777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-1777MAINTENANCE PLANNING DATA (MPD) DOCUMENTSECTION 9AIRWORTHINESS LIMITATIONS (AWLs) ANDCERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)D622W001-9JULY 2011COMPILED AND PUBLISHED BY:MAINTENANCE PROGRAMS ENGINEERINGCOMMERCIAL AVIATION SERVICESBOEING COMMERCIAL AIRPLANE GROUPSEATTLE, WASHINGTONJUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-2777 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3TABLE OF CONTENTSREVISIONS .................................................................................................................................................................................................................................. 9.0-5LIST OF EFFECTIVE PAGES .................................................................................................................................................................................................... 9.0-21A. SCOPE................................................................................................................................................................................................................................... 9.0-23B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS..................................................................................................................................... 9.0-23C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFELIMITS ............................................................................................................................ 9.0-107D. AIRWORTHINESS LIMITATIONS – SYSTEMS....................................................................................................................................................................9.0-112E. PAGE FORMAT: SYSTEMS AIRWORTHINESS LIMITATIONS............................................................................................................................................9.0-115F. AIRWORTHINESS LIMITATIONS – NITROGEN GENERATIONSYSTEMS TASKS........................................................................................................... 9.0-128G. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)............................................................................................................................................ 9.0-133H. PAGE FORMAT – CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs).............................................................................................................. 9.0-138I. CERTIFICATION MAINTENANCE REQUIREMENTS TASKS.............................................................................................................................................. 9.0-139J. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS..................................................................................................................... 9.0-142JUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4777 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALAPRIL 1995 (Original Release) Prepared by:M. C. Toepke (Boeing) 4/95Supervised by:S. R. Williford(Boeing) 4/95Approved by:D. L. Riggin(FAA) 5/15/95Alvin Habbestadfor D. RigginSEPTEMBER 1995 (Revision 1)Added GE90 Fatigue RequirementsCMR 27-CMR-03 DeletedCMR 31-CMR-01 Wording ChangedCMR 78-CMR-01 RevisedCMR 78-CMR-02 AddedPrepared by:M. C. Toepke (Boeing) 9/95Supervised by:S. R. Williford(Boeing) 9/95Approved by:D. L. Riggin(FAA) 11/8/95SEPTEMBER 1995 (Revision 2)Replaced N/A with None – 15 PlacesAdded SSI 53-40-I01 (Side Mount Satcom)Added SSIs 57-53-I07, 57-53-I11, 57-53-I18, 57-53-I23, 57-53-I28 for IncreasedGross Weight.Deleted SSI 57-53-I21 Duplicate RequirementPrepared by:L. E. Harrison (Boeing) 12/95Supervised by:S. R. Williford(BOEING) 12/95Approved by:D. L. Riggin(FAA) 12/14/95JUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6777 MAINTENANCE PLANNING DATAJANUARY 1996 (Revision 3)Added four Fatigue Critical Items for Rolls-Royce Trent engine.Prepared by:L. E. Harrison (Boeing) 1/96Supervised by:S. R. Williford(Boeing) 1/96Approved by:D. E. Gonder(FAA) 3/8/96APRIL 1996 (Revision 4)Added FAA to front pageRevised Flight Deck StowageCompartment Latch wording.Revised Nose Landing Gear Life LimitCMR 78-CMR-02 RevisedPrepared by:L. E. Harrison (Boeing) 4/96Supervised by:S. R. Williford(Boeing) 4/96Approved by:D. L. Riggin(FAA) 4/10/96AUGUST 1996 (Revision 5)CMR 78-CMR-02 RevisedPrepared by:L. E. Harrison (Boeing) 8/96Supervised by:S. R. Williford(Boeing) 8/96Approved by:D. E. Gonder(FAA) 9/96MARCH 1997 (Revision 6)Added CMR 72-CMR-01 for inspection of the Step-Aside-Gearbox (SAGB)Housing and External Gearbox Lower Bevel Box (LBB) Housing for oil leakageand cracking.Added CMR 72-CMR-02 for inspection of the Step-Aside-Gearbox (SAGB)Housing with fluorescent penetrant for evidence of cracking.Prepared by:S. A. Pierini (Boeing) 3/97Supervised by:S. R. Williford(Boeing) 3/97Approved by:D. L. Riggin(FAA) 3/97REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7APRIL 1997 (Revision 7)Added revised safe life limits for the 777-200/-200 IGW landing gear componentsbased on fatigue test cycles completed to date.Prepared by:R. C. Moore (Boeing)4/97Supervised by:S. R. Williford(Boeing) 4/97Approved by:D. L. Riggin(FAA) 8/97SEPTEMBER 1997 (Revision 8)Added SSIs 53-30-I05 and 53-60-I06 tothe Airworthiness Limitations section.Deleted CMRs 72-CMR-01 and 72-CMR-02 since Airworthiness Directive 97-06-13 makes the CMR reference redundant.Submitted by:S. R. Williford (Boeing) 9/97Approved by:D. L. Riggin (FAA) 12/97MAY 1998 (Revision 9)Added SSIs for 777-200 IGW and -300 to the Airworthiness Limitations section.Amended “Related Tasks” in “AirworthinessLimitations – Structural Inspections”table to reflect revised task numbering system.Revised Scope and Airworthiness Limitations section wordings to standardizewith 757 and 767 section wordings.Added CMR 72-CMR-03 for inspection of the main fan blades for evidence ofcracking and CMR-28-CMR-01 to inspectFQIS wiring in the center fuel tank.Submitted by:S. R. Williford (Boeing) 5/98Approved by:D. L. Riggin (FAA) 5/98MAY 1998 (Revision 10)Added SSIs 54-51-I02D, 54-51-I03B, 54-51-I04A, 54-51-I04F, 54-51-I05D,54-51-I08B, and 54-51-I09I for PW 4090 engine struts on the 777-300 airplane.Additional changes include revision to SSI number sub-letters, related tasks andairplane applicability.Submitted by:S. R. Williford (Boeing) 5/98Approved by:D. L. Riggin (FAA) 6/98REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8777 MAINTENANCE PLANNING DATAMAY 1999 (Revision 11)Deleted CMR 78-CMR-02 based on the incorporation of Service Bulletins 777-78-0010 and 777-78-0018 on all production and in-service airplanes and theaccumulation of over 200,000 flight hours of in-service data.Submitted by:S. R. Williford (Boeing) 5/99Approved by: A. Bahrami (FAA) 11/99OCTOBER 1999 (Revision 12)Revised Airworthiness Limitations StructuralInspection text in the Introduction,Threshold and airplane applicability sections.Revised Airworthiness Limitations 54-51-102D, 54-51-103B, 54-51-104A,54-51-104F, 54-51-105D, 54-51-108B and 54-51-109I to add PW4098 engineapplicability.Revised Airworthiness Limitations 57-20-10I, 57-20-I02 and 57-54-I17.Renumbered Airworthiness Limitation 57-20-I01 to 57-20-I02.Revised Note in Section C to change Service Letter revision level from D to E andadded airplane derivatives to sub-section C.2.Added PW4098 and Trent 895 engine designation to Section E.Submitted by:S. Pierini (Boeing) 10/99Approved by: A. Bahrami (FAA)OCTOBER 2000 (Revision 13)Revised to include the addition of the GE90-94B Powerplant applicability toSection E of the Certification Maintenance Requirements. In addition, in SectionC.2 Life Limited Parts, the applicability for the FlightDeck Stowage CompartmentLatch was clarified. The latch life limitation is not applicable to Production LineNumbers 282 and on or incorporation of SB 777-25-0140.Submitted by:S. Pierini (Boeing)10/00Approved by: A. Bahrami (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9MARCH 2001 (Revision 14)Revised Life Limitation for 777-200 MainLanding Gear Door Actuator. LifeLimitation is not applicable following incorporation of SB 777-32-0028 on 777-200airplanes. There is no Life Limitation for actuators on the -2IGW or 300 airplanes.Submitted by:S. Pierini (Boeing)CANCELLED(See Revision 21)Approved by:A. Bahrami (FAA)CANCELLEDJULY 2002 (Revision 15)Added CMR 26-CMR-01 to inspect cargo fire bottles for leaks and applyCorrosion Inhibiting Compoundto burst discs on fill fittings of cargo fire bottles.Submitted by: Approved by:SEPTEMBER 2002 (Revision 16)Added CMR 52-CMR-01 applicable only to airplanes incorporating BoeingService Bulletin 777-25-0216. This amended type certificate complies with thenew 14 CFR 25.795 and the amended 14 CFR 25.772 as issued under FederalRegister Docket No. FAA-2001-11032.Submitted by: Approved by:NOVEMBER 2002 (Revision 17)Added Airworthiness Limitations 57-12-I02-1 and 57-12-I02-2 applicable to allairplanes L/N 423 and on due to design change.Revised statement in preamble to airworthiness limitations thatspecifies roll backof any escalated baseline structural inspection intervals when reaching theAWL Threshold.Submitted by:S. A. Pierini (Boeing)Approved by:JANUARY 2003 (Revision 18)Added L/N 427 and on applicability for 52-CMR-01.Submitted by:S. A. Pierini (Boeing) 1/31/03Approved by:REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-10777 MAINTENANCE PLANNING DATAJULY 2003 (Revision 19)Added SSIs 54-51-I07-a, b, c for Rolls Royce aluminum aft strut bulkheads to theAirworthiness Limitations. These SSIsare applicable to 777-200ER (200IGW)Rolls Royce Struts, Production Line Numbers 447 and on.Submitted by:S. A. Pierini (Boeing)Approved by:NOVEMBER 2003 (Revision 20)Added Section G which contains new airline operator reporting requirements foruncontrollable high thrust failure conditions or associated causal failures. Thisnew section supports words added to the 777 Type Certificate Data Sheet statingoccurrences of these subject failure conditions may endanger the safe operationof the airplane and hence are reportable under 121.703(c), 125.409 and 135.415.Section G contains a listing of thesefailures. ReferenceExemption No. 7955"Partial Exemption from 25.901(c) as it relates to uncontrollable high thrust.Deleted the related task field from the Airworthiness Limitations – StructuralInspection listing to be common with other Boeing models.Added an Applicability Note toclarify 26-CMR-01 requirement.Added "applicable to airplanes with -2 bottles installed, Line Numbers 410and on".Revised the 777-200/2IGW/300 Nose LandingGear Structural Safe Life limit from37,200 landings to 77,500 landings as a result of completion of further fatiguetesting on the nose landing gear.Deleted reference to Service Letter 777-SL-32-001-E and added reference toComponent Interchangeability Lists 161W0003(Main Landing Gear) and162W0002 (Nose Landing Gear) which provide a complete list of 777-200/-200IGW/-300 landing gear related components subject to life limitations.Submitted by:S. A. Pierini (Boeing)Approved by:Jeffrey E. Duven (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-11MARCH 2004 (Revision 21)This revision includes changes to theformat of the Airworthiness LimitationsStructural Inspections table with more explicit airplane applicability informationwas added. “Flight length sensitive” AWLswere also identified in the new listingfor the 777-300ER. Miscellaneous updates were made to non -300ER AWLs tocorrespond to the latest released SIPD information. SafeLife Limits for the MainLanding Gear, Main Landing Gear Support Fittings, and Nose Landing Gear wereadded for the 777-300ER. Specific safe life limits for the 777-300ER NoseLanding Gear Shock Strut components were also added. These componentsinclude; Upper Floating Piston, Upper Cylinder, Lower Cylinder, Metering Pin andOrifice Plate. This revision also includesthe Life Limitation (2,000 cycles) for the777-300ER Semi Lever Gear Hydraulic Strut (P/N 293W4201-2).Paragraph “G” "Reporting UncontrollableHigh Thrust Failure Conditions" wasalso revised for the 777-300ER.Main landing gear door actuator life limitation applicability was clarified with theaddition of a note. This addition thereby cancels Revision 14 of this document.26-CMR-01: Revised Airplane Note to clarify applicability. CMR is not applicableto -3 Bottles.Submitted by:S. A. Pierini (Boeing)Approved by:Jeffrey E. Duven (FAA)JUNE 2004 (Revision 22)Revised DTR number from 53-10-I02 to 53-10-I02A.Added DTR 53-10-I02B and 53-10-I02C for rework structural provisions for AntiCollision Light Installation.Submitted by:S. A. Pierini (Boeing)Approved by:Jeffrey E. Duven (FAA)JULY 2004 (Revision 23)Revised 27-CMR-02 task interval from 100 FH to 250 FH based on the PrimaryFlight Control System (PFCS) SafetyAnalysis and service data reported bythe airlines.Submitted by:S. A. Pierini (Boeing)Approved by:Jeffrey E. Duven (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12777 MAINTENANCE PLANNING DATADECEMBER 2004 (Revision 24)Added SSI 53-10-I02D applicable to airplanes L/N 501 and on.Added Airworthiness Limitations SSIs 53-30-I01A,53-30-I01B and 53-30-I01C that are applicable to airplanes with Connexion NextGeneration Antenna installation incorporated in production.Submitted by:S. A. Pierini (Boeing)Approved by:Jeffrey E. Duven (FAA)JUNE 2005 (Revision 25)Added SSI 57-53-I10 and 57-53-I11 applicable to all airplanes for the torque tubeand inboard closeout rib fitting. The reason for the added SSIs is the damagetolerance category changed from a Category 2 to a Category 3.Submitted by:S. A. Pierini (Boeing)Approved by:Jeffrey E. Duven (FAA)DECEMBER 2005 (Revision 26)Revised Airworthiness Limitations to addall Structural Significant Items (SSIs)for the 777-200LR. These changes support certification of the 777-200LR.Submitted by:S. A. Pierini (Boeing)Approved by:Jeffrey E. Duven (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-13JANUARY 2006 (Revision 27)Revised Airworthiness Limitations to addthree new Structural Significant Items(SSIs) in the Structural Inspections Table to addressa design change to the wingtrailing edge flap support pins. Revised related DTR Check Form Titles to addapplicability information for the existingflap pin design effective on L/N 504and L/N 519.Submitted by:S. A. Pierini (Boeing)Approved by:Dorr M. Anderson (FAA)FEBRUARY 2006 (Revision 28)Added new Airworthiness Limitations Numbers 28-AWL-19 and 28-AWL-20 toaddress inspection and repair ofthe Motor Operated Valve Actuators.Submitted by:S. A. Pierini (Boeing)Approved by:A. J. Pasion (FAA)MARCH 2006Revised the Applicability Table in Section B to clarify engine applicabilityinformation. Revised the Applicability section of the table shown in Section G toupdate the GE90 applicability to include 110B.Revised Fuel System Airworthiness Limitations to include paragraph (b) of thenew standard introduced by§ 25.981. Added 28-AWL-01 through 28-AWL-17 tothe Airworthiness Limitations Tableto satisfy SFAR 88 requirements.Revised 26-CMR-01 Airplane Note to remove reference to line numbers, as theinstallation of a -2 bottle is not line number dependent.Added text referencing the addition of Appendix L, “Post Threshold Intervals forStructures and Zonal Tasks”, to the MPD.Submitted by:S. A. Pierini (Boeing)Approved by: (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-14777 MAINTENANCE PLANNING DATAOCTOBER 2006Revised CMR 52-CMR-01 interval from 4 years to 2250 days to reflect theimproved reliability data for the Flight Deck Door Strike Assembly.Submitted by: S. A. Pierini (Boeing) Approved by: (FAA)DECEMBER 2006Revised applicability of fuel system airworthiness limitation number 28-AWL-20 toremove ITT actuator part number reference. The part number is listed in ServiceBulletin 777-28A0034.Revised Airworthiness Limitations – Systems section introduction to includerevisions recommended by the Seattle FAA Flight Standards group.Submitted by: S. A. Pierini (Boeing) Approved by: (FAA)JUNE 2007Revised the Airworthiness Limitations –Structural Inspections table to update-200LR thresholds to cover new configuration.Submitted by: (Boeing) Approved by: (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-15SEPTEMBER 2007Added a new fuel system Airworthiness Limitation number 28-AWL-18 toincorporate an operational check of FuelPump Ground Fault Interrupter (GFI).Revised Section D. Airworthiness Limitations – Systems- Exceptional Short-TermExtensions to clarify notification requirements. Revised Section F. CertificationMaintenance Requirements (CMRs) – Exception Short-Term Extensions to clarifynotification requirements.Revised Paragraph “I” to incorporate “Reporting Uncontrolled High Thrust FailureConditions” per FAR 121.703 and FAR 135.415.Submitted by: B. McLoughlin (Boeing) Approved by: Dorr Anderson (FAA)OCTOBER 2007Revised Section C.1. Structural Safe Life Parts and associated Figures 3 and 4 asper the changes submitted by Landing GearStructures Design Center, Boeing.These changes reflect the latest landing gear safe life limit information containedin the revised landing gear interchangeability drawings (a) Main GearInterchangeability List 161W0003 Revision E, and (b) Nose GearInterchangeability List 162W0002 Revision E.Revised AWL 28-AWL-01 task descriptionby removing "between reference toSta 1035 to Sta 1045 and Zones 131 and 132" and adding "per Boeing AMM28-11-00".Revised 28-AWL-18 interval from 1 YR to 375 DYS be consistent with 777Program usage parameters.Revised Exceptional Short-Term Extensions for CMRs to clarify notificationrequirements for CMR 52-CMR-01.Revised CMR 52-CMR-01 interval from 2250 days to 3375 days to reflect theimproved reliability data forthe Flight Deck Door Strike Assembly and relatedupdates to the exceptional short-term extensions information.Submitted by: E. B. Lange (Boeing) Approved by: Philip Forde (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-16777 MAINTENANCE PLANNING DATADECEMBER 2007Added new SSIs 28-00-I01A and 28-00-I01B that are applicable to 777-200LRaircraft with Auxiliary Fuel Tanks installed.Revised Section C.2, Life Limited Parts, to include 777-200LR Optional AuxiliaryBody Fuel Tanks. Revised Section D.Airworthiness Limitations – Systems byadding a note to clarify that the auxiliary fuel tankcomplies with CFR 25.981,Amendment 25-102.Revised AWLs 28-AWL-11 through -14 and 18 toincorporate Auxiliary Fuel Tankinformation. Revised AWL 28-AWL-16 from "The following must be maintainedduring fuel tank access door installation" to "The following must be maintainedduring installation of the tank access doors located on the lower wing skin".Revised AWL 28-AWL-19 by adding additional AMM procedures.Added new AWLs 28-AWL-21 through 28-AWL-26 to support 777-200LR aircraftwith Auxiliary Fuel Tanks installed.Submitted by: E. B. Lange (Boeing) Approved by: T. A. Enyart (FAA)FEBRUARY 2008Revised 28-AWL-03 to reflect the new maximum loop resistance valuesassociated with the lightning protectionof the unpressurized FQIS wire bundleinstallations so as to satisfy the Airworthiness Limitation Instructions required bySFAR 88. Also removed the joint resistance values based upon engineeringreview and operator maintenance practice.Submitted by: J. Sabolchy (Boeing) Approved by: Philip Forde (FAA)NOVEMBER 2008Revised Section B., Airworthiness Limitations – Structural Inspections, by addinginformation regarding Individual AirplaneSpecific Airworthiness Limitations foraircraft L/N 740.Submitted by: J. Sabolchy (Boeing) Approved by: Philip Forde (FAA)REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-17JANUARY 2009Revised the AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSTable to include references to the 777F, as well as additional, separate sectionsaddressing threshold inspections for freighter and passenger aircraft.Revised the Airworthiness Limitations to incorporate the 777F configuration.Revised C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFELIMITS to include life limits for the 777F aircraft.Revised G. PAGE FORMAT – CERTIFICATION MAINTENANCEREQUIREMENTS (CMRs) table to includeapplicability for the 777F aircraft.Added the following CMR Tasks: 21-CMR-01, 27-CMR-05, 27-CMR-06,27-CMR-07, 27-CMR-08, and 27-CMR-09.Revised I. REPORTING UNCONTROLLABLE HIGH THRUST FAILURECONDITIONS to incorporate 777F aircraft.Submitted by: J. Onorati (Boeing) Approved by: Jeffrey E. Duven (FAA)FEBRUARY 2009Revised 28-AWL-02, 28-AWL-03, and 28-AWL-16 per the Approved AlternativeMethod of Compliance to Airworthiness Directive 2008-11-13.Revised 28-AWL-01 – 05, 28-AWL-07 – 08, 28-AWL-10, 28-AWL-13 – 16, and28-AWL-19 – 23 by adding updates to enhance clarity of the AirworthinessLimitations.Revised Section F front matter by addingthe Airworthiness Limitations – NitrogenGeneration System (NGS) requirementsand by adding 47-AWL-01 – 47-AWL-06NGS tasks.Submitted by: J. Sabolchy (Boeing) Approved by: Jeffrey E. Duven (FAA)JANUARY 2010Revised the AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSTable to include updated inspectionrequirements for the 777-200/200LR/300/300ER aircraft as part of a planned re-assessment of the Supplemental FatigueInspection Program.Submitted by: J. Onorati (Boeing) Approved by: Jeffrey E. Duven (FAA)SIGNATURE ON FILE02/11/2010REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-18777 MAINTENANCE PLANNING DATAAUGUST 2010Revised Paragraph F. Airworthiness Limitations – Nitrogen Generation SystemsTasks by updating the following text "CDCCLs" with "AWLs (ALIs and CDCCLs)","design limitations", and "Final Flammability Rule, ParagraphIII(F), Section 7,Paragraph M25.4(a)" to clarify the intent of the paragraph.Revised 47-AWL-01 47-AWL-02, 47-AWL-03, 47-AWL-04, 47-AWL-05, 47-AWL06, and 47-AWL-07 by updating the Applicability column to include airplanes thathave incorporated Service Bulletin 777-47-0002.Revised 47-AWL-01 and 47-AWL-05 by updating the Task Description to includeinstructions and a Note to clarify the procedure and parameters for themaintenance action.Revised 47-AWL-02 by replacing the text "replaced and installed" with "replacedor reinstalled" to clarify the procedure and parameters for the maintenance action.Revised 47-AWL-04 by replacing the text"per Boeing AMM 47-43-02" with "(referto Boeing AMM 47-42-04)".Added 47-AWL-07, an identification of the maintenance standard for the NitrogenGeneration System and notice of potential future compliance requirementsassociated with decreased aircraft descent rates.Submitted by: John Sabolchy(Boeing)Approved by: Jeffrey E. Duven(Seattle FAA ACO)Robert D. BrenemanSIGNATURE ON FILE11/02/2010JANUARY 2011Added CMR Number 32-CMR-01, a 50 flightor 25 day cycle, whichever occurslater, lubrication task for the left andright Main Landing Gear truck beam andinner cylinder pivot joints. Applicable to airplanes Line Number 915 and on orairplanes incorporating Boeing Service Bulletin 777-32-0085.Submitted by: Mark Arnold (Boeing) Approved by: Philip Forde (FAA) forRobert D. BrenemanSIGNATURE ON FILE1/28/2011REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-19JULY 2011Revised 47-AWL-03 to incorporate NGS performance features to showcompliance with 14 CFR 26.33.Submitted by: Mark Arnold(Boeing)Approved by: Robert D. Breneman(Seattle FAA ACO)SIGNATURE ON FILE7/21/2011REVISIONSREVISION AND REVISION DESCRIPTIONAPPROVALJUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-20777 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANKSection Page Date Section Page Date Section Page Date Section Page Date Section Page DateD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-21LIST OF EFFECTIVE PAGES777 MAINTENANCE PLANNING DATA9.0 1 JUL 20119.0 2 BLANK9.0 3 JUL 20119.0 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 JUL 20119.0 22 BLANK9.0 23 JAN 20109.0 24 JAN 20109.0 25 JAN 20109.0 26 JAN 20109.0 27 JAN 20109.0 28 JAN 20109.0 29 JAN 20099.0 30 JAN 20109.0 31 JAN 20109.0 32 JAN 20109.0 33 JAN 20109.0 34 JAN 20109.0 35 JAN 20109.0 36 JAN 20109.0 37 JAN 20109.0 38 JAN 20109.0 39 JAN 20109.0 40 JAN 20109.0 41 JAN 20109.0 42 JAN 20109.0 43 JAN 20109.0 44 JAN 20109.0 45 JAN 20109.0 46 JAN 20109.0 47 JAN 20109.0 48 JAN 20109.0 49 JAN 20109.0 50 JAN 20109.0 51 JAN 20109.0 52 JAN 20109.0 53 JAN 20109.0 54 JAN 20109.0 55 JAN 20109.0 56 JAN 20109.0 57 JAN 20109.0 58 JAN 20109.0 59 JAN 20109.0 60 JAN 20109.0 61 JAN 20109.0 62 JAN 20109.0 63 JAN 20109.0 64 JAN 20109.0 65 JAN 20109.0 66 JAN 20109.0 67 JAN 20109.0 68 JAN 20109.0 69 JAN 20109.0 70 JAN 20109.0 71 JAN 20109.0 72 JAN 20109.0 73 JAN 20109.0 74 JAN 20109.0 75 JAN 20109.0 76 JAN 20109.0 77 JAN 20109.0 78 JAN 20109.0 79 JAN 20109.0 80 JAN 20109.0 81 JAN 20109.0 82 JAN 20109.0 83 JAN 20109.0 84 JAN 20109.0 85 JAN 20109.0 86 JAN 20109.0 87 JAN 20109.0 88 JAN 20109.0 89 JAN 20109.0 90 JAN 20109.0 91 JAN 20109.0 92 JAN 20109.0 93 JAN 20109.0 94 JAN 20109.0 95 JAN 20109.0 96 JAN 20109.0 97 JAN 20109.0 98 JAN 20109.0 99 JAN 20109.0 100 JAN 20109.0 101 JAN 20109.0 102 JAN 20109.0 103 JAN 20109.0 104 JAN 20109.0 105 JAN 20109.0 106 NOV 20089.0 107 OCT 20079.0 108 JAN 20099.0 109 JAN 20099.0 110 JAN 20099.0 111 JAN 20099.0 112 DEC 20079.0 113 SEP 20079.0 114 SEP 20079.0 115 FEB 20099.0 116 FEB 20099.0 117 FEB 20099.0 118 FEB 20099.0 119 FEB 20099.0 120 FEB 20099.0 121 FEB 20099.0 122 FEB 20099.0 123 FEB 20099.0 124 FEB 20099.0 125 FEB 20099.0 126 FEB 20099.0 127 FEB 20099.0 128 AUG 20109.0 129 JUL 20119.0 130 JUL 20119.0 131 JUL 20119.0 132 JUL 20119.0 133 FEB 20099.0 134 DEC 20069.0 135 OCT 20079.0 136 MAY 19989.0 137 MAR 20069.0 138 FEB 20099.0 139 JAN 20119.0 140 JAN 20119.0 141 JAN 20119.0 142 FEB 20099.0 143 SEP 20079.0 144 BLANKJUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-22777 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-23A. SCOPEThe scheduled maintenance requirements described in this section result from Model 777 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 777 Type Certificate DataSheet. 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 by the Seattle FAA ACO. Principal Maintenance Inspectors (local regulatory authority) may notchange these requirements or the intervals associated withthese requirements.B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSINTRODUCTIONThe Structural Inspection Program approved inSection 3 of the 777 Maintenance ReviewBoard (MRB) Report and contained in Section 2 of this MPDdescribes an initial baseline structural maintenance program for all Structural Significant Items (SSIs). This program was developed in accordance withthe guidelines of MSG-3 and partially satisfies the requirementsof FAR 25.571 by providing accidental and environmental damagedetection opportunityfor all SSIs, and in some cases, fatigue damage detection opportunity. The supplemental structural inspections listed in thisSection 9 AirworthinessLimitations are for those SSIs that do notreceive adequate fatigue damage detection opportunity from the initial baseline structural program that is listed inSection 2. The supplemental inspections shown in Section 9 Airworthiness Limitations are to be accomplished in addition to thebaseline program.JAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-24777 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 therequired DTR are contained in D622W001-DTR. One form is shown for each SSI.The supplemental inspections are not presentlycompletely included in Section 2, but will be added at a future date. Until thesupplemental inspections areincorporated into Section 2, the Structural Inspections Table defines the inspection items. Document D622W001-DTR defines therequired inspectionmethods and intervals.THRESHOLD (777-200/200LR/300/300ER Airplanes)The fatigue inspection requirements apply after accumulation ofa certain number of flights (threshold). The initial fatigue inspections must beaccomplished within one repeat interval of the threshold for 777-200/200LR/300/300ER and must neverexceed 44,000 flights. Thethreshold for each ofthe 777-200/200LR/300/300ER aircraft fatigue inspections is defined in the Structural Inspections Table.When reaching a threshold of 40,000 flight cycles, all MPD 4,000 flight cycle (or higher) structural inspection repeat intervals must be no greater than thoseshown in the MPD Section 2. This means that any operator, who has escalated the structures program by changing task intervals,must reduce the repeatfrequencies back to the MPD baseline structures program intervals before accumulating 40,000 flightcycles. The reason for this is that the FAR 25.571damage tolerance evaluation takes credit for the baseline structures program. The Airworthiness Limitations listed in Section9 cover structure for whichthe required DTR is not met by the baseline structural inspections of Section 2. Any continued escalation beyond the MPD baseline structures programmay result in additional structure not meeting therequired DTR which was the basis of certification.In 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, constitutingCPCP implementation. The Corrosion Prevention and Control program identified withinthe Structural Maintenance Program of the 777 Maintenance Review Board Report (D622W001-MRBR) is FAA approved.JAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-25Additionally, some structures and zonal MPD items have been escalated by the Industry Steering Committee beyond the initial repeat interval consideredat certification. The intervals listed in Appendix L correspondto the original task intervals used in determining the DTR which satisfies FAR 25.571. As aresult, at 40,000 flight cycles, the items listed in Appendix L are required to be returned to the interval in that appendix, rather than what is listed inSections 2 and 3. This is to be in compliancewith the damage tolerance certification requirements.The Structural Inspections Table defines the Inspection Implementation Threshold for the 777-200/200LR/300/300ER. Some items are sensitive to flightlength and are identified by FLS in the Threshold column of the Structural Inspections Table (SeeFigure 1). Flight Length Sensitive (FLS) Items requireboth flight hours and flight cycles to determine the Implementation Threshold. Referto Figure 1 to determine the threshold forFLS Items.For the 777-200/200LR/300/300ER, SSIs are also categorized as Group (1) or Group (2). Group 1 SSI Inspection Thresholds are limited to a maximum of30,000 flight cycles and Group 2 SSI Inspection Thresholds are limited to a maximum of 40,000 flight cycles.For those items which are not flight lengthsensitive, the lowest threshold shown inthe Structural Inspections Table is 30,000flights. Exceptions to thisrequirement are: SSI 54-51-I02R, which hasa threshold of 28,600 flights for the 777-200LR/300ER, and SSIs 28-00-I01A and 28-00-I01B have a thresholdof 11,250 flights for the 777-200LR airplanes that have the optional auxiliary fuel tank installations. All other 777-200LR/300ER items which are not flightlength sensitive have either a 30,000 flightthreshold or 40,000 flight threshold depending upon whether the item is identifiedas Group 1 or Group 2. Theminimum threshold for those items which are identified as flightlength sensitive must be determined from Figure 1, based upon the actual airplaneutilization.A formal control system must be established for removable structural parts (repairable/rotable/expendables)which are subject to supplementalinspections, such as the flap support members. If part usage history data is available for all parts, the supplemental inspection program would follow theactual part usage history data. If part usage history data is not available, but records indicate that no part changes have occurred between airplanes,airplane usage history data can be used to start a tracking program for the supplemental inspections. If parts usage data is not available and the partscould have been switched between airplanes in the same maintenance program, it should be assumed that the time on any part is equal to the oldestairplane in the maintenance program. If a maintenance program includes airplanes from several operators, the oldest airplane inthat group of airplaneswould be used as the oldest airplane in the maintenance program. After overhaul or upon replacement of a part, as appropriate,a tracking program shouldbe established to control the removable parts. This system must also apply to used structural parts which are purchased for installation on an airplane.JAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-26777 MAINTENANCE PLANNING DATAFIGURE 1. FLIGHT LENGTH SENSITIVE (FLS) THRESHOLD CURVE (777-200/200LR/-300ER ONLY)USE OF FLIGHT LENGTH SENSITIVE THRESHOLD CURVE (777-200/200LR/300ER ONLY)(For FLS Items only; all non-FLS SSIs have thresholdsas listed in the Airworthiness Limitations Table)1. Determine the FLS status and Group of the SSI (777-200/200LR/300ER) from the Airworthiness Limitations Table.2. Determine the total number of flight cycles and flight hours experienced by the detail.3. If the detail is FLS, locate the intersection of Flight Hours and Cycles on the graph.4. If the point determined by Step 3 lies below the Threshold Curve for the group from Step 1, the detail has not reached the Inspection Threshold. If thepoint is on, above, or to the right of the Threshold Curve forthe specified group, then the Inspection Threshold has been reached.JAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-27THRESHOLD (777F Airplanes)The fatigue inspection requirements apply after accumulation ofa certain number of flights (threshold). The initial fatigue inspections must beaccomplished at the threshold defined in the Structural Inspections Table, or within an interval not to exceed 2,500 flight cycles beyond the threshold. Thethreshold for 777F aircraft fatigue inspectionsis defined in the Structural Inspections Table.When reaching a threshold of 25,000 flight cycles, all MPD 4,000 flight cycle (or higher) structural inspection repeat intervals must be no greater than thoseshown in the MPD Section 2. This means that any operator, who has escalated the structures program by changing task intervals,must reduce the repeatfrequencies back to the MPD baseline structures program intervals before accumulating 25,000 flightcycles. The reason for this is that the FAR 25.571damage tolerance evaluation takes credit for the baseline structures program. The Airworthiness Limitations listed in Section9 cover structure for whichthe required DTR is not met by the baseline structural inspections of Section 2. Any continued escalation beyond the MPD baseline structures programmay result in additional structure not meeting therequired DTR which was the basis of certification.In addition to the thresholds described above, a calendar threshold of 20 years applies unless an initial inspection of an FAAapproved CorrosionPrevention and Control Program (CPCP) has occurred, constituting CPCP implementation.The CPCP identified within the StructuralMaintenanceProgram of the 777 Maintenance Review Board Report (D622W001-MRBR) is FAA approved.Additionally, some structures and zonal MPD items have been escalated by the Industry Steering Committee beyond the initial repeat interval consideredat certification. The intervals listed in Appendix L correspondto the original task intervals used in determining the DTR which satisfies FAR 25.571. As aresult, at 25,000 flight cycles, the items listed in Appendix L are required to be returned to the interval in that appendix, rather than what is listed inSections 2 and 3. This is to be in compliancewith the damage tolerance certification requirements.The Structural Inspections Table defines the Inspection Implementation Threshold for the 777F. Some items are sensitive to flight length and are identifiedby FLS in the Threshold column of the Structural Inspections Table (See Figure 2). Flight Length Sensitive (FLS) Items requireboth flight hours and flightcycles to determine the Implementation Threshold. Referto Figure 2 to determine the threshold for FLS Items.For the 777F, SSIs are also categorized as Group 1 or Group 2.Group 1 SSI Inspection Thresholds are limited to a maximum of 18,750 flight cycles andGroup 2 SSI Inspection Thresholds are limited to a maximum of 25,000 flight cycles.JAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-28777 MAINTENANCE PLANNING DATAFor those items which are not flight lengthsensitive, the lowest threshold shown inthe Structural Inspections Table is 18,750flights. All other 777F itemswhich are not flight length sensitive have either a 18,750 flightthreshold or 25,000 flight threshold depending upon whether the item is identified asGroup 1 or Group 2. The minimum threshold for those items which are identified as flight length sensitive must be determined from Figure 2, based uponthe actual airplane utilization.JAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-29FIGURE 2. FLIGHT LENGTH SENSITIVE (FLS) THRESHOLD CURVE (777F ONLY)USE OF FLIGHT LENGTH SENSITIVE THRESHOLD CURVE (777F ONLY)(For FLS Items only; all non-FLS SSIs have thresholdsas listed in the Airworthiness Limitations Table)1. Determine the FLS status and Group of the SSI(777F) from the Airworthiness Limitations Table.2. Determine the total number of flight cycles and flight hours experienced by the detail.3. If the detail is FLS, locate the intersection of Flight Hours and Cycles on the graph.4. If the point determined by Step 3 lies below the Threshold Curve for the group from Step 1, the detail has not reached the Inspection Threshold. If thepoint is on, above, or to the right of the Threshold Curve forthe specified group, then the Inspection Threshold has been reached.FIGURE 10.2 FLIGHT LENGTH SENSITIVE (FLS) THRESHOLD CURVEFLIGHT HOURS ( x 1,000)Group 1 & 2Threshold ExceededGroup 1 ThresholdExceeded51015202530

FLIGHT CYCLES ( x 1,000)GROUP 1GROUP 200 20 40 60 80 100 120 14016052.257518.75JAN 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-30777 MAINTENANCE PLANNING DATAREPEAT INSPECTION INTERVALA Repeat Interval for the Fatigue Inspectionof an SSI is established from its respective Damage Tolerance Rating (DTR) Check Form. The DTR CheckForms are the result of the damage tolerance assessment / evaluation documented during certification of the airplane. Revisionto the required DTRCheck Form or the DTR Curve is not allowed without the prior approval from the FAA Seattle Aircraft Certification Office (ACO).For -200/200LR/300ER/777F only: If the applicability/threshold box for the item includes a "<7 Hrs" or "> 7 Hrs" designation, the average airplane hoursper flight should be calculated for the airplane and the repeatinspection interval should be based on the DTR Check Form withthe corresponding"<7 Hrs" or "> 7 Hrs" label. If the current average hours per flight is longer than the prior average hours per flight, the current average hours per flightshould be used for determining which DTR Check Form should be utilized.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, the Transport AirplaneDirectorate, the FAA, and to Boeing Commercial Airplane Groupusing the Discrepant Structure Report Form. Refer to D622W001-DTR for the requiredreport form (any suitable alternative whichcontains the same information may be used).REMOVAL OF EXCESS SEALANT WHEN INSPECTING:1. In areas where DTR Check Form (Section 9) visual inspection is prevented due tosealant, remove any fastener cap, fillet or brush sealant that extendsbeyond 0.20" around the fastener at locations that are to beinspected. Remove anyadditional sealant which impairs visibilityof the structure adjacentto the fastener cap, fillet or brush sealant.JAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-312. The following Structural Items require fastener cap, fillet orbrush sealant that extends beyond 0.20" to be removed for baseline maintenance visualinspections (MPD Section 2 and 3) at orprior to reaching the listed thresholds:Principle Structural Element(PSE) ThresholdInstallationDrawing Drawing Title NotesFuselage – UnderwingLongeron (777 All)P: 40,000 FCF: 25,000 FC140W9250Under WingLongeron Instl1) Fasteners on the Underwing Longeron common to theFuselage Front Spar Bulkhead Outer Chord within 3 inchesforward of the Wing Front Spar. In this area, also removeexcess fillet seal at the free edge of the longeron thatextends more than 0.25” from the fuselage skin surface.2) Fasteners on the Underwing Longeron common to theWing Lower Skin within 3 inchesaft of the Fuselage FrontSpar Bulkhead. In this area, also remove excess fillet sealat the free edge of the longeron that extends more than0.25" from the lower wing skin surface.Note: Does not require sealant removal inside the fuel tank.Fuselage – Front SparSide Frame Fitting(777 All)P: 40,000 FCF: 25,000 FC110W1652Front Spar InstlIntegration –BBL 122.45Fasteners on the Front Spar Side Frame Fitting within6 inches above and below the Wing Upper Surface.Note: Does not require sealant removal inside the fuel tank.Fuselage – Rear SparSide Frame Fitting(777 All)P: 40,000 FCF: 25,000 FC110W1651Rear Spar InstlIntegration –BBL 122.45Fasteners on the Rear Spar Side Frame Fitting within6 inches above and below the Wing Upper Surface.Note: Does not require sealant removal inside the fuel tank.Engine Strut –Pratt and Whitney(777-200/200IGW/300)P: 40,000 FCF: 25,000 FC311W3110 (Fwd)311W3130 (Aft)Spar Assy – FwdUpper Nacelle/StrutStrut Frame Assy –AftFasteners on the LHS upper spar chords common to upperspar webs between NSTA 245.0 and 255.0 and betweenNSTA 319.0 and 333.0, except where spar chord is notvisible.JAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-32777 MAINTENANCE PLANNING DATATable Notes: P: = 777-200/-200IGW/-200LR/-300/-300ER (Passenger) airplanesF: = 777F (Freighter) airplanesAs an option to sealant removal; if sealant does not extend beyond 0.50" from the fastener, perform surface HFEC inspection 360degreesaround the fastener per NDT Part 6.Principle Structural Element(PSE)ThresholdInstallationDrawingDrawing TitleNotesEngine Strut –General Electric(777-200/200IGW)P: 40,000 FCor 120,000 FHwhichevercomes first.F: 25,000 FCor 120,000 FHwhichevercomes first311W1110 (Fwd)311W1130 (Aft)Spar Assy – FwdUpperTorque Box Assy –Aft1) Fasteners on the RHS upperspar chord common toupper spar web between NSTA 213.5 and 230.0 and allfasteners on the RHS upper spar chord common to theforward engine mount bulkhead between NSTA 187.0 and192.0, except where sparchord is not visible.2) Fasteners on the LHS upper spar chords common to thebulkhead between NSTA 303.0 and 316.0, except wherespar chord is not visible.Engine Strut –Rolls Royce(777-200/200IGW/300)P: 40,000 FCF: 25,000 FC311W5110 (Fwd)Spar Assy – FwdUpperFasteners on the upper spar chord common to forwardengine mount bulkhead betweenNSTA 187.0 and 192.0,except where spar chord is not visible.Horizontal Stabilizer –BL 0, Upper ExternalSplice Plate (777 All)P: 40,000 FCF: 25,000 FC182W7000Splice Instl –Centerline, HorizStabFasteners on the Upper External Splice Plate common tothe Rear Spar Terminal Fitting and Upper Rear SparExternal Splice Fitting within 3 inches of BL 0.Horizontal Stabilizer –BL 0, Upper Rear SparExternal Splice Fitting(777 All)P: 40,000 FCF: 25,000 FC182W7000Splice Instl –Centerline, HorizStabFasteners on the Upper Rear Spar External Splice Fittingcommon to the Rear Spar Terminal Fitting and UpperExternal Splice Plate within 3 inches of BL 0.Horizontal Stabilizer –BL 0, Rear Spar TerminalFitting (777 All)P: 40,000 FCF: 25,000 FC182W7500Terminal FittingInstl – Rear Spar,Horiz StabFasteners on the Rear Spar Terminal Fitting common tothe Upper Rear Spar External Splice Fitting and UpperExternal Splice Plate within 3 inches of BL 0.Wing – Side of BodySplice Upper Surface(777 All)P: 40,000 FCor 120,000 FHwhichevercomes first.F: 25,000 FCor 120,000 FHwhichevercomes first110W1653(Inboard)112W3301(Outboard)Upper Panel InstlIntegration – BBL122.45Rib Chord Instl –Upper Panel, BBL122.45Fastener row on the Rib Chord common to the upper skinpanels both inboard and outboard within 2 inches ofBBL 122.45.Note: Does not require sealant removal inside the fuel tank.JAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-333. General Notes:Refer to AMM 51-31-01 for general sealant removal and application.Refer to AMM 28-11-00 (Task 28-11-300-802) for sealant (BMS 5-45) inside the fuel tank removal and application.Refer to AMM 28-11-00 (Task 28-11-300-803) for secondary fuel barrier sealant (BMS 5-81, Type II) outside the fuel tank removaland application.If sealant is removed inside the fuel tank for inspection, caremust be taken to remove any sealant debris in the fuel tank.Locations where sealant is removed for inspections must have the sealant restored to drawing or AMM requirements (and any applicable ServiceBulletins or repair instructions) after completion of the inspections. Sealant of fueltank fasteners must comply with MPD Section 9, Parts D and E.JAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-34777 MAINTENANCE PLANNING DATASUPPLEMENTAL STRUCTURAL INSPECTION REQUIREMENTSThe table starting on the next page liststhe Airworthiness Limitation supplemental structural inspection requirements. Each item is listed by SSI Number,DTR Check Form Title, DTR Location, and Airplane Applicability/Threshold.There are correspondingDTR Check Forms in D622W001-DTR for each itemlisted in the table. Where there is morethan one listing for a given SSI Number, theDTR Check Form title and location is theunique identifier.Airplane applicability is listed as shown below (no entryimplies all 777 airplanes):ALL = All 777 Airplanes-200 = 777-200 up to or equal to 547,000 lbs.MTW-300 = 777-300-300ER = 777-300ER-200IGW = 777-200 IGW: Any 777-200 airplane greater than 547,000 lbs. MTW (also equates to -200ER)-200LR = 777-200LR (Longer Range)777F = 777 FreighterRR = Rolls Royce TRENT = TRENT 800 (875-17, 877-17, 884-17, 890-17, 892, 892B, 895)PW = Pratt & Whitney PW4000 = PW4074, PW4077, PW4084, PW4090, PW4098GE = General Electric GE90= 75B/76B/85B/90B/94B/110B/115BNOTE: C/L or L/N = Airplane Cumulative Line Number, where mentioned with DTR Check Form Title, identifies certainDTR Check Forms to specific airplane line numbers.JAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-35AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777F27-41-I01 Safety Rod, Horizontal StabilizerTrim ActuatorZone 310, Section 481 30,000 30,000 30,000 30,000 30,00027-41-I01 Safety Rod, Horizontal StabilizerTrim ActuatorZone 310, Section 48118,75028-00-I01A Auxiliary Body Fuel Tanks InternalCorner AnglesOuter Angle around peripheryof Forward Panel & Lower SidePanel Edges111,250(7)28-00-I01B Auxiliary Body Fuel Tank Inner Skin At Fastener Holes of PanelsConnecting to Diaphragms111,250(7)52-10-I02 Passenger Doors Outer Skin andStructureOuter Skin Between Handleand Window Cutouts2 40,000 40,000 40,000 40,000 40,000 25,00052-34-I03A Large Cargo Door Latch SupportFrame FittingsLatch Cam Support Fitting LugBore2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)52-34-I03B Large Cargo Door Latch SupportFrame Fitting (135W1191)Outer Chord2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)52-34-I05A Large Cargo Door Latch FrameInner ChordSplice to Latch Support Fitting1 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)52-34-I05B Large Cargo Door Outer Skin atAttachment to Main HingesOuter Skin and Latch FrameOuter Chord1 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)52-37-I03A Large Cargo Door Latch SupportFrame FittingsLatch Cam Support Fitting LugBore2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)52-37-I03B Large Cargo Door Latch SupportFrame Fitting (135W1191)Outer Chord2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)52-37-I05A Large Cargo Door Latch FrameInner ChordSplice to Latch Support Fitting1 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)52-37-I05B Large Cargo Door Outer Skin atAttachment to Main HingesOuter Skin and Latch FrameOuter Chord1 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)52-38-I01 Main Deck Cargo Door – MainLatch Cam AssembliesMain Rotary Cam Latch – CamShaft118,750(7)JAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-36777 MAINTENANCE PLANNING DATA52-38-I03A Main Deck Cargo Door – LatchCam and Roller Support FittingsLatch Cam Support Fitting LugBore2 25,000(7)52-38-I03B Main Deck Cargo Door – LatchCam and Roller Support FittingsLatch Cam Support Fitting –Outer Chord2 25,000(7)52-38-I05A Main Deck Cargo Door – LatchCam and Roller Support FittingsLatch Cam Support Fitting –Latch Frame Inner Chord Spliceto Latch Support Fitting1 18,75052-38-I05B Main Deck Cargo Door – Skin andDoor StructureOuter Skin at Attachment toMain Hinges: Outer Skin andLatch Frame Outer Chord.1 18,75053-00-I01 Upper Lobe Skin Panels Entire Fuselage – Skin BS132.5 to BS 2150 Above WL200 Except Under Fairings2 40,000 40,000 40,000 40,000 40,00053-00-I02 Lower Lobe Skin Panels Entire Fuselage – Skin BS132.5 to BS 2150 Below WL200 Except Under Fairings2 40,000 40,000 40,000 40,000 40,00053-00-I03 Upper and Lower Lobe Skin Panels Sections 43, 46, 47 – SkinUnder Fairings2 30,000 30,000 30,000 30,000 30,00053-10-I02A Crown Skin Antenna Installation –TCASBody Station 455.5 @ B.L. 0 2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I02B ACL Installation External Doubler Crown Skin STA 602, BL 0Under Stringer2 30,000(8)30,000(7)30,000(7)30,000(7)53-10-I02C ACL Installation External Doubler Crown Skin STA 602, BL 0 atCutout2 30,000(8)30,000(7)30,000(7)30,000(7)53-10-I02D Crown Skin Production ACLInstallationCrown Skin STA 602.5, BL 0 2 40,000 40,000 40,000 40,000 40,000 18,75053-10-I06 Ground Maneuver CameraInstallationLower Lobe STA 604.06 @ BL02 40,000 40,00053-10-I07A Longitudinal Skin Lap Splices InnerSkinTypical – All Section 41 LapSplices2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3753-10-I07B Longitudinal Skin Lap Splices OuterSkinTypical – All Section 41 LapSplices2 40,000 40,000 40,000 40,000 40,000 25,00053-10-I09A Passenger Entry Door #1– Cutout Upper Corner @ STA 332.5and Lower Corner @ STA 3822 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I09B Passenger Entry Door #1– Cutout Edge Frames @ STA 332.5andSTA 3822 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I09C Passenger Entry Door#1 – Cutout Bear Strap 2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I09D Passenger Entry Door #1 – CutoutUpper SillSta 309.5 to Sta 357.25 2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I11A Forward Large Cargo Door – Cutout Upper Corner @ STA 5012 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I11B FWD Large Cargo Door – CutoutOuter Chord – Upper SillBody Station 592 to 6131 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)53-10-I11C Forward Large Cargo Door – Cutout Upper Sill, STA 487 to STA 508 2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I11D Forward Large Cargo Door – Cutout Lower Sill, STA 592 to STA 634 2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I14 Forward Equipment Bay AccessHatch Cutout StructureSTA 143.5 to 172.5 Forward ofNLG Well2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I16 E/E Bay Access Hatch CutoutStructureSTA 360 to 382 Aft of NLG Well 2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I18 NO. 1 Crew Window CutoutStructureLower Window Sill, Left andRight2 40,000 40,000 40,000 40,000 40,000 25,00053-10-I20 NO. 3 Crew Window CutoutStructureEF Window Post BetweenWindows 2 & 3, Left & Right2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I24 NLG Well Top PanelSTA 246.2 Step Beam at BL 01 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-38777 MAINTENANCE PLANNING DATA53-10-I25 WL 152 Beam (C/L 1 to 40)Nose Wheel Well Aft Bulkhead@STA 332.5 LBL and RBL 301 30,000(8)53-10-I25 WL 152 Beam (C/L 41 and on)Nose Wheel Well Aft Bulkhead@STA 332.5 LBL and RBL 301 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)53-10-I26-1 Nose Wheel Well Cutout Structure(C/L 1 to 40)Forward End of Cutout LBL 30toRBL 302 40,000(7)53-10-I26-1 Nose Wheel Well Cutout Structure(C/L 41 and on)Forward End of Cutout LBL 30toRBL 302 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I26-2 Nose Landing Gear Well Cutout(C/L 1 to 40)STA 332.5 Aft End of Cutout2 40,000(7)53-10-I26-2 Nose Landing Gear Well Cutout(C/L 41 and on)STA 332.5 Aft End of Cutout2 40,000(7)40,000(7)40,000(7)53-10-I26-2 Nose Landing Gear Well Cutout STA 332.5 Aft End of Cutout240,000(7)40,000(7)25,000(7)53-10-I29-1 Nose Wheel Well Trunnion SupportFitting (C/L 1 to 40)BS 320.5, WL 121 to WL 133,Left & Right Side Free Flange2 40,000(8)53-10-I29-1 Nose Wheel Well Trunnion SupportFitting (C/L 41 and on)BS 320.5, WL 121 to WL 133,Left & Right Side Free Flange2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I29-2 Nose Wheel Well Trunnion SupportFitting (C/L 1 to 40)BS 320.5, Left and Right Side,WL 181, Side Panel to TopPanel Joint2 40,000(8)53-10-I29-2 Nose Wheel Well Trunnion SupportFitting (C/L 41 and on)BS 320.5, Left and Right Side,WL 181, Side Panel to TopPanel Joint2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-10-I30 NLG Drag Brace Fitting – Lug andBushing InterfaceSTA 260, WL 173, RBL/LBL 301 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3953-30-I01A Crown Panel Skin/Stringer CrackingUnder RadomeS-3L to S-3R, BS 755.5 to 846 2 40,000 40,000 40,000 40,000 40,00053-30-I01B Longitudinal Skin Crack UnderRadomeBS 755.5 to 846, S-3L to S-3R 2 30,000 30,000 30,000 30,000 30,00053-30-I01C Longitudinal Skin Crack UnderAntenna Attach Angle or Skin LugFittingsBS 755.5 to 846, BTWN S-3LandS-3R2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)53-30-I03 Fuselage Skin adjacent to StrakeletAttach Fitting (L/N 1-218)STA 930 S-28 to S-30, STA 972S-27 to S-292 30,000(8)30,000(7)30,000(7)53-30-I03 Fuselage Skin adjacent to StrakeletAttach Fitting (L/N 219 and on)STA 930 S-28 to S-30, STA 972S-27 to S-292 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-30-I05-1 Fuselage Circumferential Skin/Stringer Splice, BS 1035 (L/N 75 –and on)Bulkhead Outer Chord 1 30,000(8)30,000(7)30,000(7)18,750(7)53-30-I05-1 Fuselage Circumferential Skin/Stringer SpliceBS 1035, Bulkhead OuterChord1 30,000(7)30,000(7)53-30-I05-2 Fuselage Circumferential Skin/Stringer Splice, BS 1035 (L/N 75 –and on)Stringer End Fasteners 2 40,000(7)40,000(7)40,000(7)25,000(7)53-30-I05-2 Fuselage Circumferential Skin/Stringer SpliceBS 1035, Stringer EndFasteners2 40,000(7)40,000(7)53-30-I05-3 Fuselage Circumferential Skin/Stringer Splice, BS 1035 (L/N 75 –and on)Paddle Fitting End Fasteners 2 40,000(7)40,000(7)40,000(7)25,000(7)53-30-I05-3 Fuselage Circumferential Skin/Stringer SpliceBS 1035, Paddle Fitting EndFasteners2 40,000(7)40,000(7)53-30-I06A Longitudinal Skin Lap Splices InnerSkin (L/N 1-422)Section 43 Lap Splices at S-142 30,000(8)30,000(7)30,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-40777 MAINTENANCE PLANNING DATA53-30-I06A Longitudinal Skin Lap Splices InnerSkin (L/N 423 and on)Section 43 Lap Splices at S-14 2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-30-I06A Longitudinal Skin Lap SplicesInner SkinAll Section 43 Lap SplicesexceptS-142 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-30-I06B Longitudinal Skin Lap SplicesOuter Skin – Except Lower Row (S45)Typical – All Section 43 LapSplices2 40,000 40,000 40,000 40,000 40,000 25,00053-30-I12A Passenger Entry Door #2– Cutout Upper Corner @ STA 739 andLower Corner @ STA 788.52 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)53-30-I12B Passenger Entry Door #2– Cutout Edge Frames @ STA 739 andSTA 788.52 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)53-30-I12C Passenger Entry Door#2 – Cutout Bear strap 2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)53-30-I12D Passenger Entry Door #2 – CutoutUpper SillUpper Sill, STA 718 to STA755.52 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)53-30-I12E Passenger Entry Door #2 – Cutout Lower Main Sill, STA 772 toSTA 8042 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)53-30-I13 Passenger Entry Door #2 – CutoutDoor Stop Backup FittingFittings #7A & 8A, #1A & #2A,STA 788.52 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)53-40-I01 Satcom Antenna – CircumferentialCracking with Broken StringerSTA 1077 to STA 1119 atStringer 10 to 121 30,000(8)30,000(7)53-40-I01 Skin and Stringer at SATCOMantenna installationSTA 1077 to STA 1119 atStringer 10 to 122 40,00053-40-I01 Crown Panel, Skin and StringerSection 44At Skin to Stringer FastenerLocations225,000(7)53-40-I03A Longitudinal Skin Lap Splices InnerSkin (L/N 1-450)Section 44 Lap Splices at S-142 30,000(8)30,000(7)40,000(7)40,000(7)53-40-I03A Longitudinal Skin Lap Splices InnerSkin (L/N 451 and on)Section 44 Lap Splices at S-142 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4153-40-I03A Longitudinal Skin Lap SplicesInner SkinAll Section 44 Lap Splicesexceptat S-142 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-40-I03B Longitudinal Skin Lap SplicesOuter SkinTypical – All Section 44 LapSplices2 40,000 40,000 40,000 40,000 40,000 25,00053-40-I05 Front Spar Side Fitting Inner ChordSpliceBS 1035, Upper Crown Spliceat Top Centerline and Stringer212 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-40-I06-1 Rear Spar Side Fitting Inner ChordSpliceBS 1245, Ring Frame Splice atStringer 12.5 and Stringer 212 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-40-I06-2 Rear Spar Side FittingBS 1245, Inner Chord atStringer 262 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-40-I06-3 Rear Spar Side Fitting at SeatTrack AttachmentBS 1245 at Stringer 27,Fastener in Inner Chord2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-40-I07 Aft Wheel Well Bulkhead InnerChord SpliceBS 1434, Upper Crown Slice atTop Centerline2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-40-I14A Passenger Entry Overwing Door#3 CutoutUpper and Lower corners atSTA 1154 and 1204130,000(7)30,000(7)53-40-I14B Passenger Entry Overwing Door#3 CutoutEdge Frame Inner Chord andWeb at STA 1154.4 and 1204240,000(7)40,000(7)53-40-I14C Passenger Entry Overwing Door#3 CutoutEdge Frame Inner Chord atSTA 1154.4 and 1204240,000(7)40,000(7)53-40-I14D Passenger Entry Overwing Door#3 CutoutEdge Frame Straps at STA1154.4and 1204240,000(7)40,000(7)53-40-I14E Passenger Entry Overwing Door#3 Cutout Upper Main SillUpper Main Sill, STA 1140 to1180240,000(7)40,000(7)53-50-I04-1 Aft Wheel Well Bulkhead SideFitting Inner Chord SpliceBS 1434, Splice at Stringer 212 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-50-I04-2 Aft Wheel Well Bulkhead SideFitting Outer ChordBS 1434 From Stringer 28 toStringer 452 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-42777 MAINTENANCE PLANNING DATA53-50-I04-3 Aft Wheel Well Bulkhead SideFitting Outer ChordBS 1434 Lower Splice atStringer 35 Strap and OuterChord at Fasteners2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-50-I04-4 Aft Wheel Well Bulkhead SideFitting Outer ChordBS 1434 Lower Splice atStringer 35 Outer Chord atFasteners1 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)53-50-I04-5 Aft Wheel Well Bulkhead HorizontalStiffeners (L/N 1-33)Horizontal Stiffeners at WL 109through 153, LBL5 – RBL52 30,000(8)53-50-I04-5 Aft Wheel Well Bulkhead HorizontalStiffeners (L/N 34 and on)Horizontal Stiffeners at WL 109through 153, LBL5 – RBL52 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-60-I01 Crown Panel, Skin and StringerSection 46At Skin to Stringer FastenerLocations2 40,000(7)40,000(7)53-60-I01 Crown Panel, Skin and StringerSection 46At Skin to Stringer FastenerLocations2 40,000(7)40,000(7)25,000(7)53-60-I06-1 Fuselage Circumferential Skin/Stringer Splice (L/N 75 – and on)BS 1434, Bulkhead OuterChord1 30,000(8)30,000(7)30,000(7)53-60-I06-1 Fuselage Circumferential Skin/Stringer SpliceBS 1434, Bulkhead OuterChord1 30,000(7)30,000(7)53-60-I06-1 Fuselage Circumferential Skin/Stringer SpliceBS 1434, Bulkhead OuterChord1 18,750(7)53-60-I06-2 Fuselage Circumferential Skin/Stringer Splice (L/N 75 – and on)BS 1434, Stringer EndFasteners2 40,000(7)40,000(7)40,000(7)53-60-I06-2 Fuselage Circumferential Skin/Stringer SpliceBS 1434, Stringer EndFasteners240,000(7)40,000(7)53-60-I06-2 Fuselage Circumferential Skin/Stringer SpliceBS 1434, Stringer EndFasteners225,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4353-60-I06-3 Fuselage Circumferential Skin/Stringer Splice (L/N 75 – and on)BS 1434, Paddle Fitting EndFasteners2 40,000(8)40,000(7)40,000(7)53-60-I06-3 Fuselage Circumferential Skin/Stringer SpliceBS 1434, Paddle Fitting EndFasteners2 40,000(7)40,000(7)53-60-I06-3 Fuselage Circumferential Skin/Stringer SpliceBS 1434, Paddle Fitting EndFasteners2 25,000(7)53-60-I07A Longitudinal Skin Lap Splices InnerSkin (L/N 1-422)Section 46 Lap Splice at S-5 2 30,000(8)30,000(7)30,000(7)53-60-I07A Longitudinal Skin Lap Splices InnerSkin (L/N 423 and on)Section 46 Lap Splices at S-5 2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-60-I07A Longitudinal Skin Lap Splices InnerSkinAll Section 46 Lap Splicesexceptat S-52 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-60-I07B Longitudinal Skin Lap SplicesOuter SkinTypical – All Section 46 LapSplices2 40,000 40,000 40,000 40,000 40,000 25,00053-60-I12A Passenger Entry Door #3 (-200)/#4(-300) – CutoutSection 46, Lower Corner @STA 1497 and Upper Corner @STA 1546.52 30,000(8)40,000(7)53-60-I12A Passenger Entry Door #3 (-200IGW) CutoutSection 46, Lower Corner @STA 1497 and Upper Corner @STA 1546.51 <= 7 Hrs,FLS, SeeFigure 1(7)53-60-I12A Passenger Entry Door #3 (-200LR)/#4(-300ER) – CutoutSection 46, Lower Corner @STA 1497 and Upper Corner @STA 1546.52 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)53-60-I12A Passenger Entry Door #3 (-200IGW/200LR) / #4 (-300ER)CutoutSection 46, Lower Corner @STA 1497 and Upper Corner @STA 1546.51> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-44777 MAINTENANCE PLANNING DATA53-60-I12B Passenger Entry Door #3 (-200)/#4(-300) CutoutEdge Frames @ STA 1497 andSTA 1546.52 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)53-60-I12C Passenger Entry Door #3 (-200)/#4(-300) CutoutBear Strap 2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)53-60-I12D Passenger Entry Door #3 (-200)/#4(-300) – CutoutUpper Main Sill, STA 1540 toSTA 15672 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)53-60-I12E Passenger Entry Door #3 (-200)/#4(-300) – CutoutLower Main Sill, STA 1476 toSTA 1513.52 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)53-60-I14A Small Cargo Door – Cutout LowerMain SillBody Station 1678.5 2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)53-60-I14B Small Cargo Door – Cutout UpperMain SillBody Station 1740 to 17692 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)53-60-I14C Small Cargo Door – Cutout InnerChord – Edge Frames – STA1678.5 and STA 1754.5Stringers at Door Stop Fittings2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)53-60-I14D Small Cargo Door – Cutout InnerChord – Edge Frames – STA1678.5 and STA 1754.5Stringers away from Door StopFittings2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)53-60-I14E Small Cargo Door – Cutout OuterChord – Edge Frames – STA1678.5 and STA 1754.5Stringers at Backup Fittings2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)53-60-I14F Small Cargo Door – CutoutBear Strap2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)53-60-I16A Aft Large Cargo Door – CutoutUpper Corner @ STA 17902 30,000(8)30,000(7)30,000(7)40,000(7)40,000(7)25,000(7)53-60-I16B Aft Large Cargo Door – CutoutOuter Chord – Upper SillBody Station 1683 to 16941 30,000(7)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)53-60-I16C Aft Large Cargo Door – Upper MainSillSTA 1769 to STA 18112 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4553-60-I20A Main Deck Cargo Door – Cutout –CornersUpper Corner, STA 1790Upper Corner, STA 1637.5Lower Corner STA 1637.51 18,750(7)53-60-I20D Main Deck Cargo Door – CutoutOuter Chord Upper SillBS 1648 – 1673 & BS 1756 –1780,S-6L1 18,750(7)53-70-I01 Crown Panel, Skin and StringerSection 47At Skin to Stringer FastenerLocations2 25,000(7)53-70-I04A Longitudinal Skin Lap SplicesInner Skin (L/N 1-422)Section 47 Lap Splices at S-5 2 30,000(7)30,000(7)30,000(7)53-70-I04A Longitudinal Skin Lap SplicesInner Skin (L/N 423 and on)Section 47 Lap Splices at S-5 2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-70-I04A Longitudinal Skin Lap SplicesInner SkinAll Section 47 Lap Splicesexceptat S-52 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-70-I04B Longitudinal Skin Lap SplicesOuter SkinTypical – All Section 47 LapSplices2 40,000 40,000 40,000 40,000 40,000 25,00053-70-I07A Passenger Entry Door #4 (-200)/#5(-300) – CutoutEdge Frames @ STA 2017 andSTA 20672 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)53-70-I07B Passenger Entry Door #4 (-200)/#5(-300) – CutoutBear Strap 2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)53-70-I07C Passenger Entry Door #4 (-200)/#5(-300) – CutoutSection 47, Upper Sill, STA2050 to STA 20872 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)53-70-I07D Passenger Entry Door #4 (-200)/#5(-300) – CutoutSection 47, Lower Sill, STA2000 to STA 20172 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)53-70-I09 Bulk Cargo Door – Cutout EdgeFramesSTA 1895 from Stringer S-33RtoS-40R, STA 1937 from StringerS-33R to S-35R2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-46777 MAINTENANCE PLANNING DATA53-80-I13A Pressure Bulkhead at STA 2150;Sec 48 Lap Splice (L/N 1-3)(5 of 12Lap Splices)Gore Lap Splices – WebSurface Hidden Crack FastenerRow at Stiffener1 30,000(8)53-80-I13A Pressure Bulkhead at STA 2150;Sec 48 Lap Splice (L/N 1-422)Gore Lap Splices – WebSurface Visible Crack FastenerRow at Stiffener2 30,000(8)30,000(7)30,000(7)53-80-I13A Pressure Bulkhead at STA 2150;Sec 48 Lap Splice (L/N 423 and on)Gore Lap Splices – WebSurface Visible Crack FastenerRow at Stiffener2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-80-I13B Pressure Bulkhead at STA 2150;Sec 48 Circumferential Crack inWeb at Radial StiffenerEntire Dome Between SuperTear Straps2 40,000 40,000 40,000 40,000 40,000 25,00053-80-I13C Pressure Bulkhead, STA 2150,Dome Web Attachment to Y-Ring(L/N 1-422)Entire Dome Web BetweenStiffeners2 30,000(8)30,000(7)30,000(7)53-80-I13C Pressure Bulkhead, STA 2150,Dome Web Attachment to Y-Ring(L/N 423 and on)Entire Dome Web BetweenStiffeners2 40,000(8)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-80-I14A Stabilizer Pivot Bulkhead STA 2370 Vertical Stiffener at BL 36.5 2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-80-I14B Stabilizer Pivot Bulkhead STA 2370– Vertical StiffenersLH/RH Upper/Lower corner ofcutout, BS 2370, LBL/RBL 15,WL 230/2801 30,000 30,000 30,000 30,000 30,000 18,75053-80-I15 Stabilizer Pivot Fitting Lug; Section48Station 2365 2 40,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)53-80-I17 Jackscrew Support Fitting Lug Section 48Fin Support –Station 2245240,000(7)40,000(7)40,000(7)40,000(7)40,000(7)25,000(7)54-51-I02A Aft Upper Spar Chord Splice (PW) Fasteners Common to theChord, Splice and Side Skinfrom NSTA 298-3081 30,000(8)30,000(7)30,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4754-51-I02D Strut Upper Spar (PW) Upper Spar Left and RightSides From NSTA 245 – NSTA2921 30,000(8)54-51-I02D Strut Upper Spar (PW) Upper Spar Left and RightSides From NSTA 245 – NSTA2921 30,000(7)54-51-I02D Strut Upper Spar (PW) Forward Chords between NSTA245 and 292 Left and Right1 30,000(7)54-51-I03B Strut Side Skin (PW) Cutout at NSTA 317 to NSTA330 on Left and Right SideSkins1 30,000(8)54-51-I03B Strut Side Skin (PW)Cutout at NSTA 317 to NSTA330 on Left and Right SideSkins1<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I03B Strut Side Skin (PW)Cutout at NSTA 317 to NSTA330 on Left and Right SideSkins1> 7 Hrs,FLS, SeeFigure 1(7)54-51-I03B Strut Side Skin (PW)Pressure Relief Door Cutoutbetween NSTA 317 and 330130,000(7)54-51-I04A Lower Spar Chord (PW)Spar Chord from NSTA 242 toNSTA 2481 30,000(8)54-51-I04A Lower Spar Chord (PW)Spar Chord from NSTA 242 toNSTA 248130,000(7)54-51-I04A Lower Spar (PW)Spar Chord from NSTA 242 toNSTA 248130,000(7)54-51-I04D Lower Spar (PW)Fastener Locations on LowerSpar Common to Web andChord, NSTA 261-2811 30,000(8)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-48777 MAINTENANCE PLANNING DATA54-51-I04D Lower Spar (PW)Fastener Locations on LowerSpar Common to Web andChord, NSTA 261-281130,000(7)54-51-I04D Lower Spar (PW)Fastener Locations on LowerSpar Common to Web andChord, NSTA 261-281130,000(7)54-51-I04F Lower Spar @ AEMB(PW)At Fasteners Common toChord, Web, AEMB – Fwd andAft of the Mount Attach Holes1 30,000(8)54-51-I04F Lower Spar @ AEMB(PW)At Fasteners Common toChord, Web, AEMB – Fwd andAft of the Mount Attach Holes130,000(7)54-51-I04F Strut Lower Spar (PW)Spar Chord at Aft Engine MountBulkhead between NSTA 298and 310130,000(7)54-51-I05D Forward Engine Mount Bulkhead(PW)Forward Flange @ 1.188 IN.Diameter GSE Holes, T = .451 30,000(8)54-51-I05D Forward Engine Mount Bulkhead(PW)Forward Flange @ 1.188 IN.Diameter GSE Holes, T = .601 30,000(8)54-51-I05D Forward Engine Mount Bulkhead(PW)Forward Flange at GSE Holes;T =.60130,000(7)54-51-I05D Strut Forward Engine MountBulkhead Assembly (PW)Front Flange at open GSEHoles130,000(7)54-51-I08B Strut Aft Bulkhead (PW)AtFastener Common to the AftUpper Spar Fitting, WL 153.46to WL 164.99130,000(7)54-51-I09I PW4090 and PW4098 ForwardEngine Mount Assembly (PW)Forward Mount Thrust Link130,000AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4954-51-I02B Upper Spar Bay 3 (GE)Upper Spar Between NSTA 230and NSTA 2451 30,000(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I02B Upper Spar Bay 3 (GE)Upper Spar Between NSTA 230and NSTA 2451> 7 Hrs,FLS, SeeFigure 1(7)54-51-I02E Strut Upper Spar Bay 5/6 at Cutout(GE)Upper Spar in Bay 5/6 at CutoutNSTA 268 to NSTA 2931 30,000(7)54-51-I02E Strut Upper Spar Bay 5/6 at Cutout(GE)Upper Spar in Bay 5/6 at CutoutNSTA 268 to NSTA 2931<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I02E Strut Upper Spar Bay 5/6 at Cutout(GE)Upper Spar in Bay 5/6 at CutoutNSTA 268 to NSTA 2931> 7 Hrs,FLS, SeeFigure 1(7)54-51-I02F Strut Upper Spar Bay 5 at Cutout(GE)Side Skin in Bay 5 at CutoutNSTA 268 to NSTA 2771 30,000(7)54-51-I02F Strut Upper Spar Bay 5 at Cutout(GE)Side Skin in Bay 5 at CutoutNSTA 268 to NSTA 2771<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I02F Strut Upper Spar Bay 5 at Cutout(GE)Side Skin in Bay 5 at CutoutNSTA 268 to NSTA 2771> 7 Hrs,FLS, SeeFigure 1(7)54-51-I02T Strut Upper Spar Bay 6 at Cutout(GE)Side Skin in Bay 6 at CutoutNSTA 283 to NSTA 2931 30,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-50777 MAINTENANCE PLANNING DATA54-51-I02T Strut Upper Spar Bay 6 at Cutout(GE)Side Skin in Bay 6 at CutoutNSTA 283 to NSTA 2931 <= 7 Hrs,FLS, SeeFigure 1(7)54-51-I02T Strut Upper Spar Bay 6 at Cutout(GE)Side Skin in Bay 6 at CutoutNSTA 283 to NSTA 2931> 7 Hrs,FLS, SeeFigure 1(7)54-51-I02R Upper Spar (GE)Fasteners Common to UpperChord, Web, Frames, @NSTA213/230/245/265/280/2951 30,000(7)54-51-I02R Upper Spar (GE)Fasteners Common to UpperChord, Web, Frames, @NSTA213/230/245/265/280/295130,000(7)54-51-I02S Upper Spar (GE)Fastener Common to the UpperChord and Web BetweenFrames at NSTA 245 andNSTA 2651 30,000(7)30,000(7)54-51-I03B Side Skin Cutout (GE)Side Skin Cutout, NSTA 310 toNSTA 3251 30,000(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I03B Side Skin Cutout (GE)Side Skin Cutout, NSTA 310 toNSTA 3251> 7 Hrs,FLS, SeeFigure 1(7)54-51-I04A Lower Spar Bay 3 (GE)Bay 3 Fasteners Common tothe Chord Between Frames atNSTA 230 and 2451 30,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5154-51-I04A Lower Spar Bay 3 (GE)Bay 3 Fasteners Common tothe Chord Between Frames atNSTA 230 and 2451<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I04A Lower Spar Bay 3 (GE)Bay 3 Fasteners Common tothe Chord Between Frames atNSTA 230 and 2451> 7 Hrs,FLS, SeeFigure 1(7)54-51-I04B Lower Outboard Spar Chord at AftEngine Mount Bulkhead (GE)Lower Spar at Aft EngineMount, NSTA 303 to NSTA 3171 30,000(7)30,000(7)54-51-I04J Lower Spar @ Cutout (GE)Bay 2 Fasteners Common tothe Chord and Web BetweenNSTA 212 and NSTA 2301 30,000(7)30,000(7)54-51-I04M Lower Spar (GE)Frames NSTA 213, 230, 245,265, 280, and 295, LH and RHSides1 30,000(7)54-51-I04M Lower Spar (GE)Frame NSTA 213, 230, 245,265, 280, and 295, LH and RHSide130,000(7)54-51-I05A Forward Engine Mount Bulkhead(GE)Tension Fitting Gusset atNSTA 186.651 30,000(7)30,000(7)54-51-I01i Aft Upper Spar Fitting R4 (GE)Horizontal Flange FirstFastener1> 7 Hrs,FLS, SeeFigure 1> 7 Hrs,FLS, SeeFigure 154-51-I02a Strut Upper Spar Bay2 (GE)RH Web/Chord/Skin BetweenNS 213-230130,000(7)30,000(7)18,750(7)54-51-I02b Strut Upper Spar Bay 3 (GE)LH and RH Chord and Web,NSTA 232-240130,000(7)30,000(7)54-51-I02B Strut Upper Spar Bay3 (GE)LH and RH Chord and Web,NSTA 232-240118,750(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-52777 MAINTENANCE PLANNING DATA54-51-I02c Strut Upper Spar Bay 3 (GE)Web Cutout at Sta 235-240130,000(7)30,000(7)54-51-I02e Strut Upper Spar Bay 5 (GE)Bay 5 Cutout Between NSTA268 and NSTA 2771<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I02e Strut Upper Spar Bay 5 (GE)Bay 5 Cutout Between NSTA268 and NSTA 2771> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I02e Strut Upper Spar Bay 5 (GE)Bay 5 Cutout Between NSTA268 and NSTA 2771<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I02e Strut Upper Spar Bay 5 (GE)Bay 5 Cutout Between NSTA268 and NSTA 2771> 7 Hrs,FLS, SeeFigure 2(7)54-51-I02f Strut Upper Spar Bay 6(GE)Side Skin Between NSTA 281and NSTA 2921<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I02f Strut Upper Spar Bay 6(GE)Side Skin Between NSTA 281and NSTA 2921> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I02f RHS Upper Spar Bay 6 (GE)Side Skin Between NSTA 281and NSTA 2921<= 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5354-51-I02f RHS Upper Spar Bay 6 (GE)Side Skin Between NSTA 281and NSTA 2921> 7 Hrs,FLS, SeeFigure 2(7)54-51-I02i Strut Upper Spar (GE)Upper Chord Splice BetweenNSTA 305 and NSTA 315130,000(7)30,000(7)54-51-I02i Strut Upper Spar (GE)Upper Chord Splice BetweenNSTA 305 and NSTA 3151 FLS,SeeFigure 2(7)54-51-I02m Strut Upper Spar (GE)R3/R4 Fitting Inboard Flange1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I02m Strut Upper Spar (GE)R3/R4 Fitting Inboard Flange1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I02m Strut Aft Upper Spar (GE)R3/R4 Fitting Inboard Flange1<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I02m Strut Aft Upper Spar (GE)R3/R4 Fitting Inboard Flange1> 7 Hrs,FLS, SeeFigure 2(7)54-51-I02p Strut Upper Spar (GE)R1 Fitting Attachment NSTA225 to NSTA 268130,000(7)30,000(7)54-51-I02p Pylon R1/Web Interface (GE)R1 Fitting – NSTA 188 to NSTA314118,750(7)54-51-I02u Pylon R1/Web Interface (GE)R1 Fitting – NSTA 188 to NSTA314118,750(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-54777 MAINTENANCE PLANNING DATA54-51-I02v Pylon R1/Web Interface (GE)R1 Fitting – NSTA 188 to NSTA314118,750(7)54-51-I02w Pylon R1/Web Interface (GE)R1 Fitting – NSTA 188 to NSTA314118,750(7)54-51-I02r Upper Spar Assembly (GE)Upper Spar Common toFrames/Bulkheads128,600(7)28,600(7)54-51-I02r Upper Spar Assembly (GE)Upper Spar Common toFrames/Bulkheads118,750(7)54-51-I02s Upper Spar Assembly (Bay 4) (GE) NSTA 245 to NSTA 264.61<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I02s Upper Spar Assembly (Bay 4) (GE) NSTA 245 to NSTA 264.61> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I02s Upper Spar Assembly (Bay 4) (GE) NSTA 245 to NSTA 265118,750(7)54-51-I03a Side Skin Cutout, Bay 8 (GE)Cutout at Bay 81<= 7 Hrs,FLS, SeeFigure 254-51-I03b Side Skin Cutout, Bay 8 (GE)NSTA 310 to NSTA 3251<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I03b Side Skin Cutout, Bay 8 (GE)Cutout at Bay 81<= 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5554-51-I03b Side Skin Cutout, Bay 8 (GE)Cutout at Bay 81> 7 Hrs,FLS, SeeFigure 2(7)54-51-I03c Side Skin Cutout, Bay 8 (GE)NSTA 310 to NSTA 3251> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I03C Side Skin Cutout, Bay 8 (GE)Cutout at Bay 81> 7 Hrs,FLS, SeeFigure 2(7)54-51-I03e Pylon Side Skin (GE)Side Skin Between NSTA 267and NSTA 278118,750(7)54-51-I03v Pylon Side Skin (GE)Side Skin Between NSTA 267and NSTA 278118,750(7)54-51-I03g Strut Side Skin Bay 4 (GE)NSTA 245 to NSTA 264.61<= 7 Hrs,FLS, SeeFigure 1<= 7 Hrs,FLS, SeeFigure 154-51-I03g Strut Side Skin Bay 4 (GE)NSTA 245 to NSTA 264.61> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I03g Pylon Side Skin (GE)Side Skin Between NSTA 247and NSTA 263118,750(7)54-51-I03w Pylon Chord (GE)Upper Spar Chord BetweenNSTA 247 and NSTA 263118,750(7)54-51-I03x Pylon Side Skin (GE)Side Skin Between NSTA 247and NSTA 263118,750(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-56777 MAINTENANCE PLANNING DATA54-51-I03i Side Skin Cutout (Bay 3) (GE)NSTA 230 to 2451<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I03i Side Skin Cutout (Bay 3) (GE)NSTA 230 to 2451> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I03I GE90-115B Side Skin Cutout (Bay3) (GE)NSTA 230 to NSTA 245118,750(7)54-51-I03j Side Skin Cutout (Bay 2) (GE)NSTA 213.5 to NSTA 2301<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I03j Side Skin Cutout (Bay 2) (GE)NSTA 213.5 to NSTA 2301> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I03j Side Skin Cutout Bay 2 (GE)NSTA 213.5 to NSTA 230.0,Skin and Upper Spar Chord1<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I03j Side Skin Cutout Bay 2 (GE)NSTA 213.5 to NSTA 230.0,Skin and Upper Spar Chord1> 7 Hrs,FLS, SeeFigure 2(7)54-51-I03k Side Skin Cutout (Bay 2)(GE)NSTA 213.5 to NSTA 2301<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5754-51-I03k Side Skin Cutout Bay 2 (GE)NSTA 213.5 to NSTA 230.0,Skin and Upper Spar Chord1<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I03k Side Skin Cutout Bay 2 (GE)NSTA 213.5 to NSTA 230.0,Skin and Upper Spar Chord1> 7 Hrs,FLS, SeeFigure 2(7)54-51-I03s Strut LH Side Skin Bay 4 (GE)NSTA 245 to NSTA 264.6, LHS 1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I03s Strut LH Side Skin Bay 4 (GE)NSTA 245 to NSTA 264.6, LHS 1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I03s Bay 4 Upper Spar (GE)LHS NSTA 245 to NSTA 264118,750(7)54-51-I04a Strut Lower Chord (GE)Bays 2 and 3 RH Chord/Web,NSTA at 213-2451<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I04a Strut Lower Chord (GE)Bays 2 and 3 RH Chord/Web,NSTA at 213-2451> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I04a Lower Spar Bay 3 (GE)Lower Spar Between NSTA 230and 2451<= 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-58777 MAINTENANCE PLANNING DATA54-51-I04a Lower Spar Bay 3 (GE)Lower Spar Between NSTA 230and 2451> 7 Hrs,FLS, SeeFigure 2(7)54-51-I04b Strut Lower Chord Bay 3 (GE)LH Chord Between NSTA 230and 2451> 7 Hrs,FLS, SeeFigure 1> 7 Hrs,FLS, SeeFigure 154-51-I04b Strut Lower Chord Bay 3 (GE)LH Chord Between NSTA 230and NSTA 2451<= 7 Hrs,FLS, SeeFigure 254-51-I04b Strut Lower Chord Bay 3 (GE)LH Chord Between NSTA 230and NSTA 2451> 7 Hrs,FLS, SeeFigure 254-51-I04c Strut Lower Spar (GE)Bay 3 Lower Spar Web Cutout1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I04c Strut Lower Spar (GE)Bay 3 Lower Spar Web Cutout1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I04d Strut Lower Spar (GE)Bays 5, 6 and 7 LH Chord/Web,NSTA 264-3091> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I04d Pylon Lower Spar (GE)LH Chord/Skin/Web JointBetween NSTA 266 and NSTA278.51 FLS,SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5954-51-I04s Pylon Side Skin (GE)LH Chord/Skin/Web JointBetween NSTA 266 and NSTA278.51<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I04s Pylon Side Skin (GE)LH Chord/Skin/Web JointBetween NSTA 266 and NSTA278.51> 7 Hrs,FLS, SeeFigure 2(7)54-51-I04e Pylon Lower Spar (GE)RH Chord/Skin/Web JointBetween NSTA 266 and NSTA278.51<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I04e Pylon Lower Spar (GE)RH Chord/Skin/Web JointBetween NSTA 266 and NSTA278.51> 7 Hrs,FLS, SeeFigure 2(7)54-51-I04t Pylon Side Skin (GE)RH Chord/Skin/Web JointBetween NSTA 266 and NSTA278.51<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I04t Pylon Side Skin (GE)RH Chord/Skin/Web JointBetween NSTA 266 and NSTA278.51> 7 Hrs,FLS, SeeFigure 2(7)54-51-I04f Pylon Lower Spar (GE)Bay5 Lwr Spar Web Cutout1<= 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-60777 MAINTENANCE PLANNING DATA54-51-I04f Pylon Lower Spar (GE)Bay5 Lwr Spar Web Cutout1> 7 Hrs,FLS, SeeFigure 2(7)54-51-I04g Strut Lower Spar (GE)Chord at Aft Engine MountBulkhead NSTA 303 to NSTA317130,000(7)30,000(7)18,750(7)54-51-I04h RHS Lower Spar Chord-Web-SkinJoint (GE)Bay 2, STA 213 to STA 2301<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I04h RHS Lower Spar Chord-Web-SkinJoint (GE)Bay 2, STA 213 to STA 2301> 7 Hrs,FLS, SeeFigure 2(7)54-51-I04j Strut Lower Spar (GE)Bays 2 and 3 LH ChordNSTA 213-2451<= 7 Hrs,FLS, SeeFigure 1<= 7 Hrs,FLS, SeeFigure 154-51-I04j Strut Lower Spar (GE)Bays 2 and 3 LH ChordNSTA 213-2451> 7 Hrs,FLS, SeeFigure 1> 7 Hrs,FLS, SeeFigure 154-51-I04j LHS Lower Spar Chord-web-skinJoint (GE)Bay 21<= 7 Hrs,FLS, SeeFigure 254-51-I04j LHS Lower Spar Chord-web-skinJoint (GE)Bay 21> 7 Hrs,FLS, SeeFigure 254-51-I04l Strut Lower Spar Bay 4 (GE)NSTA 245 to NSTA 264LHSand RHS Lower Spar130,000(7)30,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6154-51-I04l Lower Spar Bay 4 (GE)NSTA 245 to NSTA 264LHSand RHS Lower Spar1<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I04l Lower Spar Bay 4 (GE)NSTA 245 to NSTA 264LHSand RHS Lower Spar1> 7 Hrs,FLS, SeeFigure 2(7)54-51-I04u Lower Spar Bay 4 (GE)NSTA 245 to NSTA 264LHSand RHS Lower Spar1<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I04u Lower Spar Bay 4 (GE)NSTA 245 to NSTA 264LHSand RHS Lower Spar1> 7 Hrs,FLS, SeeFigure 2(7)54-51-I04m Strut Lower Spar (GE)Chord STA at Bulkhead1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I04m Strut Lower Spar (GE)Chord STA at Bulkhead1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 2(7)54-51-I04r Strut Lower Spar (GE)Bays 5,6, and 7 NSTA 264-309 1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-62777 MAINTENANCE PLANNING DATA54-51-I04r Lower Spar Chords/Web Bays 6-7(GE)Lower Spar Chord JointBetween NSTA 280 and NSTA3081 <= 7 Hrs,FLS, SeeFigure 2(7)54-51-I04r Lower Spar Chords/Web Bays 6-7(GE)Lower Spar Chord JointBetween NSTA 280 and NSTA3081 > 7 Hrs,FLS, SeeFigure 2(7)54-51-I05a Strut Fwd Engine Mount Bulkhead(GE)Gusset Edge130,000(7)30,000(7)54-51-I05a Strut Fwd Engine Mount Bulkhead(GE)Gusset Upper Edge118,750(7)54-51-I05b Strut Fwd Engine Mount Bulkhead(GE)Tension Fitting130,000(7)30,000(7)54-51-I05b Fwd Engine Mount Bulkhead (GE) Tension Fitting118,75054-51-I06a Strut Mid Bulkhead STA 295 (GE) Flange1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I06a Strut Mid Bulkhead STA 295 (GE) Flange1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 2(7)54-51-I06b Strut Mid Bulkhead STA 295 (GE) R1 Attachment Pad @ BoltHole130,000(7)30,000(7)18,750(7)54-51-I07a Strut Aft Engine Mount Bulkhead(GE)R1 Fitting Attachment130,000(7)30,000(7)54-51-I07a Aft Engine Mount Bulkhead (GE) R1 Fitting Fastener Attachment118,750(7)54-51-I07b Aft Engine Mount Bulkhead (GE) Engine Mount Tension Fitting118,750AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6354-51-I07d Strut Aft Engine Mount Bulkhead(GE)Cutout Flange 1 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I07d Strut Aft Engine Mount Bulkhead(GE)Cutout Flange1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I07d Strut Aft Engine Mount Bulkhead(GE)Cutout Flange118,750(7)54-51-I08b Aft Strut Bulkhead (GE)Aft Bulkhead from NWL 147 toNWL 1621<= 7 Hrs,FLS, SeeFigure 2(7)54-51-I08b Aft Strut Bulkhead (GE)Aft Bulkhead from NWL 147 toNWL 1621> 7 Hrs,FLS, SeeFigure 2(7)54-51-I08d Aft Strut Bulkhead (GE)Forward Upper Flange NSTA325.331<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I08d Aft Strut Bulkhead (GE)Forward Upper Flange NSTA325.331> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)54-51-I08d Aft Strut Bulkhead (GE)Forward Upper Flange NSTA325.33118,750(7)54-51-I02A Upper Spar Chord (RR)Upper Spar Chord Splice Plateat NSTA 313 to NSTA 3231 30,000(7)30,000(7)30,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-64777 MAINTENANCE PLANNING DATA54-51-I02C Forward Upper Spar(RR) Upper Spar at Frame/Bulkheads1 30,000(7)30,000(7)30,000(7)54-51-I02D Forward Upper Spar (RR) Fasteners Common to theUpper Chord and Web, NSTA223 toNSTA 294, non-frame locations1 30,000(7)30,000(7)30,000(7)54-51-I04A Lower Chord (RR) Lower Chord, Web at AftEngine Mount Attachment BoltHoles atNSTA 307.7, 309.9, 313.3, and315.51 30,000(7)30,000(7)30,000(7)54-51-I04B Aft Lower Chord at Aft EngineMount Bulkhead (RR)Fasteners Common to Chordand Web under Engine MountFitting, NSTA 305 to NSTA 3171 30,000(7)30,000(7)54-51-I04B Aft Lower Spar Chord Under EngineMount Bulkhead (RR)Fasteners Common to Chordand Web under Engine MountFitting, NSTA 305 to NSTA 3171 30,000(7)54-51-I05A Forward Engine Mount Bulkhead(RR)Fwd Engine Mount BulkheadTension Fitting End Pad1 30,000(7)30,000(7)54-51-I05A Forward Engine Mount Bulkhead(RR)Fwd Engine Mount BulkheadTension Fitting End Pad1 30,000(7)54-51-I06A Aft Engine Mount Bulkhead(RR) R1 Fitting Attach TensionFitting1 30,000(7)54-51-I06A Aft Engine Mount Bulkhead(RR) R1 Fitting Attach TensionFitting1 30,000(7)54-51-I06A Aft Engine Mount Bulkhead(RR) Upper Tension (Bathtub) FittingEnd Pad1 30,000(7)54-51-I07B Strut Aft Bulkhead (RR) AtFastener Common to the AftUpper Spar Fitting WL 148.26to WL 159.291 30,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6554-51-I07A,B Aluminum Aft Strut Bulkhead (RR) At Fasteners Common to theAft Upper Spar from WL 148.26to WL 159.29 and the TwoUppermost Fasteners Commonto the R2 Fitting130,000(7)54-51-I07A,B Aluminum Aft Strut Bulkhead(RR) At Fastener Common to the AftUpper Spar from WL 148.26 toWL 159.29 and the TwoUppermost Fasteners Commonto the R2 Fitting130,000(7)54-51-I07C Aluminum Aft Strut Bulkhead (RR) Forward Upper Flange NSTA344.001<= 7 Hrs,FLS, SeeFigure 1(7)54-51-I07C Aluminum Aft Strut Bulkhead (RR) Forward Upper Flange NSTA344.001> 7 Hrs,FLS, SeeFigure 1(7)54-51-I07C Aluminum Aft Strut Bulkhead (RR) Forward Upper Flange NSTA344.00130,000(7)55-12-I03 Upper Double Plus ChordHorizontal StabilizerBL 0.0 Skin/Stringer Splice1 30,000(8)30,000(7)30,000(7)55-12-I03 Upper Double Plus ChordHorizontal StabilizerBL 0.0 Skin/Stringer Splice130,000(7)30,000(7)55-12-I03 Upper Double Plus ChordHorizontal StabilizerBL 0.0 Skin/Stringer Splice118,750(7)55-12-I07 Splice Fitting – F/S Upper ChordHorizontal StabilizerInboard Jackscrew AttachFastenerat BL 4.21 30,000(8)30,000(7)30,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-66777 MAINTENANCE PLANNING DATA55-12-I07 Splice Fitting – F/S Upper ChordHorizontal StabilizerInboard Jackscrew AttachFastenerat BL 4.21 30,000(7)30,000(7)55-12-I07 Splice Fitting – F/S Upper ChordHorizontal StabilizerInboard Jackscrew AttachFastenerat BL 4.21 18,750(7)55-17-I03A Pivot Fitting Lugs BL +/- 42 and Pivot Hinge Line 1 30,000(8)55-17-I03A Pivot Fitting Lugs BL +/- 42 and Pivot Hinge Line 1 30,000(7)55-17-I03A Pivot Fitting Lugs BL +/- 42 and Pivot Hinge Line 1 30,000(7)55-17-I03A Pivot Fitting Lugs BL +/- 42 and Pivot Hinge Line 1 30,000(7)30,000(7)55-17-I03A Pivot Fitting Lugs BL +/- 42 and Pivot Hinge Line 1 18,750(7)55-17-I03B Pivot FittingStraps (Both Pairs –Upper and Lower)BL +/- 42, WL 246 and 263, BS23651 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)55-17-I03B Pivot Fitting Straps LowerStrap BL +/- 42, WL 255, BS 2365 1 18,750(7)55-17-I03C Pivot Fitting Pins Outer Pin BL 42 and Pivot Hinge Line 1 30,000(8)55-17-I03C Pivot Fitting Pins Outer Pin BL 42 and Pivot Hinge Line 1 30,000(7)55-17-I03C Pivot Fitting Pins Outer Pin BL 42 and Pivot Hinge Line 1 30,000(7)55-17-I03C Pivot Fitting Pins Outer Pin BL 42 and Pivot Hinge Line 1 30,000(7)30,000(7)55-17-I03C Pivot Fitting Pins Outer Pin BL 42 and Pivot Hinge Line 1 18,750(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6755-18-I01 Jackscrew Fitting, Lugs Dwg.182W7402Back-to-Back Lugs BL +/- 5.0WL 256.321 30,000(8)55-18-I01 Jackscrew Fitting, Lugs Dwg.182W7402Back-to-Back Lugs BL +/- 5.0WL 256.321 30,000(7)55-18-I01 Jackscrew Fitting, Lugs Dwg.182W7402Back-to-Back Lugs BL +/- 5.0WL 256.321 30,000(7)55-18-I01 Jackscrew Fitting, Lugs Dwg.182W7402Back-to-Back Lugs BL +/- 5.0WL 256.321 30,000(7)30,000(7)55-18-I01 Jackscrew Fitting, Lugs Dwg.182W7402Back-to-Back Lugs BL +/- 5.0WL 256.321 18,750(7)55-27-I03 Elevator Actuator Fitting183W1312,L/N 718 and on, and all retrofittedairplanesUpper Middle Flange 1 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)57-10-I02A SOB Splice, Lower Surface, TChordINBD and OBD Flanges of T-Chord1 30,000(8)30,000(7)57-10-I02A SOB Splice, Lower Surface, TChordINBD and OBD Flanges of T-Chord1 30,000(7)57-10-I02A SOB Splice, Lower Surface, TChordINBD and OBD Flanges of T-Chord1 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-10-I02A SOB Splice, Lower Surface, TChordINBD and OBD Flanges of T-Chord1 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-10-I02A Side of Body Splice, LowerSurface Inboard and outboard flanges oftheT-Chord at Stringer L-11 <= 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-68777 MAINTENANCE PLANNING DATA57-10-I02A Side of Body Splice, LowerSurface Inboard and outboard flanges oftheT-Chord at Stringer L-11 > 7 Hrs,FLS, SeeFigure 2(7)57-10-I02B SOB Splice, Lower Surface, TChordAll Fasteners locations notcovered by splice plate1 30,000(8)30,000(7)57-10-I02B SOB Splice, Lower Surface, TChordAll Fasteners locations notcovered by splice plate1 30,000(7)57-10-I02B SOB Splice, Lower Surface, TChordAll Fasteners locations notcovered by splice plate1 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-10-I02B SOB Splice, Lower Surface, TChordAll Fasteners locations notcovered by splice plate1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-10-I02B Side of Body Splice, Lower Surface Inspect at all fastener locationsnot covered by the splice plate1<= 7 Hrs,FLS, SeeFigure 2(7)57-10-I02B Side of Body Splice, Lower Surface Inspect at all fastener locationsnot covered by the splice plate1> 7 Hrs,FLS, SeeFigure 2(7)57-10-I02C SOB Splice,Lower Surface, TChordINBD and OBD Flanges of T-chord @ Splice Plate (Str L1,L10,L14,L-20 and L-23)1 30,000(8)30,000(7)57-10-I02C SOB Splice,Lower Surface, TChordINBD and OBD Flanges of T-chord @ Splice Plate (Str L1,L10,L14,L-20 and L-23)130,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6957-10-I02C SOB Splice,Lower Surface, TChordINBD and OBD Flanges of T-chord @ Splice Plate (Str L1,L10,L14,L-20 and L-23)1 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-10-I02C SOB Splice,Lower Surface, TChordINBD and OBD Flanges of T-chord @ Splice Plate (Str L1,L10,L14,L-20 and L-23)1 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-10-I02C Side of Body Splice, Lower Surface Inboard and Outboard flangesofT-chord at splice plate locations(Str L1,L-10,L14,L-20 and L-23)1<= 7 Hrs,FLS, SeeFigure 2(7)57-10-I02C Side of Body Splice, Lower Surface Inboard and Outboard flangesofT-chord at splice plate locations(Str L1,L-10,L14,L-20 and L-23)1> 7 Hrs,FLS, SeeFigure 2(7)57-10-I03A SOB Splice, Front Spar,ChordUpper and Lower Front SparChords (INBD and OBD of SOBrib)1 30,000(8)<= 7 Hrs,FLS, SeeFigure 1(7)57-10-I03A SOB Splice, Front Spar,ChordUpper and Lower Front SparChords (INBD and OBD of SOBrib)1> 7 Hrs,FLS, SeeFigure 1(7)57-10-I03A SOB Splice, Front Spar,ChordUpper and Lower Front SparChords (INBD and OBD of SOBrib)130,000(7)57-10-I03A SOB Splice, Front Spar,ChordUpper and Lower Front SparChords (INBD and OBD of SOBrib)1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-70777 MAINTENANCE PLANNING DATA57-10-I03A SOB Splice, Front Spar,Chord Upper and Lower Front SparChords (INBD and OBD of SOBrib)1 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-10-I03A Side of Body Splice, FrontSpar Chords, Front Spar Lower andUpper Chords (Inboard andOutboard of SOB rib)1 <= 7 Hrs,FLS, SeeFigure 2(7)57-10-I03A Side of Body Splice, Front Spar,ChordChords, Front Spar Lower andUpper Chords (Inboard andOutboard of SOB rib)1> 7 Hrs,FLS, SeeFigure 2(7)57-10-I03B Side of Body Splice, Front Spar Skin, Front Spar Lower andUpper Chords (Inboard andOutboard of SOB rib)1<= 7 Hrs,FLS, SeeFigure 2(7)57-10-I03B Side of Body Splice, Front Spar Skin, Front Spar Lower andUpper Chords (Inboard andOutboard of SOB rib)1> 7 Hrs,FLS, SeeFigure 2(7)57-10-I04A SOB Splice, Rear Spar,ChordUpper and Lower Rear SparChords (INBD and OBD of SOBrib)1 30,000(8)<= 7 Hrs,FLS, SeeFigure 1(7)57-10-I04A SOB Splice, Rear Spar,ChordUpper and Lower Rear SparChords (INBD and OBD of SOBrib)1> 7 Hrs,FLS, SeeFigure 1(7)57-10-I04A SOB Splice, Rear Spar,ChordUpper and Lower Rear SparChords (INBD and OBD of SOBrib)130,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7157-10-I04A SOB Splice, Rear Spar,Chord Upper and Lower Rear SparChords (INBD and OBD of SOBrib)1 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-10-I04A SOB Splice, Rear Spar,ChordUpper and Lower Rear SparChords (INBD and OBD of SOBrib)1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-10-I04A Side of Body Splice, RearSpar Chords, Rear Spar Lower andUpper Chords (Inboard andOutboard of SOB rib)1<= 7 Hrs,FLS, SeeFigure 2(7)57-10-I04A Side of Body Splice, RearSpar Chords, Rear Spar Lower andUpper Chords (Inboard andOutboard of SOB rib)1> 7 Hrs,FLS, SeeFigure 2(7)57-10-I04B Side of Body Splice, Rear Spar Skin, Rear Spar Lower andUpper Chords (Inboard andOutboard of SOB rib)1<= 7 Hrs,FLS, SeeFigure 2(7)57-10-I04B Side of Body Splice, Rear Spar Skin, Rear Spar Lower andUpper Chords (Inboard andOutboard of SOB rib)1> 7 Hrs,FLS, SeeFigure 2(7)57-12-I02-1 Body Chord Inspection at Stringer36 to 41Front Spar Bulkhead, Station1035, Stringer 36 to 411 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)57-12-I02-2 Body Chord Inspection at SplicePlateFront Spar Bulkhead, Station1035 Stringer 38 to 391 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)18,750(7)57-15-I01A Wing Center Section (WCS), LowerPanel Typical StringerTypical stringer on Lower Panel(WCS from SOB to SOB)2 40,000 40,000AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-72777 MAINTENANCE PLANNING DATA57-15-I01A Wing Center Section (WCS), LowerPanel Typical StringerTypical stringer on Lower Panel(WCS from SOB to SOB)2 40,00057-15-I01A Wing Center Section (WCS), LowerPanel Typical StringerTypical stringer on Lower Panel(WCS from SOB to SOB)2 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-15-I01A Wing Center Section (WCS), LowerPanel Typical StringerTypical stringer on Lower Panel(WCS from SOB to SOB)2 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-15-I01A Wing Center Section – Lower Panel– Typical StringerAll WCS Lower Panel TypicalStringers from SOB to SOB2 <= 7 Hrs,FLS, SeeFigure 2(7)57-15-I01A Wing Center Section – Lower Panel– Typical StringerAll WCS Lower Panel TypicalStringers from SOB to SOB2 > 7 hrsFLS, SeeFigure 257-15-I01B Wing Center Section (WCS), LowerPanel Splice StringerSplice stringer on Lower Panel(WCS @ L10,L14, L20 fromSOB to SOB)2 40,000 40,000 40,00057-15-I01B Wing Center Section (WCS), LowerPanel Splice StringerSplice stringer on Lower Panel(WCS @ L10,L14, L20 fromSOB to SOB)2 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-15-I01B Wing Center Section – Lower Panel– Splice StringerAll WCS Lower Panel SpliceStringers2 <= 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7357-15-I01B Wing Center Section – Lower Panel– Splice StringerAll WCS Lower Panel SpliceStringers2 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 2(7)57-15-I01C Wing Center Section (WCS), LowerRear Spar Chord, Lower ChordRear Spar Lower Chord(WCS from SOB to SOB)2 40,00057-15-I01C Wing Center Section (WCS), LowerRear Spar Chord, Lower ChordRear Spar Lower Chord(WCS from SOB to SOB)2 <= 7 Hrs,FLS, SeeFigure 1(7)57-15-I01C Wing Center Section (WCS), LowerRear Spar Chord, Lower ChordRear Spar Lower Chord(WCS from SOB to SOB)2 > 7 hrsFLS, SeeFigure 1(7)57-15-I01C Wing Center Section (WCS), LowerRear Spar Chord, Lower ChordRear Spar Lower Chord(WCS from SOB to SOB)2 40,000(7)57-15-I01C Wing Center Section (WCS), LowerRear Spar Chord, Lower ChordRear Spar Lower Chord(WCS from SOB to SOB)2 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-15-I01C Wing Center Section (WCS), LowerRear Spar Chord, Lower ChordRear Spar Lower Chord(WCS from SOB to SOB)2 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-15-I01C Wing Center Section – Lower PanelRear Spar Lower ChordChord, WCS Lower Panel RearSpar Chord from SOB to SOB2 <= 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-74777 MAINTENANCE PLANNING DATA57-15-I01C Wing Center Section – Lower PanelRear Spar Lower ChordChord, WCS Lower Panel RearSpar Chord from SOB to SOB2 > 7 Hrs,FLS, SeeFigure 2(7)57-15-I01D Wing Center Section (WCS), LowerRear Spar Chord, Lower SkinRear Spar Lower Chord(WCS from SOB to SOB)2 40,00057-15-I01D Wing Center Section (WCS), LowerRear Spar Chord, Lower SkinRear Spar Lower Chord(WCS from SOB to SOB)2 <= 7 Hrs,FLS, SeeFigure 157-15-I01D Wing Center Section (WCS), LowerRear Spar Chord, Lower SkinRear Spar Lower Chord(WCS from SOB to SOB)2 > 7 hrsFLS, SeeFigure 157-15-I01D Wing Center Section (WCS), LowerRear Spar Chord, Lower SkinRear Spar Lower Chord(WCS from SOB to SOB)240,000(7)57-15-I01D Wing Center Section (WCS), LowerRear Spar Chord, Lower SkinRear Spar Lower Chord(WCS from SOB to SOB)2<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-15-I01D Wing Center Section (WCS), LowerRear Spar Chord, Lower SkinRear Spar Lower Chord(WCS from SOB to SOB)2> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-15-I01D Wing Center Section – Lower PanelRear Spar Lower ChordSkin, WCS Lower Panel RearSpar Chord from SOB to SOB2<= 7 Hrs,FLS, SeeFigure 2(7)57-15-I01D Wing Center Section – Lower PanelRear Spar Lower ChordSkin, WCS Lower Panel RearSpar Chord from SOB to SOB2> 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7557-15-I01E Wing Center Section (WCS), LowerPanel Keel Beam Chord, LowerSkinLower Skin at Rear Spar Chord/Keel Attachment (LBL 15 toRBL 15)1 30,00057-15-I01E Wing Center Section (WCS), LowerPanel Keel Beam Chord, LowerSkinLower Skin at Rear Spar Chord/Keel Attachment (LBL 15 toRBL 15)1 <= 7 Hrs,FLS, SeeFigure 1(7)57-15-I01E Wing Center Section (WCS), LowerPanel Keel Beam Chord, LowerSkinLower Skin at Rear Spar Chord/Keel Attachment (LBL 15 toRBL 15)1> 7 Hrs,FLS, SeeFigure 1(7)57-15-I01E Wing Center Section (WCS), LowerPanel Keel Beam Chord, LowerSkinLower Skin at Rear Spar Chord/Keel Attachment (LBL 15 toRBL 15)130,000(7)57-15-I01E Wing Center Section (WCS), LowerPanel Keel Beam Chord, LowerSkinLower Skin at Rear Spar Chord/Keel Attachment (LBL 15 toRBL 15)1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-15-I01E Wing Center Section (WCS), LowerPanel Keel Beam Chord, LowerSkinLower Skin at Rear Spar Chord/Keel Attachment (LBL 15 toRBL 15)1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-15-I01E Wing Center Section Lower Panel –Keel Beam Chord AttachmentSkin, WCS Lower Panel KeelBeam Chord Attachment at theRear Spar Chord1<= 7 Hrs,FLS, SeeFigure 2(7)57-15-I01E Wing Center Section Lower Panel –Keel Beam Chord AttachmentSkin, WCS Lower Panel KeelBeam Chord Attachment at theRear Spar Chord1> 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-76777 MAINTENANCE PLANNING DATA57-15-I01F Wing Center Section (WCS), LowerPanel Keel Beam Chord, LowerChordRear Spar Chord at KeelAttachment (LBL 15 to RBL 15)2 40,000(7)40,000(7)57-15-I01F Wing CenterSection, Lower Panel– Keel Beam Chord, Lower ChordRear Spar Chord at KeelAttachment (LBL 15 to RBL 15)2 40,000(7)57-15-I01F Wing CenterSection, Lower Panel– Keel Beam Chord, Lower ChordRear Spar Chord at KeelAttachment (LBL 15 to RBL 15)2 40,000 40,00057-15-I01F Wing Center Section Lower Panel –Keel Beam Chord AttachmentChord, WCS Lower Panel KeelBeam Chord Attachment at theRear Spar Chord2 <= 7 Hrs,FLS, SeeFigure 2(7)57-15-I01F Wing Center Section Lower Panel –Keel Beam Chord AttachmentChord, WCS Lower Panel KeelBeam Chord Attachment at theRear Spar Chord2 > 7 hrsFLS, SeeFigure 257-15-I01G Wing Center Section (WCS) LowerFront Spar Chord Lower ChordFront Spar Lower Chord (WCSfrom BL 67 to BL103)2 40,000 40,000 40,000 40,000 40,00057-20-I01A Wing Outboard, Typical Rear SparAttachment, Lower ChordRear Spar Attachment fromSOB to Rib 12 (Mid Rib)2 40,000(8)<=7hrsFLS SeeFigure 1(7)57-20-I01A Wing Outboard, Typical Rear SparAttachment, Lower ChordRear Spar Attachment fromSOB to Rib 12 (Mid Rib)2 >7hrsFLS SeeFigure 1(7)57-20-I01A Wing Outboard, Typical Rear SparAttachment, Lower ChordRear Spar Attachment fromSOB to Rib 12 (Mid Rib)2 40,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7757-20-I01A Wing Outboard, Typical Rear SparAttachment, Lower ChordRear Spar Attachment fromSOB to Rib 15 (Mid Rib)2 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01A Wing Outboard, Typical Rear SparAttachment, Lower ChordRear Spar Attachment fromSOB to Rib 15 (Mid Rib)2> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01A Wing Outboard – Lower Panel RearSpar Lower ChordChord, O/B Wing Lower PanelRear Spar Chord from SOB toRib 15 except at Ribpostlocations2<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01A Wing Outboard – Lower Panel RearSpar Lower ChordChord, O/B Wing Lower PanelRear Spar Chord from SOB toRib 15 except at Ribpostlocations2> 7 Hrs,FLS, SeeFigure 2(7)57-20-I01B Wing Outboard, Typical Rear SparAttachment, Lower ChordRear Spar Chord Attachmentfrom Rib 15 to Wingtip (Mid Rib)2<= 7 Hrs,FLS, SeeFigure 1<= 7 Hrs,FLS, SeeFigure 157-20-I01B Wing Outboard, Typical Rear SparAttachment, Lower ChordRear Spar Chord Attachmentfrom Rib 15 to Wingtip (Mid Rib)2> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01B Wing Outboard – Lower Panel RearSpar Lower ChordChord, O/B Wing Lower PanelRear Spar Chord from SOB toRib 15 except at Ribpostlocations2<= 7 Hrs,FLS, SeeFigure 257-20-I01B Wing Outboard – Lower Panel RearSpar Lower ChordChord, O/B Wing Lower PanelRear Spar Chord from SOB toRib 15 except at Ribpostlocations2> 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-78777 MAINTENANCE PLANNING DATA57-20-I01C Wing Outboard, Typical Rear SparAttachment, Lower SkinRear Spar Chord Attachmentat Trailing Edge fairinglocations2 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01C Wing Outboard, Typical Rear SparAttachment, Lower SkinRear Spar Chord Attachmentat Trailing Edge fairinglocations2 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01C Wing Outboard – Lower Panel RearSpar Lower ChordSkin, O/B Wing Lower PanelRear Spar Chord at the trailingedge fairing locations2<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01C Wing Outboard – Lower Panel RearSpar Lower ChordSkin, O/B Wing Lower PanelRear Spar Chord at the trailingedge fairing locations2> 7 Hrs,FLS, SeeFigure 2(7)57-20-I01D Wing Outboard, Typical SpliceStringerStringer L10-L14 from SOB toRib 36, L20 From Rib 8 to Rib182 40,000(7)57-20-I01D Wing Outboard, Typical SpliceStringerStringer L10-L14 from SOB toRib 36, L20 From Rib 8 to Rib182<= 7 Hrs,FLS, SeeFigure 157-20-I01D Wing Outboard, Typical SpliceStringerStringer L10-L14 from SOB toRib 36, L20 From Rib 8 to Rib182> 7 hrsFLS, SeeFigure 157-20-I01D Wing Outboard, Typical SpliceStringerStringer L10-L14 from SOB toRib 36, L20 From Rib 8 to Rib18240,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7957-20-I01E Wing Outboard, Typical SpliceStringerStringer L10-L14 at NacelleFitting and Dry Bay Locations2 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01E Wing Outboard, Typical SpliceStringerStringer L10-L14 at NacelleFitting and Dry Bay Locations2> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01E Outboard Wing – Lower PanelSplice StringerO/B Wing Lower SpliceStringers at the nacelle fairingand dry bay locations2<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01E Outboard Wing – Lower PanelSplice StringerO/B Wing Lower SpliceStringers at the nacelle fairingand dry bay locations2> 7 Hrs,FLS, SeeFigure 2(7)57-20-I01F Wing Outboard, Typical SpliceStringerStringer L1 0- L14 at NacelleFitting, and L10 at Rib 30, 21and 122 40,000(7)57-20-I01F Wing Outboard, Typical SpliceStringerStringer L10 - L14 at NacelleFitting, and L10 at Rib 30, 21and 122<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01F Wing Outboard, Typical SpliceStringerStringer L10 - L14 at NacelleFitting, and L10 at Rib 30, 21and 122> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01G Wing Outboard, Lower Panel RearSpar Chord, Lower ChordRear Spar Chord Attachmentfrom SOB to Rib 12 at Rib Post1 30,000(8)<= 7 Hrs,FLS, SeeFigure 1(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-80777 MAINTENANCE PLANNING DATA57-20-I01G Wing Outboard, Lower Panel RearSpar Chord, Lower ChordRear Spar Chord Attachmentfrom SOB to Rib 12 at Rib Post1 > 7 Hrs,FLS, SeeFigure 1(7)57-20-I01G Wing Outboard, Lower Panel RearSpar Chord, Lower ChordRear Spar Chord Attachmentfrom SOB to Rib 12 at Rib Post130,000(7)57-20-I01G Wing Outboard, Lower Panel RearSpar Chord, Lower ChordRear Spar Chord Attachmentfrom SOB to Rib 15 at Rib Post1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01G Wing Outboard, Lower Panel RearSpar Chord, Lower ChordRear Spar Chord Attachmentfrom SOB to Rib 15 at Rib Post1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01G Wing Outboard, Lower Panel RearSpar Lower ChordO/B Wing Lower Panel RearSpar Chord from Rib 15 towingtip at all ribpost locations1<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01G Wing Outboard, Lower Panel RearSpar Lower ChordO/B Wing Lower Panel RearSpar Chord from Rib 15 towingtip at all ribpost locations1> 7 Hrs,FLS, SeeFigure 2(7)57-20-I01H Wing Outboard, Lower Panel RearSpar Chord, Lower ChordSkin and Rear Spar WebAttachment from Rib 15 toWingtip at Rib Post1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01H Wing Outboard, Lower Panel RearSpar Chord, Lower ChordSkin and Rear Spar WebAttachment from Rib 15 toWingtip at Rib Post1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8157-20-I01H Wing Outboard, Lower Panel FrontSpar Lower ChordO/B Wing Lower Panel FrontSpar Chord from Rib 15 towingtip at all ribpost locations1 18750<= 7 Hrs(7)57-20-I01H Wing Outboard, Lower Panel FrontSpar Lower ChordO/B Wing Lower Panel FrontSpar Chord from Rib 15 towingtip at all ribpost locations118750> 7 Hrs(7)57-20-I01J Wing Outboard, Lower Panel FrontSpar Chord, Lower ChordSkin to F/Spar ChordAttachment at Nacelle Fitting1 30,000(8)30,000(7)57-20-I01J Wing Outboard, Lower Panel FrontSpar Chord, Lower ChordSkin to F/Spar ChordAttachment at Nacelle Fitting130,000(7)57-20-I01J Wing Outboard, Lower Panel FrontSpar Chord, Lower ChordSkin to F/Spar ChordAttachment at Nacelle Fitting1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01J Wing Outboard, Lower Panel FrontSpar Chord, Lower ChordSkin to F/Spar ChordAttachment at Nacelle Fitting1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01J Wing Outboard, Lower Panel FrontSpar Lower ChordChord, O/B Wing Lower PanelFront Spar Chord at the nacellefitting attachment locations1<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01J Wing Outboard, Lower Panel FrontSpar Lower ChordChord, O/B Wing Lower PanelFront Spar Chord at the nacellefitting attachment locations1> 7 Hrs,FLS, SeeFigure 2(7)57-20-I01K Wing Outboard, Lower Panel FrontSpar Chord, Lower SkinSkin to F/Spar ChordAttachment at Nacelle Fitting1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-82777 MAINTENANCE PLANNING DATA57-20-I01K Wing Outboard, Lower Panel FrontSpar Chord, Lower SkinSkin to F/Spar ChordAttachment at Nacelle Fitting1 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01K Wing Outboard, Lower Panel FrontSpar Lower ChordSkin, O/B Wing Lower PanelFront Spar Chord at the nacellefitting attachment locations1 <= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01K Wing Outboard, Lower Panel FrontSpar Lower ChordSkin, O/B Wing Lower PanelFront Spar Chord at the nacellefitting attachment locations1> 7 Hrs,FLS, SeeFigure 2(7)57-20-I01L1 Wing Outboard, Lower Panel FrontSpar Chord, Lower ChordSkin to F/Spar ChordAttachment from SOB toWingtip except between Rib 30to 44 and at Nacelle Fitting andRib Post2<= 7 Hrs,FLS, SeeFigure 1<= 7 Hrs,FLS, SeeFigure 157-20-I01L2 Wing Outboard, Lower Panel FrontSpar Chord, Lower ChordSkin to F/Spar ChordAttachment from Rib 30 to Rib44, except at Rib Post2<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01L Wing Outboard, Lower Panel FrontSpar Chord, Lower ChordSkin to F/Spar ChordAttachment from SOB toWingtip except at NacelleFitting Attachment and Rib Post2> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01L Wing Outboard, Lower Panel FrontSpar Lower ChordChord, O/B Wing Lower PanelFront Spar Chord from SOB toWingtip except at ribpostlocations2<= 7 Hrs,FLS, SeeFigure 2AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8357-20-I01L Wing Outboard, Lower Panel FrontSpar Lower ChordChord, O/B Wing Lower PanelFront Spar Chord from SOB toWingtip except at ribpostlocations2> 7 Hrs,FLS, SeeFigure 2(7)57-20-I01M Wing Outboard, Lower Panel FrontSpar Chord, Lower ChordSkin to F/Spar ChordAttachment from SOB toWingtip at all Rib Post1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01M Wing Outboard, Lower Panel FrontSpar Chord, Lower ChordSkin to F/Spar ChordAttachment from SOB toWingtip at all Rib Post1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01M Wing Outboard, Lower Panel FrontSpar Lower ChordChord, O/B Wing Lower PanelFront Spar Chord from SOB toWingtip at all ribpost locations1<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01M Wing Outboard, Lower Panel FrontSpar Lower ChordChord, O/B Wing Lower PanelFront Spar Chord from SOB toWingtip at all ribpost locations1> 7 Hrs,FLS, SeeFigure 2(7)57-20-I01N Wing Outboard, MLG BeamSupport Fitting, Mid Rib, Lower SkinWing Skin Tab-Out btwn Ribs11 and 12 at MLG BeamSupport Fitting2 40,000(8)40,000(7)57-20-I01N Wing Outboard, MLG BeamSupport Fitting, Mid Rib, Lower SkinWing Skin Tab-Out btwn Ribs11 and 12 at MLG BeamSupport Fitting240,000(7)57-20-I01N Wing Outboard, MLG BeamSupport Fitting, Mid Rib, Lower SkinWing Skin Tab-Out btwn Ribs11 and 12 at MLG BeamSupport Fitting2<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-84777 MAINTENANCE PLANNING DATA57-20-I01N Wing Outboard, MLG BeamSupport Fitting, Mid Rib, Lower SkinWing Skin Tab-Out btwn Ribs11 and 12 at MLG BeamSupport Fitting2 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01N Lower Panel – MLG BeamOutboard Support FittingAttachmentAll fastener locations commonto the O/B Wing Lower PanelSkin tab and the MLG BeamOutboard Support Fitting2<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01N Lower Panel – MLG BeamOutboard Support FittingAttachmentAll fastener locations commonto the O/B Wing Lower PanelSkin tab and the MLG BeamOutboard Support Fitting2> 7 Hrs,FLS, SeeFigure 2(7)57-20-I01P Wing Outboard, Typical StringerAttachment at Nacelle FTGTypical stringers at NacelleFitting locations2 40,000(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01P Wing Outboard, Typical StringerAttachment at Nacelle FTGTypical stringers at NacelleFitting locations2> 7 Hrs,FLS, SeeFigure 1(7)57-20-I01P Wing Outboard, Typical StringerAttachment at Nacelle FTGTypical stringers at NacelleFitting locations240,000(7)57-20-I01P Wing Outboard, Typical StringerAttachment at Nacelle FTGTypical stringers at NacelleFitting locations2<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01P Wing Outboard, Typical StringerAttachment at Nacelle FTGTypical stringers at NacelleFitting locations2> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8557-20-I01P Outboard Wing – Lower PanelTypical Skin-Stringer AttachmentO/B Wing Lower Panel TypicalStringers at Nacelle FairingLocation2 <= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01P Outboard Wing – Lower PanelTypical Skin-Stringer AttachmentO/B Wing Lower Panel TypicalStringers at Nacelle FairingLocation2 > 7 Hrs,FLS, SeeFigure 2(7)57-20-I01Q Wing Outboard, Typical RailStringer at Access DoorTypical Rail Stringers at Accessdoor from SOB to Wingtipexcept at Nacelle Fairing2 40,00057-20-I01Q Wing Outboard, Typical RailStringer at Access DoorTypical Rail Stringers at Accessdoor from SOB to Wingtipexcept at Nacelle Fairing2> 7 hrsFLS, SeeFigure 1> 7 hrsFLS, SeeFigure 157-20-I01Q Outboard Wing – Lower PanelTypical Attachment at Access Door/HoleStringer, O/B Wing Lower PanelRail Stringer from SOB toWingtip except at the nacellefairing2<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01Q Outboard Wing – Lower PanelTypical Attachment at Access Door/HoleStringer, O/B Wing Lower PanelRail Stringer from SOB toWingtip except at the nacellefairing2> 7 hrsFLS, SeeFigure 257-20-I01R Wing Outboard, Typical RailStringer at Access DoorTypical Rail Stringers at Accessdoor at Nacelle Fairing2<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I01R Wing Outboard, Typical RailStringer at Access DoorTypical Rail Stringers at Accessdoor at Nacelle Fairing2> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-86777 MAINTENANCE PLANNING DATA57-20-I01R Outboard Wing – Lower PanelTypical Attachment at Access Door/HoleStringer, O/B Wing Lower PanelRail Stringer at the NacelleFairing2 <= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01R Outboard Wing – Lower PanelTypical Attachment at Access Door/HoleStringer, O/B Wing Lower PanelRail Stringer at the NacelleFairing2 > 7 Hrs,FLS, SeeFigure 2(7)57-20-I01S Outboard Wing – Lower PanelSplice at Rib 46Fastener locations (inboard andoutboard of Rib 46) common tothe Lower Rib Chord and LowerRear Spar Chord2<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01S Outboard Wing – Lower PanelSplice at Rib 46Fastener locations (inboard andoutboard of Rib 46) common tothe Lower Rib Chord and LowerRear Spar Chord2> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 2(7)57-20-I01T Outboard Wing – Lower PanelSplice at Rib 46Fastener locations (inboard andoutboard of Rib 46) common tothe Lower Rib Chord andPaddle Fittings1<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I01T Outboard Wing – Lower PanelSplice at Rib 46Fastener locations (inboard andoutboard of Rib 46) common tothe Lower Rib Chord andPaddle Fittings1> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 2(7)57-20-I02A Wing Outboard, Upper Panel, MLGBeam Support Fitting, Upper SkinFastener locations C/T UpperPanel Skin Tab and MLG BeamSPRT FTG2 40,000(7)40,000(7)40,000(7)57-20-I02A Wing Outboard, Upper Panel, MLGBeam Support Fitting, Upper SkinFastener locations C/T UpperPanel Skin Tab and MLG BeamSPRT FTG240,000(7)40,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8757-20-I02A Upper Panel – MLG BeamOutboard Support FittingAttachmentFastener locations common totheO/B Wing Upper panel Skin Taband the MLG Beam OutboardSupport Fitting2<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I02A Upper Panel – MLG BeamOutboard Support FittingAttachmentFastener locations common totheO/B Wing Upper panel Skin Taband the MLG Beam OutboardSupport Fitting2> 7 Hrs,FLS, SeeFigure 2(7)57-20-I02B Wing Outboard, Upper Panel, FrontSpar Upper ChordF/Spar Upper Chord from Rib 8to Rib 11 (MidRib)2 40,000 <= 7 Hrs,FLS, SeeFigure 140,00057-20-I02B Wing Outboard, Upper Panel, FrontSpar Upper ChordF/Spar Upper chords from SOBto Wingtip (MidRib)2> 7 Hrs,FLS, SeeFigure 157-20-I02B Wing Outboard, Upper Panel, FrontSpar Upper ChordF/Spar Upper Chord from Rib 7to Rib 11 (MidRib)2<= 7 Hrs,FLS, SeeFigure 1<= 7 Hrs,FLS, SeeFigure 157-20-I02B Wing Outboard, Upper Panel, FrontSpar Upper ChordF/Spar Upper chords from SOBto Wingtip at Mid Rib except atF/Spar Splice between Rib 43and Rib 442> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I02B Wing Outboard – Upper Panel,Front Spar Upper ChordO/B Wing Upper Panel FrontSpar Chord from SOB toWingtip except at Ribpostlocations2> 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-88777 MAINTENANCE PLANNING DATA57-20-I02C Wing Outboard, Upper Panel, FrontSpar Upper ChordFront Spar Upper chords fromSOB to Wingtip at Rib PostLocation1 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I02C Wing Outboard, Upper Panel, FrontSpar Upper ChordFront Spar Upper chords fromSOB to Wingtip at Rib PostLocation1 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I02C Wing Outboard, Upper Panel, FrontSpar Upper ChordO/B Wing Upper Panel FrontSpar Chord from SOB toWingtip at all Ribpost Locations1<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I02C Wing Outboard, Upper Panel, FrontSpar Upper ChordO/B Wing Upper Panel FrontSpar Chord from SOB toWingtip at all Ribpost Locations1> 7 Hrs,FLS, SeeFigure 2(7)57-20-I02D Wing Outboard, Upper Panel, RearSpar Upper ChordRear Spar Upper Chord fromSOB to Wingtip at Rib PostLocation1 30,000(8)57-20-I02D Wing Outboard, Upper Panel, RearSpar Upper ChordRear Spar Upper Chord fromSOB to Wingtip at Rib PostLocation1<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I02D Wing Outboard, Upper Panel, RearSpar Upper ChordRear Spar Upper Chord fromSOB to Wingtip at Rib PostLocation1> 7 Hrs,FLS, SeeFigure 1(7)57-20-I02D Wing Outboard, Upper Panel, RearSpar Upper ChordRear Spar Upper Chord fromSOB to Wingtip at Rib PostLocation130,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8957-20-I02D Wing Outboard, Upper Panel, RearSpar Upper ChordRear Spar Upper Chord fromSOB to Wingtip at Rib PostLocation1 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I02D Wing Outboard, Upper Panel, RearSpar Upper ChordRear Spar Upper Chord fromSOB to Wingtip at Rib PostLocation1 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I02D Wing Outboard, Upper Panel, RearSpar Upper ChordO/B Wing Upper Panel RearSpar Chord from SOB toWingtip at all Ribpost Locations1<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I02D Wing Outboard, Upper Panel, RearSpar Upper ChordO/B Wing Upper Panel RearSpar Chord from SOB toWingtip at all Ribpost Locations1> 7 Hrs,FLS, SeeFigure 2(7)57-20-I02E Wing Outboard, Upper Panel, RearSpar Upper Chord, Upper SkinRear Spar Upper Chord fromRib 8 to Rib 122> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I02E Wing Outboard, Upper Panel, RearSpar Upper ChordO/B Wing Upper Panel RearSpar Chord from Rib 8 to Rib 12only2<= 7 Hrs,FLS, SeeFigure 257-20-I02E Wing Outboard, Upper Panel, RearSpar Upper ChordO/B Wing Upper Panel RearSpar Chord from Rib 8 to Rib 12only2> 7 Hrs,FLS, SeeFigure 2(7)57-20-I02F Wing Outboard, Upper Panel, RearSpar Upper ChordRear Spar Upper Chord fromRib 8 to Rib 11 (Mid Rib)2 40,000 <= 7 Hrs,FLS, SeeFigure 140,000AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-90777 MAINTENANCE PLANNING DATA57-20-I02F Wing Outboard, Upper Panel, RearSpar Upper ChordRear Spar Upper Chord fromSOB to Wingtip (Mid Rib)2 > 7 Hrs,FLS, SeeFigure 157-20-I02F Wing Outboard, Upper Panel, RearSpar Upper ChordRear Spar Upper Chord fromRib 7 to Rib 11 (Mid Rib)2 <= 7 Hrs,FLS, SeeFigure 1<= 7 Hrs,FLS, SeeFigure 157-20-I02F Wing Outboard, Upper Panel, RearSpar Upper ChordRear Spar Upper Chord fromSOB to Wingtip (Mid Rib)2 > 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I02F Wing Outboard, Upper Panel, RearSpar Upper ChordO/B Wing Upper Panel RearSpar Chord from SOB toWingtip except at Ribpost2<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I02F Wing Outboard, Upper Panel, RearSpar Upper ChordO/B Wing Upper Panel RearSpar Chord from SOB towingtip except at Ribpost2> 7 Hrs,FLS, SeeFigure 2(7)57-20-I02G Wing Outboard, Upper SkinTab Upper Skin Tab at fastenerlocations C/T Skin and R1Fitting2 40,000 40,000 40,00057-20-I02H Wing Outboard, Upper Skin NacelleAttachment TabUpper Skin Tab at fastenerlocations C/T Skin and F/SparChord240,000(7)40,000(7)57-20-I02H Upper Panel – Nacelle AttachmentTabFastener locations common totheO/B Wing Upper Panel Skinand Front Spar Upper Chord2<= 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9157-20-I02H Upper Panel – Nacelle AttachmentTabFastener locations common totheO/B Wing Upper Panel Skinand Front Spar Upper Chord2> 7 Hrs,FLS, SeeFigure 2(7)57-20-I02J Wing Outboard, Upper Panel,Typical Splice StringerUpper Panel Splice Stringers @U-10, U24 from Rib 3 to Rib 152 40,000 40,000 40,000 40,000 40,00057-20-I03A Wing Outboard, Rear Spar Web atFWD Trunnion FittingAll Fastener locations C/T RearSpar Chords and FWDTrunnion SPRT Fitting btwnRibs 7 and 81 30,000(8)30,000(7)57-20-I03A Wing Outboard, Rear Spar Web atFWD Trunnion FittingAll Fastener locations C/T RearSpar Chords and FWDTrunnion SPRT Fitting btwnRibs 7 and 8130,000(7)57-20-I03A Wing Outboard, Rear Spar Web atFWD Trunnion FittingAll Fastener locations C/T RearSpar Chords and FWDTrunnion SPRT Fitting btwnRibs 7 and 81<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-20-I03A Wing Outboard, Rear Spar Web atFWD Trunnion FittingAll Fastener locations C/T RearSpar Chords and FWDTrunnion SPRT Fitting btwnRibs 7 and 81> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-20-I03A Rear Spar Web at Fwd TrunnionSupport Fitting attachmentFasteners at the Lower RearSpar Chord and the Upper RearSpar Chord common to theRear Spar Web between Ribs 7and 81<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I03A Rear Spar Web at Fwd TrunnionSupport Fitting attachmentFasteners at the Lower RearSpar Chord and the Upper RearSpar Chord common to theRear Spar Web between Ribs 7and 81> 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-92777 MAINTENANCE PLANNING DATA57-20-I04A Outboard Wing– Front Spar Splicebetween Ribs 43 and 44Front Spar Splice between Ribs43 and 441 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 2(7)57-20-I04A Outboard Wing– Front Spar Splicebetween Ribs 43 and 44Front Spar Splice between Ribs43 and 441> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 2(7)57-20-I06A Wing Box Flap Support FTG, ShearTie RibsAll Fastener locations C/T FlapSupport Back-up Fittings andShear Tie Ribs 12, 21, 30240,000 40,00057-20-I06A Wing Box Flap Support Fitting atShear Tie Rib #30Fastener locations common tothe Flap Support Back-upFittings and Shear Tied Ribs2<= 7 Hrs,FLS, SeeFigure 257-20-I06A Wing Box Flap Support Fitting atShear Tie Rib #30Fastener locations common tothe Flap Support Back-upFittings and Shear Tied Ribs2> 7 hrsFLS, SeeFigure 257-20-I11 112W5093 Back-up Fitting TypicalRib #9Wing Station 414.5225,00057-30-I01A Lower Panel- Wing Tip Splice at Rib50Tension Bolts at Rear Spar130,000 30,000 18,75057-30-I01B Lower Panel- Wing Tip Splice at Rib50Tension Bolts at Front Spar130,000 30,000 18,75057-30-I01C Lower Panel- Wing Tip Splice at Rib50Fitting Pad at Front Spar130,000(7)30,000(7)18,750(7)57-30-I01D Lower Panel- Wing Tip Splice at Rib50Lower Skin Attachment at RearSpar240,000(7)40,000(7)25,000(7)57-53-I07A Inboard Main Flap OutboardCloseout RibAft Access Hole2 40,000(7)40,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9357-53-I07A Inboard Main Flap OutboardCloseout RibAft Access Hole 2 40,000(7)57-53-I07A Inboard Main Flap OutboardCloseout RibAft Access Hole 2 40,000(7)40,000(7)57-53-I07A Inboard Main Flap OutboardCloseout RibAft Access Hole 2 25,000(7)57-53-I07B Inboard Main Flap OutboardRibs Aft Carrier Beam Attachments 2 40,000(7)40,000(7)40,000(7)57-53-I07B Inboard Main Flap OutboardRibs Aft Carrier Beam Attachments 2 25,00057-53-I10 Inboard Main Flap Torque Tube Cross-section just Outboard ofCloseout Rib Splines1 30,000 30,000 30,000 30,000 30,00057-53-I10 Inboard Main Flap Torque Tube Cross-section just Outboard ofCloseout Rib Splines1 18,750(7)57-53-I11A Inboard Main Flap Inboard CloseoutRibSection thru Lower Chord atForward Track Support1 30,000(8)57-53-I11A Inboard Main Flap Inboard CloseoutRibSection thru Lower Chord atForward Track Support1 30,000(7)57-53-I11A Inboard Main Flap Inboard CloseoutRibSection thru Lower Chord atForward Track Support1 30,000(7)57-53-I11A Inboard Main Flap Inboard CloseoutRibSection thru Lower Chord atForward Track Support1 30,000(7)30,000(7)57-53-I11A Inboard Main Flap Inboard CloseoutRibSection thru Lower Chord atForward Track Support1 18,750(7)57-53-I11B Inboard Main Flap Inboard CloseoutRibSection through Torque TubeAccess Hole1 30,000(8)57-53-I11B Inboard Main Flap Inboard CloseoutRibSection through Torque TubeAccess Hole1 30,000(7)57-53-I11B Inboard Main Flap Inboard CloseoutRibSection through Torque TubeAccess Hole1 30,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-94777 MAINTENANCE PLANNING DATA57-53-I11B Inboard Main Flap Inboard CloseoutRibSection through Torque TubeAccess Hole1 30,000(7)30,000(7)57-53-I11B Inboard Main Flap Inboard CloseoutRibSection through Torque TubeAccess Hole1 18,750(7)57-53-I11C Inboard Main Flap Inboard CloseoutRib FittingSpline Region 1 30,000 30,000 30,000 30,000 30,00057-53-I11C Inboard Main Flap Inboard CloseoutRib FittingSpline Region 1 18,75057-53-I16A No. 3 (and No. 6) Inboard FlapSupport Underwing FittingLugs, Outer Lug 1 30,000(8)57-53-I16A No. 3 (and No. 6) Inboard FlapSupport Underwing FittingLugs, Outer Lug 1 30,000(7)57-53-I16A No. 3 (and No. 6) Inboard FlapSupport Underwing FittingLugs, Outer Lug 1 30,000(7)57-53-I16A No. 3 (and No. 6) Inboard FlapSupport Underwing FittingLugs, Outer Lug 1 30,000(7)30,000(7)18,750(7)57-53-I16B No. 3 (and No. 6) Inboard FlapSupport Underwing FittingLugs, Inner Lug 1 30,000(8)57-53-I16B No. 3 (and No. 6) Inboard FlapSupport Underwing FittingLugs, Inner Lug 1 30,000(7)57-53-I16B No. 3 (and No. 6) Inboard FlapSupport Underwing FittingLugs, Inner Lug 1 30,000(7)57-53-I16C No. 3 (and No. 6) Inboard FlapSupport Underwing FittingSection at Aft MainAttach Bolt(Section C-C)1 30,000(8)57-53-I16C No. 3 (and No. 6) Inboard FlapSupport Underwing FittingSection at Aft MainAttach Bolt(Section C-C)1 30,000(7)57-53-I16C No. 3 (and No. 6) Inboard FlapSupport Underwing FittingSection at Aft MainAttach Bolt(Section C-C)1 30,000(7)57-53-I16C No. 3 (and No. 6) Inboard FlapSupport Underwing FittingSection at Aft MainAttach Bolt(Section C-C)1 30,000(7)30,000(7)18,750(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9557-53-I18A No. 3 (and No. 6) Inboard FlapSupport Forward Tension LinkAft Clevis Fillet, Inboard Lug 1 30,000(8)57-53-I18A No. 3 (and No. 6) Inboard FlapSupport Forward Tension LinkAft Clevis Fillet, Inboard Lug 1 30,000(7)57-53-I18B No. 3 (and No. 6) Inboard FlapSupport Forward Tension LinkCenter Section 2 40,000(8)57-53-I18B No. 3 (and No. 6) Inboard FlapSupport Forward Tension LinkCenter Section 2 40,000(7)57-53-I18B No. 3 (and No. 6) Inboard FlapSupport Forward Tension LinkCenter Section 2 40,000(7)57-53-I18B No. 3 (and No. 6) Inboard FlapSupport Forward Tension LinkCenter Section240,000(7)40,000(7)25,000(7)57-53-I18C No. 3 (and No. 6) Inboard FlapSupport Forward Tension LinkLugs2 30,000(8)57-53-I18C No. 3 (and No. 6) Inboard FlapSupport Forward Tension LinkLugs230,000(7)57-53-I18C No. 3 (and No. 6) Inboard FlapSupport Forward Tension LinkLugs230,000(7)57-53-I18C No. 3 (and No. 6) Inboard FlapSupport Forward Tension LinkLugs230,000(7)30,000(7)25,000(7)57-53-I20A No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamForward and Aft Lugs2 40,000(8)57-53-I20A No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamForward and Aft Lugs240,000(7)57-53-I20A No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamForward and Aft Lugs240,000(7)57-53-I20A No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamForward and Aft Lugs240,000(7)40,000(7)57-53-I20A No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamAft Lug – Pin D (Forward andAft Lugs)225,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-96777 MAINTENANCE PLANNING DATA57-53-I20B No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamGeneral Section 2 40,000(8)57-53-I20B No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamGeneral Section 2 40,000(7)57-53-I20B No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamGeneral Section 2 40,000(7)57-53-I20B,C No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamGeneral Section (includes areaaround compression rodattachment point)2 40,000(7)40,000(7)57-53-I20C No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamAft Section of Beam, areaaround compression rodattachment point2 40,000(8)57-53-I20C No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamAft Section of Beam, areaaround compression rodattachment point2 40,000(7)57-53-I20C No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamAft Section of Beam, areaaround compression rodattachment point2 40,000(7)57-53-I20C No. 3 (and No. 6) Inboard FlapSupport Aft Tension BeamAft Section of Beam 2 25,000(7)57-53-I21A No. 3 (and No. 6) Inboard FlapSupport Pivot LinkLug Cross-Sections 2 30,000(8)57-53-I21A No. 3 (and No. 6) Inboard FlapSupport Pivot LinkLug Cross-Sections 2 30,000(7)57-53-I21A No. 3 (and No. 6) Inboard FlapSupport Pivot LinkLug Cross-Sections 2 30,000(7)57-53-I21A No. 3 (and No. 6) Inboard FlapSupport Pivot LinkLug Cross-Sections 2 30,000(7)30,000(7)25,000(7)57-53-I21B No. 3 (and No. 6) Inboard FlapSupport Pivot LinkCenter Section thru Fastener 1 30,000(8)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9757-53-I21B No. 3 (and No. 6) Inboard FlapSupport Pivot LinkCenter Section thru Fastener 1 30,000(7)57-53-I21B No. 3 (and No. 6) Inboard FlapSupport Pivot LinkCenter Section thru Fastener 1 30,000(7)57-53-I21B No. 3 (and No. 6) Inboard FlapSupport Pivot LinkCenter Section thru Fastener 1 30,000(7)30,000(7)18,750(7)57-53-I23 No. 3 (and No. 6) Inboard FlapSupport Drive Arm Assembly3rd Fastener Row from ForwardInboard Side1 30,000(8)57-53-I23 No. 3 (and No. 6) Inboard FlapSupport Drive Arm Assembly3rd Fastener Row from ForwardInboard Side1 30,000(7)57-53-I24A No. 3 (and No. 6) Inboard FlapSupport Carrier BeamInboard Forward Arm2 40,000(8)57-53-I24A No. 3 (and No. 6) Inboard FlapSupport Carrier BeamInboard Forward Arm240,000(7)57-53-I24A No. 3 (and No. 6) Inboard FlapSupport Carrier BeamInboard Forward Arm240,000(7)57-53-I24A No. 3 (and No. 6) Inboard FlapSupport Carrier BeamInboard Forward Arm240,000(7)40,000(7)18,750(7)57-53-I24B No. 3 (and No. 6) Inboard FlapSupport Carrier BeamCross-Over Beam1 30,000(8)57-53-I24B No. 3 (and No. 6) Inboard FlapSupport Carrier BeamCross-Over Beam130,000(7)57-53-I24B No. 3 (and No. 6) Inboard FlapSupport Carrier BeamCross-Over Beam130,000(7)57-53-I24C No. 3 (and No. 6) Inboard FlapSupport Carrier BeamFlap Forward Attachment1 30,000(8)57-53-I24C No. 3 (and No. 6) Inboard FlapSupport Carrier BeamFlap Forward Attachment130,000(7)57-53-I24C No. 3 (and No. 6) Inboard FlapSupport Carrier BeamFlap Forward Attachment130,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-98777 MAINTENANCE PLANNING DATA57-53-I24C No. 3 (and No. 6) Inboard FlapSupport Carrier BeamFlap Forward Attachment 1 30,000(7)30,000(7)57-53-I24D No. 3 (and No. 6) Inboard FlapSupport Carrier BeamFlap Aft Attachment 1 30,000(8)57-53-I24D No. 3 (and No. 6) Inboard FlapSupport Carrier BeamFlap Aft Attachment 1 30,000(7)57-53-I24D No. 3 (and No. 6) Inboard FlapSupport Carrier BeamFlap Aft Attachment 1 30,000(7)57-53-I24D No.3 (and No. 6) Inboard FlapSupport Carrier BeamFlap Aft Attachment 1 30,000(7)30,000(7)57-53-I24F No. 3 (andNo. 6 Inboard FlapSupport Carrier Beam'B' Point Lug1 30,000(8)30,000(7)30,000(7)57-53-I24G No. 3 (and No. 6) Inboard FlapSupport Carrier Beam'C' Point Lug1 30,000(8)30,000(7)57-53-I24G No. 3 (and No. 6) Inboard FlapSupport Carrier Beam'C' Point Lug130,000(7)57-53-I24G No. 3 (and No. 6) Inboard FlapSupport Carrier Beam'C' Point Lug130,000(7)30,000(7)57-53-I24G No. 3 (and No. 6) Inboard FlapSupport Carrier Beam'C' Point Lug118,750(7)57-53-I26A No. 3 (and No. 6) Inboard FlapSupport 113W1027Outer Pins A, B, and W1 30,000 30,000 30,000 30,000 30,000 18,75057-53-I26B No. 3 (and No. 6) Inboard FlapSupport 113W1027Outer Pins C, D, X, and Y1 30,000 30,000 30,000 30,000 30,000 18,75057-53-I27A No. 4 (and No. 5) Inboard FlapSupport Drive ArmJoint 'A' Pivot Hole2 40,000(8)57-53-I27A No. 4 (and No. 5) Inboard FlapSupport Drive ArmJoint 'A' Pivot Hole240,000(7)57-53-I27A No. 4 (and No. 5) Inboard FlapSupport Drive ArmJoint 'A' Pivot Hole240,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-99777 MAINTENANCE PLANNING DATA57-53-I27A No. 4 (and No. 5) Inboard FlapSupport Drive ArmJoint 'A' Pivot Hole 2 40,000(7)40,000(7)25,000(7)57-53-I27B No. 4 (and No. 5) Inboard FlapSupport Drive Arm'B' Point Lugs 2 40,000(8)40,000(7)57-53-I27B No. 4 (and No. 5) Inboard FlapSupport Drive Arm'B' Point Lugs 2 40,000(7)57-53-I27B No. 4 (and No. 5) Inboard FlapSupport Drive Arm'B' Point Lugs 2 40,000(7)40,000(7)25,000(7)57-53-I28A No. 4 (and No. 5) Inboard FlapSupport Actuator Support FittingOutboard Beam at 9.88 inchesAft of Point 'A'2 40,000(8)57-53-I28A No. 4 (and No. 5) Inboard FlapSupport Actuator Support FittingOutboard Beam at 9.88 inchesAft of Point 'A'240,000(7)57-53-I28A No. 4 (and No. 5) Inboard FlapSupport Actuator Support FittingOutboard Beam at 9.88 inchesAft of Point 'A'240,000(7)57-53-I28A No. 4 (and No. 5) Inboard FlapSupport Actuator Support FittingOutboard Beam at 9.88 inchesAft of Point 'A'240,000(7)40,000(7)25,000(7)57-53-I28B No. 4 (and No. 5) Inboard FlapSupport Actuator Support FittingPoint 'A' Lugs2 40,000(8)40,000(7)57-53-I28B No. 4 (and No. 5) Inboard FlapSupport Actuator Support FittingPoint 'A' Lugs240,000(7)57-53-I28B No. 4 (and No. 5) Inboard FlapSupport Actuator Support FittingPoint 'A' Lugs240,000(7)40,000(7)25,000(7)57-53-I29A No. 4 (and No. 5) Inboard FlapSupport Carrier BeamSection at Torque TubeAttachment Fitting1 30,000(8)57-53-I29A No. 4 (and No. 5) Inboard FlapSupport Carrier BeamSection at Torque TubeAttachment Fitting130,000(7)57-53-I29A No. 4 (and No. 5) Inboard FlapSupport Carrier BeamSection at Torque TubeAttachment Fitting130,000(7)57-53-I29A No. 4 (and No. 5) Inboard FlapSupport Carrier BeamSection at Torque TubeAttachment Fitting130,000(7)30,000(7)18,750(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-100777 MAINTENANCE PLANNING DATA57-53-I29B No. 4 (and No. 5) Inboard FlapSupport Pillow BlockSection at Aft Fasteners 1 30,000(8)57-53-I29B No. 4 (and No. 5) Inboard FlapSupport Pillow BlockSection at Aft Fasteners 1 30,000(7)57-53-I29B No. 4 (and No. 5) Inboard FlapSupport Pillow BlockSection at Aft Fasteners 1 30,000(7)57-53-I29B No. 4 (and No. 5) Inboard FlapSupport Pillow BlockSection at Aft Fasteners 1 30,000(7)30,000(7)18,750(7)57-53-I33 No. 4 (and No. 5) Inboard FlapSupport PinsInner and Outer Pin B 1 30,000 30,000 30,000 30,000 30,000 18,75057-53-I34 No. 1 (and No. 8) Outboard FlapSupport and No.2 (and No. 7)Outboard Flap SupportUnderwing Fitting Inner andOuter Pins1 30,000(8)30,000(7)30,000(7)30,000(7)30,000(7)57-54-I17A MLG FWD Trunnion SideloadFittingAll fastener locations C/TSideload Fitting and SideloadStraps2 40,000(7)40,000(7)57-54-I17A MLG FWD Trunnion SideloadFittingAll fastener locations C/TSideload Fitting and SideloadStraps2 40,000(7)57-54-I17B MLG FWD Trunnion SideloadStrapsAll Fastener Locations C/TUpper/Lower Strap and INBDO/B Vertical Support Fitting2 40,000 40,00057-54-I17B MLG FWD Trunnion SideloadStrapsAll Fastener Locations C/TUpper/Lower Strap and INBDO/B Vertical Support Fitting2 40,00057-54-I17C MLG FWD Trunnion OutboardSupport Fitting, R/S Attach FittingFlangeAll Fasteners Locations C/T112W1702 and 112W1704 FTGand R/Spar Web2 40,000 <= 7 Hrs,FLS, SeeFigure 1AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-101777 MAINTENANCE PLANNING DATA57-54-I17C MLG FWD Trunnion OutboardSupport Fitting, R/S Attach FittingFlangeAll Fasteners Locations C/T112W1702 and 112W1704 FTGand R/Spar Web2 > 7 Hrs,FLS, SeeFigure 1(7)40,000(7)57-54-I17C MLG FWD Trunnion OutboardSupport Fitting, R/S Attach FittingFlangeAll Fasteners Locations C/T112W1702 and 112W1704 FTGand R/Spar Web2 <= 7 Hrs,FLS, SeeFigure 1(7)<= 7 Hrs,FLS, SeeFigure 1(7)57-54-I17C MLG FWD Trunnion OutboardSupport Fitting, R/S Attach FittingFlangeAll Fasteners Locations C/T112W1702 and 112W1704 FTGand R/Spar Web2> 7 Hrs,FLS, SeeFigure 1(7)> 7 Hrs,FLS, SeeFigure 1(7)57-54-I17C 112W1704, MLG FWD TrunnionSupport FittingSection A-A, Spar Flange Crack 2<= 7 Hrs,FLS, SeeFigure 2(7)57-54-I17C 112W1704, MLG FWD TrunnionSupport FittingSection A-A, Spar Flange Crack 2> 7 Hrs,FLS, SeeFigure 2(7)57-54-I18A MLG Beam OBD Support FTG, LwrSkin FlangeAll fastener holes locations C/TLower flange and Lower SkinPanel2 40,000 40,00057-54-I18A MLG Beam OBD Support FTG, LwrSkin FlangeAll fastener holes locations C/TLower flange and Lower SkinPanel240,000(7)57-54-I18B MLG Beam OBD Support FTG,FittingLower Horizontal Rib of MLGBeam Support Fitting @Fastener Hole240,000(7)40,000(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-102777 MAINTENANCE PLANNING DATA57-54-I18B 112W1722, MLG Beam OutboardSupport FittingLower Horizontal Rib, SectionA-A Lead crack at fastener hole2 <= 7 Hrs,FLS, SeeFigure 2(7)57-54-I18B 112W1722, MLG Beam OutboardSupport FittingLower Horizontal Rib, SectionA-A Lead crack at fastener hole2> 7 Hrs,FLS, SeeFigure 2(7)57-54-I18C MLG Beam OBD Support FTG,FittingLower Horizontal Rib of MLGBeam Support Fitting @ FreeEdge240,000(7)40,000(7)57-54-I18C 112W1722, MLG Beam OutboardSupport FittingLower Horizontal Rib, SectionA-A Lead Crack at Free Edge2<= 7 Hrs,FLS, SeeFigure 257-54-I18C 112W1722, MLG Beam OutboardSupport FittingLower Horizontal Rib, SectionA-A Lead Crack at Free Edge2> 7 hrsFLS, SeeFig 2 (7)57-54-I19A MLG Drag Brace Support Fitting Section A-A Fitting Flange2 40,000(8)40,000(7)57-54-I19A MLG Drag Brace Support Fitting Section A-A Fitting Flange240,000(7)57-54-I19A MLG Drag Brace Support Fitting Section A-A Fitting Flange240,000(7)40,000(7)57-54-I19A 112W1752, MLG Drag BraceSupport FittingSection A-A Flange Crack2<= 7 Hrs,FLS, SeeFigure 2(7)AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-10357-54-I19A 112W1752, MLG Drag BraceSupport FittingSection A-A Flange Crack 2 > 7 Hrs,FLS, SeeFigure 2(7)57-54-I19B MLG Drag Brace Support Fitting,Base of FittingSection A-A Fastener LocationsC/T Base of fitting and RearSpar Web2 40,000(7)40,000(7)40,000(7)57-54-I19B MLG Drag Brace Support Fitting,Base of FittingSection A-A Fastener LocationsC/T Base of fitting and RearSpar Web2 40,000(7)40,000(7)57-54-I19B 112W1752, MLG Drag BraceSupport FittingSection A-A Base Crack 2 <= 7 Hrs,FLS, SeeFigure 2(7)57-54-I19B 112W1752, MLG Drag BraceSupport FittingSection A-A Base Crack 2 > 7 Hrs,FLS, SeeFigure 2(7)57-54-I19C MLG Drag Brace Internal BackupFittingEntire Fitting C/T SOB Rib andRear Spar, including StiffeningRibs2 40,00057-54-I19C MLG Drag Brace Internal BackupFittingEntire Fitting C/T SOB Rib andRear Spar, including StiffeningRibs2 <= 7 Hrs,FLS, SeeFigure 1<= 7 Hrs,FLS, SeeFigure 157-54-I19C MLG Drag Brace Internal BackupFittingEntire fitting c/t SOB Rib andRear Spar, including StiffeningRibs2 > 7 hrsFLS, SeeFigure 1> 7 hrsFLS, SeeFigure 157-54-I19C 112W1756, MLG Drag BraceSupport Back-up FittingSection A-A, Lead Crack inBase2 <= 7 Hrs,FLS, SeeFigure 2AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-104777 MAINTENANCE PLANNING DATA57-54-I19C 112W1756, MLG Drag BraceSupport Back-up FittingSection A-A, Lead Crack inBase2 > 7 hrsFLS, SeeFig 257-54-I20 Retraction Actuator Support Fitting,Fitting Attach FlangeRear Spar Attach Flange 2 40,000 40,000 40,000 25,000AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSGROUP(4)APPLICABILITY/THRESHOLDS(1,5,6)SSI #(2)DTR CHECK FORM TITLE(3)DTR LOCATION-200 -200IGW -300 -300ER -200LR 777FJAN 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-105TABLE NOTES:1. Blank entries in table indicate field is not applicable for that SSI/Check Form.2. Multiple listings under a single SSI# are uniquely identifiedby Check Form Title, Location, and Model-Series Information. All inspections listed under asingle SSI# for a given model must be performed.3. C/L or L/N in DTR Check Form title identifies certain forms as pertinent to specific airplane line numbers.4. Group designations only apply to 777-300ER/200LR/777F.5. Thresholds for airplanes other than -300ER/200LR/777F are set at 30,000 flight cycles.6. 777-300ER/200LR/777F Thresholds that include “FLS” (e.g., “> 7Hrs, FLS, See Figure 1 or Figure 2”) are sensitive to flight length. All other valuesshown are in flight cycles.7. No airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedures arevalidated, published in theappropriate manual, and accepted by the FAA.8. No airplane may be operated beyond the stated threshold requirements (or operational limit) unless it has been validated thatthe applicable publishedinspection procedures can be accomplished and the inspection hasbeen accomplished per the stated threshold requirements. If the applicablepublished inspection procedure can not be accomplished, an alternative procedure must be used which the FAA has accepted for this inspection.JAN 2010D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-106777 MAINTENANCE PLANNING DATAINDIVIDUAL AIRPLANE SPECIFIC AIRWORTHINESS LIMITATIONSPURPOSEThe purpose of this section is to identify additional or revised Supplemental Structures Airworthiness Limitation (AWL) Structural Inspection requirementsunique to a specific airplane serial number. Only those individual airplanes listed in this section have these additional or revised AWLs. These additionalor revised AWLs are due to differences in configuration as a result of Material Review Board actions.The following table lists the additional supplemental Structures Inspection requirements for certain individual serial number airplanes. Each item is listed byProduction Line/Serial Number, SSI Number, DTR Check Form Title, DTR Location, InspectionRequirements and Threshold.LINENUMBER/SERIALNUMBER SSI NUMBER DTR CHECK FORM TITLEDTRLOCATION INSPECTION REQUIREMENTS THRESHOLDL/N 740S/N 3766653-80-I13-MRB1Pressure Bulkhead STA2150; Section 48; MaterialReview Board WebDisposition forNonconformance Record(NCR): N1780061195;Aft Side Doubler/FillerSTA 2190,WL 264,BL LBL 271. Inspect the pressure bulkhead web at all fastenerscommon to web and NCR doubler/filler from the forwardside (except at radial stiffener) with HFEC per 777 NonDestructive Test (NDT) Manual, Part 6,51-00-01 every 16,000 flight cycles.2. Inspect the NCR doubler/filler at all fasteners commonto pressure bulkhead web and NCR doubler/filler fromthe aft side with HFEC per777 NDT Manual, Part 6,51-00-01 every 16,000 flight cycles.3. All other Supplemental Inspections required for SSI 53-80-I13 in the preceding section must still be conductedexcept at the fastener locations common to the NCRdoubler and filler.30,000NOV 2008777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-107C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFE LIMITSC.1 STRUCTURAL SAFE LIFE PARTSLANDING GEAR: See NoteLANDING GEAR LIFE LIMIT:*FAAEASA777-200/-200IGW/-300 Nose Landing Gear77,50046,500Except: Inner Cylinder73,30044,000777-200/-200IGW/-300 Main Landing Gear,86,20051,700Except: Outer Cylinder, 161W1110-3 S/N 5JHW and 161W1110-4 S/N 1JHW12,8577,714Outer Cylinder, 161W1110-3 S/N 4JHW and 161W1110-4 S/N 6JAN15,0909,054Outer Cylinder, 161W1110-3 S/N 1JJW and 161W1110-4 S/N 3JRW15,6779,406Outer Cylinder, 161W1110-3, -4, -9, -1016,66610,000Outer Cylinder, Other Part Numbers66,60040,000Lower Drag Strut, 161W4003 and 161W410376,30045,700Upper Side Strut Spindle, 161W010083,30050,000Lower Actuator Attach Pin, 161W102083,30050,000Spacer Tube, 161W115983,30050,000Aft Trunnion Pin, 161W130183,30050,000Lower Side Strut Spindle, 161W131083,30050,000777-200/-200IGW/-300 Main Landing Gear Support Structure86,20051,700Except: Load Distribution Plate – Outboard Gear Beam Support 112W1725-1, -3, -4, -19, -21, -2244,00026,400112W1725-7, -8, -9, -1099,60059,500112W1725-13, -14, -15, -1674,20044,500Pin – Fuse, Outboard Gear Beam Support, 112W1728-3, -929,40017,600112W1728-4, -599,60059,500112W1728-774,20044,500Pin – Fuse Retract Actuator, 112W176928,18116,908Hanger Pin Details (Fwd & Aft), 115W151083,30050,000Pin – Stabilizer Brace, MLG Beam, 115W167183,30050,000* Shown in number of landings.OCT 2007D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-108777 MAINTENANCE PLANNING DATANOTE: Component Interchangeability Lists 161W0003 (Main LandingGear) and 162W0002 (Nose LandingGear) provide complete listingsof777-200/200IGW/200LR/300/300ER/777F landing gearrelated components subject to life limitations.C.2 LIFE LIMITED PARTSNOTE: Component Interchangeability Lists 161W0003 (Main LandingGear) and 162W0002 (Nose LandingGear) provides a complete listof777-200/200 IGW/200LR/300/300ER/777F landing gear related components subject to life limitations.LANDING GEAR:LANDING GEAR LIFE LIMIT:FAAEASA777-200LR/300ER/777F Main Landing GearFigure 3 (FAA & EASA)777-200LR/300ER/777F Main Landing Gear Support StructureFigure 4 (FAA & EASA)777-200LR/300ER/777F Nose Landing GearFigure 5 (FAA & EASA)COMPONENT:LIFE LIMIT:777-200 Actuator Assembly – Door Main Landing GearNOTE: Life Limitation applies only to P/N 293W3702-5 actuators installed on 777-200 airplane Line Numbers 2-13, 15-17 and19-29. Incorporation of SB 777-32-0028 (reference Service Letters 777-SL-32-006 and 777-SL-001-E) removes the lifelimit and re-identifies it as a -7 Actuator.10,000 Landings777-200/-200 IGW/-300 Flight Deck Side Stowage Compartment Latch – Captain & First Officer (if compartment is installed).NOTE: Life Limitation is not Applicable Production Line Nos. 282 and on or following incorporation of SB 777-25-0140.365 Days Time In-Service777-200LR Optional Auxiliary Body Fuel TanksNOTE: This limit is based on fatigue test cycles completed todate and this limit will be increased or removed after additionaltest cycles are completed.1,800 Landings777-300ER Semi Lever Gear Hydraulic Strut (P/N 293W4201-2). 2,000 LandingsJAN 2009777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-109Instructions for using Safe Life Charts:1. For each safe life component, determine theaccumulated flight cycles and flight hours.2. Enter the Safe Life Limit Curve atthe appropriate flight cycles and flighthours and locate the intersection.3. If the point determined in Step 2 lies below the Safe Life Limit Curve, the component has not reached the safe life limit. If the point is on, above,orto the right of the the safe life curve, then the safe life limit has been reached.FIGURE 3. 777-200LR/300ER/777F MAIN LANDINGGEAR SAFE-LIFE LIMITSMain Landing Gear Safe-Life Limits265.60, 33.2099.90, 66.60124.95, 83.30129.30, 86.20114.45, 76.3001020304050607080901000 50 100 150 200 250 300Flight Hours (x 1,000)

Flight Cycles (x 1,000)Outer CylinderAll Other ComponentsAft Trunnion PinSpacer TubeLower Retract PinSide Strut SpindlesLower Drag StrutJAN 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-110777 MAINTENANCE PLANNING DATAFIGURE 4. 777-200LR/300ER/777F MAIN LANDING GEAR SUPPORT FITTINGS SAFE-LIFE LIMITSMain Landing Gear Support Fittings Safe-Life Limits124.95, 83.30320.00, 40.00182.40, 121.60129.30, 86.20111.30, 74.200204060801001201400 50 100 150 200 250 300 350Flight Hours (x 1,000)

Flight Cycles (x 1,000)All Other ComponentsLoad Distribution PlateFuse Pin BUpper and Lower Stabilizer Aft PinsHanger Link Fwd and Aft PinsOutboard Gear Beam Fuse PinRetract Actuator Fuse Pin(40K cycles for all Flight Hours)JAN 2009777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-111FIGURE 5. 777-200LR/300ER/777F NOSE LANDING GEAR SAFE-LIFE LIMITSNose Landing Gear Safe-Life Limits348.00, 43.50109.95, 73.30116.25, 77.50286.40, 35.8066.00, 44.000102030405060708090050100150200250300350400Flight Hours (x 1,000)

Flight Cycles (x 1,000)All Other ComponentsInner Cylinder777-300ER Upper Floating Piston,Upper Cylinder, Lower Cylinder,Metering Pin, and Orifice PlateJAN 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-112777 MAINTENANCE PLANNING DATAD. AIRWORTHINESS LIMITATIONS – SYSTEMSFUEL SYSTEMS AIRWORTHINESS LIMITATIONSThis section contains an FAA approved program of Airworthiness Limitations (AWLs) for operators to incorporate into their maintenance program for thistype design to meet the new standards and assumptions introduced by§ 25.981 and Special Federal Aviation Regulation (SFAR) No.88. SFAR 88 – FuelTank System Fault Tolerance Evaluation Requirements and Title 14Code of Federal Regulations § 25.981 – Fuel Tank Ignition Prevention requiremaintenance instructions, and control limitations for certain fuel tank critical design configurations. Note: The auxiliary fuel tank installation has beenshown to comply with CFR 25.981 at Amendment 25-102.Paragraph 2(a) of SFAR 88 and Paragraph (b) of the new standardintroduced by § 25.981 requires certain design approval holdersof Type Certificates(TCs) and Supplemental Type Certificates (STCs) of large transportairplanes to conduct a safety review of the fuel tank systems. The purpose of the safetyreview is to identify design features that may result in development of ignition sources in the fuel tank systems. Fuel system Airworthiness Limitations(AWLs) are mandatory maintenance actions required to ensure that unsafe conditions identified by the SFAR 88 safety review do not occur or are notintroduced into the fuel tank system as a result of configuration changes, repairs, alterations, or deficiencies in the maintenance program throughout theoperational life of the airplane. An AWL may be an AirworthinessLimitation 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 that is responsiblefor the airplanemodel Type Certificate, or applicable regulatory agency. A critical fuel tank ignition sourceprevention feature may exist inthe fuel system and its relatedinstallation or in systems that, if a failure condition were to develop,could interact with the fuelsystem in such a way thatan unsafe condition woulddevelop 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 practices not contained in the applicable CDCCL mustbe approved by the Seattle FAA ACO orapplicable regulatory agency.DEC 2007777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-113ALIs 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 that is responsible for theairplane model Type Certificate, or applicable regulatory agency. Strict adherence to methods, techniques and practices as prescribed is required toensure the ALI is complied with. Any use of methods, techniques orpractices not contained in these ALIs must be approved by the Seattle FAA ACO orapplicable regulatory agency.USE OF ALTERNATE TOOLSFor AWLs which require use of certain tools, use of alternate tools requires prior approval from the Seattle FAA ACO.EXCEPTIONAL SHORT-TERM EXTENSIONSSince AWL intervals are based on estimations of the probability ofan event, an exceptional short-term extension for each fuelsystem AWL listed in thisdocument may be made without jeopardizing safety. The local regulatory authority (e.g. a Principal Maintenance Inspector) mustconcur 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 operators “short-term escalation” program fornormal maintenance tasks described in the operators’manuals and in the Flight Standards Handbook 8300.10.The Seattle FAA ACO has accepted that these exceptional short-term extensions may be granted without consultation with that office:1. The term “exceptional short-termextension” is defined as an increase in a fuelsystem 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 United StatesFAA jurisdiction only.Operators who are not underthe U.S. FAA jurisdiction should obtain interval extension approvals from their local regulatory agency.SEP 2007D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-114777 MAINTENANCE PLANNING DATAREGULATORY AGENCY APPROVALAny deviations from the published AWL instructions included in this document require approval from the Seattle FAA ACO. This applies to operatorsunder the U.S. FAA jurisdiction only and toairplanes registered in the U.S. All other operators should obtain approval from 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 be approved by the Seattle FAA ACO. This revision will thenbe forwarded to all 777 operators and the Seattle FAA ACO.SEP 2007777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-115E. PAGE FORMAT: SYSTEMS AIRWORTHINESS LIMITATIONSCOLUMN EXPLANATIONAWL NUMBER Each task is given a unique AWL Item Number. The first and second digits are the ATA Chapter Number.TASKALI = Airworthiness Limitation Instruction. These tasks are inspectionsthat should be performed at the listedintervals.CDCCL = Critical Design Configuration Control Limitation.INTERVALTask frequencies are specified in terms of a usage parameter such as flight hours, cycles or calendar time.APPLICABILITY Airplanemodel applicability.DESCRIPTIONDescription of the task to be performed or criticaldesign configurations aspects that cannot be changed withoutviolating the intent of the design.FEB 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-116777 MAINTENANCE PLANNING DATAAIRWORTHINESS LIMITATIONS – FUEL SYSTEMSAWLNUMBER TASK INTERVAL APPLICABILITY DESCRIPTION28-AWL-01 ALI 16,000 FC/3,000 DYSNOTEALLExternal Wires Over Center Fuel TankConcern: Potential for Wire Chafing andArcing to Center Fuel Tank Upper Panel.Perform a detailed inspection of the wire bundles routed over the center fuel tank and under the maindeck floor boards per Boeing AMM 28-11-00 to detect damaged clamps, wire chafing, and the wirebundle is not in contact with surface of the center fuel tank. If discrepancies are found, repair per theBoeing Standard Wiring Practices Manual D6-54446 (SWPM Section 20-10).Interval Note: Whichever comes first.28-AWL-02 CDCCL N/A ALLExternal Wires Over Center Fuel TankConcern: Potential for Wire Chafing and Arcing to Center Fuel Tank Upper Panel.If any maintenance is performed inthe area under the main deck floorboards and over the center fueltank, verify the following:1. Maintain the existing wire bundle routing and clamping.2. Perform a detailed inspection of the wire bundles routed over the center fuel tank and under the maindeck floor boards in the areas of the performed maintenance to detect damaged clamps, wire chafing,and that the wire bundle is not in contact with the surface of the center fueltank. If discrepancies arefound, repair per the Boeing Standard Wiring Practices Manual, D6-54446 (SWPM Section 20-10).FEB 2009777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-11728-AWL-03 ALI 16,000 FC/3,000 DYSNOTEALLFuel Quantity Indicating System (FQIS) – Out TankWiring Lightning Shield to Ground TerminationConcern: Potential for Lightning induced voltages on the FQIS wiring to enter the fuel tank.Using a Loop Resistance Tester, P/N 906-10246-2 or 906-10246-3, perform the following inspection andrepair as necessary to ensure the functional integrity of the FQIS wiring shield to ground termination perBoeing AMM 05-55-54:1. Measure and verify the resistance of the shield to groundtermination for the following items:• The loop resistance shall not exceed 40 milliohms for Connector D28103P (Left Inboard MainTank Rear Spar) Wire Bundle W8073.• The loop resistance shall not exceed 54 milliohms for Connector D28102P (Left Outboard MainTank Rear Spar) Wire Bundle W8072.• The loop resistance shall not exceed 40 milliohms for Connector D28101P (Left Center TankFront Spar) Wire Bundle W8010.• The loop resistance shall not exceed 40 milliohms for Connector D28201P (Right Center TankFront Spar) Wire Bundle W8020.• The loop resistance shall not exceed 53 milliohms for Connector D28202P (Right Outboard MainTank Rear Spar) Wire Bundle W8077.• The loop resistance shall not exceed 40 milliohms for Connector D28203P (Right Inboard MainTank Rear Spar) Wire Bundle W8078.Interval Note: Whichever comes first.28-AWL-04 CDCCL N/A ALLFQIS – Out Tank Wiring Lightning Shield to Ground TerminationConcern: Potential for Lightning induced voltages on the FQIS wiring to enter the fuel tank.If any maintenance is performed on the FQIS wire bundle in the unpressurized zone outside of fuselageand outside the fuel tank, verify the following:1. Presence of shielded wiring.2. Presence of bonding jumper betweenreceptacle at the rear sparand ground stud or structure and theresistance between red end of the jumper and the structure is no more than 0.001 ohm (1 milliohm).3. Presence of sealant at the bonding jumper terminal and the ground stud or screw to which itis attached.4. The shield ground is terminated per Boeing SWPM 20-10-15.5. The installation is inspected per 28-AWL-03 if the wire bundle shield (or wire bundle, if shield isintegral) is repaired or replaced.Use Loop Resistance Tester as specified in Boeing AMM 05-55-54.AWLNUMBER TASK INTERVAL APPLICABILITY DESCRIPTIONFEB 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-118777 MAINTENANCE PLANNING DATA28-AWL-05 CDCCL N/A 777 airplanesLine Numbers 498and on; or allairplanes thathave incorporatedService Bulletin777-28-0044.Lightning Protection – Engine Fuel Feed Line Fuel Tank PenetrationConcern: Potential for arcing, sparking or filamentheating inside the tank at the interface between thebulkhead fitting and the spar during a lightning strike event.The following must be maintained per Boeing AMM 28-22-15 if the bulkhead fitting or attached tubing areremoved and replaced:1. Verify electrical fay surface bond from bulkhead fitting to structure is 0.001 ohm (1 milliohm) or less.2. Install full-bodied fillet seal encapsulating the bulkhead fitting to the tank wall interface inside the tank.3. Install full bodied fillet sealencapsulating the first coupling interface inside the tank.4. Verify an electrostatic bonding jumper presence between the structure and the first tube mating withthe bulkhead fitting inside the tank.5. Verify electrical bond from structure to first tube mating with the bulkhead fitting is 0.010 ohm(10 milliohms) or less.28-AWL-06 CDCCL N/AALLLightning Protection – Hydraulic Line Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interface between the bulkhead fitting andthe spar during a lightning strike event.When the bulkhead fitting or attached tubing are removed and replaced, maintain fay surface bondconfiguration of hydraulic line fuel tank penetration at interface between bulkheadfitting and the spar perBoeing AMM 29-11-60. This configuration has the following CDCCLs:1. Fay Surface bond at the bulkhead fitting. Bonding resistance betweenthe fitting and the spar must be0.001 ohm (1 milliohm) or less.2. A bonding jumper from the hydraulic heat exchanger to structure inside the tank. The maximumresistance between the heat exchanger and the bonding jumper is 0.0025 ohm (2.5 milliohms).3. Apply full bodied cap seal at the fitting to the tank wall interface inside and outside the fuel tank.28-AWL-07 CDCCL N/AALLAC and DC Pump MaintenanceConcern: Potential for maintenance error during pump overhaul. 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 Eaton (VK2523) Component Maintenance Manual(CMM) 28-20-42 Revision 7, CMM 28-20-44 Revision 6, CMM 28-20-45 Revision 3, CMM 28-20-47Revision 2, or later revisions of these CMMs that have been approved by the FAA Seattle ACO.AWLNUMBER TASK INTERVAL APPLICABILITYDESCRIPTIONFEB 2009777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-11928-AWL-08 CDCCL N/A All 777-200 “A”market airplanesLine Numbers 523and on; orairplanes modifiedper BoeingService Bulletin777-28-0045.Center Wing Tank Sump Drain ValveConcern: Potential for arcing or sparking inside thetank at the interface between the sump drain valveand the lower skin in the center wingtank during a lightning strike event.The following must be maintained per Boeing AMM 28-11-06 if the drain valve is removed and replaced:1. Phenolic washer at sump drain valve inside the tank.2. Full bodied fillet seal of the washer interface inside the tank.28-AWL-09 CDCCL N/A ALLLightning, Fault Current, or Hot Short Protection – 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 bonding withinthe 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 design features ofthe existing equipment penetrations (such as fuelmeasuring sticks, sump drain valves, fueling manifold, fuel temperature sensor, and motor operated fuelshutoff valve adaptor plate) requires approval by the FAA Seattle ACO.28-AWL-10 CDCCL N/A ALLAC Fuel Pump Fault Current Bonding Jumper InstallationConcern: Potential for fault current path through the pump housing to structure inside the tank.Electrical faults internal to the fuel pump motorimpeller are by design routed through the motor impellerassembly to the bonding jumpers on the front face ofthe motor impeller assembly to structure outsidethe tank. The bonding jumpers ensure that fault currents are conducted to structure outside the tankuntil the circuit breaker and/or GFI has had time to remove power from the pump.The following must be maintained during pump replacement per Boeing AMM 28-22-06:1. Installation of the bonding jumper between the pump motor impeller and structure.2. Motor Impeller bonding resistance to structureless than or equal to 0.00025 ohms (0.25 milliohms).28-AWL-11 CDCCL N/A ALLFuel Quantity Indicating System (FQIS) and AuxiliaryFuel Tank Electronic Fuel Level Indication System(EFLI) – Out of Tank Wiring Installation Separation RequirementConcern: Potential for hot shorts and EMI induced voltages on the FQIS or Auxiliary Fuel Tank EFLIwiring outside of the tank to enter the fuel tank.Routing and installation of any new wiring mustuse wire types BMS 13-48, BMS 13-60 or BMS 13-58,and not be within a 2 inch radius of the FQIS or Auxiliary Fuel Tank EFLI wiring. When a single clampfails, a separation greater than 1⁄2 inch must be maintained from Auxiliary Fuel Tank EFLI or FQIS wiring.AWLNUMBER TASK INTERVAL APPLICABILITY DESCRIPTIONFEB 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-120777 MAINTENANCE PLANNING DATA28-AWL-12 CDCCL N/AALLCenter Wing Tank Fueling Valve and Aux Tank Refuel Valve V28001 – Fault Current BondConcern: Potential for arcing or filamentheating inside the center wing fuel tank.For the CWT and Auxiliary Tank Refuel Valve V28001, the following must be maintained per BoeingAMM 28-21-02 or AMM 28-21-21 if the refueling valve is removed and replaced:1. Fay Surface bond between the valve body and the rear spar inside the tank is 0.0025 ohm(2.5 milliohms).2. Fillet seal around valve body and gask-o-seal perimeter inside the tank.28-AWL-13 CDCCL N/AALLFuel Quantity Indicating System (FQIS) – Fuel Quantity Processor Unit (FQPU) Repair and AuxiliaryFuel Tank Electronic Fuel Level indication System (EFLI) RepairConcern: Potential for maintenance error during FQPUor Auxiliary Fuel Tank EFLI repair. The FQPUand Auxiliary Fuel Tank EFLI is designed to limit the levels of energy, voltage, current, and powerallowed within the FQIS / EFLI circuit to intrinsicallysafe levels in order to preclude the potential of anignition source within any fuel tank.Repair and overhaul of FQPU must be per GEAviation (VK5294) Component Maintenance Manual(CMM) Volume 1, 28-47-69 Revision1, and CMM Volume 2 (IPC) 28-47-69 Revision 2, CMM Volume 128-47-65 Revision 3 and CMM Volume 2 (IPC) 28-47-65Revision 4, or later revisions of these CMMsthat have been approved by the FAA Seattle ACO.NOTE: Prior to repair and overhaul of FQPU PartNumber 0310KPU02, it must be modified/upgradedper Smiths Industries Service Bulletin 0310KPU-28-400.Repair and overhaul of EFLI must be per Parker (V26055) CMM 28-41-81 Revision 0, or later revisionsthat have been approved by the FAA Seattle ACO.28-AWL-14 CDCCL N/AALLFuel Quantity Indicating System (FQIS)and Auxiliary Fuel Tank Electronic Fuel Level indication System(EFLI) – Repair of In-TankHardware (Tank Units, Densitometers, Water Detector)Concern: Potential for maintenance error duringrepair of in-tank hardware (tank units anddensitometers). Arc gaps may develop that could result in an ignition source inside the fuel tank.Repair and overhaul of FQIS tank units anddensitometers must be per GE Aviation (VK5294)Component Maintenance Manual (CMM) 28-47-58 Revision 4, CMM 28-47-59 Revision 1, CMM 28-47-60 Revision 4, CMM 28-48-03 Revision 2, CMM 28-47-71Revision 5, or later revisions of these CMMsthat have been approved by the Seattle FAA ACO.Repair and overhaul of EFLI probe must be per Parker (V26055) CMM 28-41-70 Revision 1, or laterrevisions of this CMM that have been approved by the Seattle FAA ACO.AWLNUMBER TASK INTERVAL APPLICABILITYDESCRIPTIONFEB 2009777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12128-AWL-15 CDCCL N/AALLFuel Quantity Indicating System (FQIS) – Repair or Replacement of In-Tank Wire HarnessConcern: Potential for error during repair or replacement of in-tank wire harness. Arc gaps may developthat could result in an ignition source inside the fuel tank.Repair and overhaul of FQIS in-tank wire harness must be per Boeing SWPM 20-14-12 when the repairis accomplished on the airplane, or per GE Aviation(VK5294) CMM 28-47-61 Revision 7, or laterrevisions of this CMM that have been approvedby the Seattle FAA ACO when the repair isaccomplished in the shop.Installation of FQIS in-tank wire harness mustbe per Boeing AMM 28-41-05. Wire slack clearancebetween the wires and structures must be greater than 0.125 inches.Verify the following when installing the spar FQIS adapter penetration:1. The mating surface of the tank wiring harness adapter on the spar is cleaned with solvent as specifiedin the Boeing AMM 28-41-05.2. New O-ring(s) are installed.3. The Jamnuts are tightened to a torque asspecified in the Boeing AMM Task 28-41-05.4. Sealant is installed on the threads and the bonding jumper terminal and the ground studs perinstruction in the Boeing AMM Task 28-41-05.5. Verify the bonding resistance between the adapterand the structure is not more than 0.0005 ohm(0.5 milliohms).After installation of the airplane wire connector, verify that the bonding resistance between the connectorand the spar is not more than 0.0005 ohm (0.5 milliohms).28-AWL-16 CDCCL N/AALLFuel Tank Access Doors ConfigurationConcern: Potential for arcing or sparking inside thetank at the interface between the door and the tankstructure as a result of a direct strikeor conducting currents through the wing skin.The following must be maintained during installationof fuel tank access doors located on the lower wingskin. (Boeing AMMs 28-11-01, 28-11-02,28-11-07, 28-11-03, and 28-13-05):Verify presence of a phenolic strip positioned aroundthe outermost periphery of the door that mates withthe wing skin inside the tank, do a check of the knitted aluminum mesh gasket for serviceability andreplace if necessary, and apply grease or anti-corrosioncompound to both sides of the knitted aluminummesh gasket. Install the prepared knitted aluminummesh gasket between the outside face of the doorand the wing skin to establish the electrical conductivity between the access door and the wing skinusing the clamp ring and fasteners torqued tothat specified in the applicable Boeing AMM.For the surge tank access door with vent scoop, verifythe installation of a bonding jumper between theupper duct and the door; 0.010 ohm (10 milliohms) or less.AWLNUMBER TASK INTERVAL APPLICABILITYDESCRIPTIONFEB 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-122777 MAINTENANCE PLANNING DATA28-AWL-17 CDCCL N/AALLResetting Tripped Fuel Pump Circuit BreakersConcern: Potential for arcing or sparking insidethe tank between fuel pumps and fuel pump housingsand outside the tank between pump wiring and structure in flammable leakage zones.Verify it is safe to reset the circuit breaker(s) by following the applicable OEM troubleshootingprocedures. Fault(s) that resulted in circuit breaker trip must be isolated and corrected prior to reset.28-AWL-18 ALI 375 DYSALLNOTEAC Fuel Pump Ground Fault Interrupter (GFI)Concern: Potential for pump housing burn-through, eitherinternal or external to the fuel tank, as a resultof major arcing due to electrical failure (i.e., damaged electrical connector, stator windings or leadwire tohousing/end cap shorting).The GFI is designed to detect electrical faults and open the circuit prior to pump housing burn-through.The following maintenance check is required in orderto ensure continued functionality of the GFI circuit:Operationally check the GFI of Center Tank Override/Jettison Pumps, Auxiliary Tank Pumps, Main TankJettison Pumps and Main Tank Boost Pumps per AMM 28-22-00 or AMM 28-14-05.Applicability Note:a. Center Tank Override/Jettison Pumps and Main Tank Jettison Pumps on airplanes with LinePositions 423, 429, 454 and on.b. Center Tank Override/Jettison Pumps and MainTank Jettison Pumps on airplanes prior to LinePosition 454, except 423 and 429 that haveincorporated Service Bulletin 777-28A0037.c. All Main Tank Boost Pumps on airplanes starting with Line Position 662.d. All Main Tank Boost Pumps on airplanes prior to Line Position 662 that have incorporatedService Bulletin 777-28A0038.e. Auxiliary Tank Pumps on 777-200LRs only if equipped with Auxiliary Fuel Tanks.AWLNUMBER TASK INTERVAL APPLICABILITYDESCRIPTIONFEB 2009777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12328-AWL-19 CDCCL N/A Airplane LinePosition 552 andon; or airplanesmodified perSB 777-28A0034orSB 777-28A0059as noted.Lightning and Fault Current Protection– Motor Operated Valve (MOV) ActuatorConcern: Potential for arcing or sparking inside thefuel tank at a conductive metal-to-ground structureinterface as a result of electrical fault currents event.The following design features must be maintainedper Boeing AMMs 28-22-02, 28-22-01, 28-22-03, 28-22-04, 28-26-01, 28-26-02, 28-31-02, 28-31-03, 28-31-04, 28-31-05,28-14-21, 28-14-22, 24-14-24, 28-14-25, 28-21-23, 28-21-24, 28-14-11,28-14-12 during actuator, adapterplate or index plate repair orreplacement (Only AMM 28-31-03 isapplicable to SB 777-28A0059):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/(auxiliary fueltank cell wall structure) is 0.0005 ohms (0.5 milliohms) or less. Install fillet seal around theperiphery of the adapter plate and the spar outside the tank.b. Wet install and cap seal the four bolts that attach the adapter plate to the spar inside the tank andfillet seal around the edge of the hole and on thestationary part of theadapter plate inside thetank.c. Install sealed electrical fay surface bond between the serrated mating surfaces of the index plateand the adapter plate. Wet install the index plate screws using same sealant.d. Install sealed electrical fay surface bond between the mating surfacesof the actuator and theindex plate. Wet install the actuator screws using same sealant.e. With the bonding jumper not installed, verifyelectrical bonding resistance between the actuatorbond strap attachment point and the spar/(auxiliary fuel tank cell wall structure) is 0.0025 ohms(2.5 milliohms) or less.f. Prior to attachment of the bonding jumper tothe actuator, verify electrical bonding resistancebetween the loose end of the bonding jumper and the spar/(auxiliary fuel tank cell wall structure)is 0.0015 ohms (1.5 milliohms) or less.g. Attach the bonding jumper to the upper housing of the actuator using a sealed electrical faysurface bond and verify electrical bonding resistance between the actuator housing and theattached bonding jumper terminal is 0.001 ohms (1 milliohm) or less.(Continued on next page)AWLNUMBER TASK INTERVAL APPLICABILITYDESCRIPTIONFEB 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-124777 MAINTENANCE PLANNING DATA28-AWL-19(Cont.)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 index plateand the adapter plate. Wet install the index plate screws using same sealant.b. Install sealed electrical fay surface bond between the mating surfacesof 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 the upperhousing of the actuator and the spar is 0.0025 ohm (2.5 milliohms) or less.d. Prior to attachment of the bonding jumper tothe actuator, verify electrical bonding resistancebetween the loose end of the bonding jumper and the spar/(auxiliary fuel tank cell wall structure)is 0.0015 ohms (1.5 milliohms) or less.e. Attach the bonding jumper to the upper housing of the actuator using a sealed electrical faysurface bond and verify electrical bonding resistance between the actuator housing and theattached bonding jumper terminal is0.001 ohm (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 surfacesof the actuator and theindex plate. Wet install the actuator screws using the same sealant.b. With the bonding jumper not installed, verifyelectrical bonding resistance between the upperhousing of the actuator and the spar/(auxiliary fueltank cell wall structure) is 0.0025 ohms (2.5milliohms) or less.c. Prior to attachment of the bonding jumper tothe actuator, verify electrical bonding resistancebetween the loose end of the bonding jumper and the spar/(auxiliary fuel tank cell wall structure)is 0.0015 ohms (1.5 milliohms) or less.d. Attach the bonding jumper to the upper housing of the actuator using a sealed electrical faysurface bond and verify electrical bonding resistance between the actuator housing and theattached bonding jumper terminal is 0.001 ohms (1 milliohm) or less.AWLNUMBER TASK INTERVAL APPLICABILITYDESCRIPTIONFEB 2009777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12528-AWL-20 CDCCL N/A ITT actuators(P/N MA20A2027or MA30A1001)installed onAirplane LinePosition 552 andon; or airplanesmodified perSB 777-28A0034orSB 777-28A0059.Motor Operated Valve (MOV) Actuator – RepairConcern: Potential for arcing or sparking inside thefuel tank at a conductive metal-to-ground structureinterface as a result of lightning orelectrical fault current event. Anelectrical isolatoron the actuatoroutput shaft is intended to disconnect the output shaft electrically from the motor internal electricalcircuitry and ground path structure.To verify the integrity of the electrical isolationfeature, conduct the following bench test per ITT(V73760) CMM 28-20-21:A Dielectric Strength test on thecompleted actuator assembly shall be performed by applying 3000 VACRMS, 60 Hz for one (1) minute between any mounting foot of the actuator and the output shaft spline.There shall be no evidence of disruptive discharge inthe form of leakage current in excess of 1.0 milliamps. The 3000V test is a bench test only and must not be performed on the aircraft.28-AWL-21 ALI 4500 DYS 777-200LR withAuxiliary FuelTankExternal Wires Over Auxiliary Fuel TankConcern: Potential for Arching or Wire Chafing to Auxiliary Fuel Tank.Perform a detailed inspection of thewire bundles routed over the auxiliary fuel tank and under the maindeck floor boards to detect damaged clamps, chafingwires, and a wire bundle that is in contact withstructure. If discrepancies are found, repair per the Boeing Standard Wiring Practices Manual D6-54446(SWPM Section 20-10).28-AWL-22 CDCCL N/A 777-200LR withAuxiliary FuelTankExternal Wires Over Auxiliary Fuel TankConcern: Potential for Arching or Wire Chafing to Auxiliary Fuel Tank.If any maintenance is performed in the area under the main deck floor boards and over the auxiliary tank,verify the following:1. Maintain the existing wire bundle routing and clamping.2. Perform a detailed inspection of the wire bundles routed over the auxiliary fuel tank and under the maindeck floor boards in the areas ofthe performed maintenance to detect damaged clamps, chafing wires,and a wire bundle that is in contact with structure.If discrepancies are found, repair per the BoeingStandard Wiring Practices Manual D6-54446 (SWPM Section 20-10).AWLNUMBER TASK INTERVAL APPLICABILITY DESCRIPTIONFEB 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-126777 MAINTENANCE PLANNING DATA28-AWL-23 CDCCL N/A 777-200LR withAuxiliary FuelTankAuxiliary Tank Bonding Jumper InstallationConcern: Potential for fault current path through to structure inside the tank. Electrical faults internal tothe fuel pump motor impeller are, bydesign, routed through the motor impeller assembly to the bondingjumpers on the front face of the motor impeller assembly to the tank structure. The tank containsbonding jumpers which provide a pathfrom the tank to airplane structure. The bonding jumpers ensurethat fault currents are conducted to structure outsideof the tank until the circuit breaker and or/GFI hashad time to remove power.The following must be maintained during pump replacement per Boeing AMM 28-14-15 or MarshallAerospace (VK3784) CMM 28-14-02:1. The installation of the bonding jumper between the pump motor impeller and tank structure.2. Perform the following resistance checks:a. Fuel pump motor-impeller unit to the pump housing bonding resistance is less than 2 milliohms(0.002 ohm).b. Fuel Pump motor-impeller to the tank structure bonding resistance is less than 2.5 milliohms(0.0025 ohm).The following must be maintained during tank replacement / installation per Boeing AMM 28-14-01:1. On the right side of the cell the resistance between the tank bonding jumpers to stanchions should beless than or equal to 10 milliohms.2. The electrical fay surface bond resistance between the stanchions and the structure must be less thanor equal to 10 milliohms.28-AWL-24 CDCCL N/A 777-200LR withAuxiliary FuelTankAuxiliary Tank Thermal ProtectionConcern: Potential for heating of the auxiliary tank structure as a result of a cargo fire event.If any maintenance is performed on oraround the auxiliary tanks, verify the following thermal protectioncomponents:i. Cargo Liners which separate the cargo compartment from the auxiliary fuel tank.ii. 9G Thermal Impact Barrier is installed on the auxiliary fuel tank barrier cell.iii. The Thermal Insulation Blanket located betweenthe end wall cargo liner and the thermal impactbarrier is installed.AWLNUMBER TASK INTERVAL APPLICABILITY DESCRIPTIONFEB 2009777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12728-AWL-25 CDCCL N/A 777-200LR withAuxiliary FuelTankAuxiliary Tank Lightning ProtectionConcern: Potential for arcing or sparking insidethe tank at a conductive metal-to ground structureinterface as a result of lightningstrike events to aux tank drains.If any maintenance is performed onor around the auxiliary tank drain system, verify the following:i. Aeroquip Low Pressure Teflon Lightning Safe Hoses are installed on the auxiliary fuel tank drain lines.ii. Flame Arrestors are installed in fuel tank drains.iii. Foil backed fairing panels and associated bonding located below drain lines from STA 1428 toSTA 1530 are installed.28-AWL-26 ALI 375 DYS 777-200LR withAuxiliary FuelTankAuxiliary Fuel Tank AC Fuel Pump Uncommanded ON /Automatic Shutoff CircuitConcern: Potential for failure of fuel pump power control circuit in the energized state allowing dryrunning of fuel pump with a potential ignitionthreat due to pump overheat or sparking.The Pump Uncommanded ON/AutomaticShutoff Circuit provides redundant circuitry to remove powerfrom the Auxiliary Tank Pump if pump pressure is low for >15 seconds.The following maintenance check is required in order to ensure continued functionality of this circuit.1. Operationally check the Pump Uncommanded ON/Automatic Shutoff Circuit per Boeing AMM28-14-05.AWLNUMBER TASK INTERVAL APPLICABILITYDESCRIPTIONFEB 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-128777 MAINTENANCE PLANNING DATAF. AIRWORTHINESS LIMITATIONS – NITROGEN GENERATION SYSTEMS TASKSThe following list of AWLs (ALIs and CDCCLs)contain FAA approved scheduled inspections and design limitations for operators toincorporate into theirmaintenance program for this typedesign to meet the requirements for the introduction of theFlammability Reduction Means (FRM) Nitrogen GenerationSystem (NGS). The FAA operational rule change E8-16084 Final Flammability Rule requires maintenance instructions and control limitations for certainNGS critical design configurations.§ 25.981 also requires CDCCLs to preclude ignition sources inside the fuel tank that may beintroduced by the additionof NGS.Final Flammability Rule, Paragraph III(F), Section 7, Paragraph M25.4(a) requiresthat if FRM is usedto comply with ParagraphM25.1, airworthinesslimitations must be identified for all maintenance or inspection tasks required to identify failuresof components within the FRM that are needed to meetParagraph M25.1. NGS AWLs are mandatory maintenance actions thatensure that unsafe conditions that arise due to NGS failures do not occur or arenot introduced into the airplane as a result of configuration changes, repairs, alterations, ordeficiencies in the NGS Maintenance Program throughout theoperational life of the airplane.AUG 2010777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-129AIRWORTHINESS LIMITATIONS – NITROGEN GENERATION SYSTEM (NGS)AWLNUMBER TASK INTERVAL APPLICABILITY DESCRIPTION47-AWL-01 CDCCL N/A All AirplanesLine Number772 and on,or airplanesthat haveincorporatedService Bulletin777-47-0002Lightning Protection – NGS NEA Distribution Line Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interface between the bulkhead fitting /flame arrestor and the spar during a lightning strike event. The following must be maintained if thebulkhead fitting or attached tubing is removed andreplaced or reinstalled (refer to Boeing AMM 47-21-06):1. Install the same part number bulkhead fitting.2. Verify electrical fay surface bond between the bulkhead fitting and the front spar structure inside thetank is 0.0005 ohm (0.5 milliohms) or less.3. Install full-bodied fillet seal between the frontspar structure and bulkhead fitting flange inside ofthe tank.4. Install full-bodied fillet seal encapsulating the first coupling interface inside the tank at the bulkheadfitting between the flareless fitting nut and tubeand between the flareless fitting nut and bulkheadfitting.5. Verify electrical bond from structure to first tube mating with the bulkhead fitting is 1.0 ohm or less.NOTE: The bulkhead fitting is a special part which has an integral flame arrestor. Any change to thispart requires approval by the Seattle FAA ACO.47-AWL-02 CDCCL N/A All AirplanesLine Number772 and on,or airplanesthat haveincorporatedService Bulletin777-47-0002Lightning Protection – NGS NEA Distribution Line Fuel Tank PenetrationConcern: Potential for arcing, sparking of filamentheating inside the tank at the interface between thedielectric isolator hose and the NEA tubing during a lightning strike event.The NGS installation is designed to prevent lightning currents from entering the center wing fuel tank byadding a dielectric isolator hose in the forwardleading edge fairing area NEA distribution line. Theisolator must be maintained if thedielectric isolator hose or attachedtubing is removed and replaced orreinstalled (refer toBoeing AMM 47-21-00).JUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-130777 MAINTENANCE PLANNING DATA47-AWL-03 CDCCL N/A All AirplanesLine Number772 and on,or airplanesthat haveincorporatedService Bulletin777-47-0002Nitrogen Generation System (NGS) – Flammability Exposure and PerformanceConcern: Airplane alterations may impact the performance of the NGS and hencethe flammability of theCenter Wing Fuel Tank.Background: The NGS is designed to provide the proper level of nitrogen to the center wing tank inorder to reduce the flammability exposure by reducing the oxygen content of the ullage. Theflammability exposure is also affectedby the temperature of the fuel. The followingare critical featuresof the airplane that, if altered, can negatively affect the performance of the NGS which in turn mayincrease the center fuel tank flammability exposurebeyond the limits of 14 Code of Federal Regulations,Section 25.981 at Amendment25-125, utilizing the equivalent level of safety finding described in FAAMemorandum PS05-0177-P-2.1. Transferring air (20.9% oxygen) to the center fueltank will dilute the nitrogen rich atmosphere createdby the NGS in the fuel tank. Some Auxiliary Fuel Tank installations transfer air to the center wing tankas part of venting and fuel transfer.2. NGS performance depends on bleed air pressure inthe bleed air cross-over manifold supplied bythe engines.3. Certification of the NGSdepends on the inherent flammability ofthe center fuel tank without NGSinstalled. Center tank flammability is a direct function of fuel tank temperature. Any heat sourcesaround the tank, heat sources introduced into the tank (such as warmfuel or new heat exchangers), orchanges that would cause heat to be retained (suchinstallation of blanketsadjacent to tank walls)could affect fuel tank flammability in a negative manner.CDCCL: Any design change that affects the vent system by adding air to the center tank, reduces thebleed pressure in the cross-over manifold during any phase of flight or ground operations, or adds anyheat to the center wing fuel tank or increases heat retention of the center wingfuel tank is not allowedwithout an FAA approved analysis to show that the change, or combination of changes, does not affectthe NGS performance per the requirements of 14 CFR Section 25.981(b), Amendment 25-125 utilizingthe equivalent level of safety finding described 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.AWLNUMBER TASK INTERVAL APPLICABILITYDESCRIPTIONJUL 2011777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-13147-AWL-04 ALI 108,000 FH All AirplanesLine Number772 and on,or airplanesthat haveincorporatedService Bulletin777-47-0002Nitrogen Generation System – Thermal Switch Functional and Operational CheckConcern: Latent Failure of the Thermal Switch removes a layer of protection against fuel tank ignition byhot bleed air.The NGS uses engine bleed air from the engine bleed system cross-over manifold to generate nitrogento reduce the flammability of the center fuel tank. The NGS has features to prevent directly feeding hotbleed air into the fuel tank. The Thermal Switchprovides a redundant backup to the NGS Controller toprotect the Air Separation Module (ASM) and prevent hot bleed air from entering the fuel tank. TheThermal Switch backup feature is a latent (not detected) failure and must be tested to maintaincertification of the NGS.Perform a functional and operational check of the Thermal Switch to ensureintegrity of the ThermalSwitch (refer to Boeing AMM 47-42-04).47-AWL-05 ALI 10,682 FH All AirplanesLine Number772 and on,or airplanesthat haveincorporatedService Bulletin777-47-0002Nitrogen Generation System– Cross-Vent Check Valve – Operational CheckConcern: The Cross-Vent Check Valve may fail open latently allowing air to flow through the center tankdiluting the 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 the operation ofthe Cross-Vent Check Valve (refer to Boeing AMM ATA 47-21-05). Verify thevalve opens against spring force and closes by spring force.47-AWL-06 ALI 10,682 FH All AirplanesLine Number772 and on,or airplanesthat haveincorporatedService Bulletin777-47-0002Nitrogen Generation System – NEADistribution Ducting InspectionConcern: The NEA Distribution System ducting outside the fuel tank may fail latently allowing NEA toleak without reaching the fuel tank, resulting inthe fuel tank not reaching required inert levels.Inspect the NEA distribution lines from the ASM to the fuel tank front spar for damage and leaks (refer toBoeing AMM ATA 47-21-00).AWLNUMBER TASK INTERVAL APPLICABILITY DESCRIPTIONJUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-132777 MAINTENANCE PLANNING DATA47-AWL-07 CDCCL N/A All AirplanesLine Number772 and on,or airplanesthat haveincorporatedService Bulletin777-47-0002Industry Fleet Average Flammability ExposureConcern: NGS performance is dependent on industry descent times. Industry efforts to reduce descenttime may result in NGS performancethat does not meetFAA requirements.Fleet Average flammability exposure for the fuel tankswith flammability reduction of this airplane typemust be maintained in accordance with 14 CFR Part25, Appendix M. Boeing will monitor U.S. descentstatistics and, if necessary to maintain compliance, will publish service information. If Boeing publishessuch service information, this CDCCL requires either that operators implement these FAA-approveddesign changes or that operators implement other design changes or operational procedural changesapproved by the Seattle FAA ACO to maintain compliance with 14 CFR Part 25, Appendix M.NOTE: This CDCCL does not require individual operators to monitor descent rates of their fleets.Boeing will monitor US descentstatistics and provide any needed service instructions tooperators. To prevent increasing flammability exposure above permissible levels, this CDCCLrequires operators to incorporate future Boeing published service instructions denoted tomaintain compliance with this CDCCL, or other approved actions, within the compliance timesstated in the service instructions.AWLNUMBER TASK INTERVAL APPLICABILITYDESCRIPTIONJUL 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-133777 MAINTENANCE PLANNING DATAG. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)SELECTION OF CMRsIn order to grant operators of the 777 airplane an opportunity toparticipate in the evaluation and selection of CMRs in an integrated process with MRBtasks and intervals, a Certification Maintenance Coordination Committee (CMCC) was convened to review all of the 777 CMRs. TheCMRs listed in thisdocument are the result of applying the CMCC process as described in AC 25-19.CMR DEFINITIONAs defined by AC 25-19, a CMR is a required periodic task, established during the design certification of the airplane as an operating limitation of the typecertificate. CMRs usually result froma formal, numerical analysis conducted to show compliance with catastrophic and hazardous failure conditions.Additional notes concerning the definition of CMRs:1. A CMR is intended to detect safety-significant latent (hidden) failures that would, in combination with one or more specificfailures or events, result in ahazardous or catastrophic failure condition.2. It is important to note that CMRs are derived from a fundamentally different analysis process than the maintenance tasks andintervals thatresult fromthe Maintenance Steering Group (MSG-3) Analysis associated withMaintenance Review Board (MRB) activities. MSG-3 Analysis activity producesmaintenance tasks that are performed for safety, operational, or economic reasons, involving both preventative maintenance tasks, which are performedbefore failure occurs (andare intended to prevent failures), as well as failure-finding tasks.CMRs, on the other hand, are failure-finding tasks only, andexist solely to limit the exposure to otherwise hidden failures. Although CMR tasks are failure-finding tasks, use of potential failure-finding tasks, suchas functional checks and inspections, may also be appropriate.3. CMRs are designed to verify that a certain failure has or has not occurred, anddo notprovide any preventative maintenance function. CMRs “restartthe failure clock to zero” for latent failures by verifyingthat the item has not failed, or cause repair if it has failed. Because the exposure time to a latentfailure is a key element in the calculations used in a safety analysis performed to show compliance with FAR 25.1309, limitingthe exposure time willhave a significant effect on the resultant overall failure probability ofthe system. The CMR TaskInterval should be designated in terms of flight hours,cycles, or calendar time, as appropriate.FEB 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-134777 MAINTENANCE PLANNING DATA4. The type certification process assumes that the airplanewill be maintained in a conditionof airworthiness at least equal toits certified or properly alteredcondition. The process described in AC 25-19 is not intended toestablish normal maintenance tasks that should be defined through the MSG-3Analysis process. Also, this process is not intended to establish CMRs for the purpose of providing supplemental margins of safety for concerns arisinglate in the type design approval process.5. CMRs should not be confused with required structural inspection programs that are developedby the type certificate applicantto meet the inspectionrequirements for damage tolerance, as required by FAR 25.571 or25.1529, Appendix H25.4 (Airworthiness Limitations section). CMRs are to bedeveloped and administered separately from any structural inspection programs.CMR TYPESCMR Tasks are divided into two categories: One Star CMRs (*) and Two Star CMRs(**). They are defined as follows:1. One Star CMRs (*) – The tasks and intervals specified are mandatory and cannot be changed, escalated, or deleted without theconcurrence of theSeattle FAA ACO.2. Two Star CMRs (**) – Task intervals may be adjusted in accordance with each operator’s approved escalation program or an approved reliabilityprogram in a like manner for any MRB Report task, but may not be deleted without prior Seattle FAAACO approval.ESCALATION OF TWO STAR CMRs (**)All Two Star CMRs (**) can be managed and controlled the same asany MRB Report task; however, they can not be deleted from anoperator’s programwithout prior Seattle FAA ACO approval. For operators with approved escalation practices oran approved reliability program, data collection andanalytical techniques are used to make adjustments to an operator’s maintenance program. It has been demonstrated that the management of amaintenance program does not give rise to undue escalations; consequently, the escalation of Two Star CMR (**) intervals withinan operator’smaintenance program will be properly managed by the operator subject to local regulatory authority approval.DEC 2006D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-135777 MAINTENANCE PLANNING DATAEXCEPTIONAL SHORT-TERM EXTENSIONSSince CMR intervals are based on statistical averages and reliability rates, an exceptional short-term extension of 10% for each CMR listed in thisdocument may be made, except as noted in Item 1, without jeopardizing safety. The local regulatory authority (e.g. a PrincipleMaintenance Inspector)must concur with any exceptional short-term extensions before they take place using procedures established with the local regulatory authority in theoperators’ manuals. The “exceptional short-term extension” process is applicable to CMR intervals. It should not be confused with the operator’s shortterm escalation” programfor normal maintenance tasks describedin the operators’ manuals and in the FlightStandards Handbook8300.10.The Seattle FAA ACO has accepted that these exceptional short-term extensions may be granted without consultation with that office:1. The term “exceptional short-term extension” is defined as an increase in a CMR interval that may be needed to cover an uncontrollable or unexpectedsituation. All CMRs listed in this section have been approved for an exceptional short-term extension of 10%, except as notedbelow:• CMR 52-CMR-01, which has been approved for a short-termextension, is restrictedto a maximum of 90 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 CMR extensions.After a CMR has experienced an exceptionalshort-term extension, the CMR interval will revert back toits interval listed in this document. The Seattle FAAACO must approve, prior to its use, any desired extension not explicitly listed above.This exceptional short-term extension listed above applies to airlines that fall under the United StatesFAA jurisdiction only.Operators who are not underthe U.S. FAA jurisdiction should obtain interval extension approvals from their local regulatory agency.OCT 2007D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-136777 MAINTENANCE PLANNING DATAPOST-CERTIFICATION CHANGES TO CMRsAny post-certification changes to CMRsshould be reviewed by the 777 CMCC and approved by the Seattle FAA ACO:1. Since the purpose of a CMR is to limit the exposure time to agiven significant latent failure as part of an engineering analysis of overall system reliability,instances of a CMR task repeatedly finding that no failure hasoccurred may not be sufficient justification for deleting the task or increasing the timebetween repetitive performances of the CMR task. In general,* CMRs are not good candidates for escalation under an operator’sreliability program.A * CMR task change or interval escalation can only be made ifworld fleet service experience indicates that certain assumptionsregarding componentfailure rates made early during the engineering analysis were overly conservative, and a re-calculation of system reliability with revised failure rates ofcertain components reveals that the * CMR task or interval may be changed.2. The introduction of a new CMR or any change to an existing CMR should be reviewed by the same process used during initial certification. It isimportant that operators be afforded the same opportunity to participate that they received during the original certification of the airplane, in order toallow the operators to manage their own maintenance programs.3. In the event that later data provide sufficient basis for relaxation of a CMR (less restrictive actions to be required), thechange may be documented by anFAA-ACO approved change to this CMR document.4. If the requirements of an existing CMR must be increased (morerestrictive actions to be performed), it will be implemented by a change to this CMRdocument and enforced by an FAA Airworthiness Directive (AD).5. After initial aircraft certification, the only basis for addinga new CMR is in association with the certification of designchanges.6. A new CMR created as part of a design change should be partof the approved data for that change and added to this CMR document.In the event that a CMR is revised, Boeing will document it by preparing a revision to this document that will be approved by the Seattle FAA ACO. Thisrevision will then be forwarded to all 777 operators and the Seattle FAA ACO offices.MAY 1998D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-137777 MAINTENANCE PLANNING DATAFIGURE 6. PAGE FORMAT CERTIFICATION MAINTENANCE REQUIREMENTSMAR 2006D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-138777 MAINTENANCE PLANNING DATAH. PAGE FORMAT – CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)COLUMNEXPLANATIONCMRITEM NUMBEREach task is given a unique CMR item number. The first character, if applicable, is the engine prefix:G = General Electric, N = Pratt & Whitney, and R = Rolls RoyceThe second and third digits are the ATA chapter number.TYPECMR TYPECMRs are categorized into one or two star CMRs based on whetheror not they can be escalated by the operator without prior FAA-ACOapproval.* Cannot be escalated or deleted without prior Seattle ACO approval.** Can be escalated based on the operator’s approved program for continued airworthiness based on continuous analysis andsurveillance; however, these tasks cannot be deleted without prior Seattle ACO approval.RELATED MRBITEM NUMBERThis column is for the related MRB Item Number, if there is an applicable MRB Item Number. Not all CMRs have a one to one relationship to aMRB Item Number.TASKMSG-3 TASK CATEGORIESOP = OPERATIONAL CHECKA failure finding task to determineif an item is fulfilling its intended purposes. Doesnot require quantitative tolerances.CMR INTERVALTask frequencies are specified in terms of a usageparameter such as flight hours, cycles or calendar time.APPLICABILITYAPL ENGApplicable Airplane Model and Engine.AIRPLANEALL = All Airplanes300 = 777-300777F = 777 FreighterENGINEALL = All Engines4000 = PW4074, PW4077, PW4084, PW4090, PW4098GE90 = GE90 (75B/76B/85B/90B/94B/110B/115B)TRENT = TRENT 800 (875-17, 877-17, 884-17, 890-17,892, 892B, 895)TASKDESCRIPTIONDescription of the task to be performed.FEB 2009D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-139777 MAINTENANCE PLANNING DATAI. CERTIFICATION MAINTENANCE REQUIREMENTS TASKSCMRITEMNUMBERTYPERELATEDMRBITEMNUMBERTASKCMRINTERVALAPPLICABILITY777CERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTION21-CMR-01 ** 21-33 OP 7500 Hrs 777F ALL Operationally check the manual and automatic activation of the Main Deck AlertingSystem.26-CMR-01 * --- IN 6000 Hrs or18 Mos,whicheveroccurs firstALLNOTEALL Inspect Cargo Fire Bottles, supplierPart Numbers 473474-2, 473475-2, 473854-2,and 473876-2, for leaks using a Halide Leak Detector. Apply Corrosion InhibitorCompound to burst disc (inside fill fitting).AIRPLANE NOTE: Applicable to airplanes with -2 bottles installed. (CMR is notapplicable to -3 bottles).27-CMR-01 * 27-140 OP 500 Hrs ALL ALL Operationally checkPRIMARY FLIGHT CONTROL ACTUATION. Use hydraulics-onactuation confidence tests.27-CMR-02 * 27-160 OP 250 Hrs ALL ALL Operationally check ACTUATOR CONTROL ELECTRONICS (ACE) MONITORINGFunctions of Flight ControlsSystem (use ACE self-test).27-CMR-04 * 27-360 OP 12000 Hrs ALL ALL Operationally check LE SLAT SKEW/LOSS CABLE SYSTEM.27-CMR-05 * IN 5000 FC 777F ALL Conduct a visual inspection ofthe 24 Horizontal StabilizerTrim Actuator (HSTA)Karon lined bushings and pins common to the Jackscrew Upper and Lower Gimbals,Section 48 and Section 82 Fittings. Inspect for Karon liner or pin wear/damage andliner delamination27-CMR-06 * 12-002 LUB 5000 Hrs or500 Dyswhichevercomes first777F ALL Lubricate the Elevator Power Control Units (PCUs) and Elevator Hinges.27-CMR-07 * 12-004 LUB 5000 Hrs or500 Dyswhichevercomes first777F ALL Lubricate the Rudder and Rudder Tab Hinge Bearings, Rudder Power Control Units(PCUs) Reaction Link Rod Ends and PCU Rod Ends.JAN 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-140777 MAINTENANCE PLANNING DATA27-CMR-08 * 27-240 FC 12000 Hrs or1125 Dys,whichevercomes first777F ALLFunctionally Check Elevator Surface Freeplay.27-CMR-09 * 27-430 FC 12000 Hrs or1125 Dys,whichevercomes first777F ALL Functionally Check Rudder/Rudder Tab Surface Freeplay.28-CMR-01 * --- IN 6000 Hrs 300 ALL Conduct a visual inspection ofthe center fuel tank FQIS wiring for damage or chafing.29-CMR-01 * 29-030 FC 12000 Hrs ALL ALL Functionally check theGROSS INTERNAL LEAKAGE of the Main (Center) HydraulicSystem.29-CMR-02 * 29-130 OP 12000 Hrs ALL ALL Operationallycheck CENTER HYDRAULIC ISOLATION SYSTEM.29-CMR-03 * 29-150 OP 6000 Hrs ALL ALL Operationally check RAT System (using RAT checkout module) and check RAT Autoand Manual Deployment Systems.31-CMR-01 * 31-100 OP 24 HrsNOTEALL ALL Operationally check FIRE WARNING SYSTEM using the Fire/Overheat Test switch(if not checked by crew).INTERVAL NOTE: Under exceptional operational circumstances the interval may beextended beyond 24 hours (elapsed clock hours) but not exceed 48 hours (clocktime).32-CMR-01 * 12-081 LUB 50 FC or25 DYS,whicheveroccurs laterNOTE ALL Lubricate the left and right Main Landing Gear truck beam and inner cylinder pivotjoints.AIRPLANE NOTE: Applicable to airplanes production line number 915 and on, orairplanes that have incorporatedService Bulletin 777-32-0085.52-CMR-01 * --- DS 3375 Dys NOTE ALL Discard the Flight Deck Door Strike Assembly.AIRPLANE NOTE: Applicable to airplanes production line number 427 and on, orincorporation of Service Bulletin 777-25-0216.CMRITEMNUMBERTYPERELATEDMRBITEMNUMBERTASKCMRINTERVALAPPLICABILITY777CERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTIONJAN 2011777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-14172-CMR-01DELETED*---IN24 HrsNOTENOTETRENTNOTEInspect (Detailed) STEP-ASIDE-GEARBOX (SAGB) HOUSING and EXTERNALGEARBOX LOWER BEVEL BOX (LBB) HOUSING for evidence of oil leakage andcracking per RR Non-Modification Service Bulletin 72-C129, Issue 3. AD 97-06-13.INTERVAL NOTE: Under exceptional operational circumstances the interval may beextended beyond 24 hours (clock time) but not to exceed 48 hours (clock time).AIRPLANE NOTE: Applicable to all Increased Gross Weight 777-200 airplanes andto any 777-200 with Rolls-Royce Trent engines capable of the 892-17 thrust rating.ENGINE NOTE: Applicable to all Rolls-Royce Trent engines capable of the 892-17thrust rating and to all Trent engines installed on Increased Gross Weight 777-200’s.72-CMR-02DELETED*---IN10 CycNOTETRENTNOTEInspect (Special Detailed) STEP-ASIDE-GEARBOX (SAGB) HOUSING withfluorescent penetrant for evidence of cracking per RR Non-Modification ServiceBulletin 72-C129, Issue 3. AD 97-06-13.AIRPLANE NOTE: Applicable to all Increased Gross Weight 777-200 airplanes andto any 777-200 with Rolls-Royce Trent engines capable of the 892-17 thrust rating.ENGINE NOTE: Applicable to all Rolls-Royce Trent engines capable of the 892-17thrust rating and to all Trent engines installed on Increased Gross Weight 777-200’s.72-CMR-03 * --- IN 1000 CycNOTE300 TRENTInspect (Special Detailed) MAIN FAN BLADES with ultrasonic test for evidence of fanblade root cracking per Rolls-Royce Non-Modification Service Bulletin 72-C445,Rev. 1.INTERVAL NOTE: Repeat inspections at 500 cycles.78-CMR-01 * 78-02578-22078-365OP 5000 Hrs ALL ALLOperationally check Thrust Reverser SYNC LOCK on left and right engine.78-CMR-02DELETED*78-03578-040-NOTEALLGE90PRECOOLER INLET DUCT ASSEMBLY KISS SEALINTERVAL NOTE: For Part Number S315W134-2 and -11 inspect perService Bulletin 777-78-0010, Revision 2.All CMRs on this list may have a 10% exceptional short-term extension of the task interval for a specific airplane. For further explanation, see Section 9.D.CMRITEMNUMBERTYPERELATEDMRBITEMNUMBERTASKCMRINTERVALAPPLICABILITY777CERTIFICATION MAINTENANCE REQUIREMENTSAPL ENG TASK DESCRIPTIONJAN 2011D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-142777 MAINTENANCE PLANNING DATAJ. REPORTING UNCONTROLLABLE HIGH THRUSTFAILURE CONDITIONSTitle 14 Code of Federal Regulations Sections 121.703 and 135.415 state that “each certificate holder shall report any failure,malfunction, or defect in anaircraft, system, component, or powerplant that occurs or is detected at any time if, in its opinion, that failure, malfunction, or defect has endangered ormay endanger the safe operation of an aircraft”. Section 125.409also requires reporting of failures, malfunctions, or defects.In many cases a reportablefailure or malfunction will be obvious, but thereare some failure modes related to uncontrolled high thrust that are reportable but may not be obvious. Thefollowing information is provided, as required by FAA Exemption No. 7955, 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:777-200 (777-200IGW or 777-200ER), 777-300• Auto-acceleration or uncommanded thrust change to higher power• Stuck thrust lever above idle power• Inability to reduce thrust777-300ER, 777-200LR, 777F• Stuck thrust lever above idle power• No response to thrust lever, with the cause being a mechanical failure in the thrustlever mechanism or resolver• Although some or these incidents may not appear to be safetyrelated, documenting the events is important to ensure the present level of safety ismaintained and/or to identify failure conditions that must be corrected.FEB 2009777 MAINTENANCE PLANNING DATAD622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-143When filing a report of such an event with the FAA, the operatoris requested to include in the description of the event one ormore of thefollowing phrases:• “thrust control”• “no response to thrust lever”• “auto-acceleration”• “uncontrolled high thrust”In addition, the following information should be included in the report:• Event description• Flight Crew action• Maintenance action• List of affected or removed componentsReports should be submitted to the local representative of theFAA Administrator that handles the appropriate reporting responsibility for 121.703, 125.409,and 135.415. In addition to filing reports with the FAA, it is recommended that a copybe sent to Boeing and to the engine manufacturer.SEP 2007D622W001-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-144777 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK