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

767-200/300/300F/400ER

AIRWORTHINESS LIMITATIONS (AWLs)

D622T001-9-01

JUNE 2019

This document has EAR data with an Export Control Classification Number (ECCN) of 9E991. Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.

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COMPILED AND PUBLISHED BY: MAINTENANCE PROGRAMS ENGINEERING BOEING COMMERCIAL AIRPLANE GROUP SEATTLE, WASHINGTON

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TABLE OF CONTENTS

REVISIONS ...... 1.0-5

LIST OF EFFECTIVE PAGES ...... 1.0-18

A. SCOPE...... 1.0-19

B. AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS...... 1.0-20

C. AIRWORTHINESS LIMITATIONS - STRUCTURAL SAFE LIFE PARTS ...... 1.0-93

D. AWLS - STRUCTURAL LIMIT OF VALIDITY (LOV)...... 1.0-95

APPENDIX A – STRUCTURES BASELINE REQUIREMENTS...... A.0-1

A. SCOPE...... A.0-1

B. STRUCTURES BASELINE INSPECTION REQUIREMENTS ...... A.1-1

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REVISIONS

JULY 2014 Original Release This revision contains no technical changes. Please see the 767 MPD Section 9, D622T001-9 for historical Revision Log information.

NOVEMBER 2014 Revised Subsection B. Airworthiness Limitations - Structural Inspections to add a paragraph which addresses special inspection requirements for operators that have incorporated Service Bulletin 767-23-0228.

DECEMBER 2014 Added a new Section D. AWLs - Structural Limit of Validity (LOV) as required by Title 14 Code of Federal Regulations (CFR) Section 26.21 (Amendment 26-6).

FEBRUARY 2015 Revised Structural Safe Life Parts section by reformatting for clarification and updating the 767-400ER life limits based on completion of the main landing gear full-scale fatigue tests and analysis.

OCTOBER 2015 Revised SSI 52-30-I02A to reflect changes made to the DTR Check Form requirements. Added SSI 57-10-I03B - Rear Spar Lower Chord and Skin - Wing Center Section - Hidden Locations - BBL 49.5, 62.05 and 73.0 for the -200SF and -300BCF to the table of Airworthiness Limitations - Structural Inspections in Section B. Added Item 5 to the Table Notes for the Airworthiness Limitations - Structural Inspections Table and added a footnote to the following SSI Items affected by this new note: 57-10- I01A, 57-10-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. DECEMBER 2015 Revised Section D. AWLs - Structural Limit of Validity (LOV) to add applicability for the 767-300BCF.

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JULY 2016 Deleted the FAA Approval signature column from the Revision Log to improve the layout and provide consistency across all Section 9/AWL/CMR/SCI documents. Submittal signatures will no longer be included in the Revision Log. Revised front matter under “REMOVAL OF EXCESS SEALANT WHEN INSPECTING” to update the reference to sealant of fuel tank fasteners to point to the 767 Special Compliance Items/Airworthiness Limitations document, D622T001-9-04. Revised the Airworthiness Limitations - Structural Inspections Table in Section B by adding SSI 53-30-I08A - Fuselage Circumferential Skin and Stringer Splice - BS 434 for the 767-300F, L/N 1108 and on. Revised SSI 57-53-I03I.2 to combine SSI/DTR Forms and their requirements into one SSI/DTR Form to cover all aircraft and added #5 Inboard Flap Support to the title for clarification. Revised SSI 57-53-I03J.1 to combine with SSI 57-53-I03J.2 DTR Form and their requirements into one SSI/DTR Form to cover all aircraft and added #5 Inboard Flap Support to the title for clarification and removed Flag Note <2>. Revised SSI 57-53-I03J.2 to combine SSI/DTR Forms and their requirements into one SSI/DTR Form to cover all airplane models and added #5 Inboard Flap Support to the title for clarification. Revised SSI 57-53-I03K to combine SSI/DTR Forms and their requirements into one SSI/DTR Form to cover all aircraft and added #5 Inboard Flap Support to the title for clarification. Deleted SSI 57-53-I03L.1 and 57-53-I03L.2 as those requirements are now covered in SSI 57-53-I03L. Revised SSI 57-53-I03L to combine SSI/DTR Forms and their requirements into one SSI/DTR Form to cover all aircraft and added #5 Inboard Flap Support to the title for clarification. JULY 2018 Revised document header from 767 to 767-200/300/300F/400ER to list all derivatives. Revised Section A. Scope to add requirement for document to be used in its entirety. Added guidelines that provides a 24 month grace period of change incorporation. Revised Section B reference document names for consistency within this document. Revised to address the inclusion of Appendix A being added to the document to define the baseline inspection program. Revised Threshold section to clarify A-Check and C-check inspection interval, after reaching threshold, to be 3,000 flight cycles, 24 months or 9,000 flight hours for the C-check, and 300 flight cycles or 900 flight hours for the A-check. Revised structural inspection results reporting instructions. The manager of the FAA Oversight Office, the Transport Airplane Directorate, and the FAA have been removed from the list of required recipients. Revised Removal of Excess Sealant When Inspecting to add excess sealant removal instructions and added a table with detailed descriptions table for Excess Sealant. Added the word “Fuselage” to the beginning of phrase “Structural Inspections “ regarding the Airworthiness Limitations document for the 767-300BCF. Revised definition of 767-300, 767-300ER from “300” to “300 PASS”, for clarity. Removed the two notes stating that some ALIs for the 767-200SF and 767-300BCF do not have corresponding DTR check forms. This is to clarify that all 200SF and 300BCF ALIs are included in the DTR Check Form Document. Removed "No DTR Check Form" notes from ALIs table to clarify that all ALIs are included in the DTR Check Form Document.

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JULY 2018, Continued ATA 52 Revised the following SSIs to include the intercostal numbers for the inspection area: 52-30-I05B 52-30-I07B 52-30-I09B Revised SSI 52-30-I07B to correct an error in the July 2016 revision of this document by adding 300F to the Type and Threshold column. Revised the following SSIs to remove the Flagnote <2> as inspection procedures for these items have been published in the applicable 767 Non-Destructive Testing Manual: 52-30-I02A 52-30-I07A 52-30-I07B 52-30-I07C 52-30-I07E 52-30-I07F ATA 53 Revised 137 SSIs to make clarifications. Added the following 6 new SSIs: 53-10-I06A all 767 models 53-10-I32A all 767 models 53-10-I32B all 767 models except 767-300F 53-10-I34/53-30-I29/53-60-I31 all 767 models 53-50-I29A all 767 models 53-50-I29B 767-300 Passenger Deleted the following 3 SSIs: 53-30-I01 767-200SF item SF8A 53-30-I01 767-200SF item SF8B 53-60-I29F Fuselage frame inspections for the 767-200SF and 767-300BCF were reorganized and simplified such that 5 SSIs were merged into other existing SSIs. As a result, updates have been made to the SSI number and the Airplane/Engine Applicability of some of these SSIs. The updated 767-200SF fuselage frame inspection SSIs are the following: 53-30-I24A/53-30-I24B/53-50-I01A/53-50-I02A/53-60-I08A 767-200SF 53-30-I24A/53-30-I24B/53-60-I08A 767-200SF 53-10-I08B 767-200SF and 767-300BCF item BCF3 53-10-I08C/53-30-I24C/53-60-I08C 767-200SF and 767-300BCF item BCF5 53-30-I24C/53-60-I08C 767-200SF and 767-300BCF item BCF6

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JULY 2018, Continued ATA 53, Continued The updated 767-300BCF fuselage frame inspection SSIs are the following: 53-30-I24A/53-30-I24B/53-50-I01A /53-50-I02A /53-60-I08A 767-300BCF item BCF1 53-30-I24A/53-30-I24B 767-300BCF item BCF2/BCF4 53-10-I08B 767-200SF and 767-300BCF item BCF3 53-10-I08C/53-30-I24C/53-60-I08C 767-200SF and 767-300BCF item BCF5 53-30-I24C/53-60-I08C 767-200SF and 767-300BCF item BCF6 The following 13 767-200SF SSIs, that had 767-200SF listed under the Airplane/Engine Applicability for a similar SSI on another airplane model, were separated into their own line item. This was done to clarify the difference between the DTR Check Form for the 767-200SF and the other 767 models in the D622T001-DTR document. 53-30-I14A 53-30-I14C 53-30-I14D 53-50-I06A 53-50-I06B 53-50-I06C 53-50-I06D 53-50-I06E 53-50-I06F 53-60-I06B 53-60-I06C 53-60-I06D 53-60-I10 767-200SF item SF2 The threshold for SSI 53-60-I06B (767-200SF item) was changed from 40,000 cycles to 50,000 cycles. Of the 137 SSIs that were revised for clarifications, the following SSIs were changed more significantly than minor clarifications: The airplane model applicability was changed for the following 6 SSIs: 53-30-I04A RHS 767-300BCF 53-30-I19AD 53-30-I19AD1 53-30-I19AF 53-30-I19AF1 53-50-I19

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JULY 2018, Continued ATA 53, Continued Revised the following 13 SSIs to change the inspection region: 53-10-I10B 53-30-I01 767-200SF item SF5 53-30-I19D 53-30-I19E 53-30-I19F 53-50-I06C 767-200 53-50-I06C 767-200SF 53-60-I10 767-300BCF item BCF2 53-60-I10 767-200SF item SF2 53-60-I10C 53-60-I29A 53-60-I29B 53-60-I29D Revised the following SSIs to add or update required Flagnotes in the Airplane/Engine Applicability: 53-10-I07C/53-30-I04C/53-60-I04C 53-10-I07D/53-30-I04D/53-60-I05D 53-10-I10A 53-10-I10B 53-10-I14A 53-10-I20C 53-10-I21A Line numbers 1- 757 53-10-I21A Line numbers 758 and on 53-30-I14A 767-200SF 53-30-I19A 53-30-I19D 53-30-I19E 53-30-I19F 53-30-I19AD 53-30-I20A 53-30-I22D 767-300 Passenger 53-30-I22D 767-400ER 53-30-I27A/53-50-I03/53-60-I03 53-30-I28 767-200SF 53-30-I28A 53-30-I28B

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JULY 2018, Continued ATA 53, Continued Revised the following SSIs to add or update required Flagnotes (continued): 53-30-I28C 53-30-I28D 53-30-I28E 53-30-I28F 53-50-I06 53-50-I13C 53-50-I14B 53-60-I06B 767-300BCF and All Passenger 53-60-I06B 767-200SF 53-60-I06C 53-60-I06D/53-30-I14D 53-30-I14D 53-60-I06D 53-60-I06E/53-30-I14E 53-60-I06E 53-60-I10C 53-60-I14F 53-60-I27A 767-300 Passenger 53-60-I27A 767-400ER 53-60-I27B 53-60-I27C 53-60-I29A 53-60-I29B 53-60-I29C 53-60-I29D 53-60-I30A 53-80-I01C Revised the following SSIs to remove Flagnote. 53-30-I05/53-30-I08/53-30-I21/53-50-I03/53-60-I03/53-60-I04/53-60-I24/53-60-I33 53-80-I01A 53-80-I01B 53-80-I01D 53-80-I01E 53-80-I15/53-80-I16/53-80-I17

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JULY 2018, Continued ATA 54 Revised 20 SSIs to clarify the title. Revised 59 SSIs to clarify the notes. Revised the following SSIs to change the recommended inspection interval: 54-50-I01 JT9D 54-50-I01 PW4000 54-50-I01 CF6-80C (Except 400E) 54-50-I01c CF6-80C (400E) ≥ 8 Hours 54-50-I03b 524 54-50-I04c CF6-80C (400E) ≥ 8 Hours 54-50-I04e CF6-80C (400E) < 8 Hours 54-50-I17e CF6-80C (400E) ≥ 8 Hours 54-50-I17e CF6-80C (400E) < 8 Hours 54-50-I17f CF6-80C (400E) < 8 Hours Revised the following SSIs to change the recommended inspection type: 54-50-I01c CF6-80C (400E) ≥ 8 Hours 54-50-I04c CF6-80C (400E) ≥ 8 Hours 54-50-I04e CF6-80C (400E) ≥ 8 Hours 54-50-I06 JT9D 54-50-I06 PW4000 54-50-I06 CF6-80A 54-50-I06 CF6-80C (Except 400E) 54-50-I10b CF6-80C (400E) < 8 Hours 54-50-I10b CF6-80C (400E) ≥ 8 Hours 54-50-I14 CF6-80C (400E) < 8 Hours 54-50-I14 CF6-80C (400E) ≥ 8 Hours 54-50-I17e CF6-80C (400E) ≥ 8 Hours 54-50-I17f CF6-80C (400E) < 8 Hours 54-50-I18 CF6-80C (400E) < 8 Hours 54-50-I18 CF6-80C (400E) ≥ 8 Hours

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JULY 2018, Continued ATA 54, Continued Added the following SSIs: 54-50-I01d 80C (400E) < 8 Hours 54-50-I01d 80C (400E) ≥ 8 Hours 54-50-I01e 80C (400E) 54-50-I13f 80C (400E) < 8 Hours 54-50-I13f 80C (400E) ≥ 8 Hours 54-50-I16f 80C (400E) 54-50-I17g CF6-80C (400E) < 8 Hours 54-50-I17g CF6-80C (400E) ≥ 8 Hours Revised the following SSIs to add Flagnote <2> in the Airplane/Engine Applicability Column: 54-50-I01 7R4 54-50-I01 4000 54-50-I01 80C Revised the following SSIs to remove the Flagnote <2> as inspection procedures for these items have been published in the applicable 767 Non-Destructive Testing Manual: 54-50-I01a 54-50-I02/I03a 524 54-50-I03b 524 54-50-I04a 80C (400E) 54-50-I04c 80C (400E) 54-50-I04e 80C (400E) 54-50-I05 7R4 54-50-I05 4000 54-50-I05 80A 54-50-I05 80C (Except 400E) 54-50-I05a 80C (400E) 54-50-I06a 80C (400E) 54-50-I06c 80C (400E) 54-50-I06d 80C (400E) 54-50-I09a/I07/I08/I12 80C (400E) 54-50-I10 524 54-50-I10b 80C (400E) 54-50-I12b 80C (400E) 54-50-I13 7R4 54-50-I13 4000 54-50-I13 80A 54-50-I13 80C 54-50-I13a 80C (400E) (Continued on next page)

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JULY 2018, Continued ATA 54, Continued Revised the following SSIs to remove the Flagnote <2> as inspection procedures for these items have been published in the applicable 767 Non-Destructive Testing Manual, Continued: 54-50-I13e 80C (400E) 54-50-I14 80C (400E) 54-50-I16a 80C (400E) 54-50-I16e 80C (400E) 54-50-I17a 80C (400E) 54-50-I17c 80C (400E) 54-50-I17e 80C (400E) 54-50-I17f 80C (400E)

ATA 55 Revised 2 SSIs to clarify the titles.

ATA 57 Revised 180 SSIs to clarify the titles. Revised 23 SSIs to clarify the zones. Revised the following SSIs to clarify the data in the Airplane/Engine Applicability Column (as described): 57-10-I03A 200ER/300ER with center section fuel, with stage length < 8 hours 57-10-I03A 200ER/300ER with center section fuel, with stage length ≥ 8 hours 57-10-I03B 200ER/300ER with center section fuel, with stage length < 8 hours 57-10-I03B 200ER/300ER with center section fuel, with stage length ≥ 8 hours 57-10-I03C 200ER/300ER with center section fuel, with stage length < 8 hours 57-10-I03C 200ER/300ER with center section fuel, with stage length ≥ 8 hours 57-10-I24 all except 200SF and 300BCF with stage length < 8 hours 57-10-I24 all except 200SF and 300BCF with stage length ≥ 8 hours 57-53-I04Y all except 400ER Revised the following SSIs to replace Flagnote <5> with Flagnote <6> in the Type and Threshold Column, to correct the inspection threshold: 57-10-I03A 200SF & 300BCF 57-10-I03B 200SF & 300BCF 57-10-I03C 200SF & 300BCF 57-20-I15J 200SF & 300BCF 57-20-I16K 200SF & 300BCF (Continued on next page)

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JULY 2018, Continued ATA 57, Continued Revised the following SSIs to add Flagnote <6> in the Type and Threshold Column, to correct the inspection threshold: 57-20-I15K 200SF & 300BCF 57-20-I16L 200SF & 300BCF Revised SSI 57-10-I02 for the 400ER to be applicable to airplanes with stage length < 8 hours. Added SSI 57-10-I02 for the 400ER with stage length ≥ 8 hours. Revised SSI 57-20-I15E to remove 400ER effectivity for airplanes with stage length < 8 hours and airplanes with stage length ≥ 8 hours. Revised 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 airplanes with stage length > 8 hours. Revised 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 to differentiate it from bolt shank inspections. Revised SSI # for SSI 57-53-I03F - Inboard Flap Support No. 3/6 - Flap Attachment Bolts - Shank Location to SSI 57-53-I03F.2 to differentiate it from SSI 57-53-I03F.1 Revised the threshold for SSI 57-10-I08 to correct a typographical error from 70,000 flight hours to 80,000 flight hours. Revised the following SSIs to add Flagnote <2> in the Airplane/Engine Applicability Column: 57-20-I07 400ER, and all airplane types L/N 922 and later Revised the following SSIs to remove the Flagnote <2> as inspection procedures for these items have been published in the applicable 767 Non-Destructive Testing Manual: 57-10-I02B 400ER with stage length < 8 hours 57-10-I02B 400ER with stage length ≥ 8 hours 57-10-I25 400ER with stage length < 8 hours 57-10-I25 400ER with stage length ≥ 8 hours 57-20-I15F 400ER with stage length < 8 hours 57-20-I15F 400ER with stage length ≥ 8 hours 57-53-I02A.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I02A.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I02B 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 922 and Later and 400ER 57-53-I02D.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I02E 200, 200SF, 300BCF, 300F, 300 PASS L/N 922 and later and 400ER 57-53-I02G.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I02I ALL 57-53-I02J.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I02J.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I02L.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I02L.3 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I02M.1 200, 200SF, 300BCF, 300F, 300 PASS L/N 922 and later and 400ER 57-53-I03E.1 200, 200SF, 300BCF, 300F, 300 PASS L/N 922 and later and 400ER

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JULY 2018, Continued ATA 57, Continued Revised the following SSIs to remove the Flagnote <2> as inspection procedures for these items have been published in the applicable 767 Non-Destructive Testing Manual (continued):

57-53-I04A.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I04B.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-882 57-53-I04B.3 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-882 57-53-I04D.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-882 57-53-I04E.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I04E.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I04E.3 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I04F.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I04F.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I04H 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I04I ALL 57-53-I04K.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I04N.1 200, 200SF, 300BCF, 300F, 300 PASS L/N 922 and later and 400ER 57-53-I04P ALL 57-53-I04Q.1 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I04Q.2 200, 200SF, 300BCF, 300F, 300 PASS L/Ns 1-921 57-53-I04S ALL 57-53-I04T ALL 57-53-I04AA 200, 200SF, 300BCF, 300F, 300 PASS L/N 922 and later and 400ER 57-54-I13 400ER 57-54-I14 400ER Revised the following SSIs to revise the threshold from 80,000 flight hours to 70,000 flight hours in the Type and Threshold Column, to reflect the 200SF & 300BCF fatigue requirements, including a grace period for the 300BCF: 57-10-I16C 300BCF 57-10-I16D 200SF 57-20-I15K 200SF and 300BCF 57-20-I16L 200SF and 300BCF

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JULY 2018, Continued ATA 57, Continued Revised the following SSIs to revise the threshold from 50,000 flight cycles to 25,000 flight cycles in the Type and Threshold Column, to reflect the 200SF & 300BCF fatigue requirements, including a grace period for the 300BCF: 57-10-I03A 200SF and 300BCF 57-10-I03B 200SF and 300BCF 57-10-I03C 200SF and 300BCF 57-20-I15J 200SF and 300BCF 57-20-I16K 200SF and 300BCF Revised Flagnote <1> description to reflect that this Flagnote is no longer being used. Revised Flagnote <3> and <4> description to be consistent with Flagnote <2>. Added Flagnote <6>. Added Appendix A to provide information related to AD 2014-14-04 paragraph (g) requirements. JUNE 2019 Revised A. Scope to update guidelines that provides a 24 month grace period of change incorporation. Revised the structural inspection requirements when reaching threshold for clarity. ATA 52 Revised SSIs 52-30-I05A and 52-30-I09A (300F) to remove the Flagnote <2> as inspection procedures for these items have been published in the applicable 767 Non-Destructive Testing Manual. ATA 53 Revised 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-I34/53-30-I29/53-60-I31, 53-30-I19AB (300BCF, 300F, and 400E), 53-30-I19AC (300BCF, 300F, and 400E), 53-50-I29A, 53-50-I29B (300 PASS), 53-60-I27B (300 PASS and 400E), 53-60-I27C (300 PASS and 400E), and 53-80-I01C (Line numbers 424 and on) to remove the Flagnote <2> as inspection procedures for these items have been published in the applicable 767 Non-Destructive Testing Manual. Revised SSI 53-60-I10C (300F) to remove the Flagnote <3> as inspection procedures for these items have been published in the applicable 767 Non-Destructive Testing Manual. Revised SSIs 53-30-I01 (200SF), 53-30-I14A (200SF), 53-60-I06C (300BCF), 53-60-I10 (300BCF), and 53-60-I10 (200SF) to remove the Flagnote <4> as inspection procedures for these items have been published in the applicable 767 Non-Destructive Testing Manual. Revised Appendix A to change the applicability for MPD Item 53-550-91 from "300, 300BCF, 400ER" to "300, 300BCF, 400E". Revised Appendix A to change MPD Item 53-618-00 to Internal - Detailed: Wing Center Section Lower Surface At Rear Spar Chord and Splice Stringers in the structures baseline inspection requirements. Revised Appendix A to add MPD Item 53-618-91 Internal - Detailed: Wing Center Section Lower Surface At Rear Spar Chord and Splice Stringers to the structures baseline inspection requirements. Revised Appendix A to change the applicability for MPD Item 53-710-92 from "ALL" to "200, 300, 300BCF, 400E". Revised Appendix A to change the applicability for MPD Item 53-710-93 from "300, 300BCF, 400ER" to "300, 300BCF, 400E". (Continued on next page)

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JUNE 2019, Continued ATA 54 Added SSIs 54-50-I01f (80C (400E), < 8 Hours), 54-50-I01f (80C (400E), ≥ 8 Hours), 54-50-I04f (80C (400E), < 8 Hours), 54-50-I04f (80C (400E), ≥ 8 Hours), 54-50-I13g (80C (400E), < 8 Hours), 54-50-I13g (80C (400E), ≥ 8 Hours), 54-50-I17h (80C (400E), < 8 Hours), and 54-50-I17h (80C (400E), ≥ 8 Hours). Revised SSIs 54-50-I01e (80C (400E)), 54-50-I18 (80C (400E), < 8 Hours), and 54-50-I18 (80C (400E), ≥ 8 Hours) to remove the Flagnote <2> as inspection procedures for these items have been published in the applicable 767 Non-Destructive Testing Manual. ATA 57 Revised SSIs 57-20-I16F (400E, < 8 Hours) and 57-20-I16F (400E, ≥ 8 Hours) to add Flagnote <2> in the Airplane/Engine Applicability Column. Revised the threshold for SSI 57-53-I03K to include 25,000 Cycles after SB 767-27A0176 was accomplished in the Type and Threshold Column. Revised Appendix A front matter for clarity. Revised Appendix A to remove the special note for MPD Item 57-416-91 requiring the removal of sealant.

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A. SCOPE

The scheduled maintenance requirements described in this document result from Model 767 airplane certification activities with the U.S. Federal Aviation Administration (FAA). Accordingly, this FAA approved Airworthiness Limitations document is cross-referenced in the Model 767 Type Certificate Data Sheet. These maintenance actions are mandatory.

This Airworthiness Limitations document is FAA approved and specifies maintenance required under Title 14 Code of Federal Regulations (CFR) § 43.16 and § 91.403 unless an alternative program has been FAA Oversight Office approved. The Airworthiness Limitations document must be used in its entirety at a specific revision level, and maintenance requirements and limitations from different revision levels shall not be combined.

Where used in this document, the term “FAA Oversight Office” is defined as the FAA office that currently has oversight responsibility for the type certificate of the Boeing model 767. At the time of publication, the FAA office with oversight responsibility for the type certificate of the 767 is the FAA Boeing Aviation Safety Oversight Office (BASOO).

AIRWORTHINESS LIMITATIONS

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

If the inspections cannot be accomplished due to repairs and/or modifications, an alternate inspection approved by the FAA Oversight Office must be used.

CHANGE INCORPORATION

Within 24 months after the release date of the June 2019 version of this document, operators should revise their maintenance program to incorporate all the changes contained in this document, including Appendix A.

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B. AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS

The Structural Inspection Program approved in Section 3 of the 767 Maintenance Review Board (MRB) Report and contained in Section 2 of the Maintenance Planning Document (MPD) D622T001 describes an initial baseline structural maintenance program for all Structural Significant Items (SSIs). This program was developed in accordance with the guidelines of MSG-3 and partially satisfies the requirements of Title 14 CFR § 25.571 by providing accidental and environmental damage detection opportunity for all SSIs, and in some cases, fatigue damage detection opportunity until the supplemental inspection threshold is reached. The supplemental structural inspections listed in this “Airworthiness Limitations” document are for those SSIs that do not receive adequate fatigue damage detection opportunity from the initial baseline structural program that is listed in Section 2 of the MPD and in Appendix A of this document. The inspections shown in this section and Appendix A are to be accomplished in conjunction with and not as a substitute for the existing structural maintenance program found in Section 2 of the MPD.

The supplemental structural inspection program uses the Damage Tolerance Rating (DTR) system to determine the inspections (and repeat intervals) necessary to provide adequate fatigue damage detection. The DTR system defines a required DTR (a numerical value) that must be achieved for each SSI. DTR Check Forms which define the inspection options and the required DTR are contained in Document D622T001-DTR.

THRESHOLD

The certifying authority (FAA Oversight Office) requires designation of all SSIs into two categories. These two categories are referred to as Type 1 and Type 2. Type 1 structure requires the implementation threshold to be established by crack growth analysis. Type 2 structure is allowed to have the implementation threshold established by fatigue analysis (supported by test evidence) and allows for the future escalation of the inspection threshold when sufficient data from the initial inspections statistically support an increased threshold. See Document D622T001-DTR for a detailed definition of Type 1 and Type 2 categories.

The inspections are to be done on the basis of the threshold specified in the AWL - Structural Inspections table and repeat inspections determined from DTR Check Forms contained in Document D622T001-DTR.

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Initial inspection (threshold) and intervals are measured in flight cycles or flight hours that a particular SSI detail has accumulated regardless of what the airframe as a whole has accumulated. Most SSI details have never been replaced and therefore have accumulated the same flight cycles and flight hours as the airframe. Some SSI details are replaced, such as when installing Removable Structural Components (repairable/rotable/expendables) or installing used structural parts as a repair. In these cases the SSI details have accumulated flight cycles and flight hours that may be different than the airframe. The operator must account for this in determining when inspections must be done.

Although intended for repairs, FAA AC 120-93 Appendix 7, provides a method for determining the age of a Removable Structural Component, which may be applied to the baseline structure.

The Airworthiness Limitations - Structural Inspections table defines the inspection implementation threshold. Some items are sensitive to flight length and identified by “FLS” (Flight Length Sensitive) in the Threshold column of the table. FLS Items require both flight hours and flight cycles to determine the implementation threshold. Refer to Figure 1, shown on the next page, to determine the threshold for FLS Items.

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FIGURE 1. FLIGHT LENGTH SENSITIVE (FLS) THRESHOLD CURVE

Instructions for the use of the Flight Length Sensitive (FLS) Threshold Curve:

1. Determine, for each airplane, the accumulated flight cycles and flight hours.

2. Enter the FLS Threshold Curve at the appropriate flight cycles and flight hours and plot point.

3. The initial supplemental inspection must be accomplished before crossing into the shaded area on the FLS Threshold Curve. Note that the shaded area for the -200, -200SF, -300 Passenger, and -300BCF aircraft is different from that for the -300F Freighter and -400ER Passenger aircraft.

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In addition to the thresholds described above, a calendar threshold of 20 years applies unless an initial inspection of an FAA approved Corrosion Prevention and Control Program (CPCP) has occurred, constituting CPCP implementation.

The information contained in Appendix A provides operators with the Baseline Structures and Zonal Inspection tasks that must be used upon the airplane reaching the fatigue threshold. This must be done in order to ensure the maintenance program complies with Title 14 CFR § 25.571 Damage Tolerance Requirements.

As such, when reaching the threshold the inspection must be the lesser of: 1) the FAA approved Structural and Zonal Inspection intervals in the Operator's baseline inspection program or 2) the inspection intervals contained in Appendix A.

When reaching the threshold of 50,000 flight cycles (-200, -200SF1 and -300 Passenger or -300 Passenger converted to -300BCF aircraft after 10,000 cycles or more as a -300 Passenger) or 40,000 flight cycles (-300F Freighter or -400ER Passenger or -300 Passenger converted to -300BCF aircraft before 10,000 cycles as a -300 Passenger) or the FLS curve, whichever comes first, the Structures A-check inspection interval described in Appendix A as "S 1A" must be no greater than 300 flight cycles or 900 flight hours whichever comes first, and the Structures C-check inspection interval described in Appendix A as “S 1C” must be no greater than 3,000 flight cycles or 24 months or 9,000 flight hours, whichever comes first. This means that any operator who has escalated their structures inspection program by increasing the Structures A-check or C-check inspection interval must reduce their Structures A- check or C-check inspection interval to within these limits when they reach the threshold. The reason for this is that the Title 14 CFR § 25.571 damage tolerance evaluation takes credit for the baseline Structures Inspection Program defined in Appendix A. The Airworthiness Limitations listed in this document are supplemental structural inspections of the SSIs for which the required DTR is not satisfied by the baseline Structural Inspection Program defined in Appendix A. Any continued escalation beyond the baseline Structures A-check or C-check inspection interval could result in additional structure not meeting the required DTR which was the basis of certification. The inspections contained within the Airworthiness Limitations are to be accomplished in conjunction with, and not as a substitute for, the existing Structures Inspection Program found in Appendix A.

767 PASSENGER-TO-FREIGHTER CONVERSION AIRPLANES

Certain 767 airplanes are modified from passenger model airplanes to a freighter configuration via Boeing service bulletin. After incorporation of the Boeing passenger-to-freighter service bulletin, these 767-200 and 767-300 airplanes are designated as 767-200SF and 767-300BCF. Refer to Section C of this chapter for additional data related to 767-200SF and 767-300BCF structural safe life parts.

1 Only one -200SF exists, and it was modified after 14,900 cycles as a Passenger aircraft.

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Certain 767-300BCF supplemental inspection thresholds are calculated based on the summation of fatigue damage accrued as a passenger and then a freighter. These are identified by “Combined Threshold” in the Threshold column. Refer to Figure 2 to determine the threshold for these items.

Certain 767-300BCF supplemental inspection thresholds are calculated from the date of modification. These are identified by “Mod Date Sensitive” in the Threshold column. Refer to Figure 3 to determine the threshold for these items.

Instructions for the use of the Combined Life Threshold curve:

1. Determine, for each airplane, the accumulated flight cycles prior to BCF modification. 2. Enter the threshold curve at the appropriate flight cycles as 300ER. 3. The initial supplemental inspection must be accomplished before crossing the 300BCF Combined Threshold curve.

Instructions for the use of the Mod Date Sensitive curve:

1. Determine, for each airplane, the accumulated flight cycles prior to BCF modification. 2. Enter the threshold curve at the appropriate flight cycles as 300ER. 3. The initial supplemental inspection must be accomplished before crossing the 300BCF Mod Date Sensitive curve.

Note: The 767-300BCF Airworthiness Limitations - Fuselage Structural Inspections contained in this section are applicable to converted airplane variable numbers VN191 thru VN197. For the Airworthiness limitations - Fuselage Structural inspections of all other 767-300BCF, the operator must refer to document D622T200-01 "767-300BCF Instructions for Continued Airworthiness - Airworthiness Limitation Items Supplement," Revision New or later.

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Combined Threshold

55000

50000

45000

40000

35000

Combined ThresholdCombined (Cycles) 30000

25000 0 5000 10000 15000 20000 25000 30000 35000 40000 45000 50000 Flights as 300ER (Cycles)

53-30-I01 BCF2 Section 43 Crown SK/STR at Aft Edge External Doubler 53-30-I01 BCF10 Crown Stringer STA 654+110 to STA 786 53-30-I04D BCF1 Inner Skin at Lower Fastener Row S-26L Lap 53-30-I04A BCF2 Out er Skin at Upper Fastener row S-8L Lap (L2 Panel) 53-30-I04B STR 8R Lap BS 434 - 654+22 Inner Skin at Lower Fastner Row

FIGURE 2. Combined Passenger and Freighter Life Threshold

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FIGURE 3. Mod Date Sensitive Structure

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REPEAT INSPECTION INTERVAL

A repeat inspection interval for the fatigue inspection of an SSI is established from its DTR Check Form. Airplanes with an average flight length (flight hours per landing) equal to or more than 8 hours must use the DTR Check Form labeled "767 > 8 hours" at the top of the form (see Document D622T001- DTR for DTR Check Forms). Revision to the required DTR or the DTR curve is not allowed without approval from the FAA Oversight Office.

SPECIAL STRUCTURAL INSPECTIONS

For operators that incorporate the SATCOM retrofit, given in SB 767-23-0228, supplemental structural inspections apply. After incorporation of SB 767-23-0228, prior to returning the aircraft to service the supplemental inspections in SB 767-23-0228 shall be incorporated into the aircraft maintenance program.

REPORTING RESULTS OF STRUCTURAL INSPECTIONS

All cracks found during these inspections shall be reported within ten (10) days directly to Boeing Commercial Airplanes using the Discrepant Structure Report Form. Refer to Document D622T001-DTR for the required report form (any suitable alternative which contains the same information may be used).

REMOVAL OF EXCESS SEALANT WHEN INSPECTING

1. In areas where the DTR Check Forms, or the MPD Items listed in Paragraph 2, require sealant removal, use the following: • Refer to AMM 51-31-01 for general sealant removal and application, and the use of proper tools. Do not use a metal blade or knife. Check to make sure 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 application. • Refer to AMM 28-11-00 (Task 28-11-00-308-060) for secondary fuel barrier sealant (BMS 5-81, Type II) outside the fuel tank removal and application, on the wing center section. • If sealant is removed inside the fuel tank for inspection, care must be taken to remove any sealant debris in the fuel tank. • Sealant of fuel tank fasteners must comply with the 767 Special Compliance Items/Airworthiness Limitations document, D622T001-9-04. 2. The following MPD Items require sealant to be removed, or limited, to accomplish the baseline visual inspections at, or prior to, the listed thresholds:

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EXCESS SEALANT TABLE

INSTALLATION DRAWING DESCRIPTION OF SEALANT REMOVAL AT AREAS WHERE INSPECTIONS NEED TO BE PERFORMED General Notes AIRPLANE MPD ITEM THRESHOLD APPLICABILITY ITEM NO. 1. Any sealant that is removed does not need to be NUMBER TITLE reapplied except where indicated. 2. Do not remove fillet seals along the edges of parts unless where indicated.

Prior to inspection of the splice stringers L-6 and L-10 the following sealant removal is required: 1. At all locations, remove fastener cap seals on the stringer horizontal flange surfaces. Replace fastener cap 1. Wing - Center 25,000 FC or seals after inspections. Section - Lower 80,000 FH, Lower Panel Instl and Assy - 400ER 57-416-00 111T4000 Surface Splice whichever Wing, Center Section 2. At all locations, ensure that the fillet seals that overlap Stringers comes first onto the stringer horizontal flanges do not extend past the centerline of the nearest fastener row. 3. At the intersection with the external beams at BL 9.5 and BL 62, remove the fillet seals that overlap onto the surface of the stringer horizontal flanges.

Prior to inspection of the side-of-body rib web at the lower plus chord, the following sealant removal is required: 2. Wing - Center 25,000 FC or Section - Side of ALL models with 1. At the rib web to lower plus chord attachment, remove 80,000 FH, Body Rib Web - at Wing Center 57-526-00 112T5000 Rib Instl - Wing, BBL 97.42 whichever the fillet seal overlap onto the vertical surface of the rib Attachment to the Section Fuel comes first web. Lower Plus Chord 2. Limit fastener cap seals on the rib web along the lower plus chord to 0.4 inches from the edge of the fastener head or collar.

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EXCESS SEALANT TABLE

INSTALLATION DRAWING DESCRIPTION OF SEALANT REMOVAL AT AREAS WHERE INSPECTIONS NEED TO BE PERFORMED General Notes AIRPLANE MPD ITEM THRESHOLD APPLICABILITY ITEM NO. 1. Any sealant that is removed does not need to be NUMBER TITLE reapplied except where indicated. 2. Do not remove fillet seals along the edges of parts unless where indicated.

Prior to inspection of the rear spar lower chord the following sealant must be removed: 1. At all locations, remove any fillet sealant which overlaps onto the horizontal and vertical flanges of the spar chord. 2. At the external fittings at BL 49.5, BL 62.05 and BL 73 25,000 FC or 3. Wing - Center 200ER and 300ER Rear Spar Assembly and remove the fastener cap seals on the horizontal and 80,000 FH, Section - Rear with center section 57-420-00 111T1000 Installation - Wing, Center whichever vertical flanges of the spar chord. Replace fastener cap Spar Lower Chord fuel Section comes first seals after the inspection. 3. At all other locations limit the fastener cap seals on the horizontal spar chord flange to 0.150 inches from the edge of the collars. 4. At all other locations limit the fastener cap seals on the vertical spar chord flange to 0.25 inches from the edge of the collars or fastener heads.

Prior to inspection of the lower skin adjacent to rear spar 4. Wing - Center 200ER and 300ER lower chord at the hidden locations at BL 49.5, BL 62.05 Section - Lower with center section Lower Panel Instl and Assy - and BL 73.0, remove any fillet sealant extending more Skin adjacent to 57-420-00 FLS 111T4000 fuel and flight Wing, Center Section Rear Spar Lower than 0.18 inches from the edge of the spar chord onto length < 8 hours Chord the lower skin as described in 767 NDT Manual, Part 6, 57-10-04, Paragraph 3B.

Prior to inspection of the rear spar lower chord between 5. Wing - Center 25,000 FC or BL 62 and WBL 97.9, and between LBL 11 and RBL 11, Section - Rear 400ER with flight 80,000 FH Rear Spar Assy and Instl - remove sealant on the fastener cap seals of the rear spar Spar Lower Chord 57-422-00 111T1000 length < 8 hours whichever Wing, Center Section at Web lower chord vertical flange such that at least 0.40 inches comes first Attachment of spar chord surface is visible between the fastener rows.

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EXCESS SEALANT TABLE

INSTALLATION DRAWING DESCRIPTION OF SEALANT REMOVAL AT AREAS WHERE INSPECTIONS NEED TO BE PERFORMED General Notes AIRPLANE MPD ITEM THRESHOLD APPLICABILITY ITEM NO. 1. Any sealant that is removed does not need to be NUMBER TITLE reapplied except where indicated. 2. Do not remove fillet seals along the edges of parts unless where indicated.

6. Wing - Prior to inspection of the lower surface splice stringers Outboard - Lower L-6 and L-10, ensure that fillet seal overlap onto the 25,000 FC or Surface Splice stringer horizontal flange does not extend past the ALL except 80,000 FH Panel Installation - Inspar, Stringers - 57-516-00 112T4000 200SF, 300BCF whichever Wing, Lower centerline of the nearest fastener row. Stringers L-6 and comes first L-10 - Side-of- Body to Rib 3

Prior to inspection of the rear spar lower chord, the following sealant removal is required: 7. Wing - 1. Remove the fillet seal overlaps onto the surfaces of Outboard - Rear 25,000 FC or Rear Spar Instl - Wing the spar chord vertical and horizontal flanges. Spar Lower Chord 57-522-00 112T1000 ALL except 200SF 80,000 FH and Skin - 2. Ensure that the fastener cap seals on the horizontal and 300BCF whichever Panel Installation - Inspar, Between Fairing 57-524-00 112T4000 spar chord flange do not extend more than 0.150 inches comes first Wing, Lower at Side-of-Body from the edge of the collars. and Rib 3 3. Ensure that the fastener cap seals on the vertical spar chord flange do not extend more than 0.25 inches from the edge of the collars or fastener heads.

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EXCESS SEALANT TABLE

INSTALLATION DRAWING DESCRIPTION OF SEALANT REMOVAL AT AREAS WHERE INSPECTIONS NEED TO BE PERFORMED General Notes AIRPLANE MPD ITEM THRESHOLD APPLICABILITY ITEM NO. 1. Any sealant that is removed does not need to be NUMBER TITLE reapplied except where indicated. 2. Do not remove fillet seals along the edges of parts unless where indicated.

Prior to inspection of the front spar lower chord, the following sealant removal is required: 1. At external stiffeners and auxiliary track ribs, between Rib 9 and Rib 31, ensure that the fillet seal overlap onto the spar chord horizontal flange does not extend past the 8. Wing - centerline of the nearest fastener row. Outboard - Front 400ER with flight Spar Lower Chord 57-530-00 FLS 112T2000 Front Spar Instl - Wing 2. At external stiffeners between Rib 9 and Rib 14, and length < 8 hours at Externally between Rib 24 and Rib 31, ensure that fillet seal overlap Hidden Details onto the spar chord vertical flange does not extend past the centerline of the nearest fastener row. 3. At external stiffeners between Rib 14 and Rib 24, ensure that the fillet seal on the front spar chord vertical flange does not extend more than 0.125 inches below the fastener collars on the lower fastener row.

Prior to inspection of the front spar lower chord between 9. Wing - ALL except Rib 9 and Rib 10, ensure that the fillet seal overlap onto Outboard - Front 400ER, 200SF 57-530-00 FLS 112T2000 Front Spar Instl - Wing Spar Lower Chord and 300BCF the spar chord horizontal and vertical flanges does not extend past the centerline of the nearest fastener row.

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EXCESS SEALANT TABLE

INSTALLATION DRAWING DESCRIPTION OF SEALANT REMOVAL AT AREAS WHERE INSPECTIONS NEED TO BE PERFORMED General Notes AIRPLANE MPD ITEM THRESHOLD APPLICABILITY ITEM NO. 1. Any sealant that is removed does not need to be NUMBER TITLE reapplied except where indicated. 2. Do not remove fillet seals along the edges of parts unless where indicated.

Prior to inspection of the front spar lower chord, between Ribs 14 and Ribs 24, at hidden details common to external stiffeners and aux track ribs, the following sealant removal is required: 10. Wing - 1. Ensure that the fillet seal overlap onto the spar chord Outboard - Front 400ER with stage 57-538-00 FLS 112T2000 Front Spar Instl - Wing Spar Lower Chord length < 8 hours horizontal flange does not extend past the centerline of - Hidden Details the nearest fastener row. 2. Ensure that fillet sealant overlap on the spar chord vertical flange does not extend more than 0.125 inches below the edge of the fastener collars on the lower fastener row.

Prior to inspection of the rear spar lower chord, between Rib 6 and Rib 8, the following sealant removal is required: 1. Ensure that the fillet seal overlap onto the spar chord 11. Wing - horizontal flange does not extend more than 0.125 Outboard - Rear 400ER 57-538-00 FLS 112T1000 Rear Spar Instl - Wing Spar Lower Chord inches aft of the edge of the fastener collars in the aft fastener row. 2. Ensure that the fillet seal overlap onto the spar chord vertical flange does not extend past the centerline of the nearest fastener row.

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EXCESS SEALANT TABLE

INSTALLATION DRAWING DESCRIPTION OF SEALANT REMOVAL AT AREAS WHERE INSPECTIONS NEED TO BE PERFORMED General Notes AIRPLANE MPD ITEM THRESHOLD APPLICABILITY ITEM NO. 1. Any sealant that is removed does not need to be NUMBER TITLE reapplied except where indicated. 2. Do not remove fillet seals along the edges of parts unless where indicated.

Prior to inspection of the rear spar lower chord, between Rib 3 and Rib 6 and between Rib 8 and Rib 11, the following sealant removal is required: 1. Ensure that the fillet seal overlap onto the horizontal 12. Wing - 400ER with stage spar chord flange does not extend past the centerline of Outboard - Rear 57-538-00 FLS 112T1000 Rear Spar Instl - Wing length > 8 hours Spar Lower Chord the nearest fastener row. 2. Ensure that the fillet seal overlap onto the spar chord vertical flange does not extend more than 0.125 inches below the edge of the fastener collars on the lower fastener row.

Prior to inspection of the rear spar lower chord, between Rib 3 and Rib 11 at external stiffeners, the following sealant removal is required: 13. Wing - 1. Ensure that the fillet seal overlap onto the spar chord Outboard - Rear horizontal flange does not extend past the centerline of 400ER 57-538-00 FLS 112T1000 Rear Spar Instl - Wing Spar Lower Chord the nearest fastener row. - Hidden Details 2. Ensure that the fillet seal and fastener cap seals on the spar chord vertical flange does not extend more than 0.125 inches below the edge of the fastener collars on the lower fastener row.

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EXCESS SEALANT TABLE

INSTALLATION DRAWING DESCRIPTION OF SEALANT REMOVAL AT AREAS WHERE INSPECTIONS NEED TO BE PERFORMED General Notes AIRPLANE MPD ITEM THRESHOLD APPLICABILITY ITEM NO. 1. Any sealant that is removed does not need to be NUMBER TITLE reapplied except where indicated. 2. Do not remove fillet seals along the edges of parts unless where indicated.

Prior to inspection of the lower surface splice stringer L- 10 the following sealant removal is required: 1. Between Rib 7 and Rib 20, ensure that fillet seal 14. Wing - overlap onto the splice stringer horizontal flange does 25,000 FC or Outboard - Lower not extend past the centerline of the nearest fastener ALL except 200SF 80,000 FH Panel Installation - Inspar, Surface Splice 57-540-00 112T4000 row. and 300BCF whichever Wing, Lower Stringers - comes first 2. Under the nacelle fairing, remove fastener cap seals Stringers L-10 on the stringer horizontal flanges. Replace fastener cap seals after inspection. 3. Under the nacelle fairing, remove fillet seal overlap on the splice stringer horizontal flanges.

15. Wing - Center Prior to inspection of the lower surface stringer L-1, L-2 25,000 FC or Section - Lower and L-5, the following sealant removal is required: 80,000 FH Lower Panel Instl and Assy - Panel - Typical ALL 53-830-00 111T4000 whichever Wing, Center Section Ensure that the fillet seal overlap onto the stringer Stringers 1, 2, and comes first horizontal attach flange does not extend past the 5 - Typical Details centerline of the nearest fastener row.

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The following pages, included in the Airworthiness Limitations - Structural Inspections table, list the Airworthiness Limitation supplemental inspection requirements. Each item is listed by SSI Number, DTR Check Form Title, Inspection Zone, Airplane/Engine Applicability, Type and Threshold.

There are corresponding DTR Check Forms (in Document D622T001-DTR) for each item listed in the table. Where there is more than one listing for a given SSI Number, the DTR Check Form Title is the unique identifier along with the Airplane/Engine Applicability. Airplane/engine applicability is listed as follows

ALL = All Airplanes PASS (-ER ONLY) = Passenger Airplanes, Extended Range Only.

PASS = Passenger Airplanes < 8 HOURS = Airplanes with cumulative stage length (Flight Hours per Landing) less than 8 hours.

200 = 767-200, -200ER

200SF = 767-200 Special Freighter

300 PASS = 767-300, -300ER > 8 HOURS = Airplanes with cumulative stage length (Flight Hours per Landing) equal to or more than 8 hours.

300BCF = 767-300 Boeing Converted Freighter

300F = All 767-300 Freighters

400E = 767-400ER

4000 = P&W PW4052, PW4056, PW4060, PW4062

7R4 = P&W JT9D-7R4D and -7R4E

80A = GE CF6-80A

80C = GE CF6-80C

524 = RR RB211-524H

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 27-40-I01A Stabilizer Trim Actuator - Lower Gimbal Lug Assy BS 1708.5, WL 239.9 311, 312 ALL Type 1 50,000 Cycles (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 27-40-I01B Stabilizer Trim Actuator - Lower Gimbal Plate Assy BS 1708.5, WL 239.9, BL 0.0 311, 312 400E Type 1 40,000 Cycles

52-30-I02A Standard Cargo Door Forward and Aft - Applicable to 767 Airplanes with Standard 821, 822 200, 200SF Type 1 (70x69) Cargo Doors - 8 Places (At Beams #1, #2, #3, and #4 between Door Sta 184.4 300BCF, 300 PASS 50,000 Cycles and 189.6 and between Door Sta 208.4 & 213.6) 400E (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (400E) 52-30-I05A Latch Cam Support Frame Fitting - Forward large Cargo Door - Fitting Lug Bore 821 ALL Type 2 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300BCF, 300F, 400E) 52-30-I05B Latch frame inner chord - Forward large Cargo Door - Latch Frame Inner Chord at 821 ALL Type 1 Splice to Latch Frame Support Fitting in the area common to intercostal #6 37,500 Cycles (200, 300 PASS) 30,000 Cycles (300BCF, 300F, 400E) 52-30-I05C Outer Skin - Forward large Cargo Door - Outer Skin at attachment to main hinge 821 ALL Type 1 segments at forward and aft ends of the door 37,500 Cycles (200, 300 PASS) 30,000 Cycles (300BCF, 300F, 400E) 52-30-I07A Latch Cam Support Fitting - Main Deck Cargo Door - Fitting Lug Bore 838 200SF Type 2 300BCF, 300F 40,000 Cycles (300F) 50,000 Cycles (200SF) Mod Date Sensitive (300BCF)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 52-30-I07B Latch Frame Inner Chord - Main Deck Cargo Door - Latch Frame Inner Chord at Splice 838 200SF Type 1 to Latch Frame Support Fitting in the area common to intercostal #11 300BCF, 300F 30,000 Cycles (300F) 44,900 Cycles (200SF) Mod Date Sensitive (300BCF) 52-30-I07C Outer Skin - Main Deck Cargo Door - Outer Skin at attachment to main hinge 838 200SF Type 1 segments at forward and aft ends of the door 300BCF, 300F 44,900 Cycles (200SF) Mod Date Sensitive (300BCF) 30,000 Cycles (300F) 52-30-I07E MDCD Outer Skin Lap Splice - Upper row (upper skin) - Intercostal #5 838 200SF Type 2 300BCF, 300F 50,000 Cycles (200SF) Mod Date Sensitive (300BCF) 40,000 Cycles (300F) 52-30-I07F MDCD Outer Skin Lap Splice - Lower row (lower skin) - Intercostal #5 838 200SF Type 1 300BCF, 300F 44,900 Cycles (200SF) Mod Date Sensitive (300BCF) 30,000 Cycles (300F) 52-30-I09A Latch Cam Support Fitting - Aft large Cargo Door - Fitting Lug Bore 822 300F Type 2 40,000 Cycles 52-30-I09B Latch Frame Inner Chord - Aft large Cargo Door - Latch Frame Inner Chord at Splice to 822 300F Type 1 Latch Frame Support Fitting in the area common to intercostal #6 30,000 Cycles 52-30-I09C Outer Skin - Aft large Cargo Door - Outer Skin at attachment to main hinge segments 822 300F Type 1 at forward and aft ends of the door 30,000 Cycles 53-10-I06A Outflow Valve Cutout Doubler 123 ALL Type 2 BS 400 to BS 410, S-35L to S-36L 50,000 Cycles (200, 300 PASS, Note: Only applicable to aircraft configured at delivery with the subject structure. 300BCF) 40,000 Cycles (300F, 400E)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-10-I07A Skin Longitudinal Lap Splices - Upper Row - Crown and Upper Lobe, Sections 41, 43 220, 230, 250 ALL Type 2 53-30-I04A and 46 50,000 Cycles 53-60-I05A Inspection requirements are altered for the following locations: (200, 200SF, 300BCF, 1) 767-300BCF: S-8L STA 654+22 to 654+110 and S-8R, STA 434 to 654+22. See 300 PASS) additional entries for SSI # 53-30-I04A. 40,000 Cycles (300F, 400E) 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. 53-10-I07B Skin Longitudinal Lap Splices - Lower Row - Crown and Upper Lobe, Sections 41, 43 220, 230, 250 ALL Type 2 53-30-I04B and 46 50,000 Cycles 53-60-I05B Inspection requirements are altered for the following locations: (200, 200SF, 300BCF, 300 1) 300BCF: S-8R, STA 434 to 654+22; S-8L, STA 654+22 to 654+110. See additional PASS) entries for SSI # 53-30-I04B. 40,000 Cycles (300F, 400E) 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. 53-10-I07C Skin Longitudinal Lap Splices - Upper Row - Bilge and Lower Lobe, Sections 41, 43 100 ALL Type 2 53-30-I04C and 46 <2> 50,000 Cycles 53-60-I05C Not applicable to 300BCF and 200SF, S-37R, STA 368 to 434. No inspection required (200, 200SF, 300BCF, 300 at these locations. PASS) 40,000 Cycles (300F, 400E) 53-10-I07D Skin Longitudinal Lap Splices - Lower Row - Bilge and Lower Lobe, Sections 41, 43 100 ALL Type 2 53-30-I04D and 46 <2> 50,000 Cycles 53-60-I05D Inspection requirements are altered for the following locations: (200, 200SF, 300BCF, 300 1) 300BCF: STA 434 to 654+110, S-26L. See additional entry for SSI # 53-30-I04D PASS) BCF1. 40,000 Cycles (300F, 400E) 2) 200SF: STA 434 to 676, S-26L. See additional entry for BCF1 SSI # 53-30-I04D. 53-10-I08B Frames - Above S-20 220, 230 ALL Except 200SF, Type 2 53-30-I24B For 200 Pass: From BS 246 to BS 786, S-20L to S-20R 300BCF 50,000 Cycles (200, 300 PASS) For 300 Pass: From BS 246 to BS 654, S-20L to S-20R 40,000 Cycles (300F, 400E) For 300F and 400E: From BS 246 to BS 434, S-20L to S-20R 53-10-I08B BCF3 Frames - Above S-20 220, 230 200SF, 300BCF Type 2 BS 246 to BS 412 50,000 Cycles (200SF, 300BCF)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-10-I08C Frames - S-20 and Below 100 ALL Except Type 2 53-30-I24C BS 246 to BS 786 and BS 1065 to BS 1582 200SF, 300BCF 50,000 Cycles (200, 300 PASS) 53-60-I08C 40,000 Cycles (300F, 400E) 53-10-I08C BCF5 Frames - S-20 and Below 100 200SF, 300BCF Type 2 53-30-I24C BS 246 to BS 786 and BS 1065 to BS 1582 50,000 Cycles (200SF, 300BCF) 53-60-I08C For additional inspections required at locations with partially visible frame structure, see entry for BCF6 SSI # 53-30-I24C / 53-60-I08C. 53-10-I10A Forward Passenger Entry/Service Door Cutout- Edge Frame - Inner Chord 119, 221, 222, ALL Type 2 Door STA 76.3, S-7 to S-12 and S-19 to S-23 223, 224 50,000 Cycles Door STA 123.7, S-8 to S-12 and S-19 to S-23 (200, 300 PASS) 40,000 Cycles (200SF, 300BCF, 300F, 400E) 53-10-I10B Forward Passenger Entry/Service Door Cutout- Upper Main Sill - Inner Chord 221, 222 ALL Type 2 BS 287 to Door STA 89 50,000 Cycles (200, 300 PASS) 40,000 Cycles (200SF, 300BCF, 300F, 400E) 53-10-I12 Main Equipment Center Access Door Cutout 119 ALL Type 2 BS 303 - BS 325, LBL 13.1 - RBL 13.1 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-10-I13 Forward Equipment Bay Access Door Cutout - BS 144.5 - BS 163.2. LBL 9 - RBL 9 113, 114 ALL Type 2 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-10-I14A Window #1 Cutout Structure - AB POST 211, 212 ALL Type 1 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-10-I14B Window #1 Cutout Structure - BD SILL 211, 212 ALL Type 1 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-10-I16 Window #2 Cutout Structure - EF POST 211, 212 ALL Type 1 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-10-I18A Nose Landing Gear Wheel Well - Canted Bulkhead Details - Outer Chord Typical 113, 114 ALL Type 1 Locations Between S-32L & S-32R 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-10-I18B Nose Landing Gear Wheel Well - Canted Bulkhead Details - Outer Chord Hidden 113, 114 ALL Type 1 Locations L/RBL 10.60 & L/RBL 25.00 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-10-I20A Nose Landing Gear Wheel Well - BL25 Side Panel Details - Vertical Beams & Panel 117, 118 ALL Type 1 Web from BS 180.5 to BS 276 50,000 Cycles (200, 300 PASS) 40,000 Cycles (200SF, 300BCF, 300F, 400E) 53-10-I20B Nose Landing Gear Wheel Well - Trunnion Support Fitting at Top Panel Beam 117, 118 ALL Type 1 Attachment. BS 276, BL 30, WL 181 to WL 187 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-10-I20C Nose Landing Gear Wheel Well - Trunnion Support Fitting at Strap Attachment BS 276, 117, 118 ALL Type 1 BL 30, WL 165 to WL 169 <2> 50,000 Cycles (200, 300 PASS) 40,000 Cycles (200SF, 300BCF, 300F, 400E) 53-10-I21A Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - WL 159 Beam & Bulkhead 119 ALL Type 1 Web from LBL 27 to LBL 23, LBL 10.0 to RBL 10.0, RBL 23 to RBL 27 L/N 1-757 50,000 Cycles Applicable to 767 Line Numbers 1 - 757. <2> (200, 300 PASS) For Line Numbers 758 and on: See additional entries for SSI # 53-10-I21A and 40,000 Cycles 53-10-I21E. (200SF, 300BCF, 300F) 53-10-I21A Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - WL 159 Beam & Bulkhead 119 ALL Type 1 Web from LBL 10.0 to RBL 10.0 L/N 758 and on 50,000 Cycles (200, 300 PASS) Applicable to 767 Line Numbers 758 and on. <2> 40,000 Cycles (300F, 400E) For Line Numbers 1-757: See additional entry for SSI # 53-10-I21A. 53-10-I21B Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - Outer Chord Typical 119 ALL Type 1 Locations between S-24L and S-24R 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-10-I21C Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - Outer Chord - Stringer 119 ALL Type 1 Splices between S-24L and S-24R 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-10-I21D Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - Outer Chord Hidden 119 ALL Type 1 Locations at S-36L, S-36R and S-27R 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-10-I21E Nose Landing Gear Wheel Well - BS 287 Bulkhead Details - WL 159 Beam and 119 ALL Type 1 Bulkhead Web LBL 27 to LBL 23 and RBL 23 to RBL 27 L/N 758 and on 50,000 Cycles (200, 300 PASS) Applicable to 767 Line Numbers 758 and on. 40,000 Cycles (300F, 400E) For Line Numbers 1-757: See entry for SSI # 53-10-I21A. 53-10-I32A T.C.A.S. Antenna Cutout Doubler 223, 224 ALL Type 2 BS 368 to BS 390, S-1L to S-1R 50,000 Cycles (200, 200SF, 300 Note: Only applicable to aircraft configured at delivery with the subject structure. PASS, 300BCF) 40,000 Cycles (300F, 400E) 53-10-I32B T.C.A.S. Antenna Cutout Doubler 123, 124 ALL Type 2 BS 390 to BS 412, S-39L to S-39R Except 300F 50,000 Cycles (200, 200SF, 300 Note: Only applicable to aircraft configured at delivery with the subject structure. PASS, 300BCF) Not applicable to 767-200SF or 767-300BCF airplanes with external service panel 40,000 Cycles (400E) doubler installed between BS 368 and BS 434. 53-10-I33B BCF2 - Section 41 External Skin Doubler first fastener common to skin and doubler 121 200SF, 300BCF Type 2 between BS 368 and BS 434 at S-38L <4> 50,000 Cycles

53-10-I33E BCF5 - Section 41 Service Panel Cutout Structure BS 390 to BS 412; BL 0 to 121 200SF, 300BCF Type 2 RBL 13.65 <4> 48,300 Cycles (200SF) Mod Date Sensitive (300BCF)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-10-I34 Pressurized Door Cutouts 122, 124, 154, ALL Type 2 53-30-I29 Forward and aft lower corners of door cutouts 156, 161, 163, 50,000 Cycles (200, 200SF, 300 53-60-I31 Applicable to Forward Passenger Entry/Service Doors, Mid Passenger Entry/Service 221, 222, 231, PASS, 300BCF) Doors, Aft Passenger Entry/Service Doors, Bulk Cargo Door, Forward Main Cargo 232, 251, 252 40,000 Cycles (300F, 400E) Door, Aft Main Cargo Door, Forward Large Cargo Door, Aft Large Cargo Door, and Main Deck Cargo Door 53-30-I01 Fuselage Crown Stringers - BS 654 to BS 1395, S-8L to S-8R 230, 240, 250 ALL Type 2 53-50-I01 Not applicable to: Except where noted 50,000 Cycles 53-60-I01 1) 200SF: from BS 676 to 786 at stringers S-2R and S-3R, from BS 742 to 786 at for (200, 200SF, 300BCF, stringers S-1R to S-5L. See additional entry for SSI # 53-30-I01, SF10. 200SF and 300BCF 300 PASS) 2) 300BCF: from BS 654+110 to 786 at stringers S-4L to S-4R. See additional entry for 40,000 Cycles SSI # 53-30-I01, BCF10. (300F, 400E) 53-30-I01 BCF1 - Crown Doubler, BS 654+28 to 654+115, S-6L to S-8L and S-6R to S-8R 231, 232 300BCF Type 2 <4> 50,000 Cycles

53-30-I01 BCF2 - Crown Doubler Aft Edge Circumferential Crack - BS 654+115, S-7L to S-7R 231, 232 300BCF Type 1 <4> Combined Threshold

53-30-I01 BCF3 - Circumferential Splice - Upper Crown - BS 654+22 233, 234 300BCF Type 2 <4> 50,000 Cycles 53-30-I01 BCF5 - Crown Skin Doubler - Longitudinal Crack in Skin at forward corners - 231, 232 300BCF Type 2 BS 654+22, S-8L and S-8R <4> 50,000 Cycles 53-30-I01 BCF9 - Fuselage Crown Skin - BS 654+115 to 786, S-4L to 4R 231, 232 300BCF Type 2 50,000 Cycles 53-30-I01 BCF10 - Fuselage Crown Stringers - BS 654+110 to 786, S-4L to 4R 230 300BCF Type 2 Combined Threshold

53-30-I01 SF1 - Crown Skin Doubler - RHS Edge of Crown Skin Doubler at RBL 9 233, 234 200SF Type 2 <4> 50,000 Cycles

53-30-I01 SF2 - Crown Skin Doubler - Aft Edge BS 742 233, 234 200SF Type 2 <4> 30,000 Cycles

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-30-I01 SF3 - Crown Skin Doubler - Stringer at Circumferential Splice 233, 234 200SF Type 2 50,000 Cycles

53-30-I01 SF5 - Crown Skin Doubler - At BS 676 Skin Splice, at S-8L and S-2R 233, 234 200SF Type 2 <4> 50,000 Cycles

53-30-I01 SF6 - Crown Skin Doubler - At VHF Comm. Antenna Installation at BL 0.0, BS 698 to 233, 234 200SF Type 2 720 50,000 Cycles

53-30-I01 SF9 - Section 43 Crown Skin - Aft of External Doubler 233, 234 200SF Type 2 <4> 37,500 Cycles

53-30-I01 SF10 - Section 43 Crown Stringers - Aft of External Doubler 233, 234 200SF Type 2 <4> 25,000 Cycles

53-30-I04A Skin Longitudinal Lap Splices - Upper Row - Crown and Upper Lobe, Section 43 230 300BCF Type 2 Applicable to S-8R, STA 434 to 654 + 22. Mod Date Sensitive (300BCF)

53-30-I04A BCF2 Skin Longitudinal Lap Splices - Upper Row - Upper Lobe 230 300BCF Type 2 Applicable to S-8L, STA 654 + 22 to 654 + 110. Combined Threshold

53-30-I04B Skin Longitudinal Lap Splices - Lower Row - Crown and Upper Lobe, Section 43 230 300BCF Type 2 Applicable to S-8L, STA 654 + 22 to 654 + 110. Mod Date Sensitive

53-30-I04B Skin Longitudinal Lap Splices - Lower Row - Crown and Upper Lobe, Section 43 230 200SF, 300BCF Type 2 200SF: Applicable to S-8R, STA 434 to 676. 30,700 Cycles (200SF) 300BCF: Applicable to S-8R, STA 434 to 654+22. Combined Threshold (300BCF) 53-30-I04D BCF1 - Skin Longitudinal Lap Splices - Lower Row - Bilge S-26L MDCD and 100 200SF Type 2 L2 Panel 300BCF 27,900 Cycles (200SF) 200SF: Applicable to S-26L, STA 434 to 676. <4> Combined Threshold (300BCF) 300BCF: Applicable to S-26L, STA 434 to 654+110. 53-30-I05 Circumferential Splice in the Body Crown 240 200SF Type 2 Applicable to BS 786 S-7L to S-7R. 50,000 Cycles

D622T001-9-01 JUN 2019 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-44 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-30-I05 Fuselage Circumferential Splices in the Body Crown 230, 240, 250 200 Type 1 53-30-I21 50,000 Cycles 53-30-I27 53-50-I03 53-60-I03 53-60-I26 53-30-I05 Fuselage Circumferential Splices in the Body Crown 230, 240, 250 300BCF, 300 PASS, Type 1 53-30-I21 Note: For 767-300BCF, STA 654+22, see additional entry for SSI # 53-30-I27 50,000 Cycles 53-30-I27 53-50-I03 53-60-I03 53-60-I26 53-30-I05 Fuselage Circumferential Splices in the Body Crown 230, 240, 250 300F Type 1 53-30-I21 Not applicable to 767-300F Line Numbers 1070 and on, BS 786 and BS 1065. See Except as noted 40,000 Cycles 53-30-I27 additional entries for SSI # 53-30-I05A / 53-50-I03A and 53-30-I05B / 53-50-I03B 53-50-I03 53-60-I03 53-60-I26 53-30-I05 Fuselage Circumferential Splices in the Body Crown 230, 240, 250 400E Type 1 53-30-I08 40,000 Cycles 53-30-I21 53-50-I03 53-60-I03 53-60-I04 53-60-I24 53-60-I33 53-30-I05A Fuselage Circumferential Splices In the Body Crown - BS 1065 and BS 785.9, S-4L/R 230, 240, 250 300F Type 1 53-50-I03A to S-5L/R L/N 1070 and on 40,000 Cycles <3> 53-30-I05B Fuselage Circumferential Splices In the Body Crown - BS 1065 and BS 785.9, S-13L to 230, 240, 250 300F Type 1 53-50-I03B S-13R L/N 1070 and on 40,000 Cycles

53-30-I08A Fuselage Circumferential Skin and Stringer Splice - BS 434 120, 220, 230 300F Type 1 L/N 1108 and on 40,000 Cycle

D622T001-9-01 JUL 2018 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-45 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-30-I14A Forward Main Cargo Door Cutout - Edge Frames - Frames at BS 539.5 & 615.5 122, 124, 232 200 Type 2 Stringers S-17R to S-21R and S-28R to S-36R 300 PASS 50,000 Cycles

53-30-I14A Forward Main Cargo Door Cutout - Edge Frames - Frames at BS 539.5 & 615.5 122, 124, 232 200SF Type 2 Stringers S-17R to S-36R 50,000 Cycles

53-30-I15 Front Spar Bulkhead Body Station 786 - Hidden Details Under Seal Pan at S-23L/R, 120 300F Type 1 S-24L/R, and S-27L/R L/N 1070 and on 40,000 Cycles DTR Check Form applicable to: <3> L/N 1070 and on. 53-30-I19A Forward Large Cargo Door Cutout - Edge Frame Inner Chord 122 200 Type 2 BS 478, S-23R to S-28R and BS 618, S-27R to S-28R and S-29R to S-30R 300 PASS 50,000 Cycles <2> 53-30-I19B Forward Large Cargo Door Cutout - Edge Frame Inner Chord 122 200 Type 2 BS 478, S-26R to S-27R and BS 618, S-29R to S-30R 300 PASS 50,000 Cycles

53-30-I19C Forward Large Cargo Door Cutout - Edge Frame Inner Chord 122 200 Type 2 BS 618, S-28R to S-29R 300 PASS 50,000 Cycles

53-30-I19D Forward Large Cargo Door Cutout - Upper Main Sill - Inner Cord 122, 124 200 Type 2 BS 456 to BS 478 and BS 482 to BS 493 300 PASS 50,000 Cycles <2> 53-30-I19E Forward Large Cargo Door Cutout - Upper Main Sill - Inner Cord 122 200 Type 2 BS 478 - BS 479.5 300 PASS 50,000 Cycles <2> 53-30-I19F Forward Large Cargo Door Cutout - Upper Main Sill - Inner Cord 122 200 Type 2 BS 479.5 to BS 482 300 PASS 50,000 Cycles <2> 53-30-I19G Forward Large Cargo Door Cutout - Upper Main Sill - Inner Cord 122 200 Type 2 BS 482 to BS 493 300 PASS 50,000 Cycles

53-30-I19AB Forward Large Cargo Door Cutout - Edge Frame Inner Chord 122 300BCF Type 2 BS 478, S-20R to S-22R and BS 618, S-20R to S-22R 300F 40,000 Cycles 400E

D622T001-9-01 JUN 2019 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-46 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-30-I19AC Forward Large Cargo Door Cutout - Edge Frame Inner Chord 122, 232 300BCF Type 2 BS 478, S-17R to S-20R and S-22R to S-23R 300F 40,000 Cycles 400E 53-30-I19AD Forward Large Cargo Door Cutout - Upper Main Sill - Inner Chord 122 ALL Type 2 BS 607 to BS 618 <2> 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300BCF, 300F, 400E) 53-30-I19AD1 Forward Large Cargo Door Cutout - Upper Main Sill - Inner Chord Covered Locations 122 ALL Type 2 BS 607 to BS 618 <2> 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300BCF, 300F, 400E) 53-30-I19AF Forward Large Cargo Door Cutout - Lower Main Sill Inner Chord Covered Locations 124 ALL Type 2 BS 466 to BS 483 and BS 614 to BS 625 <2> 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300BCF, 300F, 400E) 53-30-I19AF1 Forward Large Cargo Door Cutout - Lower Main Sill Inner Chord 124 ALL Type 2 BS 466 to BS 483 and BS 614 to BS 625 <2> 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300BCF, 300F, 400E) 53-30-I20A Forward Large Cargo Door Cutout - Lower Latch Backup Structure - Latch Support 124 ALL Type 2 Fitting at BS 487.7 & BS 608.3 <2> 50,000 Cycles (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-30-I22C Mid Passenger Entry/Service Door Cutout - Edge Frame - Inner Chord - BS 654+44, 230 300 PASS Type 2 S-8 to S-15 and BS 654+91.4, S-8 to S-20 400E 50,000 Cycles (300 PASS) 40,000 Cycles (400E) 53-30-I22D Mid Passenger Entry/Service Door Cutout - Upper Main Sill Inner Chord - BS 654+33 230 300 PASS Type 2 to BS 654+110 <2> 50,000 Cycles

53-30-I22D Mid Passenger Entry/Service Door Cutout - Upper Main Sill Inner Chord - BS 654+33 230 400E Type 2 to BS 654+110 <2> 40,000 Cycles

D622T001-9-01 JUN 2019 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-47 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-30-I24A Frames - Above S-20 230, 240, 250 ALL Except 200SF, Type 2 53-50-I01A For 200 PASS: From BS 786 to BS 1582, S-20L to S-20R. 300BCF 50,000 Cycles (200, 300 PASS) 53-50-I02A For 300 PASS: From BS 654 to BS 1582, S-20L to S-20R. 40,000 Cycles (300F, 400E) 53-60-I08A For 300F and 400E: From BS 434 to BS 1582, S-20L to S20R. 53-30-I24A Frames - (Partially Visible) - Above S-20 230, 240, 250 200SF Type 2 53-30-I24B BS 434 to BS 786 and BS 1065 to BS 1582 <4> 50,000 Cycles 53-60-I08A For additional frame inspection requirements, see entry for 200SF SSI # 53-30-I24A / 53-30-I24B / 53-50-I01A / 53-50-I02A / 53-60-I08A. 53-30-I24A BCF1 Frames - Above S-20 231, 232 300BCF Type 2 53-30-I24B BS 434 to BS 1582 50,000 Cycles 53-50-I01A For additional inspections required at locations with partially visible frame structure, see 53-50-I02A entry for BCF2 SSI # 53-30-I24A / 53-30-I24B. 53-60-I08A 53-30-I24A Frames - Above S-20 230, 240, 250 200SF Type 2 53-30-I24B BS 434 to BS 1582 50,000 Cycles 53-50-I01A For additional inspections required at locations with partially visible frame structure, see 53-50-I02A entry for 200SF SSI # 53-30-I24A / 53-30-I24B / 53-60-I08A. 53-60-I08A 53-30-I24A BCF2, BCF4 Frames - (Partially Visible) - Above S-20 231, 232 300BCF Type 2 53-30-I24B BS 434 to BS 786 <4> 50,000 Cycles For additional frame inspection requirements, see entry for BCF1 SSI # 53-30-I24A / 53-30-I24B / 53-50-I01A / 53-50-I02A / 53-60-I08A. 53-30-I24C BCF6 Frames - (Partially Visible) - S-20 and Below 100 200SF Type 2 53-60-I08C BS 434 to BS 786 and BS 1065 to BS 1582 300BCF 50,000 Cycles (200SF, 300BCF) For additional frame inspection requirements, see entry for BCF5 SSI # 53-10-I08C / <4> 53-30-I24C / 53-60-I08C. 53-30-I27 BCF2 Fuselage Circumferential Splice in the Body Crown - BS 654+22, S-8L to S-8R 231, 232 300BCF Type 2 50,000 Cycles

53-30-I27A Fuselage Circumferential Splices in the Body Crown 230, 240, 250 200SF Type 1 53-50-I03 Applicable to: <4> 50,000 Cycles 53-60-I03 1) BS 676: S-4L TO S-4R 2) BS 1065: S-9L TO S-9R 3) BS 1395: S-8L TO S-8R

D622T001-9-01 JUL 2018 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-48 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-30-I28 BCF1 - Main Deck Cargo Door Cutout - Upper Auxiliary Sill Inner Chord 231 300BCF Type 2 <4> 50,000 Cycles 53-30-I28 SF1 - Main Deck Cargo Door Cutout - Upper Auxiliary Sill Inner Chord 231 200SF Type 2 <4> 50,000 Cycles

53-30-I28A Main Deck Cargo Door Cutout - Upper Main Sill Inner Chord - BS 478 to BS 500, 231 200SF Type 2 BS 505 to BS 514, and BS 599 to BS 610 300BCF, 300F 50,000 Cycles (200SF) <3>,<4> Mod Date Sensitive (300BCF) 40,000 Cycles (300F) 53-30-I28B Main Deck Cargo Door Cutout - Lower Main Sill Inner Chord between BS 626 and 231 200SF Type 2 BS 643 300BCF, 300F 50,000 Cycles (200SF) <3>,<4> Mod Date Sensitive (300BCF) 40,000 Cycles (300F) 53-30-I28C Main Deck Cargo Door Cutout - Forward Edge Frame Inner Chord between S-4L and 233 200SF Type 2 S-7L 300BCF, 300F 50,000 Cycles (200SF) <3>,<4> Mod Date Sensitive (300BCF) 40,000 Cycles (300F) 53-30-I28D Main Deck Cargo Door Cutout - Aft Edge Frame Inner Chord - BS 632 at Frame Splice 231 200SF Type 2 centered between S-15L and S-16L 300BCF, 300F 50,000 Cycles (200SF) <3>,<4> Mod Date Sensitive (300BCF) 40,000 Cycles (300F) 53-30-I28E Main Deck Cargo Door Cutout - Aft Edge Frame Inner Chord - BS 632 - S-1L to S-3L 231, 233 200SF Type 2 and S-14L to S-17L 300BCF, 300F 50,000 Cycles (200SF) <3>,<4> 40,000 Cycles (300F) Mod Date Sensitive (300BCF) 53-30-I28F Main Deck Cargo Door Cutout - Upper and Lower Main Sill Outer Chord - BS 496 and 231, 233 200SF Type 2 628 300BCF, 300F 50,000 Cycles (200SF) <3>,<4> Mod Date Sensitive (300BCF) 40,000 Cycles (300F) 53-50-I06 SF - Single Emergency Exit Cutout Auxiliary Sill Inner Chord 241, 242 200SF Type 2 <4> 50,000 Cycles

53-50-I06A Single Emergency Exit Cutout - Edge Frame Inner Chord 241, 242 200 Type 2 50,000 Cycles

D622T001-9-01 JUL 2018 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-49 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-50-I06A SF - Single Emergency Exit Cutout - Edge Frame Inner Chord 241, 242 200SF Type 2 50,000 Cycles

53-50-I06B Single Emergency Exit Cutout - Frame Inner Chord at Sill Intersect 241, 242 200 Type 2 50,000 Cycles

53-50-I06B SF - Single Emergency Exit Cutout - Frame Inner Chord at Sill Intersect 241, 242 200SF Type 2 50,000 Cycles

53-50-I06C Single Emergency Exit Cutout - Sill Inner Chord 241, 242 200 Type 2 50,000 Cycles

53-50-I06C SF - Single Emergency Exit Cutout - Sill Inner Chord 241, 242 200SF Type 2 50,000 Cycles

53-50-I06D Single Emergency Exit Cutout - Sill Inner Chord at Frame Intersect 241, 242 200 Type 2 50,000 Cycles

53-50-I06D SF - Single Emergency Exit Cutout - Sill Inner Chord at Frame Intersect 241, 242 200SF Type 2 50,000 Cycles

53-50-I06E Single Emergency Exit Cutout - Sill Outer Chord 241, 242 200 Type 2 50,000 Cycles

53-50-I06E SF - Single Emergency Exit Cutout - Sill Outer Chord 241, 242 200SF Type 2 50,000 Cycles

53-50-I06F Single Emergency Exit Cutout - Sill Outer Chord at Frame Intersect 241, 242 200 Type 2 50,000 Cycles

53-50-I06F SF - Single Emergency Exit Cutout - Sill Outer Chord at Frame Intersect 241, 242 200SF Type 2 50,000 Cycles

53-50-I11 BS 1043 Frame Splice with the Landing Gear Fitting - BS 1043, BL 92, WL 193 to 141, 142 ALL Type 2 WL 199 50,000 Cycles (200, 200SF, 300 PASS) 40,000 Cycles (300BCF, 300F, 400E)

D622T001-9-01 JUL 2018 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-50 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-50-I13B Fuselage Rear Spar Bulkhead - Side Frame Fitting Inner Chord - BS 955, S-20 to S-21 131, 132 ALL Type 1 at Seat Track Support Bracket 25,000 Cycles

53-50-I13C Fuselage Rear Spar Bulkhead - Side Frame Fitting Inner Chord Flange - BS 955, S-18 241, 242 ALL Type 2 to S-20 <2> 50,000 Cycles (200, 200SF, 300 PASS) 40,000 Cycles (300BCF, 300F, 400E) 53-50-I14A Aft Wheel Well Bulkhead BS 1065 - BL 26 Vertical Beam Intercostal Upper Chord 151, 152 ALL Type 2 Splice 50,000 Cycles (200, 200SF, 300 PASS) 40,000 Cycles (300BCF, 300F, 400E) 53-50-I14B Aft Wheel Well Bulkhead BS 1065 - Hidden Details at Outer Chord Splices S-27 to S-28 151, 152 ALL Type 1 and S-35 to S-36 <2> 50,000 Cycles (200, 200SF, 300 PASS) 40,000 Cycles (300BCF, 300F, 400E) 53-50-I14C Aft Wheel Well Bulkhead BS 1065 - Hidden Details at Outer Chord between S-29 & 151, 152 ALL Type 1 S-34 Except 767-300F 25,000 Cycles Applicable to all 767 except for 767-300F Line Numbers 1070 and on. L/N 1070 and on For 767-300F Line Numbers 1070 and on: See additional entry for SSI # 53-30-I04C. 53-50-I14C Aft Wheel Well Bulkhead BS 1065 - Lower Lobe Outer Chord between S-29 and S-34 151, 152 767-300F Type 1 L/N 1070 and on 25,000 Cycles 53-50-I18 Section 45 Stub Frames - BS 808 - 933 Frame Inner Chord at Stub Beam 131, 132 200, 200SF Type 2 53-50-I24 300BCF, 300F, 50,000 Cycles 53-50-I28 300 PASS (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F) 53-50-I19 Main Landing Gear Wheel Well - BS 1021 Transverse Floor Beam Lower Chord - 143, 144 PASS Type 2 LBL 33 to LBL 60 and RBL 33 to RBL 60 50,000 Cycles (200, 300 PASS) 40,000 Cycles (400E)

D622T001-9-01 JUL 2018 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-51 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-50-I22A Dual Emergency Exit Cutout - Edge Frame Inner Chords 241, 242 200 Type 2 300 PASS 50,000 Cycles

53-50-I22A BCF - Dual Emergency Exit Cutout - Edge Frame Inner Chords 241, 242 300BCF Type 2 50,000 Cycles

53-50-I22B Dual Emergency Exit Cutout - Frame Inner Chord at Sill Intersect 241, 242 200 Type 2 300 PASS 50,000 Cycles

53-50-I22B BCF - Dual Emergency Exit Cutout - Frame Inner Chord at Sill Intersect 241, 242 300BCF Type 2 50,000 Cycles

53-50-I22C BCF - Dual Emergency Exit Cutout - Sill Inner Chord 241, 242 300BCF Type 2 50,000 Cycles 53-50-I22D BCF - Dual Emergency Exit Cutout - Sill Inner Chord at Frame Intersect 241, 242 300BCF Type 2 50,000 Cycles

53-50-I22E BCF - Dual Emergency Exit Cutout - Upper Sill Inner Chord - BS 859.5 and BS 903.5 241, 242 300BCF Type 2 50,000 Cycles

53-50-I22F BCF - Dual Emergency Exit Cutout - Sill Outer Chord 241, 242 300BCF Type 2 50,000 Cycles 53-50-I22G BCF - Dual Emergency Exit Cutout - Sill Outer Chord at Frame Intersect 241, 242 300BCF Type 2 50,000 Cycles 53-50-I22 BCF1 Dual Overwing Emergency Exit Auxiliary Sill Inner Chord at Frame Intersect 241, 242 300BCF Type 2 <4> 50,000 Cycles

53-50-I22 BCF2 Dual Overwing Emergency Exit Auxiliary Sill Inner Chord 241, 242 300BCF Type 2 BS 830 to BS 955 <4> 50,000 Cycles

53-50-I22C Dual Emergency Exit Cutout - Sill Inner Chord 241, 242 200 Type 2 300 PASS 50,000 Cycles

53-50-I22D Dual Emergency Exit Cutout - Sill Inner Chord at Frame Intersect 241, 242 200 Type 2 300 PASS 50,000 Cycles

53-50-I22E Dual Emergency Exit Cutout - Upper Sill Inner Chord - BS 859.5 and BS 903.5 241, 242 300 PASS Type 2 50,000 Cycles

D622T001-9-01 JUL 2018 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-52 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-50-I22F Dual Emergency Exit Cutout - Sill Outer Chord 241, 242 200 Type 2 300 PASS 50,000 Cycles

53-50-I22G Dual Emergency Exit Cutout - Sill Outer Chord at Frame Intersect 241, 242 200 Type 2 300 PASS 50,000 Cycles

53-50-I25A Single Aft Emergency Exit Cutout - Edge Frame Inner Chord 241, 242 300 PASS Type 2 50,000 Cycles

53-50-I25B Single Aft Emergency Exit Cutout - Frame Inner Chord at Sill Intersect 241, 242 300 PASS Type 2 50,000 Cycles

53-50-I25C Single Aft Emergency Exit Cutout - Sill Inner Chord 241, 242 300 PASS Type 2 50,000 Cycles

53-50-I25D Single Aft Emergency Exit Cutout - Sill Inner Chord at Frame Intersect 241, 242 300 PASS Type 2 50,000 Cycles

53-50-I25E Single Aft Emergency Exit Cutout - Upper Sill Inner Chord - BS 903.5 241, 242 300 PASS Type 2 50,000 Cycles

53-50-I25F Single Aft Emergency Exit Cutout - Sill Outer Chord 241, 242 300 PASS Type 2 50,000 Cycles

53-50-I25G Single Aft Emergency Exit Cutout - Sill Outer Chord at Frame Intersect 241, 242 300 PASS Type 2 50,000 Cycles

53-50-I28 Section 45 Stub Frames - BS 808 - 933 Frame Inner Chord at Stub Beam 131, 132 400E Type 2 40,000 Cycles

53-50-I29A SATCOM Antenna Installation 243, 244 ALL Type 2 BS 977 to BS 1043, S-1.5L to S-1.5R 30,000 Cycles Note: Only applicable to aircraft configured at delivery with the subject structure. 53-50-I29B SATCOM Antenna Installation - External Skin Doubler 243, 244 300 PASS Type 2 BS 1004 to BS 1043, S-1.5L to S-1.5R 25,000 Cycles Note: Only applicable to aircraft configured at delivery with the subject structure. 53-60-I02 BCF - Fuselage Stringer with Stringer Reinforcement Strap STA 1076 to 1143 153, 154 300BCF Type 2 S-10R to S-13R and S-9L to S-13L 40,000 Cycles

D622T001-9-01 JUN 2019 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-53 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-60-I06B Aft Main Cargo Door Cutout - Edge Frames - Inner Chord at BS 1270 and BS 1346 154 300BCF Type 2 PASS 50,000 Cycles (200, 300 PASS) <2> 40,000 Cycles (300BCF, 400E) 53-60-I06B Aft Main Cargo Door Cutout - Edge Frames - Inner Chord at BS 1270 and BS 1346 154 200SF Type 2 <4> 50,000 Cycles

53-60-I06C BCF Aft Main Cargo Door Cutout - Edge Frame - Outer Chord 154 300BCF Type 2 BS 1270 and BS 1346 between Upper and Lower Sills 50,000 Cycles 53-60-I06C Forward/Aft Main Cargo Door Cutout - Edge Frame - Outer Chord 122, 154 PASS Type 2 53-30-I14C BS 539.5, BS 615, BS 1270, and BS 1346 between Upper and Lower Sills 50,000 Cycles (200, 300 PASS) 40,000 Cycles (400E) 53-30-I14C Forward Main Cargo Door Cutout - Edge Frame - Outer Chord 122 200SF Type 2 BS 539.5 and BS 615 between Upper and Lower Sills 40,000 Cycles

53-60-I06C Aft Main Cargo Door Cutout - Edge Frame - Outer Chord 154 200SF Type 2 BS 1270 and BS 1346 between Upper and Lower Sills 40,000 Cycles

53-60-I06D Forward/Aft Main Cargo Door Cutout - Upper Main Sill - Inner Chord 122, 154 300BCF Type 2 53-30-I14D BS 522 to BS 544 and BS 1346 to BS 1395 PASS 50,000 Cycles <2> (200, 300BCF, 300 PASS) 40,000 Cycles (400E) 53-30-I14D Forward Main Cargo Door Cutout - Upper Main Sill - Inner Chord 122 200SF Type 2 BS 522 to BS 544 <4> 40,000 Cycles

53-60-I06D Aft Main Cargo Door Cutout - Upper Main Sill - Inner Chord 154 200SF Type 2 BS 1346 to BS 1395 <4> 40,000 Cycles

53-60-I06E Forward/Aft Main Cargo Door Cutout - Lower Main Sill - Inner Chord 122, 154 200SF Type 2 53-30-I14E BS 610 to BS 632 and BS 1263 to BS 1270 PASS 50,000 Cycles <2> (200, 200SF, 300 PASS) 40,000 Cycles (400E) 53-60-I06E BCF1 - Aft Main Cargo Door Cutout - Lower Main Sill - Inner Chord 154 300BCF Type 2 BS 1263 to STA 1270 <4> 50,000 Cycles

D622T001-9-01 JUN 2019 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-54 EXPORT CONTROLLED - EAR ECCN: 9E991 767-200/300/300F/400ER AIRWORTHINESS LIMITATIONS

AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-60-I10 BCF2 - Bulk Cargo Door Cutout - Aft Edge Frame BS 1461 Inner Chord 161, 163 300BCF Type 2 S-22L to S-22.5L 50,000 Cycles

53-60-I10 SF2 - Bulk Cargo Door Cutout - Aft Edge Frame BS 1461 Inner Chord 161, 163 200SF Type 2 S-20L to S-22.5L 50,000 Cycles

53-60-I10A Bulk Cargo Door Cutout - Edge Frames Inner Chord 161, 163 ALL Type 2 200SF and 300BCF: See entries for SSI # 53-60-I10 for additional inspections at 50,000 Cycles BS 1461, S-22L to S-22.5L (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-60-I10B Bulk Cargo Door Cutout - Frame Splice - Aft Edge Frame, BS 1461 Inner Chord at S-26 161 ALL Type 2 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-60-I10C Bulk Cargo Door Cutout - Upper Main Sill Inner Chord - BS 1458 to BS 1464 161 300F Type 2 40,000 Cycles

53-60-I14E Aft Passenger Entry/Service Door Cutout - Edge Frames - Inner Chord 251, 252 200SF Type 2 300BCF 50,000 Cycles PASS (200, 200SF, 300 PASS) 40,000 Cycles (300BCF, 400E) 53-60-I14F Aft Passenger Entry/Service Door Cutout - Upper Main Sill - Inner Chord 251, 252 200SF Type 2 Door Sta. 911 to BS 1562 300BCF 50,000 Cycles PASS (200, 200SF, 300 PASS) <2> 40,000 Cycles (300BCF, 400E) 53-60-I27A Type I Emergency Exit Door Cutout - Edge Frame - Inner Chord - BS 1153 and 153, 154, 300 PASS Type 2 BS 1183.4, S-8 to S-13 & S-16 to S-23 251, 252 <2> 50,000 Cycles

53-60-I27A Type I Emergency Exit Door Cutout - Edge Frame - Inner Chord - BS 1153 and 153, 154, 400E Type 2 BS 1183.4, S-8 to S-13 & S-16 to S-23 251, 252 <2> 40,000 Cycles

53-60-I27B Type I Emergency Exit Door Cutout - Upper Main Sill - Inner Chord, BS 1131 to 251, 252 300 PASS Type 2 BS 1197+22 400E 50,000 Cycles (300 PASS) 40,000 Cycles (400E)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-60-I27C Type I Emergency Exit Door Cutout - Lower Main Sill - Inner Chord, BS 1131 to 251, 252 300 PASS Type 2 BS 1175 400E 50,000 Cycles (300 PASS) 40,000 Cycles (400E) 53-60-I29A Aft Large Cargo Door Cutout - Edge Frame - Inner Chord, BS 1344 154 300F Type 2 Between S-24R and S-26R <3> 40,000 Cycles

53-60-I29B Aft Large Cargo Door Cutout - Edge Frame - Inner Chord, BS 1344 154 300F Type 2 Between S-24R and S-26R <3> 40,000 Cycles

53-60-I29C Aft Large Cargo Door Cutout - Upper Main Sill - Inner Chord, BS 1219 154 300F Type 2 <3> 40,000 Cycles

53-60-I29D Aft Large Cargo Door Cutout - Lower Main Sill - Inner Chord, BS 1342 to BS 1348 154, 156 300F Type 2 <3> 40,000 Cycles

53-60-I30A Aft Large Cargo Door Cutout - Latch Backup Fitting - Latch 12 156 300F Type 2 <3> 40,000 Cycles

53-80-I01A Aft Pressure Bulkhead - Circumferential Attachment of Web to Y-Ring 165, 166, 251, ALL Type 2 For Line Numbers 1 to 423, equivalent inspections are included in Service Bulletins. 252, 253, 254 L/N 424 & on 50,000 Cycles See applicable Service Bulletins for inspection requirements. (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-80-I01B BS 1582 Pressure Bulkhead - Radial Web Lap Splices - BS 1582 (Fwd Web) 311, 312 ALL Type 2 For Line Numbers 1 to 423, equivalent inspections are included in Service Bulletins. L/N 424 & on 50,000 Cycles See applicable Service Bulletins for inspection requirements. (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-80-I01C BS 1582 Pressure Bulkhead - Radial Web Lap Splices - BS 1582 (Aft Web) 311, 312 ALL Type 2 For Line Numbers 1 to 423, equivalent inspections are included in Service Bulletins. L/N 424 & on 50,000 Cycles See applicable Service Bulletins for inspection requirements. (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-80-I01D BS 1582 Pressure Bulkhead - Circumferential Tear Strap Splices - BS 1582 311, 312 ALL Type 2 (Fwd Tear Strap) L/N 424 & on 50,000 Cycles For Line Numbers 1 to 423, equivalent inspections are included in Service Bulletins. (200, 300BCF, 300 PASS) See applicable Service Bulletins for inspection requirements. 40,000 Cycles (300F, 400E)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 53-80-I01E BS 1582 Pressure Bulkhead - Circumferential Tear Strap Splices - BS 1582 311, 312 ALL Type 2 (Aft Tear Strap) L/N 424 & on 50,000 Cycles For Line Numbers 1 to 423, equivalent inspections are included in Service Bulletins. (200, 300BCF, 300 PASS) See applicable Service Bulletins for inspection requirements. 40,000 Cycles (300F, 400E) 53-80-I03 Section 48 - Jackscrew Fitting Lug - Upper Bulkhead at BS 1702 311, 312 200SF Type 1 50,000 Cycles

53-80-I03 Section 48 - Jackscrew Fitting Lug - Upper Bulkhead at BS 1702 311, 312 300BCF, 300F Type 1 PASS 50,000 Cycles (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-80-I13 Section 48 - Pivot Fitting Lug 313, 314 200SF Type 1 38,600 Cycles

53-80-I13 Section 48 - Pivot Fitting Lug 313, 314 300BCF, 300F Type 1 PASS 50,000 Cycles (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 53-80-I15 BS 1809.5 Bulkhead Outboard Chord 313, 314 ALL Type 1 53-80-I16 For Line Numbers 1 to 709: Inspect per Service Bulletin 767-53A0078, Revision 6 or L/N 710 & on 25,000 Cycles 53-80-I17 later. 53-80-I25 Horizontal Stabilizer Fitting Hinge Pins - BS 1809, BL 41.5 313, 314 ALL Type 1 Note: For Line Numbers 1 to 98: If terminating action per Service Bulletin 767-55-0005 25,000 Cycles has been accomplished, the inspection threshold is 25,000 cycles from accomplishment of terminating action. 54-50-I01 Typical Mid Spar Chord Construction - JT9D Strut 432, 434, 436, 7R4 Type 2 Nsta 164.0 - 172.0 - 182.0 442, 444, 446 <2> 50,000 Cycles 54-50-I01 Typical Mid Spar Chord Construction - PW4000 Strut 432, 434, 436, 4000 Type 2 Nsta 172.0 - 182.0 442, 444, 446 <2> 25,000 Cycles 54-50-I01 Typical Mid Spar Chord Construction - CF6-80A Strut 432, 434, 436, 80A Type 2 NSTA 221.0 - 237.5 442, 444, 446 50,000 Cycles 54-50-I01 Typical Mid Spar Chord Construction - CF6-80C Strut 432, 434, 436, 80C (Except 400E) Type 2 NSTA 221.0 - 237.5 442, 444, 446 <2> 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300F)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 54-50-I01a Forward Mid Spar Chord - CF6-80C Strut 432, 442 80C (400E) Type 2 Frame 1 to Frame 2 - NSTA 225.25 to 237.5 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I01a Forward Mid Spar Chord - CF6-80C Strut 432, 442 80C (400E) Type 2 Frame 1 to Frame 2 - NSTA 225.25 to 237.5 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I01c Forward Mid Spar - CF6-80C Strut 432, 442 80C (400E) Type 2 Visible Portions of Bay 1 (NSTA 206 to 220.73) & Bay 3 (NSTA 228.3 to 250.16) < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I01c Forward Mid Spar - CF6-80C Strut 432, 442 80C (400E) Type 2 Visible Portions of Bay 1 (NSTA 206 to 220.73) & Bay 3 (NSTA 228.3 to 250.16) ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I01d Forward Mid Spar Chord - CF6-80C Strut 432, 442 80C (400E) Type 2 Frame 1 to Frame 2 - NSTA 225.25 to 237.5 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I01d Forward Mid Spar Chord - CF6-80C Strut 432, 442 80C (400E) Type 2 Frame 1 to Frame 2 - NSTA 225.25 to 237.5 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I01e Forward Mid Spar - CF6-80C Strut 432, 442 80C (400E) Type 2 Visible Portions Bay 1: NSTA 206 to 220.73 and Bay 3: NSTA 228.23 to 250.16 40,000 Cycles/90,000 Flt. Hrs. 54-50-I01f Forward Mid Spar – CF6-80C Strut 432, 442 80C (400E) Type 2 Bay 1, Horizontal Chord, Exterior Edge < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I01f Forward Mid Spar – CF6-80C Strut 432, 442 80C (400E) Type 2 Bay 1, Horizontal Chord, Exterior Edge ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I02 Lower Spar Chords, Webs, and Thrust Plate, Side Skins, Stiffeners and Back-up 433, 443 524 Type 2 54-50-I03a Chords 50,000 Cycles Approx. NSTA 171 - RB211 Strut 54-50-I03b Lower Spar Chords, Webs, and Thrust Plate 431, 433, 524 Type 2 NSTA 140 - RB211 Strut 441, 443 25,000 Cycles 54-50-I04 Forward Engine Mount Bulkhead - RB211 Strut 433, 443 524 Type 2 NSTA 96.201, NBL 2.55 <2> 50,000 Cycles 54-50-I04 Typical Mid Spar Chord Construction - JT9D Strut 432, 434, 436, 7R4 Type 2 442, 444, 446 50,000 Cycles 54-50-I04 Typical Mid Spar Chord Construction - PW4000 Strut 432, 434, 436, 4000 Type 2 442, 444, 446 25,000 Cycles 54-50-I04 Typical Mid Spar Chord Construction - CF6-80A Strut 432, 434, 436, 80A Type 2 442, 444, 446 50,000 Cycles

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 54-50-I04 Typical Mid Spar Chord Construction - CF6-80C Strut 432, 434, 436, 80C (Except 400E) Type 2 442, 444, 446 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300F) 54-50-I04a Mid Spar Fitting to Chord Splice - CF6-80C Strut 434, 436, 80C (400E) Type 2 Forward most fastener row common to Mid Spar Fitting 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I04a Mid Spar Fitting to Chord Splice - CF6-80C Strut 434, 436, 80C (400E) Type 2 Forward most fastener row common to Mid Spar Fitting 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I04c Mid Spar Chord - CF6-80C Strut 434, 436, 80C (400E) Type 2 Mid Spar Chord to Mid Bulkhead, Frame 3 and Frame 4 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I04c Mid Spar Chord - CF6-80C Strut 434, 436, 80C (400E) Type 2 Mid Spar Chord to Mid Bulkhead, Frame 3 and Frame 4 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I04e Mid Spar Chord - CF6-80C Strut 434, 436, 80C (400E) Type 2 All visible portions between midbulkhead and aft mid spar fittings 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I04e Mid Spar Chord - CF6-80C Strut 434, 436, 80C (400E) Type 2 All visible portions between midbulkhead and aft mid spar fittings 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I04f Mid Spar Chord – CF6-80C Strut 434, 436, 80C (400E) Type 2 All visible portions between midbulkhead and aft mid spar fittings 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I04f Mid Spar Chord – CF6-80C Strut 434, 436, 80C (400E) Type 2 All visible portions between midbulkhead and aft mid spar fittings 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead - JT9D Strut 432, 442 7R4 Type 2 NSTA 147.14, NWL 127.0 50,000 Cycles 54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead 432, 442 4000 Type 2 NSTA 127.14, NWL 127. 0 - PW4000 Strut 50,000 Cycles 54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead - CF6-80A Strut 432, 442 80A Type 2 NSTA 204.5, NWL 119.75 50,000 Cycles 54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead - CF6-80C Strut 432, 442 80C (Except 400E) Type 2 NSTA 206.5, NWL 120.88 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300F) 54-50-I05a Forward Engine Mount Fitting Thrust Tang - CF6-80C Strut 432, 442 80C (400E) Type 2 Fwd Engine Mount < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I05a Forward Engine Mount Fitting Thrust Tang - CF6-80C Strut 432, 442 80C (400E) Type 2 Fwd Engine Mount ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs.

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 54-50-I06 Aft Engine Mount Bulkhead - JT9D Strut 434, 436, 7R4 Type 2 NSTA 222.3, NWL 135.785 444, 446 50,000 Cycles 54-50-I06 Aft Engine Mount Bulkhead - PW4000 Strut 434, 436, 4000 Type 2 NSTA 222.3, NWL 135.785 444, 446 50,000 Cycles 54-50-I06 Aft Engine Mount Bulkhead - CF6-80A Strut 436, 437, 80A Type 2 NSTA 298.93, NWL 134.58 446, 447 50,000 Cycles 54-50-I06 Aft Engine Mount Bulkhead - CF6-80C Strut 436, 437, 80C (Except 400E) Type 2 NSTA 298.93, NWL 134.58 446, 447 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300F) 54-50-I06a Aft Engine Mount Bulkhead - CF6-80C Strut 436, 437, 80C (400E) Type 2 Barrel Nut Bore 446, 447 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I06a Aft Engine Mount Bulkhead - CF6-80C Strut 436, 437, 80C (400E) Type 2 Barrel Nut Bore 446, 447 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I06c Aft Engine Mount Bulkhead, Vertical Splice Strap - CF6-80C Strut 436, 437, 80C (400E) Type 2 Vertical Splice Strap at Aft Eng Mount Blkhd and Mid Spar Ftg Vertical Tang 446, 447 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I06c Aft Engine Mount Bulkhead, Vertical Splice Strap - CF6-80C Strut 436, 437, 80C (400E) Type 2 Vertical Splice Strap at Aft Eng Mount Blkhd and Mid Spar Ftg Vertical Tang 446, 447 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I06d Aft Engine Mount Bulkhead - CF6-80C Strut 436, 437, 80C (400E) Type 2 Aft Flange 446, 447 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I06d Aft Engine Mount Bulkhead - CF6-80C Strut 436, 437, 80C (400E) Type 2 Aft Flange 446, 447 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting - JT9D Strut 437, 447 7R4 Type 2 50,000 Cycles 54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting - PW4000 Strut 437, 447 4000 Type 2 50,000 Cycles 54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting - CF6-80A Strut 437, 447 80A Type 2 50,000 Cycles 54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting - CF6-80C Strut 437, 447 80C (Except 400E) Type 2 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300F) 54-50-I09 Mid Spar Fitting - JT9D Strut 437, 447 7R4 Type 2 50,000 Cycles

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 54-50-I09 Mid Spar Fitting - PW4000 Strut 437, 447 4000 Type 2 50,000 Cycles 54-50-I09 Mid Spar Fitting - CF6-80A Strut 437, 447 80A Type 2 50,000 Cycles 54-50-I09 Mid Spar Fitting - CF6-80C Strut 437, 447 80C (Except 400E) Type 2 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300F) 54-50-I09 Diagonal Brace and Strut Attach Fitting and Fuse Pins - RB211 Strut 434, 444 524 Type 2 50,000 Cycles 54-50-I09a Strut to Wing Attachments - CF6-80C Strut 431, 433, 437, 80C (400E) Type 2 54-50-I07 Strut to Wing Fittings 441, 443, 447, < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I08 511, 521, 611, 54-50-I12 621 54-50-I09a Strut to Wing Attachments - CF6-80C Strut 431, 433, 437, 80C (400E) Type 2 54-50-I07 Strut to Wing Fittings 441, 443, 447, ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I08 511, 521, 611, 54-50-I12 621 54-50-I10 Aft Upper Spar Fittings and Fuse Pins - RB211 Strut 434, 444 524 Type 2 50,000 Cycles 54-50-I10a Forward Engine Mount - CF6-80C Strut 410, 420 80C (400E) Type 1/ Platform at Forward Tension Bolt Holes < 8 Hours 16,000 Cycles/70,000 Flt. Hrs. 54-50-I10a Forward Engine Mount - CF6-80C Strut 410, 420 80C (400E) Type 1/ Platform at Forward Tension Bolt Holes ≥ 8 Hours 16,000 Cycles/70,000 Flt. Hrs. 54-50-I10b Forward Engine Mount - CF6-80C Strut 410, 420 80C (400E) Type 1/ Platform Forward Through Hole < 8 Hours 16,000 Cycles/70,000 Flt. Hrs. 54-50-I10b Forward Engine Mount - CF6-80C Strut 410, 420 80C (400E) Type 1/ Platform Forward Through Hole ≥ 8 Hours 16,000 Cycles/70,000 Flt. Hrs. 54-50-I11 Side Link and Strut Attach Fittings - RB211 Strut 434, 444 524 Type 2 50,000 Cycles 54-50-I11d Aft Engine Mount - CF6-80C Strut 410, 420 80C (400E) Type 1/ Lugs < 8 Hours 25,000 Cycles/80,000 Flt. Hrs. 54-50-I11d Aft Engine Mount - CF6-80C Strut 410, 420 80C (400E) Type 1/ Lugs ≥ 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 54-50-I11f Aft Engine Mount - CF6-80C Strut 410, 420 80C (400E) Type 1/ Engine Turbine Rear Frame (TRF) Clevis Lugs < 8 Hours 16,000 Cycles/70,000 Flt. Hrs. 54-50-I11f Aft Engine Mount - CF6-80C Strut 410, 420 80C (400E) Type 1/ Engine Turbine Rear Frame (TRF) Clevis Lugs ≥ 8 Hours 16,000 Cycles/70,000 Flt. Hrs. 54-50-I12 Side Load Links - JT9D Strut 437, 447 7R4 Type 2 50,000 Cycles 54-50-I12 Side Load Links - PW4000 Strut 437, 447 4000 Type 2 50,000 Cycles 54-50-I12 Side Load Links - CF6-80A Strut 437, 447 80A Type 2 50,000 Cycles 54-50-I12 Side Load Links - CF6-80C Strut 437, 447 80C (Except 400E) Type 2 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300F) 54-50-I12b Side Load Fittings - CF6-80C Strut 437, 447 80C (400E) Type 2 Side Load Fitting. Includes Mid Spar Fitting, Aft Strut Bulkhead and Splice Straps < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I12b Side Load Fittings - CF6-80C Strut 437, 447 80C (400E) Type 2 Side Load Fitting. Includes Mid Spar Fitting, Aft Strut Bulkhead and Splice Straps ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I13 Typical Lower Spar Chord and Spar Web Construction - JT90 Strut 434, 436 7R4 Type 2 All 444, 446 50,000 Cycles 54-50-I13 Typical Lower Spar Chord and Spar Web Construction - CF6-80A Strut 434, 436 80A Type 2 All 444, 446 50,000 Cycles 54-50-I13 Typical Lower Spar Chord and Spar Web Construction - PW4000 Strut 434, 436 4000 Type 2 All 444, 446 50,000 Cycles 54-50-I13 Typical Lower Spar Chord and Spar Web Construction - CF6-80C Strut 434, 436 80C (Except 400E) Type 2 All 444, 446 50,000 Cycles (200, 300 PASS) 40,000 Cycles (300F) 54-50-I13a Lower Spar Chord and Web - CF6-80C Strut 434, 436 80C (400E) Type 2 All locations on lower spar where chord is hidden. 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I13a Lower Spar Chord and Web - CF6-80C Strut 434, 436 80C (400E) Type 2 All locations on lower spar where chord is hidden. 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I13e Lower Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 All visible portions from mid bulkhead to aft engine mount bulkhead. 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs.

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 54-50-I13e Lower Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 All visible portions from mid bulkhead to aft engine mount bulkhead. 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs 54-50-I13f Lower Spar Chord and Web - CF6-80C Strut 434, 436 80C (400E) Type 2 All locations on lower spar where chord is hidden. 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I13f Lower Spar Chord and Web - CF6-80C Strut 434, 436 80C (400E) Type 2 All locations on lower spar where chord is hidden. 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I13g Lower Spar Chord and Web – CF6-80C Strut 434, 436 80C (400E) Type 2 Horizontal Flange Fwd end of Chord. 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I13g Lower Spar Chord and Web – CF6-80C Strut 434, 436 80C (400E) Type 2 Horizontal Flange Fwd end of Chord. 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I14 Mid Bulkhead - Upper Link Fitting (R1) Joint - CF6-80C Strut 432, 434, 436, 80C (400E) Type 2 Mid Bulkhead 442, 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I14 Mid Bulkhead - Upper Link Fitting (R1) Joint - CF6-80C Strut 432, 434, 436, 80C (400E) Type 2 Mid Bulkhead 442, 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I16a Forward Upper Spar - CF6-80C Strut 432, 442 80C (400E) Type 2 Hidden Portions of Forward Upper Spar Chord < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I16a Forward Upper Spar - CF6-80C Strut 432, 442 80C (00E) Type 2 Hidden Portions of Forward Upper Spar Chord ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I16e Forward Upper Spar - CF6-80C Strut 432, 442 80C (400E) Type 2 Visible Portions of Forward Upper Spar Chord < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I16e Forward Upper Spar - CF6-80C Strut 432, 442 80C (400E) Type 2 Visible Portions of Forward Upper Spar Chord ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I16f Forward Upper Spar - CF6-80C Strut 432, 442 80C (400E) Type 2 Hidden Portions of Forward Upper Spar Chord 40,000 Cycles/90,000 Flt. Hrs. 54-50-I17a Aft Upper Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 Horizontal and Vertical Flange at the Midbulkhead and Frame 3, 4, and 5 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I17a Aft Upper Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 Horizontal and Vertical Flange at the Midbulkhead and Frame 3, 4, and 5 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I17c Aft Upper Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 Aft Upper Spar Chord at NSTA 279 (R.H. Side Only) 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I17c Aft Upper Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 Aft Upper Spar Chord at NSTA 279 (R.H. Side Only) 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs.

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 54-50-I17e Aft Upper Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 Horizontal and Vertical Flange from Frame 4 to Frame 5 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I17e Aft Upper Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 Horizontal and Vertical Flange from Frame 4 to Frame 5 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I17f Aft Upper Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 Horizontal and Vertical Flange from NSTA 251 to NSTA 275 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I17f Aft Upper Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 Horizontal and Vertical Flange from NSTA 251 to NSTA 275 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I17g Aft Upper Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 NSTA 285 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I17g Aft Upper Spar Chord - CF6-80C Strut 434, 436 80C (400E) Type 2 NSTA 285 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I17h Aft Upper Spar Chord – CF6-80C Strut 434, 436 80C (400E) Type 2 Horizontal and Vertical Flange at the Midbulkhead and Frame 3, 4, and 5 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I17h Aft Upper Spar Chord – CF6-80C Strut 434, 436 80C (400E) Type 2 Horizontal and Vertical Flange at the Midbulkhead and Frame 3, 4, and 5 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I18 Side Skin/Aft Upper Spar Chord/Stiffener - CF6-80C Strut 434, 436 80C (400E) Type 2 STA 268, Aft - Upper Portion of the Side Skin Cutout 444, 446 < 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 54-50-I18 Side Skin/Aft Upper Spar Chord/Stiffener - CF6-80C Strut 434, 436 80C (400E) Type 2 STA 268, Aft - Upper Portion of the Side Skin Cutout 444, 446 ≥ 8 Hours 40,000 Cycles/90,000 Flt. Hrs. 55-10-I09 Horizontal Stabilizer Upper Skin - At BBL 41.5 Side of Body Splice 331, 341 ALL Except 200SF Type 1 50,000 Cycles (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 55-10-I09A Horizontal Stabilizer Upper Skin - At BBL 41.5 Side of Body Splice 331, 341 200SF Type 1 50,000 Cycles

55-10-I13A Horizontal Stabilizer Pivot Fitting Lug 331, 341 ALL Except 200SF Type 1 50,000 Cycles (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 55-10-I13B Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments 331, 341 ALL Except 200SF Type 1 25,000 Cycles

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 55-10-I13C Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments 331, 341 ALL Except 200SF Type 1 25,000 Cycles

55-10-I13D Horizontal Stabilizer Pivot Fitting Lug 331, 341 200SF Type 1 50,000 Cycles

55-10-I13E Horizontal Stabilizer Pivot Fitting - Upper and Lower Attachments 331, 341 200SF Type 1 25,000 Cycles

55-10-I14A Horizontal Stabilizer - Jackscrew Fitting Lug 331, 341 ALL Except 200SF Type 1 50,000 Cycles (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 55-10-I14B Horizontal Stabilizer Jackscrew Fitting - Upper and Lower Attachments 331, 341 ALL Except 200SF Type 1 50,000 Cycles (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 55-10-I14C Horizontal Stabilizer Jackscrew Fitting Lug 331, 341 200SF Type 1 50,000 Cycles

55-10-I14D Horizontal Stabilizer Jackscrew Fitting - Upper and Lower Attachments 331, 341 200SF Type 1 50,000 Cycles

55-10-I31 Horizontal Stabilizer Rear Spar Upper Chord and Skin - Side-of-Body Hidden Area 331, 341 ALL Except 200SF Type 1 50,000 Cycles (200, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 55-10-I31A Horizontal Stabilizer Rear Spar Upper Chord - Side-of-Body Hidden Area 331, 341 200SF Type 1 50,000 Cycles

55-10-I31B Horizontal Stabilizer Upper Skin 334, 344 200SF Type 1 50,000 Cycles

57-10-I01 Skin at Typical Stringer - Wing Center Section, Lower Surface at External Lower Beams 133, 134 400E Type 1 (BBL 9.5 and BBL 62.0) < 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-10-I01 Skin at Typical Stringer - Wing Center Section, Lower Surface at External Lower Beams 133, 134 400E Type 1 (BBL 9.5 and BBL 62.0) > 8 Hour 25,000 Cycles/80,000 Flt. Hrs.

57-10-I01A Wing Center Section Wet Bay - Upper and Lower Surfaces, Front and Rear Spar, 133,134 300BCF Type 1 Spanwise Beams and Access Door Cutouts, Lower Surface Beams, Side of Body Ribs, 50,000 Cycles/70,000 Flt. Hrs. Splices, Lower Surface Access Hole Cutout and Adjacent Stringers, and Drain <5> 57-10-I01B Wing Center Section - Upper and Lower Surfaces, Rear Spar, Beams and Access Door 133, 134 200SF Type 1 Cutouts, Lower Surface Beams, Side of Body Ribs, Splices, Lower Surface Access 50,000 Cycles/70,000 Flt. Hrs. Hole Cutout and Adjacent Stringers, and Drain 57-10-I01C.1 Typical Stringer - Wing Center Section - Typical - In Areas of Attach Fasteners Between 133, 134 300F Type 1 Left and Right WBL 97.9 25,000 Cycles / 80,000 Flt Hrs

57-10-I01C.2 Typical Stringer and Skin - Wing Center Section - Lower Surface - Stringers 1, 2 and 5 133, 134, 300F Type 1 at External Beams (BL 9.5 and BL 62) 135, 136 25,000 Cycles / 80,000 Flt Hrs

57-10-I02 Splice Stringer - Wing Center Section at Stringer 6 and 10 133, 134 300F Type 1 40,000 Cycles

57-10-I02 Splice Stringer - Wing Center Section at Stringer 6 and 10 133, 134 400E Type 1 < 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-10-I02 Splice Stringer - Wing Center Section at Stringer 6 and 10 133, 134 400E Type 1 > 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-10-I02A Front Spar Lower Chord and Skin - Wing Center Section at Radius Fillers 133, 134 ALL Except 200SF, Type 1 300BCF 25,000 Cycles/80,000 Flt. Hrs. < 8 Hours 57-10-I02A Front Spar Lower Chord and Skin - Wing Center Section at Radius Fillers 133, 134 ALL Except 200SF, Type 1 300BCF 25,000 Cycles/80,000 Flt. Hrs. > 8 Hours 57-10-I02B Skin at Front Spar Lower Chord - Wing Center Section at Underwing Longeron 193, 194 400E Type 1, FLS < 8 Hours See Graph

57-10-I02B Skin at Front Spar Lower Chord - Wing Center Section at Underwing Longeron 193, 194 400E Type 1, FLS > 8 Hours See Graph

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-10-I02C Wing Center Section - Lower Surface Splice Stringers L-6 and L-10 in Areas of Attach 133, 134 300BCF Type 1 Fasteners Between Left and Right WBL 97.9 50,000 Cycles/70,000 Flt. Hrs. <5> 57-10-I02D Wing Center Section - Lower Surface Splice Stringers L-6 and L-10 in Areas of Attach 133, 134 200SF Type 1 Fasteners Between Left and Right WBL 97.9 50,000 Cycles/70,000 Flt. Hrs.

57-10-I03A Rear Spar Lower Chord - Wing Center Section - Typical - BBL 23.0 to Inboard Edge of 133, 134 PASS Type 1 Terminal Fitting (200ER, 300ER) 25,000 Cycles/80,000 Flt. Hrs. with center section fuel < 8 Hours 57-10-I03A Rear Spar Lower Chord - Wing Center Section - Typical - BBL 23.0 to Inboard Edge of 133, 134 PASS Type 1 Terminal Fitting (200ER, 300ER) 25,000 Cycles/80,000 Flt. Hrs. with center section fuel > 8 Hours 57-10-I03A Rear Spar Lower Chord - Wing Center Section - Typical - BBL 23.0 to Inboard Edge of 133, 134 300F Type 1 Terminal Fitting 25,000 Cycles/80,000 Flt. Hrs.

57-10-I03A Rear Spar Lower Chord - Wing Center Section - Inboard Edge of Left Terminal Fitting to 133, 134 400E Type 1 Inboard Edge of Right Terminal Fitting < 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-10-I03A Rear Spar Lower Chord - Wing Center Section - Inboard Edge of Left Terminal Fitting to 133, 134 400E Type 1 Inboard Edge of Right Terminal Fitting > 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-10-I03A Rear Spar Lower Chord - Wing Center Section - Typical - BBL 23.0 to Inboard Edge of 133, 134 200SF Type 1 Terminal Fitting 300BCF 25,000 Cycles/70,000 Flt. Hrs. <6> 57-10-I03B Rear Spar Lower Chord - Wing Center Section - Hidden Locations 133, 134 PASS Type 1 - BBL 49.5, 62.05 and 73.0 (200ER, 300ER) 25,000 Cycles/80,000 Flt. Hrs. with center section fuel < 8 Hours

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-10-I03B Rear Spar Lower Chord - Wing Center Section - Hidden Locations 133, 134 PASS Type 1 - BBL 49.5, 62.05 and 73.0 (200ER, 300ER) 25,000 Cycles/80,000 Flt. Hrs. with center section fuel > 8 Hours 57-10-I03B Rear Spar Lower Chord - Wing Center Section - Hidden Locations - BBL 49.5, 62.05 133, 134 300F Type 1 and 73.0 25,000 Cycles/80,000 Flt. Hrs.

57-10-I03B Rear Spar Lower Chord and Skin - Wing Center Section - Hidden Locations - 133, 134 200SF, 300BCF Type 1 BBL 49.5, 62.05, and 73.0 25,000 Cycles/70,000 Flt. Hrs. <6> 57-10-I03C Skin at Rear Spar Lower Chord - Wing Center Section - Hidden Locations - BBL 49.5, 133, 134 PASS Type 1, FLS 62.05 and 73.0 (200ER, 300ER) See Graph with center section fuel < 8 Hours 57-10-I03C Skin at Rear Spar Lower Chord - Wing Center Section - Hidden Locations - 133, 134 PASS Type 1, FLS BBL 49.5, 62.05 and 73.0 (200ER, 300ER) See Graph with center section fuel > 8 Hours 57-10-I03C Skin at Rear Spar Lower Chord - Wing Center Section - Hidden Locations - 133, 134 300F Type 1, FLS BL 49.5, 62.05 and 73.0 See Graph

57-10-I03C Skin at Rear Spar Lower Chord - Wing Center Section - Hidden Locations - BBL 49.5, 133, 134 200SF, 300BCF Type 1 62.05 and 73.0 25,000 Cycles/70,000 Flt. Hrs. <6> 57-10-I08 Rear Spar Lower Chord - Wing Center Section - Wing BBL 62.0 to inboard edge of 133, 134 400E Type 1 terminal fitting and LBL 11.0 - RBL 11.0 < 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-10-I08 Rear Spar Lower Chord - Wing Center Section - Wing BBL 62.0 to inboard edge of 133, 134 400E Type 1 terminal fitting and LBL 11.0 - RBL 11.0 > 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-10-I16B Lower Surface Side-Of-Body Splice (Sections 11 and 12) - Stringer 1 to Stringer 10, 193, 194 ALL Except 200SF, Type 1 Inboard and Outboard of BBL 97.42 531, 631 300BCF 25,000 Cycles/80,000 Flt. Hrs. < 8 Hours 57-10-I16B Lower Surface Side-Of-Body Splice (Sections 11 and 12) - Stringer 1 to Stringer 10, 193, 194 ALL Except 200SF, Type 1 Inboard and Outboard of BBL 97.42 531, 631 300BCF 25,000 Cycles/80,000 Flt. Hrs. > 8 Hours 57-10-I16C Wing Lower Surface Side-of-Body Splice (Sections 11 and 12) - Stringer 1 to Stringer 193, 194 300BCF Type 1, 10 Inboard and Outboard of BBL 97.42 531, 631 25,000 Cycles/70,000 Flt. Hrs. <6> 57-10-I16D Wing Lower Surface Side-of-Body Splice (Sections 11 And 12) - Stringer 1 to Stringer 193, 194 200SF Type 1, 10 Inboard and Outboard of BBL 97.42 531, 631 25,000 Cycles/70,000 Flt. Hrs.

57-10-I20 Rear Spar Lower Chord Side-of-Body Splice (Sections 11 and 12) - Chords at Splice 143, 144 ALL Except 200SF, Type 1, FLS Fittings Inboard and Outboard of BBL 97.42 551, 651 300BCF See Graph < 8 Hours 57-10-I20 Rear Spar Lower Chord Side-of-Body Splice (Sections 11 and 12) - Chords at Splice 143, 144 ALL Except 200SF, Type 1, FLS Fittings Inboard and Outboard of BBL 97.42 551, 651 300BCF See Graph > 8 Hours 57-10-I20A Rear Spar Lower Chord Side-of-Body Splice (Sections 11 and 12) - Chords at Splice 143, 144 300BCF Type 1 Fittings Inboard and Outboard of BBL 97.42 551, 651 50,000 Cycles/70,000 Flt. Hrs. <5> 57-10-I20B Rear Spar Lower Chord Side-of-Body Splice (Sections 11 and 12) - Chords at Splice 143, 144 200SF Type 1 Fittings Inboard and Outboard of BBL 97.42 551, 651 50,000 Cycles/70,000 Flt. Hrs.

57-10-I24 Underwing Longeron Attachment (Center Section Structure) - BBL 70 Longeron from 193, 194 200ER, 300ER with Type 1, FLS Front Spar Lower Chord to Stringer 18 4 bay center section See Graph fuel tanks, and 300F < 8 Hours 57-10-I24 Underwing Longeron Attachment (Center Section Structure) - BBL 70 Longeron from 193, 194 200ER, 300ER with Type 1, FLS Front Spar Lower Chord to Stringer 18 4 bay center section See Graph fuel tanks, and 300F > 8 Hours

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-10-I24A Underwing Longeron Attachment - Wing Center Section - Hidden Locations - BBL 70 193, 194 300BCF Type 1 Longeron from Front Spar Lower Chord to Stringer 18 50,000 Cycles/70,000 Flt. Hrs. <5> 57-10-I24B Underwing Longeron Attachment - Wing Center Section - Hidden Locations - BBL 70 193, 194 200SF Type 1 Longeron from Front Spar Lower Chord to Stringer 18 50,000 Cycles/70,000 Flt. Hrs.

57-10-I25 Rear Spar Lower Chord - Wing Center Section at Stiffener Clips at 133, 134 400E Type 1 BBL 32.9, 40.2, 47.5, 54.7 and 62 < 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-10-I25 Rear Spar Lower Chord - Wing Center Section at Stiffener Clips at 133, 134 400E Type 1 BBL 32.9, 40.2, 47.5, 54.7 and 62 > 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-20-I03A Rear Spar Lower Chord and Web - Outboard Wing Structure - Typical Details Between 532, 541, 400E Type 1 Rib 12 and Rib 19 551, 561, < 8 Hours 25,000 Cycles/80,000 Flt. Hrs. 632, 641, 651, 661 57-20-I03A Rear Spar Lower Chord and Web - Outboard Wing Structure - Typical Details Between 532, 541, 400E Type 1 Rib 12 and Rib 19 551, 561, > 8 Hours 25,000 Cycles/80,000 Flt. Hrs. 632, 641, 651, 661 57-20-I03B Rear Spar Lower Chord and Web - Outboard Wing Structure - Hidden Details at 532, 541, 400E Type 1, FLS External Stiffeners and Fittings Between Rib 12 and Rib 19 551, 561, < 8 Hours See Graph 632, 641, 651, 661 57-20-I03B Rear Spar Lower Chord and Web - Outboard Wing Structure - Hidden Details at 532, 541, 400E Type 1, FLS External Stiffeners and Fittings Between Rib 12 and Rib 19 551, 561, > 8 Hours See Graph 632, 641, 651, 661 57-20-I05 Rear Spar at Forward Main Landing Gear Trunnion - Rib 5, WS 329.10 532, 632 400E Type 1, FLS 551, 651 < 8 Hours See Graph <2> 57-20-I05 Rear Spar at Forward Main Landing Gear Trunnion - Rib 5, WS 329.10 532, 632 400E Type 1, FLS 551, 651 > 8 Hours See Graph <2>

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-20-I06 Rear Spar at Main Landing Gear Outboard Support - Rib 7, WS 372.20 532, 632 400E Type 1, FLS 551, 651 < 8 Hours See Graph <2> 57-20-I06 Rear Spar at Main Landing Gear Outboard Support - Rib 7, WS 372.20 532, 632 400E Type 1, FLS 551, 651 > 8 Hours See Graph <2> 57-20-I07 Rear Spar at Flap/Spoiler Backup Fitting Installation - Rear Spar Web, Rib Bay 16, 551, 651 400E, and All Type 1, FLS WS 605.50 Airplane Types, See Graph L/N 922 and later (200, 300 PASS, <2> 300F L/N 922 and Later, 400E) 50,000 Cycles/ 70,000 Flt Hrs (200SF, 300BCF L/N 922 and later) 57-20-I12A Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 16 (Dry Bay) under 533, 633 ALL Except 200SF, Type 1, FLS Nacelle Fairing 300BCF, and 400E See Graph < 8 Hours 57-20-I12A Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 16 (Dry Bay) under 533, 633 ALL Except 200SF, Type 1, FLS Nacelle Fairing 300BCF, and 400E See Graph > 8 Hours 57-20-I12A Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 16 (Dry Bay) under 533, 633 400E Type 1, FLS Nacelle Fairing < 8 Hours See Graph

57-20-I12A Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 16 (Dry Bay) under 533, 633 400E Type 1, FLS Nacelle Fairing > 8 Hours See Graph

57-20-I12B Outboard Wing Typical Stringers Lower Surface -- Rib 9: Stringer 17 at Outboard Side 533, 633 ALL Except 200SF, Type 1, FLS Load Fitting under Nacelle Fairing 300BCF, and 400E See Graph < 8 Hours 57-20-I12B Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 17 at Outboard Side 533, 633 ALL Except 200SF, Type 1, FLS Load Fitting under Nacelle Fairing 300BCF, and 400E See Graph > 8 Hours 57-20-I12B Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 17 at Outboard Side 533, 633 400E Type 1, FLS Load Fitting under Nacelle Fairing < 8 Hours See Graph

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-20-I12B Outboard Wing Typical Stringers Lower Surface - Rib 9: Stringer 17 at Outboard Side 533, 633 400E Type 1, FLS Load Fitting under Nacelle Fairing > 8 Hours See Graph

57-20-I12C Outboard Wing Lower Surface Typical Stringer 193, 194 200SF Type 1 437, 447 300BCF 50,000 Cycles/70,000 Flt Hrs. 530, 630 <5> 540, 640 533, 633 57-20-I15A Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10. Stringer 10: Between 530, 630 ALL Except 200SF, Type 1 Rib 7 and 20 (Except Under Nacelle Strut Fairing) and Stringer 6: Side-of-Body to Rib 3 531, 631 300BCF 25,000 Cycles/80,000 Flt. Hrs. 532, 632 < 8 Hours 540, 640 541, 641 57-20-I15A Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10. Stringer 10: Between 530, 630 ALL Except 200SF, Type 1 Rib 7 and 20 (Except Under Nacelle Strut Fairing) and Stringer 6: Side-of-Body to Rib 3 531, 631 300BCF 25,000 Cycles/80,000 Flt. Hrs. 532, 632 > 8 Hours 540, 640 541, 641 57-20-I15B Outboard Wing Lower Surface Splice Stringer - Stringer 10 under Nacelle Fairing 532, 541 ALL Except 200SF, Type 1 632, 641 300BCF 25,000 Cycles/80,000 Flt. Hrs. 437, 447 < 8 Hours 57-20-I15B Outboard Wing Lower Surface Splice Stringer - Stringer 10 under Nacelle Fairing 532, 541 ALL Except 200SF, Type 1 632, 641 300BCF 25,000 Cycles/80,000 Flt. Hrs. 437, 447 > 8 Hours 57-20-I15C Outboard Wing Lower Surface Splice Stringer - Stringer 6, 10 and 15 under Nacelle 532, 632 ALL Except 200SF, Type 1 Strut at External Doublers, Fittings and Angles 533, 633 300BCF, and 400E 25,000 Cycles/80,000 Flt. Hrs. 541, 641 < 8 Hours 57-20-I15C Outboard Wing Lower Surface Splice Stringer - Stringer 6, 10 and 15 under Nacelle 532, 632 ALL Except 200SF, Type 1 Strut at External Doublers, Fittings and Angles 533, 633 300BCF, and 400E 25,000 Cycles/80,000 Flt. Hrs. 541, 641 > 8 Hours 57-20-I15C Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10 under Nacelle Strut at 532, 541 400E Type 1 External Fittings and Skate Angles 632, 641 < 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-20-I15C Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10 under Nacelle Strut at 532, 541 400E Type 1 External Fittings and Skate Angles 632, 641 > 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-20-I15D Outboard Wing Lower Surface Splice Stringer - Stringer 15 under Nacelle Strut at Rib 9 437, 447 ALL Except 200SF, Type 1, FLS (Seal Pans) 530, 630 300BCF, and 400E See Graph < 8 Hours 57-20-I15D Outboard Wing Lower Surface Splice Stringer - Stringer 15 under Nacelle Strut at Rib 9 437, 447 ALL Except 200SF, Type 1, FLS (Seal Pans) 530, 630 300BCF, and 400E See Graph > 8 Hours 57-20-I15D Outboard Wing Lower Surface Splice Stringer - Stringer 15 under Nacelle Strut at Rib 9 437, 447 400E Type 1, FLS (Seal Pans) 530, 630 < 8 Hours See Graph

57-20-I15D Outboard Wing Lower Surface Splice Stringer - Stringer 15 under Nacelle Strut at Rib 9 437, 447 400E Type 1, FLS (Seal Pans) 530, 630 > 8 Hours See Graph

57-20-I15E Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10 at Rib 3 530, 630 All Except 200SF, Type 1, FLS 300BCF, and 400E See Graph < 8 Hours 57-20-I15E Outboard Wing Lower Surface Splice Stringer - Stringer 6 and 10 at Rib 3 530, 630 All Except 200SF, Type 1, FLS 300BCF, and 400E See Graph > 8 Hours 57-20-I15F Outboard Wing Lower Surface Splice Stringer - Seal Pan/Baffles at Ribs 3, 5, 18 530, 540 400E Type 1 and 31 630, 640 < 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-20-I15F Outboard Wing Lower Surface Splice Stringer - Seal Pan/Baffles at Ribs 3, 5, 18 530, 540 400E Type 1 and 31 630, 640 > 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-20-I15G Outboard Wing Lower Surface Splice Stringer - Stringer 6 at External Nacelle Fitting 532, 541 400E Type 1 and Outboard Skate Angle 632, 641 < 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-20-I15G Outboard Wing Lower Surface Splice Stringer - Stringer 6 at External Nacelle Fitting 532, 541 400E Type 1 and Outboard Skate Angle 632, 641 > 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-20-I15H Outboard Wing Lower Surface Splice Stringer - Stringer 15 at External Nacelle Fitting 532, 541 400E Type 1 and Outboard Skate Angle 632, 641 < 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-20-I15H Outboard Wing Lower Surface Splice Stringer - Stringer 15 at External Nacelle Fitting 532, 541 400E Type 1 and Outboard Skate Angle 632, 641 > 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-20-I15J Outboard Wing Lower Surface Splice Stringers 437, 447 200SF Type 1 530, 630 300BCF 25,000 Cycles/70,000 Flt. Hrs. 531, 631 <6> 532, 632 533, 633 540, 640 541, 641 57-20-I15K Outboard Wing Lower Surface Splice Stringers 437, 447 200SF Type 1 531, 631 300BCF 25,000 Cycles/70,000 Flt. Hrs. 532, 632 <6> 541, 641 57-20-I16A Rear Spar Lower Chord (Outboard Wing Structure) - Typical Details between Fairing at 531, 631 ALL Except 200SF, Type 1 Side-Of-Body & Rib 3 300BCF 25,000 Cycles/80,000 Flt. Hrs. < 8 Hours 57-20-I16A Rear Spar Lower Chord (Outboard Wing Structure) - Typical Details between Fairing at 531, 631 ALL Except 200SF, Type 1 Side-Of-Body & Rib 3 300BCF 25,000 Cycles/80,000 Flt. Hrs. > 8 Hours 57-20-I16B Rear Spar Lower Chord (Outboard Wing Structure) - Details Hidden by Rib Shear Ties 531, 631 ALL Except 200SF, Type 1, FLS Side-Of-Body to Rib 3 532, 632 300BCF, and 400E See Graph < 8 Hours 57-20-I16B Rear Spar Lower Chord (Outboard Wing Structure) - Details Hidden by Rib Shear Ties 531, 631 ALL Except 200SF, Type 1, FLS Side-Of-Body to Rib 3 532, 632 300BCF, and 400E See Graph > 8 Hours 57-20-I16B Rear Spar Lower Chord (Outboard Wing Structure) - Details Hidden by Rib Shear Ties 531, 631 400E Type 1, FLS Side-Of-Body to Rib 3 532, 632 < 8 Hours See Graph

57-20-I16B Rear Spar Lower Chord (Outboard Wing Structure) - Details Hidden by Rib Shear Ties 531, 631 400E Type 1, FLS Side-Of-Body to Rib 3 532, 632 > 8 Hours See Graph

57-20-I16C Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details at Ribs 5, 6, 8 and 532, 632 ALL Except 200SF, Type 1, FLS 9 (Not Covered by Fairings) 300BCF, and 400E See Graph < 8 Hours

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-20-I16C Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details at Ribs 5, 6, 8 and 532, 632 ALL Except 200SF, Type 1, FLS 9 (Not Covered by Fairings) 300BCF, and 400E See Graph > 8 Hours 57-20-I16C Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details at Ribs 5, 6, 8 and 532, 632 400E Type 1, FLS 9 (Not Covered by Fairings) < 8 Hours See Graph

57-20-I16C Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details at Ribs 5, 6, 8 and 532, 632 400E Type 1, FLS 9 (Not Covered by Fairings) > 8 Hours See Graph

57-20-I16D Rear Spar Lower Chord (Outboard Wing Structure) - Details Outboard of Terminal 531, 631 ALL Except 200SF, Type 1 Fitting Wing-to-Body Fairing Area 300BCF, and 400E 25,000 Cycles/80,000 Flt. Hrs. < 8 Hours 57-20-I16D Rear Spar Lower Chord (Outboard Wing Structure) - Details Outboard of Terminal 531, 631 ALL Except 200SF, Type 1 Fitting Wing-to-Body Fairing Area 300BCF, and 400E 25,000 Cycles/80,000 Flt. Hrs. > 8 Hours 57-20-I16D Rear Spar Lower Chord (Outboard Wing Structure) - Details Outboard of Terminal 531, 631 400E Type 1 Fitting Wing-to-Body Fairing Area < 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-20-I16D Rear Spar Lower Chord (Outboard Wing Structure) - Details Outboard of Terminal 531, 631 400E Type 1 Fitting Wing-to-Body Fairing Area > 8 Hours 25,000 Cycles/80,000 Flt. Hrs.

57-20-I16E Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details - Trunnion, Nacelle 530, 540 ALL Except 200SF, Type 1, FLS and Inboard Flap Fairing Areas 630, 640 300BCF, and 400E See Graph < 8 Hours 57-20-I16E Rear Spar Lower Chord (Outboard Wing Structure) - Hidden Details - Trunnion, Nacelle 530, 540 ALL Except 200SF, Type 1, FLS and Inboard Flap Fairing Areas 630, 640 300BCF, and 400E See Graph > 8 Hours 57-20-I16E Rear Spar Lower Chord, Rib Bay 11, WSTA 449.2 - Hidden Details 530, 540 400E Type 1, FLS 630, 640 < 8 Hours See Graph

57-20-I16E Rear Spar Lower Chord, Rib Bay 11, WSTA 449.2 - Hidden Details 530, 540 400E Type 1, FLS 630, 640 > 8 Hours See Graph

57-20-I16F Skin at Front Spar Lower Chord (Outboard Wing Structure) - Lower Skin Panel Splice 540,640 ALL Except 200SF, Type 1, FLS Location between Ribs 18 and 19 only 300BCF, and 400E See Graph < 8 Hours

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-20-I16F Skin at Front Spar Lower Chord (Outboard Wing Structure) - Lower Skin Panel Splice 540, 640 ALL Except 200SF, Type 1, FLS Location between Ribs 18 and 19 only 300BCF, and 400E See Graph > 8 Hours 57-20-I16F Skin at Front Spar Lower Chord Outboard Wing Structure) - Lower Skin Panel Splice 540, 640 400E Type 1, FLS Location between Ribs 18 and 19 only < 8 Hours See Graph <2> 57-20-I16F Skin at Front Spar Lower Chord (Outboard Wing Structure) - Lower Skin Panel Splice 540, 640 400E Type 1, FLS Location between Ribs 18 and 19 only > 8 Hours See Graph <2> 57-20-I16G Front Spar Lower Chord and Skin (Outboard Wing Structure) - Details Hidden by 530, 540 ALL Except 200SF, Type 1, FLS Rib Shear Ties Rib 9 to and including Rib 23 630, 640 300BCF, and 400E See Graph < 8 Hours 57-20-I16G Front Spar Lower Chord and Skin (Outboard Wing Structure) - Details Hidden by 530, 540 ALL Except 200SF, Type 1, FLS Rib Shear Ties Rib 9 to and including Rib 23 630, 640 300BCF, and 400E See Graph > 8 Hours 57-20-I16G Front Spar Lower Chord (Outboard Wing Structure) - Details Hidden by Rib Shear Ties 540, 640 400E Type 1, FLS Rib 9 to and including Rib 23 < 8 Hours See Graph

57-20-I16G Front Spar Lower Chord (Outboard Wing Structure) - Details Hidden by Rib Shear Ties 540, 640 400E Type 1, FLS Rib 9 to and including Rib 23 > 8 Hours See Graph

57-20-I16H Front Spar Lower Chord (Outboard Wing Structure) - Hidden Details 533, 633 ALL Except 200SF, Type 1, FLS - Ribs 8/9 and at Side Brace Fitting between Ribs 8/9 300BCF, and 400E See Graph < 8 Hours 57-20-I16H Front Spar Lower Chord (Outboard Wing Structure) - Hidden Details 533, 633 ALL Except 200SF, Type 1, FLS - Ribs 8/9 and at Side Brace Fitting between Ribs 8/9 300BCF, and 400E See Graph > 8 Hours 57-20-I16H Front Spar Lower Chord (Outboard Wing Structure) - Hidden Details - Ribs 8/9 and at 533, 633 400E Type 1, FLS Side Brace Fitting between Ribs 8/9 < 8 Hours See Graph

57-20-I16H Skin at Front Spar Lower Chord (Outboard Wing Structure) - Hidden Details - Ribs 8/9 533, 633 400E Type 1, FLS and at Side Brace Fitting between Ribs 8/9 > 8 Hours See Graph

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-20-I16I Front Spar Lower Chord and Skin - Hidden Details - Rib Shear Ties, Rib 24 to and 540, 640 400E Type 1, FLS including Rib 31 < 8 Hours See Graph <2> 57-20-I16I Front Spar Lower Chord and Skin - Hidden Details - Rib Shear Ties, Rib 24 to and 540, 640 400E Type 1, FLS including Rib 31 > 8 Hours See Graph <2> 57-20-I16J Rear Spar Lower Chord - Hidden Details - Rib Shear Ties, Rib 22 up to and including 540, 640 400E Type 1, FLS Rib 32 < 8 Hours See Graph <2> 57-20-I16J Rear Spar Lower Chord - Hidden Details - Rib Shear Ties, Rib 22 up to and including 540, 640 400E Type 1, FLS Rib 32 > 8 Hours See Graph <2> 57-20-I16K Outboard Wing Lower Surface Front and Rear Spar Chords and Skin 530, 630 200SF Type 1 531, 631 300BCF 25,000 Cycles/70,000 Flt. Hrs. 532, 632 <6> 533, 633 540, 640 541, 641 57-20-I16L Wing Rear Spar Lower Chord and Skin (Outboard Wing Structure) - Details Outboard of 531, 631 200SF Type 1 Terminal Fitting Wing-to- Body Fairing Area 300BCF 25,000 Cycles/70,000 Flt. Hrs. <6> 57-20-I19 Nacelle Fitting Area at the Lower Surface - Outboard Wing Lower Surface - 532, 632 400E Type 1, FLS WS 436.9, Aft Pitch Load Fitting Forward End at Stringer 5 < 8 Hours See Graph

57-20-I19 Nacelle Fitting Area at the Lower Surface - Outboard Wing Lower Surface - 532, 632 400E Type 1, FLS WS 436.9, Aft Pitch Load Fitting Forward End at Stringer 5 > 8 Hours See Graph

57-20-I27 Skin Tab at Front Spar Pitch Load Fitting 511, 611 ALL See Service Bulletin 767-57A0117

57-20-I36 Main Landing Gear Forward Trunnion Support to Lower Skin Attachment - Inboard 530, 630 400E Type 1 Forward Trunnion Support, Most Inboard Aft Fastener 25,000 Cycles/80,000 Flt. Hrs.

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I02A Outboard Flap Supports No. 1/8 and No. 2/7 - Support Ribs (Rear Spar Fittings) in 572, 573 200, 200SF Type 2 Bathtub Region, Lug 6 Region and Lower Aft Flange 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F L/N 922 <2> and Later, 400E) 57-53-I02A.1 Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fittings - Lugs at Joint 1 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I02A.2 Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fittings - Lugs at Joint 6 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I02A.3 Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fittings - Lower Aft Flange 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921 57-53-I02B Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fitting Tension Bolts - 572, 573 200, 200SF Type 1 BACB30US12 Bolt - Thread Runout 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 922 and Later and 400E 57-53-I02B Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fitting Tension Bolts 572, 573 200, 200SF Type 1 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I02C Outboard Flap Supports No. 1/8 and No. 2/7 - Doublers - 0.375” Diameter Fastener 572, 573 200, 200SF Type 2 Holes 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F <2> L/N 922 and Later, 400E) 57-53-I02C Outboard Flap Supports No. 1/8 and No. 2/7 - Rear Spar Fittings - Actuator Bore and 572, 573 200, 200SF Type 2 Fastener Holes 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921 57-53-I02D.1 Outboard Flap Supports No. 1/8 and No. 2/7 - 9-10 Beam - Joint 9 Lug 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I02D.2 Outboard Flap Supports No. 1/8 and No. 2/7 - 9-10 Beam 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I02E Outboard Flap Supports No. 1/8 and No. 2/7 - 9-10 Beam Swivel Fitting - Upper 572, 573 200, 200SF Type 1 Surface 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/N 922 and Later and 400E 57-53-I02F Outboard Flap Supports No. 1/8 and No. 2/7 - Flap Attachment Bolts 572, 573 200, 200SF Type 1 672, 673 300BCF, 300F 25,000 Cycles After 300 PASS Accomplishing Terminating L/Ns 1 - 710 Action of SB 767-27A0155

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I02F Outboard Flap Supports No. 1/8 and No. 2/7 - Flap Attachment Bolts 572, 573 200, 200SF Type 1 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 711 - 921 57-53-I02G.1 Outboard Flap Supports No. 1/8 and No. 2/7 - 6-8-9 Beam (Main Drive Link), Flanges in 572, 573 200, 200SF Type 2 Vicinity of Joint 8 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F L/N 922 <2> and Later, 400E) 57-53-I02G.1 Outboard Flap Supports No. 1/8 and No. 2/7 - 6-8-9 Beam - Typical Section 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921 57-53-I02G.2 Outboard Flap Supports No. 1/8 and No. 2/7 - 6-8-9 Beam (Main Drive Link), Lug 8 572, 573 200, 200SF Type 2 Region 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F L/N 922 <2> and Later, 400E) 57-53-I02G.2 Outboard Flap Supports No. 1/8 and No. 2/7 - 6-8-9 Beam - Lugs 6, 8 and 9 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I02G.3 Outboard Flap Supports No. 1/8 and No. 2/7 - 6-8-9 Beam - Fastener Holes 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I02I Outboard Flap Supports No. 1/8 and No. 2/7 - 4-5 Drive Arm - Spline Outer Surface 572, 573 ALL Type 2 672, 673 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 57-53-I02J.1 Outboard Flap Support No. 1/8 - Link 3-10 - Lug 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I02J.2 Outboard Flap Support No. 2/7 - Link 3-10 - Lugs 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I02L.1 Outboard Flap Supports No. 1/8 and No. 2/7 - Beam 1-2-3 - Beam at Field Fasteners 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921 57-53-I02L.2 Outboard Flap Supports No. 1/8 and No. 2/7 - Beam 1-2-3 - Lug at Joint 1 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I02L.3 Outboard Flap Supports No. 1/8 and No. 2/7 - Beam 1-2-3 - Lugs at Joint 3 572, 573 200, 200SF Type 2 672, 673 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I02M.1 Outboard Flap Supports No. 1/8 and No. 2/7 - Outer Pins at Supports No. 1/8: Joints 5, 572, 573 200, 200SF Type 1 6, 8 and 10 and Supports No. 2/7: Joints 5, 6 and 10 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/N 922 and Later and 400E 57-53-I02M.2 Outboard Flap Supports No. 2/7 - Outer Pin at Inboard Main Support: Joint 8 572, 672 200, 200SF Type 1 300BCF, 300F 25,000 Cycles 300 PASS L/N 922 and Later and 400E 57-53-I02M.4 Outboard Flap Pins - Support No. 2/7 - Outer Pins at Joint 2 and Joint 8 572, 672 200, 200SF Type 1 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921 57-53-I02M.5 Outboard Flap Pins - Support No. 1/8 and No. 2/7 - Joint #1 Fuse Pin - Pin Shank at 572, 573 200, 200SF Type 1 Outboard Rib Support 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921 57-53-I02M.6 Outboard Flap Pins - Support No. 1/8, Joints 2, 3, 5, 6, 8, 9, and 10 - Support No. 2/7, 572, 573 200, 200SF Type 1 Joints 3, 5, 6, 9, and 10 672, 673 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921 57-53-I03E.1 Inboard Flap Box Support No. 3/6 - Backup Fittings - Forward Bathtub 555, 655 200, 200SF Type 1 300BCF, 300F 25,000 Cycles 300 PASS L/N 922 and Later and 400E 57-53-I03E.2 Inboard Flap Box Support No. 3/6 - Backup Fittings - Aft Bathtub End Pads 555, 655 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F <2> L/N 922 and Later, 400E)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I03F.1 Inboard Flap Box Support No. 3/6 - Flap Attachment Bolts, IFS 251.25 555, 655 200, 200SF Type 1 300BCF, 300F 25,000 Cycles 300 PASS L/N 922 and Later and 400E 57-53-I03F.2 Inboard Flap Support No. 3/6 - Flap Attachment Bolts - Shank Location 555, 655 200, 200SF Type 1 300BCF, 300F 25,000 Cycles After 300 PASS Accomplishing Terminating L/Ns 1 - 849 Action of SB 767-27A0176 57-53-I03F.2 Inboard Flap Support No. 3/6 - Flap Attachment Bolts - Shank Location 555, 655 200, 200SF Type 1 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 850 - 921 57-53-I03I.1 Inboard Flap Box at Support No. 4/5 - Inboard Closure Rib - Lower Chord, IFS 108.5 555, 655 ALL Type 1 25,000 Cycles

57-53-I03I.2 Inboard Flap Supports #4, #5 - Splined Bushing at IFS 108.5, Internal Spline Base of 555, 655 ALL Type 1 Tooth/Rim 25,000 Cycles

57-53-I03J.1 Inboard Flap Supports #4, #5 - Collar Fitting Bathtubs, IFS 92, Bathtub End Pads 555, 655 ALL Type 2 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 57-53-I03J.2 Inboard Flap Supports #4, #5 - Collar Fitting, Spline Cross Section 555, 655 ALL Type 1 25,000 Cycles

57-53-I03K Inboard Flap Box at Supports #4, #5 - Collar Fitting Attachment Bolts, IFS 92 555, 655 ALL Type 1 25,000 Cycles or 25,000 Cycles after SB 767-27A0176 was accomplished 57-53-I03L Inboard Flap Box Supports #4, #5 - Torque Tube, IFS 92 to IFS 124.5 555, 655 ALL Type 1 25,000 Cycles

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I04A.1 Inboard Flap Support No. 3/6 - Actuator Support Rib Assembly - Section Forward of 571, 671 200, 200SF Type 2 Joint 6 Lug - Lower Flange 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F L/N 922 and Later, 400E) 57-53-I04A.1 Inboard Flap Support No. 3/6 - Actuator Support Rib - Section Forward of Joint 6 Lug 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I04A.2 Inboard Flap Support No. 3/6 - Actuator Support Rib Assembly - Lug Details at Joints 0, 571, 671 200, 200SF Type 2 1 and 6 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F <2> L/N 922 and Later, 400E) 57-53-I04A.2 Inboard Flap Support No. 3/6 - Actuator Support Rib - Lugs at Joints 0, 1, 6 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I04B.2 Inboard Flap Support No. 3/6 - Underwing Fitting - Field Fasteners 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 883 and Later PASS L/N 883 and Later) and 400E 40,000 Cycles (300F <2> L/N 883 and Later, 400E)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I04B.2 Wing Trailing Edge, Inboard Flap, Support No. 3/6 - Underwing Fitting - Field Fasteners 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 882 PASS L/Ns 1 - 882) 40,000 Cycles (300F L/Ns 1 - 882) 57-53-I04B.3 Wing Trailing Edge, Inboard Flap, Support No. 3/6 - Underwing Fitting - Lug at Fuse Pin 571, 671 200, 200SF Type 2 location 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 882 PASS L/Ns 1 - 882) 40,000 Cycles (300F L/Ns 1 - 882) 57-53-I04C Wing Trailing Edge, Inboard Flap, Support No. 3/6 - Underwing Fitting to Forward 571, 671 200, 200SF Type 1 Tension Link Fuse Pin 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 882 57-53-I04D Inboard Flap Support No. 3/6 - Forward Tension Link - Section A-A - Typical Section at 571, 671 200, 200SF Type 2 Field Fasteners and Aft Lugs 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 883 and Later PASS L/N 883 and Later) and 400E 40,000 Cycles (300F <2> L/N 883 and Later, 400E) 57-53-I04D.1 Wing Trailing Edge, Inboard Flap, Support No. 3/6 - Forward Tension Link - Typical 571, 671 200, 200SF Type 2 Cross Section Through Fasteners 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 882 PASS L/Ns 1 - 882) 40,000 Cycles (300F L/Ns 1 - 882) 57-53-I04D.2 Wing Trailing Edge, Inboard Flap, Support No. 3/6 - Forward Tension Link - Forward 571, 671 200, 200SF Type 2 Clevis and Aft Lug 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 882 PASS L/Ns 1 - 882) 40,000 Cycles (300F L/Ns 1 - 882)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I04E Inboard Flap Support No. 3/6 - 1-2-3 Beam - Lugs at Joints 1, 2, and 3 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F <2> L/N 922 and Later, 400E) 57-53-I04E.1 Inboard Flap Support No. 3/6 - Beam 1-2-3 - Lug at Joint 1 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I04E.2 Inboard Trailing Edge Flap Support No. 3/6 - Beam 1-2-3 - Lugs at Joint 2 and Joint 3 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I04E.3 Inboard Flap Support No. 3/6 - Beam 1-2-3 - Beam at Field Fasteners 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I04F.1 Inboard Flap Support No. 3/6 - 3-10 Link - Lugs 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I04F.1 Inboard Flap Support No. 3/6 - 3-10 Link - Lugs 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F <2> L/N 922 and Later, 400E) 57-53-I04F.2 Inboard Flap Support No. 3/6 - 3-10 Link - Between Lugs 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I04F.2 Inboard Flap Support No. 3/6 - 3-10 Link - Between Lugs 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F <2> L/N 922 and Later, 400E) 57-53-I04H Inboard Flap Support No. 3/6 - 6-7-8-9 Beam - Lug 9 Detail 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F <2> L/N 922 and Later, 400E) 57-53-I04H Inboard Flap Support No. 3/6 - 6-7-8-9 Beam - Lugs 6, 7, 8 and 9 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I04I Inboard Flap Support No. 3/6 - 4-5 Drive Arm - Internal Spline, Outer Surface 571, 671 ALL Type 2 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 57-53-I04K Inboard Flap Support No. 3/6 - 9-10 Beam - Lug at Joint 9 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F <2> L/N 922 and Later, 400E) 57-53-I04K.1 Inboard Flap Support No. 3/6 - 9-10 Beam - Joint 9 Lug 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I04K.2 Inboard Flap Support No. 3/6 - 9-10 Beam - Typical Section at Lower Field Fasteners 571, 671 200, 200SF Type 2 and Lower Flange 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921 57-53-I04K.3 Inboard Flap Support No. 3/6 - 9-10 Beam 571, 671 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I04N.1 Inboard Flap Support No. 3/6 - Flap Support Pins - Outer Pins at Joints 0, 1, 2, 3, 5, 6, 571, 671 200, 200SF Type 1 7, 8, 9 and 10 300BCF, 300F 25,000 Cycles 300 PASS L/N 922 and Later and 400E

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I04N.2 Inboard Flap Support No. 3/6 - Flap Support Pins - Outer Pins at Joints A and B 571, 671 200, 200SF Type 1 300BCF, 300F 25,000 Cycles 300 PASS L/N 922 and Later and 400E 57-53-I04N.3 Inboard Flap Support No. 3/6 - Flap Support Pins - Outer Pins at Joints 0, 2, 3, 5, 6, 7, 571, 671 200, 200SF Type 1 8, 9, 10, A, and B 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921 57-53-I04N.4 Inboard Flap Support No. 3/6 - Flap Support Pins - Outer Pin at Joint 1 571, 671 200, 200SF Type 1 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921 57-53-I04P Inboard Flap Support No. 4/5 - 4-5 Drive Arm - Internal Spline Outer Surface 195, 196 ALL Type 2 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 57-53-I04Q.1 Inboard Flap Support No. 4/5 - 5-7 Link - Lugs 195, 196 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F <2> L/N 922 and Later, 400E) 57-53-I04Q.1 Inboard Flap Support No. 4/5 - 5-7 Link - Lugs 195, 196 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921)

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I04Q.2 Inboard Flap Support No. 4/5 - 5-7 Link - Cross Sections 3.16 inches from Lugs 195, 196 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F <2> L/N 922 and Later, 400E) 57-53-I04Q.2 Inboard Flap Support No. 4/5 - 5-7 Link - Body of Link around Field fasteners 195, 196 200, 200SF Type 2 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/Ns 1 - 921 PASS L/Ns 1 - 921) 40,000 Cycles (300F L/Ns 1 - 921) 57-53-I04S Inboard Flap Support No. 4/5 - 6-7 Drive Arm - at Field Fasteners Between Joints 6 and 195, 196 ALL Type 2 7, and Joint 7 Lug 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 57-53-I04T Inboard Flap Support No. 4/5 - 6-9 Drive Arm Flanges - Near the Bend in the Part 195, 196 ALL Type 2 50,000 Cycles (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F, 400E) 57-53-I04V Inboard Flap Support No. 4/5 - Carrier Beam 9-11 - Aft Bathtub Bolt Hole and Forward 195, 196 200, 200SF Type 2 Field Fasteners 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 L/N 922 and Later PASS L/N 922 and Later) and 400E 40,000 Cycles (300F <2> L/N 922 and Later, 400E) 57-53-I04Y Inboard Flap Support No. 4/5 - Flap Support Fitting - Upper Flange Inboard Bolt 195, 196 400E Type 2 Location 40,000 Cycles

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-53-I04Y Inboard Flap Support No. 4/5 - Side Strut Swivel Support Fitting - Satellite Holes at 195, 196 200, 200SF Type 2 Lug 6 300BCF, 300F 50,000 Cycles 300 PASS (200, 200SF, 300BCF, 300 PASS) 40,000 Cycles (300F) 57-53-I04Z Inboard Flap Support No. 4/5 - 6-6’ Outer Pin - Section at Spline #2 (Common to 6-7 195, 196 ALL Type 1 Arm) Inner Diameter (Inner Bore) 25,000 Cycles

57-53-I04AA Inboard Flap Support No. 4/5- Flap Support Pins - Outer Pins at Joints 5, 7 and 9 195, 196 200, 200SF Type 1 300BCF, 300F 25,000 Cycles 300 PASS L/N 922 and Later and 400E 57-53-I04AA Inboard Flap Support No. 4/5 - Flap Support Pins - Outer Pins at Joints 5, 7, 9, and RL 195, 196 200, 200SF Type 1 300BCF, 300F 25,000 Cycles 300 PASS L/Ns 1 - 921 57-54-I02A Main Landing Gear Beam, Inboard Lug Bore 552, 652 200SF Type 1 300BCF 50,000 Cycles <4> 57-54-I02B Main Landing Gear Beam, Outboard Lug Bore. 552, 652 200SF Type 1 300BCF 50,000 Cycles <4> 57-54-I02C Main Landing Gear Beam, Aft Trunnion Bore 552, 652 200SF Type 1 300BCF 50,000 Cycles <4> 57-54-I02D Main Landing Gear Beam, Upper Flange, between the Inboard and Outboard Web 552, 652 200SF Type 1 Stiffeners adjacent to Aft Trunnion Bore 300BCF 50,000 Cycles <4> 57-54-I02E Main Landing Gear Beam, Upper Flange, except the flange adjacent to Aft Trunnion 552, 652 200SF Type 1 Bore covered by SSI 57-54-I02D 300BCF 50,000 Cycles <4>

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AIRWORTHINESS LIMITATIONS - STRUCTURAL INSPECTIONS AIRPLANE/ INSPECTION ENGINE SSI # DTR CHECK FORM TITLE ZONE APPLICABILITY TYPE AND THRESHOLD 57-54-I03A Load Distribution Plates, Flange around Outboard Upper Lug 552, 652 200SF Type 1 300BCF 50,000 Cycles <4> 57-54-I03B Load Distribution Plates, Flange around Outboard Lower Lug 552, 652 200SF Type 1 300BCF 50,000 Cycles <4> 57-54-I03C Load Distribution Plates, Flange around Inboard Lug. 552, 652 200SF Type 1 300BCF 50,000 Cycles <4> 57-54-I03D Load Distribution Plates, Flange except in the Lug areas covered by SSI 57-54-I03A, 552, 652 200SF Type 1 57-54-I03B and 57-54-I03C 300BCF 50,000 Cycles <4> 57-54-I04 Main Landing Gear Beam, Outboard Pin 552, 652 200SF Type 1 300BCF 50,000 Cycles <4> 57-54-I13 Main Landing Gear Forward Trunnion Support - Side Load Fitting - Side Load Fitting to 551, 651 400E Type 1 Strap Inboard Fastener Row 25,000 Cycles/80,000 Flt. Hrs.

57-54-I14 Main Landing Gear Forward Trunnion Support - Side Load Strap - First Fastener Row 551, 651 400E Type 1 Either Side of Trunnion 25,000 Cycles/80,000 Flt. Hrs.

<1> This flagnote is no longer being used. <2> No 767 airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedures are validated, published in the appropriate manual, and accepted by the FAA. <3> No 767-300F airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedures are validated, published in the appropriate manual, and accepted by the FAA. <4> No 767-300BCF and 767-200SF airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedures are validated, published in the appropriate manual, and accepted by the FAA. <5> Threshold is 50,000 Flight Cycles / 70,000 Flight Hours or 8,000 Flight Hours after conversion to 767-300BCF, whichever occurs later, not to exceed 50,000 total Flight Cycles and 78,000 total Flight Hours. <6> Threshold is 25,000 Flight Cycles / 70,000 Flight Hours or 8,000 Flight Hours after conversion to 767-300BCF, whichever occurs later, not to exceed 25,000 total Flight Cycles and 78,000 total Flight Hours.

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C. AIRWORTHINESS LIMITATIONS - STRUCTURAL SAFE LIFE PARTS

ITEM LIFE LIMIT

767-200, 767-200SF Nose Landing Gear 80,000 Landings *

767-200, 767-200SF Main Landing Gear 70,000 Landings *

767-200, 767-200SF Main Landing Gear Support Structure 90,000 Landings *

767-300, 767-300BCF, 767-300F Nose Landing Gear 80,000 Landings **

767-300, 767-300BCF, 767-300F Main Landing Gear 50,000 Landings **

767-300, 767-300BCF, 767-300F Main Landing Gear Support Structure 62,000 Landings **

767-300, 767-300BCF, 767-300F Main Landing Gear Retract Actuator Fitting and Pin 90,000 Landings **

767-400ER Nose Landing Gear 80,000 Landings **

767-400ER Main Landing Gear 50,000 Landings **

767-400ER Main Landing Gear Inner Cylinder 161T7120 36,800 Landings **

767-400ER Main Landing Gear Outer Cylinder 161T7110 31,800 Landings **

767-400ER Main Landing Gear Support Structure 50,000 Landings **

767-400ER Wing Main Landing Gear Beam Upper Stabilizer Brace Fuse Pin 113T1140-3 16,175 Landings ** NOTE: Service Letter 767-SL-32-092 (Latest Revision) and its reference Boeing Drawing 160T0002, 767 Main and Nose Landing Gear Component 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 airplanes. ** These values are based on completed fatigue tests and analysis.

SERVICE BULLETIN LIFE LIMIT NUMBER DESCRIPTION PRIOR TO INCORPORATION

767-32-44 MLG Upper Spindle-Drag Strut, Part # 161T6007 9,000 Landings

767-32-45 MLG Outer Cylinder Assembly, Part # 161T1110 18,000 Landings

767-32-46 MLG Upper Bulkhead-Shock Strut, Part # 16T1161 30,000 Landings

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The following data is applicable to the Rolls-Royce RB211-524H engine mounts for use on the 767-300 airplane:

ITEM LIFE LIMIT 767-300 Front Mount Pylon Mounting Bracket 30,000 Landings *** 767-300 Front Mount Center Thrust Link And Associated Hardware 30,000 Landings *** 767-300 Rear Mount Pylon Bracket 50,000 Landings ***

*** These values are based on completed Safe-Life testing and analysis.

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D. AWLs - STRUCTURAL LIMIT OF VALIDITY (LOV)

This section provides the Limit of Validity (LOV) in accordance with the requirements of Title 14 CFR § 26.21 (Amendment 26-6). This regulation requires the establishment of an airplane level limit of validity of the engineering data that supports the structural maintenance program that corresponds to the period of time, stated as a number of total accumulated flight cycles or flight hours or both, during which it is demonstrated that widespread fatigue damage will not occur in the airplane. The LOVs listed in the following table support operator compliance with Title 14 CFR Sections 121.1115 and 129.115 for the 767.

LIMIT OF VALIDITY

MODEL FLIGHT CYCLE LOV FLIGHT HOUR LOV

767-200* 75,000 180,000 767-300**

767-300F 60,000 180,000 767-400ER

* 767-200 LOV applies to 767-200SF **767-300 LOV applies to 767-300BCF

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APPENDIX A – STRUCTURES BASELINE REQUIREMENTS

A. SCOPE

This appendix provides operators with the Baseline Structures and Zonal Inspection tasks that must be used upon the airplane reaching the fatigue threshold. This must be done in order to ensure the maintenance program complies with Title 14 CFR § 25.571 Damage Tolerance Requirements.

As such, when reaching the threshold the inspection interval must be the lesser of: 1) the FAA approved Structural and Zonal Inspection interval in the Operator baseline inspection program or 2) the inspection interval contained in this appendix.

The structures A-check and C-check interval, when reaching threshold, is defined in Section B of the baseline document.

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B. STRUCTURES BASELINE INSPECTION REQUIREMENTS

MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

EXTERNAL - GENERAL VISUAL: Bulk Cargo Compartment Door 3000 FC 52-402-00 ALL ALL Bulk cargo compartment door external surface, frame, hinges, and stops. 18 MO

EXTERNAL - GENERAL VISUAL: Forward Cargo Compartment Door 3000 FC 52-406-00 Large forward cargo door external surface and frame including hinges, latches, and fittings. ALL ALL Standard (70x69) Forward Cargo Door external surface and frames including hooks and door stops. 18 MO

EXTERNAL - GENERAL VISUAL: Aft Cargo Door 3000 FC 52-410-00 Large Aft Cargo Door external surface and frame including hinges, latches, and fittings. ALL ALL Standard (70x69) Aft Cargo Door external surface and frames including hooks and door stops. 18 MO

INTERNAL - GENERAL VISUAL: Entry & Galley Service Doors PASS Entry and galley service doors internal beams and frames. 12000 FC 52-412-00 200SF ALL 72 MO ACCESS NOTE: Passenger airplanes: Zone and access defined by each operator's door configuration. 300BCF

EXTERNAL - GENERAL VISUAL: Entry & Galley Service Doors PASS Entry and galley service door external surface, frame, latches, and continuous stops. 3000 FC 52-416-00 200SF ALL 18 MO ACCESS NOTE: Passenger airplanes: Zone and access defined by each operator's door configuration. 300BCF EXTERNAL - GENERAL VISUAL: Overwing Emergency Exit Hatch Overwing emergency hatch external surface, frame, latch and stops. 3000 FC ALL 52-418-00 ALL 18 MO NOTE AIRPLANE NOTE: Airplanes with overwing escape hatch configurations, including deactivated hatches. EXTERNAL - GENERAL VISUAL: Emergency Exit Door Emergency exit door external surface, frame, latch, and stops. 3000 FC ALL 52-422-00 ALL 18 MO NOTE AIRPLANE NOTE: Airplanes with emergency exit door.

INTERNAL - GENERAL VISUAL: Crew Entry Door 12000 FC 52-424-00 300F ALL Crew entry door internal beams and frames. 72 MO

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

EXTERNAL - GENERAL VISUAL: Crew Entry Door 3000 FC 52-428-00 300F ALL Crew entry door external surface, frame, latches, and continuous stops. 18 MO

200SF EXTERNAL - GENERAL VISUAL: Main Deck Cargo Door 3000 FC 52-430-00 300F ALL Main deck cargo door external surface and frame including hinges, latches, and fittings. 18 MO 300BCF INTERNAL - ZONAL (GV): Bulk Cargo Compartment Door Perform internal general visual inspection of zone. 24000 FH 52-800-00 ALL ALL 72 MO CPC NOTE: Corrosion Prevention and Control Basic Task required. INTERNAL - ZONAL (GV): Forward Cargo Compartment Door Perform internal general visual inspection of zone. 24000 FH ALL 52-806-00 ALL CPC NOTE: Corrosion Prevention and Control Basic Task required. 72 MO NOTE AIRPLANE NOTE: Airplanes with large forward cargo door. INTERNAL - ZONAL (GV): Forward Cargo Compartment Door Perform internal general visual inspection of zone. 24000 FH ALL 52-808-00 ALL CPC NOTE: Corrosion Prevention and Control Basic Task required. 72 MO NOTE AIRPLANE NOTE: Airplanes with standard forward cargo door. INTERNAL - ZONAL (GV): Aft Cargo Compartment Door Perform internal general visual inspection of zone. 24000 FH ALL 52-812-00 ALL CPC NOTE: Corrosion Prevention and Control Basic Task required. 72 MO NOTE AIRPLANE NOTE: Applicable to airplanes with Standard (70 x 69) Aft Cargo Door. INTERNAL - ZONAL (GV): Aft Cargo Compartment Door Perform internal general visual inspection of zone. 24000 FH ALL 52-814-00 ALL CPC NOTE: Corrosion Prevention and Control Basic Task required. 72 MO NOTE AIRPLANE NOTE: Airplanes with large aft cargo door. INTERNAL - ZONAL (GV): Overwing Emergency Exit Hatches - Left / Right Perform internal general visual inspection of the zones. 24000 FH ALL 52-824-00 ALL CPC NOTE: Corrosion Prevention and Control Basic Task required. 72 MO NOTE AIRPLANE NOTE: Dual overwing emergency exit configuration.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - ZONAL (GV): Overwing Emergency Exit Hatches - Left / Right Perform internal general visual inspection of zone. 200 CPC NOTE: Corrosion Prevention and Control Basic Task required. 24000 FH 52-826-00 200SF ALL 72 MO AIRPLANE NOTE: 767-200 Airplanes with single overwing emergency exit configuration and 200SF airplanes with NOTE deactivated single overwing emergency exit configuration. INTERNAL - ZONAL (GV): Overwing Emergency Exit Hatches - Left / Right Perform internal general visual inspection of zone. 24000 FH 300 52-832-00 ALL CPC NOTE: Corrosion Prevention and Control Basic Task required. 72 MO NOTE AIRPLANE NOTE: 767-300 Airplanes with single overwing emergency exit configuration.

INTERNAL - ZONAL (GV): Main Deck Cargo Compartment Door 200SF Perform internal general visual inspection of zone. 24000 FH 52-840-00 300F ALL 72 MO CPC NOTE: Corrosion Prevention and Control Basic Task required. 300BCF INTERNAL - ZONAL (GV): Emergency Exit Door - Left / Right Perform internal general visual inspection of the zone. 300 24000 FH 52-848-00 400E ALL CPC NOTE: Corrosion Prevention and Control Basic Task required. 72 MO AIRPLANE NOTE: 767-300 and 767-400ER airplanes with emergency exit doors. NOTE ACCESS NOTE: Remove emergency door lining/insulation. EXTERNAL - GENERAL VISUAL: Lower Half Of Fuselage - Exterior Body external skin between Body Station (BS) 132.5 and BS 1582 in major zone 100 with attention to: skin splices, areas of 53-400-91 attachments to BS 955.1 bulkhead, and areas within 12 inches of all cutouts (doors, hatches and equipment installations) and S 1C ALL ALL NOTE all antenna locations.

NOTE: This inspection can be accomplished concurrently with MPD item number 53-800-00. EXTERNAL - GENERAL VISUAL: Door Stops, Sills, and Frames 53-406-91 Door stops, sills, frames, and body external skin within 22 inches around door cutouts. S 1A ALL ALL NOTE 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. EXTERNAL - DETAILED: Large Forward Cargo Door Hinges Large forward cargo door hinges. ALL 53-408-00 S 1C ALL NOTE AIRPLANE NOTE: Airplanes with large forward cargo door.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

EXTERNAL - DETAILED: Door Stops and Cutouts 53-412-00 Door stops (if installed) and visible adjacent cutout structure within aircraft contour at all cargo door locations including door S 1C ALL ALL sills and frame chords.

INTERNAL - DETAILED: Body Station 132.5 Bulkhead 53-414-00 S 4C ALL ALL Body Station (BS) 132.5 Bulkhead.

INTERNAL - GENERAL VISUAL: Fuselage Lower Lobe 53-416-91 Control cabin floor beams, aft side of Body Station (BS) 132.5 bulkhead, and entire forward side of canted BS 168.5/188.5 bulkhead. S 2C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-416-00. INTERNAL - GENERAL VISUAL: Structure Forward of Nose Landing Gear Wheel Well 53-416-92 Forward access door outer frame, hinges, latch, and stops. S 1C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-804-00.

INTERNAL - DETAILED: Forward Equip Bay Access Door Cutout 53-418-00 Body skin, doubler, frames, adjacent to the access door cutout including fittings and back up structures, and forward S 4C ALL ALL equipment bay access door internal structure.

INTERNAL - GENERAL VISUAL: Nose Landing Gear Wheel Well Structure 53-428-91 Nose landing gear wheel well flat pressure panels with attention to areas of attachments to: frames and beams, nose landing gear trunnion and actuator attach fittings. S 1C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-806-00.

INTERNAL - GENERAL VISUAL: Area Outboard & Above Nose Wheel Well 53-430-00 Fuselage lower lobe interior body floor beams and nose landing gear wheel well flat pressure panels including the gear S 4C ALL ALL trunnion fitting, the aft lock link fitting, the drag brace fitting, and the actuator support beam fitting.

INTERNAL - DETAILED: Bulkhead and Nose Landing Gear Wheel Well 53-432-00 Body skin, bulkhead and nose landing gear wheel well side panel at intersection of the Body Station (BS) 287 bulkhead and S 4C ALL ALL the aft end of the nose landing gear wheel well side panel.

INTERNAL - GENERAL VISUAL: Fuselage Lower Lobe Interior 53-440-00 Fuselage lower lobe interior floor beams, seat tracks, Body Station (BS) 287 bulkhead, body skin, stringers, and frames from S 4C ALL ALL the lower surface of the cabin floor to Stringer S-36.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Forward Entry / Service Door Cutouts Body skin, doubler, stringers, frames and lower sill within 22 inches forward and aft of the forward entry and service door 53-442-00 cutouts between stringer S-20 to stringer S-23. S 4C ALL ALL

NOTE: This inspection also applies to the crew entry door on 767-300F.

INTERNAL - GENERAL VISUAL: Main Equipment Center Access Door 53-444-00 S 1C ALL ALL Main equipment center access door outer frame, stops, and latch.

INTERNAL - DETAILED: Main Equipment Center Body skin, stringers, and frames, from stringer S-36L to stringer S-36R and from 10 inches forward and 10 inches aft of the 53-446-00 S 4C ALL ALL main equipment center access door and lower portion of Body Station (BS) 287 bulkhead between Left Buttock Line (LBL) 40 and Right Buttock Line (RBL) 40.

INTERNAL - GENERAL VISUAL: Main Equipment Center Access Door 53-448-00 S 4C ALL ALL Main equipment center access door internal structure.

INTERNAL - GENERAL VISUAL: Forward Cargo Compartment Fuselage lower lobe interior structure, Body Station (BS) 355 to BS 738.5, between stringer S-20 and S-32 including, body 53-452-91 skin, stringers, skin splices, stringer splices and frames from lower surface of cabin floor to upper surface of cargo floor on the S 4C ALL ALL NOTE left 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 (Right). INTERNAL - DETAILED: Mid-Cabin Entry/Service Door Cutouts Body skin, doubler, stringers, frames and lower sill within 22 inches forward and aft of the mid-cabin entry/service door 53-452-92 cutouts between stringer S-20 and S-23. ALL S 4C ALL NOTE AIRPLANE NOTE: Airplanes with mid cabin doors. NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-452-00 (Left) and 53-454-00 (Right), except detailed inspection is required. INTERNAL - DETAILED: Main Deck Cargo Door Cutout Body skin, doubler, stringers, frames, intercostals, fittings and lower sill within 14 inches forward and 22 inches aft of the main 200SF 53-452-93 deck cargo door cutout between stringer S-20 and S-23. S 4C 300F ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-452-00, except detailed inspection is 300BCF required.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Forward Cargo Compartment Door Cutout 53-454-91 Body skin, doubler, stringers and intercostals within 22 inches forward and aft of the forward cargo compartment door cutout. S 4C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-454-00, except detailed inspection is required.

INTERNAL - DETAILED: Forward Cargo Compartment Door Cutout 53-456-00 S 2C ALL ALL Forward cargo door cutout lower main sill upper and lower surface.

INTERNAL - DETAILED: Forward Cargo Compartment Door Cutout 53-458-00 S 4C ALL ALL Edge frames of the forward cargo compartment door cutout.

INTERNAL - DETAILED: Body Below Forward Cargo Compartment Floor Lower lobe interior body skin, stringers, keel beam extension, roller trays, and frames from upper surface of cargo floor to Buttock Line (BL) 0.0, including area within 22 inches of the forward cargo compartment door cutout lower main sill.

53-460-00 ACCESS NOTE: No permanently attached structure is to be removed to accomplish this inspection. Several configurations of S 4C ALL ALL electronics bay cooling skin heat exchangers have been installed between Body Station (BS) 434 and 522, S-32L to S-33L. These heat exchangers cover various structures in this area. As an alternative to removal of the heat exchanger, access for this inspection may be gained by removing the lower plenum and by loosening and lifting the lower edge of the heat exchanger. Viewing aids will be required if using this technique. INTERNAL - GENERAL VISUAL: Area Aft of Forward Cargo Compartment 53-474-91 Fuselage lower lobe interior, Body Station (BS) 738.5 to BS 785.9, stringer S-20 to stringer S-35, body floor beams, body skin, bulkheads, stringers, frames, and overwing and underwing longeron extensions. S 4C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-474-00.

INTERNAL - DETAILED: Keel Beam Extension 738.5 - 785.9 53-478-00 S 4C ALL ALL Keel beam extension chords and body skin, stringers, and frames between stringer S-35L and stringer S-35R.

INTERNAL - DETAILED: Body Station 785.9 Bulkhead Inner Chord 53-480-00 S 4C ALL ALL Body Station (BS) 785.9 bulkhead inner chord between stringers S-20 and stringer S-21.

INTERNAL - GENERAL VISUAL: Front Spar Bulkhead Below Floor 53-482-00 Wing front spar bulkhead and side of body splice, including area of attachment of body skin to front spar and vertical stiffeners S 4C ALL ALL in area of lower front spar chord.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Wing Center Section Upper Surface Structure below floor between Body Station (BS) 786 and BS 955.1 and wing center section upper surface including: body 53-496-00 S 4C ALL ALL skin. Body frames and BS 786 and BS 955.1 bulkheads, forward and aft sides. Side of body splice chord. BS 786 skin/ stringer circumferential splice. INTERNAL - GENERAL VISUAL: Structure above Wing Center Section Upper Skin and Main Landing Gear Wheel Well Pressure Deck 53-496-91 Longitudinal floor beams, cargo tracks, intercostals, horizontal shear webs and cargo floor fitting support structure from the upper surface of the cabin floor to the lower surface of the cabin floor, Body Station (BS) 785.9 to 1065. S 4C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-824-00, 53-826-00, 53-834-00 or 53-836-00.

INTERNAL - GENERAL VISUAL: Keel Beam & Wing Center Section 53-502-00 Keel beam webs including shear web at Body Station (BS) 863, Stiffeners, and chords; and wing center section lower surface S 1C ALL ALL and body bulkheads at BS 785.9 and BS 955.1.

INTERNAL - DETAILED: Wing Center Section Tension Fitting 53-504-00 Tension fitting installation on the wing center section lower surface at Buttock Line (BL) 0 from the rear spar to wing stringer S 1C ALL ALL S-1L.

INTERNAL - DETAILED: Below Floor Structure - Body Station 955 to 1065 Structure below floor between Body Station (BS) 955 and BS 1065 including: floor beams; body frames and BS 1065 bulkhead, forward and aft sides; pressure deck; BS 1065 skin/stringer circumferential splice; main landing gear support fitting 53-508-00 S 4C ALL ALL attachment at BS 1043.

ACCESS NOTE: Cabin equipment from BS 955 to BS 1065. INTERNAL - GENERAL VISUAL: Left / Right Main Wheel Well 53-518-91 Main landing gear wheel well structure with attention to wing rear spar. Body bulkhead at Body Station (BS) 1065, body frames, keel beam, pressure deck, main landing gear beam support fitting at BS 1043, overwing longeron. S 1C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-838-00. 300 INTERNAL - DETAILED: Transverse Beams 300BCF 53-520-00 Transverse beam lower chords at Body Station (BS) 999 between Buttock Line (BL) 22 and BL 33, BS 1021 between S 1C ALL BL 0 and BL 69, and BS 1043 between BL 0 and BL 42. 300F 400E

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Rear Spar Bulkhead At Wheel Well 53-524-00 Body Station (BS) 955.1 rear spar bulkhead and wing rear spar terminal fitting between Buttock line (BL) 62 and Wing Buttock S 1C ALL ALL Line (WBL) 97.9 including spar web adjacent to fitting, rear spar lower chord splice and overwing longeron.

INTERNAL - DETAILED: Transverse Beams At Main Wheel Wells 200 53-526-00 Transverse beam lower chords at Body Station (BS) 1021 between Buttock Line (BL) 20 and BL 69 and BS 1043 between S 1C ALL BL 0 and BL 14. 200SF

INTERNAL - DETAILED: Rear Spar At Keel Beam 53-528-00 S 1C ALL ALL Wing rear spar at Buttock Line (BL) 0 in area of attachment to the keel beam.

INTERNAL - GENERAL VISUAL: Keel Beam - Aft Section 53-540-91 Keel beam chords, webs, stiffeners, Body Station (BS) 955.1 to BS 1081, and body bulkhead at BS 1081. S 4C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-540-00.

INTERNAL - GENERAL VISUAL: Body Forward of Aft Cargo Compartment 53-542-00 Floor beams, seat tracks; body skin, stringers, frames, splices & Body Station (BS) 1065 bulkhead from lower surface of cabin S 4C ALL ALL floor to stringer S-32.

INTERNAL - DETAILED: Body Forward of Aft Cargo Compartment 53-544-91 Buttock Line (BL) 26 and BL 47 intercostals; keel beam extension chords and body skin, stringers, frames, splices and Body Station (BS) 1065 bulkhead outer chord between stringer S-32L and stringer S-32R. S 4C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-544-00 (Left) and 53-548-00 (Right). INTERNAL - DETAILED: Emergency Exit Door Cutout Body skin, doubler, stringers, frames, and lower sill within 22 inches forward and aft of the emergency exit door cutouts 300 53-550-91 between stringer S-20 and stringer S-23. 300BCF S 4C ALL NOTE AIRPLANE NOTE: Airplanes with Type I emergency exit doors. 400E NOTE: This inspection can be accomplished concurrently with MPD item number 53-550-00, except detailed inspection is NOTE required. INTERNAL - GENERAL VISUAL: Aft Cargo Compartment Fuselage lower lobe interior structure, Body Station (BS) 1088.7 to BS 1404, between stringer S-20 and S-32 including, body 53-552-91 skin, stringers, skin splices, stringer splices and frames from lower surface of cabin floor to upper surface of cargo floor on left S 4C ALL ALL NOTE and right hand sides of the airplane.

NOTE: This inspection can be accomplished concurrently with MPD item number 53-552-00.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Aft Cargo Compartment Body skin, doubler, stringers, intercostals and frames within 22 inches forward and aft of the aft cargo compartment door 53-552-92 cutout. S 4C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-552-00, except detailed inspection is required.

INTERNAL - DETAILED: Aft Cargo Compartment Door Cutout 53-554-00 S 2C ALL ALL Aft cargo door cutout lower main sill upper and lower surface.

INTERNAL - DETAILED: Aft Cargo Compartment Door Cutout 53-556-00 S 4C ALL ALL Edge frames of the aft cargo compartment door cutout.

INTERNAL - DETAILED: Body Below Aft Cargo Compartment Floor Lower lobe interior, body skin, stringers, roller trays, skin splices, stringer splices and frames from upper surface of cargo floor 53-558-00 to Buttock Line (BL) 0.0 including area within 22 inches of the aft cargo compartment door cutout lower main sill. S 4C ALL ALL

ACCESS NOTE: No permanently attached structure is to be removed to accomplish this inspection. INTERNAL - GENERAL VISUAL: Bulk Cargo Compartment Fuselage lower lobe interior structure, Body Station (BS) 1404 to BS 1540, between stringer S-20 and S-32 including body 53-572-91 skin, stringers, skin splices, and frames from lower surface of cabin floor to upper surface of cargo floor on the left and right S 4C ALL ALL NOTE hand sides of the airplane.

NOTE: This inspection can be accomplished concurrently with MPD item number 53-572-00. INTERNAL - DETAILED: Bulk Cargo Compartment Door Cutout Body skin, doubler, stringers, intercostals, frames, and upper sill within 22 inches forward and aft of bulk cargo compartment 53-572-92 door cutout. S 4C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-572-00, except detailed inspection is required.

INTERNAL - DETAILED: Bulk Cargo Door Lower Sill 53-574-00 S 2C ALL ALL Bulk cargo door cutout lower sill upper surface.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Aft Entry / Service Door Cutouts PASS 53-582-00 Lower lobe interior body skin, doubler, stringers, frames, and lower sill within 22 inches forward and aft of the aft entry and S 4C 200SF ALL service door cutouts between stringer S-20 and stringer S-23. 300BCF INTERNAL - DETAILED: Bulk Cargo Compartment Below Floor Lower lobe interior body skin from Body Station (BS) 1404 to BS 1540, between stringer S-32L and S-32R, including skins, 53-584-91 stringers, and frames from upper surface of cargo floor to BL 0, with attention to area within 22 inches of the bulk cargo S 4C ALL ALL NOTE compartment door cutout lower main sill.

NOTE: This inspection can be accomplished concurrently with MPD item numbers 53-584-00 (Left) and 53-586-00 (Right). INTERNAL - GENERAL VISUAL: Fuselage Lower Lobe Interior Fuselage lower lobe interior structure, Body Station (BS) 1540 to BS 1629, between 53-588-91 stringer S-20 and stringer S-28, including forward side of pressure dome. S 4C ALL ALL NOTE ACCESS NOTE: Waste tank removal is recommended in order to facilitate inspection. NOTE: This inspection can be accomplished concurrently with MPD item number 53-588-00. INTERNAL - DETAILED: Body Below Floor - Rear Pressure Dome Body skin, stringers, frames, Body Station (BS) 1582 skin/stringer splice, and forward side of the pressure dome from stringer 53-592-91 S-28 to Buttock Line (BL) 0. S 4C ALL ALL NOTE ACCESS NOTE: Waste and potable water tank removal, if installed, is recommended in order to facilitate inspection. NOTE: This inspection can be accomplished concurrently with MPD item number 53-592-00.

INTERNAL - GENERAL VISUAL: Upper Wing / Side Of Body Splice 53-602-00 S 2C ALL ALL Wing upper surface and side of body splice normally covered by the fairing between Body Station (BS) 785.9 and BS 955.1.

INTERNAL - DETAILED: Overwing Longeron 53-606-00 S 2C ALL ALL Overwing longeron in areas of attachments at Body Station (BS) 859.5, BS 883.5 and BS 911.

INTERNAL - GENERAL VISUAL: Wing Lower Surface Buttock Line 62 - Fairing Edge Lower wing surface between Buttock Line (BL) 62 and outboard edge of wing/body fairing including side of body splice, wing 53-614-00 S 2C ALL ALL front spar splice, bulkhead at Body Station (BS) 785.9 and body skin normally covered by the fairing from forward edge of fairing to BS 955.1 and the portion of the outboard wing lower panel normally concealed by the fairings.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Lower Side of Body Splice Plates 53-616-00 S 1C ALL ALL Side of body splice plates in areas of attachment to the lower wing surface between the rear spar and stringer S-10L.

INTERNAL - DETAILED: Wing Center Section Lower Surface At Rear Spar Chord and Splice Stringers 53-618-00 Lower external wing surface at the rear spar chord and splice stringer L-6 and splice stringer L-10 from Buttock Line (BL) 62.0 S 1C ALL ALL to outboard edge of wing/body fairing.

INTERNAL - DETAILED: Wing Center Section Lower Surface At Rear Spar Chord and Splice Stringers 53-618-91 Lower external wing surface at the rear spar chord and splice stringer L-6 and splice stringer L-10 from Left Buttock Line S 1C ALL ALL (LBL) 62.0 to Right Buttock Line (RBL) 62.0.

INTERNAL - DETAILED: Wing Lower Rear Spar Splice Fitting 53-620-00 S 1C ALL ALL Wing lower surface rear spar splice fitting at Wing Buttock Line (WBL) 97.9.

INTERNAL - DETAILED: Buttock Line 70 Underwing Longeron Fitting 53-622-00 S 1C ALL ALL Buttock Line (BL) 70 underwing longeron fitting installation.

INTERNAL - GENERAL VISUAL: Wing-to-body Fairing 53-634-00 Body skin and outboard wing upper panel normally covered by the wing/body fairing from Body Station (BS) 955.1 to aft edge S 2C ALL ALL of fairing.

INTERNAL - GENERAL VISUAL: Wing To Body Fairings - Aft Left / Right 53-634-91 Support structure for inboard flap mechanisms. S 1C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-870-00. EXTERNAL - GENERAL VISUAL: Upper Half of Fuselage - Exterior Control cabin windshields, cabin windows and body external skin between Body Station (BS) 132.5 and BS 1582 in major 53-642-91 zone 200 with attention to: skin splices, areas of attachments to BS 955.1 bulkhead, and areas within 12 inches of all cutouts S 1C ALL ALL NOTE (doors, hatches, windows and equipment installations) and all antenna locations.

NOTE: This inspection can be accomplished concurrently with MPD item number 53-872-00. EXTERNAL - GENERAL VISUAL: Deactivated Door Cutouts 53-648-91 Body external skin within 22 inches around deactivated door cutouts. S 1A ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-648-00.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

EXTERNAL - DETAILED: Door Stops And Cutouts Door stops and visible adjacent cut-out structure within aircraft contour at all door locations (cabin entry/service, and 53-650-00 emergency) including section 41 access doors and visible adjacent support and cutout structure at No. 2 Cockpit window. S 1C ALL ALL

ACCESS NOTE: Zone and Access defined by each airplanes door configuration. INTERNAL - DETAILED: Control Cabin Windshield Structure Control cabin windshields and visible portions of window posts and sills after accessed.

53-654-91 INTERVAL NOTE: This task should also be performed at windshield and window replacement. S 4C ALL ALL NOTE ACCESS NOTE: Removal of readily removed sidewall panels required. Removal of overhead dripshield, glare panel, NOTE windows, 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 inspection is required.

INTERNAL - GENERAL VISUAL: Control Cabin Floor Structure 53-656-00 S 2C ALL ALL Control cabin floor structure.

INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior Structure Fuselage upper lobe interior structure, Body Station (BS) 243.5/246 to BS 434, between stringer S-20 and stringer S-12, including lap joints, circumferential joints, window forgings, bonded tear straps, stringer splices, frames and sills within 53-662-91 22 inches of doors, door cutout structure, and horizontal shear web. S 4C ALL ALL NOTE ACCESS NOTE: Outboard equipment, sidewall panels and movable ceiling panels to be removed (for freighters only). Removal 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. INTERNAL - DETAILED: Forward Entry and Service Door Cutouts Body skin, doubler, stringers, frames, and upper sill within 22 inches of the forward entry and service door cutouts. 53-662-92 ACCESS NOTE: Outboard equipment, sidewall panels and movable ceiling panels. S 4C ALL ALL NOTE 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 inspection is required. INTERNAL - GENERAL VISUAL: Cargo Floor Structure - Shear Web Rigid cargo barrier attachment structure to fuselage and floor from stringer S-9 to the floor and horizontal shear web, Body 200SF 53-670-91 Station (BS) 266 to BS 412. S 4C 300F ALL NOTE ACCESS NOTE: Cargo compartment floor panel removal required. Removal of rigid barrier, fittings, and drain trough not 300BCF required. NOTE: This inspection can be accomplished concurrently with MPD item number 53-670-00.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior Structure Fuselage upper lobe interior structure, Body Station (BS) 243.5/246 to BS 434, between stringer S-12 and Buttock Line (BL) 0.0, including lap joints, circumferential joints, bonded tear straps, stringer splices, and rigid cargo barrier attachment structure ALL 53-678-00 to fuselage from BL 0 to stringer S-9. S 4C ALL NOTE AIRPLANE NOTE: Inspection is applicable to all aircraft. However, rigid cargo barrier is installed only on 200SF, 300F, and 300BCF. INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior Fuselage upper lobe interior structure, including the main deck floor structure, Body Station (BS) 434 to BS 785.9, between stringer S-12 and stringer S-20, including 53-682-91 lap joints, circumferential joints, window forgings, bonded tear straps, stringer S 4C ALL ALL NOTE splices, 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 (Right). 200SF INTERNAL - DETAILED: Main Deck Cargo Door Cutout Sill 53-686-00 S 2C 300F ALL Main deck cargo door cutout lower sill upper surface. 300BCF INTERNAL - DETAILED: Mid Entry / Service Door Cutouts Body skin, doubler, stringers, frames, intercostals, and upper sill within 22 inches of the mid entry and service door cutouts. 53-688-91 ALL AIRPLANE NOTE: Airplanes with mid cabin doors. S 4C ALL NOTE ACCESS NOTE: Outboard equipment, sidewall panels and moveable ceiling panels. NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 53-688-00, except detailed inspection is required. INTERNAL - DETAILED: Main Deck Cargo Door Cutout Body skin, doubler, stringers, frames, intercostals, fittings and upper sill within 14 inches forward and 22 inches aft of the main 200SF 53-690-91 deck cargo door cutout. S 4C 300F ALL NOTE ACCESS NOTE: Outboard equipment, sidewall panels, and movable ceiling panels. 300BCF NOTE: This inspection can be accomplished concurrently with MPD item number 53-690-00, except detailed inspection is required.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Fuselage Upper Lobe Interior Near Forward Cargo Door Body skin, doubler, stringers, intercostals, fittings, frames, and upper sill within 22 inches forward and aft of the forward cargo 53-692-91 compartment door cutout from stringer S-17 to stringer S-20. S 4C ALL ALL NOTE 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 inspection is required.

INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior 53-698-00 Fuselage upper lobe interior structure Body Station (BS) 434 to BS 785.9, between stringer S-12L and Buttock Line (BL) 0.0, S 4C ALL ALL including lap joints, circumferential joints, frames, bonded tear straps, stringer splices.

INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior 53-700-00 Fuselage upper lobe interior structure, Body Station (BS) 434 to BS 785.9, between stringer S-12R and Buttock Line (BL) 0.0, S 4C ALL ALL including lap joints, circumferential joints, frames, bonded tear straps, stringer splices.

INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior Structure Fuselage upper lobe interior structure, Body Station (BS) 785.9 to BS 1065, between stringer S-12 and the upper surface of the pressure deck/wing center section, including lap joints, circumferential joints, window forgings, bonded tear straps, 53-704-91 stringer splices, frames and sills within 22 inches of doors and escape hatches, stub beam to wing upper panel interface, and S 4C ALL ALL NOTE hatch cutout structure, and body window forgings in areas of attach fasteners between BS 785.9 and BS 1065.

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. INTERNAL - GENERAL VISUAL: Cabin Above Ceiling Body Station 785-1065 Fuselage upper lobe interior structure, Body Station (BS) 785.9 to BS 1065, between stringer S-12L and stringer S-12R, 53-706-00 S 4C ALL ALL including lap joints, circumferential joints, bonded tear straps, stringer splices. Body bulkhead and adjacent skin and stringer splices at BS 785.9, BS 955, and BS 1065 (forward and aft sides) between stringer S-12L and stringer S-12R. INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior Fuselage upper lobe interior structure, Body Station (BS) 1065 to BS 1636, between stringer S-20 and S-12, including lap 53-710-91 joints, circumferential joints, window forgings, bonded tear straps, stringer splices, frames and sills within 22 inches of doors, S 4C ALL ALL NOTE forward 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 53-714-00 (Right).

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Fuselage Upper Lobe Interior Body skin, doubler, stringers, intercostals, frames, fittings, and upper sill within 22 inches of the aft cabin entry and service 200 53-710-92 door cutouts. 300 S 4C ALL NOTE 300BCF NOTE: This inspection can be accomplished concurrently with MPD item numbers 53-710-00 (Left) and 53-714-00 (Right), 400E except detailed inspection is required. INTERNAL - DETAILED: Fuselage Upper Lobe Interior Body skin, doubler, stringers, intercostals, frames, stops, fittings, and upper sill within 22 inches of the emergency exit door 300 53-710-93 cutouts. 300BCF S 4C ALL NOTE AIRPLANE NOTE: airplanes with Type I emergency exit doors. 400E NOTE: This inspection can be accomplished concurrently with MPD item numbers 53-710-00 (Left) and 53-714-00 (Right), NOTE except detailed inspection is required. INTERNAL - DETAILED: Fuselage Upper Lobe Interior Body skin, doubler, stringers, intercostals, frames, fittings and upper sill within 22 inches forward and aft of aft cargo 53-714-91 compartment door cutout from stringer S-17 to stringer S-20. S 4C ALL ALL NOTE 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 inspection is required. INTERNAL - GENERAL VISUAL: Fuselage Upper Lobe Interior Structure Fuselage upper lobe interior structure, Body Station (BS) 1065 to BS 1636, between stringer S-12L and stringer S-12R, including lap splices, circumferential joints, frames, bonded tear straps, stringer splices, and forward side of BS 1582 aft 53-720-00 S 4C ALL ALL pressure bulkhead.

ACCESS NOTE: Ceiling panels from BS 1065 to BS 1636.

INTERNAL - DETAILED: Forward and Aft Sides of Body Station 1702 - 1725.5 Bulkheads 53-726-00 Forward and aft sides of Body Station (BS) 1702 and BS 1725.5 bulkheads between Left Buttock Line (LBL) 15 and Right S 2C ALL ALL Buttock Line (RBL) 15.

INTERNAL - DETAILED: Horizontal Stabilizer Trim Actuator Support 53-728-00 S 2C ALL ALL Horizontal stabilizer trim actuator support fitting in area of lugs and attachment to Body Station (BS) 1702 bulkhead.

EXTERNAL - GENERAL VISUAL: Exterior Section 48, Left / Right Side 53-730-00 S 2C ALL ALL Exterior of section 48, Body Station (BS) 1582 through BS 1832/1843.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Aft Pressure Bulkhead - Body Station 1582 53-732-00 Aft pressure bulkhead, Body Station (BS) 1582, aft surface for damage; dents, scratches, nicks, gouges or corrosion, S 2C ALL ALL including cracks at splices, doublers, and around all cutouts.

INTERNAL - SPECIAL DETAILED: Vertical Stabilizer Attach Bolt 53-734-00 S 4C ALL ALL Vertical stabilizer attach bolts (14 bolts in zone 311/312 and 2 bolts in zone 313/314).

INTERNAL - DETAILED: Horizontal Stabilizer Pivot Fittings 53-746-00 Horizontal stabilizer pivot fittings in areas of attachment to the Body Station (BS) 1809.5 bulkhead, lugs for pivot pin, the S 2C ALL ALL backup fittings, and the pivot nut lockwire.

INTERNAL - DETAILED: Body Longerons At Horizontal Stabilizer Cutout 53-748-00 S 2C ALL ALL Body upper and lower longerons adjacent to the horizontal stabilizer cutout.

INTERNAL - GENERAL VISUAL: Power Plant Strut (GE Configuration) Power Plant strut, including pylon skin, spars, struts, braces, attach fittings, lugs, pins, engine cowlings and wing fittings (GE configuration). 80A 54-400-00 Task notes: S 4C ALL 1) Inspect visible structure with pylon in place. 80C 2) Engine removal not required for this inspection. 3) Service Bulletin reference: Service Bulletin 767-54-0052. 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 wing fittings (P&W configuration). 4000 54-402-00 Task notes: S 4C ALL 1) Inspect visible structure with pylon in place. 7R4 2) Engine removal not required for this inspection. 3) Service Bulletin reference: Service Bulletin 767-54-0052.

INTERNAL - GENERAL VISUAL: Power Plant Strut 54-404-00 Power Plant strut, including pylon skin, spars, struts, braces, attach fittings, lugs, pins, engine cowlings, and wing fittings. S 12C ALL ALL Task Note: Inspect all fittings, including wing fittings with pylon dropped.

4000 EXTERNAL - GENERAL VISUAL: Nacelle Strut No. 1 / 2 7R4 54-406-00 S 1A ALL Nacelle strut. 80A 80C

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

4000 EXTERNAL - GENERAL VISUAL: No. 1 / 2 Nacelle Strut 7R4 54-408-00 S 1C ALL Nacelle strut skin and aft strut fairing including areas of attachment to: bulkhead and frames. Spars and stringers. 80A 80C 4000 EXTERNAL - DETAILED: Nacelle Strut No. 1 / 2 7R4 54-410-00 S 2C ALL Nacelle strut skin (under side strut fairing) in area of attachment to the strut mid bulkhead and spar. 80A 80C

INTERNAL - DETAILED: Strut 1 / 2 Lower Spar and Engine Mounts 54-412-00 Lower spar chords, webs, thrust plate and forward and aft engine mount bulkheads. Diagonal brace, strut attach fitting and S 1C ALL 524 associated fuse pins. Forward and aft engine mount fittings, links, and attach bolts.

INTERNAL - DETAILED: Strut 1 / 2 Lower spar chords and thrust plate. Diagonal brace, strut attach fittings and fuse pins. Forward and aft engine mount fittings, ENG CNG 54-414-00 links, and attach bolts (including dye penetrant inspection of attach bolts). ALL 524 <1> ACCESS NOTE: At engine removal. INTERNAL - GENERAL VISUAL: Strut 1 / 2 Forward and aft engine mount bulkheads. ENG CNG 54-416-00 ALL 524 <1> ACCESS NOTE: At engine removal. 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 fittings (RR configuration). 54-418-00 Task Notes: S 4C ALL 524 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.

EXTERNAL - GENERAL VISUAL: Strut 1 / 2 54-422-00 S 1A ALL 524 Visible external portions of strut.

4000 INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Forward Upper Spar 7R4 54-424-00 S 3C ALL Nacelle strut forward upper spar, upper link and upper link attach fitting. 80A 80C

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

4000 INTERNAL - GENERAL VISUAL: Nacelle Strut No. 1 / 2 - Forward Torque Box 7R4 54-426-00 S 3C ALL Nacelle strut forward torque box stiffeners, skins, spars, frames and mid bulkhead. 80A 80C 4000 INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 - Forward Torque Box 7R4 54-428-00 Nacelle strut mid spar (lower spar of forward torque box) chords in areas of attachments, and nacelle strut forward engine S 3C ALL mount bulkhead. 80A 80C

INTERNAL - GENERAL VISUAL: Strut 1 / 2 Upper Spar 54-430-00 S 1C ALL 524 Upper spar chords, webs and stiffeners.

INTERNAL - DETAILED: Strut 1 / 2 Upper Link Upper link, strut attach fitting and fuse pins. Aft upper spar fitting and fuse pins. ALL 54-432-00 S 1C 524 AIRPLANE NOTE: SB 767-54-0082. This task is applicable to airplanes prior to line number 702 which have not incorporated NOTE this service bulletin. INTERNAL - DETAILED: Strut 1 / 2 Upper Link Upper link, strut attach fitting and fuse pins. Aft upper spar fitting and fuse pins. ALL 54-434-00 S 2C 524 AIRPLANE NOTE: SB 767-54-0082. This task is applicable to airplanes line numbers 702 and on or those which have NOTE incorporated this service bulletin. 4000 INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Mid-spar Fitting Nacelle strut outboard mid-spar fitting forward upper ALL 7R4 54-436-00 tang.AIRPLANE NOTE: SB 767-54-0080 (P&W) and SB 767-54-0081 (GE). This task is applicable to airplanes prior to line S 1C number 665 (GE) and 664 (P&W) which have not incorporated this service bulletin. NOTE 80A 80C INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Upper Link Nacelle strut upper link forward attach fitting and upper link including the forward attach lug. 4000 7R4 54-438-00 S 1C ALL ACCESS NOTE: Access Panel 431ET applicable to 7R4 and 4000 engines only. Access Panel 432ET applicable to 80A and 80A 80C engines only. 80C Access Panel 441ET applicable to 7R4 and 4000 engines only. Access Panel 442ET applicable to 80A and 80C engines only.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Mid-spar Fitting 4000 Nacelle strut outboard mid-spar fitting forward upper tang. ALL 7R4 54-440-00 S 3C AIRPLANE NOTE: SB 767-54-0080 (P&W) and SB 767-54-0081 (GE). This task is applicable to airplanes line numbers 665 NOTE 80A and on (GE) and 664 and on (P&W) or those which have incorporated this service bulletin. 80C

INTERNAL - DETAILED: Strut 1 / 2 Torque Box 54-442-00 Upper spar chords, webs, stiffeners, and backup chords. Lower spar chords and webs. Thrust plate, forward engine mount S 1C ALL 524 bulkhead, and aft upper spar fitting and fuse pins.

INTERNAL - GENERAL VISUAL: Strut 1 / 2 Aft Torque Box 54-444-00 Side skin stiffeners and backup chords, mid bulkhead, aft engine mount bulkhead, and aft strut bulkhead, diagonal brace, S 1C ALL 524 strut attach fittings and fuse pins, side link and strut attach fittings.

4000 INTERNAL - GENERAL VISUAL: Nacelle Strut - Mid & Aft Torque Box 7R4 54-446-00 S 2C ALL Nacelle strut mid and aft torque box stiffeners, spars, frames, bulkheads, and fittings. 80A 80C 4000 INTERNAL - DETAILED: Strut No. 1 / 2 Aft Engine Mount Bulkhead 7R4 54-448-00 S 2C ALL Nacelle strut No. 1 and No. 2 aft engine mount support bulkhead. 80A 80C INTERNAL - DETAILED: Strut 1 / 2 Aft Torque Box Aft strut bulkhead, diagonal brace, strut attach fitting and fuse pins. Aft upper spar fitting, fuse pins, lug area of strut attach fitting, side links and side load fittings. ALL 54-450-00 S 1C 524 NOTE AIRPLANE NOTE: SB 767-54-0082. This task is applicable to airplanes prior to line number 702 which have not incorporated this service bulletin. INTERNAL - DETAILED: Strut 1 / 2 Aft Torque Box Aft strut bulkhead, diagonal brace, strut attach fitting and fuse pins. Aft upper spar fitting, fuse pins, lug area of strut attach fitting, side links and side load fittings, strut attach fitting. ALL 54-452-00 S 1C 524 NOTE AIRPLANE NOTE: SB 767-54-0082. This task is applicable to airplanes line numbers 702 and on or those which have incorporated this service bulletin.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Mid Spar Fitting Visible portions of nacelle strut mid spar fitting forward lower tangs (inboard and outboard), vertical tang and diagonal brace 4000 attach fitting above strut firewall. ALL 7R4 54-458-00 S 2C NOTE 80A AIRPLANE NOTE: SB 767-54-0080 (P&W) and SB 767-54-0081 (GE). This task is applicable to airplanes prior to line number 80C 665 (GE) and 664 (P&W) which have not incorporated this service bulletin. INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Mid Spar Fitting Visible portions of nacelle strut mid spar fitting forward lower tangs (inboard and outboard), vertical tang and diagonal brace 4000 attach fitting above strut firewall. ALL 7R4 54-460-00 S 3C NOTE 80A AIRPLANE NOTE: SB 767-54-0080 (P&W) and SB 767-54-0081 (GE). This task is applicable to airplanes line numbers 665 80C and on (GE) and 664 and on (P&W) or those which have incorporated this service bulletin. INTERNAL - DETAILED: Left / Right Nacelle Strut Mid Spar Fitting Nacelle strut mid spar fittings (wing and strut), side load links, side link attach fittings, diagonal brace attach fittings (wing and 4000 strut) and aft torque box bulkhead. ALL 7R4 54-462-00 S 1C NOTE 80A AIRPLANE NOTE: SB 767-54-0080 (P&W) and SB 767-54-0081 (GE). This task is applicable to airplanes prior to line number 80C 665 (GE) and 664 (P&W) which have not incorporated this service bulletin. INTERNAL - DETAILED: Left / Right Nacelle Strut Mid Spar Fitting Nacelle strut mid spar fittings (wing and strut), side load links, side link attach fittings, diagonal brace attach fittings (wing and 4000 strut) and aft torque box bulkhead. ALL 7R4 54-464-00 S 3C NOTE 80A AIRPLANE NOTE: SB767-54-0080 (P&W) and SB767-54-0081 (GE). This task is applicable to airplanes line numbers 665 80C and on (GE) and 664 and on (P&W) or those which have incorporated this service bulletin.

INTERNAL - GENERAL VISUAL: Left / Right Nacelle Strut / Wing Lower Surface 54-466-00 S 1C ALL ALL Wing lower inspar surface including nacelle fairing supports including nacelle support fittings.

INTERNAL - DETAILED: Left / Right Nacelle Strut / Wing Lower Surface 54-468-00 Wing lower inspar skin at splice stringers L-6, L-10, and L-15, front and rear spar chords, and in areas adjacent to nacelle S 1C ALL ALL strut attach fittings and nacelle fairing attach angles.

INTERNAL - ZONAL (GV): Underwing Fairing - Strut 1 / 2 Perform internal general visual inspection of zones. (EZAP <2>) 54-804-00 CPC NOTE: Corrosion Prevention and Control Basic Task required S 1C ALL 7R4

INTERVAL NOTE: The EZAP inspection requirement with interval 24000 FH or 72 MO is satisfied by this zonal inspection.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - ZONAL (GV): Underwing Fairing - Strut 1 / 2 Perform internal general visual inspection of zones. (EZAP <2>) 54-816-00 CPC NOTE: Corrosion Prevention and Control Basic Task required. S 1C ALL 80

INTERVAL NOTE: The EZAP inspection requirement with interval 24000 FH or 72 MO is satisfied by this zonal inspection. INTERNAL - ZONAL (GV): Underwing Fairing - Strut 1 / 2 Perform internal general visual inspection of zones. (EZAP <2>) 54-828-00 S 1C ALL 4000 INTERVAL NOTE: The EZAP inspection requirement with interval 24000 FH or 72 MO is satisfied by this zonal inspection.

EXTERNAL - ZONAL (GV): Strut No. 1 / 2 54-838-00 Perform external general visual inspection of the zone (including fairings). S 1C ALL 524 CPC NOTE: Corrosion Prevention & Control Basic Task required.

INTERNAL - DETAILED: Vertical Stabilizer Fixed Leading Edge 55-406-00 Body skin within vertical stabilizer fixed leading edge in area of attachment to Body Station (BS) 1629 and BS 1654.5 S 4C ALL ALL bulkheads and stringers S-2L and S-2R, and vertical stabilizer fin-to-body fittings on forward side of front spar.

INTERNAL - GENERAL VISUAL: Vertical Stabilizer Front Spar To Rear Spar 55-410-00 Vertical stabilizer left and right surfaces, front and rear spars, and inspar ribs between rib 10 (Fin Station 225) and the S 4C ALL ALL stabilizer tip rib including spar webs.

INTERNAL - GENERAL VISUAL: Vertical Stabilizer - Front Spar To Rear Spar Vertical stabilizer left and right surfaces, front and rear spars, and inspar ribs between the fin-body deck and rib 10 (fin sta. 55-410-91 225) including front and rear spar webs, rear spar chords, stringer S-6, fin-body deck around cutouts and areas of attachment to body frames at Body Station 1654, 1678, 1702, and 1725, rib webs around cutouts, rib shear ties, and rib attach posts to S 2C ALL ALL NOTE front and rear spars.

NOTE: This inspection can be accomplished concurrently with MPD item number 55-816-00. INTERNAL - GENERAL VISUAL: Vertical Stabilizer - Rear Spar To Trailing Edge 55-410-92 Rudder actuator support fittings, vertical stabilizer rear spar, trailing edge support ribs, and rudder hinge support fittings between top of body and Rudder Station 18 and between Rudder Station 106 and Station 181. S 2C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 55-820-00. INTERNAL - GENERAL VISUAL: Vertical Stabilizer - Rear Spar To Trailing Edge 55-410-93 Vertical stabilizer rear spar, trailing edge support ribs, and rudder hinge support fittings between top of body and stabilizer tip except between Rudder Station 106 and Station 181 and at Rudder Station 18. S 4C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 55-820-00.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Vertical Stabilizer Fin-to-Body Fittings 55-412-00 S 2C ALL ALL Vertical stabilizer fin-to-body fittings at front and rear spars and stringers S-4 and S-8.

EXTERNAL - GENERAL VISUAL: Left and Right Vertical Stabilizer Inspar Structure 55-414-00 Vertical stabilizer surfaces between top of body and rib 10 (Fin Station 225), including areas of attachment to rib 1 (Fin Station S 1C ALL ALL 16), spar chords and stringer S-6.

EXTERNAL - GENERAL VISUAL: Vertical Stabilizer Front Spar To Rear Spar 55-416-00 S 2C ALL ALL Vertical stabilizer left and right surfaces from rib 10 (Fin Station 225) to the stabilizer tip rib.

EXTERNAL - DETAILED: Vertical Stabilizer Inspar Structure 55-418-00 Vertical stabilizer left and right surfaces from top of body to rib 1 (Fin Station 16) in areas of attachment to the fin-to-body S 1C ALL ALL fittings at front and rear spar chords and stringers S-4 and S-8.

INTERNAL - GENERAL VISUAL: Vertical Stabilizer Trailing Edge 55-420-00 Vertical stabilizer fin-to-body fitting and body skin within vertical stabilizer trailing edge in area of attachment to Body Station S 2C ALL ALL (BS) 1725.5 bulkhead and stringers S-2L and S-2R.

INTERNAL - GENERAL VISUAL: Rudder 55-422-00 S 4C ALL ALL Rudder interior.

EXTERNAL - GENERAL VISUAL: Rudder 55-422-91 Rudder external structure including areas of attach fasteners through the front spar between Rudder Station 106 and Station 181. S 1C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 55-824-00.

EXTERNAL - DETAILED: Rudder 55-424-00 S 1C ALL ALL Rudder spar, hinge, and actuator attach fittings between Rudder Stations 106 and 181.

EXTERNAL - DETAILED: Rudder 55-426-00 S 2C ALL ALL Rudder spar and hinge fittings between Rudder Station 0 and top of rudder except between Rudder Stations 106 and 181.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

EXTERNAL - SPECIAL DETAILED: Rudder Rudder spar and adjacent structure between Rudder Stations 106 and 181. 55-428-00 S 4C ALL ALL The NDI method(s) necessary to accomplish the intent of this inspection are contained in the 767 Non-Destructive Testing Manual, D634T301. The inspection procedure is contained in part 4, subjects 55-40-01, 55-40-02, and 55-40-03.

INTERNAL - GENERAL VISUAL: Vertical Stabilizer Tip 55-430-00 S 4C ALL ALL Vertical stabilizer tip and upper side of stabilizer tip rib.

INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Center Section Horizontal stabilizer center section upper and lower surfaces, front and rear spars and inspar ribs between ribs 3L and 3R 55-434-00 S 2C ALL ALL including: rib webs around cutouts. Rib shear ties. Rib attach posts to front and rear spars. Attachment of stringer free flanges to the upper and lower chords of rib 2. EXTERNAL - GENERAL VISUAL: Horizontal Stabilizer Center Section Horizontal stabilizer center section upper and lower surfaces and front and rear spars between inboard edge of left and right 55-434-91 stab./body fairings, including: The chordwise splice at rib 2. Upper spanwise splice at stringer S-3. Rear spar web. S 1C ALL ALL NOTE Pivot and jackscrew fittings.

NOTE: This inspection can be accomplished concurrently with MPD item number 55-830-00. INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Center Section Horizontal stabilizer center section upper and lower surfaces. Front and rear spars and inspar ribs between ribs 3L and 3R 55-434-92 including rib webs around cutouts, rib shear ties, rib attach posts to front and rear spars, and attachment of stringer free S 2C ALL ALL NOTE flanges to the upper and lower chords of rib 2.

NOTE: This inspection can be accomplished concurrently with MPD item number 55-828-00. INTERNAL - GENERAL VISUAL: Areas Aft of Pressure Bulkhead To Body Station 1725.5 55-436-91 Body internal surface, stringers, frames and bulkhead between Body Station (BS) 1582 and BS 1725.5 with attention to the body upper and lower longeron backup fittings forward of the horizontal stabilizer cutout at BS 1725.5. S 2C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 55-800-00. INTERNAL - GENERAL VISUAL: Fuselage Areas Aft of Body Station 1725.5 55-438-91 Body internal surface, stringers, frames and bulkheads between Body Station (BS) 1725.5 and BS 1832/1843 with attention to bulkhead at BS 1809.5. S 2C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 55-804-00.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Front To Rear Spar Left & Right 55-454-00 Horizontal stabilizer upper and lower surfaces, front and rear spars and inspar ribs between ribs 8 and 17 including front and S 4C ALL ALL rear spar webs, rib webs, rib shear ties, and rib attach posts to front and rear spars.

INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Outboard Section Left and Right 55-456-00 Horizontal stabilizer upper and lower surfaces front and rear spars and inspar ribs between ribs 3 and 8 including front and S 4C ALL ALL rear spar webs, rear spar upper chord, rib webs around cutouts, rib shear ties, and rib attach posts to front and rear spars.

EXTERNAL - GENERAL VISUAL: Horizontal Stabilizer Upper Outboard Surface Left and Right 55-458-00 Horizontal stabilizer upper surface from outboard edge of stabilizer / body fairing to rib 17, including areas of attachment to S 1C ALL ALL spar chords and stringer S-3 from edge of fairing to rib 8.

EXTERNAL - GENERAL VISUAL: Horizontal Stabilizer Lower Outboard Surface Left and Right 55-460-00 S 2C ALL ALL Horizontal stabilizer lower surface from outboard edge of stabilizer / body fairing to rib 17.

EXTERNAL - DETAILED: Horizontal Stabilizer Upper Outboard Surface Left and Right 55-462-00 Horizontal stabilizer upper skin in area of attach fasteners through upper rear spar chord and upper spanwise splice stringer S 1C ALL ALL S-3 from outboard edge of stabilizer / body fairing to rib 5.

INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Trailing Edge Left and Right 55-464-00 Horizontal stabilizer rear spar, trailing edge panels and support ribs, and elevator hinge support fittings between outboard S 4C ALL ALL edge of stabilizer/body fairing and rib 17 except between stabilizer Rear Spar Stations 104.1 and 177.6.

INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Trailing Edge Right and Left 55-466-00 Elevator actuator support fittings, horizontal stabilizer rear spar, trailing edge panels and support ribs, and elevator hinge S 2C ALL ALL support fittings between stabilizer rear spar stations 104.1 and 177.6.

INTERNAL - GENERAL VISUAL: Left / Right Elevator Interior 55-470-00 S 4C ALL ALL Elevator interior.

EXTERNAL - DETAILED: Elevator Spar & Hinge Fittings Left and Right 55-474-00 Elevator spar and hinge fittings between Elevator Station 51.8 and horizontal stabilizer Buttock Line 317 except between S 2C ALL ALL Elevator Stations 139.3 and 212.7.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

EXTERNAL - GENERAL VISUAL: Left / Right Elevator - Inboard / Outboard 55-478-00 Elevator external structure including areas of attach fasteners through the front spar between Elevator Stations 139.3 and S 1C ALL ALL 212.7 and the elevator interconnect fitting.

EXTERNAL - DETAILED: Left / Right Elevator - Outboard 55-480-00 S 1C ALL ALL Elevator spar, hinge, and actuator attach fittings between Elevator Stations 139.3 and 212.7.

EXTERNAL - SPECIAL DETAILED: Elevator Spar & Adjacent Structure Left and Right Elevator spar and adjacent structure between Elevator Stations 139.3 and 212.7. 55-484-00 S 4C ALL ALL The NDI method(s) necessary to accomplish the intent of this inspection are contained in the 767 Non-Destructive Testing Manual, D634T301. The inspection procedure is contained in part 4, subjects 55-20-01, 55-20-02, and 55-20-03.

INTERNAL - GENERAL VISUAL: Horizontal Stabilizer Tip Left and Right 55-486-00 S 4C ALL ALL Horizontal stabilizer tip and outboard side of rib 17.

INTERNAL - DETAILED: Horizontal Stabilizer Center Section 55-490-00 Horizontal stabilizer rear spar upper chord and skin between rear spar and stringer S-1, from rib 2 to rib 3, including areas of S 2C ALL ALL attach fasteners.

EXTERNAL - DETAILED: Horizontal Stabilizer Jackscrew Fitting 55-492-00 Horizontal stabilizer jackscrew fitting lug area at cross brace fitting and at attachment of fitting to the stabilizer upper and S 1C ALL ALL lower front spar chords, and upper and lower skin attach straps.

EXTERNAL - DETAILED: Horizontal Stabilizer Pivot Fittings 55-494-00 Horizontal stabilizer pivot fitting lug and areas of attachment to stabilizer spar and upper and lower splice plates at rib 2 S 1C ALL ALL including areas of the splice plates aft of the spar.

EXTERNAL - DETAILED: Horizontal Stabilizer Center Section Rear Spar 55-496-00 S 1C ALL ALL Horizontal stabilizer rear spar upper chord and adjacent skin between rib 1 and inboard edge of stabilizer / body fairing.

INTERNAL - GENERAL VISUAL: Wing Center Section Left and Right Wing center section upper and lower surfaces, front and rear spars, spanwise beams, side of body ribs and splices, and lower ALL 57-400-00 surface beams including lower surface access hole cutout and adjacent stringers. S 1C ALL NOTE AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Wing Center Section Lower Surface Splice Wing center section lower surface splice stringers L-6 and L-10 in areas of attach fasteners between left and right Wing ALL 57-402-00 Buttock Line (WBL) 97.9. S 1C ALL NOTE AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank. INTERNAL - DETAILED: Wing Center Section Rear Spar Chord Wing center section rear spar lower chord between left and right Wing Buttock Line (WBL) 97.9. ALL 57-404-00 S 1C ALL NOTE AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank. INTERNAL - DETAILED: Wing Center Section Side of Body Splice Lower left and right Wing Buttock Line (WBL) 97.9 side of body splice chord in areas of attachment to the rib web and lower ALL 57-406-00 wing surface between the wing rear spar and stringer L-10. S 1C ALL NOTE AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank. INTERNAL - DETAILED: Wing Center Section Rear Spar Web Left and right wing center section rear spar web in areas of attach fasteners between buttock line (BL) 62 and Wing Buttock ALL 57-408-00 Line (WBL) 97.9 and between Left Buttock Line (LBL) 11 and Right Buttock Line (RBL) 11. S 1C ALL NOTE AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank. INTERNAL - DETAILED: Wing Center Section Side of Body Rib Web Left and right Wing Buttock Line (WBL) 97.9 side of body rib web surrounding cutouts, and attachments to rear spar terminal ALL 57-410-00 fitting and lower rib chord between the rear spar and spanwise beam #1. S 1C ALL NOTE AIRPLANE NOTE: For airplanes without two-bay or four-bay center section fuel tank. INTERNAL - DETAILED: Wing Center Section Lower Surface Buttock Line 70 Wing center section lower surface left and right Buttock Line (BL) 70 underwing longeron backup structure aft of the front ALL 57-412-00 spar. S 1C ALL NOTE AIRPLANE NOTE: For airplanes without four-bay center section fuel tank. INTERNAL - GENERAL VISUAL: Wing Center Section Fuel Tank Dry Bay Area Wing center section dry bay upper and lower surface, front spar, spanwise beam, side of body ribs and splices and lower ALL 57-414-00 surface beams including lower surface access hole cutout, adjacent stringers, and drain. S 1C ALL NOTE AIRPLANE NOTE: Airplanes with two-bay center section fuel tank.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Wing Center Section Fuel Tank Wet Bay Wing center section lower surface splice stringers L-6 and L-10 in areas of attach fasteners between left and right Wing Buttock Line (WBL) 97.9. ALL 57-416-00 S 4C ALL SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of this document NOTE for sealant limits and threshold values.

AIRPLANE NOTE: For airplanes with two-bay or four-bay center section fuel tank. INTERNAL - GENERAL VISUAL: Wing Center Section Wing center section wet bay upper and lower surfaces, rear spar, span wise beams and access door cutouts, lower surface 57-416-91 beams, side of body ribs, splices and drain. ALL S 4C ALL NOTE AIRPLANE NOTE: Airplanes with 2-BAY or 4-BAY center section fuel tank. NOTE

NOTE: This inspection can be accomplished concurrently with MPD item number 53-830-00. INTERNAL - DETAILED: Wing Center Section Fuel Tank Wet Bay Left and right Wing Buttock Line (WBL) 97.9 side of body rib web and lower chord cutouts, and attachments to rear spar ALL 57-418-00 terminal fitting and lower rib chord between the rear spar and spanwise beam no. 2. S 4C ALL NOTE AIRPLANE NOTE: For airplanes with two-bay or four-bay center section fuel tank. INTERNAL - DETAILED: Wing Center Section Fuel Tank Wet Bay Wing center section rear spar lower chord and skin between left and right Wing Buttock Line (WBL) 97.9. ALL 57-420-00 SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of this document S 4C ALL for sealant limits and threshold values. NOTE

AIRPLANE NOTE: For airplanes with two-bay or four-bay center section fuel tank. 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 Line (WBL) 97.9 and between Left Buttock Line (LBL) 11 and Right Buttock Line (RBL) 11. ALL 57-422-00 S 4C ALL SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of this document NOTE for sealant limits and threshold values.

AIRPLANE NOTE: For airplanes with two-bay or four-bay center section fuel tank.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

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 lower wing surface ALL 57-424-00 between the wing rear spar and stringer L-10. S 4C ALL NOTE AIRPLANE NOTE: For airplanes with two-bay or four-bay center section fuel tank. INTERNAL - DETAILED: Wing Center Section Lower Surface Buttock Line 70 Wing center section lower surface left and right Buttock Line (BL) 70 underwing longeron backup structure aft of the front ALL 57-426-00 spar. S 4C ALL NOTE AIRPLANE NOTE: Airplanes with four-bay center section fuel tank.

INTERNAL - GENERAL VISUAL: Wing Center Section Lower Surface 57-458-00 Wing center section lower surface including the area surrounding the access hole cutout, front spar bulkhead at Body Station S 1C ALL ALL (BS) 785.9, Keel beam and wing lower surface beam at Buttock Line (BL) 62 between BS 785.9 and BS 955.1.

EXTERNAL - GENERAL VISUAL: Inboard Flap Support Structure - Left / Right 57-460-00 S 1C ALL ALL Inboard flap inboard support and mechanism.

INTERNAL - GENERAL VISUAL: Nacelle Strut No. 1 / 2 Aft Upper Spar 57-468-00 S 1C ALL ALL Nacelle strut aft upper spar (visible inboard portion).

INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Upper Link 57-470-00 Nacelle strut upper link and upper link to wing attach fitting including the area of attachment to the wing front spar and the S 1C ALL ALL upper and lower wing skin projections.

INTERNAL - GENERAL VISUAL: Right and Left Wing Leading Edge To Front Spar Right and left wing leading edge panels and ribs, support structure for slats and actuators, main and auxiliary slat tracks, and 57-470-91 wing front spar and skin including the side of body splice at WBL 97.9. S 2C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 57-802-00, 57-802-01, 57-812-00 and 57-812-01.

EXTERNAL - GENERAL VISUAL: Left / Right Wing Inspar Lower Surface, Exterior 57-504-00 S 1A ALL ALL Wing lower surface between wing/body fairings and Wing Buttock Line (WBL) 929.1/rib 36.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

EXTERNAL - GENERAL VISUAL: Left / Right Wing Inspar Lower Surface 57-506-00 Wing lower surface between wing/body fairings and Wing Buttock Line (WBL) 929.1/rib 36 including areas under fairings at S 1C ALL ALL main landing gear forward trunnion, and ribs 7, 17 and 24.

EXTERNAL - GENERAL VISUAL: Left / Right Wing Inspar Upper Surface Wing inspar upper surface between wing/body fairing and Wing Buttock Line (WBL) 929.1/rib 36 (tip) including areas of attach 57-508-00 S 2C ALL ALL fasteners at: nacelle support at front spar (WBL 310). Main landing gear beam outboard fitting (WS 394) at rear spar. Main landing gear forward trunnion fitting (WS 308) at rear spar.

EXTERNAL - DETAILED: Left / Right Wing Inspar Upper Surface 57-510-00 S 1C ALL ALL Wing upper surface in the area of the nacelle strut fitting attachments at Wing Buttock Line (WBL) 310.

EXTERNAL - DETAILED: Left / Right Wing Inspar Lower Surface Wing lower surface surrounding fuel access plate cutouts between wing/body fairing and rib 3 and between ribs 7 and 20 and 57-512-00 in the following areas of attachments: main landing gear beam outboard support fitting. Rear spar chord from wing/body S 1C ALL ALL fairing to Wing Station (WS) 590.2 (rib 16). Spanwise splice stringer L-6 between wing/body fairing and rib 3, and between rib 8 and rib 14. Spanwise splice stringer L-10, from rib 7 to rib 20. Front spar chord from rib 7 to rib 24.

EXTERNAL - DETAILED: Left / Right Wing Inspar Upper Surface 57-514-00 S 2C ALL ALL Wing upper surface in areas of attachment to rear spar upper chord between ribs 5 and 21.

INTERNAL - DETAILED: Left / Right Wing Lower Surface Spanwise Splice Wing lower surface spanwise splice stringers L-6 and L-10 between Wing Buttock Line (WBL) 97.9 and rib 3. 57-516-00 S 4C ALL ALL SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of this document for sealant limits and threshold values. INTERNAL - GENERAL VISUAL: Center Auxiliary Tank - Left / Right Wing Left and right wing upper and lower surfaces, front and rear spars, and inspar ribs between WBL 97.9 and rib 3 including 57-516-91 cavity drain adjacent to the side of body rib, wing rib access cutouts in ribs 1 and 2, rib attach posts to front and rear spars S 4C ALL ALL NOTE and lower surface splice stringer L-15.

NOTE: This inspection can be accomplished concurrently with MPD item number 57-834-00.

INTERNAL - DETAILED: Left / Right Wing Lower Surface Access Hole Cutouts 57-518-00 S 4C ALL ALL Wing lower surface access hole cutouts and adjacent stringers.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Left / Right Wing Lower Surface / Side of Body Rib 57-520-00 Wing Buttock Line (WBL) 97.9 side of body rib lower chord in areas of attachment to the lower surface and stringers between S 4C ALL ALL the rear spar and stringer L-10.

INTERNAL - DETAILED: Left / Right Wing Rear Spar Web & Lower Chord Wing rear spar web and lower chord between Wing Buttock Line (WBL) 97.9 and rib 1. 57-522-00 S 4C ALL ALL SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of this document for sealant limits and threshold values. INTERNAL - DETAILED: Left / Right Wing Rear Spar Lower Chord & Rib 1 & 3 Wing rear spar lower chord between rib 1 and rib 3. 57-524-00 S 4C ALL ALL SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of this document for sealant limits and threshold values. INTERNAL - DETAILED: Left / Right Wing Side of Body Rib Web Wing Buttock Line (WBL) 97.9 side of body rib web in areas of rib attach fasteners and reinforcements surrounding cutouts between rear spar and spanwise beam no. 1. 57-526-00 S 4C ALL ALL SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of this document for sealant limits and threshold values. INTERNAL - GENERAL VISUAL: Left / Right Wing Main Tank Wing upper and lower surfaces, front and rear spars, spanwise dry bay barrier, and inspar ribs between rib 3 and rib 31 including: cavity drain adjacent to rib 3. Wing rib access cutouts in ribs 4, 5, and 9. Rib shear ties at ribs 4, 7, 8, 10, 17, and 57-530-00 24. Rib attach posts to front and rear spars. S 4C ALL ALL

SPECIAL NOTE: This MPD task requires removal of sealant. Refer to the Excess Sealant Table in Section B of this document for sealant limits and threshold values.

INTERNAL - DETAILED: Left / Right MLG Trunnion Backup Structure 57-532-00 S 4C ALL ALL Wing main landing gear forward trunnion support backup structure forward of rear spar at Wing Station (WS) 308.1.

INTERNAL - DETAILED: Left / Right MLG Beam Backup Structure 57-534-00 S 4C ALL ALL Wing main landing gear beam outboard support backup structure forward of rear spar adjacent to ribs 7 and 8.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Left / Right Wing Nacelle Strut Support Backup 57-536-00 Wing nacelle strut support backup structure forward of the rear spar adjacent to stringers L-5 and L-6 and Wing Buttock Line S 4C ALL ALL (WBL) 310.

INTERNAL - DETAILED: Left / Right Wing Lower Spar Chords Lower spar chords as follows: front spar chord between ribs 14 and 24, rear spar chord between ribs 3 and 11. 57-538-00 S 4C ALL ALL SPECIAL NOTE: This MPD task requires removal of sealant prior to inspection. Refer to the Excess Sealant Table in Section B of this document for sealant limits and threshold values. INTERNAL - DETAILED: Left / Right Wing Lower Spanwise Splice Stringers Lower surface spanwise splice stringers; L-6 between ribs 8 and 14, L-10 between ribs 7 and 20, L-15 between ribs 9 and 11. 57-540-00 S 4C ALL ALL SPECIAL NOTE: This MPD task requires removal of sealant prior to inspection. Refer to the Excess Sealant Table in Section B of this document for sealant limits and threshold values.

INTERNAL - DETAILED: Left / Right Wing Lower Surface Access Hole Cutouts 57-542-00 S 4C ALL ALL Lower surface access hole cutouts and adjacent stringers between ribs 7 and 20.

INTERNAL - DETAILED: Nacelle Strut No. 1 / 2 Backup Structure 57-544-00 S 1C ALL ALL Nacelle strut support backup structure aft of the front spar between ribs 8 and 9.

INTERNAL - GENERAL VISUAL: Dry Bay - Inboard Left / Right Wing 57-544-91 Left and right wing upper & lower surfaces, front spar & the spanwise dry bay barrier and inspar ribs between rib 6 and rib 9. S 1C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 57-838-00.

INTERNAL - DETAILED: Left / Right Wing Spanwise Splice Stringer L-15 57-546-00 S 1C ALL ALL Lower surface spanwise splice stringer L-15 between ribs 8 and 9.

INTERNAL - DETAILED: Left / Right Wing Front Spar Lower Chord, Rib 7&9 57-548-00 S 1C ALL ALL Front spar lower chord between ribs 7 and 9.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - GENERAL VISUAL: Left / Right Wing Inboard Dry Bay Wing lower surface, Wing Station (WS) 314.3 to (WS) 404.4 front spar to aft dry bay barrier (leveling compound). S 1C ALL 57-550-00 ALL INTERVAL NOTE: Or 15 months, whichever comes first. NOTE NOTE

AIRPLANE NOTE: Applicable to airplanes prior to line number 260.

INTERNAL - DETAILED: Left / Right Trailing Edge Flap Support Backup Structure 57-552-00 S 4C ALL ALL Wing trailing edge flap support backup structure forward of rear spar at ribs 17 and 24.

INTERNAL - GENERAL VISUAL: Surge Tank - Left / Right Wing 57-552-91 Left and right wing upper and lower surfaces. Front and rear spars, and inspar ribs between ribs 31 and 34 including access hole cutouts, and rib attach posts to front and rear spars. S 4C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 57-842-00.

INTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Dry Bay 57-554-00 Left/right wing upper and lower surfaces, front and rear spars, and inspar ribs between rib 34 (Wing Station 1075) and Wing S 4C ALL ALL Buttock Line 929 including access hole cutout and rib attach posts to front and rear spars.

INTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Dry Bay 57-556-00 Wing upper and lower surfaces, front and rear spars, and inspar ribs between rib 34 (Wing Station 1075) and rib 36 including S 4C 400E ALL access hole cutout and rib attach post to front and rear spars.

INTERNAL - GENERAL VISUAL: Left / Right Wing Tip and Outboard Side of Wing Buttock Line 929 Rib Wing tip and outboard side of Wing Buttock Line (WBL) 929 rib. ALL 57-558-00 S 4C ALL NOTE AIRPLANE NOTE: Applicable to ALL airplanes except 400E. INTERNAL - SPECIAL DETAILED: Wing Tip Rib & Outboard Side of Rib 36 Left and Right Raked wing tip rib, rib attachment to skin and attach bolts (wing tip rib to rib 36 attachment bolts) (Borescope inspection). 57-560-00 S 4C 400E ALL NOTE: Use illuminated borescope. Inspect raked wing tip rib, attachment to skin, attach bolts and general area inside of raked wing tip. Insert borescope through holes in rib 36 and raked wing tip rib. INTERNAL - GENERAL VISUAL: Left / Right Wing Trailing Edge Support Structure & Rear Spar Wing Trailing Edge (TE) support structure and wing rear spar and skin from Wing Buttock Line (WBL) 97.9 to outboard end of 57-564-00 inboard aileron including: main landing gear beam and support structure; lower stabilizer beam/strut/brace assembly, upper S 1C ALL ALL stabilizer beam/strut/brace (-400 only) support structure for main landing gear drag brace, forward trunnion, and actuator; support structure for inboard aileron, flap, and # 5, # 6, # 7, and # 8 spoilers including actuator supports.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - DETAILED: Left / Right Upper Wing / Side of Body Splice 57-566-00 S 2C ALL ALL Wing upper surface side of body splice at the rear spar including the kick fitting.

EXTERNAL - GENERAL VISUAL: Left / Right Wing Trailing Edge 57-568-00 S 1A ALL ALL Wing trailing edge.

EXTERNAL - GENERAL VISUAL: Left / Right Main Gear Drag Brace & MLG Beam 57-570-00 Main landing gear drag brace support fitting attached to wing rear spar at Wing Station (WS) 220 and visible portion of main S 5A ALL ALL landing gear beam.

INTERNAL - GENERAL VISUAL: Left / Right Wing Inboard Trailing Edge 57-578-00 S 4C ALL ALL Inboard trailing edge flap box except in area of outboard support structure.

EXTERNAL - GENERAL VISUAL: Inboard Trailing Edge Flap - Left / Right Wing 57-578-91 Left and right wing inboard trailing edge flap including linkage, support fittings, support beam, and main flap lower surface in area of flap outboard support. S 1C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 57-850-00.

INTERNAL - GENERAL VISUAL: Left / Right Wing Inboard Trailing Edge 57-580-00 S 2C ALL ALL Wing inboard flap box in area of outboard support structure.

INTERNAL - SPECIAL DETAILED: Left / Right Wing Inboard Trailing Edge Flap Box Wing inboard trailing edge flap to support No. 3 / 6 beam attach bolts - re-torque. ALL 57-584-00 S 4C ALL NOTE AIRPLANE NOTE: Applicable to line numbers 922 and on, and all 400E airplanes.

EXTERNAL - GENERAL VISUAL: Left / Right Wing Inboard Trailing Edge Flap 57-586-00 S 1A ALL ALL Wing inboard trailing edge flap.

INTERNAL - GENERAL VISUAL: Wing Trailing Edge Support Structure / Rear Spar Left and Right 57-596-00 Wing trailing edge support structure and wing rear spar and skin from outboard end of inboard aileron to Wing Buttock Line S 2C ALL ALL (WBL) 929.1/ rib 36 including support structure for outboard aileron, flap and spoilers including actuator supports.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - GENERAL VISUAL: Rear Spar To Wing Trailing Edge - Left / Right Wing 57-596-91 Left and right wing rear spar and skin in area of outboard aileron actuator and hinge support structure between wing STA. 1006.7 and STA. 1031.7. S 1C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 57-854-00.

INTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Trailing Edge Flap Box 57-598-00 S 4C ALL ALL Outboard trailing edge flap box except in area of support structure.

INTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Trailing Edge Flap Box 57-600-00 S 2C ALL ALL Wing outboard trailing edge flap box in area of support structure.

INTERNAL - SPECIAL DETAILED: Left / Right Wing Outboard Trailing Edge Flap Box Wing outboard trailing edge flap to support beam attach bolts - re-torque. ALL 57-602-00 S 4C ALL AIRPLANE NOTE: This task is applicable to airplanes line numbers 1 through 710 that have incorporated service bulletin NOTE 767-27A0155, and to all airplanes line number 711 and on.

EXTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Trailing Edge Flap 57-604-00 S 1A ALL ALL Wing outboard trailing edge flap.

EXTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Trailing Edge Flap Wing outboard trailing edge flap including linkage, support fittings, support beam, outboard auxiliary support and rib, and flap 57-606-00 S 1C ALL ALL lower surface in areas of flap supports. For Airplanes which are line numbers 922 and later, and all 400E aircraft regardless of line number, also inspect the inboard auxiliary support and rib. INTERNAL - GENERAL VISUAL: Left / Right Wing Inboard Trailing Edge Flap Wing inboard trailing edge flap support mechanism No. 3 / 6 including actuator support rib assembly, underwing attach fitting, 400E 57-616-00 aft flap drive, flap box attachment fasteners, reaction ring, drive arm, fuse pins, flap support pins, all beams and links. S 2C ALL NOTE AIRPLANE NOTE: Applicable to all 400E airplanes and applicable to all airplanes L/N 883 and later. INTERNAL - GENERAL VISUAL: Left/Right Wing Inboard Flap - Outboard Flap Support 57-616-91 Left and right wing inboard TE flap, outboard support linkage. S 1C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 57-860-00.

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MPD ITEM APPLICA- INSPECTION LEVEL and TASK DESCRIPTION INTERVAL ENG NUMBER BILITY

INTERNAL - GENERAL VISUAL: Left / Right Wing Outboard Trailing Edge Flap Wing outboard trailing edge flap support mechanism No. 1 / 8 and No. 2 / 7 including rear spar fitting, rear spar fitting tension 57-618-00 S 2C 400E ALL bolts, flap box attachment fasteners, reaction ring and doubler, drive arm, swivel fitting, fuse pins, flap support pins, all beams and links. INTERNAL - GENERAL VISUAL: Inboard Flap Support Fairing - Left / Right Outboard Flap 57-618-91 Left and right wing outboard TE flap, inboard support linkage. S 1C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 57-862-00. INTERNAL - GENERAL VISUAL: Outboard Flap Support Fairing - Left / Right Outboard Flap 57-618-92 Left and right wing outboard TE flap, outboard support linkage. S 1C ALL ALL NOTE NOTE: This inspection can be accomplished concurrently with MPD item number 57-864-00. INTERNAL - DETAILED: Side of Body Rib Lower Chord Cutouts Left and Right Area surrounding side of body rib lower chord cutouts from rear spar to spanwise beam No. 2. ALL 57-686-00 S 4C ALL NOTE AIRPLANE NOTE: Airplanes with two-bay or four-bay center section fuel tank. 4000 INTERNAL - DETAILED: No. 1 / 2 Power Plant 7R4 71-600-00 Forward engine mount bulkhead fitting, visible portion of diagonal brace attach fitting at aft end of firewall, forward and aft S 1C ALL engine mounts, links, and attachments. 80A 80C INTERNAL - GENERAL VISUAL: No. 1 / 2 Power Plant 4000 Forward engine mount bulkhead fitting, visible portion of diagonal brace attach fitting at aft end of firewall, forward and aft ENG CNG 7R4 71-602-00 engine mounts, links, attachments, and strut lower surface (firewall). ALL <1> 80A ACCESS NOTE: At engine removal. 80C

<1> Engine Change

To comply with 14 CFR 26.11(b), an analysis was conducted for each maintenance zone using an "Enhanced Zonal Analysis Procedure" (EZAP) with guidance from Advisory Circular (AC) 25-27. The objective of the EZAP analysis was to identify maintenance and inspection tasks to: 1) minimize the accumulation of combustible materials; 2) detect EWIS component defects; and 3) detect EWIS installation discrepancies that may not be reliably detected by inspections contained in existing maintenance programs. <2> The term "EWIS" is defined in the 767 Maintenance Review Board Report (MRBR), D622T001-MRBR, Appendix D, Definitions. This appendix includes definitions of other terms related to EZAP tasks such as: "Power Feeder Wiring" and "Combustible Materials". For all other definitions related to EZAP, refer to AC 25-27.

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