 2Mod Date Sensitive (300BCF)

5 300BCF Type 2Combined Threshold

5 300BCF Type 2Mod Date Sensitive

5 200SF, 300BCF Type 230,700 Cycles (200SF)

Combined Threshold (300BCF)5 200SF

300BCF<4>


Combined Threshold (300BCF)


SAIRPLANE/


JU
D622T001-9-01


3-30-I01 SF3 - Crown Skin Doubler - Stringer at Circumferential Splice 233, 234

3-30-I01 SF5 - Crown Skin Doubler - At BS 676 Skin Splice, at S-8L and S-2R 233, 234

3-30-I01 SF6 - Crown Skin Doubler - At VHF Comm. Antenna Installation at BL 0.0, BS 698 to 720

233, 234

3-30-I01 SF9 - Section 43 Crown Skin - Aft of External Doubler 233, 234

3-30-I01 SF10 - Section 43 Crown Stringers - Aft of External Doubler 233, 234

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



ZONE A

N 2019

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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


JUL 20




-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

230, 240, 250L/N 1

-I08A Fuselage Circumferential Skin and Stringer Splice - BS 434 120, 220, 230L/N 1



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IONS

5 200300 PASS

Type 250,000 Cycles


5 300FL/N 1070 and on

<3>

Type 140,000 Cycles

5 200300 PASS

<2>

Type 250,000 Cycles

5 200300 PASS

Type 250,000 Cycles

5 200300 PASS

Type 250,000 Cycles

5 200300 PASS

<2>

Type 250,000 Cycles

5 200300 PASS

<2>

Type 250,000 Cycles

5 200300 PASS

<2>

Type 250,000 Cycles

5 200300 PASS

Type 250,000 Cycles

53 300BCF300F400E

Type 240,000 Cycles

SAIRPLANE/


JU
D622T001-9-01


3-30-I14A Forward Main Cargo Door Cutout - Edge Frames - Frames at BS 539.5 & 615.5 Stringers S-17R to S-21R and S-28R to S-36R

122, 124, 232

3-30-I14A Forward Main Cargo Door Cutout - Edge Frames - Frames at BS 539.5 & 615.5 Stringers S-17R to S-36R

122, 124, 232

3-30-I15 Front Spar Bulkhead Body Station 786 - Hidden Details Under Seal Pan at S-23L/R, S-24L/R, and S-27L/R

DTR Check Form applicable to: L/N 1070 and on.

120

3-30-I19A Forward Large Cargo Door Cutout - Edge Frame Inner Chord BS 478, S-23R to S-28R and BS 618, S-27R to S-28R and S-29R to S-30R

122

3-30-I19B Forward Large Cargo Door Cutout - Edge Frame Inner Chord BS 478, S-26R to S-27R and BS 618, S-29R to S-30R

122

3-30-I19C Forward Large Cargo Door Cutout - Edge Frame Inner Chord BS 618, S-28R to S-29R

122

3-30-I19D Forward Large Cargo Door Cutout - Upper Main Sill - Inner CordBS 456 to BS 478 and BS 482 to BS 493

122, 124

3-30-I19E Forward Large Cargo Door Cutout - Upper Main Sill - Inner CordBS 478 - BS 479.5

122

3-30-I19F Forward Large Cargo Door Cutout - Upper Main Sill - Inner CordBS 479.5 to BS 482

122

3-30-I19G Forward Large Cargo Door Cutout - Upper Main Sill - Inner CordBS 482 to BS 493

122

-30-I19AB Forward Large Cargo Door Cutout - Edge Frame Inner ChordBS 478, S-20R to S-22R and BS 618, S-20R to S-22R

122



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53-30- 00BCF300F400E

Type 240,000 Cycles

53-30- ALL<2>

Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300BCF, 300F,

400E)53-30-I ALL

<2>Type 2

50,000 Cycles (200, 300 PASS)40,000 Cycles (300BCF, 300F,

400E)53-30- ALL

<2>Type 2


400E)53-30-I ALL

<2>Type 2


400E)53-30 ALL

<2>Type 2

50,000 Cycles (200, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)53-30 0 PASS

400EType 2

50,000 Cycles (300 PASS)40,000 Cycles (400E)

53-30 0 PASS<2>

Type 250,000 Cycles

53-30 400E<2>

Type 240,000 Cycles

SS


JUN 20




I19AC Forward Large Cargo Door Cutout - Edge Frame Inner Chord BS 478, S-17R to S-20R and S-22R to S-23R

122, 232 3

I19AD Forward Large Cargo Door Cutout - Upper Main Sill - Inner Chord BS 607 to BS 618

122

19AD1 Forward Large Cargo Door Cutout - Upper Main Sill - Inner Chord Covered LocationsBS 607 to BS 618

122

I19AF Forward Large Cargo Door Cutout - Lower Main Sill Inner Chord Covered LocationsBS 466 to BS 483 and BS 614 to BS 625

124

19AF1 Forward Large Cargo Door Cutout - Lower Main Sill Inner Chord BS 466 to BS 483 and BS 614 to BS 625

124

-I20A Forward Large Cargo Door Cutout - Lower Latch Backup Structure - Latch Support Fitting at BS 487.7 & BS 608.3

124

-I22C Mid Passenger Entry/Service Door Cutout - Edge Frame - Inner Chord - BS 654+44, S-8 to S-15 and BS 654+91.4, S-8 to S-20

230 30

-I22D Mid Passenger Entry/Service Door Cutout - Upper Main Sill Inner Chord - BS 654+33 to BS 654+110

230 30

-I22D Mid Passenger Entry/Service Door Cutout - Upper Main Sill Inner Chord - BS 654+33 to BS 654+110

230



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IONS

5555

LL Except 200SF, 300BCF


40,000 Cycles (300F, 400E)

555

200SF<4>

Type 250,000 Cycles

55555

300BCF Type 250,000 Cycles

55555

200SF Type 250,000 Cycles

55

300BCF<4>

Type 250,000 Cycles

55

200SF300BCF

<4>

Type 250,000 Cycles (200SF, 300BCF)

5 300BCF Type 250,000 Cycles

555

200SF<4>

Type 150,000 Cycles

SAIRPLANE/


JU
D622T001-9-01


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.

230, 240, 250

3-30-I24A3-30-I24B

BCF2, BCF4 Frames - (Partially Visible) - Above S-20BS 434 to BS 786For additional frame inspection requirements, see entry for BCF1 SSI # 53-30-I24A / 53-30-I24B / 53-50-I01A / 53-50-I02A / 53-60-I08A.

231, 232

3-30-I24C3-60-I08C

BCF6 Frames - (Partially Visible) - S-20 and BelowBS 434 to BS 786 and BS 1065 to BS 1582For additional frame inspection requirements, see entry for BCF5 SSI # 53-10-I08C / 53-30-I24C / 53-60-I08C.

100

3-30-I27 BCF2 Fuselage Circumferential Splice in the Body Crown - BS 654+22, S-8L to S-8R 231, 232

3-30-I27A3-50-I033-60-I03

Fuselage Circumferential Splices in the Body CrownApplicable to:1) BS 676: S-4L TO S-4R2) BS 1065: S-9L TO S-9R3) BS 1395: S-8L TO S-8R

230, 240, 250



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53-30 00BCF<4>

Type 250,000 Cycles

53-30 200SF<4>

Type 250,000 Cycles

53-30 200SFBCF, 300F3>,<4>



53-30 200SFBCF, 300F3>,<4>



53-30 200SFBCF, 300F3>,<4>



53-30 200SFBCF, 300F3>,<4>



53-30 200SFBCF, 300F3>,<4>

Type 250,000 Cycles (200SF)40,000 Cycles (300F)

Mod Date Sensitive (300BCF)53-30 200SF

BCF, 300F3>,<4>



53-50 200SF<4>

Type 250,000 Cycles

53-50 200 Type 250,000 Cycles

SS


JUL 20




-I28 BCF1 - Main Deck Cargo Door Cutout - Upper Auxiliary Sill Inner Chord 231 3

-I28 SF1 - Main Deck Cargo Door Cutout - Upper Auxiliary Sill Inner Chord 231

-I28A Main Deck Cargo Door Cutout - Upper Main Sill Inner Chord - BS 478 to BS 500, BS 505 to BS 514, and BS 599 to BS 610

231300

<

-I28B Main Deck Cargo Door Cutout - Lower Main Sill Inner Chord between BS 626 and BS 643

231300

<

-I28C Main Deck Cargo Door Cutout - Forward Edge Frame Inner Chord between S-4L and S-7L

233300

<

-I28D Main Deck Cargo Door Cutout - Aft Edge Frame Inner Chord - BS 632 at Frame Splice centered between S-15L and S-16L

231300

<

-I28E Main Deck Cargo Door Cutout - Aft Edge Frame Inner Chord - BS 632 - S-1L to S-3L and S-14L to S-17L

231, 233300

<

-I28F Main Deck Cargo Door Cutout - Upper and Lower Main Sill Outer Chord - BS 496 and 628

231, 233300

<

-I06 SF - Single Emergency Exit Cutout Auxiliary Sill Inner Chord 241, 242

-I06A Single Emergency Exit Cutout - Edge Frame Inner Chord 241, 242



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details Page 1.0-50

IONS


5 200 Type 250,000 Cycles











(200, 200SF, 300 PASS)40,000 Cycles

(300BCF, 300F, 400E)

SAIRPLANE/


JU
D622T001-9-01


3-50-I06A SF - Single Emergency Exit Cutout - Edge Frame Inner Chord 241, 242

3-50-I06B Single Emergency Exit Cutout - Frame Inner Chord at Sill Intersect 241, 242

3-50-I06B SF - Single Emergency Exit Cutout - Frame Inner Chord at Sill Intersect 241, 242

3-50-I06C Single Emergency Exit Cutout - Sill Inner Chord 241, 242

3-50-I06C SF - Single Emergency Exit Cutout - Sill Inner Chord 241, 242

3-50-I06D Single Emergency Exit Cutout - Sill Inner Chord at Frame Intersect 241, 242

3-50-I06D SF - Single Emergency Exit Cutout - Sill Inner Chord at Frame Intersect 241, 242

3-50-I06E Single Emergency Exit Cutout - Sill Outer Chord 241, 242

3-50-I06E SF - Single Emergency Exit Cutout - Sill Outer Chord 241, 242

3-50-I06F Single Emergency Exit Cutout - Sill Outer Chord at Frame Intersect 241, 242

3-50-I06F SF - Single Emergency Exit Cutout - Sill Outer Chord at Frame Intersect 241, 242

3-50-I11 BS 1043 Frame Splice with the Landing Gear Fitting - BS 1043, BL 92, WL 193 to WL 199

141, 142



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53-50 ALL<2>

Type 250,000 Cycles

(200, 200SF, 300 PASS)40,000 Cycles

(300BCF, 300F, 400E)53-50 ALL Type 2

50,000 Cycles (200, 200SF, 300 PASS)

40,000 Cycles(300BCF, 300F, 400E)

53-50 ALL<2>

Type 150,000 Cycles

(200, 200SF, 300 PASS)40,000 Cycles

(300BCF, 300F, 400E)53-50 ALL

pt 767-300F 070 and on

Type 125,000 Cycles

53-50 67-300F 070 and on

Type 125,000 Cycles

53-5053-5053-50

0, 200SFBCF, 300F,0 PASS

Type 250,000 Cycles

(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F)53-50 PASS Type 2

50,000 Cycles (200, 300 PASS)

40,000 Cycles (400E)

SS


JUL 20




-I13B Fuselage Rear Spar Bulkhead - Side Frame Fitting Inner Chord - BS 955, S-20 to S-21 at Seat Track Support Bracket

131, 132

-I13C Fuselage Rear Spar Bulkhead - Side Frame Fitting Inner Chord Flange - BS 955, S-18 to S-20

241, 242

-I14A Aft Wheel Well Bulkhead BS 1065 - BL 26 Vertical Beam Intercostal Upper Chord Splice

151, 152

-I14B Aft Wheel Well Bulkhead BS 1065 - Hidden Details at Outer Chord Splices S-27 to S-28 and S-35 to S-36

151, 152

-I14C Aft Wheel Well Bulkhead BS 1065 - Hidden Details at Outer Chord between S-29 & S-34

Applicable to all 767 except for 767-300F Line Numbers 1070 and on.For 767-300F Line Numbers 1070 and on: See additional entry for SSI # 53-30-I04C.

151, 152ExceL/N 1

-I14C Aft Wheel Well Bulkhead BS 1065 - Lower Lobe Outer Chord between S-29 and S-34 151, 152 7L/N 1

-I18-I24-I28

Section 45 Stub Frames - BS 808 - 933 Frame Inner Chord at Stub Beam 131, 132 20300

30

-I19 Main Landing Gear Wheel Well - BS 1021 Transverse Floor Beam Lower Chord - LBL 33 to LBL 60 and RBL 33 to RBL 60

143, 144



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IONS

5 200300 PASS

Type 250,000 Cycles


5 200300 PASS

Type 250,000 Cycles







5 300BCF<4>

Type 250,000 Cycles

5 300BCF<4>

Type 250,000 Cycles

5 200300 PASS

Type 250,000 Cycles

5 200300 PASS

Type 250,000 Cycles

5 300 PASS Type 250,000 Cycles

SAIRPLANE/


JU
D622T001-9-01


3-50-I22A Dual Emergency Exit Cutout - Edge Frame Inner Chords 241, 242

3-50-I22A BCF - Dual Emergency Exit Cutout - Edge Frame Inner Chords 241, 242

3-50-I22B Dual Emergency Exit Cutout - Frame Inner Chord at Sill Intersect 241, 242

3-50-I22B BCF - Dual Emergency Exit Cutout - Frame Inner Chord at Sill Intersect 241, 242

3-50-I22C BCF - Dual Emergency Exit Cutout - Sill Inner Chord 241, 242

3-50-I22D BCF - Dual Emergency Exit Cutout - Sill Inner Chord at Frame Intersect 241, 242

3-50-I22E BCF - Dual Emergency Exit Cutout - Upper Sill Inner Chord - BS 859.5 and BS 903.5 241, 242

3-50-I22F BCF - Dual Emergency Exit Cutout - Sill Outer Chord 241, 242

3-50-I22G BCF - Dual Emergency Exit Cutout - Sill Outer Chord at Frame Intersect 241, 242

3-50-I22 BCF1 Dual Overwing Emergency Exit Auxiliary Sill Inner Chord at Frame Intersect 241, 242

3-50-I22 BCF2 Dual Overwing Emergency Exit Auxiliary Sill Inner ChordBS 830 to BS 955

241, 242

3-50-I22C Dual Emergency Exit Cutout - Sill Inner Chord 241, 242

3-50-I22D Dual Emergency Exit Cutout - Sill Inner Chord at Frame Intersect 241, 242

3-50-I22E Dual Emergency Exit Cutout - Upper Sill Inner Chord - BS 859.5 and BS 903.5 241, 242



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53-50 2000 PASS

Type 250,000 Cycles

53-50 2000 PASS

Type 250,000 Cycles

53-50 0 PASS Type 250,000 Cycles







53-50 400E Type 240,000 Cycles




SS


JUN 20




-I22F Dual Emergency Exit Cutout - Sill Outer Chord 241, 24230

-I22G Dual Emergency Exit Cutout - Sill Outer Chord at Frame Intersect 241, 24230

-I25A Single Aft Emergency Exit Cutout - Edge Frame Inner Chord 241, 242 30

-I25B Single Aft Emergency Exit Cutout - Frame Inner Chord at Sill Intersect 241, 242 30

-I25C Single Aft Emergency Exit Cutout - Sill Inner Chord 241, 242 30

-I25D Single Aft Emergency Exit Cutout - Sill Inner Chord at Frame Intersect 241, 242 30

-I25E Single Aft Emergency Exit Cutout - Upper Sill Inner Chord - BS 903.5 241, 242 30

-I25F Single Aft Emergency Exit Cutout - Sill Outer Chord 241, 242 30

-I25G Single Aft Emergency Exit Cutout - Sill Outer Chord at Frame Intersect 241, 242 30

-I28 Section 45 Stub Frames - BS 808 - 933 Frame Inner Chord at Stub Beam 131, 132

-I29A SATCOM Antenna InstallationBS 977 to BS 1043, S-1.5L to S-1.5R


243, 244

-I29B SATCOM Antenna Installation - External Skin DoublerBS 1004 to BS 1043, S-1.5L to S-1.5R


243, 244 30

-I02 BCF - Fuselage Stringer with Stringer Reinforcement Strap STA 1076 to 1143 S-10R to S-13R and S-9L to S-13L

153, 154 3



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IONS

5 300BCFPASS<2>


40,000 Cycles (300BCF, 400E)

5 200SF<4>

Type 250,000 Cycles


55

PASS Type 250,000 Cycles (200, 300 PASS)

40,000 Cycles (400E)5 200SF Type 2

40,000 Cycles


55

300BCFPASS<2>

Type 250,000 Cycles

(200, 300BCF, 300 PASS)40,000 Cycles (400E)

5 200SF<4>

Type 240,000 Cycles

5 200SF<4>

Type 240,000 Cycles

55

200SFPASS<2>

Type 250,000 Cycles

(200, 200SF, 300 PASS)40,000 Cycles (400E)

5 300BCF<4>

Type 250,000 Cycles

SAIRPLANE/


JU
D622T001-9-01


3-60-I06B Aft Main Cargo Door Cutout - Edge Frames - Inner Chord at BS 1270 and BS 1346 154

3-60-I06B Aft Main Cargo Door Cutout - Edge Frames - Inner Chord at BS 1270 and BS 1346 154

3-60-I06C BCF Aft Main Cargo Door Cutout - Edge Frame - Outer Chord BS 1270 and BS 1346 between Upper and Lower Sills

154

3-60-I06C3-30-I14C

Forward/Aft Main Cargo Door Cutout - Edge Frame - Outer Chord BS 539.5, BS 615, BS 1270, and BS 1346 between Upper and Lower Sills

122, 154

3-30-I14C Forward Main Cargo Door Cutout - Edge Frame - Outer Chord BS 539.5 and BS 615 between Upper and Lower Sills

122

3-60-I06C Aft Main Cargo Door Cutout - Edge Frame - Outer ChordBS 1270 and BS 1346 between Upper and Lower Sills

154

3-60-I06D3-30-I14D

Forward/Aft Main Cargo Door Cutout - Upper Main Sill - Inner Chord BS 522 to BS 544 and BS 1346 to BS 1395

122, 154

3-30-I14D Forward Main Cargo Door Cutout - Upper Main Sill - Inner ChordBS 522 to BS 544

122

3-60-I06D Aft Main Cargo Door Cutout - Upper Main Sill - Inner ChordBS 1346 to BS 1395

154

3-60-I06E3-30-I14E

Forward/Aft Main Cargo Door Cutout - Lower Main Sill - Inner ChordBS 610 to BS 632 and BS 1263 to BS 1270

122, 154

3-60-I06E BCF1 - Aft Main Cargo Door Cutout - Lower Main Sill - Inner ChordBS 1263 to STA 1270

154



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53-60 200SF Type 250,000 Cycles


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)53-60 ALL Type 2

50,000 Cycles (200, 200SF, 300BCF,

300 PASS)40,000 Cycles (300F, 400E)

53-60 300F Type 240,000 Cycles

53-60 200SF00BCFPASS

Type 250,000 Cycles

(200, 200SF, 300 PASS)40,000 Cycles (300BCF, 400E)

53-60 200SF00BCFPASS<2>

Type 250,000 Cycles

(200, 200SF, 300 PASS)40,000 Cycles (300BCF, 400E)

53-60 0 PASS<2>

Type 250,000 Cycles

53-60 400E<2>

Type 240,000 Cycles

53-60 0 PASS400E

Type 250,000 Cycles (300 PASS)

40,000 Cycles (400E)

SS


JUN 20




-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

-I14E Aft Passenger Entry/Service Door Cutout - Edge Frames - Inner Chord 251, 2523

-I14F Aft Passenger Entry/Service Door Cutout - Upper Main Sill - Inner ChordDoor Sta. 911 to BS 1562

251, 2523

-I27A Type I Emergency Exit Door Cutout - Edge Frame - Inner Chord - BS 1153 and BS 1183.4, S-8 to S-13 & S-16 to S-23

153, 154, 251, 252

30

-I27A Type I Emergency Exit Door Cutout - Edge Frame - Inner Chord - BS 1153 and BS 1183.4, S-8 to S-13 & S-16 to S-23

153, 154, 251, 252

-I27B Type I Emergency Exit Door Cutout - Upper Main Sill - Inner Chord, BS 1131 to BS 1197+22

251, 252 30



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IONS

5 300 PASS400E

Type 250,000 Cycles (300 PASS)

40,000 Cycles (400E)5 300F

<3>Type 2

40,000 Cycles

5 300F<3>

Type 240,000 Cycles

5 300F<3>

Type 240,000 Cycles

5 300F<3>

Type 240,000 Cycles

5 300F<3>

Type 240,000 Cycles

5 ALLL/N 424 & on

Type 250,000 Cycles


5 ALLL/N 424 & on

Type 250,000 Cycles


5 ALLL/N 424 & on

Type 250,000 Cycles


5 ALLL/N 424 & on

Type 250,000 Cycles


SAIRPLANE/


JU
D622T001-9-01


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



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53-80 ALL 424 & on

Type 250,000 Cycles


53-80 200SF Type 150,000 Cycles

53-80 BCF, 300FPASS

Type 150,000 Cycles


53-80 200SF Type 138,600 Cycles

53-80 BCF, 300FPASS

Type 150,000 Cycles


53-8053-8053-80

ALL 710 & on

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>


40,000 Cycles (300F)

SS


JUL 20




-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.

311, 312L/N

-I03 Section 48 - Jackscrew Fitting Lug - Upper Bulkhead at BS 1702 311, 312

-I03 Section 48 - Jackscrew Fitting Lug - Upper Bulkhead at BS 1702 311, 312 300

-I13 Section 48 - Pivot Fitting Lug 313, 314

-I13 Section 48 - Pivot Fitting Lug 313, 314 300

-I15-I16-I17

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.

313, 314

-I01 Typical Mid Spar Chord Construction - JT9D StrutNsta 164.0 - 172.0 - 182.0

432, 434, 436,442, 444, 446

-I01 Typical Mid Spar Chord Construction - PW4000 StrutNsta 172.0 - 182.0

432, 434, 436,442, 444, 446

-I01 Typical Mid Spar Chord Construction - CF6-80A StrutNSTA 221.0 - 237.5

432, 434, 436,442, 444, 446

-I01 Typical Mid Spar Chord Construction - CF6-80C StrutNSTA 221.0 - 237.5

432, 434, 436,442, 444, 446

80C (E



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IONS

5 80C (400E)< 8 Hours

Type 240,000 Cycles/90,000 Flt. Hrs.

5 80C (400E)≥ 8 Hours


5 80C (400E)< 8 Hours


5 80C (400E)≥ 8 Hours


5 80C (400E)< 8 Hours


5 80C (400E)≥ 8 Hours


5 80C (400E) Type 240,000 Cycles/90,000 Flt. Hrs.

5 80C (400E)< 8 Hours


5 80C (400E)≥ 8 Hours


55

524 Type 250,000 Cycles


5 524<2>

Type 250,000 Cycles

5 7R4 Type 250,000 Cycles

5 4000 Type 225,000 Cycles

5 80A Type 250,000 Cycles

SAIRPLANE/


JU
D622T001-9-01


4-50-I01a Forward Mid Spar Chord - CF6-80C StrutFrame 1 to Frame 2 - NSTA 225.25 to 237.5

432, 442

4-50-I01a Forward Mid Spar Chord - CF6-80C StrutFrame 1 to Frame 2 - NSTA 225.25 to 237.5

432, 442

4-50-I01c Forward Mid Spar - CF6-80C StrutVisible Portions of Bay 1 (NSTA 206 to 220.73) & Bay 3 (NSTA 228.3 to 250.16)

432, 442

4-50-I01c Forward Mid Spar - CF6-80C StrutVisible Portions of Bay 1 (NSTA 206 to 220.73) & Bay 3 (NSTA 228.3 to 250.16)

432, 442

4-50-I01d Forward Mid Spar Chord - CF6-80C StrutFrame 1 to Frame 2 - NSTA 225.25 to 237.5

432, 442

4-50-I01d Forward Mid Spar Chord - CF6-80C Strut Frame 1 to Frame 2 - NSTA 225.25 to 237.5

432, 442

4-50-I01e Forward Mid Spar - CF6-80C Strut Visible Portions Bay 1: NSTA 206 to 220.73 and Bay 3: NSTA 228.23 to 250.16

432, 442

4-50-I01f Forward Mid Spar – CF6-80C StrutBay 1, Horizontal Chord, Exterior Edge

432, 442

4-50-I01f Forward Mid Spar – CF6-80C StrutBay 1, Horizontal Chord, Exterior Edge

432, 442

4-50-I024-50-I03a

Lower Spar Chords, Webs, and Thrust Plate, Side Skins, Stiffeners and Back-up ChordsApprox. NSTA 171 - RB211 Strut

433, 443

4-50-I03b Lower Spar Chords, Webs, and Thrust PlateNSTA 140 - RB211 Strut

431, 433,441, 443

4-50-I04 Forward Engine Mount Bulkhead - RB211 StrutNSTA 96.201, NBL 2.55

433, 443

4-50-I04 Typical Mid Spar Chord Construction - JT9D Strut 432, 434, 436,442, 444, 446

4-50-I04 Typical Mid Spar Chord Construction - PW4000 Strut 432, 434, 436,442, 444, 446

4-50-I04 Typical Mid Spar Chord Construction - CF6-80A Strut 432, 434, 436,442, 444, 446



ZONE A

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54-50 xcept 400E) Type 250,000 Cycles (200, 300 PASS)

40,000 Cycles (300F)54-50 C (400E)

8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.54-50 C (400E)

8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.54-50 C (400E)

8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.54-50 C (400E)

8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.54-50 C (400E)

8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.54-50 C (400E)

8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.54-50 C (400E)

8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.54-50 C (400E)

8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.54-50 7R4 Type 2

50,000 Cycles54-50 4000 Type 2

50,000 Cycles54-50 80A Type 2

50,000 Cycles54-50 xcept 400E) Type 2

50,000 Cycles (200, 300 PASS)40,000 Cycles (300F)

54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


SS


JUN 20




-I04 Typical Mid Spar Chord Construction - CF6-80C Strut 432, 434, 436,442, 444, 446

80C (E

-I04a Mid Spar Fitting to Chord Splice - CF6-80C StrutForward most fastener row common to Mid Spar Fitting

434, 436,444, 446

80<

-I04a Mid Spar Fitting to Chord Splice - CF6-80C StrutForward most fastener row common to Mid Spar Fitting

434, 436,444, 446

80≥

-I04c Mid Spar Chord - CF6-80C StrutMid Spar Chord to Mid Bulkhead, Frame 3 and Frame 4

434, 436,444, 446

80<

-I04c Mid Spar Chord - CF6-80C StrutMid Spar Chord to Mid Bulkhead, Frame 3 and Frame 4

434, 436,444, 446

80≥

-I04e Mid Spar Chord - CF6-80C StrutAll visible portions between midbulkhead and aft mid spar fittings

434, 436,444, 446

80<

-I04e Mid Spar Chord - CF6-80C StrutAll visible portions between midbulkhead and aft mid spar fittings

434, 436,444, 446

80≥

-I04f Mid Spar Chord – CF6-80C StrutAll visible portions between midbulkhead and aft mid spar fittings

434, 436,444, 446

80<

-I04f Mid Spar Chord – CF6-80C StrutAll visible portions between midbulkhead and aft mid spar fittings

434, 436,444, 446

80≥

-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead - JT9D StrutNSTA 147.14, NWL 127.0

432, 442

-I05 Forward Engine Mount Bulkhead Fitting and BulkheadNSTA 127.14, NWL 127. 0 - PW4000 Strut

432, 442

-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead - CF6-80A StrutNSTA 204.5, NWL 119.75

432, 442

-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead - CF6-80C StrutNSTA 206.5, NWL 120.88

432, 442 80C (E

-I05a Forward Engine Mount Fitting Thrust Tang - CF6-80C StrutFwd Engine Mount

432, 442 80<

-I05a Forward Engine Mount Fitting Thrust Tang - CF6-80C StrutFwd Engine Mount

432, 442 80≥



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details Page 1.0-60

IONS


5 4000 Type 250,000 Cycles


5 0C (Except 400E) Type 250,000 Cycles (200, 300 PASS)

40,000 Cycles (300F)5 80C (400E)

< 8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.5 80C (400E)

≥ 8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.5 80C (400E)

< 8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.5 80C (400E)

≥ 8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.5 80C (400E)

< 8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.5 80C (400E)

≥ 8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.5 7R4 Type 2

50,000 Cycles5 4000 Type 2

50,000 Cycles5 80A Type 2

50,000 Cycles5 0C (Except 400E) Type 2



SAIRPLANE/


JU
D622T001-9-01


4-50-I06 Aft Engine Mount Bulkhead - JT9D StrutNSTA 222.3, NWL 135.785

434, 436,444, 446

4-50-I06 Aft Engine Mount Bulkhead - PW4000 StrutNSTA 222.3, NWL 135.785

434, 436,444, 446

4-50-I06 Aft Engine Mount Bulkhead - CF6-80A StrutNSTA 298.93, NWL 134.58

436, 437,446, 447

4-50-I06 Aft Engine Mount Bulkhead - CF6-80C StrutNSTA 298.93, NWL 134.58

436, 437,446, 447

8

4-50-I06a Aft Engine Mount Bulkhead - CF6-80C StrutBarrel Nut Bore

436, 437,446, 447

4-50-I06a Aft Engine Mount Bulkhead - CF6-80C StrutBarrel Nut Bore

436, 437,446, 447

4-50-I06c Aft Engine Mount Bulkhead, Vertical Splice Strap - CF6-80C StrutVertical Splice Strap at Aft Eng Mount Blkhd and Mid Spar Ftg Vertical Tang

436, 437,446, 447

4-50-I06c Aft Engine Mount Bulkhead, Vertical Splice Strap - CF6-80C StrutVertical Splice Strap at Aft Eng Mount Blkhd and Mid Spar Ftg Vertical Tang

436, 437,446, 447

4-50-I06d Aft Engine Mount Bulkhead - CF6-80C StrutAft Flange

436, 437,446, 447

4-50-I06d Aft Engine Mount Bulkhead - CF6-80C StrutAft Flange

436, 437,446, 447

4-50-I08 Diagonal Brace and Lower Spar Attachment Fitting - JT9D Strut 437, 447

4-50-I08 Diagonal Brace and Lower Spar Attachment Fitting - PW4000 Strut 437, 447

4-50-I08 Diagonal Brace and Lower Spar Attachment Fitting - CF6-80A Strut 437, 447

4-50-I08 Diagonal Brace and Lower Spar Attachment Fitting - CF6-80C Strut 437, 447 8

4-50-I09 Mid Spar Fitting - JT9D Strut 437, 447



ZONE A

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54-50 4000 Type 250,000 Cycles

54-50 80A Type 250,000 Cycles

54-50 xcept 400E) Type 250,000 Cycles (200, 300 PASS)

40,000 Cycles (300F)54-50 524 Type 2

50,000 Cycles54-5054-5054-5054-50

C (400E) 8 Hours


54-5054-5054-5054-50

C (400E) 8 Hours


54-50 524 Type 250,000 Cycles

54-50 C (400E) 8 Hours

Type 1/16,000 Cycles/70,000 Flt. Hrs.

54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


54-50 524 Type 250,000 Cycles

54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


SS


JUL 20




-I09 Mid Spar Fitting - PW4000 Strut 437, 447

-I09 Mid Spar Fitting - CF6-80A Strut 437, 447

-I09 Mid Spar Fitting - CF6-80C Strut 437, 447 80C (E

-I09 Diagonal Brace and Strut Attach Fitting and Fuse Pins - RB211 Strut 434, 444

-I09a-I07-I08-I12

Strut to Wing Attachments - CF6-80C StrutStrut to Wing Fittings

431, 433, 437,441, 443, 447,511, 521, 611,

621

80<

-I09a-I07-I08-I12

Strut to Wing Attachments - CF6-80C StrutStrut to Wing Fittings

431, 433, 437,441, 443, 447,511, 521, 611,

621

80≥

-I10 Aft Upper Spar Fittings and Fuse Pins - RB211 Strut 434, 444

-I10a Forward Engine Mount - CF6-80C StrutPlatform at Forward Tension Bolt Holes

410, 420 80<

-I10a Forward Engine Mount - CF6-80C StrutPlatform at Forward Tension Bolt Holes

410, 420 80≥

-I10b Forward Engine Mount - CF6-80C StrutPlatform Forward Through Hole

410, 420 80<

-I10b Forward Engine Mount - CF6-80C StrutPlatform Forward Through Hole

410, 420 80≥

-I11 Side Link and Strut Attach Fittings - RB211 Strut 434, 444

-I11d Aft Engine Mount - CF6-80C StrutLugs

410, 420 80<

-I11d Aft Engine Mount - CF6-80C StrutLugs

410, 420 80≥



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18

details Page 1.0-62

IONS

5 80C (400E)< 8 Hours


5 80C (400E)≥ 8 Hours



5 4000 Type 250,000 Cycles


5 0C (Except 400E) Type 250,000 Cycles (200, 300 PASS)

40,000 Cycles (300F)5 80C (400E)

< 8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.5 80C (400E)

≥ 8 HoursType 2

40,000 Cycles/90,000 Flt. Hrs.5 7R4 Type 2

50,000 Cycles5 80A Type 2

50,000 Cycles5 4000 Type 2

50,000 Cycles5 0C (Except 400E) Type 2


5 80C (400E)< 8 Hours


5 80C (400E)≥ 8 Hours


5 80C (400E)< 8 Hours


SAIRPLANE/


JU
D622T001-9-01


4-50-I11f Aft Engine Mount - CF6-80C StrutEngine Turbine Rear Frame (TRF) Clevis Lugs

410, 420

4-50-I11f Aft Engine Mount - CF6-80C StrutEngine Turbine Rear Frame (TRF) Clevis Lugs

410, 420

4-50-I12 Side Load Links - JT9D Strut 437, 447

4-50-I12 Side Load Links - PW4000 Strut 437, 447

4-50-I12 Side Load Links - CF6-80A Strut 437, 447

4-50-I12 Side Load Links - CF6-80C Strut 437, 447 8

4-50-I12b Side Load Fittings - CF6-80C StrutSide Load Fitting. Includes Mid Spar Fitting, Aft Strut Bulkhead and Splice Straps

437, 447

4-50-I12b Side Load Fittings - CF6-80C StrutSide Load Fitting. Includes Mid Spar Fitting, Aft Strut Bulkhead and Splice Straps

437, 447

4-50-I13 Typical Lower Spar Chord and Spar Web Construction - JT90 StrutAll

434, 436444, 446

4-50-I13 Typical Lower Spar Chord and Spar Web Construction - CF6-80A StrutAll

434, 436444, 446

4-50-I13 Typical Lower Spar Chord and Spar Web Construction - PW4000 StrutAll

434, 436444, 446

4-50-I13 Typical Lower Spar Chord and Spar Web Construction - CF6-80C StrutAll

434, 436444, 446

8

4-50-I13a Lower Spar Chord and Web - CF6-80C StrutAll locations on lower spar where chord is hidden.

434, 436444, 446

4-50-I13a Lower Spar Chord and Web - CF6-80C StrutAll locations on lower spar where chord is hidden.

434, 436444, 446

4-50-I13e Lower Spar Chord - CF6-80C StrutAll visible portions from mid bulkhead to aft engine mount bulkhead.

434, 436444, 446



ZONE A

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54-50 C (400E) 8 Hours

Type 240,000 Cycles/90,000 Flt. Hrs

54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


54-50 0C (00E) 8 Hours


54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


54-50 C (400E) Type 240,000 Cycles/90,000 Flt. Hrs.

54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


54-50 C (400E) 8 Hours


SS


JUN 20




-I13e Lower Spar Chord - CF6-80C StrutAll visible portions from mid bulkhead to aft engine mount bulkhead.

434, 436444, 446

80≥

-I13f Lower Spar Chord and Web - CF6-80C StrutAll locations on lower spar where chord is hidden.

434, 436444, 446

80<

-I13f Lower Spar Chord and Web - CF6-80C StrutAll locations on lower spar where chord is hidden.

434, 436444, 446

80≥

-I13g Lower Spar Chord and Web – CF6-80C StrutHorizontal Flange Fwd end of Chord.

434, 436444, 446

80<

-I13g Lower Spar Chord and Web – CF6-80C StrutHorizontal Flange Fwd end of Chord.

434, 436444, 446

80≥

-I14 Mid Bulkhead - Upper Link Fitting (R1) Joint - CF6-80C StrutMid Bulkhead

432, 434, 436,442, 444, 446

80<

-I14 Mid Bulkhead - Upper Link Fitting (R1) Joint - CF6-80C StrutMid Bulkhead

432, 434, 436,442, 444, 446

80≥

-I16a Forward Upper Spar - CF6-80C StrutHidden Portions of Forward Upper Spar Chord

432, 442 80<

-I16a Forward Upper Spar - CF6-80C StrutHidden Portions of Forward Upper Spar Chord

432, 442 8≥

-I16e Forward Upper Spar - CF6-80C StrutVisible Portions of Forward Upper Spar Chord

432, 442 80<

-I16e Forward Upper Spar - CF6-80C StrutVisible Portions of Forward Upper Spar Chord

432, 442 80≥

-I16f Forward Upper Spar - CF6-80C StrutHidden Portions of Forward Upper Spar Chord

432, 442 80

-I17a Aft Upper Spar Chord - CF6-80C StrutHorizontal and Vertical Flange at the Midbulkhead and Frame 3, 4, and 5

434, 436444, 446

80<

-I17a Aft Upper Spar Chord - CF6-80C StrutHorizontal and Vertical Flange at the Midbulkhead and Frame 3, 4, and 5

434, 436444, 446

80≥

-I17c Aft Upper Spar Chord - CF6-80C StrutAft Upper Spar Chord at NSTA 279 (R.H. Side Only)

434, 436444, 446

80<

-I17c Aft Upper Spar Chord - CF6-80C StrutAft Upper Spar Chord at NSTA 279 (R.H. Side Only)

434, 436444, 446

80≥



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details Page 1.0-64

IONS

5 80C (400E)< 8 Hours


5 80C (400E)≥ 8 Hours


5 80C (400E)< 8 Hours


5 80C (400E)≥ 8 Hours


5 80C (400E)< 8 Hours


5 80C (400E)≥ 8 Hours


5 80C (400E)< 8 Hours


5 80C (400E)≥ 8 Hours


5 80C (400E)< 8 Hours


5 80C (400E)≥ 8 Hours


5 LL Except 200SF Type 150,000 Cycles






SAIRPLANE/


JU
D622T001-9-01


4-50-I17e Aft Upper Spar Chord - CF6-80C StrutHorizontal and Vertical Flange from Frame 4 to Frame 5

434, 436444, 446

4-50-I17e Aft Upper Spar Chord - CF6-80C StrutHorizontal and Vertical Flange from Frame 4 to Frame 5

434, 436444, 446

4-50-I17f Aft Upper Spar Chord - CF6-80C StrutHorizontal and Vertical Flange from NSTA 251 to NSTA 275

434, 436444, 446

4-50-I17f Aft Upper Spar Chord - CF6-80C StrutHorizontal and Vertical Flange from NSTA 251 to NSTA 275

434, 436444, 446

4-50-I17g Aft Upper Spar Chord - CF6-80C StrutNSTA 285

434, 436444, 446

4-50-I17g Aft Upper Spar Chord - CF6-80C StrutNSTA 285

434, 436444, 446

4-50-I17h Aft Upper Spar Chord – CF6-80C StrutHorizontal and Vertical Flange at the Midbulkhead and Frame 3, 4, and 5

434, 436444, 446

4-50-I17h Aft Upper Spar Chord – CF6-80C StrutHorizontal and Vertical Flange at the Midbulkhead and Frame 3, 4, and 5

434, 436444, 446

4-50-I18 Side Skin/Aft Upper Spar Chord/Stiffener - CF6-80C StrutSTA 268, Aft - Upper Portion of the Side Skin Cutout

434, 436444, 446

4-50-I18 Side Skin/Aft Upper Spar Chord/Stiffener - CF6-80C StrutSTA 268, Aft - Upper Portion of the Side Skin Cutout

434, 436444, 446

5-10-I09 Horizontal Stabilizer Upper Skin - At BBL 41.5 Side of Body Splice 331, 341 A

5-10-I09A Horizontal Stabilizer Upper Skin - At BBL 41.5 Side of Body Splice 331, 341

5-10-I13A Horizontal Stabilizer Pivot Fitting Lug 331, 341 A

5-10-I13B Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments 331, 341 A



ZONE A

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55-10 xcept 200SF Type 125,000 Cycles

55-10 200SF Type 150,000 Cycles

55-10 200SF Type 125,000 Cycles





55-10 200SF Type 150,000 Cycles

55-10 200SF Type 150,000 Cycles



55-10 200SF Type 150,000 Cycles

55-10 200SF Type 150,000 Cycles

57-10 400E 8 Hours


SS


JUL 20




-I13C Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments 331, 341 ALL E

-I13D Horizontal Stabilizer Pivot Fitting Lug 331, 341

-I13E Horizontal Stabilizer Pivot Fitting - Upper and Lower Attachments 331, 341

-I14A Horizontal Stabilizer - Jackscrew Fitting Lug 331, 341 ALL E

-I14B Horizontal Stabilizer Jackscrew Fitting - Upper and Lower Attachments 331, 341 ALL E

-I14C Horizontal Stabilizer Jackscrew Fitting Lug 331, 341

-I14D Horizontal Stabilizer Jackscrew Fitting - Upper and Lower Attachments 331, 341

-I31 Horizontal Stabilizer Rear Spar Upper Chord and Skin - Side-of-Body Hidden Area 331, 341 ALL E

-I31A Horizontal Stabilizer Rear Spar Upper Chord - Side-of-Body Hidden Area 331, 341

-I31B Horizontal Stabilizer Upper Skin 334, 344

-I01 Skin at Typical Stringer - Wing Center Section, Lower Surface at External Lower Beams (BBL 9.5 and BBL 62.0)

133, 134<



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details Page 1.0-66

IONS

5 400E> 8 Hour


5 300BCF Type 150,000 Cycles/70,000 Flt. Hrs.

<5>5 200SF Type 1

50,000 Cycles/70,000 Flt. Hrs.

57 300F Type 125,000 Cycles / 80,000 Flt Hrs

57 300F Type 125,000 Cycles / 80,000 Flt Hrs

5 300F Type 140,000 Cycles

5 400E< 8 Hours


5 400E> 8 Hours


5 LL Except 200SF, 300BCF

< 8 Hours



> 8 Hours


5 400E< 8 Hours

Type 1, FLSSee Graph

5 400E> 8 Hours


SAIRPLANE/


JU
D622T001-9-01


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-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



ZONE A

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57-10 00BCF Type 150,000 Cycles/70,000 Flt. Hrs.

<5>57-10 200SF Type 1


57-10 PASS ER, 300ER) enter section

fuel 8 Hours


57-10 PASS ER, 300ER)enter section

fuel 8 Hours


57-10 300F Type 125,000 Cycles/80,000 Flt. Hrs.

57-10 400E 8 Hours


57-10 400E 8 Hours


57-10 200SF00BCF


<6>57-10 PASS

ER, 300ER)enter section

fuel 8 Hours


SS


JUL 20




-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

133, 134(200

with c

<



ZONE

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18

details Page 1.0-68

IONS

5 PASS (200ER, 300ER)ith center section

fuel> 8 Hours


5 300F Type 125,000 Cycles/80,000 Flt. Hrs.

5 200SF, 300BCF Type 125,000 Cycles/70,000 Flt. Hrs.

<6>5 PASS

(200ER, 300ER)ith center section

fuel< 8 Hours


5 PASS (200ER, 300ER)ith center section

fuel> 8 Hours


5 300F Type 1, FLSSee Graph

5 200SF, 300BCF Type 125,000 Cycles/70,000 Flt. Hrs.

<6>5 400E

< 8 HoursType 1


5 400E> 8 Hours


SAIRPLANE/


JU
D622T001-9-01


7-10-I03B Rear Spar Lower Chord - Wing Center Section - Hidden Locations - BBL 49.5, 62.05 and 73.0

133, 134

w

7-10-I03B Rear Spar Lower Chord - Wing Center Section - Hidden Locations - BBL 49.5, 62.05 and 73.0

133, 134

7-10-I03B Rear Spar Lower Chord and Skin - Wing Center Section - Hidden Locations -BBL 49.5, 62.05, and 73.0

133, 134

7-10-I03C Skin at Rear Spar Lower Chord - Wing Center Section - Hidden Locations - BBL 49.5, 62.05 and 73.0

133, 134

w

7-10-I03C Skin at Rear Spar Lower Chord - Wing Center Section - Hidden Locations -BBL 49.5, 62.05 and 73.0

133, 134

w

7-10-I03C Skin at Rear Spar Lower Chord - Wing Center Section - Hidden Locations -BL 49.5, 62.05 and 73.0

133, 134

7-10-I03C Skin at Rear Spar Lower Chord - Wing Center Section - Hidden Locations - BBL 49.5, 62.05 and 73.0

133, 134

7-10-I08 Rear Spar Lower Chord - Wing Center Section - Wing BBL 62.0 to inboard edge of terminal fitting and LBL 11.0 - RBL 11.0

133, 134

7-10-I08 Rear Spar Lower Chord - Wing Center Section - Wing BBL 62.0 to inboard edge of terminal fitting and LBL 11.0 - RBL 11.0

133, 134



ZONE A

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NS

ils Page 1.0-69

57-10 xcept 200SF, 00BCF

8 Hours



8 Hours


57-10 00BCF Type 1,25,000 Cycles/70,000 Flt. Hrs.

<6>57-10 200SF Type 1,



8 Hours



8 Hours


57-10 00BCF Type 150,000 Cycles/70,000 Flt. Hrs.

<5>57-10 200SF Type 1


57-10 , 300ER with enter section ks, and 300F

8 Hours


57-10 , 300ER with enter section ks, and 300F

8 Hours


SS


JUL 20




-I16B Lower Surface Side-Of-Body Splice (Sections 11 and 12) - Stringer 1 to Stringer 10, Inboard and Outboard of BBL 97.42

193, 194531, 631

ALL E3

<-I16B Lower Surface Side-Of-Body Splice (Sections 11 and 12) - Stringer 1 to Stringer 10,

Inboard and Outboard of BBL 97.42193, 194531, 631

ALL E3

>-I16C Wing Lower Surface Side-of-Body Splice (Sections 11 and 12) - Stringer 1 to Stringer

10 Inboard and Outboard of BBL 97.42193, 194531, 631

3

-I16D Wing Lower Surface Side-of-Body Splice (Sections 11 And 12) - Stringer 1 to Stringer 10 Inboard and Outboard of BBL 97.42

193, 194531, 631

-I20 Rear Spar Lower Chord Side-of-Body Splice (Sections 11 and 12) - Chords at Splice Fittings Inboard and Outboard of BBL 97.42

143, 144551, 651

ALL E3

<-I20 Rear Spar Lower Chord Side-of-Body Splice (Sections 11 and 12) - Chords at Splice

Fittings Inboard and Outboard of BBL 97.42143, 144551, 651

ALL E3

>-I20A Rear Spar Lower Chord Side-of-Body Splice (Sections 11 and 12) - Chords at Splice

Fittings Inboard and Outboard of BBL 97.42143, 144551, 651

3

-I20B Rear Spar Lower Chord Side-of-Body Splice (Sections 11 and 12) - Chords at Splice Fittings Inboard and Outboard of BBL 97.42

143, 144551, 651

-I24 Underwing Longeron Attachment (Center Section Structure) - BBL 70 Longeron from Front Spar Lower Chord to Stringer 18

193, 194 200ER4 bay cfuel tan

<-I24 Underwing Longeron Attachment (Center Section Structure) - BBL 70 Longeron from

Front Spar Lower Chord to Stringer 18193, 194 200ER

4 bay cfuel tan

>



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18

details Page 1.0-70

IONS

5 300BCF Type 150,000 Cycles/70,000 Flt. Hrs.

<5>5 200SF Type 1


5 400E< 8 Hours


5 400E> 8 Hours


5 400E< 8 Hours


5 400E> 8 Hours


5 400E< 8 Hours


5 400E> 8 Hours


5 400E< 8 Hours

<2>


5 400E> 8 Hours

<2>


SAIRPLANE/


JU
D622T001-9-01


7-10-I24A Underwing Longeron Attachment - Wing Center Section - Hidden Locations - BBL 70 Longeron from Front Spar Lower Chord to Stringer 18

193, 194

7-10-I24B Underwing Longeron Attachment - Wing Center Section - Hidden Locations - BBL 70 Longeron from Front Spar Lower Chord to Stringer 18

193, 194

7-10-I25 Rear Spar Lower Chord - Wing Center Section at Stiffener Clips at BBL 32.9, 40.2, 47.5, 54.7 and 62

133, 134

7-10-I25 Rear Spar Lower Chord - Wing Center Section at Stiffener Clips at BBL 32.9, 40.2, 47.5, 54.7 and 62

133, 134

7-20-I03A Rear Spar Lower Chord and Web - Outboard Wing Structure - Typical Details Between Rib 12 and Rib 19

532, 541,551, 561,632, 641,651, 661

7-20-I03A Rear Spar Lower Chord and Web - Outboard Wing Structure - Typical Details Between Rib 12 and Rib 19

532, 541,551, 561,632, 641,651, 661

7-20-I03B Rear Spar Lower Chord and Web - Outboard Wing Structure - Hidden Details at External Stiffeners and Fittings Between Rib 12 and Rib 19

532, 541,551, 561,632, 641,651, 661

7-20-I03B Rear Spar Lower Chord and Web - Outboard Wing Structure - Hidden Details at External Stiffeners and Fittings Between Rib 12 and Rib 19

532, 541,551, 561,632, 641,651, 661

7-20-I05 Rear Spar at Forward Main Landing Gear Trunnion - Rib 5, WS 329.10 532, 632551, 651

7-20-I05 Rear Spar at Forward Main Landing Gear Trunnion - Rib 5, WS 329.10 532, 632551, 651



ZONE A

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NS

ils Page 1.0-71

57-20 400E 8 Hours

<2>


57-20 400E 8 Hours

<2>


57-20 E, and All lane Types, 22 and later

<2>


(200, 300 PASS, 300F L/N 922 and Later, 400E)50,000 Cycles/ 70,000 Flt Hrs

(200SF, 300BCF L/N 922and later)

57-20 xcept 200SF, F, and 400E

8 Hours



8 Hours


57-20 400E 8 Hours


57-20 400E 8 Hours



8 Hours



8 Hours


57-20 400E 8 Hours


SS


JUL 20




-I06 Rear Spar at Main Landing Gear Outboard Support - Rib 7, WS 372.20 532, 632551, 651 <

-I06 Rear Spar at Main Landing Gear Outboard Support - Rib 7, WS 372.20 532, 632551, 651 >

-I07 Rear Spar at Flap/Spoiler Backup Fitting Installation - Rear Spar Web, Rib Bay 16,WS 605.50

551, 651 400Airp

L/N 9

-I12A Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 16 (Dry Bay) under Nacelle Fairing

533, 633 ALL E300BC

<-I12A Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 16 (Dry Bay) under

Nacelle Fairing533, 633 ALL E

300BC>


533, 633<


533, 633>

-I12B Outboard Wing Typical Stringers Lower Surface -- Rib 9: Stringer 17 at Outboard Side Load Fitting under Nacelle Fairing

533, 633 ALL E300BC

<-I12B Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 17 at Outboard Side

Load Fitting under Nacelle Fairing533, 633 ALL E

300BC>

-I12B Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 17 at Outboard Side Load Fitting under Nacelle Fairing

533, 633<



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details Page 1.0-72

IONS

5 400E> 8 Hours


5 200SF300BCF

Type 150,000 Cycles/70,000 Flt Hrs.

<5>


< 8 Hours



> 8 Hours



< 8 Hours



> 8 Hours


5 LL Except 200SF, 00BCF, and 400E

< 8 Hours



> 8 Hours


5 400E< 8 Hours


SAIRPLANE/


JU
D622T001-9-01


7-20-I12B Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 17 at Outboard Side Load Fitting under Nacelle Fairing

533, 633

7-20-I12C Outboard Wing Lower Surface Typical Stringer 193, 194437, 447530, 630540, 640533, 633

7-20-I15A Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10. Stringer 10: Between Rib 7 and 20 (Except Under Nacelle Strut Fairing) and Stringer 6: Side-of-Body to Rib 3

530, 630531, 631532, 632540, 640541, 641

A

7-20-I15A Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10. Stringer 10: Between Rib 7 and 20 (Except Under Nacelle Strut Fairing) and Stringer 6: Side-of-Body to Rib 3

530, 630531, 631532, 632540, 640541, 641

A

7-20-I15B Outboard Wing Lower Surface Splice Stringer - Stringer 10 under Nacelle Fairing 532, 541632, 641437, 447

A

7-20-I15B Outboard Wing Lower Surface Splice Stringer - Stringer 10 under Nacelle Fairing 532, 541632, 641437, 447

A

7-20-I15C Outboard Wing Lower Surface Splice Stringer - Stringer 6, 10 and 15 under Nacelle Strut at External Doublers, Fittings and Angles

532, 632533, 633541, 641

A3

7-20-I15C Outboard Wing Lower Surface Splice Stringer - Stringer 6, 10 and 15 under Nacelle Strut at External Doublers, Fittings and Angles

532, 632533, 633541, 641

A3

7-20-I15C Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10 under Nacelle Strut at External Fittings and Skate Angles

532, 541632, 641



ZONE A

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ils Page 1.0-73

57-20 400E 8 Hours



8 Hours



8 Hours


57-20 400E 8 Hours


57-20 400E 8 Hours


57-20 cept 200SF, F, and 400E

8 Hours


57-20 cept 200SF, F, and 400E

8 Hours


57-20 400E 8 Hours


57-20 400E 8 Hours


57-20 400E 8 Hours


57-20 400E 8 Hours


57-20 400E 8 Hours


SS


JUL 20




-I15C Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10 under Nacelle Strut at External Fittings and Skate Angles

532, 541632, 641 >

-I15D Outboard Wing Lower Surface Splice Stringer - Stringer 15 under Nacelle Strut at Rib 9 (Seal Pans)

437, 447530, 630

ALL E300BC

<-I15D Outboard Wing Lower Surface Splice Stringer - Stringer 15 under Nacelle Strut at Rib 9

(Seal Pans)437, 447530, 630

ALL E300BC

>-I15D Outboard Wing Lower Surface Splice Stringer - Stringer 15 under Nacelle Strut at Rib 9

(Seal Pans)437, 447530, 630 <

-I15D Outboard Wing Lower Surface Splice Stringer - Stringer 15 under Nacelle Strut at Rib 9 (Seal Pans)

437, 447530, 630 >

-I15E Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10 at Rib 3 530, 630 All Ex300BC

<-I15E Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10 at Rib 3 530, 630 All Ex

300BC>

-I15F Outboard Wing Lower Surface Splice Stringer - Seal Pan/Baffles at Ribs 3, 5, 18 and 31

530, 540630, 640 <

-I15F Outboard Wing Lower Surface Splice Stringer - Seal Pan/Baffles at Ribs 3, 5, 18 and 31

530, 540630, 640 >

-I15G Outboard Wing Lower Surface Splice Stringer - Stringer 6 at External Nacelle Fitting and Outboard Skate Angle

532, 541632, 641 <

-I15G Outboard Wing Lower Surface Splice Stringer - Stringer 6 at External Nacelle Fitting and Outboard Skate Angle

532, 541632, 641 >

-I15H Outboard Wing Lower Surface Splice Stringer - Stringer 15 at External Nacelle Fitting and Outboard Skate Angle

532, 541632, 641 <



ZONE

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details Page 1.0-74

IONS

5 400E> 8 Hours


5 200SF300BCF


<6>

5 200SF300BCF


<6>


< 8 Hours



> 8 Hours



< 8 Hours



> 8 Hours


5 400E< 8 Hours


5 400E> 8 Hours



< 8 Hours


SAIRPLANE/


JU
D622T001-9-01


7-20-I15H Outboard Wing Lower Surface Splice Stringer - Stringer 15 at External Nacelle Fitting and Outboard Skate Angle

532, 541632, 641

7-20-I15J Outboard Wing Lower Surface Splice Stringers 437, 447530, 630531, 631532, 632533, 633540, 640541, 641

7-20-I15K Outboard Wing Lower Surface Splice Stringers 437, 447531, 631532, 632541, 641

7-20-I16A Rear Spar Lower Chord (Outboard Wing Structure) - Typical Details between Fairing at Side-Of-Body & Rib 3

531, 631 A

7-20-I16A Rear Spar Lower Chord (Outboard Wing Structure) - Typical Details between Fairing at Side-Of-Body & Rib 3

531, 631 A

7-20-I16B Rear Spar Lower Chord (Outboard Wing Structure) - Details Hidden by Rib Shear Ties Side-Of-Body to Rib 3

531, 631532, 632

A3


531, 631532, 632

A3


531, 631532, 632


531, 631532, 632

7-20-I16C Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details at Ribs 5, 6, 8 and 9 (Not Covered by Fairings)

532, 632 A3



ZONE A

L 2018

NS

ils Page 1.0-75


8 Hours


57-20 400E 8 Hours


57-20 400E 8 Hours



8 Hours



8 Hours


57-20 400E 8 Hours


57-20 400E 8 Hours



8 Hours



8 Hours


57-20 400E 8 Hours


57-20 400E 8 Hours



8 Hours


SS


JUL 20




-I16C Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details at Ribs 5, 6, 8 and 9 (Not Covered by Fairings)

532, 632 ALL E300BC

>-I16C Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details at Ribs 5, 6, 8 and

9 (Not Covered by Fairings)532, 632

<

-I16C Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details at Ribs 5, 6, 8 and 9 (Not Covered by Fairings)

532, 632>

-I16D Rear Spar Lower Chord (Outboard Wing Structure) - Details Outboard of Terminal Fitting Wing-to-Body Fairing Area

531, 631 ALL E300BC

<-I16D Rear Spar Lower Chord (Outboard Wing Structure) - Details Outboard of Terminal

Fitting Wing-to-Body Fairing Area531, 631 ALL E

300BC>


531, 631<


531, 631>

-I16E Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details - Trunnion, Nacelle and Inboard Flap Fairing Areas

530, 540630, 640

ALL E300BC

<-I16E Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details - Trunnion, Nacelle

and Inboard Flap Fairing Areas530, 540630, 640

ALL E300BC

>-I16E Rear Spar Lower Chord, Rib Bay 11, WSTA 449.2 - Hidden Details 530, 540

630, 640 <

-I16E Rear Spar Lower Chord, Rib Bay 11, WSTA 449.2 - Hidden Details 530, 540630, 640 >

-I16F Skin at Front Spar Lower Chord (Outboard Wing Structure) - Lower Skin Panel Splice Location between Ribs 18 and 19 only

540,640 ALL E300BC

<



ZONE

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18

details Page 1.0-76

IONS


> 8 Hours


5 400E< 8 Hours

<2>


5 400E> 8 Hours

<2>



< 8 Hours



> 8 Hours


5 400E< 8 Hours


5 400E> 8 Hours



< 8 Hours



> 8 Hours


5 400E< 8 Hours


5 400E> 8 Hours


SAIRPLANE/


JU
D622T001-9-01


7-20-I16F Skin at Front Spar Lower Chord (Outboard Wing Structure) - Lower Skin Panel Splice Location between Ribs 18 and 19 only

540, 640 A3

7-20-I16F Skin at Front Spar Lower Chord Outboard Wing Structure) - Lower Skin Panel Splice Location between Ribs 18 and 19 only

540, 640

7-20-I16F Skin at Front Spar Lower Chord (Outboard Wing Structure) - Lower Skin Panel Splice Location between Ribs 18 and 19 only

540, 640

7-20-I16G Front Spar Lower Chord and Skin (Outboard Wing Structure) - Details Hidden by Rib Shear Ties Rib 9 to and including Rib 23

530, 540630, 640

A3

7-20-I16G Front Spar Lower Chord and Skin (Outboard Wing Structure) - Details Hidden by Rib Shear Ties Rib 9 to and including Rib 23

530, 540630, 640

A3

7-20-I16G Front Spar Lower Chord (Outboard Wing Structure) - Details Hidden by Rib Shear Ties Rib 9 to and including Rib 23

540, 640

7-20-I16G Front Spar Lower Chord (Outboard Wing Structure) - Details Hidden by Rib Shear Ties Rib 9 to and including Rib 23

540, 640

7-20-I16H Front Spar Lower Chord (Outboard Wing Structure) - Hidden Details - Ribs 8/9 and at Side Brace Fitting between Ribs 8/9

533, 633 A3


533, 633 A3


533, 633

7-20-I16H Skin at Front Spar Lower Chord (Outboard Wing Structure) - Hidden Details - Ribs 8/9 and at Side Brace Fitting between Ribs 8/9

533, 633



ZONE A

N 2019

NS

ils Page 1.0-77

57-20 400E 8 Hours

<2>


57-20 400E 8 Hours

<2>


57-20 400E 8 Hours

<2>


57-20 400E 8 Hours

<2>


57-20 200SF00BCF


<6>

57-20 200SF00BCF


<6>57-20 400E

8 HoursType 1, FLSSee Graph

57-20 400E 8 Hours


57-20 ALL See Service Bulletin 767-57A0117

57-20 400E Type 125,000 Cycles/80,000 Flt. Hrs.

SS


JUL 20




-I16I Front Spar Lower Chord and Skin - Hidden Details - Rib Shear Ties, Rib 24 to and including Rib 31

540, 640<

-I16I Front Spar Lower Chord and Skin - Hidden Details - Rib Shear Ties, Rib 24 to and including Rib 31

540, 640>

-I16J Rear Spar Lower Chord - Hidden Details - Rib Shear Ties, Rib 22 up to and including Rib 32

540, 640<

-I16J Rear Spar Lower Chord - Hidden Details - Rib Shear Ties, Rib 22 up to and including Rib 32

540, 640>

-I16K Outboard Wing Lower Surface Front and Rear Spar Chords and Skin 530, 630531, 631532, 632533, 633540, 640541, 641

3

-I16L Wing Rear Spar Lower Chord and Skin (Outboard Wing Structure) - Details Outboard of Terminal Fitting Wing-to- Body Fairing Area

531, 6313

-I19 Nacelle Fitting Area at the Lower Surface - Outboard Wing Lower Surface - WS 436.9, Aft Pitch Load Fitting Forward End at Stringer 5

532, 632<

-I19 Nacelle Fitting Area at the Lower Surface - Outboard Wing Lower Surface - WS 436.9, Aft Pitch Load Fitting Forward End at Stringer 5

532, 632>

-I27 Skin Tab at Front Spar Pitch Load Fitting 511, 611

-I36 Main Landing Gear Forward Trunnion Support to Lower Skin Attachment - Inboard Forward Trunnion Support, Most Inboard Aft Fastener

530, 630



ZONE

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APPL

18

details Page 1.0-78

IONS

5 200, 200SF300BCF, 300F

300 PASS/N 922 and Later

and 400E<2>

Type 250,000 Cycles

(200, 200SF, 300BCF, 300 PASS L/N 922 and Later)

40,000 Cycles (300F L/N 922 and Later, 400E)

57 200, 200SF300BCF, 300F

300 PASSL/Ns 1 - 921


(200, 200SF, 300BCF, 300 PASS L/Ns 1 - 921) 40,000 Cycles (300F

L/Ns 1 - 921)57 200, 200SF

300BCF, 300F300 PASS

L/Ns 1 - 921



L/Ns 1 - 921)57 200, 200SF


L/Ns 1 - 921

Type 225,000 Cycles

5 200, 200SF300BCF, 300F

300 PASS /Ns 922 and Later

and 400E

Type 125,000 Cycles

5 200, 200SF300BCF, 300F

300 PASSL/Ns 1 - 921

Type 125,000 Cycles

SAIRPLANE/


JU
D622T001-9-01


7-53-I02A Outboard Flap Supports No. 1/8 and No. 2/7 - Support Ribs (Rear Spar Fittings) in Bathtub Region, Lug 6 Region and Lower Aft Flange

572, 573672, 673

L

-53-I02A.1 Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fittings - Lugs at Joint 1 572, 573672, 673

-53-I02A.2 Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fittings - Lugs at Joint 6 572, 573672, 673

-53-I02A.3 Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fittings - Lower Aft Flange 572, 573672, 673

7-53-I02B Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fitting Tension Bolts - BACB30US12 Bolt - Thread Runout

572, 573672, 673

L

7-53-I02B Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fitting Tension Bolts 572, 573672, 673



ZONE A

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NS

ils Page 1.0-79

57-53 0, 200SFBCF, 300F0 PASS

22 and Laternd 400E

<2>

Type 250,000 Cycles



57-53 0, 200SFBCF, 300F0 PASSs 1 - 921

Type 225,000 Cycles

57-53-I 0, 200SFBCF, 300F0 PASSs 1 - 921

Type 250,000 Cycles

(200, 200SF, 300BCF, 300 PASS L/Ns 1 - 921)40,000 Cycles (300F

L/Ns 1 - 921)57-53-I 0, 200SF

BCF, 300F0 PASSs 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57-53 0, 200SF

BCF, 300F0 PASS

22 and Laternd 400E

Type 125,000 Cycles

57-53 0, 200SFBCF, 300F0 PASSs 1 - 710

Type 125,000 Cycles After

Accomplishing Terminating Action of SB 767-27A0155

SS


JUL 20




-I02C Outboard Flap Supports No. 1/8 and No. 2/7 - Doublers - 0.375” Diameter Fastener Holes

572, 573672, 673

20300

30L/N 9

a

-I02C Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fittings - Actuator Bore and Fastener Holes

572, 573672, 673

20300

30L/N

02D.1 Outboard Flap Supports No. 1/8 and No. 2/7 - 9-10 Beam - Joint 9 Lug 572, 573672, 673

20300

30L/N

02D.2 Outboard Flap Supports No. 1/8 and No. 2/7 - 9-10 Beam 572, 573672, 673

20300

30L/N

-I02E Outboard Flap Supports No. 1/8 and No. 2/7 - 9-10 Beam Swivel Fitting - Upper Surface

572, 573672, 673

20300

30L/N 9

a-I02F Outboard Flap Supports No. 1/8 and No. 2/7 - Flap Attachment Bolts 572, 573

672, 67320

30030

L/N



ZONE

AIRE

APPL

18

details Page 1.0-80

IONS

5 200, 200SF300BCF, 300F

300 PASSL/Ns 711 - 921

Type 125,000 Cycles

57 200, 200SF300BCF, 300F


and 400E<2>

Type 250,000 Cycles



57 200, 200SF300BCF, 300F

300 PASSL/Ns 1 - 921

Type 225,000 Cycles

57 200, 200SF300BCF, 300F


and 400E<2>

Type 250,000 Cycles



57 200, 200SF300BCF, 300F

300 PASSL/Ns 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57 200, 200SF


L/Ns 1 - 921

Type 225,000 Cycles

SAIRPLANE/


JU
D622T001-9-01


7-53-I02F Outboard Flap Supports No. 1/8 and No. 2/7 - Flap Attachment Bolts 572, 573672, 673

-53-I02G.1 Outboard Flap Supports No. 1/8 and No. 2/7 - 6-8-9 Beam (Main Drive Link), Flanges in Vicinity of Joint 8

572, 573672, 673

L

-53-I02G.1 Outboard Flap Supports No. 1/8 and No. 2/7 - 6-8-9 Beam - Typical Section 572, 573672, 673

-53-I02G.2 Outboard Flap Supports No. 1/8 and No. 2/7 - 6-8-9 Beam (Main Drive Link), Lug 8 Region

572, 573672, 673

L

-53-I02G.2 Outboard Flap Supports No. 1/8 and No. 2/7 - 6-8-9 Beam - Lugs 6, 8 and 9 572, 573672, 673

-53-I02G.3 Outboard Flap Supports No. 1/8 and No. 2/7 - 6-8-9 Beam - Fastener Holes 572, 573672, 673



ZONE A

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NS

ils Page 1.0-81


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)57-53- 0, 200SF

BCF, 300F0 PASSs 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57-53- 0, 200SF

BCF, 300F0 PASSs 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57-53- 0, 200SF

BCF, 300F0 PASSs 1 - 921

Type 225,000 Cycles

57-53- 0, 200SFBCF, 300F0 PASSs 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57-53- 0, 200SF

BCF, 300F0 PASSs 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)

SS


JUL 20




-I02I Outboard Flap Supports No. 1/8 and No. 2/7 - 4-5 Drive Arm - Spline Outer Surface 572, 573672, 673

I02J.1 Outboard Flap Support No. 1/8 - Link 3-10 - Lug 572, 573672, 673

20300

30L/N

I02J.2 Outboard Flap Support No. 2/7 - Link 3-10 - Lugs 572, 573672, 673

20300

30L/N

I02L.1 Outboard Flap Supports No. 1/8 and No. 2/7 - Beam 1-2-3 - Beam at Field Fasteners 572, 573672, 673

20300

30L/N

I02L.2 Outboard Flap Supports No. 1/8 and No. 2/7 - Beam 1-2-3 - Lug at Joint 1 572, 573672, 673

20300

30L/N

I02L.3 Outboard Flap Supports No. 1/8 and No. 2/7 - Beam 1-2-3 - Lugs at Joint 3 572, 573672, 673

20300

30L/N



ZONE

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APPL

18

details Page 1.0-82

IONS

57 200, 200SF300BCF, 300F


and 400E

Type 125,000 Cycles

57 200, 200SF300BCF, 300F


and 400E

Type 125,000 Cycles

57 200, 200SF300BCF, 300F

300 PASSL/Ns 1 - 921

Type 125,000 Cycles

57 200, 200SF300BCF, 300F

300 PASSL/Ns 1 - 921

Type 125,000 Cycles

57 200, 200SF300BCF, 300F

300 PASSL/Ns 1 - 921

Type 125,000 Cycles

57 200, 200SF300BCF, 300F

300 PASS /N 922 and Later

and 400E

Type 125,000 Cycles

57 200, 200SF300BCF, 300F


and 400E<2>

Type 250,000 Cycles



SAIRPLANE/


JU
D622T001-9-01


-53-I02M.1 Outboard Flap Supports No. 1/8 and No. 2/7 - Outer Pins at Supports No. 1/8: Joints 5, 6, 8 and 10 and Supports No. 2/7: Joints 5, 6 and 10

572, 573672, 673

L

-53-I02M.2 Outboard Flap Supports No. 2/7 - Outer Pin at Inboard Main Support: Joint 8 572, 672

L

-53-I02M.4 Outboard Flap Pins - Support No. 2/7 - Outer Pins at Joint 2 and Joint 8 572, 672

-53-I02M.5 Outboard Flap Pins - Support No. 1/8 and No. 2/7 - Joint #1 Fuse Pin - Pin Shank at Outboard Rib Support

572, 573672, 673

-53-I02M.6 Outboard Flap Pins - Support No. 1/8, Joints 2, 3, 5, 6, 8, 9, and 10 - Support No. 2/7, Joints 3, 5, 6, 9, and 10

572, 573672, 673

-53-I03E.1 Inboard Flap Box Support No. 3/6 - Backup Fittings - Forward Bathtub 555, 655

L

-53-I03E.2 Inboard Flap Box Support No. 3/6 - Backup Fittings - Aft Bathtub End Pads 555, 655

L



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57-53- 0, 200SFBCF, 300F0 PASS

22 and Laternd 400E

Type 125,000 Cycles

57-53- 0, 200SFBCF, 300F0 PASSs 1 - 849

Type 125,000 Cycles After

Accomplishing Terminating Action of SB 767-27A0176

57-53- 0, 200SFBCF, 300F0 PASS

s 850 - 921

Type 125,000 Cycles

57-53- ALL Type 125,000 Cycles



(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)57-53- ALL Type 1

25,000 Cycles

57-53 ALL Type 125,000 Cycles or

25,000 Cycles after SB 767-27A0176 was

accomplished57-53 ALL Type 1

25,000 Cycles

SS


JUN 20




I03F.1 Inboard Flap Box Support No. 3/6 - Flap Attachment Bolts, IFS 251.25 555, 655 20300

30L/N 9

aI03F.2 Inboard Flap Support No. 3/6 - Flap Attachment Bolts - Shank Location 555, 655 20

30030

L/NI03F.2 Inboard Flap Support No. 3/6 - Flap Attachment Bolts - Shank Location 555, 655 20

30030

L/NI03I.1 Inboard Flap Box at Support No. 4/5 - Inboard Closure Rib - Lower Chord, IFS 108.5 555, 655

I03I.2 Inboard Flap Supports #4, #5 - Splined Bushing at IFS 108.5, Internal Spline Base of Tooth/Rim

555, 655

I03J.1 Inboard Flap Supports #4, #5 - Collar Fitting Bathtubs, IFS 92, Bathtub End Pads 555, 655

I03J.2 Inboard Flap Supports #4, #5 - Collar Fitting, Spline Cross Section 555, 655

-I03K Inboard Flap Box at Supports #4, #5 - Collar Fitting Attachment Bolts, IFS 92 555, 655

-I03L Inboard Flap Box Supports #4, #5 - Torque Tube, IFS 92 to IFS 124.5 555, 655



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19

details Page 1.0-84

IONS

57 200, 200SF300BCF, 300F

300 PASS /N 922 and Later

and 400E

Type 250,000 Cycles



57 200, 200SF300BCF, 300F

300 PASSL/Ns 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57 200, 200SF


/N 922 and Laterand 400E

<2>

Type 250,000 Cycles



57 200, 200SF300BCF, 300F

300 PASSL/Ns 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57 200, 200SF



<2>

Type 250,000 Cycles



SAIRPLANE/


JU
D622T001-9-01


-53-I04A.1 Inboard Flap Support No. 3/6 - Actuator Support Rib Assembly - Section Forward of Joint 6 Lug - Lower Flange

571, 671

L

-53-I04A.1 Inboard Flap Support No. 3/6 - Actuator Support Rib - Section Forward of Joint 6 Lug 571, 671

-53-I04A.2 Inboard Flap Support No. 3/6 - Actuator Support Rib Assembly - Lug Details at Joints 0, 1 and 6

571, 671

L

-53-I04A.2 Inboard Flap Support No. 3/6 - Actuator Support Rib - Lugs at Joints 0, 1, 6 571, 671

-53-I04B.2 Inboard Flap Support No. 3/6 - Underwing Fitting - Field Fasteners 571, 671

L



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57-53-I 0, 200SFBCF, 300F0 PASSs 1 - 882

Type 250,000 Cycles


L/Ns 1 - 882)57-53-I 0, 200SF

BCF, 300F0 PASSs 1 - 882



L/Ns 1 - 882)57-53 0, 200SF

BCF, 300F0 PASSs 1 - 882


57-53 0, 200SFBCF, 300F0 PASS

83 and Laternd 400E

<2>

Type 250,000 Cycles



57-53-I 0, 200SFBCF, 300F0 PASSs 1 - 882

Type 250,000 Cycles


L/Ns 1 - 882)57-53-I 0, 200SF

BCF, 300F0 PASSs 1 - 882



L/Ns 1 - 882)

SS


JUL 20




04B.2 Wing Trailing Edge, Inboard Flap, Support No. 3/6 - Underwing Fitting - Field Fasteners 571, 671 20300

30L/N

04B.3 Wing Trailing Edge, Inboard Flap, Support No. 3/6 - Underwing Fitting - Lug at Fuse Pin location

571, 671 20300

30L/N

-I04C Wing Trailing Edge, Inboard Flap, Support No. 3/6 - Underwing Fitting to Forward Tension Link Fuse Pin

571, 671 20300

30 L/N

-I04D Inboard Flap Support No. 3/6 - Forward Tension Link - Section A-A - Typical Section at Field Fasteners and Aft Lugs

571, 671 20300

30L/N 8

a

04D.1 Wing Trailing Edge, Inboard Flap, Support No. 3/6 - Forward Tension Link - Typical Cross Section Through Fasteners

571, 671 20300

30L/N

04D.2 Wing Trailing Edge, Inboard Flap, Support No. 3/6 - Forward Tension Link - Forward Clevis and Aft Lug

571, 671 20300

30L/N



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18

details Page 1.0-86

IONS

5 200, 200SF300BCF, 300F


and 400E<2>

Type 250,000 Cycles



57 200, 200SF300BCF, 300F

300 PASSL/Ns 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57 200, 200SF


L/Ns 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57 200, 200SF


L/Ns 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57 200, 200SF


L/Ns 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)

SAIRPLANE/


JU
D622T001-9-01


7-53-I04E Inboard Flap Support No. 3/6 - 1-2-3 Beam - Lugs at Joints 1, 2, and 3 571, 671

L

-53-I04E.1 Inboard Flap Support No. 3/6 - Beam 1-2-3 - Lug at Joint 1 571, 671

-53-I04E.2 Inboard Trailing Edge Flap Support No. 3/6 - Beam 1-2-3 - Lugs at Joint 2 and Joint 3 571, 671

-53-I04E.3 Inboard Flap Support No. 3/6 - Beam 1-2-3 - Beam at Field Fasteners 571, 671

-53-I04F.1 Inboard Flap Support No. 3/6 - 3-10 Link - Lugs 571, 671



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57-53- 0, 200SFBCF, 300F0 PASS

22 and Laternd 400E

<2>

Type 250,000 Cycles



57-53- 0, 200SFBCF, 300F0 PASSs 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57-53- 0, 200SF

BCF, 300F0 PASS

22 and Laternd 400E

<2>

Type 250,000 Cycles



57-53 0, 200SFBCF, 300F0 PASS

22 and Laternd 400E

<2>

Type 250,000 Cycles



57-53 0, 200SFBCF, 300F0 PASSs 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)

SS


JUL 20




I04F.1 Inboard Flap Support No. 3/6 - 3-10 Link - Lugs 571, 671 20300

30L/N 9

a

I04F.2 Inboard Flap Support No. 3/6 - 3-10 Link - Between Lugs 571, 671 20300

30L/N

I04F.2 Inboard Flap Support No. 3/6 - 3-10 Link - Between Lugs 571, 671 20300

30L/N 9

a

-I04H Inboard Flap Support No. 3/6 - 6-7-8-9 Beam - Lug 9 Detail 571, 671 20300

30L/N 9

a

-I04H Inboard Flap Support No. 3/6 - 6-7-8-9 Beam - Lugs 6, 7, 8 and 9 571, 671 20300

30L/N



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18

details Page 1.0-88

IONS


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)5 200, 200SF



<2>

Type 250,000 Cycles



57 200, 200SF300BCF, 300F

300 PASSL/Ns 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57 200, 200SF


L/Ns 1 - 921

Type 225,000 Cycles

57 200, 200SF300BCF, 300F

300 PASS L/Ns 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)57 200, 200SF



Type 125,000 Cycles

SAIRPLANE/


JU
D622T001-9-01


7-53-I04I Inboard Flap Support No. 3/6 - 4-5 Drive Arm - Internal Spline, Outer Surface 571, 671

7-53-I04K Inboard Flap Support No. 3/6 - 9-10 Beam - Lug at Joint 9 571, 671

L

-53-I04K.1 Inboard Flap Support No. 3/6 - 9-10 Beam - Joint 9 Lug 571, 671

-53-I04K.2 Inboard Flap Support No. 3/6 - 9-10 Beam - Typical Section at Lower Field Fasteners and Lower Flange

571, 671

-53-I04K.3 Inboard Flap Support No. 3/6 - 9-10 Beam 571, 671

-53-I04N.1 Inboard Flap Support No. 3/6 - Flap Support Pins - Outer Pins at Joints 0, 1, 2, 3, 5, 6, 7, 8, 9 and 10

571, 671

L



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57-53-I 0, 200SFBCF, 300F0 PASS

22 and Laternd 400E

Type 125,000 Cycles

57-53-I 0, 200SFBCF, 300F0 PASSs 1 - 921

Type 125,000 Cycles

57-53-I 0, 200SFBCF, 300F0 PASSs 1 - 921

Type 125,000 Cycles


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)57-53-I 0, 200SF

BCF, 300F0 PASS

22 and Laternd 400E

<2>

Type 250,000 Cycles



57-53-I 0, 200SFBCF, 300F0 PASSs 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)

SS


JUL 20




04N.2 Inboard Flap Support No. 3/6 - Flap Support Pins - Outer Pins at Joints A and B 571, 671 20300

30L/N 9

a04N.3 Inboard Flap Support No. 3/6 - Flap Support Pins - Outer Pins at Joints 0, 2, 3, 5, 6, 7,

8, 9, 10, A, and B571, 671 20

30030

L/N04N.4 Inboard Flap Support No. 3/6 - Flap Support Pins - Outer Pin at Joint 1 571, 671 20

30030

L/N-I04P Inboard Flap Support No. 4/5 - 4-5 Drive Arm - Internal Spline Outer Surface 195, 196

04Q.1 Inboard Flap Support No. 4/5 - 5-7 Link - Lugs 195, 196 20300

30L/N 9

a

04Q.1 Inboard Flap Support No. 4/5 - 5-7 Link - Lugs 195, 196 20300

30 L/N



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18

details Page 1.0-90

IONS

57 200, 200SF300BCF, 300F


and 400E<2>

Type 250,000 Cycles



57 200, 200SF300BCF, 300F

300 PASS L/Ns 1 - 921

Type 250,000 Cycles


L/Ns 1 - 921)5 ALL Type 2

50,000 Cycles (200, 200SF, 300BCF, 300

PASS)40,000 Cycles (300F, 400E)


(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F, 400E)5 200, 200SF



<2>

Type 250,000 Cycles



5 400E Type 240,000 Cycles

SAIRPLANE/


JU
D622T001-9-01


-53-I04Q.2 Inboard Flap Support No. 4/5 - 5-7 Link - Cross Sections 3.16 inches from Lugs 195, 196

L

-53-I04Q.2 Inboard Flap Support No. 4/5 - 5-7 Link - Body of Link around Field fasteners 195, 196

7-53-I04S Inboard Flap Support No. 4/5 - 6-7 Drive Arm - at Field Fasteners Between Joints 6 and 7, and Joint 7 Lug

195, 196

7-53-I04T Inboard Flap Support No. 4/5 - 6-9 Drive Arm Flanges - Near the Bend in the Part 195, 196

7-53-I04V Inboard Flap Support No. 4/5 - Carrier Beam 9-11 - Aft Bathtub Bolt Hole and Forward Field Fasteners

195, 196

L

7-53-I04Y Inboard Flap Support No. 4/5 - Flap Support Fitting - Upper Flange Inboard Bolt Location

195, 196



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57-53 0, 200SFBCF, 300F0 PASS

Type 250,000 Cycles

(200, 200SF, 300BCF, 300 PASS)

40,000 Cycles (300F)57-53 ALL Type 1

25,000 Cycles

57-53- 0, 200SFBCF, 300F0 PASS

22 and Laternd 400E

Type 125,000 Cycles

57-53- 0, 200SFBCF, 300F0 PASSs 1 - 921

Type 125,000 Cycles

57-54 200SF00BCF<4>

Type 150,000 Cycles

57-54 200SF00BCF<4>

Type 150,000 Cycles

57-54 200SF00BCF<4>

Type 150,000 Cycles

57-54 200SF00BCF<4>

Type 150,000 Cycles

57-54 200SF00BCF<4>

Type 150,000 Cycles

SS


JUL 20




-I04Y Inboard Flap Support No. 4/5 - Side Strut Swivel Support Fitting - Satellite Holes at Lug 6

195, 196 20300

30

-I04Z Inboard Flap Support No. 4/5 - 6-6’ Outer Pin - Section at Spline #2 (Common to 6-7 Arm) Inner Diameter (Inner Bore)

195, 196

I04AA Inboard Flap Support No. 4/5- Flap Support Pins - Outer Pins at Joints 5, 7 and 9 195, 196 20300

30L/N 9

aI04AA Inboard Flap Support No. 4/5 - Flap Support Pins - Outer Pins at Joints 5, 7, 9, and RL 195, 196 20

30030

L/N-I02A Main Landing Gear Beam, Inboard Lug Bore 552, 652

3

-I02B Main Landing Gear Beam, Outboard Lug Bore. 552, 6523

-I02C Main Landing Gear Beam, Aft Trunnion Bore 552, 6523

-I02D Main Landing Gear Beam, Upper Flange, between the Inboard and Outboard Web Stiffeners adjacent to Aft Trunnion Bore

552, 6523

-I02E Main Landing Gear Beam, Upper Flange, except the flange adjacent to Aft Trunnion Bore covered by SSI 57-54-I02D

552, 6523



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18

details Page 1.0-92

IONS

5 200SF300BCF

<4>

Type 150,000 Cycles

5 200SF300BCF

<4>

Type 150,000 Cycles

5 200SF300BCF

<4>

Type 150,000 Cycles

5 200SF300BCF

<4>

Type 150,000 Cycles

5 200SF300BCF

<4>

Type 150,000 Cycles

5 400E Type 125,000 Cycles/80,000 Flt. Hrs.

5 400E Type 125,000 Cycles/80,000 Flt. Hrs.

<1>

<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/


JU
D622T001-9-01


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.



ZONE A

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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




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

767-400ER Main Landing Gear Support Structure

767-400ER Wing Main Landing Gear Beam Upper Stabilizer Brace Fuse Pin 113T1140-3

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


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




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



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




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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BLANK
D622T001-9-01
BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for detaiEXPORT CONTROLLED - EAR ECCN: 9E991



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




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


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

NS

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


BILITY ENG

JUL 20




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.


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


BILITY ENG

JU
D622T001-9-01


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.


3-416-92NOTE

INTERNAL - GENERAL VISUAL: Structure Forward of Nose Landing Gear Wheel WellForward access door outer frame, hinges, latch, and stops.


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.


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.


L 2018

NS

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


BILITY ENG

JUL 20




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.


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


BILITY ENG

JU
D622T001-9-01


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


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.


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


BILITY ENG

JUL 20




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.


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.


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


BILITY ENG

JU
D622T001-9-01


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.


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.



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


BILITY ENG

JUL 20




2-92E

INTERNAL - DETAILED: Aft Cargo CompartmentBody skin, doubler, stringers, intercostals and frames within 22 inches forward and aft of the aft cargo compartmecutout.


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.


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.


4-00 INTERNAL - DETAILED: Bulk Cargo Door Lower SillBulk cargo door cutout lower sill upper surface.


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


BILITY ENG

JU
D622T001-9-01


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.


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


BILITY ENG

JUN 20




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.

0-00 INTERNAL - DETAILED: Wing Lower Rear Spar Splice FittingWing lower surface rear spar splice fitting at Wing Buttock Line (WBL) 97.9.

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.


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.


8-91E

EXTERNAL - GENERAL VISUAL: Deactivated Door CutoutsBody external skin within 22 inches around deactivated door cutouts.



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


BILITY ENG

JU
D622T001-9-01


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.


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


BILITY ENG

JUL 20




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.


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


BILITY ENG

JU
D622T001-9-01


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


L 2018

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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


BILITY ENG

JUN 20




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.


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


BILITY ENG

JU
D622T001-9-01


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.

4-406-00 EXTERNAL - GENERAL VISUAL: Nacelle Strut No. 1 / 2Nacelle strut.


L 2018

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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


BILITY ENG

JUL 20




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.


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.


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


BILITY ENG

JU
D622T001-9-01


4-426-00 INTERNAL - GENERAL VISUAL: Nacelle Strut No. 1 / 2 - Forward Torque BoxNacelle strut forward torque box stiffeners, skins, spars, frames and mid bulkhead.

4-428-00INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 - Forward Torque BoxNacelle strut mid spar (lower spar of forward torque box) chords in areas of attachments, and nacelle strut formount bulkhead.

4-430-00 INTERNAL - GENERAL VISUAL: Strut 1 / 2 Upper SparUpper spar chords, webs and stiffeners.

4-432-00

INTERNAL - DETAILED: Strut 1 / 2 Upper LinkUpper link, strut attach fitting and fuse pins. Aft upper spar fitting and fuse pins.

AIRPLANE NOTE: SB 767-54-0082. This task is applicable to airplanes prior to line number 702 which have this service bulletin.

4-434-00

INTERNAL - DETAILED: Strut 1 / 2 Upper LinkUpper link, strut attach fitting and fuse pins. Aft upper spar fitting and fuse pins.

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


L 2018

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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


BILITY ENG

JUL 20




0-00

INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Mid-spar FittingNacelle strut outboard mid-spar fitting forward upper tang.

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.


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


BILITY ENG

JU
D622T001-9-01


4-458-00

INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Mid Spar FittingVisible portions of nacelle strut mid spar fitting forward lower tangs (inboard and outboard), vertical tang and dattach fitting above strut firewall.

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.

4-460-00

INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Mid Spar FittingVisible portions of nacelle strut mid spar fitting forward lower tangs (inboard and outboard), vertical tang and dattach fitting above strut firewall.

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


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


BILITY ENG

JUL 20




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.


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.


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.



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


BILITY ENG

JU
D622T001-9-01


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.


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


L 2018

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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


BILITY ENG

JUL 20




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.


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.


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.


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.



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


BILITY ENG

JU
D622T001-9-01


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.


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


BILITY ENG

JUL 20




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.


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


BILITY ENG

JU
D622T001-9-01


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.


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.


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.


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.


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.


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.


L 2018

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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


BILITY ENG

JUN 20




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.


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.


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.



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.




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


BILITY ENG

JU
D622T001-9-01


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.


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.

7-468-00 INTERNAL - GENERAL VISUAL: Nacelle Strut No. 1 / 2 Aft Upper SparNacelle strut aft upper spar (visible inboard portion).

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.


L 2018

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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


BILITY ENG

JUL 20




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.


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.


8-00 INTERNAL - DETAILED: Left / Right Wing Lower Surface Access Hole CutoutsWing lower surface access hole cutouts and adjacent stringers.


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


BILITY ENG

JU
D622T001-9-01


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.


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.


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.


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


L 2018

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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


BILITY ENG

JUL 20




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


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.


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


BILITY ENG

JU
D622T001-9-01


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.


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.


L 2018

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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


BILITY ENG

JUL 20




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.


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.


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


BILITY ENG

JU
D622T001-9-01


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.


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.



L 2018

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ils Page A.1-35

57-61 ing tension s, all beams S 2C 400E 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.


BILITY ENG

JUL 20




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.


8-92 E

INTERNAL - GENERAL VISUAL: Outboard Flap Support Fairing - Left / Right Outboard FlapLeft and right wing outboard TE flap, outboard support linkage.


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).


> 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


18

details Page A.1-36

IONS

BL
D622T001-9-01



ANK

Documents

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