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767

MAINTENANCE PLANNING DATA (MPD) DOCUMENT

SECTION 9

AIRWORTHINESS LIMITATIONS (AWLs) AND 

CERTIFICATION MAINTENANCE REQUIREMENTS (CM

D622T001-9

SEPTEMBER 2013

COMPILED AND PUBLISHED BY:

MAINTENANCE PROGRAMS ENGINEERING

COMMERCIAL AVIATION SERVICES

BOEING COMMERCIAL AIRPLANE GROUP

SEATTLE, WASHINGTON

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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............................................................................................................................

D.1 AWLS – FUEL SYSTEM IGNITION PREVENTION................................................................................................................

D.2 ENGINE FUEL SUCTION FEED SYSTEM.............................................................................................................................

D.3 AWLS – LOW FUEL AND FUEL CONFIGURATION INDICATION TEST ..............................................................................D.4 AWLS – NITROGEN GENERATION SYSTEM (NGS)............................................................................................................D.5 IMPACT-RESISTANT FUEL TANK ACCESS DOORS ...........................................................................................................

E. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRS) ....................................................................................................

F. 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

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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 

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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 (F

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-NELSON 

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-NELSON 

REVISIONS

REVISION AND REVISION DESCRIPTION 

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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-NELSON 

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 

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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 AC

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 

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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 

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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 

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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: S

REVISIONS

REVISION AND REVISION DESCRIPTION 

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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: J

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: J

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: J

REVISIONS

REVISION AND REVISION DESCRIPTION 

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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.

(Continued from previous page) (Con

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: J

REVISIONS

REVISION AND REVISION DESCRIPTION 

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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:  J

REVISIONS

REVISION AND REVISION DESCRIPTION 

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JUNE 2010This revision includes changes to support certain 767 passenger aircraft. For L/N 969, Tasks 53-30-I01, 53-50-I01, 53-60-I01, 53-10-I07C, 53-30-I04C, 53-60-I05C, 53-10-I07D, 

53-30-I04D, 53-60-I05D were revised by updating the additional inspections with reference to SB 767-53-0210. For L/N 971, Tasks 53-10-I07C, 53-30-I04C, 53-60-I05C, 53-10-I07D, 

53-30-I04D, 53-60-I05D were revised by updating the additional inspections with reference to SB 767-53-0211. For both L/Ns 969 and 971, the 37,500 cycle reduced threshold for the tasks noted above was revised to 50,000 cycles due to the inclusion of SB inspections.Revised the 767 Passenger-to-Freighter Conversion Airplane paragraph by removing the 3,750 flight cycle and 11,250 flight hour limitations for the 767-200 Boeing Special Freighter (767-200SF).Revised the Airworthiness Limitations Section to reflect the assessment of the 767-200SF Supplemental Structural Inspection Program. Certain Structural Significant Items (SSIs) 

include a flag note to indicate an operational limitation – no 767-300BCF and 767-200SF airplane may be operated beyond the SSI threshold until the applicable inspection procedures are validated, published in the appropriate manual and accepted by the FAA.Revised Structural Safe Life Parts by removing the operational Life Limit of 1,000 Landings for the “767-200SF Nose Landing Gear, Main Landing Gear and Gear Support Structure” and replacing it with the calculated Safe-Life Limit. Revised Structural Safe Life Parts by adding the following text “WING MAIN LANDING GEAR BEAM” to provide clarity for the Life Limit requirements for the 767-400E. Revised SSIs 57-20-I12C, 57-20-I15J, 57-20-I16K, and 57-10-I20A by changing the thresholds from FLS Curve to 50,000 FC or 70,000 FC, as applicable.Added SSI 57-10-I20B.Added SSIs 55-10-I09A, 55-10-I13D, 55-10-I13E, 55-10-I14C, 55-10-I14D, 55-10-I31A, and 55-10-I31B.

Submitted by: John Sabolchy(Boeing) 

Approved by: R J

JULY 2010Added new Section F., Airworthiness Limitations – Nitrogen Generation System Tasks.

Submitted by: John Sabolchy(Boeing) 

Approved by: R R

REVISIONS

REVISION AND REVISION DESCRIPTION 

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AUGUST 2010Revised 47-AWL-04 by updating the interval from 6,600 Flight Hours (FH) to 3,000 FH based on updated analysis.Revised 47-AWL-05 by updating the interval from 5,000 FH to 3,000 FH based upon updated analysis. Revised the Task Description by replacing “Functionally” with “Operationally” to accurately reflect the inspection intent.

Submitted by: John Sabolchy(Boeing) 

Approved by: R 

AUGUST 2010 R1Revised 47-AWL-04 and 47-AWL-05 by updating the interval from 3,000 Flight Hours (FH)to 2,600 FH based upon a change to the certification analysis for fuel tank flammability exposure for the 767 Nitrogen Generation System.

Submitted by: John Sabolchy(Boeing) 

Approved by: P 

AUGUST 2010 R2Revised SSIs 53-10-I07C/53-30-I04C/53-60-I05C and 53-10-I07D/53-30-I04D/53-60-I05D by adding the following text to provide better clarification regarding the applicability of DTR Check Forms: “L/N 994, Lap S-26R: BS 1406 to BS 1428 and S-25R to S-27R centerlines must be inspected with external detailed inspection every 600 flight cycles (after reaching threshold).” 

Submitted by: John Sabolchy(Boeing) 

Approved by: D R 

APRIL 2011Revised Airworthiness Limitations-Structural Inspection table tasks 53-10-I07A, 53-30-I04A, 53-60-I05A, 53-10-I07B, 53-30-I04B, and 53-60-I05B by adding revised inspection method due to structural repair for L/N 1004.

Submitted by: John Sabolchy(Boeing)

Approved by: S R 

JUNE 2011Revised Airworthiness Limitations - Structural Inspections table task 53-10-I07C/53-30-I04C/53-60-I05C by adding revised inspection method and threshold due to structural repair for L/N 1008.

Submitted by: Bill Lindholm(Boeing)

Approved by: S R 

REVISIONS

REVISION AND REVISION DESCRIPTION 

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JULY 2011Revised 47-AWL-03 to incorporate NGS performance features to show compliance with14 CFR 26.33.

Submitted by: Mark Arnold (Boeing) 

Approved by:  

NOVEMBER 2011Revised Airworthiness Limitations - Structural Inspections table tasks 53-10-I07C/

53-30-I04C/53-60-I05C and 53-10-I07D/53-30-I04D/53-60-I05D to provide the applicability and inspection methods due to the structural repair of L/N 1018 and L/N 1019.

Submitted by: Bill Lindholm(Boeing)

Approved by: J

DECEMBER 2011Revised Airworthiness Limitations - Structural Inspections table task SSI 53-10-I07D/53-30-I04D/53-60-I05D to provide the applicability and inspection method due to the structural repair of L/N 1020.

Submitted by: Bill Lindholm(Boeing)

Approved by: 

FEBRUARY 2012Revised Airworthiness Limitations - Structural Inspections Table Task SSI 53-10-I07A/53-30-I04A/53-60-I05A and 53-10-I07B/53-30-I04B/53-60-I05B inspection in accordance with SB 767-53-0231 for L/N 973, and inspection in accordance with SB 767-53-0238 for L/N 1004.Revised Airworthiness Limitations - Structural Inspections Table Task SSI 53-10-I07C/53-30-I04C/53-60-I05C and 53-10-I07D/53-30-I04D/53-60-I05D inspection in accordance with SB 767-53-0230 for L/N 994.Revised Airworthiness Limitations - Structural Inspections Table Task SSI 53-10-I07C/53-30-I04C/53-60-I05C and 53-10-I07D/53-30-I04D/53-60-I05D by deleting alternate inspection for L/N 1018 at Lap S-26L: BS 467 to BS 489 and S-25L to S-27L. Alternate inspections specified in revision dated NOV 2011 for structural repair are not valid due to skin replacement and return to drawing configuration.

Submitted by: Mike Eckelberry(Boeing)

Approved by: 

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OCTOBER 2012Revised the Airworthiness Limitations - Structural Inspections, Introduction Section by adding references to MPD Appendix K (Structures Baseline Requirements).Revised Airworthiness Limitations - Structural Inspections Table Task 53-10-I07C/53-30-I04C/53-60-I05C by adding Inspection Method and Repeat Interval due to structural repair of L/N 1040.Revised Airworthiness Limitations - Structural Inspections Table Task 53-10-I07C/53-30-I04C/53-60-I05C by referencing the SB 767-53-0240 for L/N 1008 and SB 767-53-0244 for L/N 1019.Revised Airworthiness Limitations - Structural Inspections Table Task 53-10-I07D/53-30-I04D/53-60-I05D by referencing the SB 767-53-0244 for L/N 1019.Revised Section D by replacing the “FUEL SYSTEMS AIRWORTHINESS LIMITATIONS” subheading with “INTRODUCTION" to be consistent with other Section 9 documents.Revised Section E lettering to be a subheading of Section D, to be consistent with other Section 9 documents.Revised the subheading of Section E from “FUEL SYSTEM AIRWORTHINESS LIMITATIONS” to “D.1 AWLs – FUEL SYSTEM IGNITION PREVENTION” to be 

consistent with other Section 9 documents.

Added Section D.2 – Engine Fuel Suction Feed System, and ALI 28-AWL-101 – Engine Fuel Suction Feed Operational Test, that is required to protect against engine flameout during suction feed operations.Revised Section F, making it Section D.3 to be consistent with other Section 9 documents. Added “AWLs – Nitrogen Generation System” subheading to be consistent with other Section 9 documents.Added Section D.4 – Impact-Resistant Fuel Tank Access Doors, and CDCCL 57-AWL-01 – Impact-Resistant Fuel Tank Access Doors, to verify the fuel tank access door is impactresistant during installation of the Fuel Tank Access Doors.Revised Section G lettering, making it Section E to be sequential in order to the heading changes made above.

(Continued on next page)

Submitted by: Sheila Reilley (Boeing)

REVISIONS

REVISION AND REVISION DESCRIPTION 

SEP 2013
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767 MAINTENANCE PLANNING DATA

OCTOBER 2012, ContinuedRevised Section H, making it a subheading of Section E to be consistent in format with other 

Section 9 documents.Revised Section I, making it a subheading of Section E and revised the subheading title from "CERTIFICATION MAINTENANCE REQUIREMENTS TASKS" to "CMR TASKS" to be consistent with other Section 9 documents.Revised CMR tasks 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 to match the MPD Task Numbers.Revised Section J, making it Section F to be sequential in order to the heading changes previously incorporated.

(Continued from previous page) (Con

JANUARY 2013Revised Airworthiness Limitations - Structural Inspections Table Tasks 53-10-I07A/53-30-I04A/53-60-I05A and 53-10-I07B/53-30-I04B/53-60-I05B by adding Inspection Location, Inspection Method, and Repeat Interval due to structural repair of L/N 1047.Revised Airworthiness Limitations – Structural Inspections Titles for SSIs 53-80-I01B, 53-80-I01C, 53-80-I01D, and 53-80-I01E in accordance with the DTR Check Form revisions.Revised 47-AWL-04 by changing the interval to "Note" and adding an Interval Note to the Description. Airplanes that incorporate an EICAS instead of the operability indicator in the wheel well have a "6600 FH" interval instead of the "2600 FH" interval. Revised the Applicability from "767 airplane Line Numbers 993 and on or airplanes that have incorporated Service Bulletin 767-47-0001" to "ALL NOTE" and added an Applicability Note in the Description.Revised 47-AWL-05 by changing the interval to "Note" and adding an Interval Note to the Description. Airplanes that incorporate an EICAS instead of the operability indicator in the wheel well have a "4391 FH" interval instead of the "2600 FH" interval. Revised the Applicability from "767 airplane Line Numbers 993 and on or airplanes that have incorporated Service Bulletin 767-47-0001" to "ALL NOTE" and added an Applicability Note in the Description.Revised 57-AWL-01 by adding a reference to Boeing AMMs 28-11-01 and 28-11-02.

Submitted by: Krupal Desai for Sameera Wijesinghe (Boeing)

REVISIONS

REVISION AND REVISION DESCRIPTION 

SEP 2013
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APRIL 2013Revised Airworthiness Limitations - Structural Inspections Table Tasks 53-10-I07C/53-30-I04C/53-60-I05C and 53-10-I07D/53-30-I04D/53-60-I05D by adding Inspection Location, Inspection Method, and Repeat Interval due to structural repair of L/N 1055.

Submitted by: Sameera Wijesinghe (Boeing)

AUGUST 2013Added Section D.3 – AWLs – Low Fuel and Fuel Configuration Indication Test, and ALI 28-AWL-102 to operationally check the Fuel indication for LOW FUEL Caution message and FUEL CONFIG Advisory message.Revised the numbering of the remaining Systems AWL sections due to the addition of Section D.3.

Submitted by: Cassandra Ho (Boeing) 

SEPTEMBER 2013Revised the Airworthiness Limitations - Structural Inspections Front Matter to clarify Removable Structural Components requirements.Revised Subsection B. Airworthiness Limitations: To account for the possibility of excess sealant: Added AMM procedure references for excess sealant removal and application.Added SSIs 57-10-I01C.1 and 57-10-I01C.2 for the 300F.Added SSIs 57-10-I02 and 57-10-I08 for the 767-400E.Added SSIs 57-20-I03A and 57-20-I03B for the 767-400E.Deleted SSIs 57-10-I03D and 57-10-I03E and replaced them with 57-10-I03A and 57-10-I03C.Revised SSI 57-10-I03A for 767-200ER, 767-300ER PASS, 300F, and 400E by extending the inspection area to the inboard edge of the terminal fitting.Revised applicability for SSI 57-10-I02A from "400E" to "ALL except 200SF, 300BCF".

(Continued on next page)

Submitted by: Sameera Wijesinghe (Boeing)

REVISIONS

REVISION AND REVISION DESCRIPTION 

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SEPTEMBER 2013, ContinuedGeneral revisions: Added L/N applicability to thresholds in ATA 57 for clarification.Revised Type for SSIs 55-10-I13B and 55-10-I13C from "Type 2" to "Type 1".Revised the title for SSI 57-20-I15F for the 767-400E, both mission to replace Rib 6 with Rib 5.Revised the applicability of SSI 57-53-I04Y for the "Flap Support Fitting - Upper Flange Inboard Bolt Location" to 767-400E.Revised the applicability of SSI 57-53-I04Y for the "Side Strut Swivel Support Fitting - Satellite Holes at Lug 6" to 767-200, 200SF, 300BCF, 300F and 300 PASS.Revised multiple SSI titles for consistency with the DTR Check Forms for ATA 55 and 57.Revised multiple SSI zones to reflect the correct inspection area.Revised applicability to separate the 200SF and/or 300BCF from SSIs associated with the DTR Check Form curves for ATA 55 and 57.Revised SSI "57-10-I16" to read "57-10-I16B".Revised the applicability of SSI 57-20-I07 to be more clear.Revised the DTR Check Form Title for SSI 57-20-I15K to more accurately describe the inspection area.Revised the threshold for SSI 57-20-I27 for 767-ALL to reference Service Bulletin 767-57A0117, similar to the notes on the DTR check form.

(Continued from previous page) (Cont

REVISIONS

REVISION AND REVISION DESCRIPTION 

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Section Page Date Section Page Date Section Page Date Section Page Date 

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LIST OF EFFECTIVE PAGES

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767 MAINTENANCE PLANNING DATA

A. SCOPE

The scheduled maintenance requirements described in this section result from Model 767 airplane certification activities with th

Administration (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 i

describes 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 dam

for all SSIs, and in some cases, fatigue damage detection opportunity until the supplemental inspection threshold is reached. T

inspections listed in this Section 9 “Airworthiness Limitations” are for those SSIs that do not receive adequate fatigue damage d

the initial baseline structural program that is listed in Section 2 and in Appendix K. The inspections shown in this section and Ap

accomplished in conjunction with and not as a substitute for the existing structural maintenance program found in Section 2.

OCT 2012
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The supplemental structural inspection program uses the Damage Tolerance Rating (DTR) system to determine the inspection

necessary 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-DTRTHRESHOLDThe certifying authority (Seattle FAA ACO) requires designation of all SSIs into two categories. These two categories are refer

Type 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 det

and Type 2 categories.The inspections are to be done on the basis of the threshold specified in the AWL – Structural Inspections table and repeat insp

DTR Check Forms contained in Document D622T001-DTR.Initial inspection (threshold) and intervals are measured in flight cycles or flight hours that a particular SSI detail has accumulat

airframe as a whole has accumulated. Most SSI details have never been replaced and therefore have accumulated the same flas the airframe. Some SSI details are replaced, such as when installing Removable Structural Components (repairable/rotable/

used structural parts as a repair. In these cases the SSI details have accumulated flight cycles and flight hours that may be diffe

operator must account for this in determining when inspections must be done.Although intended for repairs, FAA AC 120-93 Appendix 7, provides a method for determining the age of a Removable Structur

be applied to the baseline structure.The Airworthiness Limitations – Structural Inspections table defines the inspection implementation threshold. Some items are s

identified by “FLS” (Flight Length Sensitive) in the Threshold column of the table. FLS Items require both flight hours and flight implementation threshold. Refer to Figure 1, shown on the next page, to determine the threshold for FLS Items.

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

JUN 2010
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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.The information contained in Appendix K has been added to comply with the AD 2003-18-10 requirements when an airplane re

flight hour supplemental inspection threshold (whichever comes first). Appendix K contains the 1995-1999 versions of MPD SeInspection Program, and is the baseline structural inspection program associated with the October 2002 MPD Section 9, AirwoCMRs. AD 2003-18-10 paragraph (c) requires the incorporation of the October 2002 MPD Section 9 or an appropriately approv

When reaching the threshold of 50,000 flight cycles (-200, -200SF1 and -300 Passenger or -300 Passenger converted to -300B

cycles or more as a -300 Passenger) or 40,000 flight cycles (-300F Freighter or -400ER Passenger or -300 Passenger converte

before 10,000 cycles as a -300 Passenger), all C-check (or higher) structural inspection repeat intervals must be no greater thaAppendix K. Structures “S 1C” check interval is defined as 3,000 flight cycles or 18 months (whichever comes first). This means escalated the structures program by changing either task intervals (flight cycles) or the C-check interval (flight cycles), must red

back to the MPD baseline structures program intervals before accumulating 50,000 flight cycles or 40,000 flight cycles respectihours (whichever comes first). The reason for this is that the FAR 25.571 damage tolerance evaluation takes credit for the base

defined in Appendix K. The airworthiness limitations listed in Section 9 are supplemental structural inspections of the SSIs for w

not satisfied by the baseline structural inspections defined in Appendix K. Any continued escalation beyond the MPD baseline sresult in additional structure not meeting the required DTR which was the basis of certification. The inspections shown in Sectio

Limitations are to be accomplished in conjunction with and not as a substitute for the existing structures maintenance program 

767 PASSENGER-TO-FREIGHTER CONVERSION AIRPLANESCertain 767 airplanes are modified from passenger model airplanes to a freighter configuration via Boeing service bulletin. Afte

Boeing 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.

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

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767 MAINTENANCE PLANNING DATA

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.

DEC 2009
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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
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767 MAINTENANCE PLANNING DATA

FIGURE 3. Mod Date Sensitive Structure

DEC 2009
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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 D622T

report form (any suitable alternative which contains the same information may be used).

REMOVAL OF EXCESS SEALANT WHEN INSPECTINGIn areas where DTR Check Form requires sealant removal:• Refer to AMM 51-31-01 for general sealant removal and application.• Refer to AMM 28-11-00 (Task 28-11-00-308-013) for sealant (BMS 5-45) inside the fuel tank removal and application.• Refer to AMM 28-11-00 (Task 28-11-00-308-060) for secondary fuel barrier sealant (BMS 5-81, Type II) outside the fuel tan

on the wing center section.

• If sealant is removed inside the fuel tank for inspection, care must be taken to remove any sealant debris in the fuel tank.Sealant of fuel tank fasteners must comply with MPD Section 9, Parts D and E.

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767 MAINTENANCE PLANNING DATA

The following pages, included in the Airworthiness Limitations – Structural Inspections table, list the Airworthiness Limitation su

requirements. Each item is listed by SSI Number, DTR Check Form Title, Inspection Zone, Airplane/Engine Applicability, Type 

NOTE: There are 767-200SF Fuselage ALIs that do not have corresponding DTR Check Forms. The inspection type a

interval are given in the DTR document.There are 767-200SF and 767-300BCF Wing ALIs that do not have corresponding DTR Check Forms. The inspinspection interval are given in the DTR document.

There are corresponding DTR Check Forms (in Document D622T001-DTR) for each item listed in the table. Where there is mo

given SSI Number, the DTR Check Form Title is the unique identifier along with the Airplane/Engine Applicability. Airplane/engas follows:

ALL = All Airplanes PASS (-ER ONLY) = Passenger Airplanes, Extended Range Only.PASS = Passenger Airplanes < 8 HOURS = Airplanes with cumulative stage length (Flight Hours 200 = 767-200, -200ER less than 8 hours.200SF = 767-200 Special Freighter300 = 767-300, -300ER > 8 HOURS = Airplanes with cumulative stage length (Flight Hours 

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

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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, 200SF, -300, 

-300BCF (aft) and -400 passenger airplanes – Beam #2 @ STA 210.15, section 

between upper access and Vent Door Cutouts

821, 822 200, 200SF

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 200SF

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 200SF

300BCF, 300F

<2>

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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 200SF

300BCF, 300F

<2>

52-30-I07E MDCD Outer Skin Lap Splice – Upper row (upper skin) – Intercostal #5 838 200SF

300BCF, 300F

<2>

52-30-I07F MDCD Outer Skin Lap Splice – Lower row (lower skin) – Intercostal #5 838 200SF

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.DTR Check 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; S-8R, STA 434 to 654+22 (not applicable) and S-2R 654+22 to 654+110 (no inspection). 4) 200SF: S-8R, STA 434 to 676. 5) L/N 1004: BS 1464 to BS 1478, S-8R: Must inspect per SB 767-53-0238.6) L/N 973: Lap S-8R, STA 1555: Must inspect per SB 767-53-0231.7) L/N 1047: Lap S-8L: BS 595 to 610 and S-7L to S-9L centerlines must be inspected with external detailed inspection every 900 flight cycles (after reaching threshold).

220, 230, 250 ALL

Except where noted f

L/N 945, L/N 963, 

L/N 973, L/N 1004, an

L/N 1047

200SF and 300BCF

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

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

Skin Longitudinal Lap Splices – Lower Row – Crown and Upper Lobe, Sections 41, 43 and 46.DTR Check 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-8R, STA 434 to 654+22; S-8L, STA 654+22 to 654+110 (not applicable); S-2R, STA 654+22 to 654+110 (No inspection). 4) 200SF: S-8R, STA 434 to 676 (not applicable). 5) L/N 1004: BS 1464 to BS 1478, S-8R: Must inspect per SB 767-53-0238.6) L/N 973: Lap S-8R: STA 1555: Must inspect per SB 767-53-0231.7) L/N 1047: Lap S-8L: BS 595 to 610 and S-7L to S-9L centerlines must be inspected  with external detailed inspection every 900 flight cycles (after reaching threshold).

220, 230, 250 ALL

Except where noted f

L/N 945, L/N 963, 

L/N 973, L/N 1004,

and L/N 1047

200SF and 300BCF

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

Skin Longitudinal Lap Splices – Upper Row – Bilge and Lower Lobe, Sections 41, 43 and 46.DTR Check 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-26L. Must inspect per SB 767-53-0211. 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).7) 200SF: S-37R, STA 368 to 434 (No inspection). 8) L/N 994: Lap S-26R: STA 1417. Must inspect per SB 767-53-0230.9) L/N 1008: Lap S-26L: BS 303, 325, 347, and 368. Must inspect per SB 767-53- 0240.10) L/N 1019: Lap S-26L: BS 292 to BS 314. Must inspect per SB 767-53-0244.11) L/N 1040: Lap S-26R: Between BS 1560 to BS 1565 and S-25R to S-27R must  be inspected with external detailed visual inspection every 900 flight cycles,  upon reaching threshold.12) L/N 1055: Lap S-26R: Between BS 1456 to BS 1480 and S-25R to S-27R must be inspected with external detailed visual inspection every 900 flight cycles, upon reaching threshold.

100 ALL

Except where noted f

L/N 873, L/N 946, L/N 967, L/N 969, L/N 971, L/N 994,

L/N 1008, L/N 1019

L/N 1040, and 

L/N 1055

200SF and 300BCF

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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

Skin Longitudinal Lap Splices – Lower Row – Bilge and Lower Lobe, Sections 41, 43 and 46.DTR Check 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-26L. Must inspect per SB 767-53-0211. 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. 7) 200SF: STA 434 to 676, S-26L. Must inspect per 53-30-I04D BCF1 at a threshold of 27,900 cycles.8) L/N 994, Lap S-26R: STA 1417. Must inspect per SB 767-53-0230.9) L/N 1019: Lap S-26L: BS 292 to BS 314 Must inspect per SB 767-53-0244.10) L/N 1020: Lap S-36L: BS 770 to BS 784 and S-35 to S-37L centerlines must be inspected with internal detailed inspection every 900 flight cycles (after reaching threshold).11) L/N 1055: Lap S-26R: Between BS 1456 to BS 1480 and S-25R to S-27R must be inspected with external detailed visual inspection every 900 flight cycles, upon reaching threshold.

100 ALL

Except where noted f

L/N 873, L/N 946, L/N 967, L/N 969, L/N 971, L/N 994, 

 L/N 1019, L/N 1020

and L/N 1055

200SF and 300BCF

53-10-I08B53-30-I24B

Frames above S-20 220, 230 ALL Except 200SF, 

300BCF

53-10-I08B53-30-I24B

Frames above S-20, Frame (Fully visible) 220, 230 200SF 

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, Below S-20, Frame (Fully visible) 100 200SF 

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 200SF, 

300BCF

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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

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

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

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ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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>

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 200SF, 300BCF

<4>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

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INSPECTION

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ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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

to RBL 13.65

121 200SF, 300BCF

<4>

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

Fuselage Crown Stringers – BS 654 to BS 1395, S-8L to S-8RDTR 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 where noted fo

L/N 969

and 300BCF

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-I01 SF1 – Crown Skin Doubler – RHS Edge of Crown Skin Doubler at RBL 9 233, 234 200SF

<4>

53-30-I01 SF2 – Crown Skin Doubler – Aft Edge Body STA 742 233, 234 200SF

<4>

53-30-I01 SF3 – Crown Skin Doubler – Stringer at Circumferential Splice 233, 234 200SF

<4>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

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ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

53-30-I01 SF5 – Crown Skin Doubler – At STA 676 Skin Splice, at STR-8L 233, 234 200SF

<4>

53-30-I01 SF6 – Crown Skin Doubler – At VHF Antenna Installation 233, 234 200SF

<4>

53-30-I01 SF8A – Crown Skin Doubler – Skin Lap Splice at STR-2R and STR-8L Inner Skin 233, 234 200SF

<4>

53-30-I01 SF8B – Crown Skin Doubler – Skin Lap Splice at STR-2R and STR-8L Outer Skin 233, 234 200SF

<4>

53-30-I01 SF9 – Section 43 Crown Skin – Aft of Doubler 233, 234 200SF

<4>

53-30-I01 SF10 – Section 43 Crown Stringers – Aft of External Doubler 233, 234 200SF

<4>

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

and 46Note: Applicable to S-8R, STA 434 to 654 + 22.

230 200SF, 300BCF 

53-30-I04A BCF2 Skin Longitudinal Lap Splices Upper Row – Upper Lobe

Note: Applicable to S-8L, STA 654 + 22 to 654 + 110.

230 300BCF 

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

and 46Note: Applicable to S-8L, STA 654 + 22 to 654 + 110.

230 300BCF 

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

and 46Note: Applicable to S-8R, STA 434 to 654 + 22.

230 200SF, 300BCF 

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

L2 PanelDTR 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.Note: -200SF inspection is from BS 434 to BS 676.

100 200SF

300BCF

Except where noted fo

L/N 269

<4>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

53-30-I05 STA 786 Circumferential Splice in the Body Crown 240 200SF 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, 200SF

300BCF, 300F, 

300 PASS, 

Except where noted 

for 300BCF

<3><4>

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, 200SF

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

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

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ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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 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 200SF, 

300BCF

53-30-I24A53-60-I08A

Frames – Above S-20, Frame (Hidden Structure) 230, 240, 250 200SF

<4>

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

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

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

Frames – Above S-20, Frame (Fully visible) 230, 240, 250 200SF 

53-30-I24A BCF 2 – Frames above S-20, Applicable to Areas of Hidden Frame Structure 231, 232 300BCF

<4>

53-30-I24B Frames above S-20, Frame (Hidden Structure) 220, 230 200SF

<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>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

53-30-I24C53-60-I08C

Frames – Below S-20, Frame (Hidden Structure) 100 200SF

<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-I27A

53-50-I0353-60-I03

Fuselage Circumferential Splices in the Body Crown 230, 240, 250 200SF 

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

<4>

53-30-I28 SF1 – Main Deck Cargo Door Cutout – Auxiliary Sill Inner Chord 231 200SF 

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

Upper Main Sill Inner Chord at BS 492

231 200SF

300BCF, 300F

<2>

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

Lower Main Sill Inner Chord at BS 632

231 200SF

300BCF, 300F

<2>

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

FWD Edge Frame Inner Chord at S-5L

233 200SF

300BCF, 300F

<2>

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

and S-16L – Frame Splice

231 200SF

300BCF, 300F

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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

and S-2L

231, 233 200SF

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 200SF

300BCF, 300F

<2>

53-50-I06 SF – Single Emergency Exit Cutout Auxiliary Sill Inner Chord 241, 242 200SF 

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, 200SF 

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

and 883.5

241, 242 200, 200SF 

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

53-50-I06D Single Emergency Exit Cutout – Sill Inner Chord at Frame Intersect at BS 859.5 

and BS 883.5

241, 242 200, 200SF 

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

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

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

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
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, 200SF

300BCF, 300F,

300 PASS

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

LBL 60 and RBL 33 to RBL 60

143, 144 200SF

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

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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

300 PASS

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

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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 200SF

300BCF

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-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 and Lower Sills

122, 154 200SF

PASS

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 200SF

300BCF

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 200SF

PASS

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 200SF

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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 200SF

300BCF

PASS

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

Station 911 to BS 1562

251, 252 200SF

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>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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>

53-80-I01B BS 1582 Pressure Bulkhead – Radial Web Lap Splices - BS 1582 (Fwd Web) 311, 312 ALL

L/N 424 & on

<1>

53-80-I01C BS 1582 Pressure Bulkhead – Radial Web Lap Splices - BS 1582 (Aft Web) 311, 312 ALL

L/N 424 & on

<1>

53-80-I01D BS 1582 Pressure Bulkhead – Circumferential Tear Strap Splices - BS 1582 

(Fwd Tear Strap)

311, 312 ALL

L/N 424 & on

<1>

53-80-I01E BS 1582 Pressure Bulkhead – Circumferential Tear Strap Splices - BS 1582 

(Aft 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 200SF 

53-80-I03 Section 48 – Jackscrew Fitting Lug – Upper Bulkhead at STA 1702 311, 312 300BCF, 300F

PASS

53-80-I13 Section 48 – Pivot Fitting Lug 313, 314 200SF 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

53-80-I13 Section 48 – Pivot Fitting Lug 313, 314 300BCF, 300F

PASS

53-80-I1553-80-I1653-80-I17

BS 1809.5 Bulkhead Outboard ChordDTR Check Form not applicable to -200SF. Must inspect per SB 767-53A0078 Revision 6 or later.

313, 314 ALL

L/N 710 & on

<1>

Except for 200SF

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 

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>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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 

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>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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>

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>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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>

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) 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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>

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

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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 

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>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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>

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>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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>

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 Except 200SF 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

55-10-I09A Horizontal Stabilizer Upper Skin – At BBL 41.5 Side of Body Splice

Note: No DTR Check Form

331, 341 200SF 

55-10-I13A Horizontal Stabilizer Pivot Fitting Lug 331, 341 ALL Except 200SF 

55-10-I13B Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments 331, 341 ALL Except 200SF 

55-10-I13C Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments 331, 341 ALL Except 200SF 55-10-I13D Horizontal Stabilizer Pivot Fitting Lug

Note: No DTR Check Form.

331, 341 200SF 

55-10-I13E Horizontal Stabilizer Pivot Fitting – Upper and Lower Attachments

Note: No DTR Check Form.

331, 341 200SF 

55-10-I14A Horizontal Stabilizer – Jackscrew Fitting Lug 331, 341 ALL Except 200SF 

55-10-I14B Horizontal Stabilizer Jackscrew Fitting – Upper and Lower Attachments 331, 341 ALL Except 200SF 

55-10-I14C Horizontal Stabilizer Jackscrew Fitting Lug

Note: No DTR Check Form.

331, 341 200SF 

55-10-I14D Horizontal Stabilizer Jackscrew Fitting – Upper and Lower Attachments

Note: No DTR Check Form.

331, 341 200SF 

55-10-I31 Horizontal Stabilizer Rear Spar Upper Chord – SOB Hidden Area 331, 341 ALL Except 200SF 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

55-10-I31A Horizontal Stabilizer Rear Spar Upper Chord – SOB Hidden Area

Note: No DTR Check Form.

331, 341 200SF 

55-10-I31B Horizontal Stabilizer Upper Skin

Note: No DTR Check Form.

334, 344 200SF 

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 Wet Bay – Upper and Lower Surfaces, Front and Rear Spar, 

Spanwise Beams and Access Door Cutouts, Lower Surface Beams, Side of Body Ribs, Splices, Lower Surface Access Hole Cutout and Adjacent Stringers, and Drain.Note: No DTR Check Form.

133,134 300BCF 

57-10-I01B Wing Center Section – Upper and Lower Surfaces, Rear Spar, Beams and Access 

Door Cutouts, Lower Surface Beams, Side of Body Ribs, Splices, Lower Surface Access Hole Cutout and Adjacent Stringers, and Drain. Note: No DTR Check Form.

133, 134 200SF 

57-10-I01C.1 Typical Stringer - Wing Center Section - Typical - In Areas of Attach Fasteners 

Between Left and Right WBL 97.9

133, 134 300F 

57-10-I01C.2 Typical Stringer and Skin - Wing Center Section - Lower Surface - Stringers 1, 2 and 5 

at External Beams (BL 9.5 and BL 62)

133, 134,

135, 136

300F 

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

57-10-I02 Splice Stringer and Skin - Wing Center Section at Stringer 6 and 10 133, 134 400E 

57-10-I02A Front Spar Lower Chord and Skin – Wing Center Section at Radius Fillers 133, 134 ALL Except 200SF, 

300BCF

< 8 Hours

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

57-10-I02A Front Spar Lower Chord and Skin – Wing Center Section at Radius Fillers 133, 134 ALL Except 200SF, 

300BCF

> 8 Hour

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

< 8 Hours

<2>

57-10-I02B Front Spar Lower 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 in Areas of Attach 

Fasteners Between Left and Right WBL 97.9.Note: No DTR Check Form.

133, 134 300BCF 

57-10-I02D Wing Center Section – Lower Surface Splice Stringers L-6 and L-10 in Areas of Attach 

Fasteners Between Left and Right WBL 97.9.Note: No DTR Check Form.

133, 134 200SF 

57-10-I03A Rear Spar Lower Chord and Skin - Wing Center Section – Typical - BBL 23.0 to 

Inboard Edge of Terminal Fitting

133, 134 PASS 

(200ER, 300ER)

< 8 Hours

57-10-I03A Rear Spar Lower Chord and Skin - Wing Center Section – Typical - BBL 23.0 to 

Inboard Edge of Terminal Fitting

133, 134 PASS (200ER, 300ER

> 8 Hours

57-10-I03A Rear Spar Lower Chord and Skin - Wing Center Section – Typical - BBL 23.0 to 

Inboard Edge of Terminal Fitting

133, 134 300F 

57-10-I03A Rear Spar Lower Chord and Skin - Wing Center Section - Inboard Edge of Left 

Terminal Fitting to Inboard Edge of Right Terminal Fitting

133, 134 400E

< 8 Hours

57-10-I03A Rear Spar Lower Chord and Skin - Wing Center Section - Inboard Edge of Left 

Terminal Fitting to Inboard Edge of Right Terminal Fitting

133, 134 400E

> 8 Hours

57-10-I03A Rear Spar Lower Chord - Wing Center Section - Typical - BBL 23.0 to Inboard Edge of 

Terminal Fitting.Note: No DTR Check Form.

133, 134 200SF

300BCF

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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 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, 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 

57-10-I03C Rear Spar Lower Chord - Wing Center Section - Hidden Locations - BBL 49.5, 62.05 

and 73.0Note: No DTR Check Form

133, 134 200SF, 300BCF 

57-10-I08 Rear Spar Web - Wing Center Section - Wing BBL 62.0 - 97.9 and LBL 11.0 - RBL 

11.0

133, 134 400E

< 8 Hours

57-10-I08 Rear Spar Web - Wing Center Section - Wing BBL 62.0 - 97.9 and LBL 11.0 - RBL 

11.0

133, 134 400E

> 8 Hours

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

Inboard and Outboard of BBL 97.42

193, 194 ALL Except 200SF, 

300BCF

< 8 Hours

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

Inboard and Outboard of BBL 97.42

193, 194 ALL Except 200SF, 

300BCF

> 8 Hours

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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-I16D 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 200SF 

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 200SF, 

300BCF

< 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 200SF, 

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 97.42Note: No DTR Check Form.

143, 144 300BCF 

57-10-I20B 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 200SF 

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

Front Spar Lower Chord to Stringer 18

193, 194 PASS 

(200ER, 300ER)

300F

< 8 Hours

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

Front Spar Lower Chord to Stringer 18

193, 194 PASS 

(200ER, 300ER)

300F

> 8 Hours

57-10-I24A Underwing Longeron Attachment - Wing Center Section - Hidden Locations - BBL 70 

Longeron from Front Spar Lower Chord to Stringer 18Note: No DTR Check Form.

193, 194 300BCF 

57-10-I24B Underwing Longeron Attachment - Wing Center Section - Hidden Locations - BBL 70 

Longeron from Front Spar Lower Chord to Stringer 18Note: No DTR Check Form.

193, 194 200SF 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
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-I03A Rear Spar Lower Chord and Web - Outboard Wing Structure - Typical Details Between 

Rib 12 and Rib 19

532, 541,551, 561,

 632, 641,

651, 661

400E

< 8 Hours

57-20-I03A Rear Spar Lower Chord and Web - Outboard Wing Structure - Typical Details Between 

Rib 12 and Rib 19

532, 541,551, 561,

 632, 641,

651, 661

400E

> 8 Hours

57-20-I03B Rear Spar Lower Chord and Web - Outboard Wing Structure - Hidden Details at 

External Stiffeners and Fittings Between Rib 12 and Rib 19

532, 541,551, 561,

 632, 641,

651, 661

400E

< 8 Hours

57-20-I03B Rear Spar Lower Chord and Web - Outboard Wing Structure - Hidden Details at 

External Stiffeners and Fittings Between Rib 12 and Rib 19

532, 541,551, 561,

 632, 641,

651, 661

400E

> 8 Hours

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>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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, and All Airplan

Types, L/N 922 and 

later

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

Nacelle Fairing

437, 447533, 633

ALL Except 200SF, 

300BCF, and 400E

< 8 Hours

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

Nacelle Fairing

437, 447533, 633

ALL Except 200SF, 

300BCF, and 400E

> 8 Hours

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

Nacelle Fairing

533, 633 400E

< 8 Hours

57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: L-16 (Dry Bay) 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 ALL Except 200SF, 

300BCF, and 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 200SF, 

300BCF, and 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

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-20-I12C Outboard Wing Lower Surface Typical Stringer

Note: No DTR Check Form.

193, 194437, 447530, 630540, 640533, 633

200SF

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

530, 630531, 631532, 632540, 640541, 641

ALL Except 200SF, 

300BCF

< 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

530, 630531, 631532, 632540, 640541, 641

ALL Except 200SF, 

300BCF

> 8 Hours

57-20-I15B Outboard Wing Lower Surface Splice Stringer – L-10 under Nacelle Fairing 532, 541

632, 641

ALL Except 200SF, 

300BCF

< 8 Hours

57-20-I15B Outboard Wing Lower Surface Splice Stringer – L-10 under Nacelle Fairing 532, 541

632, 641

ALL Except 200SF, 

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, 632533, 633541, 641

ALL Except 200SF, 

300BCF, and 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, 632533, 633541, 641

ALL Except 200SF, 

300BCF, and 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-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

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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

(Seal Pans)

437, 447530, 630

ALL Except 200SF, 

300BCF, and 400E

< 8 Hours

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

(Seal Pans)

437, 447530, 630

ALL Except 200SF, 

300BCF, and 400E

> 8 Hours

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

(Seal Pans)

437, 447530, 630

400E

< 8 Hours

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

(Seal Pans)

437, 447530, 630

400E

> 8 Hours

57-20-I15E Outboard Wing Lower Surface Splice Stringer – L-6 and 10 at Rib 3 530, 630 ALL Except 200SF, 

300BCF

< 8 Hours

57-20-I15E Outboard Wing Lower Surface Splice Stringer – L-6 and 10 at Rib 3 530, 630 ALL Except 200SF, 

300BCF

> 8 Hours

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

Ribs 3, 5, 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, 5, 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

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

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-20-I15J Outboard Wing Lower Surface Splice Stringers

Note: No DTR Check Form.

437, 447530, 630531, 631532, 632533, 633540, 640541, 641

200SF

300BCF

57-20-I15K Outboard Wing Lower Surface Splice Stringers

Note: No DTR Check Form.

437, 447531, 631532, 632541, 641

200SF

300BCF

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

Fairing at Side-Of-Body & Rib 3

531, 631 ALL Except 200SF, 

300BCF

< 8 Hours

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

Fairing at Side-Of-Body & Rib 3

531, 631 ALL Except 200SF, 

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

531, 631 ALL Except 200SF, 

300BCF, and 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

531, 631 ALL Except 200SF, 

300BCF, and 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

531, 631 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

531, 631 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 200SF, 

300BCF, and 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 200SF, 

300BCF, and 400E

> 8 Hours

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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 200SF, 

300BCF, and 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 200SF, 

300BCF, and 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 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 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 200SF, 

300BCF, and 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 200SF, 

300BCF, and 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 200SF, 

300BCF, and 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 200SF, 

300BCF, and 400E

> 8 Hours

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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 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 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 200SF, 

300BCF, and 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 200SF, 

300BCF, and 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

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

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 200SF, 

300BCF, and 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 200SF, 

300BCF, and 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 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 400E

> 8 Hours

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

including Rib 31

540, 640 400E

< 8 Hours

<2>

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

including Rib 31

540, 640 400E

> 8 Hours

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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, 630531, 631532, 632533, 633540, 640541, 641

200SF

300BCF

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

of Terminal Fitting Wing-to- Body Fairing AreaNote: No DTR Check Form.

531, 631 200SF

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 – Outboard Fitting Aft Fastener Row 511, 611 ALL

< 8 Hours

57-20-I27 Skin Tab at R1 Nacelle Attachment – Outboard Fitting Aft Fastener Row 511, 611 ALL

> 8 Hours

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

Trunnion Support, Most Inboard Aft Fastener

530, 630 400E 

57-53-I02A Outboard Flap Supports – Support Ribs (Rear Spar Fittings) in Bathtub Region, Lug 6 

Region Flange

572, 573672, 673

200, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 - 921

<2>

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 - 921

<2>

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 - 921

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

Thread Runout

572, 573672, 673

200, 200SF

300BCF, 300F

300 PASS 

L/Ns 922 and Later 

and 400E

<2>

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 921

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 921

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 921

<2>

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 921

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

672, 673

200, 200SF

300BCF, 300F

300 PASS 

L/N 922 and Later

and 400E

<2>

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 710

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 711 – 921

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later

and 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, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 921

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later 

and 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, 200SF

300BCF, 300F

300 PASS

L/Ns 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, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 921

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

672, 673

ALL

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

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ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 921

<2>

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 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, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 921

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 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, 200SF

300BCF, 300F

300 PASS

L/Ns 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, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-53-I02M.2 Outboard Flap Supports – Outer Pin at Inboard Main Support: Joint 8 572, 672 200, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

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

672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 - 921

57-53-I02M.5 Outboard Flap Pins – Support #1 and #2 – Joint #1 Fuse Pin - Pin Shank @ Outboard 

Rib Support

572, 573672, 673

200, 200SF

300BCF, 300F

300 PASS

L/Ns 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, 200SF

300BCF, 300F

300 PASS

L/Ns 1 - 921

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

300BCF, 300F

300 PASS 

L/N 922 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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

300BCF, 300F

300 PASS

L/Ns 1 – 849

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

300BCF, 300F

300 PASS

L/Ns 850 – 921

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, 200SF

300BCF, 300F

300 PASS

L/N 910 and Later

and 400E

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

Tooth/Rim

555, 655 200, 200SF

300BCF, 300F

300 PASS

L/Ns 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, 200SF

300BCF, 300F

300 PASS

L/N 910 and Later

and 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, 200SF

300BCF, 300F

300 PASS

L/N 910 and Later

and 400E

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

57-53-I03J.2 Inboard Flap Support at #4 – Collar Fitting – Spline Cross-Section 555, 655 200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 909

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

300BCF, 300F

300 PASS

L/Ns 1 – 849

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

300BCF, 300F

300 PASS

L/Ns 850 – 921

57-53-I03L Inboard Flap – #4 Support – Torque Tube – Torque Tube Outer Surface – IFS 92 to 

IFS 124.5

555, 655 200, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 909

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

300BCF, 300F

300 PASS

L/N 910 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

L/N 910 and Later

and 400E

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

Joint 6 Lug

571, 671 200, 200SF

300BCF, 300F

300 PASS 

L/N 922 and Later

and 400E

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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

300BCF, 300F

300 PASS

L/Ns 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, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

L/Ns 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, 200SF

300BCF, 300F

300 PASS

L/N 883 and Later

and 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, 200SF

300BCF, 300F

300 PASS

L/Ns 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, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 882

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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

Tension Link

571, 671 200, 200SF

300BCF, 300F

300 PASS

 L/Ns 1 – 882

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

300BCF, 300F

300 PASS

L/N 883 and Later

and 400E

<2>

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, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 882

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

300BCF, 300F

300 PASS

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, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

L/Ns 1 – 921

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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

300BCF, 300F

300 PASS

L/Ns 1 – 921

<2>

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

300BCF, 300F

300 PASS

L/Ns 1 – 921

<2>

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

300BCF, 300F

300 PASS

L/Ns 1 – 921

<2>

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

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

L/Ns 1 – 921

<2>

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

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

L/Ns 1 – 921

<2>

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, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

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, 200SF

300BCF, 300F

300 PASS

L/Ns 1 – 921

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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

300BCF, 300F

300 PASS

 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, 200SF

300BCF, 300F

300 PASS 

 L/N 922 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

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, 200SF

300BCF, 300F

300 PASS

 L/Ns 1 – 921

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

300BCF, 300F

300 PASS

L/Ns 1 – 921

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

<2>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

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AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

 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, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

 L/Ns 1 – 921

<2>

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>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

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SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

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, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

57-53-I04Y Inboard Flap #4 Support – Flap Support Fitting – Upper Flange Inboard Bolt Location 195, 196 400E 

57-53-I04Y Inboard Flap #4 Support – Side Strut Swivel Support Fitting – Satellite Holes at Lug 6 195, 196 200, 200SF

300BCF, 300F

300 PASS

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, 200SF

300BCF, 300F

300 PASS

L/N 922 and Later

and 400E

<2>

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

300BCF, 300F

300 PASS

L/Ns 1 – 921

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

Note: No DTR Check Form.

552, 652 200SF

300BCF

<4>

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

Note: No DTR Check Form.

552, 652 200SF

300BCF

<4>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

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ENGINE 

APPLICABILITY 

SEP 2013
D622T001-9

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

767 MAINTENANCE PLANNING DATA

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

Note: No DTR Check Form.

552, 652 200SF

300BCF

<4>

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

Stiffeners adjacent to Aft Trunnion BoreNote: No DTR Check Form.

552, 652 200SF

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 200SF

300BCF

<4>

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

Note: No DTR Check Form.

552, 652 200SF

300BCF

<4>

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

Note: No DTR Check Form.

552, 652 200SF

300BCF

<4>

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

Note: No DTR Check Form.

552, 652 200SF

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 200SF

300BCF

<4>

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

Note: No DTR Check Form.

552, 652 200SF

300BCF

<4>

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>

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
767 MAINTENANCE PLANNING DATA

D622T001-9

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

<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, pand 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 revised

manual, and accepted by the FAA.<4> No 767-300BCF and 767-200SF airplane may be operated beyond the stated threshold (operational limit) until the applicable inspection pro

the appropriate manual, and accepted by the FAA.

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

SSI # DTR CHECK FORM TITLE

INSPECTION

ZONE

AIRPLANE/

ENGINE 

APPLICABILITY 

SEP 2013
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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, 767-200SF Nose Landing Gear 80,000 Landings *767-200, 767-200SF Main Landing Gear 70,000 Landings *767-200, 767-200SF Main Landing Gear Support Structure 90,000 Landings ** These values are based on completed fatigue tests and incorporation of the following Service Bulletins on applicable airplanes

SERVICE BULLETIN # DESCRIPTION

LIFE LIMIT (LA

PRIOR TO INCOR

767-32-44 MLG UPPER SPINDLE-DRAG STRUT, PART # 161T6007 9,000

767-32-45 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.

JUN 2010
767 MAINTENANCE PLANNING DATA

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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 *WING MAIN LANDING GEAR BEAM 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.

JUN 2010
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767 MAINTENANCE PLANNING DATA

D. AIRWORTHINESS LIMITATIONS – SYSTEMS

INTRODUCTION

This section of the Airworthiness Limitations contains an FAA approved program of scheduled inspections and design limitation

incorporate 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 de

Paragraph 2(a) of SFAR 88 requires certain design approval holders of Type Certificates (TCs) and Supplemental Type Certific

transport airplanes to conduct a safety review of the fuel tank systems. The purpose of the safety review is to identify design fe

development of ignition sources in the fuel tank systems. Fuel System Airworthiness Limitations (AWLs) are mandatory mainten

accordance 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 a

methods, techniques, and practices as prescribed is required to ensure compliance with the CDCCL. Any use of parts, method

not 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

OCT 2012
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 liSeattle 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. Op

the U.S FAA jurisdiction should obtain interval extension approvals from their local regulatory agency.

MAY 2010
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767 MAINTENANCE PLANNING DATA

REGULATORY AGENCY APPROVALAny deviations from the published AWL instructions included in this document require approval from the Seattle FAA ACO. Th

under 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.PAGE FORMAT: FUEL SYSTEM 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.

OCT 2012
767 MAINTENANCE PLANNING DATA

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D.1 AWLs – FUEL SYSTEM IGNITION PREVENTION

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 Upper PaPerform a detailed inspection of the wire bundles routed over the center main deck floor boards between the front spar and rear spar of the cente

damaged clamps, wire chafing, and that the wire bundle is not in contac

fuel tank. If discrepancies are found, repair per the Boeing Standard WiD6-54446.

28-AWL-02 CDCCL N/A All

External Wires Over Center Fuel TankConcern: Potential for Wire chafing and arcing to Center Fuel Tank UppIf any maintenance is performed in the area under the main deck floor bfuel tank, verify the following:1. Maintain the existing wire bundle routing and clamping.2. Installation of any new wire bundles per the Boeing Standard Wiring 

D6-54446.

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

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 tanthe bulkhead fitting and the spar during a lightning strike event.The following must be maintained if the bulkhead fitting or attached tubin

replaced (refer to Boeing AMM 28-22-07):1. Verify electrical fay surface bond from bulkhead fitting to structure is 

(0.5 milliohms) or less.

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

the tank.

3. Install full bodied fillet seal encapsulating the first coupling interface i

OCT 2012
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767 MAINTENANCE PLANNING DATA

28-AWL-04 CDCCL N/A All

Lightning Protection – Hydraulic Line Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interface 

and the spar during a lightning strike event.Maintain fay surface bond configuration of hydraulic line fuel tank penetrbulkhead fitting and the spar (refer to Boeing AMM 29-11-27). Verify the 

the bulkhead fitting or attached tubing are removed and replaced.1. The resistance between the mating surfaces of the heat exchanger an

is less than 0.001 ohm (1 milliohm).

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

less than 0.005 ohm (5 milliohms).

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

than 0.005 ohm (5 milliohms).

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

(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 interface and the spar during a lightning strike event.Perform the following inspection to ensure functional integrity (refer to B1. Use a bonding meter to do the checks of the bonding resistance in th

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

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

less than 0.005 ohm (5 milliohms).

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

less than 0.005 ohm (5 milliohms).

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

a value of 0.001 ohm (1 milliohm) or less (refer to Boeing SWPM 20-

Interval Note: Whichever comes first.

AWL 

Number Task Interval Applicability Description

MAY 2010
767 MAINTENANCE PLANNING DATA

D622T001-9

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

28-AWL-06 CDCCL N/A All

AC and DC Pump MaintenanceConcern: Potential for maintenance error during pump overhaul. Fuel pu

source prevention means (i.e., flame arrestor, thermal fuses, materials, 

etc.) that must be maintained if pump is overhauled.Repair and overhaul of Fuel Pumps must be per the manufacturer’s ComManual (CMM) Numbers, 28-20-02, Revision Number 12, 28-22-01, RevRevision Number 19, 28-22-03, Revision Number 14, 28-22-11, RevisioRevision Number 18, 28-22-13, Revision Number 11, 28-22-21, RevisioRevision Number 6, 28-22-31, Revision Number 2, 28-22-33, Revision N

of 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 to strElectrical faults internal to the fuel pump motor impeller are by design roimpeller assembly to the bonding straps on the front face of the motor imstructure outside the tank. The bonding straps ensure that fault currents 

outside the tank until the circuit breaker and/or GFI has had time to remoThe following must be maintained during pump replacement (refer to Boand 28-22-05):1. Installation of the two bonding straps between the pump housing (do

clip on structure.

2. Pump housing bonding resistance to structure less than or equal to 0

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

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

0.00035 ohms (0.35 milliohms).

AWL 

Number Task Interval Applicability Description

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D622T001-9

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767 MAINTENANCE PLANNING DATA

28-AWL-08 CDCCL N/A All

Lightning, Fault Current or Hot Short Protection – Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at a conductive interface as a result of electrical fault currents or lightning strike events dwithin the ground electrical path.Addition of any new penetrations to the fuel tanks (such as adding a braequipment) or change to the design features of the existing equipment pmeasuring sticks, sump drain valves, fueling manifold, fuel temperature fuel shutoff valve adaptor plate) requires approval by the Seattle FAA AC

28-AWL-09 CDCCL N/A All

Fuel Quantity Indicating System (FQIS) / Surge Tank Fuel Level Sensing 

Installation Separation Requirement Concern: Potential for hot shorts and EMI induced voltages on the FQIS 

enter the fuel tank.Routing and installation of any new wiring must use wire types BMS 13-

BMS 13-58, and not be within a 2-inch radius of the FQIS wiring. When separation greater than 1⁄2 inch must be maintained from FQIS wiring.

28-AWL-10 CDCCL N/A All

Center Tank Fueling Valve-Fault Current BondConcern: Potential for arcing or filament heating inside the center wing fThe following must be maintained if the system is disturbed (refer to Boeairplanes) and 28-21-12 (767-400 only)):Verify the fay surface bond resistance between the valve body and the rless than or equal to 0.0025 ohms (2.5 milliohms). Verify fillet seal is insand 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 structure on Verify the bonding resistance between the control unit and the rear spar 0.008 ohms.

AWL 

Number Task Interval Applicability Description

MAY 2010
767 MAINTENANCE PLANNING DATA

D622T001-9

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

28-AWL-11 CDCCL N/A All

Fuel Quantity Indicating System (FQIS) – Fuel Quantity Processor Unit 

Concern: Potential for maintenance error during Fuel Quantity Processo

FQPU is designed to limit the levels of energy, voltage, current, and pow

circuit to intrinsically safe levels in order to preclude the potential of an ig

fuel tank.Repair and overhaul of FQPU must be per the manufacturer Componen(CMM) Number, 28-41-68 Revision 4, or a later revision of this CMM thaSeattle FAA ACO.

28-AWL-12 CDCCL N/A All

Fuel Quantity Indicating System (FQIS) – Repair of In-Tank Hardware (Tand Compensators) Concern: Potential for maintenance error during repair of in-tank hardwa

compensators and densitometers). Arc gaps may develop that could reinside the fuel tank.Repair and overhaul of FQIS tank units, compensators, and densitometemanufacturer CMMs.Goodrich Component Maintenance Manual (CMM) Numbers 28-40-56 R28-40-59 Revision Number 4, 28-40-62 Revision Number 3, 28-41-68 Rrevisions of these CMMs that have been approved by the Seattle FAA AHoneywell CMM Numbers 28-41-01 Revision Number 5, 28-41-07 RevisRevision Number 6, 28-41-30 Revision Number 1, 28-41-33 revision numNumber 1, 28-41-35 Revision Number 1, 28-41-36 Revision Number 7, 7, 28-41- 41 Revision Number 5, 28-41-42 Revision Number 0, or later rthat have been approved by the Seattle FAA ACO.

AWL 

Number Task Interval Applicability Description

MAY 2010
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767 MAINTENANCE PLANNING DATA

28-AWL-13 CDCCL N/A All

Fuel Quantity Indicating System (FQIS) – Repair of In-Tank Wire HarnesConcern: Potential for error during repair or replacement of in-tank wire develop that could result in an ignition source inside the fuel tank.Repair and overhaul of FQIS in-tank wire harness must be per Boeing SInstall FQIS in-tank wire harness must be per Boeing AMM 28-41-09. Wbetween the wires and structures must be greater than 0.125 inches.Verify the following when installing the spar FQIS penetration:

1. The mating surface of the tank wiring harness on the front spar is cle2. New O-ring(s) are installed.3. The Jamnuts are tightened to a torque as specified in the Boeing AM4. Sealant is installed per instruction in the Boeing AMM Task 28-41-09

28-AWL-14 CDCCL N/A All

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

door that mates with the wing skin inside the tank,

2. Apply grease to both sides of the knitted aluminum mesh gasket, and3. Install the greased knitted aluminum mesh gasket between the outsid

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

AWL 

Number Task Interval Applicability Description

MAY 2010
767 MAINTENANCE PLANNING DATA

D622T001-9

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

28-AWL-15 CDCCL N/A All

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

28-AWL-16 CDCCL N/A All

Surge Tank Fuel Level Sensing System – Repair of In-Tank Wire HarneConcern: Potential for error during repair or replacement of in-tank wire develop that could result in an ignition source inside the fuel tank.Repair and overhaul Fuel Level Sensor in-tank wire harness per Boeing Install Surge Tank Fuel Level Sensor in-tank wire harness per Boeing A

28-AWL-17 CDCCL N/A All

Resetting Tripped Fuel Pump Circuit BreakersConcern: Potential for arcing or sparking inside the tank between fuel phousings and outside the tank between pump wiring and structure in flamVerify it is safe to reset the circuit breaker(s) by following the applicable 

procedures. Fault(s) that resulted in circuit breaker trip must be isolated to reset.

AWL 

Number Task Interval Applicability Description

MAY 2010
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767 MAINTENANCE PLANNING DATA

28-AWL-18 ALI 12 Yrs All

Fuel Quantity Indicating System (FQIS) – Out Tank Wiring Lightning Sh

Concern: Potential for Lightning induced voltages on the FQIS wiring to 

Perform the following inspection to ensure the functional integrity of the 

ground termination (refer to Boeing AMM 20-55-54):1. Visually inspect all connectors at the location being tested to ensure 

includes connector plugs and backshells.

2. Use a Loop Resistance Tester P/N 906-10246-2 or 906-10246-3 to m

resistance of the shield to ground termination for the following items:

767-200 CINCH Wire Bundle:The loop resistance shall not exceed 44 milliohms for Connector M1947 Wire Bundle S283T025-126.The loop resistance shall not exceed 40 milliohms for Connector M1945 

Wire Bundle S283T025-122.The loop resistance shall not exceed 40 milliohms for Connector M1948 Wire Bundle S283T025-127.The loop resistance shall not exceed 43 milliohms for Connector M1957 

Wire Bundle S283T025-136.The loop resistance shall not exceed 40 milliohms for Connector M1950 

Wire Bundle S283T025-132.The loop resistance shall not exceed 47 milliohms for Connector M1958 Wire Bundle S283T025-137.The loop resistance shall not exceed 40 milliohms for Connector M1952 

Wire Bundle S283T025-135.

(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 Sh(Continued)767-300 CINCH Wire Bundle:The loop resistance shall not exceed 44 milliohms for Connector M1944 Wire Bundle S283T025-121.The loop resistance shall not exceed 40 milliohms for Connector M1945 

Wire Bundle S283T025-122.The loop resistance shall not exceed 40 milliohms for Connector M1946 Wire Bundle S283T025-123.The loop resistance shall not exceed 43 milliohms for Connector M1949 

Wire Bundle S283T025-131.The loop resistance shall not exceed 40 milliohms for Connector M1950 

Wire Bundle S283T025-132.The loop resistance shall not exceed 47 milliohms for Connector M1951 

Wire Bundle S283T025-134.The loop resistance shall not exceed 40 milliohms for Connector M1952 

Wire Bundle S283T025-135.767-300F CINCH Wire Bundle:The loop resistance shall not exceed 44 milliohms for Connector M1944 Wire Bundle S283T025-321 (-971).The loop resistance shall not exceed 40 milliohms for Connector M1945 

Wire Bundle S283T025-122 (-922).The loop resistance shall not exceed 40 milliohms for Connector M1946 Wire Bundle S283T025-323 (-973).The loop resistance shall not exceed 43 milliohms for Connector M1949 

Wire Bundle S283T025-331 (-981).The loop resistance shall not exceed 40 milliohms for Connector M1950 

Wire Bundle S283T025-132 (-932).The loop resistance shall not exceed 47 milliohms for Connector M1951 

Wire Bundle S283T025-334 (-984).

(Continued on next page)

AWL 

Number Task Interval Applicability Description

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767 MAINTENANCE PLANNING DATA

28-AWL-18

(Continued)

Fuel Quantity Indicating System (FQIS) – Out Tank Wiring Lightning Sh(Continued)767-300F CINCH Wire Bundle, continued:The loop resistance shall not exceed 40 milliohms for Connector M1952 

Wire Bundle S283T025-135 (-935).767-200 and 767-300 Boeing Wire Bundle:The loop resistance shall not exceed 121 milliohms for Connector D158Boeing Wire Bundle 286T0446.The loop resistance shall not exceed 284 milliohms for Connector D155Boeing Wire Bundle 286T0446.The loop resistance shall not exceed 150 milliohms for Connector D281Boeing Wire Bundle 286T0454.The loop resistance shall not exceed 175 milliohms for Connector D281Boeing Wire Bundle 286T0454.The loop resistance shall not exceed 122 milliohms for Connector D158Boeing Wire Bundle 286T0448.The loop resistance shall not exceed 284 milliohms for Connector D156Boeing Wire Bundle 286T0448.The loop resistance shall not exceed 152 milliohms for Connector D281

Boeing Wire Bundle 286T0448.The loop resistance shall not exceed 184 milliohms for Connector D281

Boeing Wire Bundle 286T0448.

(Continued on next page)

AWL 

Number Task Interval Applicability Description

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767 MAINTENANCE PLANNING DATA

28-AWL-18

(Continued)

Fuel Quantity Indicating System (FQIS) – Out Tank Wiring Lightning Sh(Continued)767-400ER Wire Bundle:The loop resistance shall not exceed 59 milliohms for Connector M1944 Wire Bundle S283T025-721.The loop resistance shall not exceed 63 milliohms for Connector M1945 

Wire Bundle S283T025-722.The loop resistance shall not exceed 465 milliohms for Connector M194Wire Bundle S283T025-723.The loop resistance shall not exceed 58 milliohms for Connector M1949 

Wire Bundle S283T025-731.The loop resistance shall not exceed 59 milliohms for Connector M1950 

Wire Bundle S283T025-732.The loop resistance shall not exceed 570 milliohms for Connector M195Wire Bundle S283T025-734.The loop resistance shall not exceed 66 milliohms for Connector M1952 

Wire Bundle S283T025-735.If the measured loop resistance value is not within the defined limits, pe

repair in accordance with Boeing AMM 20-55-54.

3. Repair per Boeing AMM if the joint resistance is greater than the max

28-AWL-19 CDCCL N/A All

FQIS – Out Tank Wiring Lightning Shield to Ground TerminationConcern: Potential for Lightning induced voltages on the FQIS wiring to 

If any maintenance is performed on the FQIS wire bundle in the unpressfuselage), 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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767 MAINTENANCE PLANNING DATA

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 for sideveloping at the pump inlet due to either frictional heating or sparking a

contacting the pump rotating elements, rotating elements contacting stabearings due to bearing contamination or failure.The automatic shutoff system is installed and designed to limit continuou

15 seconds.The following test is required in order to protect against latent faults:Functionally check the center tank fuel boost pump automatic shutoff syAMM 28-22-00.Airplane Note: Applicable to airplane with installed and activated auto sh

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 Tan

Concern: Potential for wire to wire hot short voltages on the center tank wiring to enter the fuel tank. This is applicable to airplanes with optional The FQIS HSP is designed to prevent wire to wire external hot short voltank where it may cause an ignition. The following features must be maintained during replacement of the HSAMM 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 straps are 

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

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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 (MOV) A

Concern: Potential for arcing or sparking inside the fuel tank at a condu

structure interface as a result of electrical fault currents event.The following design features must be maintained during actuator, adaprepair, or replacement (refer to Boeing AMMs 28-22-01, 28-22-02, 28-22or 28-26-02):1. Maintain the following if the adapter plate is removed and replaced:

a. Verify electrical fay surface bond resistance between the adapter 

0.0005 ohms (0.5 milliohms) or less.

b. Install fillet seal around the periphery of the adapter plate and the 

c. Wet install and cap seal the four bolts that attach the adapter plat

and fillet seal around the edge of the hole and on the stationary pinside the tank.

d. Install sealed electrical fay surface bond between the serrated m

plate and the adapter plate. Wet install the index plate screws us

e. Install sealed electrical fay surface bond between the mating surf

index plate. Wet install the actuator screws using same sealant.

f. With the bonding jumper not installed, verify electrical bonding re

actuator bond strap attachment point and the spar is 0.0025 ohm

g. Prior to attachment of the bonding jumper to the actuator, verify e

between the loose end of the bonding jumper and the spar is 0.0

or less.

h. Attach the bonding jumper to the actuator bonding tab using a se

bond and verify electrical bonding resistance between the actuat

bonding jumper terminal is 0.001 ohms (1 milliohm) or less.

(Continued on next page)

AWL 

Number Task Interval Applicability Description

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767 MAINTENANCE PLANNING DATA

28-AWL-23

(Continued)

Lightning and Fault Current Protection – Motor Operated Valve (MOV) A2. Maintain the following if the index plate is removed and replaced:

a. Install sealed electrical fay surface bond between the serrated m

plate and the adapter plate. Wet install the index plate screws us

b. Install sealed electrical fay surface bond between the mating surf

index plate. Wet install the actuator screws using same sealant. 

c. With the bonding jumper not installed, verify electrical bonding re

actuator bonding tab and the spar is 0.0025 ohms (2.5 milliohms

d. Prior to attachment of the bonding jumper to the actuator, verify e

between the loose end of the bonding jumper and the spar is 0.0

or less.

e. Attach the bonding jumper to the actuator bonding tab using a se

bond and verify electrical bonding resistance between the actuat

bonding jumper terminal is 0.001 ohms (1 milliohm) or less. 

3. Maintain the following if the MOV actuator is removed and replaced:

a. Install sealed electrical fay surface bond between the mating surf

index plate. Wet install the actuator screws using the same seal

b. With the bonding jumper not installed, verify electrical bonding re

actuator bonding tab and the spar is 0.0025 ohms (2.5 milliohms

c. Prior to attachment of the bonding jumper to the actuator, verify e

between the loose end of the bonding jumper and the spar is 0.0

or less.

d. Attach the bonding jumper to the actuator bonding tab using a se

bond and verify electrical bonding resistance between the actuatbonding 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 condu

structure interface as a result of lightning or electrical fault current event. actuator output shaft is intended to disconnect the output shaft electricalelectrical circuitry and ground path structure.To verify the integrity of the electrical isolation feature, conduct the followCMM 28-20-21:A Dielectric Strength test on the completed actuator assembly shall be p3000 VAC RMS, 60 Hz for one (1) minute between any mounting foot of shaft spline. There shall be no evidence of disruptive discharge in the foexcess of 1.0 milli-amps. The 3000V test is a bench test only and must 

the aircraft.

28-AWL-25 CDCCL N/A 767-400ER airplanes

Surge Tank Fuel Level Sensor – Wiring - Electromagnetic Compatibility Concern: Potential for electromagnetic energy/power being induced on t

into the Fuel Tank.If any maintenance is performed on the surge tank sensor wire bundle focard 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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767 MAINTENANCE PLANNING DATA

28-AWL-26 ALI 12 Yrs 767-400ER airplanes

Surge Tank Fuel Level Sensor – Wiring - Electromagnetic Compatibility Concern: Potential for electromagnetic energy/power being induced on 

into the Fuel Tank.

Perform the following inspection to ensure the functional integrity of the 

wiring shield to ground termination per Boeing AMM 20-55-54:

1. Visually inspect all connectors at the location being tested to ensure 

connector plugs and backshells.

2. Use a Loop Resistance Tester P/N 906-10246-2 or 906-10246-3 to m

resistance of the shield to ground termination for the following items:The loop resistance for the right sensor W882 from D8408P to D6114213.86 milliohms and 251.6 milliohms.The loop resistance for the right sensor W884 from D6114P to D830827.45 milliohms and 32.30 milliohms.The loop resistance for the left sensor W882 from D8038P to D6116J 229.27 milliohms and 269.73 milliohms.The loop resistance for the left sensor W886 from D6116P to D8306 

and 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 Pump 

(GFI) Control Relay SystemConcern: GFI is installed to protect against burn-through of the pump ho

and to protect against overheating of the pump explosion proof cavity antemperature on the outside surface of the conduit, due to electrical arcinPerform an operational test of the Main Fuel Tank Boost Pumps and all Override/Jettison Fuel Pump GFI Control Relays per Boeing AMM 28-22

AWL 

Number Task Interval Applicability Description

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D622T001-9

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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 Uncommanded

Concern: Dry running of the Center Auxiliary Fuel Tank Override/Jettison 

single failure event has the potential to be an ignition source developing either frictional heating or sparking as a result of FOD contacting the pumrotating elements contacting stationary parts, or hot journal bearings due or failure.Perform a Functional Test of the Center Auxiliary Fuel Tank Override/JetUncommanded-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 consource in the fuel tank. The boost pump wires that are in the conduits in the fuel tanks have incoa Teflon sleeve to protect from wire chafing. The wiring also has a shielthat is monitored by the GFI for an additional layer of protection for a puthe conduit.Ensure the following conditions exist when replacing pump wiring or wiriAMM 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 

Number Task Interval Applicability Description

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D622T001-9

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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 Tank

Concern: Potential for the boost pump wiring to chafe and arc in the consource in the fuel tank. The boost pump wires that are in the conduits in 

incorporated two (2) Teflon sleeves to protect from wire chafing (refer to 767-28A0053 R2). The wiring also has a jacket to provide chafing protec

Ensure the following condition exists when replacing pump wiring or wiriAMM 28-22-15):– Jacketed wiring and a Teflon sleeve.

The Teflon sleeve is not repairable. If damaged (chafed), it must be rep

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 

Number Task Interval Applicability Description

MAY 2010
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767 MAINTENANCE PLANNING DATA

D.2 ENGINE FUEL SUCTION FEED SYSTEM

This section contains an FAA approved program of scheduled inspections for operators to incorporate into their maintenance p

to meet Title 14 CFR § 25.951.The 767 Engine Fuel Feed System was type certificated as being compliant to Title 14 CFR § 25.951(b) when performing sucti

Engine Fuel Suction Feed System AWL results from service experience of loss of fuel system suction feed capability due to air 

feed system. The AWL is required maintenance needed to detect and correct failure of the engine fuel feed system to reduce th

flameout resulting from air ingestion into the Engine Fuel Suction Feed System during low fuel level operation with boost pumpThe Engine Fuel Suction Feed System AWL is mandatory maintenance to ensure that the system retains the performance of th

Feed System required by Title 14 CFR § 25.951(b) that arise due to air leaks in the Engine Fuel Suction Feed System do not re

both engines.

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AWLs – ENGINE FUEL SUCTION FEED SYSTEM 

AWL Number Task Interval Applicability Description

28-AWL-101 ALI 7500 FH 

or 3 YRS,

whichever 

occurs first

ALL Engine Fuel Suction Feed Operational Test

An Engine Fuel Suction Feed Operational Test must be accomplished sucindividually. This test is required in order to protect against engine flameo

operations (refer to Boeing AMM 28-22-00):1. Each engine (fuel system) to be tested must meet the following Fuel 

Procedural Limitations listed below:

A. Fuel Tank Quantity – Engine No. 1:

I. The Center Tank Fuel Quantity must be 0 lb. (0 kg).II. The Main Tank No. 1 Fuel Quantity must be between 900 lbs NOTE: Excess fuel can be transferred to Main Tank No. 2.

B. Fuel Tank Quantity – Engine No. 2:

I. The Center Tank Fuel Quantity must be 0 lb. (0 kg).II. The Main Tank No. 2 Fuel Quantity must be between 900 lbs NOTE: Excess fuel can be transferred to Main Tank No. 1.

C. Test Procedural Limitations:

I. The Fuel Cross-Feed Valve must be CLOSED.II. The APU Selector Switch must be OFF.III. The Idle Engine Warm-up time of minimum two minutes with IV. Idle Engine Fuel Suction Feed (Boost Pump OFF) operation 

NOTE: The APU may be used to start the engines, provided th

Procedural Limitations are met.

2. The test is considered a success if engine operation is maintained du

the following engine parameters do not decay relative to those observA. P&W, GE: N1, N2, and Fuel FlowB. RR: N1, N2, N3 and Fuel Flow

3. An Engine Fuel Suction Feed System that fails the operational test m

successfully pass the Engine Fuel Suction Feed Operational Test prio

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767 MAINTENANCE PLANNING DATA

D.3 AWLs – LOW FUEL AND FUEL CONFIGURATION INDICATION TEST

This section contains an FAA approved program of scheduled inspections for operators to incorporate into their maintenance p

to meet Title 14 CFR § 25.901c.The Low Fuel and Fuel Configuration Indication Test AWL limits the exposure to the loss of low fuel quantity or fuel configuratio

failure. The AWL is required maintenance needed to make sure that the Low Fuel and the Fuel Configuration indication are fun

to detect and correct loss of Fuel Configuration indication may result in a loss of fuel use or subsequent delay in the capability t

The Low Fuel & Fuel Config Indication Test AWL is mandatory maintenance action to test correct functionality of the Low Fuel indication to show compliance with Title 14 CFR § 25.901(c) and ensure that a latent failure does not result in a reduction in fuedetect a critical fuel leak.

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AWLs – LOW FUEL AND FUEL CONFIGURATION INDICATION TEST 

AWL Number Task Interval Applicability Description

28-AWL-102 ALI 750 FH

767-200/300/300F 

airplanes,

Line Number 1058 

and on 

(except 1059). 

Fuel Quantity Indicating System (FQIS) – Low Fuel and Fuel Config IndicaConcern: Potential for inability to detect a fuel leak due to the loss of low fu

indication. To ensure proper function, operationally check the following Fuel Alerting I1. With the use of FUEL QTY test switch on the P61 panel, confirm that 

message and FUEL CONFIG light on P5 panel are displayed (refer to 28-41-00).

2. Using one of the following methods, confirm the FUEL CONFIG indica

Boeing AMM Section 28-21-00):A. Configure the airplane with an initial fuel quantity of 3,000 lbs (1,4

an auxiliary (center) fuel quantity of 2,200 lbs (1,000 kg) or morepumps OFF. Confirm that FUEL CONFIG EICAS Advisory messapanel are displayed after three minutes.or

B. Configure the airplane with an initial fuel quantity of 5,500 lbs (2,5

Set a fuel imbalance of 2,600 lbs (1,200 kg) or greater between ththat FUEL CONFIG EICAS Advisory message and FUEL CONFIafter three minutes.

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D.4 AWLs – NITROGEN GENERATION SYSTEM (NGS)

The following list of AWLs (ALIs and CDCCLs) contains FAA approved scheduled inspections for operators to incorporate into for this type design to meet the requirements for the introduction of the Flammability Reduction Means (FRM) Nitrogen GeneraFAA operational rule change E8-16084 Final Flammability Rule requires maintenance instructions and control limitations for ceconfigurations. § 25.981(d) also requires AWLs to preclude ignition sources inside the fuel tank that may be introduced by the aE8-16084, Final Flammability Rule, Paragraph III(F), Section 7, Identification of Airworthiness Limitations: Paragraph M25.4(a) 

to comply with Paragraph M25.1, AWLs must be identified for all maintenance or inspection tasks required to identify failures of 

FRM that are needed to meet Paragraph M25.1. NGS AWLs are mandatory maintenance actions that ensure that unsafe cond

failures do not occur or are not introduced into the airplane as a result of configuration changes, repairs, alterations, or deficienMaintenance Program throughout the operational life of the airplane.

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AWLs – NITROGEN GENERATION SYSTEM

AWL 

Number Task Interval Applicability Description

47-AWL-01 CDCCL N/A 767 airplane 

Line Numbers 993 

and on or airplanes 

that have 

incorporated 

Service Bulletin 

767-47-0001

Lightning Protection – NGS Nitrogen Enriched Air (NEA) Distribution Line Fuel TaConcern: Potential for arcing or sparking inside the tank at the interface between tduring a lightning strike event. The following must be maintained if the bulkhead fitting or attached tubing are remreinstalled (refer to Boeing AMM 47-21-05):1. Install the same part number bulkhead fitting,2. Verify electrical fay surface bond from the bulkhead fitting to the front spar st

0.0005 ohms (0.5 milliohms) or less,

3. Install full-bodied fillet seal encapsulating the bulkhead fitting and jam nut ou4. Install full-bodied fillet seal between the cast-in hex feature of the bulkhead f

inside of the tank,

5. Install full-bodied fillet seal between the B-nut and tube, and between the B-n

the first mating tube inside of the tank, and

6. Verify electrical bond from structure to first tube mating with the bulkhead fitt

NOTE: The bulkhead fitting is a special part which has an integral flame arresto

require approval by the Seattle FAA ACO.

47-AWL-02 CDCCL N/A 767 airplane

Line Numbers 993 

and on or airplanes 

that have 

incorporated 

Service Bulletin 

767-47-0001

Lightning Protection – NGS NEA Distribution Line Fuel Tank PenetrationConcern: Potential for arcing, sparking of filament heating inside the tank at the in

isolator hose and the NEA tubing during a lightning strike event. The NGS installation is designed to prevent lighting currents from entering the cedielectric isolator hose in the forward leading edge fairing area NEA distribution limaintained if the dielectric isolator hose or attached tubing are removed and repl47-00-00 and 47-21-00).

JAN 2013
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47-AWL-03 CDCCL N/A 767 airplane 

Line Numbers 993 

and on or airplanes 

that have 

incorporated 

Service Bulletin 

767-47-0001

Nitrogen Generation System (NGS) – Flammability Exposure and PerformanceConcern: Airplane alterations may impact the performance of the NGS and hence Wing Fuel Tank.Background: The NGS is designed to provide the proper level of nitrogen to the reduce the flammability exposure by reducing the oxygen content of the ullage. Talso affected by the temperature of the fuel. The following are critical features of 

negatively affect the performance of the NGS which in turn may increase the cen

exposure beyond the limits of 14 Code of Federal Regulations, Section 25.981 at 

the equivalent level of safety finding described in FAA Memorandum PS05-0177-1. Transferring air (20.9% oxygen) to the center fuel tank will dilute the nitrogen 

by the NGS in the fuel tank. Some Auxiliary Fuel Tank installations transfer as part of venting and fuel transfer. 

2. NGS performance depends on bleed air pressure in the bleed air cross-over 

the engines.

3. Certification of the NGS depends on the inherent flammability of the center f

installed. Center tank flammability is a direct function of fuel tank temperatuaround the tank, heat sources introduced into the tank (such as warm fuel or changes that would cause heat to be retained (such installation of blankets ad

affect fuel tank flammability in a negative manner.

CDCCL: Any design change that affects the vent system by adding air to the cenpressure in the cross-over manifold during any phase of flight or ground operatio

center wing fuel tank or increases heat retention of the center wing fuel tank is no

approved analysis to show that the change, or combination of changes, does not athe requirements of 14 CFR Section 25.981(b), Amendment 25-125 utilizing the edescribed in FAA Memorandum PS05-0177-P-2.See Boeing AMM Chapter 28 for a description of the Fuel System. See Boeing Adescription of the NGS.

AWL 

Number Task Interval Applicability Description

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47-AWL-04 ALI NOTE ALL

NOTE

Nitrogen Generation System – NEA Distribution Ducting InspectionConcern: The NEA Distribution System ducting outside the fuel tank may fail, late

without reaching the fuel tank, resulting in the fuel tank not reaching required inerInspect the NEA distribution lines from the Air Separation Unit (ASU) to the fuel taleaks (refer to Boeing AMM 47-21-00).INTERVAL NOTE:1. 2600 FH

A. All 767-400ERB. 767-200/300/300F Airplanes, Line Numbers (L/Ns) 993 to 1004 that hav

SB 767-47-0002.

C. Airplanes that have incorporated SB 767-47-0001 R0.

2. 6600 FH

A. 767-200/300/300F Airplanes, L/Ns 1 to 992, that have incorporated SB 7B. 767-200/300/300F Airplanes, L/Ns 993 to 1004, that have incorporated C. 767-200/300/300F Airplanes, L/N 1005 and on.

APPLICABILITY NOTE: If NGS is installed.

AWL 

Number Task Interval Applicability Description

JAN 2013
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47-AWL-05 ALI NOTE ALL

NOTE

Nitrogen Generation System – Cross-Vent Check Valve – Operational CheckConcern: The cross-vent check valve may fail open, latently allowing air to flow t

the nitrogen rich environment created by the Nitrogen Generation System.Operationally Check the cross-vent check valve by accessing left wing surge tank operation of the cross-vent check valve (refer to Boeing AMM 47-21-03).INTERVAL NOTE:1. 2600 FH

A. All 767-400ER.B. 767-200/300/300F Airplanes, L/Ns 993 to 1004 that have not incorporat

C. Airplanes that have incorporated SB 767-47-0001 R0.

2. 4391 FH

A. 767-200/300/300F Airplanes, L/Ns 1 to 992 that have incorporated SB 7B. 767-200/300/300F Airplanes, L/Ns 993 to 1004 that have incorporated S

C. 767-200/300/300F Airplanes, L/N 1005 and on.

APPLICABILITY NOTE: If NGS is installed.

47-AWL-06 CDCCL N/A 767 airplane 

Line Numbers 993 

and on or airplanes 

that have 

incorporated 

Service Bulletin 

767-47-0001

Industry Fleet Average Flammability ExposureConcern: NGS performance is dependent on industry descent times. Industry efforesult in NGS performance that does not meet FAA requirements.Fleet Average flammability exposure for the fuel tanks with flammability reduction 

maintained in accordance with 14 CFR Part 25, Appendix M. Boeing will monitor 

necessary to maintain compliance, will publish service information. If Boeing pub

this CDCCL requires either that operators implement these FAA approved design implement other design changes or operational procedural changes approved by maintain compliance with 14 CFR Part 25, Appendix M.NOTE: This CDCCL does not require individual operators to monitor descent ratemonitor U.S. descent statistics and provide any needed service instructions to opflammability exposure above permissible levels, this CDCCL requires operators t

published service instructions denoted to maintain compliance with this CDCCL, within the compliance times stated in the service instructions.

AWL 

Number Task Interval Applicability Description

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D.5 IMPACT-RESISTANT FUEL TANK ACCESS DOORS

INTRODUCTION

The 767 Fuel Tank Access Doors are compliant with FAA Title 14 CFR § 25.963. Specifically, the 767 Impact-Resistant Access § 25.963(e)(1), which requires that all covers located in an area where experience or analysis indicates a strike is likely must be 

to minimize penetration and deformation by tire fragments, low energy engine debris, or other likely debris. Airplane Line Numwith impact-resistant access doors via Service Bulletin 767-28A0019. This service bulletin also required that the impact-resista

“IMPACT-RESISTANT DOOR”. Additionally, the adjacent lower wing surface is stenciled “CAUTION: INSTALL ONLY IMPAC

THIS LOCATION”. Airplane Line Numbers 235 and on were delivered with impact-resistant access doors and stenciling.

Boeing chose to use a CDCCL for the Airworthiness Limitation of the Impact-Resistant Fuel Tank Access Doors. CDCCLs are 

understood by operators to define a design feature that must be maintained throughout the life of the airplane.

AUG 2013
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AWLs – IMPACT-RESISTANT FUEL TANK ACCESS DOOR

AWL Number Task Interval Applicability Description

57-AWL-01 CDCCL N/A ALL Impact-Resistant Fuel Tank Access Doors

Concern: A potential exists for non-impact-resistant doors to be installed 

resistant doors. A high energy impact on a non-impact-resistant fuel tank leak, and in the presence of an ignition source, may result in a catastrophImmediately prior to the installation of each of the Fuel Tank Access Door 

532EB, 632EB, 532FB, 632FB, 531BB, 631BB, perform the following:1. Verify that the fuel tank access door is impact-resistant. Impact-resis

flat and a smooth inner surface. Doors with rounded ends and visible 

the inner surface are not impact-resistant (refer to Boeing AMMs 28-1

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E. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)

Maintenance requirements arising from aircraft certification activities are described in FAR 25.1309 and AC 25.1309. Independ

process, 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" syst

expected 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.

OCT 2012
767 MAINTENANCE PLANNING DATA

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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

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 id

appropriate ATA Chapter-Section-Subject in the Boeing Maintenance Manual (MM) that deals generally with the t

the task is provided, a seventh digit indicates the first digit of the page block where it can be found in the MM. Alph

digit differentiate between multiple tasks in the same page block. When information specific to the task is not prov

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 maintaininAny act of consumable replenishment for the purpose of maintaininA visual failure finding task to determine if an item is fulfilling its intquantitative tolerances.A failure finding task to determine if an item is fulfilling its intended quantitative tolerances.An examination of an item against a specific standard. This is a poA quantitative check to determine if one or more functions of an iteThis is a potential failure finding task.Reworking, replacement of parts or cleaning necessary to return aThe 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 tw

task, the top interval is the threshold and the bottom one is the repeat interval. A "NOTE" is used to indicate that a

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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767 MAINTENANCE PLANNING DATA

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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

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.

COLUMN EXPLANATION

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767 MAINTENANCE PLANNING DATA

CMR TASKS

MPD

ITEM

NUMBER TASK

CMR 

INTERVAL ZONE ACCESS

APPLICABILITY

767

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTIO

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 OutboarCMR). 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 Overr

Airplane Note: Applicable only to A/C with deactivated 

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 shoueach)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 pro

Airplane 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 fthe 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 Deployme

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 DESCRIPTIO

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767 MAINTENANCE PLANNING DATA

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 inSB equivalent).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 o

SB 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 DESCRIPTIO

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767 MAINTENANCE PLANNING DATA

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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

D77-41-00-5A 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 Se

Fuel Control.

G73-21-07-5A OP 04000 HRS 211

411

416AR ALL 80A Verify proper EEC detection of a fault in the Fail-Fixed 

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 actua

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 actua

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 Categor

Airplane Note: Airplanes with Full Authority Electronic 

MPD

ITEM

NUMBER TASK

CMR 

INTERVAL ZONE ACCESS

APPLICABILITY

767

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTIO

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767 MAINTENANCE PLANNING DATA

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 foAccess Note: The Thrust Reverser Sleeve must be pa

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 foAccess Note: The Thrust Reverser Sleeve must be pa

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).

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 

MPD

ITEM

NUMBER TASK

CMR 

INTERVAL ZONE ACCESS

APPLICABILITY

767

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTIO

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767 MAINTENANCE PLANNING DATA

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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

P77-41-00-5A OP 00400 HRS 211 ALL 7R4 Check operation of Standby Engine Indicator by actua

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 DESCRIPTIO

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767 MAINTENANCE PLANNING DATA

F. 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, m

aircraft, system, component, or powerplant that occurs or is detected at any time if, in its opinion, that failure, malfunction, or de

may 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 enda

includes 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 prese

maintained 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 m

phrases:• “thrust control”• “no response to thrust lever”• “auto-acceleration”• “uncontrolled high thrust”

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767 MAINTENANCE PLANNING DATA

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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 respon

125.409, 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
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767 MAINTENANCE PLANNING DATA

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