# THIS PAGE INTENTIO NALLY LEFT BLANK767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-1767MAINTENANCE PLANNING DATA (MPD) DOCUMENTSECTION 9AIRWORTHINESS LIMITATIONS (AWLs) ANDCERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)D622T001-9SEPTEMBER 2013COMPILED AND PUBLISHED BY:MAINTENANCE PROGRAMS ENGINEERINGCOMMERCIAL AVIATION SERVICESBOEING COMMERCIAL AIRPLANE GROUPSEATTLE, WASHINGTONSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-2767 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3TABLE OF CONTENTSREVISIONS .................................................................................................................................................................................................................................. 9.0-5LIST OF EFFECTIVE PAGES .................................................................................................................................................................................................... 9.0-23A. SCOPE................................................................................................................................................................................................................................... 9.0-24B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS..................................................................................................................................... 9.0-24C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFEPARTS .............................................................................................................................. 9.0-90D. AIRWORTHINESS LIMITATIONS – SYSTEMS..................................................................................................................................................................... 9.0-92D.1 AWLS – FUEL SYSTEM IGNITIONPREVENTION......................................................................................................................................................... 9.0-95D.2 ENGINE FUEL SUCTION FEEDSYSTEM.....................................................................................................................................................................9.0-113D.3 AWLS – LOW FUEL AND FUEL CONFIGURATION INDICATION TEST ......................................................................................................................9.0-115D.4 AWLS – NITROGEN GENERATION SYSTEM (NGS)....................................................................................................................................................9.0-117D.5 IMPACT-RESISTANT FUEL TANK ACCESS DOORS .................................................................................................................................................. 9.0-122E. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRS)........................................................................................................................................... 9.0-124F. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS..................................................................................................................... 9.0-134SEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4767 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5REVISIONSREVISION AND REVISION DESCRIPTION APPROVALMAY 1990 – Original ReleaseAlthough this information was previously issuedas Revision "B" to Section 9 of the MPD,this issue is considered the original release because it is now assigned a new documentnumber (D622T001-9).Prepared by:M. H. LAEDER (Boeing)4/9/90Supervised by:S. J. BRADBURY(Boeing)4/9/90Approved by:S. R. MILLER forD. L. RIGGIN (FAA)5/4/90FEBRUARY 1993Revision to the Maintenance Planning Data Document, including Section 9, "AirworthinessLimitations and Certification Maintenance Requirements."Prepared by:K. L. UTTERBACK (Boeing)2/19/93Supervised by:S. J. BRADBURY(Boeing)2/19/93Approved by:S. R. MILLER (FAA)2/19/93MAY 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)4/14/95Supervised by:S. R. WILLIFORD(Boeing)4/14/95Approved by:D.E. GONLER forD. L. RIGGIN (FAA)6/2/95OCTOBER 1995Added paragraph C, "Structural Inspections –Model 767-300 Package Freighter only." Thisparagraph outlines the requirements for the 50Series inspections for the newly certifiedModel 767-300 Package Freighter airplane.Prepared by:W. F. LINDHOLM (Boeing)10/5/95Supervised by:S. R. WILLIFORD(Boeing)10/5/95Approved by:D. L. RIGGIN (FAA)10/10/95SEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6767 MAINTENANCE PLANNING DATAFEBRUARY 1996Revised CMRs H77-35-00-2B and N77-35-00-2Bto increase CMR interval from 500 HRS to1000 HRS.Prepared by:R. C. MOORE (Boeing)2/15/96Supervised by:S. R. WILLIFORD(Boeing)2/15/96Approved by:D. L. RIGGIN (FAA)12/4/96JUNE 1997Revised Airworthiness Limitations section to reflect the reassessment of the"50-Series" Supplemental Structural Inspection Program. Previous Sections B and C havebeen merged into a new section B and remaining sections have been renumbered.Submitted by:S. WILLIFORD (Boeing)6/26/97Approved by:D. L. RIGGIN (FAA)7/25/97AUGUST 1997Revised CMRs D77-35-00-2B and H77-35-00-2B from 500 HRS to 560 HRS and 1000 HRSto 2000 HRS respectively. Reworded CMR H77-35-00-2B.Submitted by:S. WILLIFORD (Boeing)8/6/97Approved by:D. L. RIGGIN (FAA)11/17/97REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7JUNE 2000Revised Airworthiness Limitations (AWL) section to include limitations for 767-400ER andrevised Airplane Applicability for current AWLs. Revised current AWL title to moreaccurately reflect inspection areas. Revised AWL for Strut to reflect reassessment of thedamage tolerance ratings.Revised interval for CMRs 24-33-00-6A and 26-10-00-6A from DAILY to 48 HRS. AddedCMR 27-51-00-5I applicable only to the 767-400ER airplane. Added CMR H78-34-00-5Aapplicable to airplanes with GE CF6-80C2 engines.Revised CMR 29-11-00-6F by adding a note to indicate the hydraulic system internalleakage limits. Revised airplane applicability for CMRs 27-51-00-5D and H77-00-00-6D.Revised effectivity for CMR 31-41-02-4A sinceit is not applicable to the 767-400ER. AddedAWLs for Fuselage to reflect reassessment ofdamage tolerance rating due to recent testand fleet performance data.Submitted by:N. HENNIGS (Boeing)7/6/00Approved by:A. BAHRAMI (FAA)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 tothe 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 byadding an airplane note applicable to the 767-200/300 airplanes only. Revised statement inpreamble to airworthiness limitations that specifies roll back of any escalated baselinestructural 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)4/18/01Approved by:L. LIU-NELSON (FAA)SEPTEMBER 2002Added CMR 52-51-07-4A applicable only to airplanes incorporating Boeing Service Bulletin767-25-0325. This amended typecertificate complies with the new 14 CFR 25.795 and theamended 14 CFR 25.772 as issued under Federal Register Docket No. FAA-2001-11032.Submitted by:LINH Q. VU (Boeing)8/30/02Approved by:L. LIU-NELSON (FAA)REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8767 MAINTENANCE PLANNING DATAOCTOBER 2002Revised CMR 52-51-07-4A to change applicability to show airplane Line Number 895 andon and any airplane that has incorporated Service Bulletin 767-25-0325 or 767-25-0327 or767-25-0332.Revised the Structural Safe Life Parts section to reference current Service Letter 767-SL-32-092 in place of superseded ServiceLetters 767-SL-32-21 and 767-SL-32-37.Submitted by:LINH Q. VU (Boeing)10/15/02Approved by:L. LIU-NELSON (FAA)AUGUST 2004Revised Airworthiness Limitations (AWL) Section 9 to add FAA Letter 120S-03-953 and 6page enclosure as an AMOC for AD 2003-18-10 in lieu of superseded AD 2001-08-28 andFAA 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 defineadditional Life Limit components for the 767-400ER.Submitted by:S. A. PIERINI (Boeing)8/15/04Approved 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 inSection 6.Submitted by:B. McLoughlin (Boeing)Approved by:Dorr AndersonREVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9MARCH 2006Added new Fuel System Airworthiness Limitations section which includes inspections of theAuto Shutoff and Ground FaultInterrupter systems, and designlimitations of the Hot ShortProtector and motor operated valves.Submitted by:S. Pierini (Boeing)Approved by:Dorr Anderson (Seattle FAA ACO):OCTOBER 2006Revised CMR Task 52-51-07-4A interval from4 years to 6 years to reflect improvedreliability data for the Flight Deck Door Strike Assembly.Submitted by:S. Pierini (Boeing)Approved by:Seattle FAA ACO:JANUARY 2007Revised Airworthiness Limitations – Systemssection introduction to include revisionsrecommended by the Seattle FAA Flight Standards group.Revised applicability of Fuel System Airworthiness Limitation Numbers 28-AWL-23 and28-AWL-24 to remove ITT actuator part numberreference. The part number is listed inService Bulletin 767-28A0090.Submitted by:S. Pierini (Boeing)Approved by:Dorr Anderson (Seattle FAA ACO):REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-10767 MAINTENANCE PLANNING DATAOCTOBER 2007Revised Section D. Airworthiness Limitations (AWLs) – Systems paragraph on ExceptionalShort-Term Extensions for AWLs toclarify notification requirements.Revised Systems AWL Page Format paragraph tobecome Section E.Page Format: FuelSystems Airworthiness Limitations, and relettered the Sections following Section E.Added AWL Number 28-AWL-27, a yearly check ofthe Main and Center Auxiliary Fuel TankBoost Pump Ground Fault Interruption (GFI) Control Relay System, applicable to airplaneLine Numbers 961 and on and airplanes thathave incorporated Service Bulletin 767-28A0085.Added AWL Number 28-AWL-28, a yearly check ofthe Center Auxiliary Fuel Tank Override/Jettison Fuel Pump Uncommanded-On System, applicable to airplane Line Numbers 961and 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 improvedreliability data for the Flight Deck Security Door.Added Section I. Reporting Uncontrolled High Thrust Failure Conditions per FAR 121.703and FAR 135.415.Submitted by:(Boeing)Approved by:Dorr Anderson (Seattle FAA ACO):MARCH 2008Revised 28-AWL-01and 28-AWL-26 by removing the 36000FH task interval limitation basedupon engineering review and operator maintenance practice.Revised 28-AWL-18 to reflect the new maximum loop resistance values associated with thelightning protection of the unpressurized FQIS wire bundle installations so as to satisfy theAirworthiness Limitation Instructions required by SFAR 88. Also removed the jointresistance values and 36000FH task interval limitation based upon engineering review andoperator maintenance practice.Submitted by: John Sabolchy(Boeing)Approved by:Dorr Anderson (Seattle FAA ACO):REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-11APRIL 2008Revised 28-AWL-06 to add additional Component Maintenance Manual (CMM) information.Submitted by: Jason Onorati(Boeing)Approved by: Philip Forde (Seattle FAA ACO):MAY 2008Revised B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS to addrestrictions on flight hours and flight cycles for 767-200SF and 76-300BCF to comply withFAA Title 14 CFR Part 26.Revised C. AIRWORTHINESS LIMITATIONS– STRUCTURAL SAFE LIFE PARTS to limit767-200SF Nose Landing Gear, Main Landing Gear and Landing Gear Support Structure to1,000 flight cycles.Revised C. AIRWORTHINESS LIMITATIONS– STRUCTURAL SAFE LIFE PARTS to limit767-300BCF Nose Landing Gear, Main LandingGear and Landing GearSupport Structureto 2,000 flight cycles.Submitted by: John Sabolchy(Boeing)Approved by: Philip Forde (Seattle FAA ACO):JUNE 2008Revised airplane applicability table to add the 767-300BCF.Added CMRs 31-51-00-5B and 31-51-00-5C that are applicableto 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: Dorr Anderson(Seattle FAA ACO):REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12767 MAINTENANCE PLANNING DATAJUNE 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 Bulletin767-53-0210.Submitted by: Mike Eckelberry(Boeing)Approved by: Dorr Anderson(Seattle FAA ACO):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 additionalinspection threshold and interval for aircraft L/N 971.Revised text to refer to correct Flight Standards Handbook.Submitted by: Jason Onorati(Boeing)Approved by: Dorr Anderson(Seattle FAA ACO):SEPTEMBER 2008Revised airplane applicability table to add the 767-200SFRevised CMRs 31-51-00-5B and 31-51-00-5C toadd 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: Dorr Anderson(Seattle FAA ACO):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 revisedinspection method and new inspection threshold of37,500 cycles due to structural repair forL/N 973.Submitted by: John Sabolchy(Boeing)Approved by: Seattle FAA ACOREVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-13JANUARY 2009Revised Section B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS byremoving the 900 flight cycle or 2,700 flight hour restrictions for the 767-300BCF, tocomply with FAA Title 14 CFR Part 26.Submitted by: John Sabolchy(Boeing)Approved by: Jeffrey Duven, Seattle FAA ACOMARCH 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: Jeffrey Duven, Seattle FAA ACOMAY 2009Revised B. AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONS to clarifyeffectivity on passenger to freighter conversion in accordance with FAA Title 14 CFRPart 26.Revised Airworthiness Limitations-Structural Inspection Table by adding airplane effectivitiesand 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 highlightoperational limits for certain applicable SSIs.Revised SSI 53-50-I11 by updating applicability column from "200" to "ALL" to reflectrequirements 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 toapplicability 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 taskrequirements.(Continued on next page)Submitted by: John Sabolchy(Boeing)Approved by: Jeffrey Duven, Seattle FAA ACOSIGNATURE ON FILE07/09/2009REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-14767 MAINTENANCE PLANNING DATAMAY 2009, ContinuedRevised SSI 54-50-I13 by adding additional rowsto clarify engine effectivity and to reflectthe DTR document (D622T001-DTR).Revised 57-20-I16A to change applicability from “400E” to “ALL” to reflect the correctairplane model.Revised text to refer to Document D622T001-DTR rather than Appendix B.Revised Airworthiness Limitations to include new cargo door limitations. One new cargodoor limitation is applicable to passenger airplanes, eight are applicable to freighterairplanes, and three are applicable to all airplanes.Revised and added new Trailing Edge Flap limitations (Flap Loss Mitigation Program) andadded wording regarding the tracking of removable parts. Forty revised Trailing Edge Flaplimitations are applicable to 767-200, -300passenger and -300 freighter airplanes, LineNumbers 922 and later, except as noted, and are applicable to all 767-400ER airplanes.Forty-nine new Trailing Edge Flap limitationsare applicable to the 767-200, -300 passengerand -300 freighter airplanes, Line Numbers 1to 921, except as noted. Added airplaneeffectivity note to the AIRPLANE ENGINE APPLICABILITY column of both entries forAirworthiness Limitation 53-10-I21A.Revised CMR section by correcting typographical errors by changing CMR D77-41-01-4A toCMR D77-41-00-5A and CMR P77-00-00-6B to CMR P77-41-00-5A.(Continued from previous page)(Continued from previous page)DECEMBER 2009Revised the Airworthiness Limitations section to reflect the assessment of the 767-300Boeing Converted Freighter's (BCF) Supplemental Structural Inspection Program.Revised 767-400 ER Landing Gear Safe Life Inner and Outer Cylinder landings by updatingtext from "16,6000" to "16,600".Revised the 767 Passenger- to-Freighter Conversion Airplane paragraph by removing theflight cycle and flight hour limitations for the 767-300BCF.Submitted by: John Sabolchy(Boeing)Approved by: Jeffrey Duven, Seattle FAA ACOSIGNATURE ON FILE01/04/2010REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-15MAY 2010Revised theAirworthiness Limitations – Systeminformation in Section D, Fuel SystemsAirworthiness Limitations as requested by FAA Letter 140S-09-396 datedNovember 23, 2009.Revised theUse of Alternate Toolsparagraph as requested by FAA Letter 140S-09-396dated November 23, 2009 and as discussedin the FAA meeting on February 11, 2010.Revised the Fuel Systems Airworthiness Limitations Table by replacing the word “per” withthe words “Refer to”, where the reference isto a non-FAA approved manual (such as theStandard Wiring Practices Manual or the Airplane Maintenance Manual) and where thereare 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 bondingstraps.Added 28-AWL-29 and 28-AWL-30 as CriticalDesign Configuration Control Items for thefuel boost pump conduit liner to preclude arcing development as a result of the wireinsulation chafing inside the fuel tank wire conduits.Submitted by: John Sabolchy(Boeing)Approved by: Robert Breneman forJeffrey Duven, Seattle FAA ACOSIGNATURE ON FILE05/27/2010REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-16767 MAINTENANCE PLANNING DATAJUNE 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 referenceto 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 referenceto SB 767-53-0211. For both L/Ns 969 and971, the 37,500 cycle reduced threshold for thetasks 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 the3,750 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 767-200SFSupplemental Structural Inspection Program.Certain Structural Significant Items (SSIs)include a flag note to indicate an operational limitation – no 767-300BCF and 767-200SFairplane may be operated beyond the SSI threshold until the applicable inspectionprocedures 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 Landingsfor the “767-200SF Nose Landing Gear, Main Landing Gear and Gear Support Structure”and replacing it with thecalculated Safe-Life Limit.Revised Structural Safe Life Parts by adding the following text“WING MAIN LANDINGGEAR 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 thethresholds 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: Robert Breneman forJeffrey Duven, Seattle FAA ACOSIGNATURE ON FILE07/09/2010JULY 2010Added new Section F., Airworthiness Limitations – Nitrogen Generation System Tasks.Submitted by: John Sabolchy(Boeing)Approved by: Ron Landes forRobert Breneman, Seattle FAA ACOSIGNATURE ON FILE07/26/2010REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-17AUGUST 2010Revised 47-AWL-04 by updating the intervalfrom 6,600 Flight Hours (FH) to 3,000 FHbased on updated analysis.Revised 47-AWL-05 by updating the interval from 5,000 FH to 3,000 FH based uponupdated analysis. Revised the Task Description by replacing “Functionally” with“Operationally” to accurately reflect the inspection intent.Submitted by: John Sabolchy(Boeing)Approved by: Robert D. Breneman,Seattle FAA ACOSIGNATURE ON FILE08/13/2010AUGUST 2010 R1Revised 47-AWL-04 and 47-AWL-05 by updatingthe interval from 3,000 Flight Hours (FH)to 2,600 FH based upon a change to the certification analysis for fuel tank flammabilityexposure for the 767 Nitrogen Generation System.Submitted by: John Sabolchy(Boeing)Approved by: Philip Forde forRobert Breneman Seattle FAA ACOSIGNATURE ON FILE08/24/2010AUGUST 2010 R2Revised SSIs 53-10-I07C/53-30-I04C/53-60-I05C and 53-10-I07D/53-30-I04D/53-60-I05Dby adding the following text to provide better clarification regarding the applicability of DTRCheck Forms: “L/N 994, Lap S-26R: BS 1406to BS 1428 and S-25R to S-27R centerlinesmust be inspected with externaldetailed inspection every 600flight cycles (after reachingthreshold).”Submitted by: John Sabolchy(Boeing)Approved by: Donald Eiford forRobert D. Breneman,Seattle FAA ACOSIGNATURE ON FILE09/21/2010APRIL 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 methoddue to structural repair for L/N 1004.Submitted by: John Sabolchy(Boeing)Approved by: Steven Fox forRobert D. Breneman,Seattle FAA ACOSIGNATURE ON FILE05/19/2011JUNE 2011Revised Airworthiness Limitations - StructuralInspections table task 53-10-I07C/53-30-I04C/53-60-I05C by adding revised inspection methodand threshold due to structural repair forL/N 1008.Submitted by: Bill Lindholm(Boeing)Approved by: Steven Fox forRobert D. Breneman,Seattle FAA ACOSIGNATURE ON FILE07/26/2011REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-18767 MAINTENANCE PLANNING DATAJULY 2011Revised 47-AWL-03 to incorporate NGS performance features to show compliance with14 CFR 26.33.Submitted by: Mark Arnold(Boeing)Approved by: Robert D. Breneman(Seattle FAA ACO)SIGNATURE ON FILE08/05/2011NOVEMBER 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 applicabilityand inspection methods due to the structural repair of L/N 1018 and L/N 1019.Submitted by: Bill Lindholm(Boeing)Approved by: Julie Alger (Seattle FAA ACO)SIGNATURE ON FILE12/21/2011DECEMBER 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 thestructural repair of L/N 1020.Submitted by: Bill Lindholm(Boeing)Approved by: Ivan Li(Seattle FAA BASOO)SIGNATURE ON FILE1/27/2012FEBRUARY 2012Revised Airworthiness Limitations - StructuralInspections 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 withSB 767-53-0231 for L/N 973, and inspection in accordance with SB 767-53-0238 forL/N 1004.Revised Airworthiness Limitations - StructuralInspections 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 withSB 767-53-0230 for L/N 994.Revised Airworthiness Limitations - StructuralInspections Table Task SSI 53-10-I07C/53-30-I04C/53-60-I05C and 53-10-I07D/53-30-I04D/53-60-I05D by deleting alternateinspection for L/N 1018 at Lap S-26L: BS 467to BS 489 and S-25L to S-27L. Alternateinspections specified in revision dated NOV 2011 for structural repair are not valid due toskin replacement and return to drawing configuration.Submitted by: Mike Eckelberry(Boeing)Approved by: Kanji Patel (Seattle FAA ACO)SIGNATURE ON FILE3/7/2012REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-19OCTOBER 2012Revised the Airworthiness Limitations - Structural Inspections, Introduction Section byadding references to MPD Appendix K (Structures Baseline Requirements).Revised Airworthiness Limitations - StructuralInspections Table Task 53-10-I07C/53-30-I04C/53-60-I05C by adding Inspection Method andRepeat Interval due to structural repairof L/N 1040.Revised Airworthiness Limitations - StructuralInspections 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 forL/N 1019.Revised Airworthiness Limitations - StructuralInspections 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 subheadingof Section D, to beconsistent with otherSection 9 documents.Revised the subheading of Section E from “FUEL SYSTEM AIRWORTHINESSLIMITATIONS” to “D.1 AWLs –FUEL SYSTEM IGNITION PREVENTION” to beconsistent with other Section 9 documents.Added Section D.2 – Engine Fuel Suction Feed System, and ALI 28-AWL-101 – EngineFuel Suction Feed Operational Test, that is required to protect against engine flameoutduring suction feed operations.Revised Section F, making it Section D.3 tobe consistent with other Section 9 documents.Added “AWLs – Nitrogen Generation System” subheading to be consistent with otherSection 9 documents.Added Section D.4 – Impact-Resistant FuelTank Access Doors, and CDCCL 57-AWL-01 –Impact-Resistant Fuel Tank Access Doors, toverify 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 headingchanges made above.(Continued on next page)Submitted by: Sheila Reilley(Boeing)SIGNATURE ON FILEFAA BASOO11/02/2012REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-20767 MAINTENANCE PLANNING DATAOCTOBER 2012, ContinuedRevised Section H, making it a subheading ofSection E to be consistent in format with otherSection 9 documents.Revised Section I, making it a subheading of Section E and revised the subheading titlefrom "CERTIFICATION MAINTENANCE REQUIREMENTS TASKS" to "CMR TASKS" to beconsistent with otherSection 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 changespreviously incorporated.(Continued from previous page)(Continued from previous page)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 Intervaldue to structural repair of L/N 1047.Revised Airworthiness Limitations – StructuralInspections 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 theDescription. Airplanes that incorporate an EICAS instead of the operability indicator in thewheel well have a "6600 FH" interval instead of the "2600 FH" interval. Revised theApplicability from "767 airplane Line Numbers993 and on or airplanes that have incorporatedService Bulletin 767-47-0001" to "ALL NOTE" and added an Applicability Note in theDescription.Revised 47-AWL-05 by changing the interval to "Note" and adding an Interval Note to theDescription. Airplanes that incorporate an EICAS instead of the operability indicator in thewheel well have a "4391 FH" interval instead of the "2600 FH" interval. Revised theApplicability from "767 airplane Line Numbers993 and on or airplanes that have incorporatedService Bulletin 767-47-0001" to "ALL NOTE" and added an Applicability Note in theDescription.Revised 57-AWL-01 by adding a reference to Boeing AMMs 28-11-01 and 28-11-02.Submitted by: Krupal Desai forSameera Wijesinghe (Boeing)SIGNATURE ON FILEFAA BASOO2/14/2013REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-21APRIL 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 Intervaldue to structural repair of L/N 1055.Submitted by: SameeraWijesinghe (Boeing)SIGNATURE ON FILEFAA BASOO5/23/2013AUGUST 2013Added Section D.3 – AWLs – Low Fuel and Fuel Configuration Indication Test, and ALI28-AWL-102 to operationally check the Fuelindication for LOW FUEL Caution message andFUEL CONFIG Advisory message.Revised the numbering of the remaining Systems AWL sections due to the addition ofSection D.3.Submitted by: Cassandra Ho(Boeing)SIGNATURE ON FILEFAA BASOO8/22/2013SEPTEMBER 2013Revised the Airworthiness Limitations - Structural Inspections Front Matter to clarifyRemovable 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-I03Eand replaced them with 57-10-I03A and57-10-I03C.Revised SSI 57-10-I03A for 767-200ER, 767-300ER PASS, 300F, and 400E by extending theinspection 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: SameeraWijesinghe (Boeing)SIGNATURE ON FILEFAA BASOO11/08/2013REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-22767 MAINTENANCE PLANNING DATASEPTEMBER 2013, ContinuedGeneral revisions:Added L/N applicability to thresholdsin 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 withRib 5.Revised the applicability of SSI 57-53-I04Yfor the "Flap Support Fitting - Upper FlangeInboard Bolt Location" to 767-400E.Revised the applicability of SSI 57-53-I04Yfor 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 200SFand/or 300BCF fromSSIs associated with theDTR 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 theinspection area.Revised the threshold for SSI 57-20-I27 for 767-ALL to reference Service Bulletin767-57A0117, similar to the notes on the DTR check form.(Continued from previous page) (Continued from previous page)REVISIONSREVISION AND REVISION DESCRIPTION APPROVALSEP 2013Section Page Date Section Page Date Section Page Date Section Page Date Section Page DateD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-23LIST OF EFFECTIVE PAGES767 MAINTENANCE PLANNING DATA9.0 1 SEP 20139.0 2 BLANK9.0 3 SEP 20139.0 4 BLANK9.0 5 SEP 20139.0 6 SEP 20139.0 7 SEP 20139.0 8 SEP 20139.0 9 SEP 20139.0 10 SEP 20139.0 11 SEP 20139.0 12 SEP 20139.0 13 SEP 20139.0 14 SEP 20139.0 15 SEP 20139.0 16 SEP 20139.0 17 SEP 20139.0 18 SEP 20139.0 19 SEP 20139.0 20 SEP 20139.0 21 SEP 20139.0 22 SEP 20139.0 23 SEP 20139.0 24 OCT 20129.0 25 SEP 20139.0 26 JUN 20109.0 27 OCT 20129.0 28 DEC 20099.0 29 NOV 20099.0 30 DEC 20099.0 31 SEP 20139.0 32 JUN 20109.0 33 SEP 20139.0 34 SEP 20139.0 35 SEP 20139.0 36 SEP 20139.0 37 SEP 20139.0 38 SEP 20139.0 39 SEP 20139.0 40 SEP 20139.0 41 SEP 20139.0 42 SEP 20139.0 43 SEP 20139.0 44 SEP 20139.0 45 SEP 20139.0 46 SEP 20139.0 47 SEP 20139.0 48 SEP 20139.0 49 SEP 20139.0 50 SEP 20139.0 51 SEP 20139.0 52 SEP 20139.0 53 SEP 20139.0 54 SEP 20139.0 55 SEP 20139.0 56 SEP 20139.0 57 SEP 20139.0 58 SEP 20139.0 59 SEP 20139.0 60 SEP 20139.0 61 SEP 20139.0 62 SEP 20139.0 63 SEP 20139.0 64 SEP 20139.0 65 SEP 20139.0 66 SEP 20139.0 67 SEP 20139.0 68 SEP 20139.0 69 SEP 20139.0 70 SEP 20139.0 71 SEP 20139.0 72 SEP 20139.0 73 SEP 20139.0 74 SEP 20139.0 75 SEP 20139.0 76 SEP 20139.0 77 SEP 20139.0 78 SEP 20139.0 79 SEP 20139.0 80 SEP 20139.0 81 SEP 20139.0 82 SEP 20139.0 83 SEP 20139.0 84 SEP 20139.0 85 SEP 20139.0 86 SEP 20139.0 87 SEP 20139.0 88 SEP 20139.0 89 SEP 20139.0 90 JUN 20109.0 91 JUN 20109.0 92 OCT 20129.0 93 MAY 20109.0 94 OCT 20129.0 95 OCT 20129.0 96 MAY 20109.0 97 MAY 20109.0 98 MAY 20109.0 99 MAY 20109.0 100 MAY 20109.0 101 MAY 20109.0 102 MAY 20109.0 103 MAY 20109.0 104 MAY 20109.0 105 MAY 20109.0 106 MAY 20109.0 107 MAY 20109.0 108 MAY 20109.0 109 MAY 20109.0 110 MAY 20109.0 111 MAY 20109.0 112 MAY 20109.0 113 OCT 20129.0 114 OCT 20129.0 115 AUG 20139.0 116 AUG 20139.0 117 AUG 20139.0 118 JAN 20139.0 119 JAN 20139.0 120 JAN 20139.0 121 JAN 20139.0 122 AUG 20139.0 123 JAN 20139.0 124 OCT 20129.0 125 SEP 20089.0 126 OCT 20129.0 127 SEP 20089.0 128 OCT 20129.0 129 OCT 20129.0 130 OCT 20129.0 131 OCT 20129.0 132 OCT 20129.0 133 OCT 20129.0 134 OCT 20129.0 135 OCT 20079.0 136 BLANKSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-24767 MAINTENANCE PLANNING DATAA. SCOPEThe scheduled maintenance requirements described in this section result from Model 767 airplanecertification activities with the U.S. Federal AviationAdministration (FAA). Accordingly, this FAA approved Airworthiness Limitations and Certification Maintenance Requirements document is crossreferenced 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 (FAR) 43.16 and 91.403unless 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 SeattleFAA ACO must be used.CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)These scheduled maintenance tasks may only be revised bythe Seattle FAA ACO (appropriate regulatory authority). Principal Airworthiness Inspectors(local regulatory authority) may not change these requirements or the intervals associated with these requirements.B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSThe Structural Inspection Program approved inSection 3 of the 767 Maintenance ReviewBoard (MRB) Report and contained in Section 2 of this MPDdescribes an initial baseline structural maintenance program for all Structural Significant Items (SSIs). This program was developed in accordance withthe guidelines of MSG-3 and partially satisfies the requirementsof FAR 25.571 by providing accidental and environmental damagedetection opportunityfor all SSIs, and in some cases, fatigue damage detection opportunity until the supplemental inspection threshold is reached.The supplemental structuralinspections listed in this Section 9 “Airworthiness Limitations” are for those SSIsthat do not receive adequate fatigue damagedetection opportunity fromthe initial baseline structural program thatis listed in Section 2 and in Appendix K.The inspections shown in this section and Appendix K are to beaccomplished in conjunction with and not asa substitute for the existing structuralmaintenance program found in Section 2.OCT 2012767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-25The supplemental structural inspection program uses the Damage Tolerance Rating (DTR)system to determine the inspections (andrepeat intervals)necessary to provide adequate fatigue damage detection. The DTR system defines a required DTR (a numerical value) that must beachieved for eachSSI. DTR Check Forms which define the inspection options and the required DTR are contained in Document D622T001-DTR.THRESHOLDThe certifying authority (Seattle FAA ACO)requires designation of allSSIs into two categories. These two categories are referred to as Type 1 andType 2. Type 1 structure requires the implementation threshold to be established by crack growth analysis. Type 2 structure isallowed to have theimplementation threshold established by fatigue analysis (supportedby test evidence) and allowsfor the future escalation of the inspection threshold whensufficient data from the initial inspections statistically support an increased threshold. See Document D622T001-DTR for a detailed definition of Type 1and Type 2 categories.The inspections are to be done on the basis of the threshold specified in the AWL – Structural Inspections table and repeat inspections determined fromDTR 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 accumulated regardless of what theairframe as a whole has accumulated. Most SSI details have never been replaced and therefore have accumulated the same flight cycles and flight hoursas the airframe. Some SSI details are replaced, such as when installing Removable Structural Components (repairable/rotable/expendables) or installingused structural parts as a repair. In these cases the SSI detailshave accumulated flight cycles and flight hours that may be different than the airframe. Theoperator must account for this in determining when inspections must be done.Although intended for repairs, FAA AC 120-93 Appendix 7, provides a method for determining the age of a Removable Structural Component, which maybe applied to the baseline structure.The Airworthiness Limitations – Structural Inspections table defines the inspection implementation threshold. Some items are sensitive to flight length andidentified by “FLS” (Flight Length Sensitive) in the Threshold column of the table. FLS Items require both flight hours and flight cycles to determine theimplementation threshold. Refer to Figure 1, shown onthe next page, to determine the threshold for FLS Items.SEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-26767 MAINTENANCE PLANNING DATAFIGURE 1. FLIGHT LENGTHSENSITIVE (FLS) THRESHOLD CURVEInstructions for the use of the FlightLength Sensitive (FLS) Threshold Curve:1. Determine, for each airplane, the accumulated flight cycles and flight hours.2. Enter the FLS Threshold Curve at the appropriate flight cycles and flight hours and plot point.3. The initial supplemental inspection must be accomplished before crossing into the shaded area on the FLS Threshold Curve. Note that the shaded areafor the -200, -200SF, -300 Passenger, and -300BCF aircraft is different from that for the -300F Freighter and -400ER Passengeraircraft.JUN 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-27In addition to the thresholds described above, a calendar threshold of 20 years applies unless an initial inspection of an FAAapproved CorrosionPrevention and Control Program (CPCP) has occurred, constituting CPCP implementation.The information contained in Appendix K has been added to complywith the AD 2003-18-10 requirements when an airplane reaches the flight cycle orflight hour supplemental inspection threshold (whichever comes first). Appendix K contains the 1995-1999 versions of MPD Section 8, StructuralInspection Program, and is the baseline structural inspection program associated with the October2002 MPD Section 9, Airworthiness Limitations andCMRs. AD 2003-18-10 paragraph (c) requires the incorporation of the October 2002 MPD Section 9 or an appropriately approved AMOC to the AD.When reaching the threshold of 50,000 flight cycles (-200, -200SF1and -300 Passenger or -300 Passenger converted to -300BCF aircraft after 10,000cycles or more as a -300 Passenger) or 40,000 flight cycles (-300F Freighter or -400ER Passenger or -300 Passenger converted to-300BCF aircraftbefore 10,000 cycles as a -300 Passenger), all C-check (or higher) structural inspection repeat intervals must be no greater than those shown inAppendix K. Structures “S 1C” check intervalis defined as 3,000 flight cycles or 18 months (whichever comes first). This means that any operator, who hasescalated the structures program by changingeither task intervals (flight cycles) or the C-check interval (flight cycles), must reduce the repeat frequenciesback to the MPD baseline structures program intervals before accumulating 50,000 flight cycles or 40,000 flight cycles respectively or the FLS cycles andhours (whichever comes first). The reason for this is that the FAR 25.571 damage tolerance evaluation takes credit for the baseline structures programdefined in Appendix K. The airworthiness limitations listed in Section 9 are supplemental structural inspections of the SSIs for which the required DTR isnot satisfied by the baseline structural inspections defined inAppendix K. Any continued escalation beyond the MPD baseline structures program mayresult in additional structure not meetingthe required DTR which was the basis of certification. The inspections shown in Section 9 AirworthinessLimitations are to be accomplished in conjunction with and not asa substitute for the existingstructures maintenance programfound in Appendix K.767 PASSENGER-TO-FREIGHTERCONVERSION AIRPLANESCertain 767 airplanes are modified from passenger model airplanes to a freighter configuration via Boeing service bulletin. After incorporation of theBoeing passenger-to-freighter service bulletin, these 767-200and 767-300 airplanes are designated as 767-200SF and 767-300BCF.Refer to Section Cof this chapter for additional data related to 767-200SF and 767-300BCF structural safe life parts.1Only one -200SF exists, and it was modified after 14,900 cycles as a Passenger aircraft.OCT 2012D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-28767 MAINTENANCE PLANNING DATACertain 767-300BCF supplemental inspection thresholds are calculated based on the summation of fatigue damage accrued as a passenger and then afreighter. These are identified by “Combined Threshold” in the Threshold column. Refer to Figure 2 to determine the threshold for these items.Certain 767-300BCF supplemental inspection thresholds are calculated from the date of modification. These are identified by “Mod Date Sensitive” in theThreshold column. Refer to Figure 3 todetermine the threshold for these items.Instructions for the use of theCombined Life Threshold curve:1. Determine, foreach airplane, the accumulated flightcycles prior to BCF modification.2. Enter the threshold curve at the appropriate flight cycles as 300ER.3. The initial supplemental inspectionmust be accomplished before crossing the 300BCF Combined Threshold curve.Instructions for the use of the Mod Date Sensitive curve:1. Determine, foreach airplane, the accumulated flightcycles prior to BCF modification.2. Enter the threshold curve at the appropriate flight cycles as 300ER.3. The initial supplemental inspectionmust be accomplished before crossing the 300BCF Mod Date Sensitive curve.DEC 2009767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-29FIGURE 2. Combined Passenger and Freighter Life ThresholdCombined Threshold250003000035000400004500050000550000 5000 10000 15000 20000 25000 30000 35000 40000 45000 50000Flights 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 RowNOV 2009D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-30767 MAINTENANCE PLANNING DATAFIGURE 3. Mod DateSensitive StructureDEC 2009767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-31REPEAT INSPECTION INTERVALA repeat inspection interval for the fatigue inspection of an SSIis established from its DTR Check Form. Airplanes with an average flight length (flighthours per landing) equal to or more than 8 hours must use the DTR Check Form labeled "767 >8 hours" at the top of the form (see Document D622T001-DTR for DTR Check Forms). Revision to the required DTR or the DTR curve is not allowed without approval from the Seattle FAA ACO.REPORTING RESULTS OFSTRUCTURAL INSPECTIONSAll cracks found during these inspections shall be reported within ten (10) days directly to the Manager of the Seattle FAA ACO, Transport AirplaneDirectorate, FAA and to Boeing Commercial Airplanes using the Discrepant Structure Report Form. Refer to Document D622T001-DTRfor the requiredreport form (any suitable alternative whichcontains 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 fuelbarrier sealant (BMS 5-81, Type II) outside the fuel tank removal and application,on the wing center section.• If sealant is removed inside the fuel tank for inspection, care must be taken to remove any sealant debris in the fuel tank.Sealant of fuel tank fasteners must comply with MPD Section 9, Parts D and E.SEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-32767 MAINTENANCE PLANNING DATAThe following pages, included in the Airworthiness Limitations –Structural Inspections table, list the Airworthiness Limitation supplemental inspectionrequirements. Each item is listed by SSI Number, DTR Check Form Title, Inspection Zone, Airplane/EngineApplicability, Type andThreshold.NOTE: There are 767-200SF Fuselage ALIs that do not have corresponding DTR Check Forms. The inspection type and repeat inspectioninterval are given in the DTR document.There are 767-200SF and 767-300BCF Wing ALIs that do not have corresponding DTR Check Forms. The inspection type and repeatinspection 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 more thanone listing for agiven SSI Number, the DTR CheckForm Title is the unique identifier along with the Airplane/Engine Applicability. Airplane/engine applicability is listedas follows:ALL= All AirplanesPASS (-ER ONLY) = Passenger Airplanes, Extended Range Only.PASS= Passenger Airplanes< 8 HOURS = Airplanes with cumulativestage length (Flight Hours per Landing)200= 767-200, -200ERless than 8 hours.200SF= 767-200 Special Freighter300= 767-300, -300ER>8 HOURS = Airplanes with cumulativestage length (Flight Hours per Landing)300BCF= 767-300 Boeing Converted Freighterequal 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 RB211-524HJUN 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-33AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLD27-40-I01AStabilizer Trim Actuator–Lower Gimbal Lug Assy BS 1708.5, WL 239.9311, 312 ALL Type 150,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)27-40-I01BStabilizer Trim Actuator–Lower Gimbal Plate Assy BS1708.5, WL 239.9, BL 0.0311, 312 400E Type 140,000 Cycles52-30-I02AStandard Cargo Door forward and aft–Applicable to 767-200, 200SF, -300,-300BCF (aft) and -400 passenger airplanes–Beam #2 @ STA 210.15, sectionbetween upper access and Vent Door Cutouts821, 822 200, 200SF300BCF, 300 PASS400E<2>Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (400E)52-30-I05A Latch Cam Support Frame Fitting – Forward large Cargo Door – Fitting Lug Bore821 ALL<2>Type 250,000 Cycles(200, 300 PASS)40,000 Cycles(300BCF, 300F, 400E)52-30-I05BLatch frame inner chord–Forward large Cargo Door–Latch Frame Inner Chord atSplice to Latch Frame Support Fitting821 ALLType 137,500 Cycles(200, 300 PASS)30,000 Cycles(300BCF, 300F, 400E)52-30-I05COuter Skin–Forward large Cargo Door–Outer Skin at attachment to main hingesegments at forward and aft ends of the door821 ALLType 137,500 Cycles(200, 300 PASS)30,000 Cycles(300BCF, 300F, 400E)52-30-I07ALatch Cam Support Fitting–Main Deck Cargo Door–Fitting Lug Bore838 200SF300BCF, 300F<2>Type 240,000 Cycles (300F)50,000 Cycles (200SF)Mod Date Sensitive (300BCF)52-30-I07BLatch Frame Inner Chord–Main Deck Cargo Door–Latch Frame Inner Chord atSplice to Latch Frame Support Fitting838 200SF300BCF, 300F<2>Type 130,000 Cycles44,900 Cycles (200SF)Mod Date Sensitive (300BCF)SEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-34767 MAINTENANCE PLANNING DATA52-30-I07COuter Skin–Main Deck Cargo Door–Outer Skin at attachment to main hingesegments at forward and aft ends of the door838 200SF300BCF, 300F<2>Type 144,900 Cycles (200SF)Mod Date Sensitive (300BCF)30,000 Cycles (300F)52-30-I07EMDCD Outer Skin Lap Splice–Upper row (upper skin)–Intercostal #5838 200SF300BCF, 300F<2>Type 250,000 Cycles (200SF)Mod Date Sensitive (300BCF)40,000 Cycles (300F)52-30-I07FMDCD Outer Skin Lap Splice–Lower row (lower skin)–Intercostal #5838 200SF300BCF, 300F<2>Type 144,900 Cycles (200SF)Mod Date Sensitive (300BCF)30,000 Cycles (300F)52-30-I09ALatch Cam Support Fitting–Aft large Cargo Door–Fitting Lug Bore822 300F<2>Type 240,000 Cycles52-30-I09BLatch Frame Inner Chord–Aft large Cargo Door–Latch Frame Inner Chord at Spliceto Latch Frame Support Fitting822 300FType 130,000 Cycles52-30-I09COuter Skin–Aft large Cargo Door–Outer Skin at attachment to main hingesegments at forward and aft ends of the door822 300FType 130,000 Cycles53-10-I07A53-30-I04A53-60-I05ASkin Longitudinal Lap Splices–Upper Row – Crown and Upper Lobe, Sections 41, 43and 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 (notapplicable) 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 610and S-7L to S-9L centerlines must beinspected with external detailed inspection every 900 flight cycles (after reachingthreshold).220, 230, 250 ALLExcept where noted forL/N 945, L/N 963,L/N 973, L/N 1004, andL/N 1047200SF and 300BCFType 250,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)37,500 Cycles (L/N 945, L/N 963)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3553-10-I07B53-30-I04B53-60-I05BSkin Longitudinal Lap Splices – Lower Row – Crown and Upper Lobe, Sections 41, 43and 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 (notapplicable); 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 inspectedwith external detailed inspection every 900 flight cycles (after reaching threshold).220, 230, 250ALLExcept where noted forL/N 945, L/N 963,L/N 973, L/N 1004,and L/N 1047200SF and 300BCFType 250,000 Cycles(200, 200SF, 300BCF, 300PASS)40,000 Cycles (300F, 400E)37,500 Cycles (L/N 945, L/N 963)53-10-I07C53-30-I04C53-60-I05CSkin Longitudinal Lap Splices – Upper Row – Bilge and Lower Lobe, Sections 41, 43and 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 perSB 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 BS314. 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 mustbe 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 beinspected with external detailed visual inspection every 900 flight cycles, uponreaching threshold.100ALLExcept where noted forL/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, andL/N 1055200SF and 300BCFType 250,000 Cycles(200, 200SF, 300BCF, 300PASS)40,000 Cycles (300F, 400E)37,500 Cycles (L/N 946, L/N 967)30,000 Cycles (L/N 873)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-36767 MAINTENANCE PLANNING DATA53-10-I07D53-30-I04D53-60-I05DSkin Longitudinal Lap Splices – Lower Row – Bilge and Lower Lobe, Sections 41, 43and 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 perSB 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 athreshold 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 toBS 314 Must inspect per SB 767-53-0244.10) L/N 1020: Lap S-36L: BS 770 to BS 784and S-35 to S-37L centerlines must beinspected with internal detailed inspection every 900 flight cycles (after reachingthreshold).11) L/N 1055: Lap S-26R: Between BS 1456 to BS 1480 and S-25R to S-27R must beinspected with external detailed visual inspection every 900 flight cycles, uponreaching threshold.100ALLExcept where noted forL/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 1055200SF and 300BCFType 250,000 Cycles(200, 200SF, 300BCF, 300PASS)40,000 Cycles (300F, 400E)37,500 Cycles (L/N 946, L/N 967)30,000 Cycles (L/N 873)53-10-I08B53-30-I24BFrames above S-20220, 230 ALL Except 200SF,300BCFType 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F, 400E)53-10-I08B53-30-I24BFrames above S-20, Frame (Fully visible)220, 230200SFType 250,000 Cycles53-10-I08B53-30-I24BBCF 3 – Frames above S-20, Not Applicable to Areas of Hidden Frame Structure220, 230300BCFType 250,000 Cycles53-10-I08C53-30-I24C53-60-I08CFrames, Below S-20, Frame (Fully visible)100200SFType 250,000 Cycles53-10-I08C53-30-I24C53-60-I08CFrames, S-20 and below. BS 246 to BS 786 and BS 1065 to BS 1582100 ALL Except 200SF,300BCFType 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3753-10-I08C53-30-I24C53-60-I08CBCF 5 – Frames below S-20, All Frames Except the Areas of Hidden Frame Structure100 300BCF Type 250,000 Cycles53-10-I10A Forward Passenger Entry/Service Door Cutout- Edge Frame – Inner Chord DoorSTA 76.3, S-7 to S-12 and S-19 to S-23,Door STA 123.7, S-8 to S-12 and S-19to S-23119, 221, 222,223, 224ALL Type 250,000 Cycles(200, 300 PASS)40,000 Cycles(200SF, 300BCF, 300F, 400E)53-10-I10B Forward Passenger Entry/Service DoorCutout- Upper Main Sill – Inner Chord DoorSTA 100 to Door STA 129.9221, 222 ALL Type 250,000 Cycles(200, 300 PASS)40,000 Cycles(200SF, 300BCF, 300F, 400E)53-10-I12 Main Equipment Center Access Door CutoutBS 303 – BS 325, LBL 13.1 – RBL 13.1119ALLType 250,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)53-10-I13 Forward Equipment Bay Access DoorCutout – BS 144.5 – BS 163.2. LBL 9 – RBL 9113, 114ALLType 250,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)53-10-I14AWindow #1 Cutout Structure–AB POST211, 212 ALL Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-38767 MAINTENANCE PLANNING DATA53-10-I14BWindow #1 Cutout Structure–BD SILL211, 212 ALL Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)53-10-I16Window #2 Cutout Structure–EF POST211, 212 ALL Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)53-10-I18A NLG Wheel Well – Canted Bulkhead Details – Outer Chord Typical Locations BetweenS-32L & S-32R113, 114 ALL Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)53-10-I18B NLG Wheel Well – Canted Bulkhead Details – Outer Chord Hidden LocationsL/RBL 10.60 & L/RBL 25.00113, 114ALLType 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)53-10-I20A NLG Wheel Well – BL25 Side Panel Details – Vertical Beams & Panel Web fromBS 180.5 to BS 276117, 118ALLType 150,000 Cycles(200, 300 PASS)40,000 Cycles(200SF, 300BCF, 300F, 400E)53-10-I20B NLG Wheel Well – Trunnion Support Fitting at Top Panel Beam Attachment. BS 276,BL 30, WL 181 to WL 187117, 118ALLType 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3953-10-I20C NLG Wheel Well – Trunnion SupportFitting at Strap Attachment. BS 276, BL 30,WL 165 to WL 169117, 118 ALL Type 150,000 Cycles(200, 300 PASS)40,000 Cycles(200SF, 300BCF, 300F, 400E)53-10-I21A NLG Wheel Well – BS 287 Bulkhead Details – WL 159 Beam & Bulkhead Web fromLBL 27 to LBL 23, LBL 10.0 to RBL 10.0, RBL 23 to RBL 27119 ALLL/N 1-757<1>Type 150,000 Cycles(200, 300 PASS)40,000 Cycles(200SF, 300BCF, 300F)53-10-I21A NLG Wheel Well – BS 287 Bulkhead Details – WL 159 Beam & Bulkhead Web fromLBL 10.0 to RBL 10.0119 ALLL/N 758 and on<1>Type 150,000 Cycles(200, 300 PASS)40,000 Cycles (300F, 400E)53-10-I21B NLG Wheel Well – BS 287 Bulkhead Details – Outer Chord Typical Locations betweenS-24L and S-24R119ALLType 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)53-10-I21C NLG Wheel Well – BS 287 Bulkhead Details – Outer Chord – Stringer Splices betweenS-24L and S-24R119ALLType 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)53-10-I21D NLG Wheel Well – BS 287 Bulkhead Details – Outer Chord Hidden Locations atS-36L, S-36R and S-27R119ALLType 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)53-10-I21E NLG Wheel Well – BS 287 Bulkhead Details – WL 159 Beam and Bulkhead WebLBL 27 to LBL 23 and RBL 23 to RBL 27, C/L 758 on119ALLType 150,000 Cycles (200, 300 PASS)40,000 Cycles (300F, 400E)53-10-I33B BCF 2 – Section 41 External Skin Doubler first fastener common to skin and doublerbetween BS 368 and BS 434 at S-38L121 200SF, 300BCF<4>Type 250,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-40767 MAINTENANCE PLANNING DATA53-10-I33E BCF 5 – Section 41 Service PanelCutout Structure BS 390 to BS 412; BL 0to RBL 13.65121 200SF, 300BCF<4>Type 248,300 Cycles (200SF)Mod Date Sensitive (300BCF)53-30-I0153-50-I0153-60-I01Fuselage 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 770must be inspected per SB 767-53-0210. 2) 300BCF: S-4L to S-4R from STA 654+110to 786.230, 240, 250ALLExcept where noted forL/N 969and 300BCFType 250,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)53-30-I01 BCF 1 – Crown Doubler, first fastener row common to skin and doubler betweenStringers S-8 and S-6 BS 654+28 to 654+115231, 232300BCF<4>Type 250,000 Cycles53-30-I01 BCF 2 – Crown Doubler Aft Edge Circumferential Crack Between BS 654+115;Between Stringer S-7L and S-7R231, 232300BCF<4>Type 1Combined Threshold53-30-I01 BCF 3 – Circumferential Splice – Upper Crown at BS 654+22233, 234300BCF<4>Type 250,000 Cycles53-30-I01 BCF 5 – Crown Skin Doubler – Longitudinal Crack in Skin at forward corners atBS 654+22 at S-8L and S-8R231, 232300BCF<4>Type 250,000 Cycles53-30-I01 BCF 9 – Fuselage Crown Skin STA 654+115 to 786 STR-4R to 4L231, 232300BCFType 250,000 Cycles53-30-I01 BCF 10 – Fuselage Crown Stringers230300BCFType 2Combined Threshold53-30-I01 SF1 – Crown Skin Doubler – RHS Edge of Crown Skin Doubler at RBL 9233, 234200SF<4>Type 250,000 Cycles53-30-I01 SF2 – Crown Skin Doubler – Aft Edge Body STA 742233, 234200SF<4>Type 230,000 Cycles53-30-I01 SF3 – Crown Skin Doubler– Stringer at Circumferential Splice233, 234200SF<4>Type 250,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4153-30-I01 SF5 – Crown Skin Doubler – At STA 676 Skin Splice, at STR-8L233, 234 200SF<4>Type 250,000 Cycles53-30-I01 SF6 – Crown Skin Doubler – At VHF Antenna Installation233, 234 200SF<4>Type 250,000 Cycles53-30-I01 SF8A – Crown Skin Doubler – SkinLap Splice at STR-2R and STR-8L Inner Skin233, 234 200SF<4>Type 250,000 Cycles53-30-I01 SF8B – Crown Skin Doubler – SkinLap Splice at STR-2R and STR-8L Outer Skin233, 234 200SF<4>Type 250,000 Cycles53-30-I01 SF9 – Section 43 Crown Skin – Aft of Doubler233, 234200SF<4>Type 237,500 Cycles53-30-I01 SF10 – Section 43 Crown Stringers – Aft of External Doubler233, 234200SF<4>Type 225,000 Cycles53-30-I04A Skin Longitudinal Lap Splices – UpperRow – Crown and Upper Lobe, Sections 41, 43and 46Note: Applicable to S-8R, STA 434 to 654 + 22.230 200SF, 300BCFType 250,000 Cycles (200SF)Mod Date Sensitive (300BCF)53-30-I04A BCF2 Skin Longitudinal Lap Splices Upper Row – Upper LobeNote: Applicable to S-8L, STA 654 + 22 to 654 + 110.230300BCFType 2Combined Threshold53-30-I04B Skin Longitudinal Lap Splices – Lower Row – Crown and Upper Lobe, Sections 41, 43and 46Note: Applicable to S-8L, STA 654 + 22 to 654 + 110.230300BCFType 2Mod Date Sensitive53-30-I04B Skin Longitudinal Lap Splices – Lower Row – Crown and Upper Lobe, Sections 41, 43and 46Note: Applicable to S-8R, STA 434 to 654 + 22.230 200SF, 300BCFType 230,700 Cycles (200SF)Combined Threshold (300BCF)53-30-I04D BCF 1 – Skin Longitudinal Lap Splices – Lower Row – Bilge S-26L MDCD andL2 PanelDTR Form not applicable to: 1) L/N 269, STA 654 + 22 to 654 + 110 must be inspectedper TBC-ANA-0008-01B (R1) 20 April 2009.Note: -200SF inspection is from BS 434 to BS 676.100200SF300BCFExcept where noted forL/N 269<4>Type 227,900 Cycles (200SF)Combined Threshold (300BCF)37,500 (L/N 269)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-42767 MAINTENANCE PLANNING DATA53-30-I05 STA 786 Circumferential Splice in the Body Crown240 200SF Type 250,000 Cycles53-30-I0553-30-I2153-30-I2753-50-I0353-60-I0353-60-I26Fuselage 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-4RSTA 654+22.230, 240, 250 200, 200SF300BCF, 300F,300 PASS,Except where notedfor 300BCF<3><4>Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F)53-30-I0553-30-I0853-30-I2153-50-I0353-60-I0353-60-I0453-60-I2453-60-I33Fuselage Circumferential Splices in the Body Crown – Specified Locations230, 240, 250 400E<2>Type 140,000 Cycles53-30-I14A Forward Main Cargo Door Cutout –Edge Frames – Frames at STA 539.5 & 615.5Stringers S-17R to S-21 R and S-28R to S-36R122, 124, 232 200, 200SF300 PASSType 250,000 Cycles53-30-I19A Forward Large Cargo Door Cutout –Edge Frame Inner Chord at BS 478, S-23R toS-28R & at BS 618, S-27R toS-28R & S-29R to S-30R122 200300 PASSType 250,000 Cycles53-30-I19B Forward Large Cargo Door Cutout –Edge Frame Inner Chord at BS 478, S-26R toS-27R and at BS 618, S-29R to S-30R122 200300 PASSType 250,000 Cycles53-30-I19C Forward Large Cargo Door Cutout– Edge Frame at BS 618, S-28R to S-29R122 200300 PASSType 250,000 Cycles53-30-I19D Forward Large Cargo Door Cutout – Lower Sill: BS 610 - 632, Upper Sill: BS 456 -478, BS 482 - 493122, 124 200300 PASSType 250,000 Cycles53-30-I19E Forward Large Cargo Door Cutout – Upper Sill: BS 478 – 482122 200300 PASSType 250,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4353-30-I19F Forward Large Cargo Door Cutout – Upper Sill: BS 480122 200300 PASSType 250,000 Cycles53-30-I19G Forward Large Cargo Door Cutout – Upper Sill: BS 482 to BS 493122 200300 PASSType 250,000 Cycles53-30-I19AB Forward Large Cargo Door Cutout – FWD Edge Frame Inner Chord at BS 478, S-20Rto S-22R and at BS 618, S-20R to S-22R122300BCF300F400E<2>Type 240,000 Cycles53-30-I19AC Forward Large Cargo Door Cutout – FWD Edge Frame Inner Chord at BS 478, S-17Rto S-20R and S-22R to S-23R122, 232300BCF300F400E<2>Type 240,000 Cycles53-30-I19AD Forward Large Cargo Door Cutout –Upper Main Sill Inner Chord at BS 607 to BS 618122300BCF300F400E<2>Type 240,000 Cycles53-30-I19AD1 Forward Large Cargo Door Cutout – Upper Main Sill Inner Chord Hidden Locations atBS 607 to BS 618122300BCF300F400E<2>Type 240,000 Cycles53-30-I19AF Forward Large Cargo Door Cutout – Lower Main Sill Inner Chord Hidden Locations atBS 466 to BS 483 and BS 614 to BS 625124300BCF300F400E<2>Type 240,000 Cycles53-30-I19AF1 Forward Large Cargo Door Cutout –Lower Main Sill Inner Chord at BS 466 to BS 483and BS 614 to BS 625124300BCF300F400E<2>Type 240,000 Cycles53-30-I20A Forward Large Cargo Door Cutout –Lower Latch Backup Structure – Latch SupportFitting at BS 487.7 & BS 608.3124ALLType 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-44767 MAINTENANCE PLANNING DATA53-30-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-20230 300 PASS400EType 250,000 Cycles (300 PASS)40,000 Cycles (400E)53-30-I22D Mid Passenger Entry/Service DoorCutout – Upper Main Sill Inner Chord230 300 PASS Type 250,000 Cycles53-30-I22D Mid Passenger Entry/Service DoorCutout – Upper Main Sill Inner Chord –BS 654+33 to BS 654+110230 400E Type 240,000 Cycles53-30-I24A53-50-I01A53-50-I02A53-60-I08AFrames above S-20230, 240, 250 ALL Except 200SF,300BCFType 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F, 400E)53-30-I24A53-60-I08AFrames – Above S-20, Frame (Hidden Structure)230, 240, 250 200SF<4>Type 250,000 Cycles53-30-I24A53-50-I01A53-50-I02A53-60-I08ABCF 1 – Frames above S-20231, 232 300BCF Type 250,000 Cycles53-30-I24A53-50-I01A53-50-I02A53-60-I08AFrames – Above S-20, Frame (Fully visible)230, 240, 250 200SF Type 250,000 Cycles53-30-I24A BCF 2 – Frames above S-20, Applicable to Areas of Hidden Frame Structure231, 232300BCF<4>Type 250,000 Cycles53-30-I24B Frames above S-20, Frame (Hidden Structure)220, 230200SF<4>Type 250,000 Cycles53-30-I24B BCF 4 – Frames above S-20, Applicable to Areas of Hidden Frame Structure220, 230300BCF<4>Type 250,000 Cycles53-30-I24C53-60-I08CBCF 6 – Frames below S-20, Applicable Only to Areas of Hidden Frame Structure100300BCF<4>Type 250,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4553-30-I24C53-60-I08CFrames – Below S-20, Frame (Hidden Structure)100 200SF<4>Type 250,000 Cycles53-30-I27 BCF 2 – Circumferential Butt Splice654+22 Splice Plate First Fastener RowFWD/AFT of Splice at BS 654+22231, 232 300BCF Type 250,000 Cycles53-30-I27A53-50-I0353-60-I03Fuselage Circumferential Splices in the Body Crown230, 240, 250 200SF Type 150,000 Cycles53-30-I28 BCF 1 – Main Deck Cargo Door Cutout – Auxiliary Sill Inner Chord231300BCF<4>Type 250,000 Cycles53-30-I28 SF1 – Main Deck Cargo Door Cutout – Auxiliary Sill Inner Chord231200SFType 250,000 Cycles53-30-I28A Reinforcement Around Cutouts – Main Deck Cargo Door – Cutout Structure –Upper Main Sill Inner Chord at BS 492231200SF300BCF, 300F<2>Type 250,000 Cycles (200SF)Mod Date Sensitive (300BCF)40,000 Cycles (300F)53-30-I28B Reinforcement Around Cutouts – Main Deck Cargo Door – Cutout Structure –Lower Main Sill Inner Chord at BS 632231200SF300BCF, 300F<2>Type 250,000 Cycles (200SF)Mod Date Sensitive (300BCF)40,000 Cycles (300F)53-30-I28C Reinforcement Around Cutouts – Main Deck Cargo Door – Cutout Structure –FWD Edge Frame Inner Chord at S-5L233200SF300BCF, 300F<2>Type 250,000 Cycles (200SF)Mod Date Sensitive (300BCF)40,000 Cycles (300F)53-30-I28D Reinforcement Around Cutouts – Main Deck Cargo Door – Aft Edge Frame at BS 632and S-16L – Frame Splice231200SF300BCF, 300F<2>Type 250,000 Cycles (200SF)Mod Date Sensitive (300BCF)40,000 Cycles (300F)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-46767 MAINTENANCE PLANNING DATA53-30-I28E Reinforcement Around Cutouts – Main Deck Cargo Door – Aft Edge Frame at BS 632and S-2L231, 233 200SF300BCF, 300F<2>Type 250,000 Cycles (200SF)40,000 Cycles (300F)Mod Date Sensitive (300BCF)53-30-I28F Reinforcement Around Cutouts – Main Deck Cargo Door – Cutout Structure –Upper and Lower Main Sill Outer Chord at BS 496 and 628231, 233 200SF300BCF, 300F<2>Type 250,000 Cycles (200SF)Mod Date Sensitive (300BCF)40,000 Cycles (300F)53-50-I06 SF – Single Emergency Exit Cutout Auxiliary Sill Inner Chord241, 242 200SF Type 250,000 Cycles53-50-I06A Single Emergency Exit Cutout – FrameInner Chords at BS 859.5, S-18 to S-20 and atBS 883.5, S-16 to S-20241, 242 200, 200SFType 250,000 Cycles53-50-I06B Single Emergency Exit Cutout – Frame Inner Chords at Sill Intersect at BS 859.5and 883.5241, 242 200, 200SFType 250,000 Cycles53-50-I06C Single Emergency Exit Cutout – Sill Inner Chord – Upper Sill at BS 859.5 to BS 871.5241, 242 200, 200SFType 250,000 Cycles53-50-I06D Single Emergency Exit Cutout – SillInner Chord at FrameIntersect at BS 859.5and BS 883.5241, 242 200, 200SFType 250,000 Cycles53-50-I06E Single Emergency Exit Cutout – Sill Outer Chord241, 242 200, 200SFType 250,000 Cycles53-50-I06F Single Emergency Exit Cutout – Sill Outer Chord at Frame Intersect241, 242 200, 200SFType 250,000 Cycles53-50-I11 BS 1043 Frame Splice with the Landing Gear Fitting – BS 1043, BL 92, WL 193 toWL 199141, 142ALLType 250,000 Cycles(200, 200SF, 300 PASS)40,000 Cycles(300BCF, 300F, 400E)53-50-I13A Fuselage Rear Spar Bulkhead – Bulkhead Fitting Inboard Prong Attachment to WingRear SparDELETEDAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4753-50-I13B Fuselage Rear Spar Bulkhead – Bulkhead Fitting Inner Chord S-20 to S-21 at SeatTrack Bracket131, 132 ALL Type 125,000 Cycles53-50-I13C Fuselage Rear Spar Bulkhead – Inboard Chord Flange – BS 955, BL 91, S-18 to S-20241, 242 ALL Type 250,000 Cycles(200, 200SF, 300 PASS)40,000 Cycles(300BCF, 300F, 400E)53-50-I14A Aft Wheel Well Bulkhead BS 1065 – Vertical Beam BL 26 Intercostal Upper ChordSplice143, 144 ALL Type 250,000 Cycles(200, 200SF, 300 PASS)40,000 Cycles(300BCF, 300F, 400E)53-50-I14B Aft Wheel Well Bulkhead BS 1065 – Hidden Details at Chord Splices S-27 to S-28 andS-35 to S-36151, 152 ALL Type 150,000 Cycles(200, 200SF, 300 PASS)40,000 Cycles(300BCF, 300F, 400E)53-50-I14C Aft Wheel Well Bulkhead BS 1065 – Hidden Details at Chord between S-29 & S-34151, 152 ALL Type 125,000 Cycles53-50-I1853-50-I2453-50-I28Section 45 Stub Frames – BS 808 – 933 Frame Inner Chord at Stub Beam131, 132 200, 200SF300BCF, 300F,300 PASSType 250,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F)53-50-I19 MLG Wheel Well – BS 1021 Transverse Floor Beam Lower Chord – From LBL 33 toLBL 60 and RBL 33 to RBL 60143, 144 200SF300BCFPASSType 250,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (400E)53-50-I19B MLG Wheel Well Transverse Floor Beam BS 1021 Lower Chord – From LBL 33 toLBL 60 & RBL 33 to RBL 60DELETEDAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-48767 MAINTENANCE PLANNING DATA53-50-I22A Dual Emergency ExitCutout – Frame Inner Chords241, 242 200300 PASSType 250,000 Cycles53-50-I22A BCF – Dual Emergency ExitCutout Edge – Frame Inner Chords241, 242 300BCF Type 250,000 Cycles53-50-I22B Dual Emergency Exit Cutout– Frame Inner Chord at Sill Intersect241, 242 200300 PASSType 250,000 Cycles53-50-I22B BCF – Dual Emergency Exit Cutout Edge Frame – Inner Chord at Sill241, 242 300BCF Type 250,000 Cycles53-50-I22C BCF – Dual EmergencyExit Cutout – Sill Inner Chord241, 242 300BCF Type 250,000 Cycles53-50-I22D BCF – Dual Emergency ExitCutout – Sill Inner Chord at Frame241, 242300BCFType 250,000 Cycles53-50-I22E BCF – Dual Emergency Exit – Sill Inner Chord & Strap BS 859.5 and BS 903.5241, 242300BCFType 250,000 Cycles53-50-I22F BCF – Dual Emergency Exit Cutout – Sill Outer Chord241, 242300BCFType 250,000 Cycles53-50-I22G BCF – Dual Emergency Exit Cutout – Sill Outer Chord at Frame Intersect241, 242300BCFType 250,000 Cycles53-50-I22 BCF 1 Dual Over wing EmergencyExit Auxiliary Sill at Frame Intersect241, 242300BCF<4>Type 250,000 Cycles53-50-I22 BCF 2 Dual Over wing Emergency Exit Auxiliary Sill241, 242300BCF<4>Type 250,000 Cycles53-50-I22C Dual Emergency ExitCutout – Sill Inner Chord241, 242200300 PASSType 250,000 Cycles53-50-I22D Dual Emergency Exit Cutout– Sill Inner Chord at Frame Intersect241, 242200300 PASSType 250,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4953-50-I22E Dual Emergency ExitCutout – Upper Sill Inner Chord at BS 859.5 and BS 903.5241, 242 300 PASS Type 250,000 Cycles53-50-I22F Dual Emergency ExitCutout – Sill Outer Chord241, 242 200300 PASSType 250,000 Cycles53-50-I22G Dual EmergencyExit Cutout – Sill OuterChord at Frame Intersect241, 242 200300 PASSType 250,000 Cycles53-50-I25A Single Aft Emergency Exit Cutout – Frame Inner Chords241, 242 300 PASS Type 250,000 Cycles53-50-I25B Single Aft Emergency Exit Cutout– Frame Inner Chord at Sill Intersect241, 242300 PASSType 250,000 Cycles53-50-I25C Single Aft Emergency Exit Cutout – Sill Inner Chord241, 242300 PASSType 250,000 Cycles53-50-I25D Single Aft Emergency Exit Cutout– Sill Inner Chord at Frame Intersect241, 242300 PASSType 250,000 Cycles53-50-I25E Single Aft Emergency Exit Cutout – Upper Sill Inner chord BS 903.5241, 242300 PASSType 250,000 Cycles53-50-I25F Single Aft Emergency Exit Cutout – Sill Outer Chord241, 242300 PASSType 250,000 Cycles53-50-I25G Single Aft Emergency Exit Cutout– Sill Outer Chord at Frame Intersect241, 242300 PASSType 250,000 Cycles53-50-I28 Section 45 Stub Frames – BS 808 – 933 Frame Inner Chord at Stub Beam131, 132400EType 240,000 Cycles53-60-I02 BCF – Fuselage Stringer with Stringer Reinforcement Strap STA 1076 to 1143STR-10R to 13R and STR -9L to 13L153, 154300BCFType 240,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-50767 MAINTENANCE PLANNING DATA53-60-I06B Aft Main Cargo Door Cutout – EdgeFrames – Inner Chord at BS 1270, S-23R toS-29R and at BS 1346, S-23R to S-29R154 200SF300BCFPASSType 250,000 Cycles (200, 300 PASS)40,000 Cycles(200SF, 300BCF, 400E)53-60-I06C BCF – Aft Main Cargo Door – Edge Frame BS 1270 and 1346, Outer Chord BetweenUpper and Lower Sills153, 154 300BCF Type 250,000 Cycles53-60-I06C53-30-I14CForward/Aft Main Cargo Door Cutout –Edge Frames – Outer Chord at BS 539.5,BS 615 and BS 1270, BS 1346 between Upper and Lower Sills122, 154200SFPASSType 250,000 Cycles (200, 300 PASS)40,000 Cycles (200SF, 400E)53-60-I06D53-30-I14DForward/Aft Main Cargo Door Cutout – Upper Main Sill – Inner Chord, BS 522 toBS 544 and BS 1346 to BS 1395122, 154200SF300BCFPASSType 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (200SF, 400E)53-60-I06E53-30-I14EForward/Aft Main Cargo Door Cutout – Lower Main Sill – Inner Chord, BS 610 toBS 632 and BS 1263 to BS 1270122, 154200SFPASSType 250,000 Cycles(200, 200SF, 300 PASS)40,000 Cycles (400E)53-60-I06E BCF 1 – Aft Main Cargo Door Cutout– Lower Sill Inner Chord at Body STA 1263 toSTA 1270153, 154300BCFType 250,000 Cycles53-60-I10 BCF 2 – Bulk Cargo Door Cutout – Edge Frames Inner Chord/Strap161, 163200SF300BCF<4>Type 250,000 Cycles53-60-I10A Bulk Cargo Door Cutout– Edge Frames Inner Chord/Strap161, 163ALLType 250,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)53-60-I10B Bulk Cargo Door Cutout – FrameSplice – Aft Edge Frame, BS 1461 Inner Chordat S-26161ALLType 250,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5153-60-I10C Bulk Cargo Door Cutout – UpperMain Sill Inner Chord and Strap – BS 1461161 300F<2>Type 240,000 Cycles53-60-I14E Aft Passenger Entry/Service Door Cutout – Edge Frames, Inner Chord, Door Station876.3, S-9 to S-12 and S-17 to S-23 and Door Station 923.7, S-8 to S-13 and S-21to S-23251, 252 200SF300BCFPASSType 250,000 Cycles(200, 200SF, 300 PASS)40,000 Cycles (300BCF, 400E)53-60-I14F Aft Passenger Entry/Service Door Cutout – Upper Main Sill – Inner Chord, DoorStation 911 to BS 1562251, 252 200SF300BCF300 PASSType 250,000 Cycles(200, 200SF, 300 PASS)40,000 Cycles (300BCF, 400E)53-60-I27A Type I Door Cutout –Edge Frame – Inner Chord – BS 1153, S-8 to S-13 & S-16 toS-23 and BS 1183.4, S-8 to S-13 and S-16 to S-23153, 154, 251,252300 PASSType 250,000 Cycles53-60-I27A Type I Door Cutout –Edge Frame – Inner Chord – BS 1153, S-8 to S-13 & S-16 toS-23 and BS 1183.4, S-8 to S-13 and S-16 to S-23153, 154, 251,252400EType 240,000 Cycles53-60-I27B Type I Door Cutout – Upper MainSill – Inner Chord, BS 1131 to BS 1197+22251, 252300 PASS400EType 250,000 Cycles (300 PASS)40,000 Cycles (400E)53-60-I27C Type I Door Cutout – Lower MainSill – Inner Chord, BS 1131 to BS 1175251, 252300 PASS400EType 250,000 Cycles (300 PASS)40,000 Cycles (400E)53-60-I29A Aft Large Cargo Door Cutout –Edge Frame – Inner Chord, BS 1344, S-24154300F<2>Type 240,000 Cycles53-60-I29B Aft Large Cargo Door Cutout –Edge Frame – Inner Chord, BS 1344, S-24.3154300F<2>Type 240,000 Cycles53-60-I29C Aft Large Cargo Door Cutout– Upper Main Sill – Inner Chord, BS 1219154300F<2>Type 240,000 Cycles53-60-I29D Aft Large Cargo Door Cutout– Lower Main Sill – Inner Chord, BS 1344154, 156300F<2>Type 240,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-52767 MAINTENANCE PLANNING DATA53-60-I29F Aft Large Cargo Door Cutout – Lower Main Sill – Inner Chord, BS 1334.3154, 156 300F<2>Type 240,000 Cycles53-60-I30A Aft Large Cargo Door Cutout– Latch Backup Fitting – BS 1331.58 Latch 12Lower Flange154 300F<2>Type 240,000 Cycles53-80-I01A Aft Pressure Bulkhead – Circumferential Attachment of Web to Y-Ring165, 166, 251,252, 253, 254ALLL/N 424 & on<1>Type 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I01B BS 1582 Pressure Bulkhead – Radial Web Lap Splices - BS 1582 (Fwd Web)311, 312 ALLL/N 424 & on<1>Type 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I01C BS 1582 Pressure Bulkhead – Radial Web Lap Splices - BS 1582 (Aft Web)311, 312ALLL/N 424 & on<1>Type 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I01D BS 1582 Pressure Bulkhead – Circumferential Tear Strap Splices - BS 1582(Fwd Tear Strap)311, 312ALLL/N 424 & on<1>Type 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I01E BS 1582 Pressure Bulkhead – Circumferential Tear Strap Splices - BS 1582(Aft Tear Strap)311, 312ALLL/N 424 & on<1>Type 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I03 Section 48 – Jackscrew FittingLug – Upper Bulkhead at STA 1702311, 312200SFType 150,000 Cycles53-80-I03 Section 48 – Jackscrew FittingLug – Upper Bulkhead at STA 1702311, 312 300BCF, 300FPASSType 150,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I13 Section 48 – Pivot Fitting Lug313, 314200SFType 138,600 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5353-80-I13 Section 48 – Pivot Fitting Lug313, 314 300BCF, 300FPASSType 150,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I1553-80-I1653-80-I17BS 1809.5 Bulkhead Outboard ChordDTR Check Form not applicable to -200SF. Must inspect per SB 767-53A0078Revision 6 or later.313, 314 ALLL/N 710 & on<1>Except for 200SFType 125,000 Cycles53-80-I25 Horizontal Stabilizer Fitting Hinge Pins – BS 1809, BL 41.5313, 314 ALL Type 125,000 Cycles54-50-I01 Typical Midspar Chord Construction – JT9D Strut432, 434, 436,442, 444, 4467R4Type 250,000 Cycles54-50-I01 Typical Midspar Chord Construction – PW4000 Strut432, 434, 436,442, 444, 4464000Type 225,000 Cycles54-50-I01 Typical Midspar Chord Construction – CF6-80A Strut432, 434, 436,442, 444, 44680AType 250,000 Cycles54-50-I01 Typical Midspar Chord Construction – CF6-80C Strut432, 434, 436,442, 444, 44680C (Except 400E)Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F)54-50-I01a Forward Midspar Chord – CF6-80C Strut432, 442 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I01a Forward Midspar Chord – CF6-80C Strut432, 442 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I01c Forward Midspar (Visible Portions) – CF6-80C2 Strut432, 442 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I01c Forward Midspar (Visible Portions) – CF6-80C2 Strut432, 442 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-54767 MAINTENANCE PLANNING DATA54-50-I0254-50-I03aSideskins/Skins, Stiffeners and Back-Up Chords – RB211 Strut433, 443 524<2>Type 250,000 Cycles54-50-I03b Lower Spar Chords, Webs and Thrust Plate – RB211 Strut431, 433, 441,443524<2>Type 225,000 Cycles54-50-I04 Forward Engine Mount Bulkhead – RB211 Strut433, 443 524<2>Type 250,000 Cycles54-50-I04 Typical Midspar Chord Construction – JT9D StrutNote: No DTR Check Form.432, 434, 436,442, 444, 4467R4 Type 250,000 Cycles54-50-I04 Typical Midspar Chord Construction – PW4000 StrutNote: No DTR Check Form.432, 434, 436,442, 444, 4464000Type 225,000 Cycles54-50-I04 Typical Midspar Chord Construction – CF6-80A StrutNote: No DTR Check Form.432, 434, 436,442, 444, 44680AType 250,000 Cycles54-50-I04 Typical Midspar Chord Construction – CF6-80C StrutNote: No DTR Check Form.432, 434, 436,442, 444, 44680C (Except 400E)Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F)54-50-I04a Mid-Spar Fitting to Chord Splice – CF6-80C Strut434, 436, 444,44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I04a Mid-Spar Fitting to Chord Splice – CF6-80C Strut434, 436, 444,44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I04c Mid-Spar Chord, Aft (Hidden Details) – CF6-80C Strut434, 436, 444,44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I04c Mid-Spar Chord, Aft (Hidden Details) – CF6-80C Strut434, 436, 444,44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I04e Mid-Spar Chord, Aft (Visible Details) – CF6-80C Strut434, 436, 444,44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5554-50-I04e Mid-Spar Chord, Aft (Visible Details) – CF6-80C Strut434, 436, 444,44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – JT9D Strut432, 442 7R4<2>Type 250,000 Cycles54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – PW4000 Strut432, 442 4000<2>Type 250,000 Cycles54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – CF6-80A Strut432, 442 80A<2>Type 250,000 Cycles54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – CF6-80C Strut432, 442 80C (Except 400E)<2>Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F)54-50-I05a Forward Engine Mount Fitting Thrust Tang – CF6-80C Strut432, 442 80C (400E)<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I06 Aft Engine Mount Bulkhead – JT9D Strut434, 436, 444,4467R4 Type 250,000 Cycles54-50-I06 Aft Engine Mount Bulkhead – PW4000 Strut434, 436, 444,4464000 Type 250,000 Cycles54-50-I06 Aft Engine Mount Bulkhead – CF6-80A Strut436, 437, 446,44780A Type 250,000 Cycles54-50-I06 Aft Engine Mount Bulkhead – CF6-80C Strut436, 437, 446,44780C (Except 400E) Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F)54-50-I06a Aft Engine Mount Bulkhead (Barrel Nut Bore) – CF6-80C Strut436, 437, 446,44780C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I06a Aft Engine Mount Bulkhead (Barrel Nut Bore) – CF6-80C Strut436, 437, 446,44780C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-56767 MAINTENANCE PLANNING DATA54-50-I06c Aft Engine Mount Bulkhead (Vertical Splice Strap) – CF6-80C Strut436, 437, 446,44780C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I06c Aft Engine Mount Bulkhead (Vertical Splice Strap) – CF6-80C Strut436, 437, 446,44780C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I06d Aft Engine Mount Bulkhead (Aft Flange) – CF6-80C Strut436, 437, 446,44780C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I06d Aft Engine Mount Bulkhead (Aft Flange) – CF6-80C Strut436, 437, 446,44780C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting – JT9D StrutNote: No DTR Check Form.437, 447 7R4 Type 250,000 Cycles54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting – PW4000 StrutNote: No DTR Check Form.437, 447 4000 Type 250,000 Cycles54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting – CF6-80A StrutNote: No DTR Check Form.437, 447 80A Type 250,000 Cycles54-50-I08 Diagonal Brace and Lower Spar Attachment Fitting – CF6-80C StrutNote: No DTR Check Form.437, 447 80C (Except 400E) Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F)54-50-I09 Midspar Fitting – JT9D StrutNote: No DTR Check Form.437, 447 7R4 Type 250,000 Cycles54-50-I09 Midspar Fitting – PW4000 StrutNote: No DTR Check Form.437, 447 4000 Type 250,000 Cycles54-50-I09 Midspar Fitting – CF6-80A StrutNote: No DTR Check Form.437, 447 80A Type 250,000 Cycles54-50-I09 Midspar Fitting – CF6-80C StrutNote: No DTR Check Form.437, 447 80C (Except 400E) Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5754-50-I09 Diagonal Brace and Strut Attach Fitting and Fuse Pins – RB211 StrutNote: No DTR Check Form.434, 444 524 Type 250,000 Cycles54-50-I09a54-50-I0754-50-I0854-50-I12Strut to Wing Attachments (Midspar Fitting) – CF6-80C Strut431, 433, 437,441, 443, 447,511, 521, 611,62180C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I09a54-50-I0754-50-I0854-50-I12Strut to Wing Attachments (Midspar Fitting) – CF6-80C Strut431, 433, 437,441, 443, 447,511, 521, 611,62180C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I10 Aft Upper Spar Fittings and Fuse Pins – RB211 StrutNote: No DTR Check Form.434, 444 524<2>Type 250,000 Cycles54-50-I10a Forward Engine Mount (Platform at Forward Tension Bolt Holes) – CF6-80C Strut410, 420 80C (400E)< 8 HoursType 1/16,000 Cycles/70,000 Flt. Hrs.54-50-I10a Forward Engine Mount (Platform at Forward Tension Bolt Holes) – CF6-80C Strut410, 420 80C (400E)>8 HoursType 1/16,000 Cycles/70,000 Flt. Hrs.54-50-I10b Forward Engine Mount – CF6-80C Strut410, 420 80C (400E)< 8 Hours<2>Type 1/16,000 Cycles/70,000 Flt. Hrs.54-50-I10b Forward Engine Mount – CF6-80C Strut410, 420 80C (400E)>8 Hours<2>Type 1/16,000 Cycles/70,000 Flt. Hrs.54-50-I11 Side Link and Strut Attach Fittings – RB211 StrutNote: No DTR Check Form.434, 444524Type 250,000 Cycles54-50-I11d Aft Engine Mount (Lugs) – CF6-80C Strut410, 420 80C (400E)< 8 HoursType 1/25,000 Cycles/80,000 Flt. Hrs.54-50-I11d Aft Engine Mount (Lugs) – CF6-80C Strut410, 420 80C (400E)>8 HoursType 1/25,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-58767 MAINTENANCE PLANNING DATA54-50-I11f Aft Engine Mount (Engine TRF Clevis Lugs) – CF6-80C Strut410, 420 80C (400E)< 8 HoursType 1/16,000 Cycles/70,000 Flt. Hrs.54-50-I11f Aft Engine Mount (Engine TRF Clevis Lugs) – CF6-80C Strut410, 420 80C (400E)>8 HoursType 1/16,000 Cycles/70,000 Flt. Hrs.54-50-I12 Side Load Links – JT9D StrutNote: No DTR Check Form.437, 447 7R4 Type 250,000 Cycles54-50-I12 Side Load Links – PW4000 StrutNote: No DTR Check Form.437, 447 4000 Type 250,000 Cycles54-50-I12 Side Load Links – CF6-80A StrutNote: No DTR Check Form.437, 447 80A Type 250,000 Cycles54-50-I12 Side Load Links – CF6-80C StrutNote: No DTR Check Form.437, 447 80C (Except 400E) Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F)54-50-I12b SideLoad Fittings – CF6-80C Strut437, 447 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I12b SideLoad Fittings – CF6-80C Strut437, 447 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I13 Typical Lower Spar Chord and Spar Web Construction – JT90 Strut434, 436444, 4467R4<2>Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F)54-50-I13 Typical Lower Spar Chord and Spar Web Construction – CF6-80A Strut434, 436444, 44680A<2>Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F)54-50-I13 Typical Lower Spar Chord and Spar Web Construction – PW4000 Strut434, 436444, 4464000<2>Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5954-50-I13 Typical Lower Spar Chord and Spar Web Construction – CF6-80C Strut434, 436444, 44680C (Except 400E)<2>Type 250,000 Cycles (200, 300 PASS)40,000 Cycles (300F)54-50-I13a Lower Spar Chord and Web (Hidden) – CF6-80C Strut434, 436444, 44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I13a Lower Spar Chord and Web (Hidden) – CF6-80C Strut434, 436444, 44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I13e Lower Spar Chord (Visible) – CF6-80C Strut434, 436444, 44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I14 Mid Bulkhead – Upper Fitting (R1) Joint – CF6-80C Strut432, 434, 436,442, 444, 44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I14 Mid Bulkhead – Upper Fitting (R1) Joint – CF6-80C Strut432, 434, 436,442, 444, 44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I16a Forward Upper Spar (Hidden) – CF6-80C Strut432, 442 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I16a Forward Upper Spar (Hidden) – CF6-80C Strut432, 442 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I16e Forward Upper Spar (Visible) – CF6-80C Strut432, 442 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I17a Aft Upper Spar Chord (Vertical Flange, Hidden) – CF6-80C Strut434, 436444, 44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-60767 MAINTENANCE PLANNING DATA54-50-I17a Aft Upper Spar Chord (Vertical Flange, Hidden) – CF6-80C Strut434, 436444, 44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I17c Aft Upper Spar Chord (Vertical Flange, Shear Tie at NSTA 279 RHS) – CF6-80C Strut434, 436444, 44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I17c Aft Upper Spar Chord (Vertical Flange, Shear Tie at NSTA 279 RHS) – CF6-80C Strut434, 436444, 44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I17e Aft Upper Spar Chord (Vertical Flange, Visible RHS) – CF6-80C Strut434, 436444, 44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I17e Aft Upper Spar Chord (Vertical Flange, Visible RHS) – CF6-80C Strut434, 436444, 44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I17f Aft Upper Spar Chord (Vertical Flange, Visible) – CF6-80C Strut434, 436444, 44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I17f Aft Upper Spar Chord (Vertical Flange, Visible) – CF6-80C Strut434, 436444, 44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I18 Side Skin/Aft Upper Spar Chord Stiffener – CF6-80C Strut434, 436444, 44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I18 Side Skin/Aft Upper Spar Chord Stiffener – CF6-80C Strut434, 436444, 44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.55-10-I09 Horizontal Stabilizer Upper Skin – At BBL 41.5 Side of Body Splice331, 341 ALL Except 200SFType 150,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6155-10-I09A Horizontal Stabilizer Upper Skin – At BBL 41.5 Side of Body SpliceNote: No DTR Check Form331, 341 200SF Type 150,000 Cycles55-10-I13A Horizontal Stabilizer Pivot Fitting Lug331, 341 ALL Except 200SF Type 150,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)55-10-I13B Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments331, 341 ALL Except 200SF Type 125,000 Cycles55-10-I13C Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments331, 341 ALL Except 200SF Type 125,000 Cycles55-10-I13D Horizontal Stabilizer Pivot Fitting LugNote: No DTR Check Form.331, 341200SFType 150,000 Cycles55-10-I13E Horizontal Stabilizer Pivot Fitting – Upper and Lower AttachmentsNote: No DTR Check Form.331, 341200SFType 125,000 Cycles55-10-I14A Horizontal Stabilizer – Jackscrew Fitting Lug331, 341 ALL Except 200SFType 150,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)55-10-I14B Horizontal Stabilizer Jackscrew Fitting – Upper and Lower Attachments331, 341 ALL Except 200SFType 150,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)55-10-I14C Horizontal Stabilizer Jackscrew Fitting LugNote: No DTR Check Form.331, 341200SFType 150,000 Cycles55-10-I14D Horizontal Stabilizer Jackscrew Fitting – Upper and Lower AttachmentsNote: No DTR Check Form.331, 341200SFType 150,000 Cycles55-10-I31 Horizontal Stabilizer RearSpar Upper Chord – SOB Hidden Area331, 341 ALL Except 200SFType 150,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-62767 MAINTENANCE PLANNING DATA55-10-I31A Horizontal Stabilizer RearSpar Upper Chord – SOB Hidden AreaNote: No DTR Check Form.331, 341 200SF Type 150,000 Cycles55-10-I31B Horizontal Stabilizer Upper SkinNote: No DTR Check Form.334, 344 200SF Type 150,000 Cycles57-10-I01 Typical Stringer and Skin – Wing Center Section, Lower Surface at External LowerBeams (BBL 9.5 and BBL 62.0)133, 134400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I01 Typical Stringer and Skin – Wing Center Section, Lower Surface at External LowerBeams (BBL 9.5 and BBL 62.0)133, 134400E>8 HourType 125,000 Cycles/80,000 Flt. Hrs.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 BodyRibs, Splices, Lower Surface Access HoleCutout and Adjacent Stringers, and Drain.Note: No DTR Check Form.133,134 300BCF Type 150,000 Cycles/70,000 Flt. Hrs.57-10-I01B Wing Center Section – Upper andLower Surfaces, Rear Spar, Beams and AccessDoor Cutouts, Lower Surface Beams, Side of Body Ribs, Splices, Lower SurfaceAccess Hole Cutout and Adjacent Stringers, and Drain.Note: No DTR Check Form.133, 134 200SF Type 150,000 Cycles/70,000 Flt. Hrs.57-10-I01C.1 Typical Stringer - Wing Center Section - Typical - In Areas of Attach FastenersBetween Left and Right WBL 97.9133, 134300FType 125,000 Cycles / 80,000 Flt Hrs57-10-I01C.2 Typical Stringer and Skin - Wing Center Section - Lower Surface - Stringers 1, 2 and 5at External Beams (BL 9.5 and BL 62)133, 134,135, 136300FType 125,000 Cycles / 80,000 Flt Hrs57-10-I02 Splice Stringer and Skin – Wing Center Section at Stringer 6 and 10133, 134300FType 140,000 Cycles57-10-I02 Splice Stringer and Skin - WingCenter Section at Stringer 6 and 10133, 134400EType 125,000 Cycles/80,000 Flt. Hrs.57-10-I02A Front Spar Lower Chord and Skin– Wing Center Section at Radius Fillers133, 134 ALL Except 200SF,300BCF< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6357-10-I02A Front Spar Lower Chord and Skin– Wing Center Section at Radius Fillers133, 134 ALL Except 200SF,300BCF>8 HourType 125,000 Cycles/80,000 Flt. Hrs.57-10-I02B Front Spar Lower Chord and Skin –Wing Center Section at Underwing Longeron133, 134400E< 8 Hours<2>Type 1, FLSSee Graph57-10-I02B Front Spar Lower Chord and Skin –Wing Center Section at Underwing Longeron133, 134400E>8 Hours<2>Type 1, FLSSee Graph57-10-I02C Wing Center Section –Lower Surface Splice Stringers L-6 and L-10 in Areas of AttachFasteners Between Left and Right WBL 97.9.Note: No DTR Check Form.133, 134300BCFType 150,000 Cycles/70,000 Flt. Hrs.57-10-I02D Wing Center Section –Lower Surface Splice Stringers L-6 and L-10 in Areas of AttachFasteners Between Left and Right WBL 97.9.Note: No DTR Check Form.133, 134200SFType 150,000 Cycles/70,000 Flt. Hrs.57-10-I03A Rear Spar Lower Chord and Skin - Wing Center Section – Typical - BBL 23.0 toInboard Edge of Terminal Fitting133, 134PASS(200ER, 300ER)< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I03A Rear Spar Lower Chord and Skin - Wing Center Section – Typical - BBL 23.0 toInboard Edge of Terminal Fitting133, 134 PASS (200ER, 300ER)>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I03A Rear Spar Lower Chord and Skin - Wing Center Section – Typical - BBL 23.0 toInboard Edge of Terminal Fitting133, 134 300F Type 125,000 Cycles/80,000 Flt. Hrs.57-10-I03A Rear Spar Lower Chord and Skin - Wing Center Section - Inboard Edge of LeftTerminal Fitting to Inboard Edge of Right Terminal Fitting133, 134 400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I03A Rear Spar Lower Chord and Skin - Wing Center Section - Inboard Edge of LeftTerminal Fitting to Inboard Edge of Right Terminal Fitting133, 134 400E>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I03A Rear Spar Lower Chord - Wing Center Section - Typical - BBL 23.0 to Inboard Edge ofTerminal Fitting.Note: No DTR Check Form.133, 134200SF300BCFType 150,000 Cycles/70,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-64767 MAINTENANCE PLANNING DATA57-10-I03B Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations- BBL 49.5, 62.05 and 73.0133, 134 PASS(200ER, 300ER)< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I03B Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations- BBL 49.5, 62.05 and 73.0133, 134PASS(200ER, 300ER)>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I03B Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations- BBL 49.5, 62.05 and 73.0133, 134300FType 125,000 Cycles/80,000 Flt. Hrs.57-10-I03C Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations- BBL 49.5, 62.05 and 73.0133, 134PASS(200ER, 300ER)< 8 HoursType 1, FLSSee Graph57-10-I03C Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations- BBL 49.5, 62.05 and 73.0133, 134 PASS (200ER, 300ER)>8 HoursType 1, FLSSee Graph57-10-I03C Rear Spar Lower Chord and Skin – Wing Center Section – Hidden Locations- BBL 49.5, 62.05 and 73.0133, 134 300F Type 1, FLSSee Graph57-10-I03C Rear Spar Lower Chord - Wing CenterSection - Hidden Locations - BBL 49.5, 62.05and 73.0Note: No DTR Check Form133, 134 200SF, 300BCFType 150,000 Cycles/70,000 Flt. Hrs.57-10-I08 Rear Spar Web - Wing Center Section - Wing BBL 62.0 - 97.9 and LBL 11.0 - RBL11.0133, 134400E< 8 HoursType 125,000 Cycles/70,000 Flt. Hrs.57-10-I08 Rear Spar Web - Wing Center Section - Wing BBL 62.0 - 97.9 and LBL 11.0 - RBL11.0133, 134400E>8 HoursType 125,000 Cycles/70,000 Flt. Hrs.57-10-I16B Lower Surface Side-Of-Body Splice (Sections 11 and 12) - Stringer 1 to Stringer 10Inboard and Outboard of BBL 97.42193, 194 ALL Except 200SF,300BCF< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I16B Lower Surface Side-Of-Body Splice (Sections 11 and 12) - Stringer 1 to Stringer 10Inboard and Outboard of BBL 97.42193, 194 ALL Except 200SF,300BCF>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6557-10-I16C Wing Lower Surface Side-of-Body Splice (Sections 11 and 12) – Stringer 1 toStringer 10 Inboard and Outboard of BBL 97.42.Note: No DTR Check Form.193, 194300BCFType 1,25,000 Cycles/ 80,000 Flt. Hrs.57-10-I16D Wing Lower Surface Side-of-Body Splice (Sections 11 And 12) – Stringer 1 toStringer 10 Inboard and Outboard of BBL 97.42.Note: No DTR Check Form.193, 194200SFType 1,25,000 Cycles/ 80,000 Flt. Hrs.57-10-I20 Rear Spar Lower Chord SOB Splice (Sections 11 and 12) – Chords at Splice FittingsInboard and Outboard of BBL 97.42143, 144 ALL Except 200SF,300BCF< 8 HoursType 1, FLSSee Graph57-10-I20 Rear Spar Lower Chord SOB Splice (Sections 11 and 12) – Chords at Splice FittingsInboard and Outboard of BBL 97.42143, 144 ALL Except 200SF,300BCF>8 HoursType 1, FLSSee Graph57-10-I20A Rear Spar Lower Chord SOB Splice (Sections 11 and 12) – Chords at Splice FittingsInboard and Outboard of BBL 97.42Note: No DTR Check Form.143, 144300BCFType 150,000 Cycles/70,000 Flt. Hrs.57-10-I20B Rear Spar Lower Chord SOB Splice (Sections 11 and 12) – Chords at Splice FittingsInboard and Outboard of BBL 97.42.Note: No DTR Check Form.143, 144200SFType 150,000 Cycles/70,000 Flt. Hrs.57-10-I24 Underwing Longeron Attachment (Center Section Structure) – BBL 70 Longeron fromFront Spar Lower Chord to Stringer 18193, 194PASS(200ER, 300ER)300F< 8 HoursType 1, FLSSee Graph57-10-I24 Underwing Longeron Attachment (Center Section Structure) – BBL 70 Longeron fromFront Spar Lower Chord to Stringer 18193, 194PASS(200ER, 300ER)300F>8 HoursType 1, FLSSee Graph57-10-I24A Underwing Longeron Attachment - Wing Center Section - Hidden Locations - BBL 70Longeron from Front Spar Lower Chord to Stringer 18Note: No DTR Check Form.193, 194300BCFType 150,000 Cycles/70,000 Flt. Hrs.57-10-I24B Underwing Longeron Attachment - Wing Center Section - Hidden Locations - BBL 70Longeron from Front Spar Lower Chord to Stringer 18Note: No DTR Check Form.193, 194200SFType 150,000 Cycles/70,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-66767 MAINTENANCE PLANNING DATA57-10-I25 Rear Spar Lower Chord and Skin – Wing Center Section at Stiffener Clips atBBL 32.9, 40.2, 47.5, 54.7 and 62133, 134 400E< 8 Hours<2>Type 125,000 Cycles/80,000 Flt. Hrs.57-10-I25 Rear Spar Lower Chord and Skin – Wing Center Section at Stiffener Clips atBBL 32.9, 40.2, 47.5, 54.7 and 62133, 134400E>8 Hours<2>Type 125,000 Cycles/80,000 Flt. Hrs.57-20-I03A Rear Spar Lower Chord and Web - Outboard Wing Structure - Typical Details BetweenRib 12 and Rib 19532, 541,551, 561,632, 641,651, 661400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I03A Rear Spar Lower Chord and Web - Outboard Wing Structure - Typical Details BetweenRib 12 and Rib 19532, 541,551, 561,632, 641,651, 661400E>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I03B Rear Spar Lower Chord and Web - Outboard Wing Structure - Hidden Details atExternal Stiffeners and Fittings Between Rib 12 and Rib 19532, 541,551, 561,632, 641,651, 661400E< 8 HoursType 1, FLSSee Graph57-20-I03B Rear Spar Lower Chord and Web - Outboard Wing Structure - Hidden Details atExternal Stiffeners and Fittings Between Rib 12 and Rib 19532, 541,551, 561,632, 641,651, 661400E>8 HoursType 1, FLSSee Graph57-20-I05 Rear Spar at Forward MLG Trunnion – Rib 5, WS 329.10532, 632551, 651400E< 8 Hours<2>Type 1, FLSSee Graph57-20-I05 Rear Spar at Forward MLG Trunnion – Rib 5, WS 329.10532, 632551, 651400E>8 Hours<2>Type 1, FLSSee Graph57-20-I06 Rear Spar at MLG Outboard Support – Rib 7, WS 372.20532, 632551, 651400E< 8 Hours<2>Type 1, FLSSee GraphAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6757-20-I06 Rear Spar at MLG Outboard Support – Rib 7, WS 372.20532, 632551, 651400E>8 Hours<2>Type 1, FLSSee Graph57-20-I07 Rear Spar at Flap/Spoiler Backup Fitting Installation – Lower Chord Rib Bay 16,WS 605.50551, 651 400E, and All AirplaneTypes, L/N 922 andlaterType 1, FLSSee Graph(200, 300PASS,300F L/N 922 and Later, 400E)50,000 Cycles/ 70,000 Flt Hrs(200SF, 300BCF L/N 922and later)57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: Stringer 16 (Dry Bay) underNacelle Fairing437, 447533, 633ALL Except 200SF,300BCF, and 400E< 8 HoursType 1, FLSSee Graph57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: Stringer 16 (Dry Bay) underNacelle Fairing437, 447533, 633ALL Except 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: L-16 (Dry Bay) underNacelle Fairing533, 633400E< 8 HoursType 1, FLSSee Graph57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: L-16 (Dry Bay) underNacelle Fairing533, 633400E>8 HoursType 1, FLSSee Graph57-20-I12B Outboard Wing Typical Stringers Lower Surface – Rib 9: L-17 at Outboard Side LoadFitting under Nacelle Fairing533, 633 ALL Except 200SF,300BCF, and 400E< 8 HoursType 1, FLSSee Graph57-20-I12B Outboard Wing Typical Stringers Lower Surface – Rib 9: L-17 at Outboard Side LoadFitting under Nacelle Fairing533, 633 ALL Except 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I12B Outboard Wing Typical Stringers Lower Surface – Rib 9: L-17 at Outboard Side LoadFitting under Nacelle Fairing533, 633400E< 8 HoursType 1, FLSSee Graph57-20-I12B Outboard Wing Typical Stringers Lower Surface – Rib 9: L-17 at Outboard Side LoadFitting under Nacelle Fairing533, 633400E>8 HoursType 1, FLSSee GraphAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-68767 MAINTENANCE PLANNING DATA57-20-I12C Outboard Wing Lower Surface Typical StringerNote: No DTR Check Form.193, 194437, 447530, 630540, 640533, 633200SF300BCFType 150,000 Cycles/70,000 Flt Hrs.57-20-I15A Outboard Wing Lower Surface Splice Stringer – L-6 and 10. L-10 between Rib 7 and20 (except under Nacelle Fairing) & L-6: SOB to Rib 3530, 630531, 631532, 632540, 640541, 641ALL Except 200SF,300BCF< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15A Outboard Wing Lower Surface Splice Stringer – L-6 and 10. L-10 between Rib 7 and20 (except under Nacelle Fairing) & L-6: SOB to Rib 3530, 630531, 631532, 632540, 640541, 641ALL Except 200SF,300BCF>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15B Outboard Wing Lower Surface Splice Stringer – L-10 under Nacelle Fairing532, 541632, 641ALL Except 200SF,300BCF< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15B Outboard Wing Lower Surface Splice Stringer – L-10 under Nacelle Fairing532, 541632, 641ALL Except 200SF,300BCF>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15C Outboard Wing Lower Surface Splice Stringer – L-6, 10 and 15 under Nacelle Strut atExternal Doublers, Fittings and Angles532, 632533, 633541, 641ALL Except 200SF,300BCF, and 400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15C Outboard Wing Lower Surface Splice Stringer – L-6, 10 and 15 under Nacelle Strut atExternal Doublers, Fittings and Angles532, 632533, 633541, 641ALL Except 200SF,300BCF, and 400E>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15C Outboard Wing Lower Surface Splice Stringer – L-6 and 10 under Nacelle Strut atExternal Fittings and Skate Angles532, 541632, 641400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15C Outboard Wing Lower Surface Splice Stringer – L-6 and 10 under Nacelle Strut atExternal Fittings and Skate Angles532, 541632, 641400E>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6957-20-I15D Outboard Wing Lower Surface SpliceStringer – L-15 under Nacelle Strut at Rib 9(Seal Pans)437, 447530, 630ALL Except 200SF,300BCF, and 400E< 8 HoursType 1, FLSSee Graph57-20-I15D Outboard Wing Lower Surface SpliceStringer – L-15 under Nacelle Strut at Rib 9(Seal Pans)437, 447530, 630ALL Except 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I15D Outboard Wing Lower Surface SpliceStringer – L-15 under Nacelle Strut at Rib 9(Seal Pans)437, 447530, 630400E< 8 HoursType 1, FLSSee Graph57-20-I15D Outboard Wing Lower Surface SpliceStringer – L-15 under Nacelle Strut at Rib 9(Seal Pans)437, 447530, 630400E>8 HoursType 1, FLSSee Graph57-20-I15E Outboard Wing Lower Surface Splice Stringer – L-6 and 10 at Rib 3530, 630 ALL Except 200SF,300BCF< 8 HoursType 1, FLSSee Graph57-20-I15E Outboard Wing Lower Surface Splice Stringer – L-6 and 10 at Rib 3530, 630 ALL Except 200SF,300BCF>8 HoursType 1, FLSSee Graph57-20-I15F Outboard Wing Lower Surface Splice Stringer – Seal Pan/Baffles atRibs 3, 5, 18 and 31530, 540630, 640400E< 8 Hours<2>Type 125,000 Cycles/80,000 Flt. Hrs.57-20-I15F Outboard Wing Lower Surface Splice Stringer – Seal Pan/Baffles atRibs 3, 5, 18 and 31530, 540630, 640400E>8 Hours<2>Type 125,000 Cycles/80,000 Flt. Hrs.57-20-I15G Outboard Wing Lower Surface Splice Stringer – L-6 at External Nacelle Fitting andOutboard Skate Angle532, 541632, 641400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15G Outboard Wing Lower Surface Splice Stringer – L-6 at External Nacelle Fitting andOutboard Skate Angle532, 541632, 641400E>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15H Outboard Wing Lower Surface Splice Stringer – L-15 at External Nacelle Fitting andOutboard Skate Angle532, 541632, 641400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15H Outboard Wing Lower Surface Splice Stringer – L-15 at External Nacelle Fitting andOutboard Skate Angle532, 541632, 641400E>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-70767 MAINTENANCE PLANNING DATA57-20-I15J Outboard Wing Lower Surface Splice StringersNote: No DTR Check Form.437, 447530, 630531, 631532, 632533, 633540, 640541, 641200SF300BCFType 150,000 Cycles/70,000 Flt. Hrs.57-20-I15K Outboard Wing Lower Surface Splice StringersNote: No DTR Check Form.437, 447531, 631532, 632541, 641200SF300BCFType 125,000 Cycles/80,000 Flt. Hrs.57-20-I16A Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Typical Details betweenFairing at Side-Of-Body & Rib 3531, 631 ALL Except 200SF,300BCF< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I16A Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Typical Details betweenFairing at Side-Of-Body & Rib 3531, 631 ALL Except 200SF,300BCF>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I16B Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden byRib Shear Ties Side-Of-Body to Rib 3531, 631ALL Except 200SF,300BCF, and 400E< 8 HoursType 1, FLSSee Graph57-20-I16B Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden byRib Shear Ties Side-Of-Body to Rib 3531, 631ALL Except 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I16B Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden byRib Shear Ties Side-Of-Body to Rib 3531, 631400E< 8 HoursType 1, FLSSee Graph57-20-I16B Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden byRib Shear Ties Side-Of-Body to Rib 3531, 631400E>8 HoursType 1, FLSSee Graph57-20-I16C Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details atRibs 5, 6, 8 and 9 (Not Covered by Fairings)530, 630 ALL Except 200SF,300BCF, and 400E< 8 HoursType 1, FLSSee Graph57-20-I16C Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details atRibs 5, 6, 8 and 9 (Not Covered by Fairings)530, 630 ALL Except 200SF,300BCF, and 400E>8 HoursType 1, FLSSee GraphAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7157-20-I16C Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details atRibs 5, 6, 8 and 9 (Not Covered by Fairings)530, 630 400E< 8 HoursType 1, FLSSee Graph57-20-I16C Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details atRibs 5, 6, 8 and 9 (Not Covered by Fairings)530, 630 400E>8 HoursType 1, FLSSee Graph57-20-I16D Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Outboard ofTerminal Fitting Wing-to-Body Fairing Area531, 631 ALL Except 200SF,300BCF, and 400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I16D Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Outboard ofTerminal Fitting Wing-to-Body Fairing Area531, 631 ALL Except 200SF,300BCF, and 400E>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I16D Rear Spar Lower Chord and Skin (Outboard Wing Structure) - Details Outboard ofTerminal Fitting Wing-to-Body Fairing Area531, 631400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I16D Rear Spar Lower Chord and Skin (Outboard Wing Structure) - Details Outboard ofTerminal Fitting Wing-to-Body Fairing Area531, 631400E>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I16E Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details –Trunnion, Nacelle and Inboard Flap Fairing Areas530, 540630, 640ALL Except 200SF,300BCF, and 400E< 8 HoursType 1, FLSSee Graph57-20-I16E Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details –Trunnion, Nacelle and Inboard Flap Fairing Areas530, 540630, 640ALL Except 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I16E Rear Spar to Skin, Rib Bay 11, WSTA 449.2 – Hidden Details530, 540630, 640400E< 8 HoursType 1, FLSSee Graph57-20-I16E Rear Spar to Skin, Rib Bay 11, WSTA 449.2 – Hidden Details530, 540630, 640400E>8 HoursType 1, FLSSee Graph57-20-I16F Front Spar Lower Chord and Skin (Outboard Wing Structure) – Lower Skin PanelSplice Location between Ribs 18 and 19 only540,640 ALL Except 200SF,300BCF, and 400E< 8 HoursType 1, FLSSee Graph57-20-I16F Front Spar Lower Chord and Skin (Outboard Wing Structure) – Lower Skin PanelSplice Location between Ribs 18 and 19 only540, 640 ALL Except 200SF,300BCF, and 400E>8 HoursType 1, FLSSee GraphAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-72767 MAINTENANCE PLANNING DATA57-20-I16F Front Spar Lower Chord and Skin (Outboard Wing Structure) - Lower Skin PanelSplice Location between Ribs 18 and 19 only540, 640 400E< 8 HoursType 1, FLSSee Graph57-20-I16F Front Spar Lower Chord and Skin (Outboard Wing Structure) - Lower Skin PanelSplice Location between Ribs 18 and 19 only540, 640 400E>8 HoursType 1, FLSSee Graph57-20-I16G Front Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden byRib Shear Ties Rib 9 to and including Rib 23530, 540630, 640ALL Except 200SF,300BCF, and 400E< 8 HoursType 1, FLSSee Graph57-20-I16G Front Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden byRib Shear Ties Rib 9 to and including Rib 23530, 540630, 640ALL Except 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I16G Front Spar Lower Chord and Skin (Outboard Wing Structure) - Details Hidden by RibShear Ties Rib 9 to and including Rib 23540, 640400E< 8 HoursType 1, FLSSee Graph57-20-I16G Front Spar Lower Chord and Skin (Outboard Wing Structure) - Details Hidden by RibShear Ties Rib 9 to and including Rib 23540, 640400E>8 HoursType 1, FLSSee Graph57-20-I16H Front Spar Lower Chord and Skin(Outboard Wing Structure) - Hidden Details- Ribs 8/9 and at Side Brace Fitting between Ribs 8/9533, 633 ALL Except 200SF,300BCF, and 400E< 8 HoursType 1, FLSSee Graph57-20-I16H Front Spar Lower Chord and Skin(Outboard Wing Structure) - Hidden Details- Ribs 8/9 and at Side Brace Fitting between Ribs 8/9533, 633 ALL Except 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I16H Front Spar Lower Chord and Skin (Outboard Wing Structure) - Hidden Details - Ribs 8/9 and at Side Brace Fitting between Ribs 8/9533, 633400E< 8 HoursType 1, FLSSee Graph57-20-I16H Front Spar Lower Chord and Skin (Outboard Wing Structure) - Hidden Details - Ribs 8/9 and at Side Brace Fitting between Ribs 8/9533, 633400E>8 HoursType 1, FLSSee Graph57-20-I16I Front Spar Lower Chord and Skin – Hidden Details Rib Shear Ties, Rib 24 to andincluding Rib 31540, 640 400E< 8 Hours<2>Type 1, FLSSee Graph57-20-I16I Front Spar Lower Chord and Skin – Hidden Details Rib Shear Ties, Rib 24 to andincluding Rib 31540, 640400E>8 Hours<2>Type 1, FLSSee GraphAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7357-20-I16J Rear Spar Lower Chord and Skin – Hidden Details Rib Shear Ties, Rib 22 up to andincluding Rib 32540, 640 400E< 8 Hours<2>Type 1, FLSSee Graph57-20-I16J Rear Spar Lower Chord and Skin – Hidden Details Rib Shear Ties, Rib 22 up to andincluding Rib 32540, 640400E>8 Hours<2>Type 1, FLSSee Graph57-20-I16K Outboard Wing Lower Surface Front and Rear Spar Chords and SkinNote: No DTR Check Form.530, 630531, 631532, 632533, 633540, 640541, 641200SF300BCFType 150,000 Cycles/70,000 Flt. Hrs.57-20-I16L Wing Rear Spar Lower Chord and Skin(Outboard Wing Structure) – Details Outboardof Terminal Fitting Wing-to- Body Fairing AreaNote: No DTR Check Form.531, 631200SF300BCFType 125,000 Cycles/80,000 Flt. Hrs.57-20-I19 Nacelle Fitting Attachment to LowerSurface – Outboard Wing Lower Surface –WS 436.9, R2 Fitting Forward End at Stringer 5532, 632400E< 8 HoursType 1, FLSSee Graph57-20-I19 Nacelle Fitting Attachment to LowerSurface – Outboard Wing Lower Surface –WS 436.9, R2 Fitting Forward End at Stringer 5532, 632400E>8 HoursType 1, FLSSee Graph57-20-I27 Skin Tab at R1 Nacelle Attachment – Outboard Fitting Aft Fastener Row511, 611 ALL< 8 HoursSee Service Bulletin767-57A011757-20-I27 Skin Tab at R1 Nacelle Attachment – Outboard Fitting Aft Fastener Row511, 611 ALL>8 HoursSee Service Bulletin767-57A011757-20-I36 MLG Forward Trunnion Support to Lower Skin Attachment – Inboard ForwardTrunnion Support, Most Inboard Aft Fastener530, 630 400E Type 125,000 Cycles/80,000 Flt. Hrs.57-53-I02A Outboard Flap Supports – Support Ribs(Rear Spar Fittings) in Bathtub Region, Lug 6Region Flange572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300F L/N 922 andLater, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-74767 MAINTENANCE PLANNING DATA57-53-I02A.1 Outboard Flap Supports – Rear Spar Fittings – Lugs at Joint 1572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 - 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 - 921)40,000 Cycles (300FL/Ns 1 - 921)57-53-I02A.2 Outboard Flap Supports – Rear Spar Fittings – Lugs at Joint 6572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 - 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 - 921)40,000 Cycles (300FL/Ns 1 - 921)57-53-I02A.3 Outboard Flap Supports – Rear Spar Fittings – Lower Aft Flange572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 - 921Type 225,000 Cycles57-53-I02B Outboard Flap Supports – Rear Spar Fitting Tension Bolts – BACB30US12 –Thread Runout572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 922 and Laterand 400E<2>Type 125,000 Cycles57-53-I02B Outboard Flap Supports – Rear Spar Fitting Tension Bolts572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 125,000 Cycles57-53-I02C Outboard Flap Supports – Doublers – .375” Diameter Fastener Holes572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7557-53-I02C Outboard Flap Supports – Rear SparFittings – Actuator Bore and Fastener Holes572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 225,000 Cycles57-53-I02D.1 Outboard Flap Supports – 9-10 Beam – Joint 9 Lug572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I02D.2 Outboard Flap Supports – 9-10 Beam572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I02E Outboard Flap Supports – 9-10 Beam Swivel Fitting572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 125,000 Cycles57-53-I02F Outboard Flap Supports – Flap Attachment Bolts572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 710Type 125,000 Cycles AfterAccomplishing TerminatingAction of SB 767-27A015557-53-I02F Outboard Flap Supports – Flap Attachment Bolts572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 711 – 921Type 125,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-76767 MAINTENANCE PLANNING DATA57-53-I02G.1 Outboard Flap Supports – 6-8-9 Beam (Main Drive Link), 5.38 inches Aft of Joint 6572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300F L/N 922 andLater, 400E)57-53-I02G.1 Outboard Flap Supports – Support No. 1 and No. 2, 6-8-9 beam – Typical Section572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 225,000 Cycles57-53-I02G.2 Outboard Flap Supports – 6-8-9 Beam (Main Drive Link), Lug 8 Region572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300F L/N 922 andLater, 400E)57-53-I02G.2 Outboard Flap Supports – No. 1 and No. 2, 6-8-9 Beam – Lugs 6, 8 and 9572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I02G.3 Outboard Flap Supports – Support No. 1 and No. 2, 6-8-9 Beam – Fastener Holes572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 225,000 Cycles57-53-I02I Outboard Flap Supports – 4-5 Drive Arm – Spline Outer Surface572, 573672, 673ALL<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7757-53-I02J.1 Outboard Trailing Edge Flap Support #1 – Link 3-10 – Lug572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I02J.2 Outboard Trailing Edge Flap Support #2 – Link 3-10 – Lug572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I02L.1 Outboard Trailing Edge Flap Supports – Beam 1-2-3 – Beam at Field Fasteners572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 225,000 Cycles57-53-I02L.2 Outboard Trailing Edge Flap Supports – Beam 1-2-3 – Lug at Joint 1572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I02L.3 Outboard Trailing Edge Flap Supports – Beam 1-2-3 – Lug at Joint 3572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I02M.1 Outboard Flap Supports – Outer Pins at Outboard Supports: Joints 5, 6, 8 and 10 andInboard Supports: Joints 5, 6, 8 and 10572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 125,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-78767 MAINTENANCE PLANNING DATA57-53-I02M.2 Outboard Flap Supports – Outer Pin at Inboard Main Support: Joint 8572, 672 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400EType 125,000 Cycles57-53-I02M.4 Outboard Flap Pins – Support #2 – Outer Pins at Joint 2 and Joint 8572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 - 921Type 125,000 Cycles57-53-I02M.5 Outboard Flap Pins – Support #1 and #2 – Joint #1 Fuse Pin - Pin Shank @ OutboardRib Support572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 - 921Type 125,000 Cycles57-53-I02M.6 Outboard Flap Pins – Support #1, Joints 2, 3, 5, 6, 8, 9, and 10 – Support #2, Joints 3,5, 6, 9, and 10572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 - 921Type 125,000 Cycles57-53-I03E.1 Inboard Flap Box at #3 Support – Backup Fittings – Forward Bathtub555, 655 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 125,000 Cycles57-53-I03E.2 Inboard Flap Box at #3 Support – Backup Fittings – Aft Bathtub End Pads555, 655 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)57-53-I03F Inboard Flap Box at #3 Support – Flap Attachment Bolts, IFS 251.25555, 655 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400EType 125,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7957-53-I03F Inboard flap #3 Support – Flap Attachment Bolts – Shank Location555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 849Type 125,000 Cycles AfterAccomplishing TerminatingAction of SB 767-27A017657-53-I03F Inboard Flap #3 Support – Flap Attachment Bolts – Shank Location555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 850 – 921Type 125,000 Cycles57-53-I03I.1 Inboard Flap Box at #4 Support –Inboard Closure Rib – Lower Chord, IFS 108.5555, 655 ALLType 125,000 Cycles57-53-I03I.2 Inboard Flap Box at #4 Support –Inboard End Rib and Splined Bushing – SplinedBushing Splines555, 655 200, 200SF300BCF, 300F300 PASSL/N 910 and Laterand 400EType 125,000 Cycles57-53-I03I.2 Inboard Flap, Support #4 – Splined Bushing at IFS 108.5 – Internal Spline base ofTooth/Rim555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 1 - 909Type 125,000 Cycles57-53-I03J.1 Inboard Flap Box at #4 Support – Pillow Block (Collar Fitting) Bathtubs IFS 92 –Bathtub End Pads555, 655 200, 200SF300BCF, 300F300 PASSL/N 910 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 910 and Later)40,000 Cycles (300FL/N 910 and Later, 400E)57-53-I03J.2 Inboard Flap Box at #4 Support – Pillow Block (Collar Fitting) Spline Region, IFS 92 –Bathtub End Pads555, 655 200, 200SF300BCF, 300F300 PASSL/N 910 and Laterand 400EType 125,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-80767 MAINTENANCE PLANNING DATA57-53-I03J.2 Inboard Flap Support at #4 –Collar Fitting – Spline Cross-Section555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 909Type 125,000 Cycles57-53-I03K Inboard Flap #4 Support – Attachment Bolts555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 849Type 125,000 Cycles AfterAccomplishing TerminatingAction of SB 767-27A017657-53-I03K Inboard Flap #4 Support – Attachment Bolts555 655 200, 200SF300BCF, 300F300 PASSL/Ns 850 – 921Type 125,000 Cycles57-53-I03L Inboard Flap – #4 Support – TorqueTube – Torque Tube Outer Surface – IFS 92 toIFS 124.5555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 909Type 125,000 Cycles57-53-I03L.1 Inboard Flap Box at #4Support – Torque Tube – IFS 108.5555, 655 200, 200SF300BCF, 300F300 PASSL/N 910 and Laterand 400E<2>Type 125,000 Cycles57-53-I03L.2 Inboard Flap Box at #4 Support – Torque Tube, IFS 92 to IFS 124.5555, 655 200, 200SF300BCF, 300F300 PASSL/N 910 and Laterand 400EType 125,000 Cycles57-53-I04A.1 Inboard Flap #3 Support – Actuator Support Rib Assembly – Section Forward ofJoint 6 Lug571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400EType 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8157-53-I04A.1 Inboard Flap #3 Support – ActuatorSupport Rib – Section Forward of Joint 6 Lug571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I04A.2 Inboard Flap #3 Support – Actuator Support Rib Assembly – Lug Details atJoints 0, 1 and 6571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)57-53-I04A.2 Inboard Flap #3 Support – ActuatorSupport Rib – Lugs at Joints 0, 1, 6571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I04B.2 Inboard Flap #3 Support – Underwing Fitting – Section 9.67Inches Forward ofAftmost Tension Link Lug Bore571, 671 200, 200SF300BCF, 300F300 PASSL/N 883 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 883 and Later)40,000 Cycles (300FL/N 883 and Later, 400E)57-53-I04B.2 Wing Trailing Edge, I/B Flap, #3 Support – Underwing Fitting – Section Through AftMost Field Fastener Row Just Forward of the Fuse Joint571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 882<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 882)40,000 Cycles (300FL/Ns 1 – 882)57-53-I04B.3 Wing Trailing Edge, I/B Flap, #3 Support – Underwing Fitting – Lug at Fuse Pinlocation571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 882<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 882)40,000 Cycles (300FL/Ns 1 – 882)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-82767 MAINTENANCE PLANNING DATA57-53-I04C Wing Trailing Edge, I/B Flap, #3 Support – Fuse Pin – Underwing Fitting to ForwardTension Link571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 882Type 125,000 Cycles57-53-I04D Inboard Flap #3 Support – Forward Tension Link571, 671 200, 200SF300BCF, 300F300 PASSL/N 883 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 883 and Later)40,000 Cycles (300FL/N 883 and Later, 400E)57-53-I04D.1 Wing Trailing Edge, I/B Flap, #3 Support – Forward Tension Link – Section A-A –Typical Cross Section Through Fasteners571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 882Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 882)40,000 Cycles (300FL/Ns 1 – 882)57-53-I04D.2 Wing Trailing Edge, I/B Flap, #3Support – Forward Tension Link – End Clevis571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 882<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 882)40,000 Cycles (300FL/Ns 1 – 882)57-53-I04E Inboard Flap #3 Support – 1-2-3 Beam – Lugs at Joints 1, 2, and 3571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)57-53-I04E.1 Inboard Flap #3 Support – Beam 1-2-3 – Lug at Joint 1571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8357-53-I04E.2 Inboard Trailing Edge Flap Support #3 – Beam 1-2-3 – Lugs at Joint 2 and 3571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I04E.3 Inboard Flap #3 Support – Beam 1-2-3 – Beam at Field Fasteners571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I04F.1 Inboard Flap #3 Support – 3-10 Link – Lugs571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I04F.1 Inboard Flap #3 Support – 3-10 Link – Lugs571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)57-53-I04F.2 Inboard Flap #3 Support – 3-10 Link – Between Lugs571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I04F.2 Inboard Flap #3 Support – 3-10 Link – Between Lugs571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-84767 MAINTENANCE PLANNING DATA57-53-I04H Inboard Flap #3 Support– 6-7-8-9 Beam – Lug 9 Detail571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)57-53-I04H Inboard Flap #3 Support – 6-7-8-9 Beam – Lugs 6, 7, 8 and 9571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I04I Inboard Flap #3 Support – 4-5 Drive Arm – Internal Spline571, 671ALL<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300PASS)40,000 Cycles (300F, 400E)57-53-I04K Inboard Flap #3 Support – 9-10 Beam – Lug at Joint 9571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)57-53-I04K.1 Inboard Flap #3 Support – 9-10 Beam – Joint 9 Lug571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I04K.2 Inboard Flap #3 Support – 9-10 Beam – Section Cut Through Field Fasteners –Section B-B571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 225,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8557-53-I04K.3 Inboard Flap #3 Support – 9-10 Beam571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/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 10571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 125,000 Cycles57-53-I04N.2 Inboard Flap #3 Support – Flap Support Pins – Outer Pins at Joints A and B571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400EType 125,000 Cycles57-53-I04N.3 Inboard Flap #3 Support – Flap Support Pins– Outer Pins at Joints 0, 2, 3, 5, 6, 7, 8,9, 10, A, and B571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 125,000 Cycles57-53-I04N.4 Inboard Flap #3 Support – Flap Support Pins – Outer Pin at Joint 1.571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 125,000 Cycles57-53-I04P Inboard Flap #4 Support – 4-5 Drive Arm – Internal Spline195, 196ALL<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-86767 MAINTENANCE PLANNING DATA57-53-I04Q.1 Inboard Flap #4 Support – 5-7 Link – Lugs195, 196 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)57-53-I04Q.1 Inboard Flap #4 Support – 5-7 Link – Lugs195, 196 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I04Q.2 Inboard Flap #4 Support – 5-7 Link – Cross Section 3.16 inches from Lug195, 196 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)57-53-I04Q.2 Inboard Flap #4 Support – 5-7 Link – Body of Link around Field fasteners195, 196 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/Ns 1 – 921)40,000 Cycles (300FL/Ns 1 – 921)57-53-I04S Inboard Flap #4 Support – 6-7 Drive Arm – Cross Section 7.399 inches fromJoint 7195, 196ALL<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300PASS)40,000 Cycles (300F, 400E)57-53-I04T Inboard Flap #4 Support – 6-9 Drive Arm – Just Aft of the Bend in the Beam195, 196ALL<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8757-53-I04V Inboard Flap #4 Support – Carrier Beam9-11 – Section Forward of Flap Attach and Aftof Flap Attach Bathtub195, 196 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASSL/N 922 and Later)40,000 Cycles (300FL/N 922 and Later, 400E)57-53-I04Y Inboard Flap #4 Support – Flap SupportFitting – Upper Flange Inboard Bolt Location195, 196400EType 240,000 Cycles57-53-I04Y Inboard Flap #4 Support – Side Strut Swivel Support Fitting – Satellite Holes at Lug 6195, 196 200, 200SF300BCF, 300F300 PASSType 250,000 Cycles(200, 200SF, 300BCF, 300PASS)40,000 Cycles (300F)57-53-I04Z Inboard Flap #4 Support – 6-6’ Outer Pin – Section at Spline #2 (Common to6-7 Arm) Inner Diameter (Inner Bore)195, 196ALLType 125,000 Cycles57-53-I04AA Inboard Flap #4 Support – Flap SupportPins – Outer Pins at Joints 5, 7 and 9195, 196 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 125,000 Cycles57-53-I04AA Inboard Flap #4 Support – Flap Support Pins – Outer Pins at Joints 5, 7, 9, and RL195, 196 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 125,000 Cycles57-54-I02A Main Landing Gear Beam, Inboard Lug BoreNote: No DTR Check Form.552, 652200SF300BCF<4>Type 150,000 Cycles57-54-I02B Main Landing Gear Beam, Outboard Lug BoreNote: No DTR Check Form.552, 652200SF300BCF<4>Type 150,000 CyclesAIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-88767 MAINTENANCE PLANNING DATA57-54-I02C Main Landing Gear Beam, Aft Trunnion BoreNote: No DTR Check Form.552, 652 200SF300BCF<4>Type 150,000 Cycles57-54-I02D Main Landing Gear Beam, Upper Flange, between the Inboard and Outboard WebStiffeners adjacent to Aft Trunnion BoreNote: No DTR Check Form.552, 652200SF300BCF<4>Type 150,000 Cycles57-54-I02E Main Landing Gear Beam, Upper Flange, except the flange adjacent to Aft TrunnionBore covered by SSI 57-54-I02D.Note: No DTR Check Form.552, 652200SF300BCF<4>Type 150,000 Cycles57-54-I03A Load Distribution Plate,Flange around Outboard Upper LugNote: No DTR Check Form.552, 652200SF300BCF<4>Type 150,000 Cycles57-54-I03B Load Distribution Plate, Flange around Outboard Lower LugNote: No DTR Check Form.552, 652200SF300BCF<4>Type 150,000 Cycles57-54-I03C Load Distribution Plate, Flange around Inboard LugNote: No DTR Check Form.552, 652200SF300BCF<4>Type 150,000 Cycles57-54-I03D Load Distribution Plate, Flange exceptin the Lug areas covered by SSI 57-54-I03A,57-54-I03B and 57-54-I03C.Note: No DTR Check Form.552, 652200SF300BCF<4>Type 150,000 Cycles57-54-I04 Main Landing Gear Beam, Outboard PinNote: No DTR Check Form.552, 652200SF300BCF<4>Type 150,000 Cycles57-54-I13 MLG Forward Trunnion Support – Side Load Fitting – Side Load Fitting to StrapInboard Fastener Row551, 651400E<2>Type 125,000 Cycles/80,000 Flt. Hrs.57-54-I14 MLG Forward Trunnion Support – SideLoad Strap – First Fastener Row Either Sideof Trunnion551, 651400E<2>Type 125,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-89<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, published in the appropriate manual,and accepted by the FAA.<3> No 767-300F airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedure is revised, published in the appropriatemanual, and accepted by the FAA.<4> No 767-300BCF and 767-200SF airplane may be operated beyond the stated threshold (operational limit) until the applicableinspection procedures are validated, published inthe appropriate manual, and accepted by the FAA.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITY TYPE AND THRESHOLDSEP 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-90767 MAINTENANCE PLANNING DATAC. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFE PARTSNOTE: Service Letter 767-SL-32-092 (Latest Revision) and its reference Boeing Drawing 160T0002, 767 Main and Nose Landing Gear ComponentInterchangeability List, identify the767 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 Landing Gear ComponentInterchangeability List, identify the767 landing gear and support structure safe-life (life limited) parts.ITEMLIFE LIMIT767-200, 767-200SF Nose Landing Gear80,000 Landings *767-200, 767-200SF Main Landing Gear70,000 Landings *767-200, 767-200SF Main Landing Gear Support Structure90,000 Landings ** These values are based on completed fatigue tests and incorporation of the following Service Bulletins on applicable airplanes:SERVICE BULLETIN #DESCRIPTIONLIFE LIMIT (LANDINGS)PRIOR TO INCORPORATION767-32-44MLG UPPER SPINDLE-DRAGSTRUT, PART # 161T60079,000767-32-45MLG OUTER CYLINDER ASSEMBLY, PART # 161T111018,000767-32-46MLG UPPER BULKHEAD-SHOCK STRUT, PART # 16T116130,000ITEMLIFE LIMIT767-300, 767-300BCF, 767-300F NOSELANDING GEAR 80,000 LANDINGS **767-300, 767-300BCF, 767-300F MAINLANDING GEAR 50,000 LANDINGS **767-300, 767-300BCF, 767-300F MAIN LANDINGGEAR SUPPORT STRUCTURE 62,000 LANDINGS **767-300, 767-300BCF, 767-300F MLG RETRACT ACTUATOR FITTING AND PIN 90,000 LANDINGS   These values are based on completed fatigue tests.JUN 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-91NOTE: Service Letter 767-SL-32-092 (Latest Revision) and its reference Boeing Drawing 160T0002, 767 Main and Nose Landing Gear ComponentInterchangeability List, identify the767 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.ITEMLIFE LIMIT767-400ER NOSE LANDING GEAR80,000 LANDINGS ** 767-400ER MAIN LANDING GEARINNER CYLINDER16,600 LANDINGS *OUTER CYLINDER16,600 LANDINGS *WING MAIN LANDING GEAR BEAM UPPER STABILIZER BRACE FUSE PIN21,300 LANDINGS *ALL OTHER SAFE-LIFE PARTS31,400 LANDINGS ** These values are based onfatigue test cycles completed to date and will be increasedwhen testing is complete.** These values are based on completed fatigue tests and analysis.ITEMLIFE LIMIT767-300 FRONT MOUNT PYLON MOUNTING BRACKET30,000 LANDINGS ***767-300 FRONT MOUNT CENTER THRUST LINK ANDASSOCIATED HARDWARE30,000 LANDINGS ***767-300 REAR MOUNT PYLON BRACKET50,000 LANDINGS ****** These values are based on completed Safe-Life testing and analysis.JUN 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-92767 MAINTENANCE PLANNING DATAD. AIRWORTHINESS LIMITATIONS – SYSTEMSINTRODUCTIONThis section of the Airworthiness Limitationscontains an FAA approved program of scheduled inspections and design limitationsfor operators toincorporate into their maintenance program for this type designto meet the new standards and assumptions introduced by § 25.981 and Special FederalAviation Regulation No. 88 (SFAR 88). SFAR 88 – Fuel Tank SystemFault Tolerance Evaluation Requirements and Title 14 Code of Federal Regulations§ 25.981 – Fuel Tank Ignition Prevention require maintenance instructions, and control limitations for certain fuel tank critical design configurations.Paragraph 2(a) of SFAR 88 requires certain design approval holders of Type Certificates (TCs) and Supplemental Type Certificates (STCs) of largetransport airplanes to conduct a safety review of the fuel tank systems. The purpose of the safety reviewis to identify designfeatures that may result indevelopment of ignition sources in the fueltank systems. Fuel System AirworthinessLimitations (AWLs) are mandatory maintenance actions established inaccordance with § 25.981, to ensure that unsafe conditions identified by the safety review do not occur or are not introduced into the fuel tank system as aresult of configuration changes, repairs, alterations, or deficiencies in the maintenance program throughout the operational life of the airplane. An AWLmay 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 operational life of theairplane. CDCCLs are mandatory and cannot be changed or deleted without the approval of the Seattle FAA ACO or applicable regulatory agency. Acritical fuel tank ignition source prevention feature may exist in the fuel system andits related installation or in systems that, if a failurecondition were todevelop, could interact with the fuel system in such a way that an unsafe condition would develop without this limitation. Strict adherence to configuration,methods, techniques, and practices as prescribed is required to ensure compliance withthe CDCCL. Any use of parts, methods, techniques or practicesnot contained in the applicable CDCCL must be approvedby the Seattle FAA ACO or applicable regulatory agency.ALIs identify inspection tasks related tofuel tank ignition source prevention which must be done to maintain the design level of safety for the operationallife of the airplane. These ALIs are mandatory and cannot be changed or deleted without the approval of the Seattle FAA ACO orapplicable regulatoryagency. Strict adherence to methods, techniques and practices as prescribed is required to ensure the ALI is complied with. Any use of methods,techniques or practices not contained in these ALIs must beapproved by the Seattle FAA ACO or applicable regulatory agency.OCT 2012767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-93USE 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 equipmentor materials requires priorapproval from the Seattle FAA ACO.The Component Maintenance Manuals (CMM) listed in the AWLs are currently FAA Seattle ACO approved.If the CMM allows the use of alternate orequivalent tools, test equipment or materials, use of an alternate or equivalent tool, test equipment or material does not require further approval by theFAA Seattle ACO.EXCEPTIONAL SHORT-TERM EXTENSIONSSince AWL intervals are based on estimations of the probability ofan event, an exceptional short-term extension for each fuelsystem AWL listed in thisdocument may be made without jeopardizing safety. The local regulatory authority (e.g. a Principal Maintenance Inspector) must concur with anyexceptional short-term extensions before they take place using procedures established with the local regulatory authority in the operators’ manuals. The“exceptional short-term extension” process is applicable to AWL intervals. It should not be confused with the operator’s “short-term escalation” program fornormal 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-termextensions may be granted without consultation with that office:1. The term "exceptional short-term extension" is defined as an increase in a fuel system AWL interval that may be needed to cover an uncontrollable orunexpected situation. All AWLs listed in this section have been approved with an exceptional short-term extension of 30 days.2. Repeated use of extensions, either on the same airplane or onsimilar airplanes in an operator's fleet, should not be used asa substitute for goodmanagement practices. Exceptionalshort-term extensions must not beused for fleet AWL extensions.After a fuel system AWL has experienced an exceptional short-term extension, the AWL interval will revert back to its intervallisted in this document. TheSeattle FAA ACO must approve, prior to its use,any desired extension notexplicitly listed above.This exceptional short-term extension listed above applies to airlines that fall under the UnitedStates FAA jurisdiction only.Operators who are not underthe U.S FAA jurisdiction should obtain interval extension approvals from their local regulatory agency.MAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-94767 MAINTENANCE PLANNING DATAREGULATORY AGENCY APPROVALAny deviations from the published AWL instructions included in this document require approval fromthe Seattle FAA ACO. This applies to operatorsunder the US FAA jurisdiction only and to airplanes registered inthe U.S. All other operators should obtain approval form their own local regulatoryagency for any deviations from the listed AWL instructions.AWL REVISION PROCESSIn the event that an AWL is revised, Boeing will prepare a revision tothis document that will beapproved by the Seattle FAA ACO. This revision will thenbe forwarded to all 767 operators and the Seattle FAA ACO.PAGE FORMAT: FUEL SYSTEM AIRWORTHINESS LIMITATIONSCOLUMNEXPLANATIONAWL NUMBER Each task is given a unique AWL Item Number.The first and second digits are the ATA Chapter Number.TASKALI = Airworthiness Limitation Instruction. These tasks are inspections that should be performed atthe listed intervals.CDCCL = Critical Design Configuration Control Limitation.INTERVALTask frequencies are specified in terms of a usage parameter such as flight hours, cycles or calendar time.APPLICABILITY Airplanemodel applicability.DESCRIPTION Description of the task to beperformed or critical designconfigurations aspects that cannot be changed without violating the intent ofthe design.OCT 2012767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-95D.1 AWLs – FUEL SYSTEM IGNITION PREVENTIONAWLNumber Task Interval Applicability Description28-AWL-01 ALI 12 YrsAllExternal Wires Over Center Fuel TankConcern: Potential for Chafing and arcing to Center Fuel Tank Upper Panel.Perform a detailed inspection of the wire bundlesrouted over the center fuel tank and under themain deck floor boards between the front spar and rear spar of the center wing box to detectdamaged clamps, wire chafing, and that the wire bundle is not in contact with surface of the centerfuel tank. If discrepancies are found, repair per the Boeing Standard Wiring Practices ManualD6-54446.28-AWL-02 CDCCL N/AAllExternal Wires Over Center Fuel TankConcern: Potential for Wire chafing andarcing to Center Fuel Tank Upper Panel.If any maintenance is performed in the area under the main deck floor boards and over the centerfuel 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 Practices ManualD6-54446.3. All wire bundles over the center fuel tank are inspected per 28-AWL-01.28-AWL-03 CDCCL N/A767 airplanes,Line Numbers869 and on andairplanes thathave incorporatedService Bulletin767-28A0071(767-200/-300/-300F) or767-28A0072(767-400ER)Lightning Protection – Engine Fuel Feed Line Fuel Tank PenetrationConcern: Potential for arcing, sparking or filamentheating inside the tank at the interface betweenthe bulkhead fitting and the spar during a lightning strike event.The following must be maintained if the bulkhead fitting or attached tubing are removed andreplaced (refer to Boeing AMM 28-22-07):1. Verify electrical fay surface bond from bulkhead fitting to structure is 0.0005 ohms(0.5 milliohms) or less.2. Install full-bodied fillet seal encapsulating the bulkhead fitting to the tankwall interface insidethe tank.3. Install full bodied fillet seal encapsulating the first coupling interface inside the tank.OCT 2012D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-96767 MAINTENANCE PLANNING DATA28-AWL-04 CDCCL N/AAllLightning Protection – HydraulicLine Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interface between the bulkhead fittingand the spar during a lightning strike event.Maintain fay surface bond configuration of hydraulicline fuel tank penetration at interface betweenbulkhead fitting and the spar (refer to Boeing AMM 29-11-27). Verify the following CDCCLs whenthe bulkhead fitting or attached tubing are removed and replaced.1. The resistance between the mating surfaces ofthe heat exchanger and the airplane structureis less than 0.001 ohm (1 milliohm).2. The fay surface bond resistance between the inlet and outlet lines and the bulkhead fitting isless than 0.005 ohm (5 milliohms).3. On airplanes with in-line fittings, the resistanceacross the in-line fittings (tube-to-tube) is lessthan 0.005 ohm (5 milliohms).4. The resistance between the bulkhead fitting and the bulkhead is less than 0.010 ohm(10 milliohms).5. The installation is inspected per 28-AWL-05.28-AWL-05 ALI25,000 Hrs6 YrsNoteAllLightning Protection – HydraulicLine Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interface between the bulkhead fittingand the spar during a lightning strike event.Perform the following inspection to ensure functional integrity (refer to Boeing AMM Task 29-11-27):1. Use a bonding meter to do the checks of the bonding resistance in the main tanks for eachheat exchanger as follows (refer to Boeing SWPM 20-20-00):(a) Make sure the resistance between the bulkheadfitting and the rear sparfor the inlet line isless than 0.005ohm (5 milliohms).(b) Make sure the resistance between the bulkhead fitting and the rear spar for the outlet line isless than 0.005ohm (5 milliohms).2. If the bonding resistance is more than 0.005 ohm (5 milliohms), reworkthe bondingsurface toa value of 0.001 ohm (1 milliohm) or less (refer to Boeing SWPM 20-20-00).Interval Note: Whichever comes first.AWLNumber Task Interval Applicability DescriptionMAY 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9728-AWL-06 CDCCL N/AAllAC and DC Pump MaintenanceConcern: Potential for maintenance error during pumpoverhaul. Fuel pump designs contain ignitionsource prevention means (i.e., flame arrestor, thermal fuses, materials, leadwire retention means,etc.) that must be maintained if pump is overhauled.Repair and overhaul of Fuel Pumps must be per the manufacturer’s Component MaintenanceManual (CMM) Numbers, 28-20-02, Revision Number 12, 28-22-01, Revision Number 12, 28-22-02,Revision Number 19, 28-22-03, Revision Number 14, 28-22-11, Revision Number 15, 28-22-12,Revision Number 18, 28-22-13, Revision Number 11, 28-22-21, Revision Number 8, 28-22-23,Revision Number 6, 28-22-31, Revision Number 2,28-22-33, Revision Number 2 or later revisionsof these CMMs that have been approved by the Seattle FAA ACO.28-AWL-07 CDCCL N/AAllAC Fuel Pump Fault Current Bonding PathConcern: Potential for fault current path through the pump housing to structure inside the tank.Electrical faults internal to the fuel pump motor impeller are by design routed through the motorimpeller assembly to the bonding straps on the front face of the motor impeller assembly tostructure outside the tank. The bonding straps ensure that fault currents are conducted to structureoutside the tank until the circuit breaker and/or GFI has had time to remove power from the pump.The following must be maintained during pump replacement (refer to Boeing AMM 28-22-03and 28-22-05):1. Installation of the two bonding straps between the pump housing (doghouse) and bondingclip on structure.2. Pump housing bonding resistance to structure less than or equal to 0.0003 ohms(0.3 milliohms) for maintank boost pumps and 0.0002 ohm(0.2 milliohms) for center tankpumps.3. Make sure the bonding resistance between the housing and the fuel pump is not more than0.00035 ohms (0.35 milliohms).AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-98767 MAINTENANCE PLANNING DATA28-AWL-08 CDCCL N/AAllLightning, Fault Current or Hot ShortProtection – Fuel Tank PenetrationsConcern: Potential for arcing or sparking insidethe tank at a conductive metal-to-ground structureinterface as a result of electrical fault currents orlightning strike events due to insufficient bondingwithin the ground electrical path.Addition of any new penetrations tothe fuel tanks (such as addinga bracket or bulkhead fitting orequipment) or change to the designfeatures of the existing equipment penetrations (such as fuelmeasuring sticks, sump drain valves, fueling manifold, fuel temperature sensor, and motor operatedfuel shutoff valve adaptor plate) requires approval by the Seattle FAA ACO.28-AWL-09 CDCCL N/AAllFuel Quantity Indicating System (FQIS) / SurgeTank Fuel Level SensingSystem – Out Tank WiringInstallation Separation RequirementConcern: Potential for hot shorts and EMI induced voltages on the FQIS wiring outside of the tank toenter the fuel tank.Routing and installation of any new wiring must use wire types BMS 13-48, BMS 13-60 orBMS 13-58, and not be within a 2-inch radius ofthe FQIS wiring. When a single clamp fails, aseparation greater than 1⁄2 inch must be maintained from FQIS wiring.28-AWL-10 CDCCL N/AAllCenter Tank Fueling Valve-Fault Current BondConcern: Potential for arcing or filamentheating inside the center wing fuel tank.The following must be maintained if the system isdisturbed (refer to Boeing AMM 28-21-02 (all 767airplanes) and 28-21-12 (767-400 only)):Verify the fay surface bond resistance between thevalve body and the rear spar inside the tank isless than or equal to 0.0025 ohms (2.5 milliohms). Verify fillet sealis installed around valve bodyand 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 the outside of the tank.Verify the bonding resistance between the control unit and the rear spar is equal to or less than0.008 ohms.AWLNumber Task Interval Applicability DescriptionMAY 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9928-AWL-11 CDCCL N/AAllFuel Quantity Indicating System (FQIS) –Fuel Quantity Processor Unit (FQPU) RepairConcern: Potential for maintenance error during FuelQuantity Processor Unit (FQPU) repair. TheFQPU is designed to limit the levels of energy, voltage, current, and power allowed within the FQIScircuit to intrinsically safe levelsin order to preclude the potentialof an ignition source within anyfuel tank.Repair and overhaul of FQPU must be per the manufacturer Component Maintenance Manual(CMM) Number, 28-41-68 Revision 4, or a later revision of this CMM that has been approved by theSeattle FAA ACO.28-AWL-12 CDCCL N/AAllFuel Quantity Indicating System (FQIS) – Repairof In-Tank Hardware (Tank Units, Densitometers,and Compensators)Concern: Potential for maintenance error during repair of in-tank hardware (tank units,compensators and densitometers). Arc gaps may develop that could result in an ignition sourceinside the fuel tank.Repair and overhaul of FQIS tank units, compensators, and densitometers must be per themanufacturer CMMs.Goodrich Component Maintenance Manual (CMM) Numbers 28-40-56 Revision Number 4,28-40-59 Revision Number 4, 28-40-62 Revision Number 3, 28-41-68 Revision Number 4, or laterrevisions of these CMMs that have been approved by the Seattle FAA ACO.Honeywell CMM Numbers 28-41-01 Revision Number5, 28-41-07 Revision Number 4, 28-41-09Revision Number 6, 28-41-30 Revision Number 1,28-41-33 revision number 2, 28-41-34 RevisionNumber 1, 28-41-35 Revision Number 1, 28-41-36 Revision Number 7, 28-41-39 Revision Number7, 28-41- 41 Revision Number 5, 28-41-42 Revision Number 0, or later revisions of these CMMsthat have been approved by the Seattle FAA ACO.AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-100767 MAINTENANCE PLANNING DATA28-AWL-13 CDCCL N/AAllFuel Quantity Indicating System (FQIS) – Repair of In-Tank Wire HarnessConcern: Potential for error during repair or replacement of in-tank wire harness. Arc gaps maydevelop that could result in an ignition source inside the fuel tank.Repair and overhaul of FQIS in-tank wireharness must be per Boeing SWPM 20-14-12.Install FQIS in-tank wire harness must be per Boeing AMM 28-41-09. Wire slack clearancebetween 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 clean.2. New O-ring(s) are installed.3. The Jamnuts are tightened to a torque as specified in the Boeing AMM Task 28-41-09.4. Sealant is installed per instruction in the Boeing AMM Task 28-41-09.28-AWL-14 CDCCL N/AAllFuel Tank Access Doors ConfigurationConcern: Potential for arcing or sparking insidethe tank at the interface between the door and thetank structure as a result of a direct strikeor conducting currents through the wing skin.The following must be maintained during fuel tank access door installation (refer to BoeingAMMs 28-11-01, 28-11-02, and 28-11-03):1. Verify presence of a molded rubber seal positioned around the outermost periphery of thedoor 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 outside face of the door andthe wing skin to establish the electrical conductivity between the access door and thewing skin.AWLNumber Task Interval Applicability DescriptionMAY 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-10128-AWL-15 CDCCL N/AAllSurge Tank Fuel Level Sensor Control Card RepairConcern: Potential for maintenance error during FuelLevel Sensor Control Card repair. The FuelLevel Sensor control card is designed to limit the levels of energy, voltage, current, and powerallowed within the fuel level sensing circuit to intrinsically safe levels in order to preclude thepotential of an ignition source within any fuel tank.Repair and overhaul of Fuel Level Sensor Control Card must be per the manufacturer’s CMMNumber 28-21-01 Revision Number 1, or later revisions of this CMM that have been approved bythe Seattle FAA ACO.28-AWL-16 CDCCL N/AAllSurge Tank Fuel Level Sensing System– Repair of In-Tank Wire HarnessConcern: Potential for error during repair or replacement of in-tank wire harness. Arc gaps maydevelop that could result in an ignition source inside the fuel tank.Repair and overhaul Fuel Level Sensor in-tank wire harness per Boeing SWPM 20-14-12.Install Surge Tank Fuel Level Sensor in-tank wire harness per Boeing AMM 28-21-11.28-AWL-17 CDCCL N/AAllResetting Tripped Fuel Pump Circuit BreakersConcern: Potential for arcing or sparking inside the tank between fuel pumps and fuel pumphousings and outside the tank between pump wiring and structure in flammable leakage zones.Verify it is safe to reset thecircuit breaker(s) by following the applicable OEM troubleshootingprocedures. Fault(s) that resulted in circuitbreaker trip must be isolated and corrected priorto reset.AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-102767 MAINTENANCE PLANNING DATA28-AWL-18 ALI 12 YrsAllFuel Quantity Indicating System (FQIS) – Out TankWiring Lightning Shield to Ground TerminationConcern: Potential for Lightning induced voltages on the FQIS wiring toenter the fuel tank.Perform the following inspection to ensure the functional integrity of theFQIS wiring shield toground termination (refer to Boeing AMM 20-55-54):1. Visually inspect all connectors at the locationbeing tested to ensurethey are tight. Thisincludes connector plugs and backshells.2. Use a Loop Resistance Tester P/N 906-10246-2 or906-10246-3 to measure and verify theresistance 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 (Left Main Tank)Wire Bundle S283T025-126.The loop resistance shall not exceed 40 milliohms for Connector M1945 (Left Main Dens Tank)Wire Bundle S283T025-122.The loop resistance shall not exceed 40 milliohms for Connector M1948 (Left Aux Tank)Wire Bundle S283T025-127.The loop resistance shall not exceed 43 milliohms for Connector M1957 (Right Main Tank)Wire Bundle S283T025-136.The loop resistance shall not exceed 40 milliohms for Connector M1950 (Right Main Dens. Tank)Wire Bundle S283T025-132.The loop resistance shall not exceed 47 milliohms for Connector M1958 (Right Aux Tank)Wire Bundle S283T025-137.The loop resistance shall not exceed 40 milliohms for Connector M1952 (Right Aux Dens. Tank)Wire Bundle S283T025-135.(Continued on next page)AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-103767 MAINTENANCE PLANNING DATA28-AWL-18(Continued)Fuel Quantity Indicating System (FQIS) – Out TankWiring Lightning Shield to Ground Termination(Continued)767-300 CINCH Wire Bundle:The loop resistance shall not exceed 44 milliohms for Connector M1944 (Left Main Tank)Wire Bundle S283T025-121.The loop resistance shall not exceed 40 milliohms for Connector M1945 (Left Main Dens Tank)Wire Bundle S283T025-122.The loop resistance shall not exceed 40 milliohms for Connector M1946 (Left Aux Tank)Wire Bundle S283T025-123.The loop resistance shall not exceed 43 milliohms for Connector M1949 (Right Main Tank)Wire Bundle S283T025-131.The loop resistance shall not exceed 40 milliohms for Connector M1950 (Right Main Dens. Tank)Wire Bundle S283T025-132.The loop resistance shall not exceed 47 milliohms for Connector M1951 (Right Aux Tank)Wire Bundle S283T025-134.The loop resistance shall not exceed 40 milliohms for Connector M1952 (Right Aux Dens. Tank)Wire Bundle S283T025-135.767-300F CINCH Wire Bundle:The loop resistance shall not exceed 44 milliohms for Connector M1944 (Left Main Tank)Wire Bundle S283T025-321 (-971).The loop resistance shall not exceed 40 milliohms for Connector M1945 (LeftMain Dens. Tank)Wire Bundle S283T025-122 (-922).The loop resistance shall not exceed 40 milliohms for Connector M1946 (Left Aux Tank)Wire Bundle S283T025-323 (-973).The loop resistance shall not exceed 43 milliohms for Connector M1949 (Right Main Tank)Wire Bundle S283T025-331 (-981).The loop resistance shall not exceed 40 milliohms for Connector M1950 (Right Main Dens. Tank)Wire Bundle S283T025-132 (-932).The loop resistance shall not exceed 47 milliohms for Connector M1951 (Right Aux Tank)Wire Bundle S283T025-334 (-984).(Continued on next page)AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-104767 MAINTENANCE PLANNING DATA28-AWL-18(Continued)Fuel Quantity Indicating System (FQIS) – Out TankWiring Lightning Shield to Ground Termination(Continued)767-300F CINCH Wire Bundle, continued:The loop resistance shall not exceed 40 milliohms for Connector M1952 (Right Aux Dens. Tank)Wire Bundle S283T025-135 (-935).767-200 and 767-300 Boeing Wire Bundle:The loop resistance shall not exceed 121 milliohms for Connector D1582 (LeftMain Tank Lo-Z)Boeing Wire Bundle 286T0446.The loop resistance shall not exceed 284 milliohms for Connector D1552 (LeftMain Tank Hi-Z)Boeing Wire Bundle 286T0446.The loop resistance shall not exceed 150 milliohms for Connector D2816 (LeftAux Tank Lo-Z)Boeing Wire Bundle 286T0454.The loop resistance shall not exceed 175 milliohms for Connector D2812 (LeftAux Tank Hi-Z)Boeing Wire Bundle 286T0454.The loop resistance shall not exceed 122 milliohms for Connector D1584 (RightMain Tank Lo-Z)Boeing Wire Bundle 286T0448.The loop resistance shall not exceed 284 milliohms for Connector D1560 (RightMain Tank Hi-Z)Boeing Wire Bundle 286T0448.The loop resistance shall not exceed 152 milliohms for Connector D2818 (RightAux Tank Lo-Z)Boeing Wire Bundle 286T0448.The loop resistance shall not exceed 184 milliohms for Connector D2814 (RightAux Tank Hi-Z)Boeing Wire Bundle 286T0448.(Continued on next page)AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-105767 MAINTENANCE PLANNING DATA28-AWL-18(Continued)Fuel Quantity Indicating System (FQIS) – Out TankWiring Lightning Shield to Ground Termination(Continued)767-400ER Wire Bundle:The loop resistance shall not exceed 59 milliohms for Connector M1944 (Left Main Tank)Wire Bundle S283T025-721.The loop resistance shall not exceed 63 milliohms for Connector M1945 (Left Main Dens Tank)Wire Bundle S283T025-722.The loop resistance shall not exceed 465 milliohms for Connector M1946 (Left Aux Tank)Wire Bundle S283T025-723.The loop resistance shall not exceed 58 milliohms for Connector M1949 (Right Main Tank)Wire Bundle S283T025-731.The loop resistance shall not exceed 59 milliohms for Connector M1950 (Right Main Dens Tank)Wire Bundle S283T025-732.The loop resistance shall not exceed 570 milliohms for Connector M1951 (Right Aux Tank)Wire Bundle S283T025-734.The loop resistance shall not exceed 66 milliohms for Connector M1952 (Right Aux Dens Tank)Wire Bundle S283T025-735.If the measured loop resistance value is not within the defined limits, perform troubleshooting andrepair in accordance with Boeing AMM 20-55-54.3. Repair per Boeing AMM if the joint resistance is greater than the maximum allowed value.28-AWL-19 CDCCL N/A AllFQIS – Out Tank Wiring Lightning Shield to Ground TerminationConcern: Potential for Lightning induced voltages on the FQIS wiring toenter the fuel tank.If any maintenance is performed on the FQIS wire bundle in the unpressurized zone (outside offuselage), verifythe 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.AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-106767 MAINTENANCE PLANNING DATA28-AWL-20 ALI 1 Yr767 airplanes,Line Number 941and on,and airplanesmodified byService Bulletins767-28A0083 or767-28A0084.NoteCenter Auxiliary Tank Override/Jettison Fuel Pumps Auto ShutoffConcern: Dry running the center tank fuel pumps has the potential for single failure ignition sourcesdeveloping at the pump inlet due to either frictional heating or sparking as a result of FODcontacting the pump rotating elements, rotating elements contacting stationary parts, or hot journalbearings due to bearing contamination or failure.The automatic shutoff system is installed and designed to limit continuousdry running condition to15 seconds.The following test is required in order to protect against latent faults:Functionally check the center tank fuel boost pump automatic shutoff system per BoeingAMM 28-22-00.Airplane Note: Applicable to airplane withinstalled and activated auto shutoff system.28-AWL-21 Reserved for future SFAR 88 AWL.28-AWL-22 CDCCL N/A767 airplanes,Line Number 938and on,and airplanesmodified byService Bulletin767-28A0094Fuel Quantity Indicating System(FQIS) – Installation of CenterFuel Tank Hot Short Protector (HSP)Concern: Potential for wire to wire hot short voltages on the center tank fuel quantity densitometerwiring to enter the fuel tank. This is applicableto airplanes with optional densitometer installed.The FQIS HSP is designed to prevent wire to wireexternal hot short voltages from entering the fueltank where it may cause an ignition.The following features must be maintained during replacement of the HSP (refer to BoeingAMM 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 terminated is0.0025 ohms (2.5 milliohms) or less.3. A new unit must be used.The Hot Short Protector unit is not repairable.AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-107767 MAINTENANCE PLANNING DATA28-AWL-23 CDCCL N/AAirplane LinePosition 941 andon, and airplanesmodified perService Bulletin767-28A0090.Lightning and Fault Current Protection– Motor Operated Valve (MOV) ActuatorConcern: Potential for arcing or sparking insidethe fuel tank at a conductive metal-to-groundstructure interface as a result ofelectrical fault currents event.The following design features must be maintained during actuator, adapter plate or index platerepair, or replacement (refer to Boeing AMMs28-22-01, 28-22-02, 28-22-11, 28-22-12, 28-26-01,or 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 plate and the spar is0.0005 ohms (0.5 milliohms) or less.b. Install fillet seal around theperiphery of the adapter plateand the spar outside the tank.c. Wet install and cap seal the four bolts that attach the adapter plate to the spar inside the tankand fillet seal around the edge of the hole andon the stationary partof the adapter plateinside the tank.d. Install sealed electrical fay surface bond between the serrated mating surfaces of the indexplate and the adapter plate. Wet install the index plate screws using same sealant.e. Install sealed electrical fay surface bond between the mating surfaces of the actuator and theindex plate. Wet install the actuator screws using same sealant.f. With the bonding jumper not installed, verify electrical bonding resistance between theactuator bond strap attachmentpoint and the spar is 0.0025ohms (2.5 milliohms) or less.g. Prior to attachment of the bonding jumper to the actuator, verify electrical bonding resistancebetween the loose end of the bonding jumper and the spar is0.0015 ohms (1.5 milliohms)or less.h. Attach the bonding jumper to the actuator bonding tab using a sealed electrical fay surfacebond and verify electrical bonding resistancebetween the actuator housing and the attachedbonding jumper terminal is 0.001 ohms (1 milliohm) or less.(Continued on next page)AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-108767 MAINTENANCE PLANNING DATA28-AWL-23(Continued)Lightning and Fault Current Protection – Motor Operated Valve (MOV) Actuator (Continued)2. Maintain the following if the index plate is removed and replaced:a. Install sealed electrical fay surface bond between the serrated mating surfaces of the indexplate and the adapter plate. Wet install the index plate screws using same sealant.b. Install sealed electrical fay surface bond between the mating surfaces of the actuator and theindex plate. Wet install the actuator screws using same sealant.c. With the bonding jumper not installed, verify electrical bonding resistance between theactuator bonding tab andthe spar is 0.0025 ohms(2.5 milliohms) or less.d. Prior to attachment of the bonding jumper to the actuator, verify electrical bonding resistancebetween the loose end of the bonding jumper and the spar is0.0015 ohms (1.5 milliohms)or less.e. Attach the bonding jumper to the actuator bonding tab using a sealed electrical fay surfacebond and verify electrical bonding resistancebetween the actuator housing and the attachedbonding 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 surfaces of the actuator and theindex plate. Wet install the actuator screws using the same sealant.b. With the bonding jumper not installed, verify electrical bonding resistance between theactuator bonding tab andthe spar is 0.0025 ohms(2.5 milliohms) or less.c. Prior to attachment of the bonding jumper to the actuator, verify electrical bonding resistancebetween the loose end of the bonding jumper and the spar is0.0015 ohms (1.5 milliohms)or less.d. Attach the bonding jumper to the actuator bonding tab using a sealed electrical fay surfacebond and verify electrical bonding resistancebetween the actuator housing and the attachedbonding jumper terminal is 0.001 ohms (1 milliohm) or less.AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-109767 MAINTENANCE PLANNING DATA28-AWL-24 CDCCL N/AAirplane LinePosition 941 andon, and airplanesmodified perService Bulletin767-28A0090.Motor Operated Valve (MOV) Actuator – RepairConcern: Potential for arcing or sparking inside the fuel tank at a conductive metal-to-groundstructure interface as a result of lightning or electricalfault current event. An electrical isolator on theactuator output shaft is intended to disconnect theoutput shaft electrically from the motor internalelectrical circuitry and ground path structure.To verify the integrity of the electrical isolation feature, conduct the following bench test per ITTCMM 28-20-21:A Dielectric Strength test on the completed actuator assembly shall be performed by applying3000 VAC RMS, 60 Hz for one (1) minute betweenany mounting foot of the actuator and the outputshaft spline. There shall be no evidence of disruptive discharge in the form of leakage current inexcess of 1.0 milli-amps. The 3000V test is abench test only and mustnot be performed onthe aircraft.28-AWL-25 CDCCL N/A767-400ERairplanesSurge Tank Fuel Level Sensor – Wiring- Electromagnetic Compatibility ShieldingConcern: Potential for electromagnetic energy/powerbeing induced on the surge tank sensor wiringinto the Fuel Tank.If any maintenance is performed on the surge tank sensor wire bundle for its routing from the P50card file to the fuel tank sparpenetration, 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.AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-110767 MAINTENANCE PLANNING DATA28-AWL-26 ALI 12 Yrs767-400ERairplanesSurge Tank Fuel Level Sensor – Wiring- Electromagnetic Compatibility ShieldingConcern: Potential for electromagnetic energy/power being induced on the surge tank sensor wiringinto the Fuel Tank.Perform the following inspection to ensure the functional integrity of the surge tank fuel level sensorwiring shield to ground termination per Boeing AMM 20-55-54:1. Visually inspect all connectors at the location being tested to ensure they are tight. This includesconnector plugs and backshells.2. Use a Loop Resistance Tester P/N 906-10246-2 or 906-10246-3 to measure and verify theresistance of the shield to ground termination for the following items:The loop resistance for the right sensor W882 from D8408P to D6114J is between213.86 milliohms and 251.6 milliohms.The loop resistance for the right sensor W884 from D6114P to D8308P is between27.45 milliohms and 32.30 milliohms.The loop resistance for the left sensor W882 from D8038P to D6116J is between229.27 milliohms and 269.73 milliohms.The loop resistance for the left sensor W886 from D6116P to D8306 isbetween 26.97 milliohmsand 31.73 milliohms.28-AWL-27 ALI 1 Yr767 airplanes,Line Numbers961 and on,and airplanes thathave incorporatedService Bulletin767-28A0085Main and Center AuxiliaryFuel Tank Boost/Override/Jettison Fuel Pump Ground Fault Interruption(GFI) Control Relay SystemConcern: GFI is installed to protect against burn-through of the pump housing and/or wiring conduit,and to protect against overheating of the pumpexplosion proof cavity and/or auto ignitiontemperature on the outside surface of the conduit, due to electrical arcing.Perform an operational test ofthe Main Fuel Tank Boost Pumpsand all Center Auxiliary TankOverride/Jettison Fuel Pump GFI Control Relays per Boeing AMM 28-22-00.AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-111767 MAINTENANCE PLANNING DATA28-AWL-28 ALI 1 Yr767 airplanes,Line Numbers961 and on,and airplanes thathave incorporatedService Bulletin767-28A0085Center Auxiliary Fuel Tank Override/Jettison Fuel Pump Uncommanded-On SystemConcern: Dry running of the CenterAuxiliary Fuel Tank Override/Jettison Fuel Pump resulting from asingle failure event has the potential to be an ignition source developing at the pump inlet due toeither frictional heating or sparking as a resultof FOD contacting the pump rotating elements,rotating elements contacting stationary parts, orhot journal bearings due to bearing contaminationor failure.Perform a Functional Test of the Center Auxiliary Fuel Tank Override/Jettison Fuel PumpUncommanded-On System per Boeing AMM 28-22-00.28-AWL-29 CDCCL N/A767 airplanes,Line Numbers990 and on,and airplanes thathave incorporatedService Bulletin767-28A0104In-Tank AC Fuel Pump Wire Bundles with Protective LinerConcern: Potential for the boost pump wiring to chafe and arc in the conduit to provide an ignitionsource in the fuel tank.The boost pump wires that are in the conduits in the fuel tanks have incorporated a conduit liner anda Teflon sleeve to protect from wire chafing. The wiring also has a shield (grounded at both ends)that is monitored by the GFI for an additional layer of protection for a pump power wire short withinthe conduit.Ensure the following conditions exist when replacing pump wiring or wiring conduit (refer toAMM 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 FuelTank Override/Jettison Fuel Pumps.AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-112767 MAINTENANCE PLANNING DATA28-AWL-30 CDCCL N/A767 airplanes,Line Numbers1 to 989, andairplanes thathave incorporatedService Bulletin767-28A0053 R2Fuel Boost Pump Wires In Conduit Installation – In Fuel TankConcern: Potential for the boost pump wiring to chafe and arc in the conduit to provide an ignitionsource in the fuel tank. The boost pump wires that are in the conduits in the fuel tanks haveincorporated two (2) Teflon sleeves to protect from wire chafing (refer to Boeing Service Bulletin767-28A0053 R2). The wiring also has ajacket to providechafing protection.Ensure the following condition exists when replacing pump wiring or wiring conduit (refer toAMM 28-22-15):– Jacketed wiring and a Teflon sleeve.The Teflon sleeve is not repairable. If damaged (chafed), it must be replaced.This applies to the following fuel pumps:1. Left and Right AFT/FWD Main Fuel Tank Boost Pumps.2. Left and Right Auxiliary FuelTank Override/Jettison Fuel Pumps.AWLNumber Task Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-113767 MAINTENANCE PLANNING DATAD.2 ENGINE FUEL SUCTION FEED SYSTEMThis section contains an FAA approved program of scheduled inspections for operators to incorporate into their maintenance program for this type designto meet Title 14 CFR § 25.951.The 767 Engine Fuel Feed System was type certificated as beingcompliant to Title 14 CFR § 25.951(b) when performing suction feed operations. TheEngine Fuel Suction Feed System AWL results from service experience of loss of fuelsystem suction feed capability due to air leaks in the engine fuelfeed system. The AWL is required maintenance needed to detect and correctfailure of the engine fuel feed system to reduce thepossibility of engineflameout resulting from air ingestion into the Engine Fuel Suction Feed System during low fuel level operation with boost pumps inoperative.The Engine Fuel Suction Feed System AWL is mandatory maintenanceto ensure that thesystem retains the performance of the Engine Fuel SuctionFeed System required by Title 14 CFR § 25.951(b) that arise dueto air leaks in the Engine Fuel Suction Feed System do not result in flameout ofboth engines.OCT 2012D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-114767 MAINTENANCE PLANNING DATAAWLs – ENGINE FUEL SUCTION FEED SYSTEMAWL Number Task Interval ApplicabilityDescription28-AWL-101 ALI 7500 FHor 3 YRS,whicheveroccurs firstALLEngine Fuel Suction Feed Operational TestAn Engine Fuel Suction Feed Operational Test must be accomplished successfully on each engineindividually. This test is required in order toprotect against engine flameoutduring fuel suction feedoperations (refer to Boeing AMM 28-22-00):1. Each engine (fuelsystem) to be tested must meet the following Fuel TankQuantity and TestProcedural 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 – 1,300 lbs (400 kg – 600 kg).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 mustbe between 900 lbs – 1,300 lbs (400 kg – 600 kg).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 Boost Pump ON.IV. Idle Engine Fuel Suction Feed (Boost PumpOFF) operation for a minimum of five minutes.NOTE: The APU may be used to start the engines, provided the Fuel Tank Quantity and TestProcedural Limitations are met.2. The test is considered a success if engine operation is maintained during the five-minute period andthe following engine parameters do not decay relative to those observed with Boost Pump ON:A. P&W, GE: N1, N2, and Fuel FlowB. RR: N1, N2, N3 and Fuel Flow3. An Engine Fuel Suction Feed System that fails the operational test must be repaired, andsuccessfully pass the Engine Fuel Suction FeedOperational Test prior to further flight.OCT 2012D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-115767 MAINTENANCE PLANNING DATAD.3 AWLs – LOW FUEL AND FUEL CONFIGURATION INDICATION TESTThis section contains an FAA approved program of scheduled inspections for operators to incorporate into their maintenance program for this type designto meet Title 14 CFR § 25.901c.The Low Fuel and Fuel Configuration Indication Test AWL limits theexposure to the loss of low fuel quantity or fuel configuration indication due to a latentfailure. The AWL is required maintenance needed to make sure thatthe Low Fuel and the Fuel Configuration indication are functioning correctly. Failureto detect and correct loss of Fuel Configuration indication mayresult in a loss of fuel use or subsequent delay in the capability to detect a critical fuel leak.The Low Fuel & Fuel Config Indication Test AWL is mandatory maintenance action to test correctfunctionality of the Low Fuel and the Fuel Configurationindication to show compliance with Title 14CFR § 25.901(c) and ensure that a latent failure does not result in a reduction infuel use or in the capability todetect a critical fuel leak.AUG 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-116767 MAINTENANCE PLANNING DATAAWLs – LOW FUEL AND FUEL CONFIGURATION INDICATION TESTAWL Number Task Interval ApplicabilityDescription28-AWL-102 ALI 750 FH767-200/300/300Fairplanes,Line Number 1058and on(except 1059).Fuel Quantity Indicating System (FQIS) – Low Fuel and Fuel Config Indication TestConcern: Potential for inability to detect a fuel leak dueto the loss of low fuel quantity or fuel configurationindication.To ensure proper function, operationally check the following Fuel Alerting Indications:1. With the use of FUEL QTY test switch on the P61 panel, confirm that LOW FUEL EICAS Cautionmessage and FUEL CONFIG light on P5 panel are displayed (refer to Boeing AMM Section28-41-00).2. Using one of the following methods, confirm theFUEL CONFIG indications are displayed (refer toBoeing AMM Section 28-21-00):A. Configure the airplane with an initial fuel quantity of 3,000 lbs (1,400 kg) or more in each main tank,an auxiliary (center) fuel quantity of2,200 lbs (1,000 kg) or more, and the auxiliary (center) tank fuelpumps OFF. Confirm that FUEL CONFIG EICAS Advisory message and FUEL CONFIG light on P5panel are displayed after three minutes.orB. Configure the airplane with an initial fuel quantity of 5,500 lbs (2,500 kg) or more in each main tank.Set a fuel imbalance of 2,600 lbs (1,200 kg) or greater between the left and right main tanks. Confirmthat FUEL CONFIG EICAS Advisory message and FUEL CONFIG light on P5 panel are displayedafter three minutes.AUG 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-117767 MAINTENANCE PLANNING DATAD.4 AWLs – NITROGEN GENERATION SYSTEM (NGS)The following list of AWLs (ALIs and CDCCLs) contains FAA approved scheduled inspections for operators to incorporate into their maintenance programfor this type design to meetthe requirementsfor the introduction of the Flammability Reduction Means (FRM) NitrogenGeneration System (NGS). TheFAA operational rule change E8-16084 Final Flammability Rule requires maintenance instructions and control limitations for certain NGS critical designconfigurations. § 25.981(d) also requires AWLs to preclude ignition sources inside the fuel tank that may be introduced by theaddition of NGS.E8-16084, Final Flammability Rule, Paragraph III(F), Section 7, Identification of Airworthiness Limitations:Paragraph M25.4(a)requires that if FRM is usedto comply with Paragraph M25.1, AWLs must be identified for all maintenance or inspection tasksrequired to identify failures of components within theFRM that are needed to meet Paragraph M25.1. NGS AWLs are mandatory maintenance actions that ensure that unsafe conditions that arise due to NGSfailures do not occur or are not introduced into the airplane asa result of configuration changes, repairs, alterations, or deficiencies in the NGSMaintenance Program throughout the operational life of the airplane.AUG 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-118767 MAINTENANCE PLANNING DATAAWLs – NITROGENGENERATION SYSTEMAWLNumber Task Interval ApplicabilityDescription47-AWL-01 CDCCL N/A 767 airplaneLine Numbers 993and on or airplanesthat haveincorporatedService Bulletin767-47-0001Lightning Protection – NGS Nitrogen Enriched Air (NEA) Distribution Line Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tankat the interface between the bulkhead fitting and the sparduring a lightning strike event.The following must be maintained if the bulkhead fitting or attached tubing are removed and replaced, orreinstalled (refer toBoeing 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 structure inside the tank is0.0005 ohms (0.5 milliohms) or less,3. Install full-bodied fillet seal encapsulating thebulkhead fitting and jam nut outside of the tank,4. Install full-bodied fillet seal between the cast-in hexfeature of the bulkheadfitting and the spar webinside of the tank,5. Install full-bodied fillet seal between the B-nut andtube, and between the B-nutand bulkhead fitting onthe first mating tube inside of the tank, and6. Verify electrical bond from structure to first tubemating with the bulkhead fitting is 1.0 ohms or less.NOTE: The bulkhead fitting is a special part which has anintegral flame arrestor. Any changes to this partrequire approval by the Seattle FAA ACO.47-AWL-02 CDCCL N/A 767 airplaneLine Numbers 993and on or airplanesthat haveincorporatedService Bulletin767-47-0001Lightning Protection – NGS NEA Distribution Line Fuel Tank PenetrationConcern: Potential for arcing, sparking of filament heating inside the tank at the interface between the dielectricisolator hose and the NEA tubing during a lightning strike event.The NGS installation is designed to prevent lighting currents from entering the center wing fuel tank by adding adielectric isolator hose in the forward leading edge fairing area NEA distribution line. The isolator must bemaintained if the dielectric isolator hose or attached tubing are removed and replaced (refer to Boeing AMM47-00-00 and 47-21-00).JAN 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-11947-AWL-03 CDCCL N/A 767 airplaneLine Numbers 993and on or airplanesthat haveincorporatedService Bulletin767-47-0001Nitrogen Generation System (NGS) – Flammability Exposure and PerformanceConcern: Airplane alterations may impact the performance of the NGS and hence the flammability of the CenterWing Fuel Tank.Background: The NGS is designed to provide the proper level of nitrogen to the center wing tank in order toreduce the flammability exposure by reducing the oxygencontent of the ullage. Theflammability exposure isalso affected by the temperature of the fuel. The following are critical features of the airplane that, if altered, cannegatively affect the performance of the NGS which in turn may increase the center fuel tank flammabilityexposure beyond the limits of 14 Code of Federal Regulations, Section 25.981 at Amendment 25-125, utilizingthe equivalent level of safety findingdescribed in FAA Memorandum PS05-0177-P-2.1. Transferring air (20.9% oxygen) to the center fueltank will dilute the nitrogen rich atmosphere createdby the NGS in the fuel tank. Some Auxiliary Fuel Tank installations transfer air to the center wing tankas part of venting and fuel transfer.2. NGS performance depends on bleed air pressure inthe bleed air cross-over manifold supplied bythe engines.3. Certification of the NGSdepends on the inherent flammability ofthe center fuel tank without NGSinstalled. Center tank flammability is a direct function of fuel tank temperature. Any heat sourcesaround the tank, heat sources introduced into the tank (such as warmfuel or new heat exchangers), orchanges that would cause heat to be retained (such installation of blankets adjacent to tank walls) couldaffect fuel tank flammability in a negative manner.CDCCL: Any design change that affects the vent system by adding air to the center tank, reduces the bleedpressure in the cross-over manifold during any phase offlight or ground operations, or adds any heat to thecenter wing fuel tank or increases heat retention ofthe center wing fuel tank isnot allowed without an FAAapproved analysis to show that the change, or combination of changes, does not affect the NGS performance perthe requirements of 14 CFR Section 25.981(b), Amendment 25-125 utilizing the equivalent level of safety findingdescribed in FAA Memorandum PS05-0177-P-2.See Boeing AMM Chapter 28 for a description of the Fuel System. See Boeing AMM Chapter 47 for adescription of the NGS.AWLNumber Task Interval Applicability DescriptionJAN 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-120767 MAINTENANCE PLANNING DATA47-AWL-04 ALI NOTEALLNOTENitrogen Generation System – NEADistribution Ducting InspectionConcern: The NEA Distribution System ducting outside the fuel tank may fail, latently allowing NEA to leakwithout reaching the fuel tank, resulting in the fuel tank not reaching required inert levels.Inspect the NEA distribution lines fromthe Air Separation Unit (ASU) to the fuel tank front spar for damage andleaks (refer to Boeing AMM 47-21-00).INTERVAL NOTE:1. 2600 FHA. All 767-400ERB. 767-200/300/300F Airplanes, Line Numbers (L/Ns) 993 to 1004 that have not incorporatedSB 767-47-0002.C. Airplanes that have incorporated SB 767-47-0001 R0.2. 6600 FHA. 767-200/300/300F Airplanes, L/Ns 1 to 992, thathave incorporated SB 767-47-0001 R1 or later.B. 767-200/300/300F Airplanes, L/Ns 993 to1004, that have incorporated SB 767-47-0002.C. 767-200/300/300F Airplanes, L/N 1005 and on.APPLICABILITY NOTE: If NGS is installed.AWLNumber Task Interval Applicability DescriptionJAN 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-12147-AWL-05 ALI NOTEALLNOTENitrogen Generation System – Cross-Vent Check Valve – Operational CheckConcern: The cross-vent check valve may fail open, latently allowing air to flow through the center tank dilutingthe nitrogen rich environment created by the Nitrogen Generation System.Operationally Check the cross-vent check valve by accessing left wing surge tank and inspecting/checking theoperation of the cross-vent check valve (refer to Boeing AMM 47-21-03).INTERVAL NOTE:1. 2600 FHA. All 767-400ER.B. 767-200/300/300F Airplanes, L/Ns 993 to 1004 that have not incorporated SB 767-47-0002.C. Airplanes that have incorporated SB 767-47-0001 R0.2. 4391 FHA. 767-200/300/300F Airplanes, L/Ns 1 to 992 that have incorporated SB 767-47-0001 R1 or later.B. 767-200/300/300F Airplanes, L/Ns 993 to1004 that have incorporated SB 767-47-0002.C. 767-200/300/300F Airplanes, L/N 1005 and on.APPLICABILITY NOTE: If NGS is installed.47-AWL-06 CDCCL N/A 767 airplaneLine Numbers 993and on or airplanesthat haveincorporatedService Bulletin767-47-0001Industry Fleet Average Flammability ExposureConcern: NGS performance is dependenton industry descent times. Industry efforts to reduce descent time mayresult in NGS performance that does not meet FAA requirements.Fleet Average flammability exposure forthe fuel tanks with flammability reduction of this airplane type must bemaintained in accordance with 14 CFR Part 25, AppendixM. Boeing will monitor U.S. descent statistics and, ifnecessary to maintain compliance, will publish service information. If Boeing publishes such service information,this CDCCL requires either that operators implementthese FAA approved design changes or that operatorsimplement other design changes or operational procedural changes approved by the Seattle FAA ACO tomaintain compliance with 14 CFR Part 25, Appendix M.NOTE: This CDCCL does not require individual operators to monitor descent rates of their fleets. Boeing willmonitor U.S. descent statistics and provide any needed service instructions tooperators. To prevent increasingflammability exposure above permissible levels, this CDCCLrequires operators to incorporate future Boeingpublished service instructions denoted to maintain compliance with this CDCCL, or other approved actions,within the compliance times stated in the service instructions.AWLNumber Task Interval Applicability DescriptionJAN 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-122767 MAINTENANCE PLANNING DATAD.5 IMPACT-RESISTANT FUEL TANK ACCESS DOORSINTRODUCTIONThe 767 Fuel Tank Access Doors are compliant with FAA Title 14CFR § 25.963. Specifically, the 767 Impact-Resistant Access Doors meet Title 14 CFR§ 25.963(e)(1), which requires that all covers located in an areawhere experience or analysis indicates a strike is likely mustbe shown by analysis or teststo minimize penetration and deformation by tire fragments, lowenergy engine debris, or other likely debris. Airplane Line Numbers 1 - 234 were retrofittedwith impact-resistant access doors via Service Bulletin 767-28A0019. This service bulletin also required that the impact-resistant doors be stenciled“IMPACT-RESISTANT DOOR”. Additionally, the adjacent lower wing surface is stenciled“CAUTION: INSTALL ONLY IMPACT-RESISTANT DOOR ATTHIS 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 commonly used andunderstood by operators to define a design feature that must be maintained throughout the life of the airplane.AUG 2013767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-123AWLs – IMPACT-RESISTANTFUEL TANK ACCESS DOORAWL Number Task Interval ApplicabilityDescription57-AWL-01 CDCCL N/AALLImpact-Resistant Fuel Tank Access DoorsConcern: A potential exists for non-impact-resistant doors to be installed in locations that require impactresistant doors. A high energy impact on a non-impact-resistant fuel tank access door may cause a fuelleak, and in the presence of an ignition source, may result in a catastrophic fire.Immediately prior to the installation of each of the Fuel Tank AccessDoor 532BB, 632BB, 532DB, 632DB,532EB, 632EB, 532FB, 632FB, 531BB, 631BB, perform the following:1. Verify that the fuel tank access door is impact-resistant. Impact-resistantdoors have ends that areflat and a smooth inner surface.Doors with rounded ends and visible machined stiffening ribs onthe inner surface are not impact-resistant (refer to Boeing AMMs 28-11-01 and 28-11-02).JAN 2013D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-124767 MAINTENANCE PLANNING DATAE. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)Maintenance requirements arising from aircraft certification activities are described in FAR 25.1309 and AC 25.1309. Independent of the MSG-3 analysisprocess, these CMRs are developed as part ofthe aircraft systems safety analyses required for aircraft certification. CMR tasks are identified wheneversystem probabilities and failure effects are not expected to fall within an acceptable range without a periodic maintenance requirement.There are two categories of CMRs. The first are those tasks associated with items critical tosafety of flight; these "critical" systems must have anexpected probability of failure within the "extremely improbable"range. The second category of CMRs are those tasks associated with items essential tosafety of flight; these "essential" systems must have an expected probability offailure 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 2012767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-125FIGURE 4. CERTIFICATION MAINTENANCE REQUIREMENTS(CMRs) EXAMPLE(P, N, H OR G)767 CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)EXAMPLE ILLUSTRATING FORMATALLALLG = G.E. CF6-80A ENGINE, AND D = RR RB211-524HENGINE.P = P&W JT9D-7R4 ENGINE,N = PW4000 ENGINE, H = G.E. CF6-80C ENGINE,(A to Z) Used where no specific MM coverage exists(00 to 99) MM SUBJECT NUMBER(12 to 80) ATA CHAPTER(00 to 99) MM SECTION NUMBER6-600 Inspection/Check7-700 Cleaning/Painting1-100 Fault Isolation2-200 Maintenance practices3-300 Servicing4-400 Removal/Installation5-500 Adjustment/Test(1 to 7) MM PAGE BLOCK(A to Z) UNIQUE ALPHA INDENTIFIER27-51-00-5DOP9-XXX-XX-XX-XXTKASCATSYSTEMS TASK DESCRIPTION04000 HRSACCESS119ALZONE120PERFORM BITE TEST OF FLAP/SLAT ELECTRONICS UNIT (FSEU).CMRINTERVALAPLENGAPPLICABILITYITEM NUMBERMPDSEP 2008D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-126767 MAINTENANCE PLANNING DATAPAGE FORMAT: CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)COLUMN EXPLANATIONMPD ITEM NUMBER Each task in the MPD is identified with a uniquenumber. The first 6 digits (excluding the P, N, H, G or D engine identifier) correspond to theappropriate ATA Chapter-Section-Subject in the Boeing Maintenance Manual (MM) that deals generally with the task. When information specific tothe task is provided, a seventh digit indicates the first digitof the page block where it can be found in the MM. Alpha characters following the seventhdigit differentiate between multiple tasks in the same page block. When information specific to the task is not provided in the MM, the seventh digit isan alpha character.TASKMSG-3 TASK CATEGORIESLU = LUBRICATIONSV = SERVICINGVC = VISUAL CHECKOP = OPERATIONAL CHECKIN = INSPECTIONFC = FUNCTIONAL CHECKRS = RESTORATIONDS = DISCARDAny act of consumable replenishment for the purpose of maintaining inherent design capabilities.Any act of consumable replenishment for the purpose of maintaining inherent design capabilities.A visual failure finding task to determine if an itemis fulfilling its intended purpose. Does not requirequantitative tolerances.A failure finding task to determine if an item isfulfilling its intended purposes. Does not requirequantitative tolerances.An examination of an item against a specific standard. This is a potential failure finding task.A quantitative check to determine if one or more functions of an item performs within specified limits.This is a potential failure finding task.Reworking, replacement of parts or cleaning necessary to return an item to a specific standard.The removal and replacement of an item.CMR INTERVAL CMR interval specified in terms of flight hours, flight cycles, calendar time, lettercheck, or Daily Check. Whentwo intervals are listed for a singletask, the top interval is the threshold and the bottom one is the repeat interval. A"NOTE" is used to indicate that an explanation is provided under thetask description.ZONEAirplane Zone Number (see Zone Diagrams,Section 3) where task is performed.ACCESSAccess Panel/Door Number (see Access Panel/Door illustrations, Section 4)required to be opened to perform the task.OCT 2012767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-127APPLICABILITYAPL ENGApplicable Airplane Model and Engine. "ALL" applies to all models of airplanes or engines. A "NOTE" refers to an explanationunder the taskdescription. Specific models of airplanes and engines are listed below:APL200 = 767-200, -200ER300 = 767-300, -300ER400E = 767-400ERPASS = Passenger AirplanesSF = 767-200 Special Freighter300F = All 767-300 FreightersBCF = 767-300 Boeing Converted FreighterALL = All AirplanesENGINE4000 = 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 RB211-524HTASK DESCRIPTION Descriptionof the task to be performed.COLUMNEXPLANATIONSEP 2008D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-128767 MAINTENANCE PLANNING DATACMR TASKSMPDITEMNUMBER TASKCMRINTERVAL ZONE ACCESSAPPLICABILITY767CERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTION24-33-00-6A OP 00048 HRS 212ALL ALLCheck Standby Power System operation (if not checked by crew).Interval Note: Task should not exceed 48 elapsed clock hours.26-10-00-6A OP 00048 HRS 212ALL ALLOperationally Check AFOLTS (AutomaticFire/Overheat Logic Test System) withEng/APU/Cargo Test Switch (if not checked by crew).Interval Note: Task should not exceed 48 elapsed clock hours.27-21-00-5A FC 00400 HRS 211ALL ALLPerform Single Hydraulic System Check ofeach rudder PCA using each HydraulicSystem in sequence. This also verifies that the Rudder and Elevator Shutoff Valvesare open.27-31-00-5B FC 00400 HRS 211ALL ALLPerform Single Hydraulic System Check ofeach Elevator PCA using each hydraulicsystem in sequence.27-51-00-5D OP 04000 HRS 120 119AL NOTE ALLPerform Bite Test of Flap/Slat Electronics Unit (FSEU).Airplane Note: Applicable to all 767 Airplanes except the 767-400ER.27-51-00-5I FC 12000 HRS 552561652661400E ALLFunctionally Check the Wing Flap Drive No-back Brakes.Note: CMR frequency is 12000 Hours for the Outboard Flap No-back Brakes (Two StarCMR). This CMR does not apply to the Inboard Flap No-back Brakes, which has a MRB2C interval. See AC 25-19 for Two Star CMR definition.28-22-00-5ADELETEDOP04000 HRS119212521119AL521QBNOTEALLOperationally Check Center Auxiliary Fuel Tank Override Pumps and Pressure Switches.Airplane Note: Applicable only to A/C with deactivated Center Auxiliary Fuel Tank.28-25-00-5BDELETEDOP04000 HRS212551ALLALLCheck operation of APU DC Fuel Pump Isolation Valve.28-41-00-5ADELETEDFC04000 HRS212531532631632NOTEALLPerform Comparison Check of each channel ofthe Fuel Quantity Indicating System(FQIS) using measuring sticks. (Main FuelTank should contain less than 10,000 LBS.each)Airplane Note: SB 767-28A5. Task is applicable to airplane Line Numbers 1 through 80and 82 through 83 which have not incorporated SB.OCT 2012767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-12929-11-00-5A OP 04000 HRS 195211195SL NOTE ALLOperationally Check ADP Speed Topping Shutdown Circuitry.SB 767-29-4. CMR Classification can bedeleted provided SB 767-29-4 is incorporated.Airplane Note: SB 767-29-4. Task is applicable to airplane Line Numbers 7-13, 15-18,20 and 21 which have not incorporated this SB.29-11-00-6F FC 12000 HRS 211 ALL ALLCheck gross internal leakage of each Hydraulic System (Left, Center & Right).Note: For the 767-200/300/300F Models, the internal leakage limit for the Left, Center,and Right Hydraulic Systems is4.5 GPM. This rate permits the leakage to increasebefore a subsequent leakage check and not become more than the 6.0 GPM approvedlimit.Note: For the 767-400ER, the internal leakage limits for the Left and Right Systems arethe same as for the other 767 models. The Internal Leakage Limit for the CenterHydraulic System is 2.5 GPM. This ratepermits the leakage to increase before asubsequent leakage check and not become more than the 4.0 GPM approved limit.29-11-00-6G FC 12000 HRS 211324335345324GL324JL324LL335EB335GB335HB345EB345GB345HBALL ALLCheck Internal leakage of Elevator and Rudder Power Control Actuators (Left, Centerand Right).29-21-00-5A OP 06000 HRS 1441982111961742ALL ALLOperationally Check Auto and Manual RAT Deployment Systems, RAT Hydraulic Pumpand Drive System.31-41-00-2A OP 00100 HRS 212NOTE ALLPerform a readout of all EICAS maintenance messages by pressing the ECS/MSGDisplay Select Switch (if not checked by crew).Airplane Note: Applicable to all 767 airplanes except the 767-400ER.31-41-02-4A OP 10800 HRS 212NOTE ALLCheck operation (including L-R Switching) ofthe Right EICAS Computer (if not checkedby crew).Airplane Note: Applicable to all 767 airplanes except the 767-400ER.MPDITEMNUMBER TASKCMRINTERVAL ZONE ACCESSAPPLICABILITY767CERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTIONOCT 2012D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-130767 MAINTENANCE PLANNING DATA31-63-00-2A OP 00100 HRS 212400E ALLPerform a readout of all EICAS Maintenance Messages through access of the 31 MCDP/MSG on the MCDU Maintenance Display (if not checked by crew).31-51-00-5B OP 00600 HRS 119211212312119AL312ARBCFSFALLOperationally Check take-off warning system.31-51-00-5C OP 00072 HRSNOTE211212BCFSFALLOperationally Check the take-off configuration warning alert.Interval Note: Task should not exceed 72 elapsed clock hours.32-35-00-5A OP 04000 HRS 119120211119AL NOTE ALLCheck operation of the Main/Nose Landing Gear Alternate Extend System. Check loadlimiters for evidence of partial or fully crushed core.Airplane Note: Applicable to all 767 Airplanes except the 767-400ER.32-41-00-5A OP 00250 HRS 211NOTE ALLOperationally Check Alternate Brake System Including Alternate Brake Selector Valve.SB 767-32-4. CMR Classification can be deleted, provided SB 767-32-4 is incorporated(Line Numbers 4, 24, 28, 30, 32, 35 and 47and on incorporated either the SB or theSB equivalent).Airplane Note: Airplanes with Dual Cable System.32-41-05-4A OP 00250 HRS 211NOTE ALLOperationally Check Accumulator Isolation Valve.Airplane Note: SB 767-32-4. Task is applicable to airplanes which have not incorporatedSB (Line Numbers 4, 24, 28, 30, 32, 35 and47 and on incorporatedeither the SB or theSB equivalent).36-11-01-6C IN 1C 411 411CL411ERALL NOTEPerform Dye Penetrant Inspection of the Eng 1 IP Bleed Duct and check the torque ofthe Flange Bolts.Engine Note: Rolls-Royce Service Bulletin 75-9285: Applicable to Rolls-RoyceRB211-524G/H engines that have not incorporated this service bulletin or equivalent.36-11-01-6C IN 1C 421 421CL421ERALL NOTEPerform Dye Penetrant Inspection of the Eng 2 IP Bleed Duct and check the torque ofthe flange bolts.Engine Note: Rolls-Royce Service Bulletin 75-9285: Applicable to Rolls-RoyceRB211-524G/H Engines that have not incorporated this service bulletin or equivalent.MPDITEMNUMBER TASKCMRINTERVAL ZONE ACCESSAPPLICABILITY767CERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTIONOCT 2012767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-13152-51-07-4A DS 9 YRS 211212NOTE ALLDiscard the Flight Deck Door Strike Assembly.Airplane Note: Applicable to Airplane Line Number 895 and on and any airplane that hasincorporated Service Bulletin 767-25-0325 or 767-25-0327 or 767-25-0332.D77-35-00-2B OP 00560 HRS 119120119AL ALL 524Verify that there are no Engine 1 EEC Category 2 faults.D77-35-00-2B OP 00560 HRS 119120119AL ALL 524Verify that there are no Engine 2 EEC Category 2 faults.D77-41-00-5A OP 00400 HRS 212ALL 524Check the operation of the Standby Engine Indicator (SEI) by actuating the Test Switch(if not checked by crew).G73-21-06-6A OP 04000 HRS 411 416AR ALL 80AVerify proper power input signal to the L Flight Idle Select Solenoid on the EngineFuel Control.G73-21-06-6A OP 04000 HRS 421 426AR ALL 80AVerify proper power input signal to the R Flight Idle Select Solenoid on the EngineFuel Control.G73-21-07-5A OP 04000 HRS 211411416AR ALL 80AVerify proper EEC detection of a faultin the Fail-Fixed Solenoid Circuit – L Eng.G73-21-07-5A OP 04000 HRS 211421426AR ALL 80AVerify proper EEC Detection of a fault in the Fail-Fixed Solenoid Circuit – R Eng.G77-00-00-6D OP 00400 HRS 211ALL 80ACheck operation of Standby Engine Indicator by actuating Test Switch (if not checkedby crew).G78-00-00-6R IN 04000 HRS 415416415AL416ARALL 80AVisually Inspect the Nacelle/Strut Fire and Drainage Seals for wear anddamage/deterioration – L Eng.G78-00-00-6R IN 04000 HRS 425426425AL426ARALL 80AVisually Inspect the Nacelle/Strut Fire and Drainage Seals for wear anddamage/deterioration – R Eng.H77-41-00-5A OP 00400 HRS 211NOTE 80CCheck operation of Standby Engine Indicator by actuating Test Switch (if not checkedby crew).Airplane Note: Applicable to all 767 Airplanes except the 767-400ER.H77-35-00-2B OP 02000 HRS 120 119AL NOTE 80CVerify that there are no Engine 1 or Engine 2 Category 2 (C2) Faults.Airplane Note: Airplanes with Full Authority Electronic Propulsion Control Systems.MPDITEMNUMBER TASKCMRINTERVAL ZONE ACCESSAPPLICABILITY767CERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTIONOCT 2012D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-132767 MAINTENANCE PLANNING DATAH78-00-00-6R IN 04000 HRS 415416415AL416ARALL 80CVisually Inspect the Nacelle/Strut Fire and Drainage Seals for wear anddamage/deterioration – L Eng.H78-00-00-6R IN 04000 HRS 425426425AL426ARALL 80CVisually Inspect the Nacelle/Strut Fire and Drainage Seals for wear anddamage/deterioration – R Eng.H78-00-00-6T IN 06000 HRS 411 NOTE413AL414AR415AL416AR417AL418AR400E 80CVisually Check the Engine 1 Thrust Reverser Bull-Nose Seal for damage.Note: This CMR is a Two Star CMR. See AC 25-19 for Two Star CMR Definition.Access Note: The Thrust Reverser Sleeve must be partially extended for this check.H78-00-00-6T IN 06000 HRS 421 NOTE423AL424AR425AL426AR427AL428AR400E 80CVisually Check the Engine 2 Thrust Reverser Bull-Nose Seal for damage.Note: This CMR is a Two Star CMR. See AC 25-19 for Two Star CMR definition.Access Note: The Thrust Reverser Sleeve must be partially extended for this check.H78-34-00-5ADELETEDFC05000 HRS211212411413AL400E80CFunctionally Check the Engine 1 Directional Pilot Valve (DPV) of the Thrust Reverser todetect pneumatic leakage.Note: This CMR is the subject of NPRM 2000-NM-24-AD. This CMR will be deletedwhen the final rule has been issued.H78-34-00-5ADELETEDFC05000 HRS211212421423AL400E80CFunctionally Check the Engine 2 Directional Pilot Valve (DPV) of the Thrust Reverser todetect pneumatic leakage.Note: This CMR is the subject of NPRM 2000-NM-24-AD. This CMR will be deletedwhen the final rule has been issued.N77-35-00-2B OP 01000 HRS 119120119AL ALL 4000Verify that there are no Engine 1 or Engine 2 EEC Category 2 Faults (EEC CH-A/B FaultCat 2).N77-41-01-4A OP 00400 HRS 212 NOTE 4000Check the operation of the Standby Engine Indicator (SEI) by actuating the Test Switch(if not checked by crew).Airplane Note: Applicable to all 767 Airplanes except the 767-400ER.MPDITEMNUMBER TASKCMRINTERVAL ZONE ACCESSAPPLICABILITY767CERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTIONOCT 2012767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-133P73-21-07-5A OP 04000 HRS 211411414AR416AR418ARALL 7R4Verify proper Power Input Signal to the L Eng EEC Trim Unlock Solenoid.P73-21-07-5A OP 04000 HRS 211421424AR426AR428ARALL 7R4Verify proper Power Input Signal to the R Eng EEC Trim Unlock Solenoid.P77-41-00-5A OP 00400 HRS 211 ALL 7R4Check operation of Standby Engine Indicator by actuating Test Switch (if not checkedby crew).P78-00-00-6R IN 04000 HRS 411413414415416431435413AL414AR415AL416AR417AL418AR431AT431BT431DTALL 7R4Visually inspect the Nacelle/Strut Fire and Drainage Seals for wear anddamage/deterioration – L Eng.P78-00-00-6R IN 04000 HRS 421423424425426441445423AL424AR425AL426AR427AL428AR441AT441BT441DTALL 7R4Visually Inspect the Nacelle/Strut Fire and Drainage Seals for wear anddamage/deterioration – R Eng.MPDITEMNUMBER TASKCMRINTERVAL ZONE ACCESSAPPLICABILITY767CERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTIONOCT 2012D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-134767 MAINTENANCE PLANNING DATAF. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONSTitle 14 Code of Federal Regulations Sections 121.703 and 135.415 state that “each certificate holder shall report any failure,malfunction, or defect in anaircraft, system, component, or powerplant that occurs or is detected at any time if, in its opinion, that failure, malfunction, or defect has endangered ormay endanger the safe operation of an aircraft”. Section 125.409also requires reporting of failures, malfunctions or defects.In many cases a reportablefailure or malfunction will be obvious, but thereare some failure modes related to uncontrolled high thrust that are reportable but may not be obvious. Thefollowing information is provided, as required by FAA Exemption No. 8119, to assist the operators in identifying reportable malfunctions related touncontrolled high thrust.The FAA has concluded that the loss of capability to control thrust dueto a failure of the enginethrust control system may endanger the aircraft. Thisincludes any malfunctions having one ormore 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 presentlevel of safety ismaintained and/or to identify failureconditions 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 ormore of the followingphrases:• “thrust control”• “no response to thrust lever”• “auto-acceleration”• “uncontrolled high thrust”OCT 2012767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-135In 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 responsibility for §§ 121.703,125.409, and 135.415.In addition to filing reports withthe FAA, it is recommended that a copy be sent to Boeing and to the engine manufacturer.OCT 2007D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for detailsPage 9.0-136767 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK