767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-1767MAINTENANCE PLANNING DATA (MPD) DOCUMENTSECTION 9AIRWORTHINESS LIMITATIONS (AWLs) ANDCERTIFICATION MAINTENANCE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)D622T001-9JULY 2011COMPILED AND PUBLISHED BY:MAINTENANCE PROGRAMS ENGINEERINGCOMMERCIAL AVIATION SERVICESBOEING COMMERCIAL AIRPLANE GROUPSEATTLE, WASHINGTONJUL 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-2767 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3TABLE OF CONTENTSREVISIONS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 .................................................................................................................................................................................................... 9.0-19A. SCOPE................................................................................................................................................................................................................................... 9.0-21B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS..................................................................................................................................... 9.0-21C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFEPARTS .............................................................................................................................. 9.0-87D. AIRWORTHINESS LIMITATIONS – SYSTEMS..................................................................................................................................................................... 9.0-89E. PAGE FORMAT: FUEL SYSTEMS AIRWORTHINESS LIMITATIONS................................................................................................................................... 9.0-92F. AIRWORTHINESS LIMITATIONS – NITROGEN GENERATION SYSTEM TASKS ..............................................................................................................9.0-111G. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRS)............................................................................................................................................9.0-115H. PAGE FORMAT: CERTIFICATION MAINTENANCE REQUIREMENTS (CMRS).................................................................................................................9.0-117I. CERTIFICATION MAINTENANCE REQUIREMENTS TASKS...............................................................................................................................................9.0-119J. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS..................................................................................................................... 9.0-125AUG 2010D622T001-9BOEING 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 issued as Revision "B" to Section 9 of theMPD, this issue is considered the originalrelease because it is now assigned a newdocument number (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."This paragraph outlines the requirements for the 50 Series inspections for the newlycertified Model 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)10/10/95JUL 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6767 MAINTENANCE PLANNING DATAFEBRUARY 1996Revised CMRs H77-35-00-2Band N77-35-00-2B to increase CMR interval from 500HRS to 1000 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 Chave been merged into a new section B and remaining sections have beenrenumbered.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 1000HRS to 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 APPROVALJUL 2011767 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 767-400ERand revised Airplane Applicability for currentAWLs. Revised current AWL title to moreaccurately reflect inspection areas. Revised AWL for Strut to reflect reassessment ofthe damage tolerance ratings.Revised interval for CMRs 24-33-00-6Aand 26-10-00-6A from DAILY to 48 HRS.Added CMR 27-51-00-5I applicable only tothe 767-400ER airplane. Added CMR H78-34-00-5A applicable to airplanes with GE CF6-80C2 engines.Revised CMR 29-11-00-6F by adding a note to indicate the hydraulic system 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.Added AWLs for Fuselage to reflect reassessment of damage tolerance rating due torecent test and fleet performance data.Submitted by:N. HENNIGS (Boeing)7/6/00Approved by:A. BAHRAMI (FAA)FEBRUARY 2001Revised CMR 31-41-00-2A to limit airplaneapplicability to the 767-200/-300 airplanes.Added CMR 31-63-00-2A applicable only tothe 767-400ER airplane. Deleted CMRH78-00-5A for both Engine 1 and Engine 2. Revised CMR N77-41-01-4A and H77-00-00-6D by adding an airplane note applicable to the 767-200/300 airplanes only. Revised statement in preamble to airworthiness limitations thatspecifies roll back of any escalated baseline structural inspection intervals whenreaching 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 toairplanes incorporating Boeing ServiceBulletin 767-25-0325. This amended typecertificate complieswith the new 14 CFR25.795 and the amended 14 CFR 25.772 as issued under Federal Register Docket No.FAA-2001-11032.Submitted by:LINH Q. VU (Boeing)8/30/02Approved by:L. LIU-NELSON (FAA)REVISIONSREVISION AND REVISION DESCRIPTION APPROVALJUL 2011D622T001-9BOEING 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 895and on and any airplane that has incorporated Service Bulletin 767-25-0325 or 767-25-0327 or 767-25-0332.Revised the Structural Safe Life Parts section to reference current Service Letter 767-SL-32-092 in place of superseded Service Letters 767-SL-32-21 and 767-SL-32-37.Submitted by:LINH Q. VU (Boeing)10/15/02Approved by:L. LIU-NELSON (FAA)AUGUST 2004Revised Airworthiness Limitations (AWL) Section 9 to add FAA Letter 120S-03-953 and6 page enclosure as an AMOC for AD 2003-18-10 in lieu of superseded AD 2001-08-28and FAA AMOC letter 120S-02-962.Revised Section 9 CMR 36-11-01-6C to add Rolls-Royce engine note on Page 9.1-3.Revised the Structural Safe Life Parts Section page 9.0-57 to escalate Life Limits anddefine additional Life Limit components for the767-400ER.Submitted by:S. A. PIERINI (Boeing)8/15/04Approved by:JULY 2005Revised CMR 31-41-02-4A Interval from04000 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 APPROVALJUL 2011767 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 ofthe Auto Shutoff and Ground Fault Interrupter systems, and design limitations of theHot Short Protector 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 from 4 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 – Systems section 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 APPROVALJUL 2011D622T001-9BOEING 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 onExceptional Short-Term Extensions for AWLs to clarify notification requirements.Revised Systems AWL Page Format paragraphto become Section E. Page Format:Fuel Systems Airworthiness Limitations,and relettered the Sections followingSection E.Added AWL Number 28-AWL-27, a yearly checkof the Main and Center Auxiliary FuelTank Boost Pump Ground Fault Interruption (GFI) Control Relay System, applicable toairplane Line Numbers 961 and on and airplanes that have incorporated ServiceBulletin 767-28A0085.Added AWL Number 28-AWL-28, a yearly check of the Center Auxiliary Fuel TankOverride/Jettison Fuel Pump Uncommanded-On System, applicable to airplane LineNumbers 961 and on and airplanes thathave incorporated Service Bulletin767-28A0085.Revised CMR 52-51-07-4A Task Interval from6 years to 9 years to reflect improvedreliability data for the Flight Deck Security Door.Added Section I. Reporting Uncontrolled High Thrust Failure Conditions perFAR 121.703 and 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 limitationbased upon engineering review and operator maintenance practice.Revised 28-AWL-18 to reflect the new maximum loop resistance values associated withthe lightning protection of the unpressurized FQIS wire bundle installations so as tosatisfy the Airworthiness Limitation Instructions required by SFAR 88. Also removedthe joint resistance values and 36000FH task interval limitation based upon engineeringreview and operator maintenance practice.Submitted by: John Sabolchy(Boeing)Approved by:Dorr Anderson (Seattle FAA ACO):REVISIONSREVISION AND REVISION DESCRIPTION APPROVALJUL 2011767 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 flighthours 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 Gearand 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 Gear Support 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 APPROVALJUL 2011D622T001-9BOEING 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 of 37,500 cycles due to structural repair forL/N 973.Submitted by: John Sabolchy(Boeing)Approved by: Seattle FAA ACOREVISIONSREVISION AND REVISION DESCRIPTION APPROVALJUL 2011767 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 flighthour 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 airplaneeffectivities and intervals from Service Bulletins 767-53-0103, 767-53-0190,767-53-0191, 767-53-0208,767-53-0210, and 767-53-0212.Revised text to refer to correct Flight Standards Handbook.Added Flag Note to the Airworthiness Limitations-Structural Inspection Table to 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 referenceto applicability and a note to refer to the DTR forms.Revised SSIs 54-50-I01 and 54-50-I04 by dividing them into their own separate taskrequirements.(Continued on next page)Submitted by: John Sabolchy(Boeing)Approved by: Jeffrey Duven, Seattle FAA ACOSIGNATURE ON FILE07/09/2009REVISIONSREVISION AND REVISION DESCRIPTION APPROVALJUL 2011D622T001-9BOEING 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)and added wording regarding the tracking of removable parts. Forty revised TrailingEdge Flap limitations are applicable to 767-200, -300 passenger and -300 freighterairplanes, Line Numbers 922 and later, except as noted, and are applicable to all 767-400ER airplanes. Forty-nine new TrailingEdge Flap limitations are applicable to the767-200, -300 passenger and -300 freighter airplanes, Line Numbers 1 to 921, exceptas noted. Added airplane effectivity note to theAIRPLANE ENGINE APPLICABILITYcolumn of both entries for Airworthiness Limitation 53-10-I21A.Revised CMR section by correcting typographicalerrors by changing CMR D77-41-01-4A toCMR D77-41-00-5A and CMR P77-00-00-6B to CMR P77-41-00-5A.DECEMBER 2009Revised the Airworthiness Limitations section to reflect the assessment of the 767-300Boeing 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 APPROVALJUL 2011767 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” toStep 1 to clarify the number of bondingstraps.Added 28-AWL-29 and 28-AWL-30 as Critical Design 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 APPROVALJUL 2011D622T001-9BOEING 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 wererevised 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 wererevised by updating the additional inspections with referenceto SB 767-53-0211. For both L/Ns 969 and 971, 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 Sectionto 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 theappropriate 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 the calculated 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 APPROVALJUL 2011767 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 interval from 6,600 Flight Hours (FH) to 3,000 FHbased on updated analysis.Revised 47-AWL-05 by updating the intervalfrom 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 1406 to BS 1428 and S-25R to S-27R centerlinesmust be inspected with external detailed inspection every600 flight 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 APPROVALJUL 2011D622T001-9BOEING 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 FILE08/05/2011REVISIONSREVISION AND REVISION DESCRIPTION APPROVALJUL 2011Section 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 9.0-19LIST OF EFFECTIVE PAGES767 MAINTENANCE PLANNING DATA9.0 1 JUL 20119.0 2 BLANK9.0 3 AUG 20109.0 4 BLANK9.0 5 JUL 20119.0 6 JUL 20119.0 7 JUL 20119.0 8 JUL 20119.0 9 JUL 20119.0 10 JUL 20119.0 11 JUL 20119.0 12 JUL 20119.0 13 JUL 20119.0 14 JUL 20119.0 15 JUL 20119.0 16 JUL 20119.0 17 JUL 20119.0 18 JUL 20119.0 19 JUL 20119.0 20 BLANK9.0 21 JUN 20009.0 22 JUN 20109.0 23 JUN 20109.0 24 JUN 20109.0 25 JUN 20109.0 26 DEC 20099.0 27 NOV 20099.0 28 DEC 20099.0 29 DEC 20099.0 30 JUN 20109.0 31 JUN 20119.0 32 JUN 20119.0 33 JUN 20119.0 34 JUN 20119.0 35 JUN 20119.0 36 JUN 20119.0 37 JUN 20119.0 38 JUN 20119.0 39 JUN 20119.0 40 JUN 20119.0 41 JUN 20119.0 42 JUN 20119.0 43 JUN 20119.0 44 JUN 20119.0 45 JUN 20119.0 46 JUN 20119.0 47 JUN 20119.0 48 JUN 20119.0 49 JUN 20119.0 50 JUN 20119.0 51 JUN 20119.0 52 JUN 20119.0 53 JUN 20119.0 54 JUN 20119.0 55 JUN 20119.0 56 JUN 20119.0 57 JUN 20119.0 58 JUN 20119.0 59 JUN 20119.0 60 JUN 20119.0 61 JUN 20119.0 62 JUN 20119.0 63 JUN 20119.0 64 JUN 20119.0 65 JUN 20119.0 66 JUN 20119.0 67 JUN 20119.0 68 JUN 20119.0 69 JUN 20119.0 70 JUN 20119.0 71 JUN 20119.0 72 JUN 20119.0 73 JUN 20119.0 74 JUN 20119.0 75 JUN 20119.0 76 JUN 20119.0 77 JUN 20119.0 78 JUN 20119.0 79 JUN 20119.0 80 JUN 20119.0 81 JUN 20119.0 82 JUN 20119.0 83 JUN 20119.0 84 JUN 20119.0 85 JUN 20119.0 86 JUN 20119.0 87 JUN 20109.0 88 JUN 20109.0 89 MAY 20109.0 90 MAY 20109.0 91 APR 20089.0 92 APR 20089.0 93 MAY 20109.0 94 MAY 20109.0 95 MAY 20109.0 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 JUL 20109.0 112 JUL 20119.0 113 JUL 20119.0 114 JUL 20119.0 115 JUL 20109.0 116 SEP 20089.0 117 JUL 20109.0 118 SEP 20089.0 119 JUL 20109.0 120 SEP 20089.0 121 SEP 20089.0 122 SEP 20089.0 123 SEP 20089.0 124 SEP 20089.0 125 JUL 20109.0 126 OCT 2007JUL 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-20767 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-21A. 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 8 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. The supplemental structural inspections listed in thisSection 9 “AirworthinessLimitations” are for those SSIs that do not receive adequate fatigue damage detection opportunity from the initial baseline structural program that is listedin Section 8. The supplemental inspections shown in Section 9Airworthiness Limitations are tobe accomplished in conjunctionwith and not as asubstitute for the existing structural maintenance program found in Section 8.JUN 2000D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-22767 MAINTENANCE PLANNING DATAThe 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.A formal control system must be established for removable structural parts (repairable/rotable/expendables) which are subject to supplemental inspections,such as the flap support members. If part usage history data isavailable for all parts, the supplemental inspection program would follow the actual partusage history data. If part usage history data is not available,but records indicate that no part changes have occurred between airplanes, airplane usagehistory data can be used to start a tracking program for the supplemental inspections. If parts usage data is not available and the parts could have beenswitched between airplanes in the same maintenance program, it should be assumed that the time on any part is equal to the oldest airplane in themaintenance program. If a maintenance program includes airplanes from several operators, the oldest airplane in that group ofairplanes would be usedas the oldest airplane in the maintenance program. After overhaulor upon replacement of a part, as appropriate, a tracking program should be establishedto control the removable parts. This system must also apply toused structural parts which are purchased for installation on anairplane.Where no cumulative cycles history is available for any removed/interchangeable SSI,then calculate the accumulated flight cycles by using previousinstallation history. If previous installation history, too, is not available thenassume that the limiting cycles (threshold)has already been reached and theninspection is to be done before installation of the removed SSI on the applicable airplane series.JUN 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-23The 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.The Airworthiness Limitations – StructuralLimitations 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.JUN 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-24767 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 beforecrossing 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 9.0-25In 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.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 in the MPDSection 8 (Structures C-check is defined inSection 1). This means that any operator, who has escalated the structures programby changing either taskintervals or the C-check interval, must reduce the repeat frequencies back to the MPD baseline structures program intervals before accumulating 50,000 or40,000 flight cycles respectively. The reasonfor this is that the FAR 25.571 damagetolerance evaluation takes credit for thebaseline structures program.The airworthiness limitations listed in Section 9 cover structure for which the required DTR is not satisfied by the baseline structural inspections ofSection 8. Any continued escalation beyond the MPD baseline structures program may result in additional structure not meeting the required DTR whichwas the basis of certification.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.1There exists only 1 -200SF, and it was modified after 14,900 cycles as a Passenger aircraft.JUN 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-26767 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 thresholdfor 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 9.0-27FIGURE 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 9.0-28767 MAINTENANCE PLANNING DATAFIGURE 3. Mod DateSensitive StructureDEC 2009767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-29REPEAT 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).DEC 2009D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-30767 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 Airplanes PASS (-ER ONLY) = Passenger Airplanes, Extended Range Only.PASS = Passenger Airplanes < 8 HOURS = Airplanes with cumulative stage length (Flight Hours per Landing)200 = 767-200, -200ER less than 8 hours.200SF = 767-200 Special Freighter300 = 767-300, -300ER >8 HOURS = Airplanes with cumulative stage length (Flight Hours per Landing)300BCF = 767-300 Boeing Converted Freighter equal to or more than 8 hours.400E = 767-400ER300F = All 767-300 Freighters4000 = P&W PW4052, PW4056, PW4060, PW40627R4 = P&W JT9D-7R4D and -7R4E80A = GE CF6-80A80C = GE CF6-80C524 = RR RB211-524HJUN 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-31AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLD27-40-I01AStabilizer Trim Actuator–Lower Gimbal Lug AssyBS 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-I05ALatch Cam Support Frame Fitting – Forward large Cargo Door – Fitting Lug Bore 821 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 Chordat Splice 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)JUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-32767 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 atSplice to 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, 43 and 46.L/N 973, lap S-8R: BS 1547 to BS 1561 and S-7R to S-9R centerlines must beinspected with external detailed inspectionevery 600 flight cycles (after reachingthreshold).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: Lap S-8R: BS 1464 to BS 1478and S-7R to S-9R centerlines mustbe inspected with external detailed inspection every 600 flight cycles (afterreaching threshold).220, 230, 250 ALLExcept where noted forL/N 945, L/N 963,L/N 973 and L/N 1004200SF 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/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3353-10-I07B53-30-I04B53-60-I05BSkin Longitudinal Lap Splices – Lower Row – Crown and Upper Lobe,Sections 41, 43 and 46.L/N 973, lap S-8R: BS 1547 to BS 1561 and S-7R to S-9R centerlines must beinspected with external detailed inspectionevery 600 flight cycles (after reachingthreshold).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: Lap S-8R: BS 1464 to BS 1478and S-7R to S-9R centerlines mustbe inspected with external detailed inspection every 600 flight cycles (afterreaching threshold).220, 230, 250 ALLExcept where noted forL/N 945, L/N 963,L/N 973, L/N 1004,200SF and 300BCFType 250,000 Cycles(200, 200SF,300BCF, 300 PASS)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 41,43 and 46.DTR Check Form not applicable to:1) L/N 946, STA 1175-1197, S-26R. Must inspect per SB 767-53-0191.2) L/N 873: STA 1197+82 and 1197+121, S-36R. Must inspect per SB767-53-0103.3) 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 toBS 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: BS 1406 to BS1428 and S-25R to S-27R centerlinesmust be inspected with external detailedinspection every 600 flight cycles (afterreaching threshold).9) L/N 1008: The area within 5 inches ofthe intersection of Lap S-26L stringercenterline with BS 303, 325, 347, and 368must be inspected with externaldetailed inspection every 600 flight cycles (after reaching threshold).100 ALLExcept where noted forL/N 873, L/N 946,L/N 967, L/N 969,L/N 971, L/N 994,and L/N 1008,200SF and 300BCFType 250,000 Cycles(200, 200SF,300BCF, 300 PASS)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/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-34767 MAINTENANCE PLANNING DATA53-10-I07D53-30-I04D53-60-I05DSkin Longitudinal Lap Splices – Lower Row – Bilge and Lower Lobe, Sections 41,43 and 46.DTR Check Form not applicable to:1) L/N 946, STA 1175-1197, S-26R.Must inspect per SB 767-53-0191.2) L/N 873: STA 1197+82 and 1197+121, S-36R. Must inspect per SB767-53-0103.3) 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 toBS 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: BS 1406 toBS1428 and S-25R to S-27R centerlinesmust be inspected with external detailed inspection every 600 flight cycles (afterreaching threshold).100 ALLExcept where noted forL/N 873, L/N 946,L/N 967, L/N 969,L/N 971 and L/N 994200SF and 300BCFType 250,000 Cycles(200, 200SF,300BCF, 300 PASS)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-20 220, 230 ALLExcept 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, 230 200SF Type 250,000 Cycles53-10-I08B53-30-I24BBCF 3 – Frames above S-20, Not Applicable to Areasof Hidden Frame Structure 220, 230 300BCF Type 250,000 Cycles53-10-I08C53-30-I24C53-60-I08CFrames, Below S-20, Frame (Fully visible)100 200SF Type 250,000 Cycles53-10-I08C53-30-I24C53-60-I08CFrames, S-20 and below. BS 246 to BS 786 and BS 1065 to BS 1582100 ALLExcept 200SF, 300BCFType 250,000 Cycles(200, 300 PASS)40,000 Cycles (300F, 400E)53-10-I08C53-30-I24C53-60-I08CBCF 5 – Frames below S-20, All Frames Except the Areas of Hidden Frame Structure 100 300BCF Type 250,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3553-10-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 13.1119 ALL Type 250,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)53-10-I13 Forward Equipment Bay Access Door Cutout– BS 144.5 – BS 163.2. LBL 9 – RBL 9 113, 114 ALL Type 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)53-10-I14BWindow #1 Cutout Structure–BD SILL211, 212 ALL Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-36767 MAINTENANCE PLANNING DATA53-10-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, 114 ALL Type 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, 118 ALL Type 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, 118 ALL Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles(300F, 400E)53-10-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)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3753-10-I21ANLG Wheel Well – BS 287 Bulkhead Details – WL 159 Beam & Bulkhead Webfrom LBL 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-I21ANLG Wheel Well – BS 287 Bulkhead Details – WL 159 Beam & Bulkhead Webfrom LBL 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-24R119 ALL Type 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-24R119 ALL Type 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-27R119 ALL Type 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 on119 ALL Type 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 Cycles53-10-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)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-38767 MAINTENANCE PLANNING DATA53-30-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, 250 ALLExcept 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, 232 300BCF<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, 232 300BCF<4>Type 1Combined Threshold53-30-I01 BCF 3 – Circumferential Splice – Upper Crown at BS 654+22 233, 234 300BCF<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, 232 300BCF<4>Type 250,000 Cycles53-30-I01 BCF 9 – Fuselage Crown Skin STA 654+115 to 786 STR-4R to 4L 231, 232 300BCF Type 250,000 Cycles53-30-I01 BCF 10 – Fuselage Crown Stringers 230 300BCF Type 2Combined Threshold53-30-I01 SF1 – Crown Skin Doubler – RHS Edge of Crown Skin Doubler at RBL 9 233, 234 200SF<4>Type 250,000 Cycles53-30-I01 SF2 – Crown Skin Doubler – Aft Edge Body STA 742 233, 234 200SF<4>Type 230,000 Cycles53-30-I01 SF3 – Crown Skin Doubler – Stringer at Circumferential Splice 233, 234 200SF<4>Type 250,000 Cycles53-30-I01 SF5 – Crown Skin Doubler – At STA 676 Skin Splice, at STR-8L 233, 234 200SF<4>Type 250,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3953-30-I01 SF6 – Crown Skin Doubler – At VHF Antenna Installation 233, 234 200SF<4>Type 250,000 Cycles53-30-I01 SF8A – Crown Skin Doubler – Skin Lap Splice at STR-2R and STR-8L Inner Skin 233, 234 200SF<4>Type 250,000 Cycles53-30-I01 SF8B – Crown Skin Doubler – Skin Lap Splice at STR-2R and STR-8L Outer Skin 233, 234 200SF<4>Type 250,000 Cycles53-30-I01 SF9 – Section 43 Crown Skin – Aft of Doubler 233, 234 200SF<4>Type 237,500 Cycles53-30-I01 SF10 – Section 43 Crown Stringers – Aft of External Doubler 233, 234 200SF<4>Type 225,000 Cycles53-30-I04A Skin Longitudinal Lap Splices – Upper Row – Crown and Upper Lobe, Sections 41, 43and 46Note: Applicable to S-8R, STA 434 to 654 + 22.230 200SF, 300BCF Type 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 + 110.230 300BCF Type 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 + 110.230 300BCF Type 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, 300BCF Type 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 676.100 200SF300BCFExcept 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/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-40767 MAINTENANCE PLANNING DATA53-30-I05 STA 786 Circumferential Splice in the Body Crown 240 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 BodyCrown – Specified Locations 230, 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 to S-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-29R 122 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 – 482 122 200300 PASSType 250,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4153-30-I19F Forward Large Cargo Door Cutout – Upper Sill: BS 480 122 200300 PASSType 250,000 Cycles53-30-I19G Forward Large Cargo Door Cutout – Upper Sill: BS 482 to BS 493 122 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-22R122 300BCF300F400E<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, 232 300BCF300F400E<2>Type 240,000 Cycles53-30-I19AD Forward Large Cargo Door Cutout – Upper Main Sill Inner Chord at BS 607 to BS 618 122 300BCF300F400E<2>Type 240,000 Cycles53-30-I19AD1 Forward Large CargoDoor Cutout – Upper Main SillInner Chord Hidden Locations atBS 607 to BS 618122 300BCF300F400E<2>Type 240,000 Cycles53-30-I19AF Forward Large CargoDoor Cutout – Lower Main SillInner Chord Hidden Locations atBS 466 to BS 483 and BS 614 to BS 625124 300BCF300F400E<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 625124 300BCF300F400E<2>Type 240,000 Cycles53-30-I20A Forward Large Cargo Door Cutout –Lower Latch Backup Structure – Latch SupportFitting at BS 487.7 & BS 608.3124 ALL Type 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-42767 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 Door Cutout – Upper Main Sill Inner Chord 230 300 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-20 230, 240, 250 ALLExcept 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-20 231, 232 300BCF Type 250,000 Cycles53-30-I24A53-50-I01A53-50-I02A53-60-I08AFrames – Above S-20, Frame (Fullyvisible) 230, 240, 250 200SF Type 250,000 Cycles53-30-I24A BCF 2 – Frames above S-20, Applicableto Areas of Hidden Frame Structure 231, 232 300BCF<4>Type 250,000 Cycles53-30-I24B Frames above S-20, Frame (Hidden Structure) 220, 230 200SF<4>Type 250,000 Cycles53-30-I24B BCF 4 – Frames above S-20, Applicableto Areas of Hidden Frame Structure 220, 230 300BCF<4>Type 250,000 Cycles53-30-I24C53-60-I08CBCF 6 – Frames below S-20, Applicable Only to Areas of Hidden Frame Structure 100 300BCF<4>Type 250,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4353-30-I24C53-60-I08CFrames – Below S-20, Frame (Hidden Structure) 100 200SF<4>Type 250,000 Cycles53-30-I27 BCF 2 – Circumferential Butt Splice 654+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 Crown 230, 240, 250 200SF Type 150,000 Cycles53-30-I28 BCF 1 – Main Deck Cargo Door Cutout – Auxiliary Sill Inner Chord 231 300BCF<4>Type 250,000 Cycles53-30-I28 SF1 – Main Deck Cargo Door Cutout– Auxiliary Sill Inner Chord 231 200SF Type 250,000 Cycles53-30-I28A Reinforcement Around Cutouts – Main Deck Cargo Door – Cutout Structure –Upper Main Sill Inner Chord at BS 492231 200SF300BCF, 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 632231 200SF300BCF, 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-5L233 200SF300BCF, 300F<2>Type 250,000 Cycles (200SF)Mod Date Sensitive (300BCF)40,000 Cycles (300F)53-30-I28D Reinforcement Around Cutouts – MainDeck Cargo Door – Aft Edge Frame at BS 632and S-16L – Frame Splice231 200SF300BCF, 300F<2>Type 250,000 Cycles (200SF)Mod Date Sensitive (300BCF)40,000 Cycles (300F)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-44767 MAINTENANCE PLANNING DATA53-30-I28E Reinforcement Around Cutouts – MainDeck 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 CutoutAuxiliary Sill Inner Chord 241, 242 200SF Type 250,000 Cycles53-50-I06A Single Emergency Exit Cutout – Frame Inner Chords at BS 859.5, S-18 to S-20 and atBS 883.5, S-16 to S-20241, 242 200, 200SF Type 250,000 Cycles53-50-I06B Single Emergency Exit Cutout – Frame Inner Chords at Sill Intersect at BS 859.5and 883.5241, 242 200, 200SF Type 250,000 Cycles53-50-I06C Single Emergency Exit Cutout– Sill Inner Chord – Upper Sill at BS 859.5 to BS 871.5 241, 242 200, 200SF Type 250,000 Cycles53-50-I06DSingle Emergency Exit Cutout – Sill Inner Chord at Frame Intersect at BS 859.5and BS 883.5241, 242 200, 200SF Type 250,000 Cycles53-50-I06E Single Emergency Exit Cutout –Sill Outer Chord 241, 242 200, 200SF Type 250,000 Cycles53-50-I06F Single Emergency Exit Cutout – Sill OuterChord at Frame Intersect 241, 242 200, 200SF Type 250,000 Cycles53-50-I11 BS 1043 Frame Splice with the Landing Gear Fitting – BS 1043, BL 92, WL 193 toWL 199141, 142 ALL Type 250,000 Cycles(200, 200SF, 300 PASS)40,000 Cycles(300BCF, 300F, 400E)53-50-I13AFuselage Rear Spar Bulkhead – Bulkhead Fitting Inboard Prong Attachment to WingRear SparDELETEDAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4553-50-I13B Fuselage Rear Spar Bulkhead – BulkheadFitting Inner Chord S-20 to S-21 at SeatTrack Bracket131, 132 ALL Type 125,000 Cycles53-50-I13C Fuselage Rear Spar Bulkhead – Inboard ChordFlange – BS 955, BL 91, S-18 to S-20 241, 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-34 151, 152 ALL Type 125,000 Cycles53-50-I1853-50-I2453-50-I28Section 45 Stub Frames – BS 808 – 933 Frame Inner Chord at Stub Beam 131, 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-I19BMLG 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/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-46767 MAINTENANCE PLANNING DATA53-50-I22A Dual Emergency Exit Cutout– Frame Inner Chords 241, 242 200300 PASSType 250,000 Cycles53-50-I22A BCF – Dual Emergency Exit CutoutEdge – Frame Inner Chords 241, 242 300BCF Type 250,000 Cycles53-50-I22B Dual Emergency Exit Cutout – FrameInner Chord at Sill Intersect 241, 242 200300 PASSType 250,000 Cycles53-50-I22B BCF – Dual Emergency Exit Cutout EdgeFrame – Inner Chord at Sill 241, 242 300BCF Type 250,000 Cycles53-50-I22C BCF – Dual Emergency Exit Cutout – Sill Inner Chord 241, 242 300BCF Type 250,000 Cycles53-50-I22D BCF – Dual Emergency Exit Cutout –Sill Inner Chord at Frame 241, 242 300BCF Type 250,000 Cycles53-50-I22E BCF – Dual Emergency Exit – Sill Inner Chord & Strap BS 859.5 and BS 903.5 241, 242 300BCF Type 250,000 Cycles53-50-I22F BCF – Dual Emergency Exit Cutout – Sill Outer Chord 241, 242 300BCF Type 250,000 Cycles53-50-I22G BCF – Dual Emergency ExitCutout – Sill Outer Chord at Frame Intersect 241, 242 300BCF Type 250,000 Cycles53-50-I22 BCF 1 Dual Over wing Emergency Exit Auxiliary Sill at Frame Intersect 241, 242 300BCF<4>Type 250,000 Cycles53-50-I22 BCF 2 Dual Over wing Emergency Exit Auxiliary Sill 241, 242 300BCF<4>Type 250,000 Cycles53-50-I22C Dual Emergency Exit Cutout – Sill Inner Chord 241, 242 200300 PASSType 250,000 Cycles53-50-I22D Dual Emergency Exit Cutout – SillInner Chord at Frame Intersect 241, 242 200300 PASSType 250,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4753-50-I22E Dual Emergency Exit Cutout – Upper Sill Inner Chord at BS 859.5 and BS 903.5 241, 242 300 PASS Type 250,000 Cycles53-50-I22F Dual Emergency Exit Cutout – Sill Outer Chord 241, 242 200300 PASSType 250,000 Cycles53-50-I22G Dual Emergency ExitCutout – Sill Outer Chord at Frame Intersect 241, 242 200300 PASSType 250,000 Cycles53-50-I25A Single Aft Emergency Exit Cutout– Frame Inner Chords 241, 242 300 PASS Type 250,000 Cycles53-50-I25B Single Aft Emergency Exit Cutout – FrameInner Chord at Sill Intersect 241, 242 300 PASS Type 250,000 Cycles53-50-I25C Single Aft Emergency Exit Cutout– Sill Inner Chord 241, 242 300 PASS Type 250,000 Cycles53-50-I25D Single Aft Emergency Exit Cutout – Sill Inner Chord at Frame Intersect 241, 242 300 PASS Type 250,000 Cycles53-50-I25E Single Aft Emergency Exit Cutout – UpperSill Inner chord BS 903.5 241, 242 300 PASS Type 250,000 Cycles53-50-I25F Single Aft Emergency Exit Cutout– Sill Outer Chord 241, 242 300 PASS Type 250,000 Cycles53-50-I25G Single Aft Emergency ExitCutout – Sill Outer Chord at Frame Intersect 241, 242 300 PASS Type 250,000 Cycles53-50-I28 Section 45 Stub Frames – BS 808 – 933 Frame Inner Chord at Stub Beam 131, 132 400E Type 240,000 Cycles53-60-I02 BCF – Fuselage Stringer with Stringer Reinforcement Strap STA 1076 to 1143STR-10R to 13R and STR -9L to 13L153, 154 300BCF Type 240,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-48767 MAINTENANCE PLANNING DATA53-60-I06B Aft Main Cargo Door Cutout – Edge Frames – 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, 154 200SFPASSType 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, 154 200SF300BCFPASSType 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, 154 200SFPASSType 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, 154 300BCF Type 250,000 Cycles53-60-I10 BCF 2 – Bulk Cargo Door Cutout –Edge Frames Inner Chord/Strap 161, 163 200SF300BCF<4>Type 250,000 Cycles53-60-I10A Bulk Cargo Door Cutout – Edge Frames Inner Chord/Strap 161, 163 ALL Type 250,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)53-60-I10B Bulk Cargo Door Cutout – Frame Splice – Aft Edge Frame, BS 1461 Inner Chordat S-26161 ALL Type 250,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4953-60-I10C Bulk Cargo Door Cutout – Upper Main Sill Inner Chord and Strap – BS 1461 161 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, 252 300 PASS Type 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, 252 400E Type 240,000 Cycles53-60-I27B Type I Door Cutout – Upper Main Sill– Inner Chord, BS 1131 to BS 1197+22 251, 252 300 PASS400EType 250,000 Cycles (300 PASS)40,000 Cycles (400E)53-60-I27C Type I Door Cutout – Lower Main Sill– Inner Chord, BS 1131 to BS 1175 251, 252 300 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-24 154 300F<2>Type 240,000 Cycles53-60-I29B Aft Large Cargo Door Cutout – Edge Frame – Inner Chord, BS 1344, S-24.3 154 300F<2>Type 240,000 Cycles53-60-I29C Aft Large Cargo Door Cutout – Upper Main Sill – Inner Chord, BS 1219 154 300F<2>Type 240,000 Cycles53-60-I29D Aft Large Cargo Door Cutout – Lower Main Sill – Inner Chord, BS 1344 154, 156 300F<2>Type 240,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-50767 MAINTENANCE PLANNING DATA53-60-I29F Aft Large Cargo Door Cutout – LowerMain Sill – Inner Chord, BS 1334.3 154, 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-I01AAft 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-I01BAft Pressure Bulkhead – Radial Web Lap Splices311, 312 ALLL/N 424 & on<1>Type 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I01CAft Pressure Bulkhead – Radial Web Lap Splices311, 312 ALLL/N 424 & on<1>Type 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I01DAft Pressure Bulkhead – Circumferential Tear Strap Splice311, 312 ALLL/N 424 & on<1>Type 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I01EAft Pressure Bulkhead – Circumferential Tear Strap311, 312 ALLL/N 424 & on<1>Type 250,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I03 Section 48 – Jackscrew Fitting Lug – Upper Bulkhead at STA 1702 311, 312 200SF Type 150,000 Cycles53-80-I03 Section 48 – Jackscrew Fitting Lug – Upper Bulkhead at STA 1702 311, 312 300BCF, 300FPASSType 150,000 Cycles(200, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)53-80-I13 Section 48 – Pivot Fitting Lug 313, 314 200SF Type 138,600 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5153-80-I13 Section 48 – Pivot Fitting Lug 313, 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 41.5 313, 314 ALL Type 125,000 Cycles54-50-I01 Typical Midspar Chord Construction – JT9D Strut 432, 434, 436,442, 444, 4467R4 Type 250,000 Cycles54-50-I01 Typical Midspar Chord Construction – PW4000 Strut 432, 434, 436,442, 444, 4464000 Type 225,000 Cycles54-50-I01 Typical Midspar Chord Construction – CF6-80A Strut 432, 434, 436,442, 444, 44680A Type 250,000 Cycles54-50-I01 Typical Midspar Chord Construction – CF6-80C Strut 432, 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 Strut 432, 442 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I01a Forward Midspar Chord – CF6-80C Strut 432, 442 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I01c Forward Midspar (Visible Portions) – CF6-80C2 Strut 432, 442 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I01c Forward Midspar (Visible Portions) – CF6-80C2 Strut 432, 442 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-52767 MAINTENANCE PLANNING DATA54-50-I0254-50-I03aSideskins/Skins, Stiffeners and Back-Up Chords – RB211 Strut 433, 443 524<2>Type 250,000 Cycles54-50-I03b Lower Spar Chords, Webs and Thrust Plate – RB211 Strut 431, 433, 441, 443 524<2>Type 225,000 Cycles54-50-I04 Forward Engine Mount Bulkhead – RB211 Strut 433, 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, 4464000 Type 225,000 Cycles54-50-I04 Typical Midspar Chord Construction – CF6-80A StrutNote: No DTR Check Form.432, 434, 436,442, 444, 44680A Type 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 Strut 434, 436, 444, 446 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I04a Mid-Spar Fitting to Chord Splice– CF6-80C Strut 434, 436, 444, 446 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I04c Mid-Spar Chord, Aft (Hidden Details) – CF6-80C Strut 434, 436, 444, 446 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I04c Mid-Spar Chord, Aft (Hidden Details) – CF6-80C Strut 434, 436, 444, 446 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5354-50-I04e Mid-Spar Chord, Aft (Visible Details) – CF6-80C Strut 434, 436, 444, 446 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I04e Mid-Spar Chord, Aft (Visible Details) – CF6-80C Strut 434, 436, 444, 446 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – JT9D Strut 432, 442 7R4<2>Type 250,000 Cycles54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – PW4000 Strut 432, 442 4000<2>Type 250,000 Cycles54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – CF6-80A Strut 432, 442 80A<2>Type 250,000 Cycles54-50-I05 Forward Engine Mount Bulkhead Fitting and Bulkhead – CF6-80C Strut 432, 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 Strut 432, 442 80C (400E)<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I06 Aft Engine Mount Bulkhead – JT9D Strut 434, 436, 444, 446 7R4 Type 250,000 Cycles54-50-I06 Aft Engine Mount Bulkhead – PW4000 Strut 434, 436, 444, 446 4000 Type 250,000 Cycles54-50-I06 Aft Engine Mount Bulkhead – CF6-80A Strut 436, 437, 446, 447 80A Type 250,000 Cycles54-50-I06 Aft Engine Mount Bulkhead – CF6-80C Strut 436, 437, 446, 447 80C (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 Strut 436, 437, 446, 447 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-54767 MAINTENANCE PLANNING DATA54-50-I06a Aft Engine Mount Bulkhead (Barrel Nut Bore) – CF6-80C Strut 436, 437, 446, 447 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I06c Aft Engine Mount Bulkhead (Vertical SpliceStrap) – CF6-80C Strut 436, 437, 446, 447 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I06c Aft Engine Mount Bulkhead (Vertical SpliceStrap) – CF6-80C Strut 436, 437, 446, 447 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I06d Aft Engine Mount Bulkhead (Aft Flange) – CF6-80C Strut 436, 437, 446, 447 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I06d Aft Engine Mount Bulkhead (Aft Flange) – CF6-80C Strut 436, 437, 446, 447 80C (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 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5554-50-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)54-50-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 Strut 431, 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 Strut 431, 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 Strut 410, 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 Strut 410, 420 80C (400E)>8 HoursType 1/16,000 Cycles/70,000 Flt. Hrs.54-50-I10b Forward Engine Mount – CF6-80C Strut 410, 420 80C (400E)< 8 Hours<2>Type 1/16,000 Cycles/70,000 Flt. Hrs.54-50-I10b Forward Engine Mount – CF6-80C Strut 410, 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, 444 524 Type 250,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-56767 MAINTENANCE PLANNING DATA54-50-I11d Aft Engine Mount (Lugs)– CF6-80C Strut 410, 420 80C (400E)< 8 HoursType 1/25,000 Cycles/80,000 Flt. Hrs.54-50-I11d Aft Engine Mount (Lugs)– CF6-80C Strut 410, 420 80C (400E)>8 HoursType 1/25,000 Cycles/80,000 Flt. Hrs.54-50-I11f Aft Engine Mount (Engine TRF ClevisLugs) – CF6-80C Strut 410, 420 80C (400E)< 8 HoursType 1/16,000 Cycles/70,000 Flt. Hrs.54-50-I11f Aft Engine Mount (Engine TRF ClevisLugs) – CF6-80C Strut 410, 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 Strut 437, 447 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I12b SideLoad Fittings – CF6-80C Strut 437, 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 Strut 434, 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 Strut 434, 436444, 44680A<2>Type 250,000 Cycles(200, 300 PASS)40,000 Cycles (300F)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5754-50-I13 Typical Lower Spar Chord and Spar Web Construction – PW4000 Strut 434, 436444, 4464000<2>Type 250,000 Cycles(200, 300 PASS)40,000 Cycles (300F)54-50-I13 Typical Lower Spar Chord and Spar Web Construction – CF6-80C Strut 434, 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 Strut 434, 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 Strut 434, 436444, 44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I13e Lower Spar Chord (Visible) – CF6-80C Strut 434, 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 Strut 432, 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 Strut 432, 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 Strut 432, 442 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I16a Forward Upper Spar (Hidden)– CF6-80C Strut 432, 442 80C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I16e Forward Upper Spar (Visible) – CF6-80C Strut 432, 442 80C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-58767 MAINTENANCE PLANNING DATA54-50-I17a Aft Upper Spar Chord (Vertical Flange, Hidden) – CF6-80C Strut 434, 436444, 44680C (400E)< 8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.54-50-I17a Aft Upper Spar Chord (Vertical Flange, Hidden) – CF6-80C Strut 434, 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 Strut 434, 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 Strut 434, 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 Strut 434, 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 Strut 434, 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 Strut 434, 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 Strut 434, 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 Strut 434, 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 Strut 434, 436444, 44680C (400E)>8 Hours<2>Type 240,000 Cycles/90,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5955-10-I09 Horizontal Stabilizer Upper Skin – At BBL 41.5 Side of Body Splice 331, 341 ALL Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)55-10-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 Lug 331, 341 ALL Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)55-10-I13B Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments 331, 341 ALL Type 225,000 Cycles55-10-I13C Horizontal Stabilizer Pivot Fitting Upper and Lower Attachments 331, 341 ALL Type 225,000 Cycles55-10-I13D Horizontal Stabilizer Pivot Fitting LugNote: No DTR Check Form.331, 341 200SF Type 150,000 Cycles55-10-I13E Horizontal Stabilizer PivotFitting – Upper and Lower AttachmentsNote: No DTR Check Form.331, 341 200SF Type 125,000 Cycles55-10-I14A Horizontal Stabilizer – Jackscrew Fitting Lug331, 341 ALL Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)55-10-I14B Horizontal Stabilizer Jackscrew Fitting – Upper and Lower Attachments 331, 341 ALL Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-60767 MAINTENANCE PLANNING DATA55-10-I14C Horizontal Stabilizer Jackscrew Fitting LugNote: No DTR Check Form.331, 341 200SF Type 150,000 Cycles55-10-I14D Horizontal Stabilizer Jackscrew Fitting – Upper and Lower AttachmentsNote: No DTR Check Form.331, 341 200SF Type 150,000 Cycles55-10-I31 Horizontal Stabilizer Rear SparUpper Chord – SOB Hidden Area 331, 341 ALL Type 150,000 Cycles(200, 200SF, 300BCF,300 PASS)40,000 Cycles (300F, 400E)55-10-I31A Horizontal Stabilizer RearSpar Upper Chord – SOB Hidden AreaNote: No DTR Check Form.331, 341 200SF Type 150,000 Cycles55-10-I31B Horizontal Stabilizer Rear Spar Upper ChordNote: No DTR Check Form.334, 344 200SF Type 150,000 Cycles57-10-I01 Typical Stringer and Skin – Wing CenterSection, Lower Surface at External LowerBeams (BBL 9.5 and BBL 62.0)133, 134 400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I01 Typical Stringer and Skin – Wing CenterSection, Lower Surface at External LowerBeams (BBL 9.5 and BBL 62.0)133, 134 400E>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 Hole Cutout 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 and Lower Surfaces, Front and Rear Spar,Beams and Access Door Cutouts, Lower Surface Beams, Side of Body Ribs, Splices,Lower Surface Access Hole Cutout and Adjacent Stringers, and Drain.Note: No DTR Check Form.133, 134 200SF Type 150,000 Cycles/70,000 Flt. Hrs.57-10-I02 Splice Stringer and Skin – Wing Center Section at Stringer 6 and 10 133, 134 300F Type 140,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6157-10-I02A Front Spar Chord and Skin – WingCenter Section at Radius Fillers 133, 134 400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I02A Front Spar Chord and Skin – WingCenter Section at Radius Fillers 133, 134 400E>8 HourType 125,000 Cycles/80,000 Flt. Hrs.57-10-I02B Front Spar Chord and Skin – WingCenter Section at Underwing Longeron 133, 134 400E< 8 Hours<2>Type 1, FLSSee Graph57-10-I02B Front Spar Chord and Skin – WingCenter Section at Underwing Longeron 133, 134 400E>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, 134 300BCF Type 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, 134 200SF Type 150,000 Cycles/ 70,000 Flt. Hrs.57-10-I03A Rear Spar Lower Chord and Skin – Wing Center Section – Typical –BBL 23.0 – 86.5133, 134 PASS(200ER, 200SF,300BCF, 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 –86.5 133, 134 PASS(200ER, 300ER)>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I03A Rear Spar Lower Chord and Skin – Wing CenterSection – Typical – BBL 23.0 – 86.5 133, 134 300F Type 125,000 Cycles/80,000 Flt. Hrs.57-10-I03A Rear Spar Lower Chord and Skin – Wing Center Section – Typical -LBL 86.5 – RBL 86.5133, 134 400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I03A Rear Spar Lower Chord and Skin – Wing Center Section – Typical –LBL 86.5 – RBL 86.5133, 134 400E>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-62767 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, 200SF,300BCF, 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, 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, 134 300F Type 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, 134 PASS(200ER, 200SF300BCF, 300ER)< 8 HoursType 1, FLSSee Graph(200ER, 300ER)50,000 Cycles/70,000 Flt. Hrs.(200SF, 300BCF)57-10-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-I03D Wing Center Section – Rear SparLower Chord Between Left and Right WBL 97.9Note: No DTR Check Form.133, 134 300BCF Type 150,000 Cycles/70,000 Flt. Hrs.57-10-I03E Wing Center Section – Rear SparLower Chord Between Left and Right WBL 97.9Note: No DTR Check Form.133, 134 200SF Type 150,000 Cycles/70,000 Flt. Hrs.57-10-I16 Lower Surface Side-Of-Body Splice (Sections 11 and 12) – L-1 to L-10 Inboard andOutboard of BBL 97.42193, 194 ALL< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-10-I16B Lower Surface Side-Of-Body Splice (Sections 11 and 12) – L-1 to L-10 Inboard andOutboard of BBL 97.42193, 194 ALLExcept 200SF, 300BCF>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6357-10-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, 194 300BCF Type 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, 194 200SF Type 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< 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 ALLExcept 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, 144 300BCF Type 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, 144 200SF Type 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 18133, 134 PASS(200ER, 200SF,300BCF, 300ER)300F< 8 HoursType 1, FLSSee Graph(200ER, 300ER, 300F)50,000 Cycles/70,000 Flt. Hrs.(200SF, 300BCF)57-10-I24 Underwing Longeron Attachment (Center Section Structure) – BBL 70 Longeron fromFront Spar Lower Chord to Stringer 18133, 134 PASS(200ER, 300ER)300F>8 HoursType 1, FLSSee Graph57-10-I24A Wing Center Section Lower SurfaceBL 70 Underwing Longeron Backup Structure Aftof the Front SparNote: No DTR Check Form.133, 134 300BCF Type 150,000 Cycles/70,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-64767 MAINTENANCE PLANNING DATA57-10-I24B Wing Center Section Lower SurfaceBL 70 Underwing Longeron Backup Structure Aftof the Front Spar.Note: No DTR Check Form.133, 134 200SF Type 150,000 Cycles/70,000 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, 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, 134 400E>8 Hours<2>Type 125,000 Cycles/80,000 Flt. Hrs.57-20-I05 Rear Spar at Forward MLG Trunnion – Rib 5, WS 329.10 532, 632551, 651400E< 8 Hours<2>Type 1, FLSSee Graph57-20-I05 Rear Spar at Forward MLG Trunnion – Rib 5, WS 329.10 532, 632551, 651400E>8 Hours<2>Type 1, FLSSee Graph57-20-I06 Rear Spar at MLG OutboardSupport – Rib 7, WS 372.20 532, 632551, 651400E< 8 Hours<2>Type 1, FLSSee Graph57-20-I06 Rear Spar at MLG OutboardSupport – Rib 7, WS 372.20 532, 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, 651 200, 200SF300BCF, 300 PASS300F and 400EL/N 922 and Later<2>Type 1, FLSSee Graph(200, 300PASS,300F L/N 922 and Later, 400E)50,000 Cycles/ 70,000 Flt Hrs(200SF, 300BCF)57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: L-16 (Dry Bay) underNacelle Fairing437, 447533, 633ALL Except 400E< 8 HoursType 1, FLSSee GraphAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6557-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: L-16 (Dry Bay) underNacelle Fairing437, 447533, 633ALLExcept 200SF,300BCF, 400E>8 HoursType 1, FLSSee Graph57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: L-16 (Dry Bay) underNacelle Fairing437, 447533, 633400E< 8 HoursType 1, FLSSee Graph57-20-I12A Outboard Wing Typical Stringers Lower Surface – Rib 9: L-16 (Dry Bay) underNacelle Fairing437, 447533, 633400E>8 HoursType 1, FLSSee Graph57-20-I12B Outboard Wing Typical Stringers LowerSurface – Rib 9: L-17 at Outboard Side LoadFitting under Nacelle Fairing533, 633 ALL Except 400E< 8 HoursType 1, FLSSee Graph57-20-I12B Outboard Wing Typical Stringers LowerSurface – Rib 9: L-17 at Outboard Side LoadFitting under Nacelle Fairing533, 633 ALLExcept 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I12B Outboard Wing Typical Stringers LowerSurface – Rib 9: L-17 at Outboard Side LoadFitting under Nacelle Fairing533, 633 400E< 8 HoursType 1, FLSSee Graph57-20-I12B Outboard Wing Typical Stringers LowerSurface – Rib 9: L-17 at Outboard Side LoadFitting under Nacelle Fairing533, 633 400E>8 HoursType 1, FLSSee Graph57-20-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 SpliceStringer – L-6 and 10. L-10 between Rib 7 and20 (except under Nacelle Fairing) & L-6: SOB to Rib 3531, 532, 541,631, 632, 641ALL< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15A Outboard Wing Lower Surface SpliceStringer – L-6 and 10. L-10 between Rib 7 and20 (except under Nacelle Fairing) & L-6: SOB to Rib 3531, 532, 541,631, 632, 641ALLExcept 200SF, 300BCF>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-66767 MAINTENANCE PLANNING DATA57-20-I15B Outboard Wing Lower Surface Splice Stringer – L-10 under Nacelle Fairing 532, 632 ALL< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I15B Outboard Wing Lower Surface Splice Stringer – L-10 under Nacelle Fairing 532, 632 ALLExcept 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, 533, 541,632, 633, 641ALL Except 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, 533, 541,632, 633, 641ALLExcept 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.57-20-I15D Outboard Wing Lower Surface Splice Stringer – L-15 under Nacelle Strut at Rib 9(Seal Pans)530, 630 ALL Except 400E< 8 HoursType 1, FLSSee Graph57-20-I15D Outboard Wing Lower Surface Splice Stringer – L-15 under Nacelle Strut at Rib 9(Seal Pans)530, 630 ALLExcept 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I15D Outboard Wing Lower Surface Splice Stringer – L-15 under Nacelle Strut at Rib 9(Seal Pans)530, 630 400E< 8 HoursType 1, FLSSee Graph57-20-I15D Outboard Wing Lower Surface Splice Stringer – L-15 under Nacelle Strut at Rib 9(Seal Pans)530, 630 400E>8 HoursType 1, FLSSee Graph57-20-I15E Outboard Wing Lower SurfaceSplice Stringer – L-6 and 10 at Rib 3530, 630 ALL< 8 HoursType 1, FLSSee GraphAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6757-20-I15E Outboard Wing Lower SurfaceSplice Stringer – L-6 and 10 at Rib 3530, 630 ALLExcept 200SF, 300BCF>8 HoursType 1, FLSSee Graph57-20-I15F Outboard Wing Lower SurfaceSplice Stringer – Seal Pan/ Baffles atRibs 3, 6, 18 and 31530, 540630, 640400E< 8 Hours<2>Type 125,000 Cycles/80,000 Flt. Hrs.57-20-I15F Outboard Wing Lower SurfaceSplice Stringer – Seal Pan/ Baffles atRibs 3, 6, 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.57-20-I15JOutboard Wing Lower Surface Splice StringersNote: No DTR Check Form.530, 630531, 631532, 632540, 640541, 641200SF300BCFType 150,000 Cycles/70,000 Flt. Hrs.57-20-I15KOutboard Wing Lower Surface Splice Stringers at Covered LocationsNote: No DTR Check Form.531, 631532, 632541, 641200SF300BCFType 125,000 Cycles80,000 Flt. Hrs.57-20-I16ARear Spar Lower Chord and Skin (Outboard Wing Structure) – Typical Detailsbetween Fairing at Side-Of-Body & Rib 3530, 630 ALL< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I16ARear Spar Lower Chord and Skin (Outboard Wing Structure) – Typical Detailsbetween Fairing at Side-Of-Body & Rib 3530, 630 ALLExcept 200SF, 300BCF>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-68767 MAINTENANCE PLANNING DATA57-20-I16B Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden byRib Shear Ties Side-Of-Body to Rib 3530, 630 ALL Except 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 3530, 630 ALLExcept 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 3530, 630 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 3530, 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 ALLExcept 400E< 8 Hours<2>Type 1, FLSSee Graph(All Except 200SF, 300BCF)50,000 Cycles/70,000 Flt Hrs(200SF, 300BCF)57-20-I16C Rear Spar Lower Chord and Skin (Outboard Wing Structure) – Hidden Details atRibs 5, 6, 8 and 9 (Not Covered by Fairings)530, 630 ALLExcept 200SF,300BCF, and 400E>8 Hours<2>Type 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-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 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 ALLExcept 200SF,300BCF, and 400E>8 HoursType 125,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6957-20-I16D Rear Spar to Skin, Rib Bay 1, WSTA 226.3 – Typical Details 531, 631 400E< 8 HoursType 125,000 Cycles/80,000 Flt. Hrs.57-20-I16D Rear Spar to Skin, Rib Bay 1, WSTA 226.3 – Typical Details 531, 631 400E>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 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, 640ALLExcept 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I16E Rear Spar to Skin, Rib Bay 11, WSTA 449.2 – Hidden Details 530, 540630, 640400E< 8 HoursType 1, FLSSee Graph57-20-I16E Rear Spar to Skin, Rib Bay 11, WSTA 449.2 – Hidden Details 530, 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 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 ALLExcept 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I16F Front Spar to Skin, Rib Bay19, WSTA 655.2 – Hidden Details 540, 640 400E< 8 HoursType 1, FLSSee Graph57-20-I16F Front Spar to Skin, Rib Bay19, WSTA 655.2 – Hidden Details 540, 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 400E< 8 HoursType 1, FLSSee GraphAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-70767 MAINTENANCE PLANNING DATA57-20-I16G Front Spar Lower Chord and Skin (Outboard Wing Structure) – Details Hidden byRib Shear Ties Rib 9 to and including Rib 23530, 540630, 640ALLExcept 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I16G Front Spar to Skin, Rib Bay 23,WSTA 759.2 – Hidden Details 540, 640 400E< 8 HoursType 1, FLSSee Graph57-20-I16G Front Spar to Skin, Rib Bay23, WSTA 759.2 – Hidden Details 540, 640 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 400E< 8 HoursType 1, FLSSee Graph57-20-I16H Front Spar Lower Chord and Skin (Outboard Wing Structure) – Ribs 8/9 and at SideBrace Fitting between Ribs 8/9533, 633 ALLExcept 200SF,300BCF, and 400E>8 HoursType 1, FLSSee Graph57-20-I16H Front Spar to Skin, Rib Bay 9, WSTA390.1 – Hidden Details – R7/R8 Backup Fitting 533, 633 400E< 8 HoursType 1, FLSSee Graph57-20-I16H Front Spar to Skin, Rib Bay 9, WSTA390.1 – Hidden Details – R7/R8 Backup Fitting 533, 633 400E>8 HoursType 1, FLSSee Graph57-20-I16I Front Spar Lower Chord and Skin – Hidden Details Rib Shear Ties, Rib 24 to andincluding Rib 31530, 540630, 640400E< 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 31530, 540630, 640400E>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, 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, 640 400E>8 Hours<2>Type 1, FLSSee GraphAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7157-20-I16K Outboard Wing Lower SurfaceFront and Rear Spar Chords and SkinNote: No DTR Check Form.530, 630532, 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, 631 200SF300BCFType 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, 632 400E< 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, 632 400E>8 HoursType 1, FLSSee Graph57-20-I27 Skin Tab at R1 Nacelle Attachment R2 Intact – Outboard Fitting Aft Fastener Row 532, 632 400E< 8 Hours<2>Type 125,000 Cycles/80,000 Flt. Hrs.57-20-I27 Skin Tab at R1 Nacelle Attachment R2 Intact – Outboard Fitting Aft Fastener Row 532, 632 400E>8 Hours<2>Type 125,000 Cycles/80,000 Flt. Hrs.57-20-I36 MLG Forward Trunnion Support to Lower Skin Attachment – Inboard ForwardTrunnion Support, Most Inboard Aft Fastener530, 540630, 640400E Type 125,000 Cycles/80,000 Flt. Hrs.57-53-I02AOutboard Flap Supports – Support Ribs (Rear Spar Fittings) in Bathtub Region,Lug 6 Region Flange572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I02A.1Outboard 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 PASS)40,000 Cycles (300F)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-72767 MAINTENANCE PLANNING DATA57-53-I02A.2Outboard 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 PASS)40,000 Cycles (300F)57-53-I02A.3Outboard Flap Supports – Rear Spar Fittings – Lower Aft Flange572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 - 921Type 225,000 Cycles57-53-I02BOutboard 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-I02BOutboard Flap Supports – Rear Spar Fitting Tension Bolts 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 125,000 Cycles57-53-I02COutboard Flap Supports – Doublers – .375” Diameter Fastener Holes 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I02COutboard Flap Supports – Rear Spar Fittings– Actuator Bore and Fastener Holes 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 225,000 Cycles57-53-I02D.1Outboard Flap Supports – 9-10 Beam – Joint 9 Lug 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7357-53-I02D.2Outboard Flap Supports – 9-10 Beam 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I02EOutboard Flap Supports – 9-10 Beam Swivel Fitting 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 125,000 Cycles57-53-I02FOutboard Flap Supports – Flap Attachment Bolts 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 710Type 125,000 Cycles AfterAccomplishing Terminating Actionof SB 767-27A015557-53-I02FOutboard Flap Supports – Flap Attachment Bolts 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 711 – 921Type 125,000 Cycles57-53-I02G.1Outboard Flap Supports – 6-8-9 Beam (Main Drive Link), 5.38 inches Aft of Joint 6 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I02G.1Outboard 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.2Outboard Flap Supports – 6-8-9 Beam (Main Drive Link), Lug 8 Region 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-74767 MAINTENANCE PLANNING DATA57-53-I02G.2Outboard Flap Supports – No. 1 and No. 2, 6-8-9 Beam – Lugs 6, 8 and 9 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I02G.3Outboard Flap Supports – Support No. 1 andNo. 2, 6-8-9 Beam – Fastener Holes 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 225,000 Cycles57-53-I02IOutboard Flap Supports – 4-5 Drive Arm – Spline Outer Surface 572, 573672, 673ALL<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I02J.1Outboard Trailing Edge Flap Support #1 – Link 3-10 – Lug 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I02J.2Outboard Trailing Edge Flap Support #2 – Link 3-10 – Lug 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I02L.1Outboard Trailing Edge Flap Supports – Beam 1-2-3 – Beam at Field Fasteners 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 225,000 Cycles57-53-I02L.2Outboard Trailing Edge Flap Supports – Beam 1-2-3 – Lug at Joint 1 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7557-53-I02L.3Outboard Trailing Edge Flap Supports – Beam 1-2-3 – Lug at Joint 3 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I02M.1Outboard Flap Supports – Outer Pins atOutboard Supports: Joints 5, 6, 8 and 10and Inboard Supports: Joints 5, 6, 8 and 10572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 125,000 Cycles57-53-I02M.2Outboard Flap Supports – Outer Pin at Inboard Main Support: Joint 8 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400EType 125,000 Cycles57-53-I02M.4Outboard Flap Pins – Support #2 – Outer Pins at Joint 2 and Joint 8 572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 - 921Type 125,000 Cycles57-53-I02M.5Outboard Flap Pins – Support #1 and #2 – Joint #1 Fuse Pin – Pin Shank @Outboard Rib Support572, 573672, 673200, 200SF300BCF, 300F300 PASSL/Ns 1 - 921Type 125,000 Cycles57-53-I02M.6Outboard 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.1Inboard Flap Box at #3 Support – Backup Fittings – Forward Bathtub 555, 655 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 125,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-76767 MAINTENANCE PLANNING DATA57-53-I03E.2Inboard Flap Box at #3 Support – Backup Fittings – Aft Bathtub End Pads 555, 655 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I03FInboard Flap Box at #3 Support – Flap Attachment Bolts, IFS 251.25 555, 655 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400EType 125,000 Cycles57-53-I03FInboard flap #3 Support – Flap Attachment Bolts – Shank Location 555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 849Type 125,000 Cycles AfterAccomplishing Terminating Actionof SB 767-27A017657-53-I03FInboard Flap #3 Support – Flap Attachment Bolts – Shank Location 555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 850 – 921Type 125,000 Cycles57-53-I03I.1Inboard Flap Box at #4 Support – Inboard Closure Rib – Lower Chord, IFS 108.5 555, 655 ALLType 125,000 Cycles57-53-I03I.2Inboard 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.2Inboard Flap, Support #4 – Splined Bushing at IFS 108.5 – Internal Spline base ofTooth/Rim555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 1 - 909Type 125,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7757-53-I03J.1Inboard 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 PASS)40,000 Cycles (300F, 400E)57-53-I03J.2Inboard 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 Cycles57-53-I03J.2Inboard Flap Support at #4 – Collar Fitting– Spline Cross-Section 555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 909Type 125,000 Cycles57-53-I03KInboard Flap #4 Support – Attachment Bolts 555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 849Type 125,000 Cycles AfterAccomplishing Terminating Actionof SB 767-27A017657-53-I03KInboard Flap #4 Support – Attachment Bolts 555 655 200, 200SF300BCF, 300F300 PASSL/Ns 850 – 921Type 125,000 Cycles57-53-I03LInboard Flap – #4 Support – Torque Tube – Torque Tube Outer Surface – IFS 92to IFS 124.5555, 655 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 909Type 125,000 Cycles57-53-I03L.1Inboard Flap Box at #4 Support – Torque Tube – IFS 108.5 555, 655 200, 200SF300BCF, 300F300 PASSL/N 910 and Laterand 400E<2>Type 125,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-78767 MAINTENANCE PLANNING DATA57-53-I03L.2Inboard Flap Box at #4 Support – Torque Tube, IFS 92 to IFS 124.5 555, 655 200, 200SF300BCF, 300F300 PASSL/N 910 and Laterand 400EType 125,000 Cycles57-53-I04A.1Inboard Flap #3 Support – Actuator Support Rib Assembly – Section Forward ofJoint 6 Lug571, 671200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400EType 250,000 Cycles(200, 200SF, 300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04A.1Inboard Flap #3 Support – Actuator Support Rib– Section Forward of Joint 6 Lug 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04A.2Inboard 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 PASS)40,000 Cycles (300F, 400E)57-53-I04A.2Inboard Flap #3 Support – Actuator Support Rib– Lugs at Joints 0, 1, 6 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04B.2Inboard Flap #3 Support – Underwing Fitting – Section 9.67 Inches 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 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7957-53-I04B.2Wing Trailing Edge, I/B Flap, #3 Support – Underwing Fitting – Section ThroughAft Most 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 PASS)40,000 Cycles (300F)57-53-I04B.3Wing 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 PASS)40,000 Cycles (300F)57-53-I04CWing Trailing Edge, I/B Flap, #3 Support – Fuse Pin – Underwing Fitting toForward Tension Link571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 882Type 125,000 Cycles57-53-I04DInboard Flap #3 Support – Forward Tension Link 571, 671 200, 200SF300BCF, 300F300 PASSL/N 883 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04D.1Wing 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 PASS)40,000 Cycles (300F)57-53-I04D.2Wing Trailing Edge, I/B Flap, #3 Support – Forward Tension Link – End Clevis 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 882<2>Type 250,000 Cycles(200, 200SF, 300BCF, 300 PASS)40,000 Cycles (300F)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-80767 MAINTENANCE PLANNING DATA57-53-I04EInboard Flap #3 Support – 1-2-3 Beam – Lugsat Joints 1, 2, and 3 571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04E.1Inboard Flap #3 Support – Beam 1-2-3 – Lug at Joint 1 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04E.2Inboard Trailing Edge Flap Support #3 – Beam 1-2-3 – Lugs at Joint 2 and 3 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04E.3Inboard Flap #3 Support – Beam 1-2-3 – Beam at Field Fasteners 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04F.1Inboard Flap #3 Support – 3-10 Link – Lugs 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04F.1Inboard Flap #3 Support – 3-10 Link – Lugs 571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8157-53-I04F.2Inboard Flap #3 Support – 3-10 Link – Between Lugs 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04F.2Inboard Flap #3 Support – 3-10 Link – Between Lugs 571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04HInboard Flap #3 Support – 6-7-8-9 Beam – Lug 9 Detail 571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04HInboard Flap #3 Support – 6-7-8-9 Beam– Lugs 6, 7, 8 and 9 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04IInboard Flap #3 Support – 4-5 Drive Arm – Internal Spline 571, 671 ALL<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04KInboard Flap #3 Support – 9-10 Beam – Lug at Joint 9 571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-82767 MAINTENANCE PLANNING DATA57-53-I04K.1Inboard Flap #3 Support – 9-10 Beam – Joint 9 Lug 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04K.2Inboard Flap #3 Support – 9-10 Beam – Section Cut Through Field Fasteners –Section B-B571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 225,000 Cycles57-53-I04K.3Inboard Flap #3 Support – 9-10 Beam 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04N.1Inboard 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.2Inboard Flap #3 Support – Flap Support Pins – Outer Pins at Joints A and B 571, 671 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400EType 125,000 Cycles57-53-I04N.3Inboard 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.4Inboard Flap #3 Support – Flap Support Pins – Outer Pin at Joint 1. 571, 671 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 125,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8357-53-I04PInboard Flap #4 Support – 4-5 Drive Arm – Internal Spline 195, 196 ALL<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04Q.1Inboard Flap #4 Support – 5-7 Link – Lugs 195, 196 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04Q.1Inboard Flap #4 Support – 5-7 Link – Lugs 195, 196 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04Q.2Inboard Flap #4 Support – 5-7 Link – Cross Section 3.16 inches from Lug 195, 196 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04Q.2Inboard Flap #4 Support – 5-7 Link – Body ofLink around Field fasteners 195, 196 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04SInboard Flap #4 Support – 6-7 Drive Arm – Cross Section 7.399 inches fromJoint 7195, 196 ALL<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04TInboard Flap #4 Support – 6-9 Drive Arm – Just Aft of the Bend in the Beam 195, 196 ALL<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-84767 MAINTENANCE PLANNING DATA57-53-I04VInboard Flap #4 Support – Carrier Beam 9-11 – Section Forward of Flap Attachand Aft of Flap Attach Bathtub195, 196 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04YInboard Flap #4 Support – Flap Support Fitting – Upper Flange Inboard BoltLocation195, 196 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400EType 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F, 400E)57-53-I04YInboard Flap #4 Support – Side Strut Swivel Support Fitting – Satellite Holes andLug 6195, 196 200, 200SF300BCF, 300F300 PASSL/Ns 1 – 921Type 250,000 Cycles(200, 200SF,300BCF, 300 PASS)40,000 Cycles (300F)57-53-I04ZInboard Flap #4 Support – 6-6’ Outer Pin – Section at Spline #2 (Common to6-7 Arm) Inner Diameter (Inner Bore)195, 196 ALLType 125,000 Cycles57-53-I04AAInboard Flap #4 Support – Flap Support Pins – Outer Pins at Joints 5, 7 and 9 195, 196 200, 200SF300BCF, 300F300 PASSL/N 922 and Laterand 400E<2>Type 125,000 Cycles57-53-I04AAInboard 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, 652 200SF300BCF<4>Type 150,000 Cycles57-54-I02B Main Landing Gear Beam, Outboard Lug BoreNote: No DTR Check Form.552, 652 200SF300BCF<4>Type 150,000 CyclesAIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8557-54-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, 652 200SF300BCF<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, 652 200SF300BCF<4>Type 150,000 Cycles57-54-I03A Load Distribution Plate,Flange around Outboard Upper LugNote: No DTR Check Form.552, 652 200SF300BCF<4>Type 150,000 Cycles57-54-I03B Load Distribution Plate,Flange around Outboard Lower LugNote: No DTR Check Form.552, 652 200SF300BCF<4>Type 150,000 Cycles57-54-I03C Load Distribution Plate, Flange around Inboard LugNote: No DTR Check Form.552, 652 200SF300BCF<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, 652 200SF300BCF<4>Type 150,000 Cycles57-54-I04 Main Landing Gear Beam, Outboard PinNote: No DTR Check Form.552, 652 200SF300BCF<4>Type 150,000 Cycles57-54-I13 MLG Forward Trunnion Support – Side Load Fitting – Side Load Fitting to StrapInboard Fastener Row551, 651 400E<2>Type 125,000 Cycles/80,000 Flt. Hrs.57-54-I14 MLG Forward Trunnion Support – Side Load Strap – First Fastener Row Either Sideof Trunnion551, 651 400E<2>Type 125,000 Cycles/80,000 Flt. Hrs.AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSSSI # DTR CHECK FORM TITLEINSPECTIONZONEAIRPLANE/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-86767 MAINTENANCE PLANNING DATA<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/ENGINEAPPLICABILITYTYPE AND THRESHOLDJUN 2011767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-87C. 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 INCORPORATION767-32-44 MLG UPPER SPINDLE-DRAG STRUT, PART # 161T6007 9,000767-32-45 MLG OUTERCYLINDER ASSEMBLY, PART # 161T1110 18,000767-32-46 MLG UPPER BULKHEAD-SHOCK STRUT, PART # 16T1161 30,000ITEMLIFE LIMIT767-300, 767-300BCF, 767-300F NOSE LANDING GEAR80,000 LANDINGS **767-300, 767-300BCF, 767-300F MAIN LANDING GEAR50,000 LANDINGS **767-300, 767-300BCF, 767-300F MAIN LANDING GEAR SUPPORT STRUCTURE62,000 LANDINGS **767-300, 767-300BCF, 767-300F MLG RETRACT ACTUATOR FITTING AND PIN90,000 LANDINGS   These values are based on completed fatigue tests.JUN 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-88767 MAINTENANCE PLANNING DATANOTE: 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.ITEM LIFE LIMIT767-400ER NOSE LANDINGGEAR 80,000 LANDINGS ** 767-400ER MAIN LANDING GEARINNER CYLINDER16,600 LANDINGS *OUTER CYLINDER16,600 LANDINGS *WING MAIN LANDING GEAR BEAM UPPERSTABILIZER BRACE FUSE PIN 21,300 LANDINGS*ALL OTHER SAFE-LIFE PARTS 31,400 LANDINGS ** These values are based on fatigue test cycles completed todate and will be increased when testing is complete.** These values are based on completed fatigue tests and analysis.ITEM LIFE LIMIT767-300 FRONT MOUNT PYLON MOUNTING BRACKET 30,000 LANDINGS ***767-300 FRONT MOUNT CENTER THRUST LINK ANDASSOCIATED HARDWARE30,000 LANDINGS ***767-300 REAR MOUNT PYLON BRACKET 50,000 LANDINGS ****** These values are based on completed Safe-Life testing and analysis.JUN 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-89D. AIRWORTHINESS LIMITATIONS – SYSTEMSFUEL SYSTEMS AIRWORTHINESS LIMITATIONSThis 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 (SFAR88). SFAR 88 – Fuel Tank System Fault Tolerance Evaluation Requirements and Title 14 Code ofFederal 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 levelof 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.MAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-90767 MAINTENANCE PLANNING DATAUSE 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 localregulatory 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 AWLintervals. 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 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-91REGULATORY 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.APR 2008D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-92767 MAINTENANCE PLANNING DATAE. PAGE FORMAT: FUEL SYSTEMS AIRWORTHINESS LIMITATIONSCOLUMN EXPLANATIONAWL NUMBER Each task is given a unique AWL Item Number.The first and second digits are the ATA Chapter Number.TASK ALI = Airworthiness Limitation Instruction. These tasks are inspections that should be performed atthe listed intervals.CDCCL = Critical Design Configuration Control Limitation.INTERVAL Task frequencies are specified in terms of a usage parameter such as flight hours, cycles or calendar time.APPLICABILITY Airplanemodel applicability.DESCRIPTION Description of the task to be performed or criticaldesign configurations aspects that cannot be changed without violating the intent ofthe design.APR 2008767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-93FUEL SYSTEMS AIRWORTHINESS LIMITATIONSAWLNumberTask Interval Applicability Description28-AWL-01 ALI 12 Yrs AllExternal 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 andrear 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/A AllExternal 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 perthe 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 tothe tank wall interface insidethe tank.3. Install full bodied fillet sealencapsulating the first coupling interface inside the tank.MAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-94767 MAINTENANCE PLANNING DATA28-AWL-04 CDCCL N/A AllLightning 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 bulkhead fitting and the rear spar for 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 ismore than 0.005ohm (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.AWLNumberTask Interval Applicability DescriptionMAY 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9528-AWL-06 CDCCL N/A AllAC 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/A AllAC 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 thehousing and the fuel pump is not more than0.00035 ohms (0.35 milliohms).AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-96767 MAINTENANCE PLANNING DATA28-AWL-08 CDCCL N/A AllLightning, 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 to the fuel tanks (such as adding a 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/A AllFuel 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 anynew 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/A AllCenter 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.AWLNumberTask Interval Applicability DescriptionMAY 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9728-AWL-11 CDCCL N/A AllFuel 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 safelevels in order to preclude the potential of 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/A AllFuel 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.AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-98767 MAINTENANCE PLANNING DATA28-AWL-13 CDCCL N/A AllFuel 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/A AllFuel 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.AWLNumberTask Interval Applicability DescriptionMAY 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9928-AWL-15 CDCCL N/A AllSurge 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 levelsin 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/A AllSurge 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/A AllResetting 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.AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-100767 MAINTENANCE PLANNING DATA28-AWL-18 ALI 12 Yrs AllFuel 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 notexceed 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 notexceed 43 milliohms for Connector M1957 (Right Main Tank)Wire Bundle S283T025-136.The loop resistance shall not exceed 40 milliohms for ConnectorM1950 (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 notexceed 40 milliohms for Connector M1952 (Right Aux Dens. Tank)Wire Bundle S283T025-135.(Continued on next page)AWLNumberTask Interval Applicability DescriptionMAY 2010767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-10128-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 notexceed 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 notexceed 43 milliohms for Connector M1949 (Right Main Tank)Wire Bundle S283T025-131.The loop resistance shall not exceed 40 milliohms for ConnectorM1950 (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 notexceed 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 notexceed 40 milliohms for Connector M1945 (Left Main 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 notexceed 43 milliohms for Connector M1949 (Right Main Tank)Wire Bundle S283T025-331 (-981).The loop resistance shall not exceed 40 milliohms for ConnectorM1950 (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)AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-102767 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 notexceed 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 notexceed 121 milliohms for Connector D1582 (Left Main Tank Lo-Z)Boeing Wire Bundle 286T0446.The loop resistance shall notexceed 284 milliohms for Connector D1552 (Left Main Tank Hi-Z)Boeing Wire Bundle 286T0446.The loop resistance shall notexceed 150 milliohms for Connector D2816 (Left Aux Tank Lo-Z)Boeing Wire Bundle 286T0454.The loop resistance shall notexceed 175 milliohms for Connector D2812 (Left Aux Tank Hi-Z)Boeing Wire Bundle 286T0454.The loop resistance shall not exceed 122 milliohms for ConnectorD1584 (Right Main Tank Lo-Z)Boeing Wire Bundle 286T0448.The loop resistance shall not exceed 284 milliohms for ConnectorD1560 (Right Main Tank Hi-Z)Boeing Wire Bundle 286T0448.The loop resistance shall notexceed 152 milliohms for Connector D2818 (RightAux Tank Lo-Z)Boeing Wire Bundle 286T0448.The loop resistance shall notexceed 184 milliohms for Connector D2814 (RightAux Tank Hi-Z)Boeing Wire Bundle 286T0448.(Continued on next page)AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-103767 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 notexceed 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 notexceed 58 milliohms for Connector M1949 (Right Main Tank)Wire Bundle S283T025-731.The loop resistance shall not exceed 59 milliohms for ConnectorM1950 (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 notexceed 66 milliohms for Connector M1952 (Right Aux Dens Tank)Wire Bundle S283T025-735.If the measured loop resistancevalue 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 greaterthan 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.AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-104767 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 Center Fuel 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.AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-105767 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 aroundthe 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)AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-106767 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.AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-107767 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. Anelectrical 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.AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-108767 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 toensure 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 Pumps and all Center Auxiliary TankOverride/Jettison Fuel Pump GFI Control Relays per Boeing AMM 28-22-00.AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-109767 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 tochafe 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. Thewiring 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.AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-110767 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. Ifdamaged (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.AWLNumberTask Interval Applicability DescriptionMAY 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-111767 MAINTENANCE PLANNING DATAF. AIRWORTHINESS LIMITATIONS – NITROGEN GENERATION SYSTEM TASKSThe 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:ParagraphM25.4(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.JUL 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-112767 MAINTENANCE PLANNING DATAAWLNumberTask Interval Applicability Description47-AWL-01 CDCCL N/A767 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 fittingor attached tubing are removed and replaced, orreinstalled (refer to Boeing AMM 47-21-05):1. Install the same part number bulkhead fitting,2. Verify electrical fay surface bond from the bulkhead fitting to the front spar structure inside the tank is0.0005 ohms (0.5 milliohms) or less,3. Install full-bodied fillet seal encapsulating the bulkhead fitting and jam nut outside of the tank,4. Install full-bodied fillet seal between the cast-inhex feature of the bulkheadfitting and the spar webinside of the tank,5. Install full-bodied fillet seal between the B-nut and tube, and between the B-nut and bulkhead fitting onthe first mating tube inside of the tank, and6. Verify electrical bond from structure to firsttube mating with the bulkhead fitting is 1.0 ohmsor less.Note: The bulkhead fitting is a special part whichhas an integral flame arrestor. Any changes tothis part require approval by the Seattle FAA ACO.47-AWL-02 CDCCL N/A767 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 interfacebetween the dielectric isolator hose and theNEA tubing during a lightning strike event.The NGS installation isdesigned to prevent lighting currents from entering the center wing fueltank by adding a dielectric isolator hose in the forward leading edge fairing area NEA distributionline. The isolator must be maintained if the dielectric isolator hose or attached tubing areremoved and replaced (refer to Boeing AMM 47-00-00 and 47-21-00).JUL 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-113767 MAINTENANCE PLANNING DATA47-AWL-03 CDCCL N/A767 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 warm fuel 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 is not 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-2See Boeing AMM Chapter 28 for a description of the Fuel System. See Boeing AMM Chapter 47 for adescription of the NGS.47-AWL-04 ALI2,600Flight Hours767 airplaneLine Numbers 993and on or airplanesthat haveincorporatedService Bulletin767-47-0001Nitrogen Generation System – NEADistribution Ducting InspectionConcern: The NEA Distribution System ducting outside the fuel tank may fail latently allowing NEA to leak withoutreaching the fuel tank, resulting in the fuel tank not reaching required inert levels.Inspect the NEA distribution lines from the ASU to the fuel tank front spar for damage and leaks (refer to BoeingAMM 47-21-00).AWLNumberTask Interval Applicability DescriptionJUL 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-114767 MAINTENANCE PLANNING DATA47-AWL-05 ALI2,600Flight Hours767 airplaneLine Numbers 993and on or airplanesthat haveincorporatedService Bulletin767-47-0001Nitrogen 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).47-AWL-06 CDCCL N/A767 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, Appendix M.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 operatorsto monitor descent rates oftheir 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 maintaincompliance with this CDCCL, or other approved actions,within the compliance times stated in the service instructions.AWLNumberTask Interval Applicability DescriptionJUL 2011D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-115767 MAINTENANCE PLANNING DATAG. 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 ofCMRs 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.JUL 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-116767 MAINTENANCE PLANNING DATAFIGURE 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 details Page 9.0-117767 MAINTENANCE PLANNING DATAH. PAGE 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 tothe appropriate ATA Chapter-Section-Subject in the Boeing Maintenance Manual (MM) that deals generally with the task. Wheninformation specific to the task is provided, a seventh digitindicates the first digit of the page block where it can be foundin the MM.Alpha characters following the seventh digit differentiate between multiple tasks in the same page block. When information specific tothe task is not provided in the MM, the seventh digit is an 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 inherentdesign capabilities.Any act of consumable replenishment for the purpose of maintaining inherentdesign capabilities.A visual failure finding task to determine if anitem is fulfilling its intended purpose.Does not require quantitative tolerances.A failure finding task to determine if an item is fulfilling its intended purposes.Does not require quantitative tolerances.An examination of an item against a specificstandard. This is a potential failurefinding task.A quantitative check to determine if one or more functions of an item performswithin specified limits. This is a potential failure finding task.Reworking, replacement of parts or cleaning necessary to return an item to aspecific standard.The removal and replacement of an item.CMR INTERVAL CMR interval specified in termsof flight hours, flight cycles, calendar time, letter check, orDaily Check. Whentwo intervals are listed fora single task, the top interval is the threshold and the bottom one is therepeat interval. A "NOTE" is used to indicate thatan explanationis provided under the task description.ZONE Airplane Zone Number (see Zone Diagrams,Section 3) where task is performed.ACCESS Access Panel/Door Number (see Access Panel/Door illustrations, Section 4)required to be opened to perform the task.JUL 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-118767 MAINTENANCE PLANNING DATAAPPLICABILITYAPL ENGApplicable Airplane Model and Engine. "ALL" applies to all models of airplanes or engines. A "NOTE" refers to an explanationunderthe task description. 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.SEP 2008767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-119I. CERTIFICATION MAINTENANCE REQUIREMENTS TASKSMPDITEMNUMBER TASKCMRINTERVAL ZONE ACCESSAPPLICABILITY767CERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTION24-33-00-6A OP 00048 HRS 212 ALL 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 212 ALL ALLOperationally Check AFOLTS (AutomaticFire/Overheat LogicTest 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 211 ALL ALLPerform Single Hydraulic System Check of each rudder PCA using each HydraulicSystem in sequence. This also verifiesthat the Rudder and Elevator Shutoff Valvesare open.27-31-00-5B FC 00400 HRS 211 ALL 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 FuelTank Override Pumps and Pressure Switches.Airplane Note: Applicable only to A/C withdeactivated 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 channelof the Fuel QuantityIndicating System(FQIS) using measuring sticks.(Main Fuel Tank shouldcontain 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.JUL 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-120767 MAINTENANCE PLANNING DATA29-11-00-5A OP 04000 HRS 195211195SL NOTE ALLOperationally Check ADP Speed Topping Shutdown Circuitry.SB 767-29-4. CMR Classification can be deleted 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 is 4.5 GPM. This rate permits theleakage 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 4.0GPM 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 212 NOTE 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 212 NOTE 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 DESCRIPTIONSEP 2008767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-12131-63-00-2A OP 00100 HRS 212 400E 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-offconfiguration 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 211 NOTE ALLOperationally Check Alternate Brake SystemIncluding 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 211 NOTE ALLOperationally Check Accumulator Isolation Valve.Airplane Note: SB 767-32-4. Task is applicableto airplanes which have not incorporatedSB (Line Numbers 4, 24, 28, 30, 32, 35 and 47and on incorporated either 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 DESCRIPTIONSEP 2008D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-122767 MAINTENANCE PLANNING DATA52-51-07-4A 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.D77-41-01-4A OP 00400 HRS 212 ALL 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 fault in 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 211 ALL 80ACheck operation of Standby Engine Indicatorby 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 211 NOTE 80CCheck operation of Standby Engine Indicatorby 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 DESCRIPTIONSEP 2008767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-123H78-00-00-6R 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).MPDITEMNUMBER TASKCMRINTERVAL ZONE ACCESSAPPLICABILITY767CERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTIONSEP 2008D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-124767 MAINTENANCE PLANNING DATAN77-41-01-4A 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.P73-21-07-5A 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.P77-00-00-6B OP 00400 HRS 211 ALL 7R4Check operation of Standby Engine Indicatorby 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 DESCRIPTIONSEP 2008767 MAINTENANCE PLANNING DATAD622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-125J. 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 oris 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”JUL 2010D622T001-9BOEING PROPRIETARY - Copyright (c) - UnpublishedWork - See title page for details Page 9.0-126767 MAINTENANCE PLANNING DATAIn 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 2007