767 MAINTENANCE PLANNING DATA

D622T001-9

MAY 2010 BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 
D622T001-9

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

767 MAINTENANCE PLANNING DATA

MAY 2010
767 MAINTENANCE PLANNING DATA

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767

MAINTENANCE PLANNING DATA (MPD) DOCUMENT

SECTION 9

AIRWORTHINESS LIMITATIONS (AWLs) AND 

CERTIFICATION MAINTENANCE REQUIREMENTS (CM

D622T001-9

MAY 2010

COMPILED AND PUBLISHED BY:

MAINTENANCE PROGRAMS ENGINEERING

COMMERCIAL AVIATION SERVICES

BOEING COMMERCIAL AIRPLANE GROUP

SEATTLE, WASHINGTON

MAY 2010
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TABLE OF CONTENTS

REVISIONS .......................................................................................................................................................................................LIST OF EFFECTIVE PAGES ...........................................................................................................................................................A. SCOPE..........................................................................................................................................................................................B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS............................................................................................C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFE PARTS .....................................................................................D. AIRWORTHINESS LIMITATIONS – SYSTEMS............................................................................................................................E. PAGE FORMAT: FUEL SYSTEMS AIRWORTHINESS LIMITATIONS..........................................................................................F. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRS).....................................................................................................G. PAGE FORMAT: CERTIFICATION MAINTENANCE REQUIREMENTS (CMRS).........................................................................H. CERTIFICATION MAINTENANCE REQUIREMENTS TASKS .....................................................................................................I. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS ..............................................................................

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REVISIONS

REVISION AND REVISION DESCRIPTION 

MAY 1990 – Original ReleaseAlthough this information was previously issued as Revision "B" to Section 9 of the 

MPD, this issue is considered the original release because it is now assigned a new document number (D622T001-9).

Prepared by:

M. H. LAEDER (Boeing) 4/9/90

Supervised by

S. J. BRADBU(Boeing)4/9/90

FEBRUARY 1993Revision to the Maintenance Planning Data Document, including Section 9, "Airworthiness 

Limitations and Certification Maintenance Requirements."

Prepared by:

K. L. UTTERBACK (Boeing) 2/19/93

Supervised by

S. J. BRADBU(Boeing)2/19/93

MAY 1995Deleted CMRs 28-22-00-5A, 28-25-00-5B, and 28-41-00-5A.Added structural safe life limits for the engine mounts on the RB211-524H Engines.

Prepared by:

E. WISEMAN (Boeing)4/14/95

Supervised by

S. R. WILLIFO(Boeing)4/14/95

OCTOBER 1995Added paragraph C, "Structural Inspections – Model 767-300 Package Freighter only." 

This paragraph outlines the requirements for the 50 Series inspections for the newly certified Model 767-300 Package Freighter airplane.

Prepared by:

W. F. LINDHOLM (Boeing)10/5/95

Supervised by

S. R. WILLIFO(Boeing)10/5/95

MAY 2010
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FEBRUARY 1996Revised CMRs H77-35-00-2B and N77-35-00-2B to increase CMR interval from 500 

HRS to 1000 HRS.

Prepared by:

R. C. MOORE (Boeing) 2/15/96

Supervised by

S. R. WILLIFO(Boeing)2/15/96

JUNE 1997Revised Airworthiness Limitations section to reflect the reassessment of the 

"50-Series" Supplemental Structural Inspection Program. Previous Sections B and C have been merged into a new section B and remaining sections have been renumbered.

Submitted by:

S. WILLIFORD (Boeing)6/26/97

Approved by: 

D. L. RIGGIN 7/25/97

AUGUST 1997Revised CMRs D77-35-00-2B and H77-35-00-2B from 500 HRS to 560 HRS and 1000 

HRS to 2000 HRS respectively. Reworded CMR H77-35-00-2B.

Submitted by:

S. WILLIFORD (Boeing) 8/6/97

Approved by: 

D. L. RIGGIN 11/17/97

REVISIONS

REVISION AND REVISION DESCRIPTION 

MAY 2010
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JUNE 2000Revised Airworthiness Limitations (AWL) section to include limitations for 767-400ER 

and revised Airplane Applicability for current AWLs. Revised current AWL title to more accurately reflect inspection areas. Revised AWL for Strut to reflect reassessment of the damage tolerance ratings.

Revised interval for CMRs 24-33-00-6A and 26-10-00-6A from DAILY to 48 HRS. 

Added CMR 27-51-00-5I applicable only to the 767-400ER airplane. Added CMR H78-34-00-5A applicable to airplanes with GE CF6-80C2 engines.

Revised CMR 29-11-00-6F by adding a note to indicate the hydraulic system internal 

leakage limits. Revised airplane applicability for CMRs 27-51-00-5D and H77-00-00-6D.

Revised effectivity for CMR 31-41-02-4A since it is not applicable to the 767-400ER. 

Added AWLs for Fuselage to reflect reassessment of damage tolerance rating due to recent test and fleet performance data.

Submitted by:

N. HENNIGS (Boeing) 7/6/00

Approved by: 

A. BAHRAMI (

FEBRUARY 2001Revised CMR 31-41-00-2A to limit airplane applicability to the 767-200/-300 airplanes. 

Added CMR 31-63-00-2A applicable only to the 767-400ER airplane. Deleted CMR H78-00-5A for both Engine 1 and Engine 2. Revised CMR N77-41-01-4A and H77-00-00-6D by adding an airplane note applicable to the 767-200/300 airplanes only. Revised statement in preamble to airworthiness limitations that specifies roll back of any escalated baseline structural inspection intervals when reaching the AWL threshold.

Revised Instruction 3 for use of FLS threshold curve to add 400ER.

Submitted by:

A. K. STENDER (Boeing)4/18/01 

Approved by:

L. LIU-NELSO

SEPTEMBER 2002Added CMR 52-51-07-4A applicable only to airplanes incorporating Boeing Service 

Bulletin 767-25-0325. This amended type certificate complies with the new 14 CFR 25.795 and the amended 14 CFR 25.772 as issued under Federal Register Docket No. FAA-2001-11032.

Submitted by:

LINH Q. VU (Boeing)8/30/02

Approved by:

L. LIU-NELSO

REVISIONS

REVISION AND REVISION DESCRIPTION 

MAY 2010
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767 MAINTENANCE PLANNING DATA

OCTOBER 2002Revised CMR 52-51-07-4A to change applicability to show airplane Line Number 895 

and on and any airplane that has incorporated Service Bulletin 767-25-0325 or 767-25-0327 or 767-25-0332.

Revised the Structural Safe Life Parts section to reference current Service Letter 767-

SL-32-092 in place of superseded Service Letters 767-SL-32-21 and 767-SL-32-37.

Submitted by:

LINH Q. VU (Boeing)10/15/02

Approved by:

L. LIU-NELSO

AUGUST 2004Revised Airworthiness Limitations (AWL) Section 9 to add FAA Letter 120S-03-953 and 

6 page enclosure as an AMOC for AD 2003-18-10 in lieu of superseded AD 2001-08-28 and FAA AMOC letter 120S-02-962.

Revised Section 9 CMR 36-11-01-6C to add Rolls-Royce engine note on Page 9.1-3. 

Revised the Structural Safe Life Parts Section page 9.0-57 to escalate Life Limits and define additional Life Limit components for the 767-400ER.

Submitted by:

S. A. PIERINI (Boeing)8/15/04

Approved by:

JULY 2005Revised CMR 31-41-02-4A Interval from 04000 HRS to 10800 HRS. Item Number H77-

00-00-6D was renamed as H77-41-00-5A to agree with corresponding Item Number in Section 6. 

Submitted by:

B. McLoughlin (Boeing)

Approved by: 

Dorr Anderson

REVISIONS

REVISION AND REVISION DESCRIPTION 

MAY 2010
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MARCH 2006Added new Fuel System Airworthiness Limitations section which includes inspections of 

the Auto Shutoff and Ground Fault Interrupter systems, and design limitations of the Hot Short Protector and motor operated valves.

Submitted by:

S. Pierini (Boeing)

Approved by: 

Dorr Anderson 

OCTOBER 2006Revised CMR Task 52-51-07-4A interval from 4 years to 6 years to reflect improved 

reliability data for the Flight Deck Door Strike Assembly.

Submitted by:

S. Pierini (Boeing)

Approved by: 

Seattle FAA A

JANUARY 2007Revised Airworthiness Limitations – Systems section introduction to include revisions 

recommended by the Seattle FAA Flight Standards group.

Revised applicability of Fuel System Airworthiness Limitation Numbers 28-AWL-23 and 

28-AWL-24 to remove ITT actuator part number reference. The part number is listed in Service Bulletin 767-28A0090.

Submitted by:

S. Pierini (Boeing)

Approved by: 

Dorr Anderson 

REVISIONS

REVISION AND REVISION DESCRIPTION 

MAY 2010
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OCTOBER 2007Revised Section D. Airworthiness Limitations (AWLs) – Systems paragraph on 

Exceptional Short-Term Extensions for AWLs to clarify notification requirements.

Revised Systems AWL Page Format paragraph to become Section E. Page Format: 

Fuel Systems Airworthiness Limitations, and relettered the Sections following Section E.

Added AWL Number 28-AWL-27, a yearly check of the Main and Center Auxiliary Fuel 

Tank Boost Pump Ground Fault Interruption (GFI) Control Relay System, applicable to airplane Line Numbers 961 and on and airplanes that have incorporated Service Bulletin 767-28A0085.

Added AWL Number 28-AWL-28, a yearly check of the Center Auxiliary Fuel Tank 

Override/Jettison Fuel Pump Uncommanded-On System, applicable to airplane Line Numbers 961 and on and airplanes that have incorporated Service Bulletin767-28A0085.

Revised CMR 52-51-07-4A Task Interval from 6 years to 9 years to reflect improved 

reliability data for the Flight Deck Security Door.

Added Section I. Reporting Uncontrolled High Thrust Failure Conditions per 

FAR 121.703 and FAR 135.415.

Submitted by:

(Boeing)

Approved by: 

Dorr Anderson 

MARCH 2008Revised 28-AWL-01and 28-AWL-26 by removing the 36000FH task interval limitation 

based upon engineering review and operator maintenance practice.

Revised 28-AWL-18 to reflect the new maximum loop resistance values associated with 

the lightning protection of the unpressurized FQIS wire bundle installations so as to satisfy the Airworthiness Limitation Instructions required by SFAR 88. Also removed the joint resistance values and 36000FH task interval limitation based upon engineering review and operator maintenance practice.

Submitted by: John Sabolchy

(Boeing)

Approved by: 

Dorr Anderson 

REVISIONS

REVISION AND REVISION DESCRIPTION 

MAY 2010
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APRIL 2008Revised 28-AWL-06 to add additional Component Maintenance Manual (CMM) information.

Submitted by: Jason Onorati

(Boeing) 

Approved by: 

MAY 2008Revised B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS to add 

restrictions on flight hours and flight cycles for 767-200SF and 76-300BCF to comply with FAA Title 14 CFR Part 26.

Revised C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFE PARTS to limit 

767-200SF Nose Landing Gear, Main Landing Gear and Landing Gear Support Structure to 1,000 flight cycles.

Revised C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFE PARTS to limit 

767-300BCF Nose Landing Gear, Main Landing Gear and Landing Gear Support Structure to 2,000 flight cycles.

Submitted by: John Sabolchy

(Boeing) 

Approved by: 

JUNE 2008Revised airplane applicability table to add the 767-300BCF.Added CMRs 31-51-00-5B and 31-51-00-5C that are applicable to the 767-300BCF model. 

The CMRs are necessary for compliance to 14 CFR 25.703 and 14 CFR 25.1309.

Submitted by: Mike Eckelberry

(Boeing) 

Approved by: 

(Seattle FAA A

REVISIONS

REVISION AND REVISION DESCRIPTION 

MAY 2010
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767 MAINTENANCE PLANNING DATA

JUNE 2008 R1Revised Airworthiness Limitations-Structural Inspection Table Tasks 53-10-I07C, 

53-30-I04C, 53-60-I05C, 53-10-I07D, 53-30-I04D, 53-30-I04D, 53-60-105D, 53-30-I01, 

53-50-I01, 53-60-I01 by adding airplane effectivities and intervals from Service Bulletin 767-53-0210.

Submitted by: Mike Eckelberry

(Boeing) 

Approved by: 

(Seattle FAA A

AUGUST 2008Revised Airworthiness Limitations-Structural Inspection Table Tasks 53-10-I07C, 

53-30-I04C, 53-60-I05C, 53-10-I07D, 53-30-I04D, 53-60-105D by adding an additional 

inspection threshold and interval for aircraft L/N 971.

Revised text to refer to correct Flight Standards Handbook.

Submitted by: Jason Onorati

(Boeing) 

Approved by: 

(Seattle FAA A

SEPTEMBER 2008Revised airplane applicability table to add the 767-200SFRevised CMRs 31-51-00-5B and 31-51-00-5C to add applicability for the 767-200SF model. 

The CMRs are necessary for compliance to 14 CFR 25.703 and 14 CFR 25.1309.

Submitted by: Jason Onorati

(Boeing) 

Approved by: 

(Seattle FAA A

NOVEMBER 2008Revised Airworthiness Limitations-Structural Inspection table tasks 53-10-I07A, 

53-30-I04A, 53-60-I05A, 53-10-I07B, 53-30-I04B, and 53-60-105B by adding revised inspection method and new inspection threshold of 37,500 cycles due to structural repair for L/N 973.

Submitted by: John Sabolchy

(Boeing) 

Approved by: 

REVISIONS

REVISION AND REVISION DESCRIPTION 

MAY 2010
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JANUARY 2009Revised Section B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS by 

removing the 900 flight cycle or 2,700 flight hour restrictions for the 767-300BCF, to comply with FAA Title 14 CFR Part 26.

Submitted by: John Sabolchy

(Boeing) 

Approved by: 

MARCH 2009Revised Section B. AIRWORTHINESS LIMITATIONS for compliance with 14 CFR 26.45 (c) 

by adding VN194 (Serial Number 25616) to the list of 767 airplanes.

Submitted by: John Sabolchy

(Boeing) 

Approved by: 

MAY 2009Revised B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS to clarify 

effectivity on passenger to freighter conversion in accordance with FAA Title 14 CFR Part 26.

Revised Airworthiness Limitations-Structural Inspection Table by adding airplane 

effectivities and intervals from Service Bulletins 767-53-0103, 767-53-0190,767-53-0191, 767-53-0208, 767-53-0210, and 767-53-0212.

Revised text to refer to correct Flight Standards Handbook.Added Flag Note to the Airworthiness Limitations-Structural Inspection Table to highlight 

operational limits for certain applicable SSIs.

Revised SSI 53-50-I11 by updating applicability column from "200" to "ALL" to reflect 

requirements called out in the DTR forms.

Revised 53-80-I01A, B, C, D, E and 53-80-I15, 16 and 17 to add line number reference 

to applicability and a note to refer to the DTR forms.

Revised SSIs 54-50-I01 and 54-50-I04 by dividing them into their own separate task 

requirements. 

(Continued on next page)

Submitted by: John Sabolchy

(Boeing) 

Approved by: 

REVISIONS

REVISION AND REVISION DESCRIPTION 

MAY 2010
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767 MAINTENANCE PLANNING DATA

MAY 2009, ContinuedRevised SSI 54-50-I13 by adding additional rows to clarify engine effectivity and to reflect 

the DTR document (D622T001-DTR).

Revised 57-20-I16A to change applicability from “400E” to “ALL” to reflect the correct 

airplane model.

Revised text to refer to Document D622T001-DTR rather than Appendix B.Revised Airworthiness Limitations to include new cargo door limitations. One new cargo 

door limitation is applicable to passenger airplanes, eight are applicable to freighter airplanes, and three are applicable to all airplanes.

Revised and added new Trailing Edge Flap limitations (Flap Loss Mitigation Program) 

and added wording regarding the tracking of removable parts. Forty revised Trailing Edge Flap limitations are applicable to 767-200, -300 passenger and -300 freighter airplanes, Line Numbers 922 and later, except as noted, and are applicable to all 767-400ER airplanes. Forty-nine new Trailing Edge Flap limitations are applicable to the 767-200, -300 passenger and -300 freighter airplanes, Line Numbers 1 to 921, except as noted. Added airplane effectivity note to the AIRPLANE ENGINE APPLICABILITY column of both entries for Airworthiness Limitation 53-10-I21A.

Revised CMR section by correcting typographical errors by changing CMR D77-41-01-4A to 

CMR D77-41-00-5A and CMR P77-00-00-6B to CMR P77-41-00-5A.

DECEMBER 2009Revised the Airworthiness Limitations section to reflect the assessment of the 767-300 

Boeing Converted Freighter's (BCF) Supplemental Structural Inspection Program. 

Revised 767-400 ER Landing Gear Safe Life Inner and Outer Cylinder landings by updating 

text from "16,6000" to "16,600".

Revised the 767 Passenger- to-Freighter Conversion Airplane paragraph by removing the 

flight cycle and flight hour limitations for the 767-300BCF.

Submitted by: John Sabolchy

(Boeing) 

Approved by: 

REVISIONS

REVISION AND REVISION DESCRIPTION 

MAY 2010
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MAY 2010Revised the Airworthiness Limitations – System information in Section D, Fuel Systems 

Airworthiness Limitations as requested by FAA Letter 140S-09-396 dated November 23, 2009.

Revised the Use of Alternate Tools paragraph as requested by FAA Letter 140S-09-396 

dated November 23, 2009 and as discussed in the FAA meeting on February 11, 2010.

Revised the Fuel Systems Airworthiness Limitations Table by replacing the word “per” with 

the words “Refer to”, where the reference is to a non-FAA approved manual (such as the Standard Wiring Practices Manual or the Airplane Maintenance Manual) and where there are specific procedures in the AWL.

Revised 28-AWL-10 by adding “all 767 airplanes” to AMM 28-21-02 to clarify applicability.Revised 28-AWL-22 by adding the word “two” to Step 1 to clarify the number of bonding 

straps.

Added 28-AWL-29 and 28-AWL-30 as Critical Design Configuration Control Items for the 

fuel boost pump conduit liner to preclude arcing development as a result of the wire insulation chafing inside the fuel tank wire conduits.

Submitted by: John Sabolchy

(Boeing) 

Approved by: 

 

REVISIONS

REVISION AND REVISION DESCRIPTION 

MAY 2010
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A. SCOPE

The scheduled maintenance requirements described in this section result from Model 767 airplane certification activities with thAdministration (FAA). Accordingly, this FAA approved Airworthiness Limitations and Certification Maintenance Requirements dreferenced in the Model 767 Type Certificate Data Sheet. These maintenance actions are mandatory.This Airworthiness Limitations Section is FAA approved and specifies maintenance required under Federal Aviation Regulation unless an alternative program has been FAA approved.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSThe Airworthiness Limitations may only be revised with the approval of the Seattle FAA Aircraft Certification Office (ACO).If the inspections cannot be accomplished due to repairs and/or modifications, an alternate inspection approved by the Seattle CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)These scheduled maintenance tasks may only be revised by the Seattle FAA ACO (appropriate regulatory authority). Principal (local regulatory authority) may not change these requirements or the intervals associated with these requirements.

B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

The Structural Inspection Program approved in Section 3 of the 767 Maintenance Review Board (MRB) Report and contained idescribes an initial baseline structural maintenance program for all Structural Significant Items (SSIs). This program was devethe guidelines of MSG-3 and partially satisfies the requirements of FAR 25.571 by providing accidental and environmental damfor all SSIs, and in some cases, fatigue damage detection opportunity. The supplemental structural inspections listed in this SeLimitations” are for those SSIs that do not receive adequate fatigue damage detection opportunity from the initial baseline strucin Section 8. The supplemental inspections shown in Section 9 Airworthiness Limitations are to be accomplished in conjunctiosubstitute for the existing structural maintenance program found in Section 8.

JUN 2000
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767 MAINTENANCE PLANNING DATA

The supplemental structural inspection program uses the Damage Tolerance Rating (DTR) system to determine the inspectionnecessary to provide adequate fatigue damage detection. The DTR system defines a required DTR (a numerical value) that mSSI. DTR Check Forms which define the inspection options and the required DTR are contained in Document D622T001-DTReach SSI. One is an example showing one possible method of achieving the required DTR. The second form is blank and inteallows development by an operator of a customized inspection program.THRESHOLDThe certifying authority (Seattle FAA ACO) requires designation of all SSIs into two categories. These two categories are referType 2. Type 1 structure requires the implementation threshold to be established by crack growth analysis. Type 2 structure is implementation threshold established by fatigue analysis (supported by test evidence) and allows for the future escalation of the sufficient data from the initial inspections statistically support an increased threshold. See Document D622T001-DTR for a detand Type 2 categories.The inspections are to be done on the basis of the threshold specified in the AWL – Structural Inspections table and repeat inspDTR Check Forms contained in Document D622T001-DTR.A formal control system must be established for removable structural parts (repairable/rotable/expendables) which are subject tsuch as the flap support members. If part usage history data is available for all parts, the supplemental inspection program wousage history data. If part usage history data is not available, but records indicate that no part changes have occurred between history data can be used to start a tracking program for the supplemental inspections. If parts usage data is not available and tswitched between airplanes in the same maintenance program, it should be assumed that the time on any part is equal to the omaintenance program. If a maintenance program includes airplanes from several operators, the oldest airplane in that group oas the oldest airplane in the maintenance program. After overhaul or upon replacement of a part, as appropriate, a tracking proto control the removable parts. This system must also apply to used structural parts which are purchased for installation on an aWhere no cumulative cycles history is available for any removed/interchangeable SSI, then calculate the accumulated flight cycinstallation history. If previous installation history, too, is not available then assume that the limiting cycles (threshold) has alreainspection is to be done before installation of the removed SSI on the applicable airplane series.

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The table shown on page 9.0-25 through 9.0-55 of this section (Airworthiness Limitations – Structural Limitations) define the ins

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

DEC 2009
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767 MAINTENANCE PLANNING DATA

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

for the -200, -300 Passenger, and -300BCF aircraft is different from that for the -300F Freighter and -400ER Passenger airc

DEC 2009
767 MAINTENANCE PLANNING DATA

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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 apPrevention and Control Program (CPCP) has occurred, constituting CPCP implementation.When reaching the threshold of 50,000 flight cycles (-200 and -300 Passenger or -300 Passenger converted to -300BCF aircramore as a -300 Passenger) or 40,000 flight cycles (-300F Freighter or -400ER Passenger or -300 Passenger converted to -30010,000 cycles as a -300 Passenger), all C-check (or higher) structural inspection repeat intervals must be no greater than those 8 (Structures C-check is defined in Section 1). This means that any operator, who has escalated the structures program by chaor the C-check interval, must reduce the repeat frequencies back to the MPD baseline structures program intervals before accu40,000 flight cycles respectively. The reason for this is that the FAR 25.571 damage tolerance evaluation takes credit for the bThe airworthiness limitations listed in Section 9 cover structure for which the required DTR is not satisfied by the baseline strucSection 8. Any continued escalation beyond the MPD baseline structures program may result in additional structure not meetinwas the basis of certification.767 PASSENGER-TO-FREIGHTER CONVERSION AIRPLANESCertain 767 airplanes are modified from passenger model airplanes to a freighter configuration via Boeing service bulletin. AfteBoeing passenger-to-freighter service bulletin, these 767-200 and 767-300 airplanes are designated as 767-200SF and 767-30of this chapter for additional data related to 767-200SF and 767-300BCF structural safe life parts.

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767 MAINTENANCE PLANNING DATA

For compliance to 14CFR §26.45 with respect to Fatigue Critical Alteration Structure (FCAS) and affected Fatigue Critical Baseoperation of the airplane is limited to 3,750 flight cycles or 11,250 flight hours, whichever occurs first (for the 767-200SF, Serial the time of conversion.Additionally, for the following significant structural items, the inspection threshold is 900 flight cycles or 2,700 flight hours, whichof conversion, for the Boeing Model 767 airplane Serial Number 22317.

SSI 53-50-I13B Rear Spar Bulkhead Inner Chord at Seat Track BracketSSI 53-50-I14C Aft Wheel Well Bulkhead-Hidden Detail at ChordSSI 57-10-I03A Center Section Rear Spar Lower Chord and SkinSSI 57-10-I03B Center Section Rear Spar Lower Chord and SkinSSI 57-10-I16 Lower Surface Side-of-Body SpliceSSI 57-20-I15A Outboard Wing Lower Surface Splice StringerSSI 57-20-I15B Outboard Wing Lower Surface Splice StringerSSI 57-20-I15C Outboard Wing Lower Surface Splice StringerSSI 57-20-I16D Outboard Wing Rear Spar Lower Chord and Skin

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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Certain 767-300BCF supplemental inspection thresholds are calculated based on the summation of fatigue damage accrued as freighter. These are identified by “Combined Threshold” in the Threshold column. Refer to Figure 2 to determine the threshold Certain 767-300BCF supplemental inspection thresholds are calculated from the date of modification. These are identified by “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.

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767 MAINTENANCE PLANNING DATA

FIGURE 2. Combined Passenger and Freighter Life Threshold

Combined Threshold

25000300003500040000450005000055000

0 5000 10000 15000 20000 25000 30000 35000 40000 45000 50

Flights as 300ER (Cycles)

Combined Threshold (Cycles)

53-30-I01 BCF2 Section 43 Crown SK/STR at Aft Edge External Doubler53-30-I01 BCF10 Crown Stringer STA 654+110 to STA 78653-30-I04D BCF1 Inner Skin at Lower Fastener Row S-26L Lap53-30-I04A BCF2 Outer Skin at Upper Fastener row S-8L Lap (L2 Panel)53-30-I04B STR 8R Lap BS 434 - 654+22 Inner Skin at Lower Fastner Row

NOV 2009
767 MAINTENANCE PLANNING DATA

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FIGURE 3. Mod Date Sensitive Structure

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767 MAINTENANCE PLANNING DATA

REPEAT INSPECTION INTERVALA repeat inspection interval for the fatigue inspection of an SSI is established from its DTR Check Form. Airplanes with an avehours 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 

DTR for DTR Check Forms). Revision to the required DTR or the DTR curve is not allowed without approval from the Seattle F

REPORTING RESULTS OF STRUCTURAL INSPECTIONSAll cracks found during these inspections shall be reported within ten (10) days directly to the Manager of the Seattle FAA ACODirectorate, FAA and to Boeing Commercial Airplanes using the Discrepant Structure Report Form. Refer to Document D622Treport form (any suitable alternative which contains the same information may be used).

DEC 2009
767 MAINTENANCE PLANNING DATA

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The following pages, included in the Airworthiness Limitations – Structural Inspections table, list the Airworthiness Limitation surequirements. Each item is listed by SSI Number, DTR Check Form Title, Inspection Zone, Airplane/Engine Applicability, Type corresponding DTR Check Forms (in Document D622T001-DTR) for each item listed in the table. Where there is more than onNumber, the DTR Check Form Title is the unique identifier along with the Airplane/Engine Applicability. Airplane/engine applica

ALL = All Airplanes PASS (-ER ONLY) = Passenger Airplanes, Extended Range OnlyPASS = Passenger Airplanes < 8 HOURS = Airplanes with cumulative stage length (Flight Hou200 = 767-200, -200ER less than 8 hours.300 = 767-300, -300ER > 8 HOURS = Airplanes with cumulative stage length (Flight Hou

300BCF = 767-300 Boeing Converted Freighter equal to or more than 8 hours.400E = 767-400ER300F = All 767-300 Freighters4000 = P&W PW4052, PW4056, PW4060, PW40627R4 = P&W JT9D-7R4D and -7R4E80A = GE CF6-80A80C = GE CF6-80C524 = RR RB211-524H

DEC 2009
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767 MAINTENANCE PLANNING DATA

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

27-40-I01A Stabilizer Trim Actuator – Lower Gimbal Lug Assy BS 1708.5, WL 239.9 311, 312 ALL 

27-40-I01B Stabilizer Trim Actuator – Lower Gimbal Plate Assy BS 1708.5, WL 239.9, BL 0.0 311, 312 400E 

52-30-I02A Standard Cargo Door forward and aft – Applicable to 767-200, -300, -300BCF 

(aft) and -400 passenger airplanes – Beam #2 @ STA 210.15, section between 

upper access and Vent Door Cutouts

821, 822 200, 300BCF,

300 PASS, 400E

<2> 

52-30-I05A Latch Cam Support Frame Fitting – Forward large Cargo Door – Fitting Lug Bore 821 ALL

<2>

52-30-I05B Latch frame inner chord – Forward large Cargo Door – Latch Frame Inner Chord 

at Splice to Latch Frame Support Fitting

821 ALL 

52-30-I05C Outer Skin – Forward large Cargo Door – Outer Skin at attachment to main hinge 

segments at forward and aft ends of the door

821 ALL 

52-30-I07A Latch Cam Support Fitting – Main Deck Cargo Door – Fitting Lug Bore 838 300BCF, 300F

<2>

52-30-I07B Latch Frame Inner Chord – Main Deck Cargo Door – Latch Frame Inner Chord at 

Splice to Latch Frame Support Fitting

838 300BCF, 300F

<2>

52-30-I07C Outer Skin – Main Deck Cargo Door – Outer Skin at attachment to main hinge 

segments at forward and aft ends of the door

838 300BCF, 300F

<2>

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

52-30-I07E MDCD Outer Skin Lap Splice – Upper row (upper skin) – Intercostal #5 838 300BCF, 300F

<2>

52-30-I07F MDCD Outer Skin Lap Splice – Lower row (lower skin) – Intercostal #5 838 300BCF, 300F

<2>

52-30-I09A Latch Cam Support Fitting – Aft large Cargo Door – Fitting Lug Bore 822 300F

<2>

52-30-I09B Latch Frame Inner Chord – Aft large Cargo Door – Latch Frame Inner Chord at 

Splice to Latch Frame Support Fitting

822 300F 

52-30-I09C Outer Skin – Aft large Cargo Door – Outer Skin at attachment to main hinge 

segments at forward and aft ends of the door

822 300F 

53-10-I07A53-30-I04A53-60-I05A

Skin Longitudinal Lap Splices – Upper Row – Crown and Upper Lobe, 

Sections 41, 43 and 46.

L/N 973, Lap S-8R: BS 1547 to BS 1561 and S-7R to S-9R centerlines must be 

inspected with external detailed inspection every 600 flight cycles (after reaching threshold).

DTR Form not applicable to: 1) L/N 945: STA 617 S-8R. Must inspect per 

SB 767-53-0190. 2) L/N 963: STA 1465 - 1476, STR 8L. Must inspect per SB 767-53-0208. 3) 300BCF: S-8L STA 654+22 to 654+110 (not applicable) and S-2R 654+22 to 654+110 (no inspection).

220, 230, 250 ALL

Except L/N 945, 

L/N 963, and L/N 973

53-10-I07B53-30-I04B53-60-I05B

Skin Longitudinal Lap Splices – Lower Row – Crown and Upper Lobe, 

Sections 41, 43 and 46.

L/N 973, Lap S-8R: BS 1547 to BS 1561 and S-7R to S-9R centerlines must be 

inspected with external detailed inspection every 600 flight cycles (after reaching threshold).

DTR Form not applicable to: 1) L/N 945: STA 617 S-8R. Must inspect per 

SB 767-53-0190. 2) L/N 963: STA 1465 - 1476, STR 8L. Must inspect per SB 767-53-0208. 3) 300BCF: S-2R STA 654+22 to 654+110 (No inspection)

220, 230, 250 ALL

Except L/N 945,

L/N 963, and L/N 973

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
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767 MAINTENANCE PLANNING DATA

53-10-I07C53-30-I04C53-60-I05C

Skin Longitudinal Lap Splices – Upper Row – Bilge and Lower Lobe, Sections 41, 

43 and 46.

DTR Form not applicable to: 1) L/N 946, STA 1175-1197, S-26R. Must inspect 

per SB 767-53-0191. 2) L/N 873: STA 1197+82 and 1197+121, S-36R. Must inspect per SB 767-53-0103. 3) L/N 969 from STA 1408 to 1417 S-26R: Must inspect per SB 767-53-0210. 4) L/N 971, Lap S-26L: BS 654 + 22 to BS 654 + 44 and S-25L to S-27L centerlines must be inspected with external detailed inspection every 600 flight cycles (after reaching threshold). 5) L/N 967, STA 1564 - 1582, STR 26R. Must inspect per SB 767-53-0212. 6) 300BCF: S-37R STA 368 to 434 (No inspection)

100 ALL

Except L/N 873,

L/N 946, L/N 967, 

L/N 969, and L/N 971

53-10-I07D53-30-I04D53-60-I05D

Skin Longitudinal Lap Splices – Lower Row – Bilge and Lower Lobe, Sections 41, 

43 and 46.

DTR Form not applicable to: 1) L/N 946, STA 1175-1197, S-26R. Must inspect 

per SB 767-53-0191. 2) L/N 873: STA 1197+82 and 1197+121, S-36R. Must inspect per SB 767-53-0103. 3) L/N 969 from STA 1408 to 1417 S-26R: Must inspect per SB 767-53-0210. 4) L/N 971, Lap S-26L: BS 654 + 22 to BS 654 + 44 and S-25L to S-27L centerlines must be inspected with external detailed inspection every 600 flight cycles (after reaching threshold). 5) L/N 967, STA 1564 - 1582, STR 26R. Must inspect per SB 767-53-0212. 6) 300BCF: STA 434 to 654+110, S-26L.

100 ALL

Except L/N 873,

L/N 946, L/N 967,

L/N 969, and L/N 971

53-10-I08B53-30-I24B

Frames above S-20 220, 230 ALL

Except 300BCF

53-10-I08B53-30-I24B

BCF 3 -– Frames above S-20, Not Applicable to Areas of Hidden Frame Structure 220, 230 300BCF 

53-10-I08C53-30-I24C53-60-I08C

Frames, S-20 and below. BS 246 to BS 786 and BS 1065 to BS 1582 100 ALL

Except 300BCF

53-10-I08C53-30-I24C53-60-I08C

BCF 5 – Frames below S-20, All Frames Except the Areas of Hidden Frame Structure 100 300BCF 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

53-10-I10A Forward Passenger Entry/Service Door Cutout- Edge Frame – Inner Chord Door 

STA 76.3, S-7 to S-12 and S-19 to S-23, Door STA 123.7, S-8 to S-12 and S-19 to S-23

119, 221, 222, 

223, 224

ALL 

53-10-I10B Forward Passenger Entry/Service Door Cutout- Upper Main Sill – Inner Chord Door 

STA 100 to Door STA 129.9

221, 222 ALL 

53-10-I12 Main Equipment Center Access Door Cutout

BS 303 – BS 325, LBL 13.1 – RBL 13.1

119 ALL 

53-10-I13 Forward Equipment Bay Access Door Cutout

BS 144.5 – BS 163.2. LBL 9 – RBL 9

113, 114 ALL 

53-10-I14A Window #1 Cutout Structure – AB POST 211, 212 ALL 

53-10-I14B Window #1 Cutout Structure – BD SILL 211, 212 ALL 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
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767 MAINTENANCE PLANNING DATA

53-10-I16 Window #2 Cutout Structure – EF POST 211, 212 ALL 

53-10-I18A NLG Wheel Well – Canted Bulkhead Details – Outer Chord Typical Locations Between 

S-32L & S-32R

113, 114 ALL 

53-10-I18B NLG Wheel Well – Canted Bulkhead Details – Outer Chord Hidden Locations 

L/RBL 10.60 & L/RBL 25.00

113, 114 ALL 

53-10-I20A NLG Wheel Well – BL25 Side Panel Details – Vertical Beams & Panel Web from 

BS 180.5 to BS 276

117, 118 ALL 

53-10-I20B NLG Wheel Well – Trunnion Support Fitting at Top Panel Beam Attachment. BS 276, 

BL 30, WL 181 to WL 187

117, 118 ALL 

53-10-I20C NLG Wheel Well – Trunnion Support Fitting at Strap Attachment. BS 276, BL 30, 

WL 165 to WL 169

117, 118 ALL 

53-10-I21A NLG Wheel Well – BS 287 Bulkhead Details – WL 159 Beam & Bulkhead Web 

from LBL 27 to LBL 23, LBL 10.0 to RBL 10.0, RBL 23 to RBL 27

119 ALL

L/N 1-757

<1>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

53-10-I21A NLG Wheel Well – BS 287 Bulkhead Details – WL 159 Beam & Bulkhead Web 

from LBL 10.0 to RBL 10.0

119 ALL

L/N 758 and on

<1>

53-10-I21B NLG Wheel Well – BS 287 Bulkhead Details – Outer Chord Typical Locations between 

S-24L and S-24R

119 ALL 

53-10-I21C NLG Wheel Well – BS 287 Bulkhead Details – Outer Chord – Stringer Splices between 

S-24L and S-24R

119 ALL 

53-10-I21D NLG Wheel Well – BS 287 Bulkhead Details – Outer Chord Hidden Locations at 

S-36L, S-36R and S-27R

119 ALL 

53-10-I21E NLG Wheel Well – BS 287 Bulkhead Details – WL 159 Beam and Bulkhead Web 

LBL 27 to LBL 23 and RBL 23 to RBL 27, C/L 758 on

119 ALL 

53-10-I33B BCF 2 – Section 41 External Skin Doubler first fastener common to skin and doubler 

between BS 368 and BS 434 at S-38L

121 300BCF

<4>

53-10-I33E BCF 5 – Section 41 Service Panel Cutout Structure BS 390 to BS 412; BL 0 

to RBL 13.65

121 300BCF

<4>

53-30-I0153-50-I0153-60-I01

Fuselage Crown Stringers – BS 654 to BS 1395, S-8L to S-8R

DTR Check Form not applicable to: 1) L/N 969 at S-4R from STA 758 to STA 770 must be inspected per SB 767-53-0210. 2) 300BCF: S-4L to S-4R from STA 654+110 to 786.

230, 240, 250 ALL 

Except L/N 969

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

53-30-I01 BCF 1 – Crown Doubler, first fastener row common to skin and doubler between 

Stringers S-8 and S-6 BS 654+28 to 654+115

231, 232 300BCF

<4>

53-30-I01 BCF 2 – Crown Doubler Aft Edge Circumferential Crack Between BS 654+115; 

Between Stringer S-7L and S-7R

231, 232 300BCF

<4>

53-30-I01 BCF 3 – Circumferential Splice – Upper Crown at BS 654+22 233, 234 300BCF

<4>

53-30-I01 BCF 5 – Crown Skin Doubler – Longitudinal Crack in Skin at forward corners at 

BS 654+22 at S-8L and S-8R

231, 232 300BCF

<4>

53-30-I01 BCF 9 – Fuselage Crown Skin STA 654+115 to 786 STR-4R to 4L 231, 232 300BCF 53-30-I01 BCF 10 – Fuselage Crown Stringers 230 300BCF 

53-30-I04A Skin Longitudinal Lap Splices – Upper Row – Crown and Upper Lobe, Sections 41, 43 

and 46

230 300BCF 

53-30-I04A BCF2 Skin Longitudinal Lap Splices Upper Row – Upper Lobe 230 300BCF 53-30-I04B Skin Longitudinal Lap Splices – Lower Row – Crown and Upper Lobe, Sections 41, 43 

and 46

230 300BCF 

53-30-I04B Skin Longitudinal Lap Splices – Lower Row – Crown and Upper Lobe, Sections 41, 43 

and 46

230 300BCF 

53-30-I04D BCF 1 – Skin Longitudinal Lap Splices – Lower Row – Bilge S-26L MDCD and 

L2 Panel

DTR Form not applicable to: 1) L/N 269, STA 654+22 to 654+110 must be inspected 

per TBC-ANA-0008-01B(R1) 20 April 2009.

100 300BCF

Except for L/N 269

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

53-30-I0553-30-I2153-30-I2753-50-I0353-60-I0353-60-I26

Fuselage Circumferential Splices in the Body Crown – Specified LocationsDTR Check Form not applicable to: 1) 300BCF: S-4L to S-4R STA 654. S-4L to S-4R 

STA 654+22.

230, 240, 250 200

300BCF

300F

300 PASS

<3>

53-30-I0553-30-I0853-30-I2153-50-I0353-60-I0353-60-I0453-60-I2453-60-I33

Fuselage Circumferential Splices in the Body Crown – Specified Locations 230, 240, 250 400E

<2>

53-30-I14A Forward Main Cargo Door Cutout – Edge Frames – Frames at STA 539.5 & 615.5 

Stringers S-17R to S-21 R and S-28R to S-36R

122, 124, 232 200

300 PASS

53-30-I19A Forward Large Cargo Door Cutout – Edge Frame Inner Chord at BS 478, S-23R to 

S-28R & at BS 618, S-27R to S-28R & S-29R to S-30R

122 200

300 PASS

53-30-I19B Forward Large Cargo Door Cutout – Edge Frame Inner Chord at BS 478, S-26R to 

S-27R and at BS 618, S-29R to S-30R

122 200

300 PASS

53-30-I19C Forward Large Cargo Door Cutout – Edge Frame at BS 618, S-28R to S-29R 122 200

300 PASS

53-30-I19D Forward Large Cargo Door Cutout – Lower Sill: BS 610 - 632, Upper Sill: BS 456 - 

478, BS 482 - 493

122, 124 200

300 PASS

53-30-I19E Forward Large Cargo Door Cutout – Upper Sill: BS 478 – 482 122 200

300 PASS

53-30-I19F Forward Large Cargo Door Cutout – Upper Sill: BS 480 122 200

300 PASS

53-30-I19G Forward Large Cargo Door Cutout – Upper Sill: BS 482 to BS 493 122 200

300 PASS

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

53-30-I19AB Forward Large Cargo Door Cutout – FWD Edge Frame Inner Chord at BS 478, S-20R 

to S-22R and at BS 618, S-20R to S-22R

122 300BCF

300F

400E

<2>

53-30-I19AC Forward Large Cargo Door Cutout – FWD Edge Frame Inner Chord at BS 478, S-17R 

to S-20R and S-22R to S-23R

122, 232 300BCF

300F

400E

<2>

53-30-I19AD Forward Large Cargo Door Cutout – Upper Main Sill Inner Chord at BS 607 to BS 618 122 300BCF

300F

400E

<2>

53-30-I19AD1 Forward Large Cargo Door Cutout – Upper Main Sill Inner Chord Hidden Locations at 

BS 607 to BS 618

122 300BCF

300F

400E

<2>

53-30-I19AF Forward Large Cargo Door Cutout – Lower Main Sill Inner Chord Hidden Locations at 

BS 466 to BS 483 and BS 614 to BS 625

124 300BCF

300F

400E

<2>

53-30-I19AF1 Forward Large Cargo Door Cutout – Lower Main Sill Inner Chord at BS 466 to BS 483 

and BS 614 to BS 625

124 300BCF

300F

400E

<2>

53-30-I20A Forward Large Cargo Door Cutout – Lower Latch Backup Structure – Latch Support 

Fitting at BS 487.7 & BS 608.3

124 ALL 

53-30-I22C Mid Passenger Entry/Service Door Cutout – Edge Frame Inner Chord at BS 654+ 44, 

S-8 to S-15, BS 654+91.4, S-8 to S-20

230 300 PASS

400E

53-30-I22D Mid Passenger Entry/Service Door Cutout – Upper Main Sill Inner Chord 230 300 PASS 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

53-30-I22D Mid Passenger Entry/Service Door Cutout – Upper Main Sill Inner Chord – 

BS 654+33 to BS 654+110

230 400E 

53-30-I24A53-50-I01A53-50-I02A53-60-I08A

Frames above S-20 230, 240, 250 ALL

Except 300BCF

53-30-I24A53-50-I01A53-50-I02A53-60-I08A

 BCF 1 – Frames above S-20 231, 232 300BCF 

53-30-I24A BCF 2 – Frames above S-20 231, 232 300BCF

<4>

53-30-I24B BCF 4 – Frames above S-20, Applicable to Areas of Hidden Frame Structure 220, 230 300BCF

<4>

53-30-I24C53-60-I08C

BCF 6 – Frames below S-20, Applicable Only to Areas of Hidden Frame Structure 100 300BCF

<4>

53-30-I27 BCF 2 – Circumferential Butt Splice 654+22 Splice Plate First Fastener Row 

FWD/AFT of Splice at BS 654+22

231, 232 300BCF 

53-30-I28 BCF 1 – Main Deck Cargo Door Cutout – Auxiliary Sill Inner Chord 231 300BCF

<4>

53-30-I28A Reinforcement Around Cutouts – Main Deck Cargo Door – Cutout Structure – 

Upper Main Sill Inner Chord at BS 492

231 300BCF

300F

<2>

53-30-I28B Reinforcement Around Cutouts – Main Deck Cargo Door – Cutout Structure – 

Lower Main Sill Inner Chord at BS 632

231 300BCF

300F

<2>

53-30-I28C Reinforcement Around Cutouts – Main Deck Cargo Door – Cutout Structure – 

FWD Edge Frame Inner Chord at S-5L

233 300BCF

300F

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

53-30-I28D Reinforcement Around Cutouts – Main Deck Cargo Door – Aft Edge Frame at BS 632 

and S-16L – Frame Splice

231 300BCF

300F

<2>

53-30-I28E Reinforcement Around Cutouts – Main Deck Cargo Door – Aft Edge Frame at BS 632 

and S-2L

231, 233 300BCF

300F

<2>

53-30-I28F Reinforcement Around Cutouts – Main Deck Cargo Door – Cutout Structure – 

Upper and Lower Main Sill Outer Chord at BS 496 and 628

231, 233 300BCF

300F

<2>

53-50-I06A Single Emergency Exit Cutout – Frame Inner Chords at BS 859.5, S-18 to S-20 and at 

BS 883.5, S-16 to S-20

241, 242 200 

53-50-I06B Single Emergency Exit Cutout – Frame Inner Chords at Sill Intersect at BS 859.5

and 883.5

241, 242 200 

53-50-I06C Single Emergency Exit Cutout – Sill Inner Chord – Upper Sill at BS 859.5 to BS 871.5 241, 242 200 53-50-I06D Single Emergency Exit Cutout – Sill Inner Chord at Frame Intersect at BS 859.5 

and BS 883.5

241, 242 200 

53-50-I06E Single Emergency Exit Cutout – Sill Outer Chord 241, 242 200 

53-50-I06F Single Emergency Exit Cutout – Sill Outer Chord at Frame Intersect 241, 242 200 

53-50-I11 BS 1043 Frame Splice with the Landing Gear Fitting – BS 1043, BL 92, WL 193 to 

WL 199

141, 142 ALL 

53-50-I13A Fuselage Rear Spar Bulkhead – Bulkhead Fitting Inboard Prong Attachment to Wing 

Rear Spar

DELETED

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

53-50-I13B Fuselage Rear Spar Bulkhead – Bulkhead Fitting Inner Chord S-20 to S-21 at Seat 

Track Bracket

131, 132 ALL 

53-50-I13C Fuselage Rear Spar Bulkhead – Inboard Chord Flange – BS 955, BL 91, S-18 to S-20 241, 242 ALL 

53-50-I14A Aft Wheel Well Bulkhead BS 1065 – Vertical Beam BL 26 Intercostal Upper Chord 

Splice

143, 144 ALL 

53-50-I14B Aft Wheel Well Bulkhead BS 1065 – Hidden Details at Chord Splices S-27 to S-28 and 

S-35 to S-36

151, 152 ALL 

53-50-I14C Aft Wheel Well Bulkhead BS 1065 – Hidden Details at Chord between S-29 & S-34 151, 152 ALL 

53-50-I1853-50-I2453-50-I28

Section 45 Stub Frames – BS 808 – 933 Frame Inner Chord at Stub Beam 131, 132 200

300BCF

300F

300 PASS

53-50-I19 MLG Wheel Well – BS 1021 Transverse Floor Beam Lower Chord – From LBL 33 to 

LBL 60 & RBL 33 to RBL 60

143, 144 300BCF

PASS

53-50-I19B MLG Wheel Well Transverse Floor Beam BS 1021 Lower Chord – From LBL 33 to 

LBL 60 & RBL 33 to RBL 60

DELETED

53-50-I22A Dual Emergency Exit Cutout – Frame Inner Chords 241, 242 200

300 PASS

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

53-50-I22A BCF – Dual Emergency Exit Cutout Edge – Frame Inner Chords 241, 242 300BCF 

53-50-I22B Dual Emergency Exit Cutout – Frame Inner Chord at Sill Intersect 241, 242 200

300 PASS

53-50-I22B BCF – Dual Emergency Exit Cutout Edge Frame – Inner Chord at Sill 241, 242 300BCF 

53-50-I22C BCF – Dual Emergency Exit Cutout – Sill Inner Chord 241, 242 300BCF 

53-50-I22D BCF – Dual Emergency Exit Cutout – Sill Inner Chord at Frame 241, 242 300BCF 

53-50-I22E BCF – Dual Emergency Exit – Sill Inner Chord & Strap BS 859.5 and BS 903.5 241, 242 300BCF 

53-50-I22F BCF – Dual Emergency Exit Cutout – Sill Outer Chord 241, 242 300BCF 

53-50-I22G BCF – Dual Emergency Exit Cutout – Sill Outer Chord at Frame Intersect 241, 242 300BCF 

53-50-I22 BCF 1 Dual Over wing Emergency Exit Auxiliary Sill at Frame Intersect 241, 242 300BCF

<4>

53-50-I22 BCF 2 Dual Over wing Emergency Exit Auxiliary Sill 241, 242 300BCF

<4>

53-50-I22C Dual Emergency Exit Cutout – Sill Inner Chord 241, 242 200

300 PASS

53-50-I22D Dual Emergency Exit Cutout – Sill Inner Chord at Frame Intersect 241, 242 200

300 PASS

53-50-I22E Dual Emergency Exit Cutout – Upper Sill Inner Chord at BS 859.5 and BS 903.5 241, 242 300 PASS 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

53-50-I22F Dual Emergency Exit Cutout – Sill Outer Chord 241, 242 200

300 PASS

53-50-I22G Dual Emergency Exit Cutout – Sill Outer Chord at Frame Intersect 241, 242 200

300 PASS

53-50-I25A Single Aft Emergency Exit Cutout – Frame Inner Chords 241, 242 300 PASS 

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

53-50-I25C Single Aft Emergency Exit Cutout – Sill Inner Chord 241, 242 300 PASS 

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

53-50-I25E Single Aft Emergency Exit Cutout – Upper Sill Inner chord BS 903.5 241, 242 300 PASS 

53-50-I25F Single Aft Emergency Exit Cutout – Sill Outer Chord 241, 242 300 PASS 

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

53-50-I28 Section 45 Stub Frames – BS 808 – 933 Frame Inner Chord at Stub Beam 131, 132 400E 

53-60-I02 BCF – Fuselage Stringer with Stringer Reinforcement Strap STA 1076 to 1143 

STR-10R to 13R and STR -9L to 13L

153, 154 300BCF 

53-60-I06C53-30-I14C

Forward/Aft Main Cargo Door Cutout – Edge Frames – Outer Chord at BS 539.5, 

BS 615 and BS 1270, BS 1346 between Upper & Lower Sills

122, 154 PASS 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

53-60-I06D53-30-I14D

Forward/Aft Main Cargo Door Cutout – Upper Main Sill – Inner Chord, BS 522 to 

BS 544 and BS 1346 to BS 1395

122, 154 300BCF

300 PASS

53-60-I06E53-30-I14E

Forward/Aft Main Cargo Door Cutout – Lower Main Sill – Inner Chord, BS 610 to 

BS 632 and BS 1263 to BS 1270

122, 154 PASS 

53-60-I06B Aft Main Cargo Door Cutout – Edge Frames – Inner Chord at BS 1270, S-23R to 

S-29R and at BS 1346, S-23R to S-29R

154 300BCF

300 PASS

53-60-I06C BCF – Aft Main Cargo Door – Edge Frame BS 1270 and 1346, Outer Chord Between 

Upper and Lower Sills

153, 154 300BCF 

53-60-I06E BCF 1 – Aft Main Cargo Door Cutout – Lower Sill Inner Chord at Body STA 1263 to 

STA 1270

153, 154 300BCF 

53-60-I10 BCF 2 – Bulk Cargo Door Cutout – Edge Frames Inner Chord/Strap 161, 163 300BCF

<4>

53-60-I10A Bulk Cargo Door Cutout – Edge Frames Inner Chord/Strap 161, 163 ALL 

53-60-I10B Bulk Cargo Door Cutout – Frame Splice – Aft Edge Frame, BS 1461 Inner Chord 

at S-26

161 ALL 

53-60-I10C Bulk Cargo Door Cutout – Upper Main Sill Inner Chord and Strap – BS 1461 161 300F

<2>

53-60-I14E Aft Passenger Entry/Service Door Cutout – Edge Frames, Inner Chord, Door Station 

876.3, S-9 to S-12 and S-17 to S-23 and Door Station 923.7, S-8 to S-13 and S-21 to S-23

251, 252 300BCF

300 PASS

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

53-60-I14F Aft Passenger Entry/Service Door Cutout – Upper Main Sill – Inner Chord, Door 

Station 911 to BS 1562

251, 252 300BCF

300 PASS

53-60-I27A Type I Door Cutout – Edge Frame – Inner Chord – BS 1153, S-8 to S-13 & S-16 to 

S-23 and BS 1183.4, S-8 to S-13 and S-16 to S-23

153, 154, 251, 252 300 PASS 

53-60-I27A Type I Door Cutout – Edge Frame – Inner Chord – BS 1153, S-8 to S-13 & S-16 to 

S-23 and BS 1183.4, S-8 to S-13 and S-16 to S-23

153, 154, 251, 252 400E 

53-60-I27B Type I Door Cutout – Upper Main Sill – Inner Chord, BS 1131 to BS 1197+22 251, 252 300 PASS

400E

53-60-I27C Type I Door Cutout – Lower Main Sill – Inner Chord, BS 1131 to BS 1175 251, 252 300 PASS

400E

53-60-I29A Aft Large Cargo Door Cutout – Edge Frame – Inner Chord, BS 1344, S-24 154 300F

<2>

53-60-I29B Aft Large Cargo Door Cutout – Edge Frame – Inner Chord, BS 1344, S-24.3 154 300F

<2>

53-60-I29C Aft Large Cargo Door Cutout – Upper Main Sill – Inner Chord, BS 1219 154 300F

<2>

53-60-I29D Aft Large Cargo Door Cutout – Lower Main Sill – Inner Chord, BS 1344 154, 156 300F

<2>

53-60-I29F Aft Large Cargo Door Cutout – Lower Main Sill – Inner Chord, BS 1334.3 154, 156 300F

<2>

53-60-I30A Aft Large Cargo Door Cutout – Latch Backup Fitting – BS 1331.58 Latch 12 

Lower Flange

154 300F

<2>

53-80-I01A Aft Pressure Bulkhead – Circumferential Attachment of Web to Y-Ring 165, 166, 251, 

252, 253, 254

ALL

L/N 424 & on

<1>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

53-80-I01B Aft Pressure Bulkhead – Radial Web Lap Splices 311, 312 ALL

L/N 424 & on

<1>

53-80-I01C Aft Pressure Bulkhead – Radial Web Lap Splices 311, 312 ALL

L/N 424 & on

<1>

53-80-I01D Aft Pressure Bulkhead – Circumferential Tear Strap Splice 311, 312 ALL

L/N 424 & on

<1>

53-80-I01E Aft Pressure Bulkhead – Circumferential Tear Strap 311, 312 ALL

L/N 424 & on

<1>

53-80-I03 Section 48 – Jackscrew Fitting Lug – Upper Bulkhead at STA 1702 311, 312 ALL 

53-80-I13 Section 48 – Pivot Fitting Lug 313, 314 ALL 53-80-I1553-80-I1653-80-I17

BS 1809.5 Bulkhead Outboard Chord 313, 314 ALL

L/N 710 & on

<1>

53-80-I25 Horizontal Stabilizer Fitting Hinge Pins – BS 1809, BL 41.5 313, 314 ALL 54-50-I01 Typical Midspar Chord Construction – JT9D Strut 432, 434, 436, 

442, 444, 446

7R4 

54-50-I01 Typical Midspar Chord Construction – PW4000 Strut 432, 434, 436, 

442, 444, 446

4000 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

54-50-I01 Typical Midspar Chord Construction – CF6-80A Strut 432, 434, 436, 

442, 444, 446

80A 

54-50-I01 Typical Midspar Chord Construction – CF6-80C Strut 432, 434, 436, 

442, 444, 446

80C (Except 400E) 

54-50-I01a Forward Midspar Chord – CF6-80C Strut 432, 442 80C (400E)

< 8 Hours

<2>

54-50-I01a Forward Midspar Chord – CF6-80C Strut 432, 442 80C (400E)

> 8 Hours

<2>

54-50-I01c Forward Midspar (Visible Portions) – CF6-80C2 Strut 432, 442 80C (400E)

< 8 Hours

<2>

54-50-I01c Forward Midspar (Visible Portions) – CF6-80C2 Strut 432, 442 80C (400E)

> 8 Hours

<2>

54-50-I02

54-50-I03a

Sideskins/Skins, Stiffeners and Back-Up Chords – RB211 Strut 433, 443 524

<2>

54-50-I03b Lower Spar Chords, Webs and Thrust Plate – RB211 Strut 431, 433, 441, 443 524

<2>

54-50-I04 Forward Engine Mount Bulkhead – RB211 Strut 433, 443 524

<2>

54-50-I04 Typical Midspar Chord Construction – JT9D Strut

Note: No DTR Check Form.

432, 434, 436, 

442, 444, 446

7R4 

54-50-I04 Typical Midspar Chord Construction – PW4000 Strut

Note: No DTR Check Form.

432, 434, 436, 

442, 444, 446

4000 

54-50-I04 Typical Midspar Chord Construction – CF6-80A Strut

Note: No DTR Check Form.

432, 434, 436, 

442, 444, 446

80A 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

54-50-I04 Typical Midspar Chord Construction – CF6-80C Strut

Note: No DTR Check Form.

432, 434, 436, 

442, 444, 446

80C (Except 400E) 

54-50-I04a Mid-Spar Fitting to Chord Splice – CF6-80C Strut 434, 436, 444, 446 80C (400E)

< 8 Hours

<2>

54-50-I04a Mid-Spar Fitting to Chord Splice – CF6-80C Strut 434, 436, 444, 446 80C (400E)

> 8 Hours

<2>

54-50-I04c Mid-Spar Chord, Aft (Hidden Details) – CF6-80C Strut 434, 436, 444, 446 80C (400E)

< 8 Hours

<2>

54-50-I04c Mid-Spar Chord, Aft (Hidden Details) – CF6-80C Strut 434, 436, 444, 446 80C (400E)

> 8 Hours

<2>

54-50-I04e Mid-Spar Chord, Aft (Visible Details) – CF6-80C Strut 434, 436, 444, 446 80C (400E)

< 8 Hours

<2>

54-50-I04e Mid-Spar Chord, Aft (Visible Details) – CF6-80C Strut 434, 436, 444, 446 80C (400E)

> 8 Hours

<2>

54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – JT9D Strut 432, 442 7R4

<2>

54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – PW4000 Strut 432, 442 4000

<2>

54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – CF6-80A Strut 432, 442 80A

<2>

54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – CF6-80C Strut 432, 442 80C (Except 400E)

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

54-50-I05a Forward Engine Mount Fitting Thrust Tang – CF6-80C Strut 432, 442 80C (400E)

<2>

54-50-I06 Aft Engine Mount Bulkhead – JT9D Strut 434, 436, 444, 446 7R4 54-50-I06 Aft Engine Mount Bulkhead – PW4000 Strut 434, 436, 444, 446 4000 

54-50-I06 Aft Engine Mount Bulkhead – CF6-80A Strut 436, 437, 446, 447 80A 54-50-I06 Aft Engine Mount Bulkhead – CF6-80C Strut 436, 437, 446, 447 80C (Except 400E) 

54-50-I06a Aft Engine Mount Bulkhead (Barrel Nut Bore) – CF6-80C Strut 436, 437, 446, 447 80C (400E)

< 8 Hours

<2>

54-50-I06a Aft Engine Mount Bulkhead (Barrel Nut Bore) – CF6-80C Strut 436, 437, 446, 447 80C (400E)

> 8 Hours

<2>

54-50-I06c Aft Engine Mount Bulkhead (Vertical Splice Strap) – CF6-80C Strut 436, 437, 446, 447 80C (400E)

< 8 Hours

<2>

54-50-I06c Aft Engine Mount Bulkhead (Vertical Splice Strap) – CF6-80C Strut 436, 437, 446, 447 80C (400E)

> 8 Hours

<2>

54-50-I06d Aft Engine Mount Bulkhead (Aft Flange) – CF6-80C Strut 436, 437, 446, 447 80C (400E)

< 8 Hours

<2>

54-50-I06d Aft Engine Mount Bulkhead (Aft Flange) – CF6-80C Strut 436, 437, 446, 447 80C (400E)

> 8 Hours

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting – JT9D Strut

Note: No DTR Check Form.

437, 447 7R4 

54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting – PW4000 Strut

Note: No DTR Check Form.

437, 447 4000 

54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting – CF6-80A Strut

Note: No DTR Check Form.

437, 447 80A 

54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting – CF6-80C Strut

Note: No DTR Check Form.

437, 447 80C (Except 400E) 

54-50-I09 Midspar Fitting – JT9D Strut

Note: No DTR Check Form.

437, 447 7R4 

54-50-I09 Midspar Fitting – PW4000 Strut

Note: No DTR Check Form.

437, 447 4000 

54-50-I09 Midspar Fitting – CF6-80A Strut

Note: No DTR Check Form.

437, 447 80A 

54-50-I09 Midspar Fitting – CF6-80C Strut

Note: No DTR Check Form.

437, 447 80C (Except 400E) 

54-50-I09 Diagonal Brace and Strut Attach Fitting and Fuse Pins – RB211 Strut

Note: No DTR Check Form.

434, 444 524 

54-50-I09a

54-50-I0754-50-I0854-50-I12

Strut to Wing Attachments (Midspar Fitting) – CF6-80C Strut 431, 433, 437, 

441, 443, 447, 

511, 521, 611, 621

80C (400E)

< 8 Hours

<2>

54-50-I09a

54-50-I0754-50-I0854-50-I12

Strut to Wing Attachments (Midspar Fitting) – CF6-80C Strut 431, 433, 437, 

441, 443, 447, 

511, 521, 611, 621

80C (400E)

> 8 Hours

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

54-50-I10 Aft Upper Spar Fittings and Fuse Pins – RB211 Strut

Note: No DTR Check Form.

434, 444 524

<2>

54-50-I10a Forward Engine Mount (Platform at Forward Tension Bolt Holes) – CF6-80C Strut 410, 420 80C (400E)

< 8 Hours

54-50-I10a Forward Engine Mount (Platform at Forward Tension Bolt Holes) – CF6-80C Strut 410, 420 80C (400E)

> 8 Hours

54-50-I10b Forward Engine Mount – CF6-80C Strut 410, 420 80C (400E)

< 8 Hours

<2>

54-50-I10b Forward Engine Mount – CF6-80C Strut 410, 420 80C (400E)

> 8 Hours

<2>

54-50-I11 Side Link and Strut Attach Fittings – RB211 Strut

Note: No DTR Check Form.

434, 444 524 

54-50-I11d Aft Engine Mount (Lugs) – CF6-80C Strut 410, 420 80C (400E)

< 8 Hours

54-50-I11d Aft Engine Mount (Lugs) – CF6-80C Strut 410, 420 80C (400E)

> 8 Hours

54-50-I11f Aft Engine Mount (Engine TRF Clevis Lugs) – CF6-80C Strut 410, 420 80C (400E)

< 8 Hours

54-50-I11f Aft Engine Mount (Engine TRF Clevis Lugs) – CF6-80C Strut 410, 420 80C (400E)

> 8 Hours

54-50-I12 Side Load Links – JT9D Strut

Note: No DTR Check Form.

437, 447 7R4 

54-50-I12 Side Load Links – PW4000 Strut

Note: No DTR Check Form.

437, 447 4000 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

54-50-I12 Side Load Links – CF6-80A Strut

Note: No DTR Check Form.

437, 447 80A 

54-50-I12 Side Load Links – CF6-80C Strut

Note: No DTR Check Form.

437, 447 80C (Except 400E) 

54-50-I12b SideLoad Fittings – CF6-80C Strut 437, 447 80C (400E)

< 8 Hours

<2>

54-50-I12b SideLoad Fittings – CF6-80C Strut 437, 447 80C (400E)

> 8 Hours

<2>

54-50-I13 Typical Lower Spar Chord and Spar Web Construction – JT90 Strut 434, 436

444, 446

7R4

<2>

54-50-I13 Typical Lower Spar Chord and Spar Web Construction – CF6-80A Strut 434, 436

444, 446

80A

<2>

54-50-I13 Typical Lower Spar Chord and Spar Web Construction – PW4000 Strut 434, 436

444, 446

4000

<2>

54-50-I13 Typical Lower Spar Chord and Spar Web Construction – CF6-80C Strut 434, 436

444, 446

80C (Except 400E)

<2>

54-50-I13a Lower Spar Chord and Web (Hidden) – CF6-80C Strut 434, 436

444, 446

80C (400E)

< 8 Hours

<2>

54-50-I13a Lower Spar Chord and Web (Hidden) – CF6-80C Strut 434, 436

444, 446

80C (400E)

> 8 Hours

<2>

54-50-I13e Lower Spar Chord (Visible) – CF6-80C Strut 434, 436

444, 446

80C (400E)

< 8 Hours

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

54-50-I14 Mid Bulkhead – Upper Fitting (R1) Joint – CF6-80C Strut 432, 434, 436, 

442, 444, 446

80C (400E)

< 8 Hours

<2>

54-50-I14 Mid Bulkhead – Upper Fitting (R1) Joint – CF6-80C Strut 432, 434, 436, 

442, 444, 446

80C (400E)

> 8 Hours

<2>

54-50-I16a Forward Upper Spar (Hidden) – CF6-80C Strut 432, 442 80C (400E)

< 8 Hours

<2>

54-50-I16a Forward Upper Spar (Hidden) – CF6-80C Strut 432, 442 80C (400E)

> 8 Hours

<2>

54-50-I16e Forward Upper Spar (Visible) – CF6-80C Strut 432, 442 80C (400E)

< 8 Hours

<2>

54-50-I17a Aft Upper Spar Chord (Vertical Flange, Hidden) – CF6-80C Strut 434, 436

444, 446

80C (400E)

< 8 Hours

<2>

54-50-I17a Aft Upper Spar Chord (Vertical Flange, Hidden) – CF6-80C Strut 434, 436

444, 446

80C (400E)

> 8 Hours

<2>

54-50-I17c Aft Upper Spar Chord (Vertical Flange, Shear Tie at NSTA 279 RHS) – CF6-80C Strut 434, 436

444, 446

80C (400E)

< 8 Hours

<2>

54-50-I17c Aft Upper Spar Chord (Vertical Flange, Shear Tie at NSTA 279 RHS) – CF6-80C Strut 434, 436

444, 446

80C (400E)

> 8 Hours

<2>

54-50-I17e Aft Upper Spar Chord (Vertical Flange, Visible RHS) – CF6-80C Strut 434, 436

444, 446

80C (400E)

< 8 Hours

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

54-50-I17e Aft Upper Spar Chord (Vertical Flange, Visible RHS) – CF6-80C Strut 434, 436

444, 446

80C (400E)

> 8 Hours

<2>

54-50-I17f Aft Upper Spar Chord (Vertical Flange, Visible) – CF6-80C Strut 434, 436

444, 446

80C (400E)

< 8 Hours

<2>

54-50-I17f Aft Upper Spar Chord (Vertical Flange, Visible) – CF6-80C Strut 434, 436

444, 446

80C (400E)

> 8 Hours

<2>

54-50-I18 Side Skin/Aft Upper Spar Chord Stiffener – CF6-80C Strut 434, 436

444, 446

80C (400E)

< 8 Hours

<2>

54-50-I18 Side Skin/Aft Upper Spar Chord Stiffener – CF6-80C Strut 434, 436

444, 446

80C (400E)

> 8 Hours

<2>

55-10-I09 Horizontal Stabilizer Upper Skin – At BBL 41.5 Side of Body Splice 331, 341 ALL 

55-10-I13A Horizontal Stabilizer Pivot Fitting Lug 331, 341 ALL 

55-10-I13B Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments 331, 341 ALL 

55-10-I13C Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments 331, 341 ALL 

55-10-I14A Horizontal Stabilizer – Jackscrew Fitting Lug 331, 341 ALL 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

55-10-I14B Horizontal Stabilizer Jackscrew Fitting – Upper and Lower Attachments 331, 341 ALL 

55-10-I31 Horizontal Stabilizer Rear Spar Upper Chord – SOB Hidden Area 331, 341 ALL 57-10-I01 Typical Stringer and Skin – Wing Center Section, Lower Surface at External Lower 

Beams (BBL 9.5 and BBL 62.0)

133, 134 400E

< 8 Hours

57-10-I01 Typical Stringer and Skin – Wing Center Section, Lower Surface at External Lower 

Beams (BBL 9.5 and BBL 62.0)

133, 134 400E

> 8 Hour

57-10-I01A Wing Center Section Lower Surface Typical Stringer

Note: No DTR Check Form.

133,134 300BCF 

57-10-I02 Splice Stringer and Skin – Wing Center Section at Stringer 6 and 10 133, 134 300F 

57-10-I02A Front Spar Chord and Skin – Wing Center Section at Radius Fillers 133, 134 400E

< 8 Hours

57-10-I02A Front Spar Chord and Skin – Wing Center Section at Radius Fillers 133, 134 400E

> 8 Hour

57-10-I02B Front Spar Chord and Skin – Wing Center Section at Underwing Longeron 133, 134 400E

< 8 Hours

<2>

57-10-I02B Front Spar Chord and Skin – Wing Center Section at Underwing Longeron 133, 134 400E

> 8 Hours

<2>

57-10-I02C Wing Center Section Lower Surface Splice Stringers L-6 and L-10

Note: No DTR Check Form.

133, 134 300BCF 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-10-I03A Rear Spar Lower Chord and Skin – Wing Center Section – Typical – 

BBL 23.0 – 86.5

133, 134 PASS 

(200ER, 300BCF, 

300ER)

< 8 Hours

57-10-I03A Rear Spar Lower Chord and Skin – Wing Center Section – Typical – BBL 23.0 – 86.5 133, 134 PASS (200ER, 300ER

> 8 Hours

57-10-I03A Rear Spar Lower Chord and Skin – Wing Center Section – Typical – BBL 23.0 – 86.5 133, 134 300F 57-10-I03A Rear Spar Lower Chord and Skin – Wing Center Section – Typical -

LBL 86.5 – RBL 86.5

133, 134 400E

< 8 Hours

57-10-I03A Rear Spar Lower Chord and Skin – Wing Center Section – Typical – 

LBL 86.5 – RBL 86.5

133, 134 400E

> 8 Hours

57-10-I03B Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations – 

BBL 49.5, 62.05 and 73.0

133, 134 PASS 

(200ER, 300BCF, 

300ER)

< 8 Hours

57-10-I03B Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations – 

BBL 49.5, 62.05 and 73.0

133, 134 PASS 

(200ER, 300ER)

> 8 Hours

57-10-I03B Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations – 

BBL 49.5, 62.05 and 73.0

133, 134 300F 

57-10-I03C Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations – 

BBL 49.5, 62.05 and 73.0

133, 134 PASS 

(200ER, 300BCF, 

300ER)

< 8 Hours

57-10-I03C Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations – 

BBL 49.5, 62.05 and 73.0

133, 134 PASS (200ER, 300ER

> 8 Hours

57-10-I03C Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations – 

BBL 49.5, 62.05 and 73.0

133, 134 300F 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-10-I03D Wing Center Section Rear Spar Lower Chord

Note: No DTR Check Form.

133, 134 300BCF 

57-10-I16 Lower Surface Side-Of-Body Splice (Sections 11 and 12) – L-1 to L-10 Inboard and 

Outboard of BBL 97.42

193, 194 ALL

< 8 Hours

57-10-I16B Lower Surface Side-Of-Body Splice (Sections 11 and 12) – L-1 to L-10 Inboard and 

Outboard of BBL 97.42

193, 194 ALL Except 300BCF

> 8 Hours

57-10-I16C Wing Lower Surface Side-of-Body Splice (Sections 11 and 12) – Stringer 1 to 

Stringer 10 Inboard and Outboard of BBL 97.42

Note: No DTR Check Form.

193, 194 300BCF 

57-10-I20 Rear Spar Lower Chord SOB Splice (Sections 11 and 12) – Chords at Splice Fittings 

Inboard and Outboard of BBL 97.42

143, 144 ALL

< 8 Hours

57-10-I20 Rear Spar Lower Chord SOB Splice (Sections 11 and 12) – Chords at Splice Fittings 

Inboard and Outboard of BBL 97.42

143, 144 ALL Except 300BCF

> 8 Hours

57-10-I20A Rear Spar Lower Chord SOB Splice (Sections 11 and 12) – Chords At Splice Fittings 

Inboard and Outboard of BBL 97.42

Note: No DTR Check Form.

143, 144 300BCF 

57-10-I24 Underwing Longeron Attachment (Center Section Structure) – BBL 70 Longeron from 

Front Spar Lower Chord to Stringer 18

133, 134 PASS 

(200ER, 300BCF, 

300ER)

300F

< 8 Hours

<2>

57-10-I24 Underwing Longeron Attachment (Center Section Structure) – BBL 70 Longeron from 

Front Spar Lower Chord to Stringer 18

133, 134 PASS 

(200ER, 300ER)

300F

> 8 Hours

<2>

57-10-I24A Wing Center Section Lower Surface BBL 70 Underwing Longeron Backup Structure

Note: No DTR Check Form.

133, 134 300BCF 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-10-I25 Rear Spar Lower Chord and Skin – Wing Center Section at Stiffener Clips at 

BBL 32.9, 40.2, 47.5, 54.7 and 62

133, 134 400E

< 8 Hours

<2>

57-10-I25 Rear Spar Lower Chord and Skin – Wing Center Section at Stiffener Clips at 

BBL 32.9, 40.2, 47.5, 54.7 and 62

133, 134 400E

> 8 Hours

<2>

57-20-I05 Rear Spar at Forward MLG Trunnion – Rib 5, WS 329.10 532, 632

551, 651

400E

< 8 Hours

<2>

57-20-I05 Rear Spar at Forward MLG Trunnion – Rib 5, WS 329.10 532, 632

551, 651

400E

> 8 Hours

<2>

57-20-I06 Rear Spar at MLG Outboard Support – Rib 7, WS 372.20 532, 632

551, 651

400E

< 8 Hours

<2>

57-20-I06 Rear Spar at MLG Outboard Support – Rib 7, WS 372.20 532, 632

551, 651

400E

> 8 Hours

<2>

57-20-I07 Rear Spar at Flap/Spoiler Backup Fitting Installation – Lower Chord Rib Bay 16,

WS 605.50

551, 651 400E

<2>

57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: L-16 (Dry Bay) under 

Nacelle Fairing

437, 447533, 633

ALL Except 400E

< 8 Hours

57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: L-16 (Dry Bay) under 

Nacelle Fairing

437, 447533, 633

ALL

Except 300BCF, 400E

> 8 Hours

57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: L-16 (Dry Bay) under 

Nacelle Fairing

437, 447533, 633

400E

< 8 Hours

57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: L-16 (Dry Bay) under 

Nacelle Fairing

437, 447533, 633

400E

> 8 Hours

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-20-I12B Outboard Wing Typical Stringers Lower Surface – Rib 9: L-17 at Outboard Side Load 

Fitting under Nacelle Fairing

533, 633 ALL Except 400E

< 8 Hours

57-20-I12B Outboard Wing Typical Stringers Lower Surface – Rib 9: L-17 at Outboard Side Load 

Fitting under Nacelle Fairing

533, 633 ALL

Except 300BCF, 400E

> 8 Hours

57-20-I12B Outboard Wing Typical Stringers Lower Surface – Rib 9: L-17 at Outboard Side Load 

Fitting under Nacelle Fairing

533, 633 400E

< 8 Hours

57-20-I12B Outboard Wing Typical Stringers Lower Surface – Rib 9: L-17 at Outboard Side Load 

Fitting under Nacelle Fairing

533, 633 400E

> 8 Hours

57-20-I12C Outboard Wing Lower Surface Typical Stringer

Note: No DTR Check Form.

193, 194437, 447530, 630540, 640533, 633

300BCF 

57-20-I15A Outboard Wing Lower Surface Splice Stringer – L-6 and 10. L-10 between Rib 7 and 

20 (except under Nacelle Fairing) & L-6: SOB to Rib 3

531, 532, 541, 

631, 632, 641

ALL

< 8 Hours

57-20-I15A Outboard Wing Lower Surface Splice Stringer – L-6 and 10. L-10 between Rib 7 and 

20 (except under Nacelle Fairing) & L-6: SOB to Rib 3

531, 532, 541, 

631, 632, 641

ALL Except 300BCF

> 8 Hours

57-20-I15B Outboard Wing Lower Surface Splice Stringer – L-10 under Nacelle Fairing 532, 632 ALL

< 8 Hours

57-20-I15B Outboard Wing Lower Surface Splice Stringer – L-10 under Nacelle Fairing 532, 632 ALL Except 300BCF

> 8 Hours

57-20-I15C Outboard Wing Lower Surface Splice Stringer – L-6, 10 and 15 under Nacelle Strut at 

External Doublers, Fittings and Angles

532, 533, 541, 

632, 633, 641

ALL Except 400E

< 8 Hours

57-20-I15C Outboard Wing Lower Surface Splice Stringer – L-6, 10 and 15 under Nacelle Strut at 

External Doublers, Fittings and Angles

532, 533, 541, 

632, 633, 641

ALL 

Except 300BCF, 400E

> 8 Hours

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-20-I15C Outboard Wing Lower Surface Splice Stringer – L-6 and 10 under Nacelle Strut at 

External Fittings and Skate Angles

532, 541632, 641

400E

< 8 Hours

57-20-I15C Outboard Wing Lower Surface Splice Stringer – L-6 and 10 under Nacelle Strut at 

External Fittings and Skate Angles

532, 541632, 641

400E

> 8 Hours

57-20-I15D Outboard Wing Lower Surface Splice Stringer – L-15 under Nacelle Strut at Rib 9 

(Seal Pans)

530, 630 ALL Except 400E

< 8 Hours

57-20-I15D Outboard Wing Lower Surface Splice Stringer – L-15 under Nacelle Strut at Rib 9 

(Seal Pans)

530, 630 ALL 

Except 300BCF, 400E

> 8 Hours

57-20-I15D Outboard Wing Lower Surface Splice Stringer – L-15 under Nacelle Strut at Rib 9 

(Seal Pans)

530, 630 400E

< 8 Hours

57-20-I15D Outboard Wing Lower Surface Splice Stringer – L-15 under Nacelle Strut at Rib 9 

(Seal Pans)

530, 630 400E

> 8 Hours

57-20-I15E Outboard Wing Lower Surface Splice Stringer – L-6 and 10 at Rib 3 530, 630 ALL

< 8 Hours

57-20-I15E Outboard Wing Lower Surface Splice Stringer – L-6 and 10 at Rib 3 530, 630 ALL Except 300BCF

> 8 Hours

57-20-I15F Outboard Wing Lower Surface Splice Stringer – Seal Pan/ Baffles at 

Ribs 3, 6, 18 and 31

530, 540630, 640

400E

< 8 Hours

<2>

57-20-I15F Outboard Wing Lower Surface Splice Stringer – Seal Pan/ Baffles at 

Ribs 3, 6, 18 and 31

530, 540630, 640

400E

> 8 Hours

<2>

57-20-I15G Outboard Wing Lower Surface Splice Stringer – L-6 at External Nacelle Fitting and 

Outboard Skate Angle

532, 541632, 641

400E

< 8 Hours

57-20-I15G Outboard Wing Lower Surface Splice Stringer – L-6 at External Nacelle Fitting and 

Outboard Skate Angle

532, 541632, 641

400E

> 8 Hours

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-20-I15H Outboard Wing Lower Surface Splice Stringer – L-15 at External Nacelle Fitting and 

Outboard Skate Angle

532, 541632, 641

400E

< 8 Hours

57-20-I15H Outboard Wing Lower Surface Splice Stringer – L-15 at External Nacelle Fitting and 

Outboard Skate Angle

532, 541632, 641

400E

> 8 Hours

57-20-I15J Outboard Wing Lower Surface Splice Stringers

Note: No DTR Check Form.

530, 630531, 631532, 632540, 640541, 641

300BCF 

57-20-I15K Outboard Wing Lower Surface Splice Stringers at Covered Locations

Note: No DTR Check Form.

531, 631532, 632541, 641

300BCF 

57-20-I16A Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Typical Details 

between Fairing at Side-Of-Body & Rib 3

530, 630 ALL

< 8 Hours

57-20-I16A Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Typical Details 

between Fairing at Side-Of-Body & Rib 3

530, 630 ALL Except 300BCF

> 8 Hours

57-20-I16B Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden by 

Rib Shear Ties Side-Of-Body to Rib 3

530, 630 ALL Except 400E

< 8 Hours

57-20-I16B Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden by 

Rib Shear Ties Side-Of-Body to Rib 3

530, 630 ALL 

Except 300BCF, 400E

> 8 Hours

57-20-I16B Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden by 

Rib Shear Ties Side-Of-Body to Rib 3

530, 630 400E

< 8 Hours

57-20-I16B Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden by 

Rib Shear Ties Side-Of-Body to Rib 3

530, 630 400E

> 8 Hours

57-20-I16C Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details at 

Ribs 5, 6, 8 and 9 (Not Covered by Fairings)

530, 630 ALL Except 400E

< 8 Hours

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-20-I16C Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details at 

Ribs 5, 6, 8 and 9 (Not Covered by Fairings)

530, 630 ALL 

Except 300BCF, 400E

> 8 Hours

<2>

57-20-I16C Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details at 

Ribs 5, 6, 8 and 9 (Not Covered by Fairings)

530, 630 400E

< 8 Hours

57-20-I16C Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details at 

Ribs 5, 6, 8 and 9 (Not Covered by Fairings)

530, 630 400E

> 8 Hours

57-20-I16D Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Outboard of 

Terminal Fitting Wing-to-Body Fairing Area

531, 631 ALL Except 400E

< 8 Hours

57-20-I16D Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Outboard of 

Terminal Fitting Wing-to-Body Fairing Area

531, 631 ALL 

Except 300BCF, 400E

> 8 Hours

57-20-I16D Rear Spar to Skin, Rib Bay 1, WSTA 226.3 – Typical Details 531, 631 400E

< 8 Hours

57-20-I16D Rear Spar to Skin, Rib Bay 1, WSTA 226.3 – Typical Details 531, 631 400E

> 8 Hours

57-20-I16E Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details – 

Trunnion, Nacelle and Inboard Flap Fairing Areas

530, 540630, 640

ALL Except 400E

< 8 Hours

57-20-I16E Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details – 

Trunnion, Nacelle and Inboard Flap Fairing Areas

530, 540630, 640

ALL 

Except 300BCF, 400E

> 8 Hours

57-20-I16E Rear Spar to Skin, Rib Bay 11, WSTA 449.2 – Hidden Details 530, 540

630, 640

400E

< 8 Hours

57-20-I16E Rear Spar to Skin, Rib Bay 11, WSTA 449.2 – Hidden Details 530, 540

630, 640

400E

> 8 Hours

57-20-I16F Front Spar Lower Chord and Skin (Outboard Wing Structure) – Lower Skin Panel 

Splice Location between Ribs 18 and 19 only

540,640 ALL Except 400E

< 8 Hours

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-20-I16F Front Spar Lower Chord and Skin (Outboard Wing Structure) – Lower Skin Panel 

Splice Location between Ribs 18 and 19 only

540, 640 ALL 

Except 300BCF, 400E

> 8 Hours

57-20-I16F Front Spar to Skin, Rib Bay 19, WSTA 655.2 – Hidden Details 540, 640 400E

< 8 Hours

57-20-I16F Front Spar to Skin, Rib Bay 19, WSTA 655.2 – Hidden Details 540, 640 400E

> 8 Hours

57-20-I16G Front Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden by 

Rib Shear Ties Rib 9 to and including Rib 23

530, 540630, 640

ALL Except 400E

< 8 Hours

57-20-I16G Front Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden by 

Rib Shear Ties Rib 9 to and including Rib 23

530, 540630, 640

ALL 

Except 300BCF, 400E

> 8 Hours

57-20-I16G Front Spar to Skin, Rib Bay 23, WSTA 759.2 – Hidden Details 540, 640 400E

< 8 Hours

57-20-I16G Front Spar to Skin, Rib Bay 23, WSTA 759.2 – Hidden Details 540, 640 400E

> 8 Hours

57-20-I16H Front Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details – 

Ribs 8/9 and at Side Brace Fitting between Ribs 8/9

533, 633 ALL Except 400E

< 8 Hours

57-20-I16H Front Spar Lower Chord and Skin (Outboard Wing Structure) – Ribs 8/9 and at Side 

Brace Fitting between Ribs 8/9

533, 633 ALL 

Except 300BCF, 400E

> 8 Hours

57-20-I16H Front Spar to Skin, Rib Bay 9, WSTA 390.1 – Hidden Details – R7/R8 Backup Fitting 533, 633 400E

< 8 Hours

57-20-I16H Front Spar to Skin, Rib Bay 9, WSTA 390.1 – Hidden Details – R7/R8 Backup Fitting 533, 633 400E

> 8 Hours

57-20-I16I Front Spar Lower Chord and Skin – Hidden Details Rib Shear Ties, Rib 24 to and 

including Rib 31

530, 540630, 640

400E

< 8 Hours

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-20-I16I Front Spar Lower Chord and Skin – Hidden Details Rib Shear Ties, Rib 24 to and 

including Rib 31

530, 540630, 640

400E

> 8 Hours

<2>

57-20-I16J Rear Spar Lower Chord and Skin – Hidden Details Rib Shear Ties, Rib 22 up to and 

including Rib 32

540, 640 400E

< 8 Hours

<2>

57-20-I16J Rear Spar Lower Chord and Skin – Hidden Details Rib Shear Ties, Rib 22 up to and 

including Rib 32

540, 640 400E

> 8 Hours

<2>

57-20-I16K Outboard Wing Lower Surface Front and Rear Spar Chords and Skin

Note: No DTR Check Form.

530, 630532, 632533, 633540, 640541, 641

300BCF 

57-20-I16L Wing Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Outboard 

of Terminal Fitting Wing-to- Body Fairing Area

Note: No DTR Check Form.

531, 631 300BCF 

57-20-I19 Nacelle Fitting Attachment to Lower Surface – Outboard Wing Lower Surface – 

WS 436.9, R2 Fitting Forward End at Stringer 5

532, 632 400E

< 8 Hours

57-20-I19 Nacelle Fitting Attachment to Lower Surface – Outboard Wing Lower Surface – 

WS 436.9, R2 Fitting Forward End at Stringer 5

532, 632 400E

> 8 Hours

57-20-I27 Skin Tab at R1 Nacelle Attachment R2 Intact – Outboard Fitting Aft Fastener Row 532, 632 400E

< 8 Hours

<2>

57-20-I27 Skin Tab at R1 Nacelle Attachment R2 Intact – Outboard Fitting Aft Fastener Row 532, 632 400E

> 8 Hours

<2>

57-20-I36 MLG Forward Trunnion Support to Lower Skin Attachment – Inboard Forward 

Trunnion Support, Most Inboard Aft Fastener

530, 540630, 640

400E 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-53-I02A Outboard Flap Supports – Support Ribs (Rear Spar Fittings) in Bathtub Region, 

Lug 6 Region Flange

572, 573672, 673

200

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I02A.1 Outboard Flap Supports – Rear Spar Fittings – Lugs at Joint 1 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1-921

<2>

57-53-I02A.2 Outboard Flap Supports – Rear Spar Fittings – Lugs at Joint 6 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1-921

<2>

57-53-I02A.3 Outboard Flap Supports – Rear Spar Fittings – Lower Aft Flange 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1-921

57-53-I02B Outboard Flap Supports – Rear Spar Fitting Tension Bolts – BACB30US12 – 

Thread Runout

572, 573672, 673

200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I02B Outboard Flap Supports – Rear Spar Fitting Tension Bolts 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-53-I02C Outboard Flap Supports – Doublers – .375” Diameter Fastener Holes 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I02C Outboard Flap Supports – Rear Spar Fittings – Actuator Bore and Fastener Holes 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

57-53-I02D.1 Outboard Flap Supports – 9-10 Beam – Joint 9 Lug 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

<2>

57-53-I02D.2 Outboard Flap Supports – 9-10 Beam 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

57-53-I02E Outboard Flap Supports – 9-10 Beam Swivel Fitting 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I02F Outboard Flap Supports – Flap Attachment Bolts 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 710

57-53-I02F Outboard Flap Supports – Flap Attachment Bolts 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 711 – 921

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-53-I02G.1 Outboard Flap Supports – 6-8-9 Beam (Main Drive Link), 5.38 inches Aft of Joint 6 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I02G.1 Outboard Flap Supports – Support No. 1 and No. 2, 6-8-9 beam – Typical Section 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

57-53-I02G.2 Outboard Flap Supports – 6-8-9 Beam (Main Drive Link), Lug 8 Region 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 922 and Later 

400E

<2>

57-53-I02G.2 Outboard Flap Supports – No. 1 and No. 2, 6-8-9 Beam – Lugs 6, 8 and 9 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

<2>

57-53-I02G.3 Outboard Flap Supports – Support No. 1 and No. 2, 6-8-9 Beam – Fastener Holes 572, 573

672, 673

200, 300BCF,

300 PASS, 300F

L/N 1 – 921

57-53-I02I Outboard Flap Supports – 4-5 Drive Arm – Spline Outer Surface 572, 573

672, 673

ALL

<2>

57-53-I02J.1 Outboard Trailing Edge Flap Support #1 – Link 3-10 – Lug 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-53-I02J.2 Outboard Trailing Edge Flap Support #2 – Link 3-10 – Lug 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

<2>

57-53-I02L.1 Outboard Trailing Edge Flap Supports – Beam 1-2-3 – Beam at Field Fasteners 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

57-53-I02L.2 Outboard Trailing Edge Flap Supports – Beam 1-2-3 – Lug at Joint 1 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

<2>

57-53-I02L.3 Outboard Trailing Edge Flap Supports – Beam 1-2-3 – Lug at Joint 3 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

<2>

57-53-I02M.1 Outboard Flap Supports – Outer Pins at Outboard Supports: Joints 5, 6, 8 and 10 

and Inboard Supports: Joints 5, 6, 8 and 10

572, 573672, 673

200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I02M.2 Outboard Flap Supports – Outer Pin at Inboard Main Support: Joint 8 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

57-53-I02M.4 Outboard Flap Pins – Support #2 – Outer Pins at Joint 2 and Joint 8 572, 573

672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 - 921

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-53-I02M.5 Outboard Flap Pins – Support No. 1 and No. 2 – Joint #1 Fuse Pin – Pin Shank 

@ Outboard Rib Support

572, 573672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

57-53-I02M.6 Outboard Flap Pins – Support #1, Joints 2, 3, 5, 6, 8, 9, and 10 – Support #2, 

Joints 3, 5, 6, 9, and 10

572, 573672, 673

200,

300BCF, 300 PASS,

300F

L/N 1 – 921

57-53-I03E.1 Inboard Flap Box at # 3 Support – Backup Fittings – Forward Bathtub 555, 655 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I03E.2 Inboard Flap Box at # 3 Support – Backup Fittings – Aft Bathtub End Pads 555, 655 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I03F Inboard Flap Box at # 3 Support – Flap Attachment Bolts, IFS 251.25 555, 655 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

57-53-I03F Inboard flap #3 Support – Flap Attachment Bolts – Shank Location 555, 655 200,

300BCF, 300 PASS,

300F

L/N 1 – 849

57-53-I03F Inboard Flap #3 support – Flap Attachment Bolts – Shank Location 555, 655 200,

300BCF, 300 PASS,

300F

L/N 850 – 921

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-53-I03I.1 Inboard Flap Box at # 4 Support – Inboard Closure Rib – Lower Chord, IFS 108.5 555, 655 ALL 57-53-I03I.2 Inboard Flap Box at # 4 Support – Inboard End Rib and Splined Bushing – Splined 

Bushing Splines

555, 655 200,

300BCF, 300 PASS,

300F

L/N 910 and Later

400E

57-53-I03I.2 Inboard Flap, Support #4 – Splined Bushing at IFS 108.5 – Internal Spline base of 

Tooth/Rim

555, 655 200,

300BCF, 300 PASS,

300F

L/N 1 - 909

57-53-I03J.1 Inboard Flap Box at # 4 Support – Pillow Block (Collar Fitting) Bathtubs IFS 92 – 

Bathtub End Pads

555, 655 200,

300BCF, 300 PASS,

300F

L/N 910 and Later

400E

<2>

57-53-I03J.2 Inboard Flap Box at # 4 Support – Pillow Block (Collar Fitting) Spline Region, 

IFS 92 – Bathtub End Pads

555, 655 200,

300BCF, 300 PASS,

300F

L/N 910 and Later

400E

57-53-I03J.2 Inboard Flap Support No. 4 – Collar Fitting – Spline Cross-Section 555, 655 200,

300BCF, 300 PASS,

300F

L/N 1 – 909

57-53-I03K Inboard Flap #4 Support – Attachment Bolts 555, 655 200,

300BCF, 300 PASS,

300F

L/N 1 – 849

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-53-I03K Inboard Flap #4 Support – Attachment Bolts 555 655 200,

300BCF, 300 PASS,

300F

L/N 850 – 921

57-53-I03L 767 Inboard Flap – #4 Support – Torque Tube – Torque Tube Outer Surface – 

IFS 92 to IFS 124.5

555, 655 200,

300BCF, 300 PASS,

300F

L/N 1 – 909

57-53-I03L.1 Inboard Flap Box at #4 Support – Torque Tube – IFS 108.5 555, 655 200,

300BCF, 300 PASS,

300F

L/N 910 and Later

400E

<2>

57-53-I03L.2 Inboard Flap Box at #4 Support – Torque Tube, IFS 92 to IFS 124.5 555, 655 200,

300BCF, 300 PASS,

300F

L/N 910 and Later

400E

57-53-I04A.1 Inboard Flap # 3 Support – Actuator Support Rib Assembly – Section Forward of 

Joint 6 Lug

571, 671 200,

300BCF, 300 PASS, 

300F

L/N 922 and Later

400E

57-53-I04A.1 Inboard Flap #3 Support – Actuator Support Rib – Section Forward of Joint 6 Lug 571, 671 200,

300BCF, 300 PASS,

300F

L/N 1 – 921

57-53-I04A.2 Inboard Flap # 3 Support – Actuator Support Rib Assembly – Lug Details at 

Joints 0, 1 and 6

571, 671 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-53-I04A.2 Inboard Flap # 3 Support – Actuator Support Rib – Lugs at Joints 0, 1, 6 571, 671 200,

300BCF, 300 PASS,

300F

L/N 1 – 921

<2>

57-53-I04B.2 Inboard Flap # 3 Support – Underwing Fitting – Section 9.67 Inches Forward of 

Aftmost Tension Link Lug Bore

571, 671 200,

300BCF, 300 PASS,

300F

L/N 883 and Later

400E

<2>

57-53-I04B.2 Wing Trailing Edge, I/B Flap, #3 Support – Underwing Fitting – Section Through 

Aft Most Field Fastener Row Just Forward of the Fuse Joint

571, 671 200, 

300BCF, 300 PASS, 

300F 

L/N 1 – 882

<2>

57-53-I04B.3 Wing Trailing Edge, I/B Flap, #3 Support – Underwing Fitting – Lug at Fuse Pin 

location

571, 671 200,

300BCF, 300 PASS, 

300F

L/N 1 – 882

<2>

57-53-I04C Wing Trailing Edge, I/B Flap, #3 Support – Fuse Pin – Underwing Fitting to 

Forward Tension Link

571, 671 200,

300BCF, 300 PASS, 

300F

L/N 1 – 882

57-53-I04D Inboard Flap # 3 Support – Forward Tension Link 571, 671 200,

300BCF, 300 PASS,

300F

L/N 883 and Later

400E

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-53-I04D.1 Wing Trailing Edge, I/B Flap, #3 Support – Forward Tension Link – Section A-A – 

Typical Cross Section Through Fasteners

571, 671 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 882

57-53-I04D.2 Wing Trailing Edge, I/B Flap, #3 Support – Forward Tension Link – End Clevis 571, 671 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 882

<2>

57-53-I04E Inboard Flap # 3 Support – 1-2-3 Beam – Lugs at Joints 1, 2, and 3 571, 671 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I04E.1 Inboard Flap # 3 Support – Beam 1-2-3 – Lug at Joint 1 571, 671 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 921

<2>

57-53-I04E.2 Inboard Trailing Edge Flap Support #3 – Beam 1-2-3 – Lugs at Joint 2 and 3 571, 671 200,

300BCF, 300 PASS, 

300F

L/Ns 1 – 921

<2>

57-53-I04E.3 Inboard Flap # 3 Support – Beam 1-2-3 – Beam at Field Fasteners 571, 671 200,

300BCF, 300 PASS, 

300F

L/Ns 1 – 921

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-53-I04F.1 Inboard Flap # 3 Support – 3-10 Link – Lugs 571, 671 200,

300BCF, 300 PASS, 

300F

L/Ns 1 – 921

<2>

57-53-I04F.1 Inboard Flap # 3 Support – 3-10 Link – Lugs 571, 671 200,

300BCF, 300 PASS, 

300F

L/N 922 and Later

400E

<2>

57-53-I04F.2 Inboard Flap # 3 Support – 3-10 Link – Between Lugs 571, 671 200, 

300BCF, 300 PASS, 

300F

L/Ns 1 – 921

<2>

57-53-I04F.2 Inboard Flap # 3 Support – 3-10 Link – Between Lugs 571, 671 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I04H Inboard Flap # 3 Support – 6-7-8-9 Beam – Lug 9 Detail 571, 671 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I04H Inboard Flap # 3 Support – 6-7-8-9 Beam – Lugs 6, 7, 8 and 9 571, 671 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 921

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-53-I04I Inboard Flap # 3 Support – 4-5 Drive Arm – Internal Spline 571, 671 ALL

<2>

57-53-I04K Inboard Flap # 3 Support – 9-10 Beam – Lug at Joint 9 571, 671 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I04K.1 Inboard Flap # 3 Support – 9-10 Beam – Joint 9 Lug 571, 671 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 921

<2>

57-53-I04K.2 Inboard Flap # 3 Support – 9-10 Beam – Section Cut Through Field Fasteners – 

Section B-B

571, 671 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 921

57-53-I04K.3 Inboard Flap # 3 Support – 9-10 Beam 571, 671 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 921

57-53-I04N.1 Inboard Flap # 3 Support – Flap Support Pins – Outer Pins at Joints 0, 1, 2, 3, 5, 

6, 7, 8, 9 and 10

571, 671 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I04N.2 Inboard Flap # 3 Support – Flap Support Pins – Outer Pins at Joints A and B 571, 671 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-53-I04N.3 Inboard Flap # 3 Support – Flap Support Pins – Outer Pins at Joints 0, 2, 3, 5, 6, 

7, 8, 9, 10, A, and B

571, 671 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 921

57-53-I04N.4 Inboard Flap #3 Support – Flap Support Pins – Outer Pin at Joint 1. 571, 671 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 921

57-53-I04P Inboard Flap # 4 Support – 4-5 Drive Arm – Internal Spline 195, 196 ALL

<2>

57-53-I04Q.1 Inboard Flap # 4 Support – 5-7 Link – Lugs 195, 196 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I04Q.1 Inboard Flap # 4 Support – 5-7 Link – Lugs 195, 196 200,

300BCF, 300 PASS,

 300F

L/Ns 1 – 921

<2>

57-53-I04Q.2 Inboard Flap # 4 Support – 5-7 Link – Cross Section 3.16 inches from Lug 195, 196 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I04Q.2 Inboard Flap # 4 Support – 5-7 Link – Body of Link around Field fasteners 195, 196 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 921

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-53-I04S Inboard Flap # 4 Support – 6-7 Drive Arm – Cross Section 7.399 inches from 

Joint 7

195, 196 ALL

<2>

57-53-I04T Inboard Flap # 4 Support – 6-9 Drive Arm – Just Aft of the Bend in the Beam 195, 196 ALL

<2>

57-53-I04V Inboard Flap # 4 Support – Carrier Beam 9-11 – Section Forward of Flap Attach 

and Aft of Flap Attach Bathtub

195, 196 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

57-53-I04Y Inboard Flap # 4 Support – Flap Support Fitting – Upper Flange Inboard Bolt 

Location

195, 196 200,

300BCF, 300 PASS,

 300F

L/N 922 and Later

400E

57-53-I04Y Inboard Flap # 4 Support – Side Strut Swivel Support Fitting – Satellite Holes and 

Lug 6

195, 196 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 921

57-53-I04Z Inboard Flap # 4 Support – 6-6’ Outer Pin – Section at Spline #2 (Common to 

6-7 Arm) Inner Diameter (Inner Bore)

195, 196 ALL 

57-53-I04AA Inboard Flap # 4 Support – Flap Support Pins – Outer Pins at Joints 5, 7 and 9 195, 196 200,

300BCF, 300 PASS,

300F

L/N 922 and Later

400E

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-53-I04AA Inboard Flap # 4 Support – Flap Support Pins – Outer Pins at Joints 5, 7, 9, 

and RL

195, 196 200,

300BCF, 300 PASS,

300F

L/Ns 1 – 921

57-54-I02A Main Landing Gear Beam, Inboard Lug Bore

Note: No DTR Check Form.

552, 652 300BCF

<4>

57-54-I02B Main Landing Gear Beam, Outboard Lug Bore

Note: No DTR Check Form.

552, 652 300BCF

<4>

57-54-I02C Main Landing Gear Beam, Aft Trunnion Bore

Note: No DTR Check Form.

552, 652 300BCF

<4>

57-54-I02D Main Landing Gear Beam, Upper Flange, between the Inboard and Outboard Web 

Stiffeners adjacent to Aft Trunnion Bore

Note: No DTR Check Form.

552, 652 300BCF

<4>

57-54-I02E Main Landing Gear Beam, Upper Flange, except the flange adjacent to Aft Trunnion 

Bore covered by SSI 57-54-I02D.

Note: No DTR Check Form.

552, 652 300BCF

<4>

57-54-I03A Load Distribution Plate, Flange around Outboard Upper Lug

Note: No DTR Check Form.

552, 652 300BCF

<4>

57-54-I03B Load Distribution Plate, Flange around Outboard Lower Lug

Note: No DTR Check Form.

552, 652 300BCF

<4>

57-54-I03C Load Distribution Plate, Flange around Inboard Lug

Note: No DTR Check Form.

552, 652 300BCF

<4>

57-54-I03D Load Distribution Plate, Flange except in the Lug areas covered by SSI 57-54-I03A, 

57-54-I03B and 57-54-I03C.

Note: No DTR Check Form.

552, 652 300BCF

<4>

57-54-I04 Main Landing Gear Beam, Outboard Pin

Note: No DTR Check Form.

552, 652 300BCF

<4>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-54-I13 MLG Forward Trunnion Support – Side Load Fitting – Side Load Fitting to Strap 

Inboard Fastener Row

551, 651 400E

<2>

57-54-I14 MLG Forward Trunnion Support – Side Load Strap – First Fastener Row Either Side 

of Trunnion

551, 651 400E

<2>

<1> See DTR Check Forms for additional information for airplanes prior to L/N indicated.<2> No 767 airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedures are validated, p

and accepted by the FAA.

<3> No 767-300F airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedure is revise

manual, and accepted by the FAA.

<4> No 767-300BCF airplane may be operated beyond the stated threshold (operational limit) until the applicable inspection procedure is revise

manual, and accepted by the FAA.

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE INSPECTION ZONE AIRPLANE/ENGINE APPLICABILITY 

DEC 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFE PARTS

NOTE: Service Letter 767-SL-32-092 (Latest Revision) and its reference Boeing Drawing 160T0002, 767 Main and Nose Lan

Interchangeability List, identify the 767 landing gear and support structure safe-life (life limited) parts.

NOTE: Service Letter 767-SL-32-092 (Latest Revision) and its reference Boeing Drawing 160T0002, 767 Main and Nose Lan

Interchangeability List, identify the 767 landing gear and support structure safe-life (life limited) parts.

ITEM LIFE LIMIT

767-200 Nose Landing Gear 80,000 Landings *767-200 Main Landing Gear 70,000 Landings *767-200 Main Landing Gear Support Structure 90,000 Landings *767-200SF Nose Landing Gear, Main Landing Gear and Gear Support Structure 1,000 Landings *** These values are based on completed fatigue tests and incorporation of the following Service Bulletins on applicable airplanes** Each component must be tracked individually (i.e., existing cycles at time of freighter conversion + 1,000 additional cycles).

SERVICE BULLETIN # DESCRIPTION

LIFE LIMIT (LA

PRIOR TO INCOR

767-32-44 MLG UPPER SPINDLE-DRAG STRUT, PART # 161T6007 9,000767-32-45 MLG OUTER CYLINDER ASSEMBLY, PART # 161T1110 18,000

767-32-46 MLG UPPER BULKHEAD-SHOCK STRUT, PART # 16T1161 30,000

ITEM LIFE LIM

767-300, 767-300BCF, 767-300F NOSE LANDING GEAR 80,000 LAND767-300, 767-300BCF, 767-300F MAIN LANDING GEAR 50,000 LAND767-300, 767-300BCF, 767-300F MAIN LANDING GEAR SUPPORT STRUCTURE 62,000 LAND767-300, 767-300BCF, 767-300F MLG RETRACT ACTUATOR FITTING AND PIN 90,000 LAND** These values are based on completed fatigue tests.

JAN 2007
767 MAINTENANCE PLANNING DATA

D622T001-9

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

NOTE: Service Letter 767-SL-32-092 (Latest Revision) and its reference Boeing Drawing 160T0002, 767 Main and Nose Lan

Interchangeability List, identify the 767 landing gear and support structure safe-life (life limited) parts.

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

ITEM LIFE LIMIT

767-400ER NOSE LANDING GEAR 80,000 LANDINGS **767-400ER MAIN LANDING GEARINNER CYLINDER 16,600 LANDINGS *OUTER CYLINDER 16,600 LANDINGS *UPPER STABILIZER BRACE FUSE PIN 21,300 LANDINGS *ALL OTHER SAFE-LIFE PARTS 31,400 LANDINGS ** These values are based on fatigue test cycles completed to date and will be increased when testing is complete.** These values are based on completed fatigue tests and analysis.

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.

MAY 2009
D622T001-9

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

767 MAINTENANCE PLANNING DATA

D. AIRWORTHINESS LIMITATIONS – SYSTEMS

FUEL SYSTEMS AIRWORTHINESS LIMITATIONS

This section of the Airworthiness Limitations contains an FAA approved program of scheduled inspections and design limitationincorporate into their maintenance program for this type design to meet the new standards and assumptions introduced by § 25Aviation Regulation No. 88 (SFAR 88). SFAR 88 – Fuel Tank System Fault Tolerance Evaluation Requirements and Title 14 C§ 25.981 – Fuel Tank Ignition Prevention require maintenance instructions, and control limitations for certain fuel tank critical deParagraph 2(a) of SFAR 88 requires certain design approval holders of Type Certificates (TCs) and Supplemental Type Certifictransport airplanes to conduct a safety review of the fuel tank systems. The purpose of the safety review is to identify design fedevelopment of ignition sources in the fuel tank systems. Fuel System Airworthiness Limitations (AWLs) are mandatory maintenaccordance with § 25.981, to ensure that unsafe conditions identified by the safety review do not occur or are not introduced inresult of configuration changes, repairs, alterations, or deficiencies in the maintenance program throughout the operational life may be an Airworthiness Limitation Instruction (ALI) or a Critical Design Configuration Control Limitation (CDCCL).CDCCLs are a means of identifying certain design configuration features intended to preclude a fuel tank ignition source for the airplane. CDCCLs are mandatory and cannot be changed or deleted without the approval of the Seattle FAA ACO or applicable critical fuel tank ignition source prevention feature may exist in the fuel system and its related installation or in systems that, if a develop, could interact with the fuel system in such a way that an unsafe condition would develop without this limitation. Strict amethods, techniques, and practices as prescribed is required to ensure compliance with the CDCCL. Any use of parts, methodnot contained in the applicable CDCCL must be approved by the Seattle FAA ACO or applicable regulatory agency.ALIs identify inspection tasks related to fuel tank ignition source prevention which must be done to maintain the design level of life of the airplane. These ALIs are mandatory and cannot be changed or deleted without the approval of the Seattle FAA ACO agency. Strict adherence to methods, techniques and practices as prescribed is required to ensure the ALI is complied with. Atechniques or practices not contained in these ALIs must be approved by the Seattle FAA ACO or applicable regulatory agency

MAY 2010
767 MAINTENANCE PLANNING DATA

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USE OF ALTERNATE OR EQUIVALENT TOOLS, TEST EQUIPMENT OR MATERIALSFor AWLs which list the use of certain tools, test equipment or materials, use of alternate or equivalent tools, test equipment or approval from the Seattle FAA ACO.The Component Maintenance Manuals (CMM) listed in the AWLs are currently FAA Seattle ACO approved. If the CMM allows equivalent tools, test equipment or materials, use of an alternate or equivalent tool, test equipment or material does not require FAA Seattle ACO.EXCEPTIONAL SHORT-TERM EXTENSIONSSince AWL intervals are based on estimations of the probability of an event, an exceptional short-term extension for each fuel sdocument may be made without jeopardizing safety. The local regulatory authority (e.g. a Principal Maintenance Inspector) mexceptional short-term extensions before they take place using procedures established with the local regulatory authority in the “exceptional short-term extension” process is applicable to AWL intervals. It should not be confused with the operator’s “short-tnormal maintenance tasks described in the operators’ manuals and in the Flight Standards Handbook 8900.1.The Seattle FAA ACO has accepted that these exceptional short-term extensions may be granted without consultation with tha1. The term "exceptional short-term extension" is defined as an increase in a fuel system AWL interval that may be needed to 

unexpected situation. All AWLs listed in this section have been approved with an exceptional short-term extension of 30 da

2. Repeated use of extensions, either on the same airplane or on similar airplanes in an operator's fleet, should not be used a

management practices. Exceptional short-term extensions must not be used for fleet AWL extensions. 

After a fuel system AWL has experienced an exceptional short-term extension, the AWL interval will revert back to its interval li

Seattle FAA ACO must approve, prior to its use, any desired extension not explicitly listed above.This exceptional short-term extension listed above applies to airlines that fall under the United States FAA jurisdiction only. Opthe U.S FAA jurisdiction should obtain interval extension approvals from their local regulatory agency.

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REGULATORY AGENCY APPROVALAny deviations from the published AWL instructions included in this document require approval from the Seattle FAA ACO. Thunder the US FAA jurisdiction only and to airplanes registered in the U.S. All other operators should obtain approval form theiagency for any deviations from the listed AWL instructions. AWL REVISION PROCESSIn the event that an AWL is revised, Boeing will prepare a revision to this document that will be approved by the Seattle FAA ACbe forwarded to all 767 operators and the Seattle FAA ACO.

APR 2008
767 MAINTENANCE PLANNING DATA

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E. PAGE FORMAT: FUEL SYSTEMS AIRWORTHINESS LIMITATIONS

COLUMN EXPLANATIONAWL NUMBER Each task is given a unique AWL Item Number. The first and second digits are the ATA Chapter Number.TASK ALI = Airworthiness Limitation Instruction. These tasks are inspections that should be performed at the listed inte

CDCCL = Critical Design Configuration Control Limitation.

INTERVAL Task frequencies are specified in terms of a usage parameter such as flight hours, cycles or calendar time.APPLICABILITY Airplane model applicability.DESCRIPTION Description of the task to be performed or critical design configurations aspects that cannot be changed without v

the design.

APR 2008
D622T001-9

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767 MAINTENANCE PLANNING DATA

FUEL SYSTEMS AIRWORTHINESS LIMITATIONS

AWL 

Number Task Interval Applicability Description

28-AWL-01 ALI 12 Yrs All

External Wires Over Center Fuel TankConcern: Potential for Chafing and arcing to Center Fuel Tank UppePerform a detailed inspection of the wire bundles routed over the cemain deck floor boards between the front spar and rear spar of the cdamaged clamps, wire chafing, and that the wire bundle is not in cofuel tank. If discrepancies are found, repair per the Boeing Standard D6-54446.

28-AWL-02 CDCCL N/A All

External Wires Over Center Fuel TankConcern: Potential for Wire chafing and arcing to Center Fuel Tank If any maintenance is performed in the area under the main deck flofuel tank, verify the following:

1. Maintain the existing wire bundle routing and clamping.2. Installation of any new wire bundles per the Boeing Standard Wi

D6-54446.

3. All wire bundles over the center fuel tank are inspected per 28-A

28-AWL-03 CDCCL N/A

767 airplanes, 

Line Numbers 

869 and on and 

airplanes that 

have incorporated 

Service Bulletin 

767-28A0071 

(767-200/-300/

-300F) or 

767-28A0072 

(767-400ER)

Lightning Protection – Engine Fuel Feed Line Fuel Tank PenetrationConcern: Potential for arcing, sparking or filament heating inside the the bulkhead fitting and the spar during a lightning strike event.The following must be maintained if the bulkhead fitting or attached replaced (refer to Boeing AMM 28-22-07):

1. Verify electrical fay surface bond from bulkhead fitting to structur

(0.5 milliohms) or less.

2. Install full-bodied fillet seal encapsulating the bulkhead fitting to t

the tank.

3. Install full bodied fillet seal encapsulating the first coupling interfa

MAY 2010
767 MAINTENANCE PLANNING DATA

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28-AWL-04 CDCCL N/A All

Lightning Protection – Hydraulic Line Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interfaand the spar during a lightning strike event.Maintain fay surface bond configuration of hydraulic line fuel tank pebulkhead fitting and the spar (refer to Boeing AMM 29-11-27). Verify the bulkhead fitting or attached tubing are removed and replaced.

1. The resistance between the mating surfaces of the heat exchang

is less than 0.001 ohm (1 milliohm).

2. The fay surface bond resistance between the inlet and outlet line

less than 0.005 ohm (5 milliohms).

3. On airplanes with in-line fittings, the resistance across the in-line 

than 0.005 ohm (5 milliohms).

4. The resistance between the bulkhead fitting and the bulkhead is 

(10 milliohms).

5. The installation is inspected per 28-AWL-05.

28-AWL-05 ALI

25,000 Hrs

6 Yrs

Note

All

Lightning Protection – Hydraulic Line Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interfaand the spar during a lightning strike event.Perform the following inspection to ensure functional integrity (refer 

1. Use a bonding meter to do the checks of the bonding resistance 

heat exchanger as follows (refer to Boeing SWPM 20-20-00):

(a) Make sure the resistance between the bulkhead fitting and the 

less than 0.005 ohm (5 milliohms).

(b) Make sure the resistance between the bulkhead fitting and the 

less than 0.005 ohm (5 milliohms).

2. If the bonding resistance is more than 0.005 ohm (5 milliohms), re

a value of 0.001 ohm (1 milliohm) or less (refer to Boeing SWPM 

Interval Note: Whichever comes first.

AWL 

Number Task Interval Applicability Description

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28-AWL-06 CDCCL N/A All

AC and DC Pump MaintenanceConcern: Potential for maintenance error during pump overhaul. Fusource prevention means (i.e., flame arrestor, thermal fuses, materietc.) that must be maintained if pump is overhauled.Repair and overhaul of Fuel Pumps must be per the manufacturer’s Manual (CMM) Numbers, 28-20-02, Revision Number 12, 28-22-01, Revision Number 19, 28-22-03, Revision Number 14, 28-22-11, RevRevision Number 18, 28-22-13, Revision Number 11, 28-22-21, RevRevision Number 6, 28-22-31, Revision Number 2, 28-22-33, Revisiof these CMMs that have been approved by the Seattle FAA ACO.

28-AWL-07 CDCCL N/A All

AC Fuel Pump Fault Current Bonding PathConcern: Potential for fault current path through the pump housing tElectrical faults internal to the fuel pump motor impeller are by desigimpeller assembly to the bonding straps on the front face of the motstructure outside the tank. The bonding straps ensure that fault curroutside the tank until the circuit breaker and/or GFI has had time to The following must be maintained during pump replacement (refer to and 28-22-05):

1. Installation of the two bonding straps between the pump housing 

clip on structure.

2. Pump housing bonding resistance to structure less than or equal 

(0.3 milliohms) for main tank boost pumps and 0.0002 ohm (0.2 pumps.

3. Make sure the bonding resistance between the housing and the 

0.00035 ohms (0.35 milliohms).

AWL 

Number Task Interval Applicability Description

MAY 2010
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28-AWL-08 CDCCL N/A All

Lightning, Fault Current or Hot Short Protection – Fuel Tank PenetraConcern: Potential for arcing or sparking inside the tank at a conduinterface as a result of electrical fault currents or lightning strike evewithin the ground electrical path.Addition of any new penetrations to the fuel tanks (such as adding a equipment) or change to the design features of the existing equipmemeasuring sticks, sump drain valves, fueling manifold, fuel temperatfuel shutoff valve adaptor plate) requires approval by the Seattle FA

28-AWL-09 CDCCL N/A All

Fuel Quantity Indicating System (FQIS) / Surge Tank Fuel Level SenInstallation Separation Requirement Concern: Potential for hot shorts and EMI induced voltages on the Fenter the fuel tank.Routing and installation of any new wiring must use wire types BMS BMS 13-58, and not be within a 2-inch radius of the FQIS wiring. Wseparation greater than 1⁄2 inch must be maintained from FQIS wirin

28-AWL-10 CDCCL N/A All

Center Tank Fueling Valve-Fault Current BondConcern: Potential for arcing or filament heating inside the center wThe following must be maintained if the system is disturbed (refer to airplanes) and 28-21-12 (767-400 only)):Verify the fay surface bond resistance between the valve body and tless than or equal to 0.0025 ohms (2.5 milliohms). Verify fillet seal iand gask-o-seal perimeter inside the tank.The last two limitations are applicable to 767-400 airplanes only.A bonding jumper is installed between the controller and the structuVerify the bonding resistance between the control unit and the rear s0.008 ohms.

AWL 

Number Task Interval Applicability Description

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28-AWL-11 CDCCL N/A All

Fuel Quantity Indicating System (FQIS) – Fuel Quantity Processor UConcern: Potential for maintenance error during Fuel Quantity ProceFQPU is designed to limit the levels of energy, voltage, current, and circuit to intrinsically safe levels in order to preclude the potential of fuel tank.Repair and overhaul of FQPU must be per the manufacturer Compo(CMM) Number, 28-41-68 Revision 4, or a later revision of this CMM Seattle FAA ACO.

28-AWL-12 CDCCL N/A All

Fuel Quantity Indicating System (FQIS) – Repair of In-Tank Hardwaand Compensators) Concern: Potential for maintenance error during repair of in-tank harcompensators and densitometers). Arc gaps may develop that coulinside the fuel tank.Repair and overhaul of FQIS tank units, compensators, and densitomanufacturer CMMs.Goodrich Component Maintenance Manual (CMM) Numbers 28-40-28-40-59 Revision Number 4, 28-40-62 Revision Number 3, 28-41-6revisions of these CMMs that have been approved by the Seattle FAHoneywell CMM Numbers 28-41-01 Revision Number 5, 28-41-07 RRevision Number 6, 28-41-30 Revision Number 1, 28-41-33 revision Number 1, 28-41-35 Revision Number 1, 28-41-36 Revision Numbe7, 28-41- 41 Revision Number 5, 28-41-42 Revision Number 0, or lathat have been approved by the Seattle FAA ACO.

AWL 

Number Task Interval Applicability Description

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767 MAINTENANCE PLANNING DATA

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28-AWL-13 CDCCL N/A All

Fuel Quantity Indicating System (FQIS) – Repair of In-Tank Wire HaConcern: Potential for error during repair or replacement of in-tank wdevelop that could result in an ignition source inside the fuel tank.Repair and overhaul of FQIS in-tank wire harness must be per BoeiInstall FQIS in-tank wire harness must be per Boeing AMM 28-41-09between the wires and structures must be greater than 0.125 inchesVerify the following when installing the spar FQIS penetration:1. The mating surface of the tank wiring harness on the front spar is 2. New O-ring(s) are installed.3. The Jamnuts are tightened to a torque as specified in the Boeing 4. Sealant is installed per instruction in the Boeing AMM Task 28-4

28-AWL-14 CDCCL N/A All

Fuel Tank Access Doors ConfigurationConcern: Potential for arcing or sparking inside the tank at the interftank structure as a result of a direct strike or conducting currents thrThe following must be maintained during fuel tank access door instaAMMs 28-11-01, 28-11-02, and 28-11-03): 1. Verify presence of a molded rubber seal positioned around the o

door that mates with the wing skin inside the tank,

2. Apply grease to both sides of the knitted aluminum mesh gasket3. Install the greased knitted aluminum mesh gasket between the o

the wing skin to establish the electrical conductivity between the wing skin.

AWL 

Number Task Interval Applicability Description

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767 MAINTENANCE PLANNING DATA

28-AWL-15 CDCCL N/A All

Surge Tank Fuel Level Sensor Control Card RepairConcern: Potential for maintenance error during Fuel Level Sensor CLevel Sensor control card is designed to limit the levels of energy, vallowed within the fuel level sensing circuit to intrinsically safe levels potential of an ignition source within any fuel tank.Repair and overhaul of Fuel Level Sensor Control Card must be per Number 28-21-01 Revision Number 1, or later revisions of this CMM the Seattle FAA ACO.

28-AWL-16 CDCCL N/A All

Surge Tank Fuel Level Sensing System – Repair of In-Tank Wire HaConcern: Potential for error during repair or replacement of in-tank wdevelop that could result in an ignition source inside the fuel tank.Repair and overhaul Fuel Level Sensor in-tank wire harness per Boe

Install Surge Tank Fuel Level Sensor in-tank wire harness per Boein

28-AWL-17 CDCCL N/A All

Resetting Tripped Fuel Pump Circuit BreakersConcern: Potential for arcing or sparking inside the tank between fuhousings and outside the tank between pump wiring and structure in Verify it is safe to reset the circuit breaker(s) by following the applicaprocedures. Fault(s) that resulted in circuit breaker trip must be isolto reset.

AWL 

Number Task Interval Applicability Description

MAY 2010
767 MAINTENANCE PLANNING DATA

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28-AWL-18 ALI 12 Yrs All

Fuel Quantity Indicating System (FQIS) – Out Tank Wiring Lightning Concern: Potential for Lightning induced voltages on the FQIS wirinPerform the following inspection to ensure the functional integrity of ground termination (refer to Boeing AMM 20-55-54):

1. Visually inspect all connectors at the location being tested to ens

includes connector plugs and backshells.

2. Use a Loop Resistance Tester P/N 906-10246-2 or 906-10246-3 

resistance of the shield to ground termination for the following ite

767-200 CINCH Wire Bundle:The loop resistance shall not exceed 44 milliohms for Connector M1Wire Bundle S283T025-126.The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-122.The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-127.The loop resistance shall not exceed 43 milliohms for Connector M1Wire Bundle S283T025-136.The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-132.The loop resistance shall not exceed 47 milliohms for Connector M1Wire Bundle S283T025-137.The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-135.

(Continued on next page)

AWL 

Number Task Interval Applicability Description

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28-AWL-18

(Continued)

Fuel Quantity Indicating System (FQIS) – Out Tank Wiring Lightning (Continued)767-300 CINCH Wire Bundle:The loop resistance shall not exceed 44 milliohms for Connector M1Wire Bundle S283T025-121.The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-122.The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-123.The loop resistance shall not exceed 43 milliohms for Connector M1Wire Bundle S283T025-131.The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-132.The loop resistance shall not exceed 47 milliohms for Connector M1Wire Bundle S283T025-134.The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-135.767-300F CINCH Wire Bundle:The loop resistance shall not exceed 44 milliohms for Connector M1Wire Bundle S283T025-321 (-971).The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-122 (-922).The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-323 (-973).The loop resistance shall not exceed 43 milliohms for Connector M1Wire Bundle S283T025-331 (-981).The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-132 (-932).The loop resistance shall not exceed 47 milliohms for Connector M1Wire Bundle S283T025-334 (-984).

(Continued on next page)

AWL 

Number Task Interval Applicability Description

MAY 2010
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28-AWL-18

(Continued)

Fuel Quantity Indicating System (FQIS) – Out Tank Wiring Lightning (Continued)767-300F CINCH Wire Bundle, continued:The loop resistance shall not exceed 40 milliohms for Connector M1Wire Bundle S283T025-135 (-935).767-200 and 767-300 Boeing Wire Bundle:The loop resistance shall not exceed 121 milliohms for Connector DBoeing Wire Bundle 286T0446.The loop resistance shall not exceed 284 milliohms for Connector DBoeing Wire Bundle 286T0446.The loop resistance shall not exceed 150 milliohms for Connector DBoeing Wire Bundle 286T0454.The loop resistance shall not exceed 175 milliohms for Connector DBoeing Wire Bundle 286T0454.The loop resistance shall not exceed 122 milliohms for Connector DBoeing Wire Bundle 286T0448.The loop resistance shall not exceed 284 milliohms for Connector DBoeing Wire Bundle 286T0448.The loop resistance shall not exceed 152 milliohms for Connector DBoeing Wire Bundle 286T0448.The loop resistance shall not exceed 184 milliohms for Connector DBoeing Wire Bundle 286T0448.

(Continued on next page)

AWL 

Number Task Interval Applicability Description

MAY 2010
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767 MAINTENANCE PLANNING DATA

28-AWL-18

(Continued)

Fuel Quantity Indicating System (FQIS) – Out Tank Wiring Lightning (Continued)767-400ER Wire Bundle:The loop resistance shall not exceed 59 milliohms for Connector M1Wire Bundle S283T025-721.The loop resistance shall not exceed 63 milliohms for Connector M1Wire Bundle S283T025-722.The loop resistance shall not exceed 465 milliohms for Connector MWire Bundle S283T025-723.The loop resistance shall not exceed 58 milliohms for Connector M1Wire Bundle S283T025-731.The loop resistance shall not exceed 59 milliohms for Connector M1Wire Bundle S283T025-732.The loop resistance shall not exceed 570 milliohms for Connector MWire Bundle S283T025-734.The loop resistance shall not exceed 66 milliohms for Connector M1Wire Bundle S283T025-735.If the measured loop resistance value is not within the defined limitsrepair in accordance with Boeing AMM 20-55-54.

3. Repair per Boeing AMM if the joint resistance is greater than the 

28-AWL-19 CDCCL N/A All

FQIS – Out Tank Wiring Lightning Shield to Ground TerminationConcern: Potential for Lightning induced voltages on the FQIS wirinIf any maintenance is performed on the FQIS wire bundle in the unpfuselage), verify the following:

1. Presence of shielded wiring.2. The shield ground is terminated per Boeing SWPM 20-10-15.3. The installation is inspected per 28-AWL-18.

AWL 

Number Task Interval Applicability Description

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28-AWL-20 ALI 1 Yr

767 airplanes, 

Line Number 941 

and on, 

and airplanes 

modified by 

Service Bulletins

767-28A0083 or 

767-28A0084.

Note

Center Auxiliary Tank Override/Jettison Fuel Pumps Auto ShutoffConcern: Dry running the center tank fuel pumps has the potential fodeveloping at the pump inlet due to either frictional heating or sparkcontacting the pump rotating elements, rotating elements contacting bearings due to bearing contamination or failure.The automatic shutoff system is installed and designed to limit conti15 seconds.The following test is required in order to protect against latent faultsFunctionally check the center tank fuel boost pump automatic shutoAMM 28-22-00.Airplane Note: Applicable to airplane with installed and activated aut

28-AWL-21 Reserved for future SFAR 88 AWL.28-AWL-22 CDCCL N/A

767 airplanes, 

Line Number 938 

and on, 

and airplanes 

modified by 

Service Bulletin

767-28A0094

Fuel Quantity Indicating System (FQIS) – Installation of Center Fuel Concern: Potential for wire to wire hot short voltages on the center twiring to enter the fuel tank. This is applicable to airplanes with optioThe FQIS HSP is designed to prevent wire to wire external hot short tank where it may cause an ignition. The following features must be maintained during replacement of thAMM 28-41-24):1. Verify the two bonding straps are installed (refer to AMM task).2. Verify the bonds from HSP to Stiffeners where the bonding strap

0.0025 ohms (2.5 milliohms) or less.

3. A new unit must be used.The Hot Short Protector unit is not repairable.

AWL 

Number Task Interval Applicability Description

MAY 2010
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767 MAINTENANCE PLANNING DATA

28-AWL-23 CDCCL N/A

Airplane Line 

Position 941 and 

on, and airplanes 

modified per 

Service Bulletin

767-28A0090.

Lightning and Fault Current Protection – Motor Operated Valve (MOConcern: Potential for arcing or sparking inside the fuel tank at a costructure interface as a result of electrical fault currents event.The following design features must be maintained during actuator, arepair, or replacement (refer to Boeing AMMs 28-22-01, 28-22-02, 2or 28-26-02):

1. Maintain the following if the adapter plate is removed and replace

a. Verify electrical fay surface bond resistance between the ada

0.0005 ohms (0.5 milliohms) or less.

b. Install fillet seal around the periphery of the adapter plate anc. Wet install and cap seal the four bolts that attach the adapter 

and fillet seal around the edge of the hole and on the stationinside the tank.

d. Install sealed electrical fay surface bond between the serrate

plate and the adapter plate. Wet install the index plate screw

e. Install sealed electrical fay surface bond between the mating 

index plate. Wet install the actuator screws using same seal

f. With the bonding jumper not installed, verify electrical bondin

actuator bond strap attachment point and the spar is 0.0025 

g. Prior to attachment of the bonding jumper to the actuator, ve

between the loose end of the bonding jumper and the spar is or less.

h. Attach the bonding jumper to the actuator bonding tab using 

bond and verify electrical bonding resistance between the acbonding jumper terminal is 0.001 ohms (1 milliohm) or less.

(Continued on next page)

AWL 

Number Task Interval Applicability Description

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28-AWL-23

(Continued)

Lightning and Fault Current Protection – Motor Operated Valve (MO

2. Maintain the following if the index plate is removed and replaced

a. Install sealed electrical fay surface bond between the serrate

plate and the adapter plate. Wet install the index plate screw

b. Install sealed electrical fay surface bond between the mating 

index plate. Wet install the actuator screws using same seala

c. With the bonding jumper not installed, verify electrical bondin

actuator bonding tab and the spar is 0.0025 ohms (2.5 millio

d. Prior to attachment of the bonding jumper to the actuator, ve

between the loose end of the bonding jumper and the spar is or less.

e. Attach the bonding jumper to the actuator bonding tab using 

bond and verify electrical bonding resistance between the acbonding jumper terminal is 0.001 ohms (1 milliohm) or less. 

3. Maintain the following if the MOV actuator is removed and replac

a. Install sealed electrical fay surface bond between the mating 

index plate. Wet install the actuator screws using the same s

b. With the bonding jumper not installed, verify electrical bondin

actuator bonding tab and the spar is 0.0025 ohms (2.5 millio

c. Prior to attachment of the bonding jumper to the actuator, ve

between the loose end of the bonding jumper and the spar is or less.

d. Attach the bonding jumper to the actuator bonding tab using 

bond and verify electrical bonding resistance between the acbonding jumper terminal is 0.001 ohms (1 milliohm) or less.

AWL 

Number Task Interval Applicability Description

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767 MAINTENANCE PLANNING DATA

28-AWL-24 CDCCL N/A

Airplane Line 

Position 941 and 

on, and airplanes 

modified per 

Service Bulletin

767-28A0090.

Motor Operated Valve (MOV) Actuator – RepairConcern: Potential for arcing or sparking inside the fuel tank at a costructure interface as a result of lightning or electrical fault current evactuator output shaft is intended to disconnect the output shaft electelectrical circuitry and ground path structure.To verify the integrity of the electrical isolation feature, conduct the fCMM 28-20-21:A Dielectric Strength test on the completed actuator assembly shall 3000 VAC RMS, 60 Hz for one (1) minute between any mounting fooshaft spline. There shall be no evidence of disruptive discharge in texcess of 1.0 milli-amps. The 3000V test is a bench test only and mthe aircraft.

28-AWL-25 CDCCL N/A 767-400ER airplanes

Surge Tank Fuel Level Sensor – Wiring - Electromagnetic CompatibConcern: Potential for electromagnetic energy/power being induced 

into the Fuel Tank.

If any maintenance is performed on the surge tank sensor wire bun

card file to the fuel tank spar penetration, verify the following:

1. Presence of shielded wiring.2. The shield ground is terminated per Boeing SWPM 20-10-15.3. Existing wire bundle routing and clamping.

AWL 

Number Task Interval Applicability Description

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28-AWL-26 ALI 12 Yrs 767-400ER airplanes

Surge Tank Fuel Level Sensor – Wiring - Electromagnetic CompatibConcern: Potential for electromagnetic energy/power being induced 

into the Fuel Tank.

Perform the following inspection to ensure the functional integrity of 

wiring shield to ground termination per Boeing AMM 20-55-54:

1. Visually inspect all connectors at the location being tested to ens

connector plugs and backshells.

2. Use a Loop Resistance Tester P/N 906-10246-2 or 906-10246-3 

resistance of the shield to ground termination for the following iteThe loop resistance for the right sensor W882 from D8408P to D213.86 milliohms and 251.6 milliohms.The loop resistance for the right sensor W884 from D6114P to D27.45 milliohms and 32.30 milliohms.The loop resistance for the left sensor W882 from D8038P to D6229.27 milliohms and 269.73 milliohms.The loop resistance for the left sensor W886 from D6116P to D8and 31.73 milliohms.

28-AWL-27 ALI 1 Yr

767 airplanes, 

Line Numbers 

961 and on, 

and airplanes that 

have incorporated 

Service Bulletin

767-28A0085

Main and Center Auxiliary Fuel Tank Boost/Override/Jettison Fuel P

(GFI) Control Relay System

Concern: GFI is installed to protect against burn-through of the pum

and to protect against overheating of the pump explosion proof cavtemperature on the outside surface of the conduit, due to electrical 

Perform an operational test of the Main Fuel Tank Boost Pumps an

Override/Jettison Fuel Pump GFI Control Relays per Boeing AMM 

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767 MAINTENANCE PLANNING DATA

28-AWL-28 ALI 1 Yr

767 airplanes, 

Line Numbers 

961 and on, 

and airplanes that 

have incorporated 

Service Bulletin

767-28A0085

Center Auxiliary Fuel Tank Override/Jettison Fuel Pump UncommaConcern: Dry running of the Center Auxiliary Fuel Tank Override/Je

a single failure event has the potential to be an ignition source deveeither frictional heating or sparking as a result of FOD contacting throtating elements contacting stationary parts, or hot journal bearingor failure.

Perform a Functional Test of the Center Auxiliary Fuel Tank Overrid

Uncommanded-On System per Boeing AMM 28-22-00.

28-AWL-29 CDCCL N/A

767 airplanes, 

Line Numbers 

990 and on, 

and airplanes that 

have incorporated 

Service Bulletin

767-28A0104

In-Tank AC Fuel Pump Wire Bundles with Protective LinerConcern: Potential for the boost pump wiring to chafe and arc in the source in the fuel tank. The boost pump wires that are in the conduits in the fuel tanks have a Teflon sleeve to protect from wire chafing. The wiring also has a sthat is monitored by the GFI for an additional layer of protection for a the conduit.Ensure the following conditions exist when replacing pump wiring or AMM 28-22-15):– Jacketed shielded (grounded at both ends) wiring.– Teflon sleeve.– Conduit liner.This applies to the following fuel pumps:1) Left and Right AFT/FWD Main Fuel Tank Boost Pumps.2) Left and Right Auxiliary Fuel Tank Override/Jettison Fuel Pumps

AWL 

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767 MAINTENANCE PLANNING DATA

28-AWL-30 CDCCL N/A

767 airplanes, 

Line Numbers

1 to 989, and 

airplanes that 

have incorporated 

Service Bulletin 

767-28A0053 R2

Fuel Boost Pump Wires In Conduit Installation – In Fuel TankConcern: Potential for the boost pump wiring to chafe and arc in the source in the fuel tank. The boost pump wires that are in the conduitincorporated two (2) Teflon sleeves to protect from wire chafing (refe767-28A0053 R2). The wiring also has a jacket to provide chafing pEnsure the following condition exists when replacing pump wiring or AMM 28-22-15):– Jacketed wiring and a Teflon sleeve.

The Teflon sleeve is not repairable. If damaged (chafed), it must be 

This applies to the following fuel pumps:1) Left and Right AFT/FWD Main Fuel Tank Boost Pumps.2) Left and Right Auxiliary Fuel Tank Override/Jettison Fuel Pumps

AWL 

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767 MAINTENANCE PLANNING DATA

F. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)

Maintenance requirements arising from aircraft certification activities are described in FAR 25.1309 and AC 25.1309. Independprocess, these CMRs are developed as part of the aircraft systems safety analyses required for aircraft certification. CMR tasksystem probabilities and failure effects are not expected to fall within an acceptable range without a periodic maintenance requThere are two categories of CMRs. The first are those tasks associated with items critical to safety of flight; these "critical" systexpected probability of failure within the "extremely improbable" range. The second category of CMRs are those tasks associasafety of flight; these "essential" systems must have an expected probability of failure within the "improbable" range.The following notes apply to all CMR Tasks:1. CMRs are a part of the aircraft's certification basis.2. Approval of CMRs and escalation of CMR task frequencies are the exclusive responsibility of FAA Engineering.3. There shall be no short-term escalation of CMRs.4. There shall be no reliability program escalation of CMRs.5. There shall be no Flight Standards inspector escalation of CMRs.

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767 MAINTENANCE PLANNING DATA

FIGURE 4. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs) EXAMPL

(P, N, H OR G)

767 CERTIFICATION MAINTENANCE REQUIREMENT

EXAMPLE ILLUSTRATING FORMAT

ALL ALL

G = G.E. CF6-80A ENGINE, AND D = RR RBENGINE.

P = P&W JT9D-7R4 ENG

N = PW4000 ENGINE, H = G.E. CF6-80C EN(A to Z) Used where no specific MM co(00 to 99) MM SUBJECT NUMBER(12 to 80) ATA CHAPTER(00 to 99) MM SECTION NUMBER

6-600 Inspection/Check7-700 Cleaning/Painting

1-100 Fault Isolation

2-200 Maintenance practices 3-300 Servicing4-400 Removal/Installation5-500 Adjustment/Test

(1 to 7) MM PAGE BLOCK(A to Z) UNIQUE ALPHA INDENTIFIER

27-51-00-5D 9 OP

-

XXX-XX-XX-XX

TKAS

CAT SYSTEMS TASK DESCRIPTION

04000 HRS

ACCESS

119AL

ZONE

120 PERFORM BITE TEST OF FLAP/SLAT ELECTRONICS UN

CMR

INTERVAL

APL ENG

APPLICABILITY

ITEM NUMBER

MPD

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767 MAINTENANCE PLANNING DATA

G. PAGE FORMAT: CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)

COLUMN EXPLANATION

MPD ITEM NUMBER Each task in the MPD is identified with a unique number. The first 6 digits (excluding the P, N, H, G or D engine ide

the appropriate ATA Chapter-Section-Subject in the Boeing Maintenance Manual (MM) that deals generally with tinformation specific to the task is provided, a seventh digit indicates the first digit of the page block where it can bAlpha characters following the seventh digit differentiate between multiple tasks in the same page block. When inthe task is not provided in the MM, the seventh digit is an alpha character.

TASK MSG-3 TASK CATEGORIES

LU = LUBRICATIONSV = SERVICINGVC = VISUAL CHECKOP = OPERATIONAL CHECKIN = INSPECTIONFC = FUNCTIONAL CHECKRS = RESTORATIONDS = DISCARD

Any act of consumable replenishment for the purpose of madesign capabilities.Any act of consumable replenishment for the purpose of madesign capabilities.A visual failure finding task to determine if an item is fulfilling Does not require quantitative tolerances.A failure finding task to determine if an item is fulfilling its intDoes not require quantitative tolerances.An examination of an item against a specific standard. This finding task.A quantitative check to determine if one or more functions owithin specified limits. This is a potential failure finding taskReworking, replacement of parts or cleaning necessary to respecific standard.The removal and replacement of an item.

CMR INTERVAL CMR interval specified in terms of flight hours, flight cycles, calendar time, letter check, or Daily Check. When two 

a single task, the top interval is the threshold and the bottom one is the repeat interval. A "NOTE" is used to indica

is provided under the task description.

ZONE Airplane Zone Number (see Zone Diagrams, Section 3) where task is performed.ACCESS Access Panel/Door Number (see Access Panel/Door illustrations, Section 4) required to be opened to perform the 

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 APPLICABILITY APL ENG

Applicable Airplane Model and Engine. "ALL" applies to all models of airplanes or engines. A "NOTE" refers to a

the task description. Specific models of airplanes and engines are listed below:

APL

200 = 767-200, -200ER300 = 767-300, -300ER400E = 767-400ERPASS = Passenger AirplanesSF = 767-200 Special Freighter300F = All 767-300 FreightersBCF = 767-300 Boeing Converted FreighterALL = All Airplanes

ENGINE

4000 = P&W PW4052, PW4056 and PW40607R4 = P&W JT9D-7R4D and -7R4E7R4D = P&W JT9D-7R4D7R4E = P&W JT9D-7R4E80 = GE CF6-80A and -80C80A = GE CF6-80A80C = GE CF6-80C524 = RR RB211-524H

TASK DESCRIPTION Description of the task to be performed.

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767 MAINTENANCE PLANNING DATA

H. CERTIFICATION MAINTENANCE REQUIREMENTS TASKS

MPD

ITEM

NUMBER TASK

CMR 

INTERVAL ZONE ACCESS

APPLICABILITY

767

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTI

24-33-00-6A OP 00048 HRS 212 ALL ALL Check Standby Power System operation (if not check

Interval Note: Task should not exceed 48 elapsed clo

26-10-00-6A OP 00048 HRS 212 ALL ALL Operationally Check AFOLTS (Automatic Fire/Overhe

Eng/APU/Cargo Test Switch (if not checked by crew)Interval Note: Task should not exceed 48 elapsed clo

27-21-00-5A FC 00400 HRS 211 ALL ALL Perform Single Hydraulic System Check of each rudd

System in sequence. This also verifies that the Ruddare open.

27-31-00-5B FC 00400 HRS 211 ALL ALL Perform Single Hydraulic System Check of each Elev

system in sequence.

27-51-00-5D OP 04000 HRS 120 119AL NOTE ALL Perform Bite Test of Flap/Slat Electronics Unit (FSEU

Airplane Note: Applicable to all 767 Airplanes except 

27-51-00-5I FC 12000 HRS 552

561652661

400E ALL Functionally Check the Wing Flap Drive No-back Bra

Note: CMR frequency is 12000 Hours for the OutboaCMR). This CMR does not apply to the Inboard Flap 2C interval. See AC 25-19 for Two Star CMR definitio

28-22-00-5A

DELETED

OP 04000 HRS 119

212521

119AL

521QB

NOTE ALL Operationally Check Center Auxiliary Fuel Tank Over

Airplane Note: Applicable only to A/C with deactivate

28-25-00-5B

DELETED

OP 04000 HRS 212

551

ALL ALL Check operation of APU DC Fuel Pump Isolation Valv

28-41-00-5A

DELETED

FC 04000 HRS 212

531532631632

NOTE ALL Perform Comparison Check of each channel of the F

(FQIS) using measuring sticks. (Main Fuel Tank shoeach)Airplane Note: SB 767-28A5. Task is applicable to aiand 82 through 83 which have not incorporated SB.

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29-11-00-5A OP 04000 HRS 195

211

195SL NOTE ALL Operationally Check ADP Speed Topping Shutdown C

SB 767-29-4. CMR Classification can be deleted proAirplane Note: SB 767-29-4. Task is applicable to air20 and 21 which have not incorporated this SB.

29-11-00-6F FC 12000 HRS 211 ALL ALL Check gross internal leakage of each Hydraulic Syste

Note: For the 767-200/300/300F Models, the internal and Right Hydraulic Systems is 4.5 GPM. This rate pbefore a subsequent leakage check and not become limit.Note: For the 767-400ER, the internal leakage limits the same as for the other 767 models. The Internal LHydraulic System is 2.5 GPM. This rate permits the lsubsequent leakage check and not become more tha

29-11-00-6G FC 12000 HRS 211

324335345

324GL

324JL

324LL

335EB

335GB

335HB

345EB

345GB

345HB

ALL ALL Check Internal leakage of Elevator and Rudder Powe

and Right).

29-21-00-5A OP 06000 HRS 144

198211

1961

742

ALL ALL Operationally Check Auto and Manual RAT Deploym

and Drive System.

31-41-00-2A OP 00100 HRS 212 NOTE ALL Perform a readout of all EICAS maintenance messag

Display Select Switch (if not checked by crew).Airplane Note: Applicable to all 767 airplanes except 

31-41-02-4A OP 10800 HRS 212 NOTE ALL Check operation (including L-R Switching) of the Righ

by crew).Airplane Note: Applicable to all 767 airplanes except 

MPD

ITEM

NUMBER TASK

CMR 

INTERVAL ZONE ACCESS

APPLICABILITY

767

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTI

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31-63-00-2A OP 00100 HRS 212 400E ALL Perform a readout of all EICAS Maintenance Messag

MSG on the MCDU Maintenance Display (if not chec

31-51-00-5B OP 00600 HRS 119

211212312

119AL

312AR

BCF

SF

ALL Operationally Check take-off warning system.

31-51-00-5C OP 00072 HRS

NOTE

211212

BCF

SF

ALL Operationally Check the take-off configuration warnin

Interval Note: Task should not exceed 72 elapsed clo

32-35-00-5A OP 04000 HRS 119

120211

119AL NOTE ALL Check operation of the Main/Nose Landing Gear Alte

limiters for evidence of partial or fully crushed core.Airplane Note: Applicable to all 767 Airplanes except 

32-41-00-5A OP 00250 HRS 211 NOTE ALL Operationally Check Alternate Brake System Includin

SB 767-32-4. CMR Classification can be deleted, pro(Line Numbers 4, 24, 28, 30, 32, 35 and 47 and on inequivalent).Airplane Note: Airplanes with Dual Cable System.

32-41-05-4A OP 00250 HRS 211 NOTE ALL Operationally Check Accumulator Isolation Valve.

Airplane Note: SB 767-32-4. Task is applicable to airpSB (Line Numbers 4, 24, 28, 30, 32, 35 and 47 and oSB equivalent).

36-11-01-6C IN 1C 411 411CL

411ER

ALL NOTE Perform Dye Penetrant Inspection of the Eng 1 IP Ble

the Flange Bolts.Engine Note: Rolls-Royce Service Bulletin 75-9285: ARB211-524G/H engines that have not incorporated th

36-11-01-6C IN 1C 421 421CL

421ER

ALL NOTE Perform Dye Penetrant Inspection of the Eng 2 IP Ble

the flange bolts.Engine Note: Rolls-Royce Service Bulletin 75-9285: ARB211-524G/H Engines that have not incorporated th

MPD

ITEM

NUMBER TASK

CMR 

INTERVAL ZONE ACCESS

APPLICABILITY

767

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTI

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52-51-07-4A DS 9 YRS 211

212

NOTE ALL Discard the Flight Deck Door Strike Assembly.

Airplane Note: Applicable to Airplane Line Number 89incorporated Service Bulletin 767-25-0325 or 767-25-

D77-35-00-2B OP 00560 HRS 119

120

119AL ALL 524 Verify that there are no Engine 1 EEC Category 2 fau

D77-35-00-2B OP 00560 HRS 119

120

119AL ALL 524 Verify that there are no Engine 2 EEC Category 2 fau

D77-41-01-4A OP 00400 HRS 212 ALL 524 Check the operation of the Standby Engine Indicator 

(if not checked by crew).

G73-21-06-6A OP 04000 HRS 411 416AR ALL 80A Verify proper power input signal to the L Flight Idle Se

Fuel Control.

G73-21-06-6A OP 04000 HRS 421 426AR ALL 80A Verify proper power input signal to the R Flight Idle S

Fuel Control.

G73-21-07-5A OP 04000 HRS 211

411

416AR ALL 80A Verify proper EEC detection of a fault in the Fail-Fixe

G73-21-07-5A OP 04000 HRS 211

421

426AR ALL 80A Verify proper EEC Detection of a fault in the Fail-Fixe

G77-00-00-6D OP 00400 HRS 211 ALL 80A Check operation of Standby Engine Indicator by actu

by crew).

G78-00-00-6R IN 04000 HRS 415

416

415AL

416AR

ALL 80A Visually Inspect the Nacelle/Strut Fire and Drainage S

damage/deterioration – L Eng.

G78-00-00-6R IN 04000 HRS 425

426

425AL

426AR

ALL 80A Visually Inspect the Nacelle/Strut Fire and Drainage S

damage/deterioration – R Eng.

H77-41-00-5A OP 00400 HRS 211 NOTE 80C Check operation of Standby Engine Indicator by actu

by crew).Airplane Note: Applicable to all 767 Airplanes except 

H77-35-00-2B OP 02000 HRS 120 119AL NOTE 80C Verify that there are no Engine 1 or Engine 2 Catego

Airplane Note: Airplanes with Full Authority Electronic 

MPD

ITEM

NUMBER TASK

CMR 

INTERVAL ZONE ACCESS

APPLICABILITY

767

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTI

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H78-00-00-6R IN 04000 HRS 415

416

415AL

416AR

ALL 80C Visually Inspect the Nacelle/Strut Fire and Drainage S

damage/deterioration – L Eng.

H78-00-00-6R IN 04000 HRS 425

426

425AL

426AR

ALL 80C Visually Inspect the Nacelle/Strut Fire and Drainage S

damage/deterioration – R Eng.

H78-00-00-6T IN 06000 HRS 411 NOTE

413AL

414AR

415AL

416AR

417AL

418AR

400E 80C Visually Check the Engine 1 Thrust Reverser Bull-No

Note: This CMR is a Two Star CMR. See AC 25-19 fAccess Note: The Thrust Reverser Sleeve must be p

H78-00-00-6T IN 06000 HRS 421 NOTE

423AL

424AR

425AL

426AR

427AL

428AR

400E 80C Visually Check the Engine 2 Thrust Reverser Bull-No

Note: This CMR is a Two Star CMR. See AC 25-19 fAccess Note: The Thrust Reverser Sleeve must be p

H78-34-00-5A

DELETED

FC 05000 HRS 211

212411

413AL 400E 80C Functionally Check the Engine 1 Directional Pilot Valv

detect pneumatic leakage.Note: This CMR is the subject of NPRM 2000-NM-24when the final rule has been issued.

H78-34-00-5A

DELETED

FC 05000 HRS 211

212421

423AL 400E 80C Functionally Check the Engine 2 Directional Pilot Valv

detect pneumatic leakage.Note: This CMR is the subject of NPRM 2000-NM-24when the final rule has been issued.

N77-35-00-2B OP 01000 HRS 119

120

119AL ALL 4000 Verify that there are no Engine 1 or Engine 2 EEC Ca

Cat 2).

MPD

ITEM

NUMBER TASK

CMR 

INTERVAL ZONE ACCESS

APPLICABILITY

767

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTI

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N77-41-01-4A OP 00400 HRS 212 NOTE 4000 Check the operation of the Standby Engine Indicator 

(if not checked by crew).Airplane Note: Applicable to all 767 Airplanes except 

P73-21-07-5A OP 04000 HRS 211

411

414AR416AR418AR

ALL 7R4 Verify proper Power Input Signal to the L Eng EEC Tr

P73-21-07-5A OP 04000 HRS 211

421

424AR426AR428AR

ALL 7R4 Verify proper Power Input Signal to the R Eng EEC T

P77-00-00-6B OP 00400 HRS 211 ALL 7R4 Check operation of Standby Engine Indicator by actu

by crew).

P78-00-00-6R IN 04000 HRS 411

413414415416431435

413AL

414AR

415AL

416AR

417AL

418AR

431AT431BT

431DT

ALL 7R4 Visually inspect the Nacelle/Strut Fire and Drainage S

damage/deterioration – L Eng.

P78-00-00-6R IN 04000 HRS 421

423424425426441445

423AL

424AR

425AL

426AR

427AL

428AR

441AT441BT

441DT

ALL 7R4 Visually Inspect the Nacelle/Strut Fire and Drainage S

damage/deterioration – R Eng.

MPD

ITEM

NUMBER TASK

CMR 

INTERVAL ZONE ACCESS

APPLICABILITY

767

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTI

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I. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS

Title 14 Code of Federal Regulations Sections 121.703 and 135.415 state that “each certificate holder shall report any failure, maircraft, system, component, or powerplant that occurs or is detected at any time if, in its opinion, that failure, malfunction, or demay endanger the safe operation of an aircraft”. Section 125.409 also requires reporting of failures, malfunctions or defects. In failure or malfunction will be obvious, but there are some failure modes related to uncontrolled high thrust that are reportable bufollowing information is provided, as required by FAA Exemption No. 8119, to assist the operators in identifying reportable malfuncontrolled high thrust.The FAA has concluded that the loss of capability to control thrust due to a failure of the engine thrust control system may endaincludes any malfunctions having one or more of the following characteristics:• Auto-acceleration or uncommanded thrust change to higher power• Stuck thrust lever above idle power• Inability to reduce thrustAlthough some of these incidents may not appear to be safety related, documenting the events is important to ensure the presemaintained and/or to identify failure conditions that must be corrected.When filing a report of such an event with the FAA, the operator is requested to include in the description of the event one or mphrases:• “thrust control”• “no response to thrust lever”• “auto-acceleration”• “uncontrolled high thrust”

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In addition, the following information should be included in the report:• Event description• Flight Crew action• Maintenance action• List of affected or removed componentsReports should be submitted to the local representative of the FAA Administrator that handles the appropriate reporting respon125.409, and 135.415. In addition to filing reports with the FAA, it is recommended that a copy be sent to Boeing and to the en

OCT 2007