777 MAINTENANCE PLANNING DATA

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777

MAINTENANCE PLANNING DATA (MPD) DOCUMENT

SECTION 9

AIRWORTHINESS LIMITATIONS (AWLs) AND 

CERTIFICATION MAINTENANCE REQUIREMENTS (CMR

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COMPILED AND PUBLISHED BY:

MAINTENANCE PROGRAMS ENGINEERING

COMMERCIAL AVIATION SERVICES

BOEING COMMERCIAL AIRPLANE GROUP

SEATTLE, WASHINGTON

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TABLE OF CONTENTS

REVISIONS ............................................................................................................................................................................................LIST OF EFFECTIVE PAGES ................................................................................................................................................................A. SCOPE...............................................................................................................................................................................................B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS.................................................................................................

C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFE LIMITS ..........................................................................................

D. AIRWORTHINESS LIMITATIONS – SYSTEMS.................................................................................................................................

E. PAGE FORMAT: SYSTEMS AIRWORTHINESS LIMITATIONS.........................................................................................................

F. AIRWORTHINESS LIMITATIONS – NITROGEN GENERATION SYSTEMS TASKS.........................................................................

G. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)..........................................................................................................

H. PAGE FORMAT – CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)............................................................................I. CERTIFICATION MAINTENANCE REQUIREMENTS TASKS............................................................................................................J. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS...................................................................................

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REVISIONS

REVISION AND REVISION DESCRIPTION 

APRIL 1995 (Original Release) Prepared by:

M. C. Toepke (Boeing) 4/95

SuperviseS. R. Willi(Boeing) 4

SEPTEMBER 1995 (Revision 1)Added GE90 Fatigue RequirementsCMR 27-CMR-03 DeletedCMR 31-CMR-01 Wording ChangedCMR 78-CMR-01 RevisedCMR 78-CMR-02 Added

Prepared by:M. C. Toepke (Boeing) 9/95

SuperviseS. R. Willi(Boeing) 9

SEPTEMBER 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 Increased Gross Weight.Deleted SSI 57-53-I21 Duplicate Requirement

Prepared by:L. E. Harrison (Boeing) 12/95

SuperviseS. R. Willi(BOEING

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JANUARY 1996 (Revision 3)Added four Fatigue Critical Items for Rolls-Royce Trent engine.

Prepared by:L. E. Harrison (Boeing) 1/96

SupeS. R. (Boei

APRIL 1996 (Revision 4)Added FAA to front pageRevised Flight Deck Stowage Compartment Latch wording.Revised Nose Landing Gear Life LimitCMR 78-CMR-02 Revised

Prepared by:L. E. Harrison (Boeing) 4/96

SupeS. R. (Boei

AUGUST 1996 (Revision 5)CMR 78-CMR-02 Revised

Prepared by:L. E. Harrison (Boeing) 8/96

SupeS. R. (Boei

MARCH 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 leakage and 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) 3/97

SupeS. R. (Boei

REVISIONS

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APRIL 1997 (Revision 7)Added revised safe life limits for the 777-200/-200 IGW landing gear components based on fatigue test cycles completed to date.

Prepared by:R. C. Moore (Boeing) 4/97

SuperviseS. R. Willi(Boeing) 4

SEPTEMBER 1997 (Revision 8)Added SSIs 53-30-I05 and 53-60-I06 to the 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) 9/97

Approved D. L. Rigg

MAY 1998 (Revision 9)Added SSIs for 777-200 IGW and -300 to the Airworthiness Limitations section.Amended “Related Tasks” in “Airworthiness Limitations – Structural Inspections” table to reflect revised task numbering system.Revised Scope and Airworthiness Limitations section wordings to standardize with 757 and 767 section wordings.Added CMR 72-CMR-03 for inspection of the main fan blades for evidence of cracking and CMR-28-CMR-01 to inspect FQIS wiring in the center fuel tank.

Submitted by:S. R. Williford (Boeing) 5/98

Approved D. L. Rigg

MAY 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 and airplane applicability.

Submitted by:S. R. Williford (Boeing) 5/98

Approved D. L. Rigg

REVISIONS

REVISION AND REVISION DESCRIPTION 

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MAY 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 the accumulation of over 200,000 flight hours of in-service data.

Submitted by:S. R. Williford (Boeing) 5/99

Appro

OCTOBER 1999 (Revision 12)Revised Airworthiness Limitations Structural Inspection 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 engine applicability. 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 and added airplane derivatives to sub-section C.2. Added PW4098 and Trent 895 engine designation to Section E. 

Submitted by:S. Pierini (Boeing) 10/99

Appro

OCTOBER 2000 (Revision 13)Revised to include the addition of the GE90-94B Powerplant applicability to 

Section E of the Certification Maintenance Requirements. In addition, in Section C.2 Life Limited Parts, the applicability for the Flight Deck Stowage Compartment Latch was clarified. The latch life limitation is not applicable to Production Line Numbers 282 and on or incorporation of SB 777-25-0140. 

Submitted by:S. Pierini (Boeing)10/00

Appro

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MARCH 2001 (Revision 14)Revised Life Limitation for 777-200 Main Landing Gear Door Actuator. Life Limitation is not applicable following incorporation of SB 777-32-0028 on 777-200 airplanes. There is no Life Limitation for actuators on the -2IGW or 300 airplanes.

Submitted by:S. Pierini (Boeing)

CANCELLED

(See Revision 21)

Approved A. Bahram

JULY 2002 (Revision 15)Added CMR 26-CMR-01 to inspect cargo fire bottles for leaks and apply Corrosion Inhibiting Compound to burst discs on fill fittings of cargo fire bottles.

Submitted by: Approved 

SEPTEMBER 2002 (Revision 16)Added CMR 52-CMR-01 applicable only to airplanes incorporating Boeing Service Bulletin 777-25-0216. This amended type certificate complies with the new 14 CFR 25.795 and the amended 14 CFR 25.772 as issued under Federal Register Docket No. FAA-2001-11032.

Submitted by: Approved 

NOVEMBER 2002 (Revision 17)Added Airworthiness Limitations 57-12-I02-1 and 57-12-I02-2 applicable to all airplanes L/N 423 and on due to design change. Revised statement in preamble to airworthiness limitations that specifies roll back 

of any escalated baseline structural inspection intervals when reaching the AWL Threshold.

Submitted by:S. A. Pierini (Boeing)

Approved 

JANUARY 2003 (Revision 18)Added L/N 427 and on applicability for 52-CMR-01.

Submitted by:S. A. Pierini (Boeing) 1/31/03

Approved 

REVISIONS

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JULY 2003 (Revision 19)Added SSIs 54-51-I07-a, b, c for Rolls Royce aluminum aft strut bulkheads to the Airworthiness Limitations. These SSIs are applicable to 777-200ER (200IGW) Rolls Royce Struts, Production Line Numbers 447 and on.

Submitted by:S. A. Pierini (Boeing) 

Appro

NOVEMBER 2003 (Revision 20)Added Section G which contains new airline operator reporting requirements for uncontrollable high thrust failure conditions or associated causal failures. This new section supports words added to the 777 Type Certificate Data Sheet stating occurrences of these subject failure conditions may endanger the safe operation of the airplane and hence are reportable under 121.703(c), 125.409 and 135.415. Section G contains a listing of these failures. Reference Exemption No. 7955 "Partial Exemption from 25.901(c) as it relates to uncontrollable high thrust.Deleted the related task field from the Airworthiness Limitations – Structural Inspection listing to be common with other Boeing models.Added an Applicability Note to clarify 26-CMR-01 requirement.Added "applicable to airplanes with -2 bottles installed, Line Numbers 410 

and on".Revised the 777-200/2IGW/300 Nose Landing Gear Structural Safe Life limit from 37,200 landings to 77,500 landings as a result of completion of further fatigue testing on the nose landing gear.Deleted reference to Service Letter 777-SL-32-001-E and added reference to Component Interchangeability Lists 161W0003 (Main Landing Gear) and 162W0002 (Nose Landing Gear) which provide a complete list of 777-200/-200 IGW/-300 landing gear related components subject to life limitations.

Submitted by:S. A. Pierini (Boeing)

ApproJeffre

REVISIONS

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MARCH 2004 (Revision 21)This revision includes changes to the format of the Airworthiness Limitations Structural Inspections table with more explicit airplane applicability information 

was added. “Flight length sensitive” AWLs were also identified in the new listing for the 777-300ER. Miscellaneous updates were made to non -300ER AWLs to correspond to the latest released SIPD information. Safe Life Limits for the Main 

Landing Gear, Main Landing Gear Support Fittings, and Nose Landing Gear were added for the 777-300ER. Specific safe life limits for the 777-300ER Nose Landing Gear Shock Strut components were also added. These components include; Upper Floating Piston, Upper Cylinder, Lower Cylinder, Metering Pin and Orifice Plate. This revision also includes the Life Limitation (2,000 cycles) for the 777-300ER Semi Lever Gear Hydraulic Strut (P/N 293W4201-2).Paragraph “G” "Reporting Uncontrollable High Thrust Failure Conditions" was also revised for the 777-300ER.Main landing gear door actuator life limitation applicability was clarified with the addition of a note. This addition thereby cancels Revision 14 of this document.26-CMR-01: Revised Airplane Note to clarify applicability. CMR is not applicable to -3 Bottles.

Submitted by:S. A. Pierini (Boeing)

Approved Jeffrey E. 

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 Jeffrey E. 

JULY 2004 (Revision 23)Revised 27-CMR-02 task interval from 100 FH to 250 FH based on the Primary Flight Control System (PFCS) Safety Analysis and service data reported by the airlines.

Submitted by:S. A. Pierini (Boeing)

Approved Jeffrey E. 

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DECEMBER 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 Next Generation Antenna installation incorporated in production.

Submitted by:S. A. Pierini (Boeing)

ApproJeffre

JUNE 2005 (Revision 25)Added SSI 57-53-I10 and 57-53-I11 applicable to all airplanes for the torque tube and inboard closeout rib fitting. The reason for the added SSIs is the damage tolerance category changed from a Category 2 to a Category 3.

Submitted by:S. A. Pierini (Boeing)

ApproJeffre

DECEMBER 2005 (Revision 26)Revised Airworthiness Limitations to add all Structural Significant Items (SSIs) for the 777-200LR. These changes support certification of the 777-200LR.

Submitted by:S. A. Pierini (Boeing)

ApproJeffre

REVISIONS

REVISION AND REVISION DESCRIPTION 

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JANUARY 2006 (Revision 27)Revised Airworthiness Limitations to add three new Structural Significant Items (SSIs) in the Structural Inspections Table to address a design change to the wing trailing edge flap support pins. Revised related DTR Check Form Titles to add applicability information for the existing flap pin design effective on L/N 504 and L/N 519.

Submitted by:S. A. Pierini (Boeing)

Approved Dorr M. A

FEBRUARY 2006 (Revision 28)Added new Airworthiness Limitations Numbers 28-AWL-19 and 28-AWL-20 to address inspection and repair of the Motor Operated Valve Actuators.

Submitted by:S. A. Pierini (Boeing)

Approved A. J. Pasi

MARCH 2006Revised the Applicability Table in Section B to clarify engine applicability information. Revised the Applicability section of the table shown in Section G to update the GE90 applicability to include 110B.Revised Fuel System Airworthiness Limitations to include paragraph (b) of the new standard introduced by § 25.981. Added 28-AWL-01 through 28-AWL-17 to 

the Airworthiness Limitations Table to satisfy SFAR 88 requirements.Revised 26-CMR-01 Airplane Note to remove reference to line numbers, as the installation of a -2 bottle is not line number dependent.Added text referencing the addition of Appendix L, “Post Threshold Intervals for Structures and Zonal Tasks”, to the MPD.

Submitted by:S. A. Pierini (Boeing)

Approved 

REVISIONS

REVISION AND REVISION DESCRIPTION 

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OCTOBER 2006Revised CMR 52-CMR-01 interval from 4 years to 2250 days to reflect the improved reliability data for the Flight Deck Door Strike Assembly.

Submitted by: S. A. Pierini (Boeing) Appro

DECEMBER 2006Revised applicability of fuel system airworthiness limitation number 28-AWL-20 to remove ITT actuator part number reference. The part number is listed in Service Bulletin 777-28A0034.Revised Airworthiness Limitations – Systems section introduction to include revisions recommended by the Seattle FAA Flight Standards group.

Submitted by: S. A. Pierini (Boeing) Appro

JUNE 2007Revised the Airworthiness Limitations – Structural Inspections table to update -200LR thresholds to cover new configuration.

Submitted by: (Boeing) Appro

REVISIONS

REVISION AND REVISION DESCRIPTION 

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SEPTEMBER 2007Added a new fuel system Airworthiness Limitation number 28-AWL-18 to incorporate an operational check of Fuel Pump Ground Fault Interrupter (GFI).Revised Section D. Airworthiness Limitations – Systems- Exceptional Short-Term Extensions to clarify notification requirements. Revised Section F. Certification Maintenance Requirements (CMRs) – Exception Short-Term Extensions to clarify notification requirements.Revised Paragraph “I” to incorporate “Reporting Uncontrolled High Thrust Failure Conditions” per FAR 121.703 and FAR 135.415.

Submitted by: B. McLoughlin (Boeing) Approved 

OCTOBER 2007Revised Section C.1. Structural Safe Life Parts and associated Figures 3 and 4 as per the changes submitted by Landing Gear Structures Design Center, Boeing. These changes reflect the latest landing gear safe life limit information contained in the revised landing gear interchangeability drawings (a) Main Gear Interchangeability List 161W0003 Revision E, and (b) Nose Gear Interchangeability List 162W0002 Revision E.Revised AWL 28-AWL-01 task description by removing "between reference to Sta 1035 to Sta 1045 and Zones 131 and 132" and adding "per Boeing AMM 28-11-00".Revised 28-AWL-18 interval from 1 YR to 375 DYS be consistent with 777 Program usage parameters.Revised Exceptional Short-Term Extensions for CMRs to clarify notification requirements for CMR 52-CMR-01.Revised CMR 52-CMR-01 interval from 2250 days to 3375 days to reflect the improved reliability data for the Flight Deck Door Strike Assembly and related 

updates to the exceptional short-term extensions information.

Submitted by: E. B. Lange (Boeing) Approved 

REVISIONS

REVISION AND REVISION DESCRIPTION 

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DECEMBER 2007Added new SSIs 28-00-I01A and 28-00-I01B that are applicable to 777-200LR aircraft with Auxiliary Fuel Tanks installed.Revised Section C.2, Life Limited Parts, to include 777-200LR Optional Auxiliary Body Fuel Tanks. Revised Section D. Airworthiness Limitations – Systems by adding a note to clarify that the auxiliary fuel tank complies with CFR 25.981, Amendment 25-102.Revised AWLs 28-AWL-11 through -14 and 18 to incorporate Auxiliary Fuel Tank 

information. Revised AWL 28-AWL-16 from "The following must be maintained during fuel tank access door installation" to "The following must be maintained during 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 aircraft with Auxiliary Fuel Tanks installed.

Submitted by: E. B. Lange (Boeing) Appro

FEBRUARY 2008Revised 28-AWL-03 to reflect the new maximum loop resistance values associated with the lightning protection of the unpressurized FQIS wire bundle installations so as to satisfy the Airworthiness Limitation Instructions required by SFAR 88. Also removed the joint resistance values based upon engineering review and operator maintenance practice.

Submitted by: J. Sabolchy (Boeing) Appro

NOVEMBER 2008Revised Section B., Airworthiness Limitations – Structural Inspections, by adding information regarding Individual Airplane Specific Airworthiness Limitations for aircraft L/N 740.

Submitted by: J. Sabolchy (Boeing) Appro

REVISIONS

REVISION AND REVISION DESCRIPTION 

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JANUARY 2009Revised the AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS Table to include references to the 777F, as well as additional, separate sections addressing threshold inspections for freighter and passenger aircraft.Revised the Airworthiness Limitations to incorporate the 777F configuration.Revised C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFE LIMITS to include life limits for the 777F aircraft.Revised G. PAGE FORMAT – CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs) table to include applicability 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 FAILURE CONDITIONS to incorporate 777F aircraft.

Submitted by: J. Onorati (Boeing) Approved 

FEBRUARY 2009Revised 28-AWL-02, 28-AWL-03, and 28-AWL-16 per the Approved Alternative Method of Compliance to Airworthiness Directive 2008-11-13.Revised 28-AWL-01 – 05, 28-AWL-07 – 08, 28-AWL-10, 28-AWL-13 – 16, and 28-AWL-19 – 23 by adding updates to enhance clarity of the Airworthiness Limitations.Revised Section F front matter by adding the Airworthiness Limitations – Nitrogen Generation System (NGS) requirements and by adding 47-AWL-01 – 47-AWL-06 NGS tasks.

Submitted by: J. Sabolchy (Boeing) Approved 

JANUARY 2010Revised the AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS Table to include updated inspection requirements for the 777-200/200LR/300/300ER aircraft as part of a planned re-assessment of the Supplemental Fatigue Inspection Program.

Submitted by: J. Onorati (Boeing) Approved 

S

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AUGUST 2010Revised Paragraph F. Airworthiness Limitations – Nitrogen Generation Systems Tasks by updating the following text "CDCCLs" with "AWLs (ALIs and CDCCLs)", "design limitations", and "Final Flammability Rule, Paragraph III(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 that have incorporated Service Bulletin 777-47-0002.Revised 47-AWL-01 and 47-AWL-05 by updating the Task Description to include instructions and a Note to clarify the procedure and parameters for the maintenance action.Revised 47-AWL-02 by replacing the text "replaced and installed" with "replaced or 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 "(refer to Boeing AMM 47-42-04)".Added 47-AWL-07, an identification of the maintenance standard for the Nitrogen Generation System and notice of potential future compliance requirements associated with decreased aircraft descent rates.

Submitted by: John Sabolchy (Boeing)

Appro 

JANUARY 2011Added CMR Number 32-CMR-01, a 50 flight or 25 day cycle, whichever occurs later, lubrication task for the left and right Main Landing Gear truck beam and inner cylinder pivot joints. Applicable to airplanes Line Number 915 and on or airplanes incorporating Boeing Service Bulletin 777-32-0085.

Submitted by: Mark Arnold (Boeing) Appro

 

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JULY 2011Revised 47-AWL-03 to incorporate NGS performance features to show compliance with 14 CFR 26.33.

Submitted by: Mark Arnold (Boeing)

Approved  

S

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A. SCOPE

The scheduled maintenance requirements described in this section result from Model 777 airplane certification activities with the U

Administration (FAA). Accordingly, this FAA approved Airworthiness Limitations and Certification Maintenance Requirements docureferenced in the Model 777 Type Certificate Data Sheet. These maintenance actions are mandatory. This Airworthiness Limitations Section is FAA approved and specifies maintenance required under Federal Aviation Regulation (Funless an alternative program has been FAA approved.AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSThe Airworthiness Limitations may only be revised with the approval of the Seattle FAA Aircraft Certification Office (ACO).If the inspections cannot be accomplished due to repairs and/or modifications, an alternate inspection approved by the Seattle FA

CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)These scheduled maintenance tasks may only be revised by the Seattle FAA ACO. Principal Maintenance Inspectors (local regul

change these requirements or the intervals associated with these requirements.

B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

INTRODUCTIONThe Structural Inspection Program approved in Section 3 of the 777 Maintenance Review Board (MRB) Report and contained in S

describes an initial baseline structural maintenance program for all Structural Significant Items (SSIs). This program was developthe guidelines of MSG-3 and partially satisfies the requirements of FAR 25.571 by providing accidental and environmental damage 

for all SSIs, and in some cases, fatigue damage detection opportunity. The supplemental structural inspections listed in this Secti

Limitations are for those SSIs that do not receive adequate fatigue damage detection opportunity from the initial baseline structura

Section 2. The supplemental inspections shown in Section 9 Airworthiness Limitations are to be accomplished in addition to the ba

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

necessary to provide adequate fatigue damage detection. The DTR system defines a required DTR (a numerical value) that SSI. DTR Check Forms which define the inspection options and the required DTR are contained in D622W001-DTR. One foThe supplemental inspections are not presently completely included in Section 2, but will be added at a future date. Until the 

incorporated into Section 2, the Structural Inspections Table defines the inspection items. Document D622W001-DTR define

methods and intervals.THRESHOLD (777-200/200LR/300/300ER Airplanes)The fatigue inspection requirements apply after accumulation of a certain number of flights (threshold). The initial fatigue insp

accomplished within one repeat interval of the threshold for 777-200/200LR/300/300ER and must never exceed 44,000 flightsthe 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 m

shown in the MPD Section 2. This means that any operator, who has escalated the structures program by changing task intefrequencies back to the MPD baseline structures program intervals before accumulating 40,000 flight cycles. The reason for 

damage tolerance evaluation takes credit for the baseline structures program. The Airworthiness Limitations listed in Section 

the required DTR is not met by the baseline structural inspections of Section 2. Any continued escalation beyond the MPD bamay result in additional structure not meeting the required 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 FAA aPrevention and Control Program (CPCP) has occurred, constituting CPCP implementation. The Corrosion Prevention and Co

the Structural Maintenance Program of the 777 Maintenance Review Board Report (D622W001-MRBR) is FAA approved.

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Additionally, some structures and zonal MPD items have been escalated by the Industry Steering Committee beyond the initial repat certification. The intervals listed in Appendix L correspond to the original task intervals used in determining the DTR which satis

result, at 40,000 flight cycles, the items listed in Appendix L are required to be returned to the interval in that appendix, rather than 

Sections 2 and 3. This is to be in compliance with the damage tolerance certification requirements.The Structural Inspections Table defines the Inspection Implementation Threshold for the 777-200/200LR/300/300ER. Some item

length and are identified by FLS in the Threshold column of the Structural Inspections Table (See Figure 1). Flight Length Sensitiv

both flight hours and flight cycles to determine the Implementation Threshold. Refer to Figure 1 to determine the threshold for FLS 

For the 777-200/200LR/300/300ER, SSIs are also categorized as Group (1) or Group (2). Group 1 SSI Inspection Thresholds are 30,000 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 length sensitive, the lowest threshold shown in the Structural Inspections Table is 30,000 fligh

requirement are: SSI 54-51-I02R, which has a threshold of 28,600 flights for the 777-200LR/300ER, and SSIs 28-00-I01A and 28-0of 11,250 flights for the 777-200LR airplanes that have the optional auxiliary fuel tank installations. All other 777-200LR/300ER ite

length sensitive have either a 30,000 flight threshold or 40,000 flight threshold depending upon whether the item is identified as G

minimum threshold for those items which are identified as flight length sensitive must be determined from Figure 1, based upon thutilization.A formal control system must be established for removable structural parts (repairable/rotable/expendables) which are subject to s

inspections, such as the flap support members. If part usage history data is available for all parts, the supplemental inspection proactual part usage history data. If part usage history data is not available, but records indicate that no part changes have occurred airplane usage history data can be used to start a tracking program for the supplemental inspections. If parts usage data is not av

could have been switched between airplanes in the same maintenance program, it should be assumed that the time on any part is 

airplane in the maintenance program. If a maintenance program includes airplanes from several operators, the oldest airplane in t

would be used as the oldest airplane in the maintenance program. After overhaul or upon replacement of a part, as appropriate, a 

be established to control the removable parts. This system must also apply to used structural parts which are purchased for instal

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FIGURE 1. FLIGHT LENGTH SENSITIVE (FLS) THRESHOLD CURVE (777-200/200LR/-30

USE OF FLIGHT LENGTH SENSITIVE THRESHOLD CURVE (777-200/200LR/300ER ONLY)(For FLS Items only; all non-FLS SSIs have thresholds as 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 

point is on, above, or to the right of the Threshold Curve for the specified group, then the Inspection Threshold has been 

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THRESHOLD (777F Airplanes)The fatigue inspection requirements apply after accumulation of a certain number of flights (threshold). The initial fatigue inspectio

accomplished at the threshold defined in the Structural Inspections Table, or within an interval not to exceed 2,500 flight cycles bethreshold for 777F aircraft fatigue inspections is 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 shown in the MPD Section 2. This means that any operator, who has escalated the structures program by changing task intervalsfrequencies back to the MPD baseline structures program intervals before accumulating 25,000 flight cycles. The reason for this i

damage tolerance evaluation takes credit for the baseline structures program. The Airworthiness Limitations listed in Section 9 co

the required DTR is not met by the baseline structural inspections of Section 2. Any continued escalation beyond the MPD baselimay result in additional structure not meeting the required 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 FAA approPrevention and Control Program (CPCP) has occurred, constituting CPCP implementation. The CPCP identified within the StructuProgram 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 repat certification. The intervals listed in Appendix L correspond to the original task intervals used in determining the DTR which satis

result, at 25,000 flight cycles, the items listed in Appendix L are required to be returned to the interval in that appendix, rather than 

Sections 2 and 3. This is to be in compliance with the damage tolerance certification requirements.The Structural Inspections Table defines the Inspection Implementation Threshold for the 777F. Some items are sensitive to flight 

by FLS in the Threshold column of the Structural Inspections Table (See Figure 2). Flight Length Sensitive (FLS) Items require bocycles to determine the Implementation Threshold. Refer to 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 Group 2 SSI Inspection Thresholds are limited to a maximum of 25,000 flight cycles.

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For those items which are not flight length sensitive, the lowest threshold shown in the Structural Inspections Table is 18,750 which are not flight length sensitive have either a 18,750 flight threshold or 25,000 flight threshold depending upon whether th

Group 1 or Group 2. The minimum threshold for those items which are identified as flight length sensitive must be determined the actual airplane utilization.

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FIGURE 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 thresholds as 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 Insp

point is on, above, or to the right of the Threshold Curve for the specified group, then the Inspection Threshold has been reach

FIGURE 10.2 FLIGHT LENGTH SENSITIVE (FLS) THRESHOLD CURVE 

FLIGHT HOURS ( x 1,000)

Group 1 & 2Threshold ExceededGroup 1 ThresholdExceeded

5

1015202530

FLIGHT CYCLES ( x 1,000) GROUP 1

GROUP 2

0

0 20 40 60 80 100 120 140 160

52.25 75

18.75

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REPEAT INSPECTION INTERVALA Repeat Interval for the Fatigue Inspection of an SSI is established from its respective Damage Tolerance Rating (DTR) Che

Forms are the result of the damage tolerance assessment / evaluation documented during certification of the airplane. Revis

Check Form or the DTR Curve is not allowed without the prior approval from the FAA Seattle Aircraft Certification Office (ACOFor -200/200LR/300ER/777F only: If the applicability/threshold box for the item includes a "< 7 Hrs" or "> 7 Hrs" designation, t

per flight should be calculated for the airplane and the repeat inspection interval should be based on the DTR Check Form wi"

< 7 Hrs" or "> 7 Hrs" label. If the current average hours per flight is longer than the prior average hours per flight, the current 

should be used for determining which DTR Check Form should be utilized.REPORTING RESULTS OF STRUCTURAL INSPECTIONSAll cracks found during these inspections shall be reported within ten (10) days directly to the Manager of the Seattle FAA AC

Directorate, the FAA, and to Boeing Commercial Airplane Group using the Discrepant Structure Report Form. Refer to D622Wreport form (any suitable alternative which contains 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 to sealant, remove any fastener cap, fillet 

beyond 0.20" around the fastener at locations that are to be inspected. Remove any additional sealant which impairs visibto the fastener cap, fillet or brush sealant.

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2. The following Structural Items require fastener cap, fillet or brush sealant that extends beyond 0.20" to be removed for baselin

inspections (MPD Section 2 and 3) at or prior to reaching the listed thresholds:

Principle Structural Element 

(PSE) Threshold

Installation 

Drawing Drawing Title Not

Fuselage – Underwing Longeron (777 All)

P: 40,000 FC 

F: 25,000 FC 

140W9250 Under Wing 

Longeron Instl

1) Fasteners on the Underwing LFuselage Front Spar Bulkhead Oforward of the Wing Front Spar. excess fillet seal at the free edge extends more than 0.25” from th2) Fasteners on the Underwing LWing Lower Skin within 3 inches Spar Bulkhead. In this area, also at the free edge of the longeron 0.25" from the lower wing skin suNote: Does not require sealant re

Fuselage – Front Spar Side Frame Fitting (777 All)

P: 40,000 FC 

F: 25,000 FC 

110W1652 Front Spar Instl 

Integration – BBL 122.45

Fasteners on the Front Spar Sid6 inches above and below the WNote: Does not require sealant re

Fuselage – Rear Spar Side Frame Fitting (777 All)

P: 40,000 FC 

F: 25,000 FC 

110W1651 Rear Spar Instl 

Integration – BBL 122.45

Fasteners on the Rear Spar Side 6 inches above and below the WNote: Does not require sealant re

Engine Strut – Pratt and Whitney(777-200/200IGW/300)

P: 40,000 FC 

F: 25,000 FC 

311W3110 (Fwd)

311W3130 (Aft)

Spar Assy – Fwd Upper Nacelle/StrutStrut Frame Assy – Aft

Fasteners on the LHS upper spaspar webs between NSTA 245.0 NSTA 319.0 and 333.0, except wvisible.

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Table Notes: P: = 777-200/-200IGW/-200LR/-300/-300ER (Passenger) airplanes

F: = 777F (Freighter) airplanesAs an option to sealant removal; if sealant does not extend beyond 0.50" from the fastener, perform surfa

around the fastener per NDT Part 6.

Principle Structural Element 

(PSE) Threshold

Installation 

Drawing Drawing Title 

Engine Strut – General Electric (777-200/200IGW)

P: 40,000 FC 

or 120,000 FH 

whichever 

comes first.

F: 25,000 FC 

or 120,000 FH 

whichever 

comes first

311W1110 (Fwd)

311W1130 (Aft)

Spar Assy – Fwd UpperTorque Box Assy – Aft

1) Fasteners on the RHS upupper spar web between NSfasteners on the RHS uppeforward engine mount bulkh192.0, except where spar c2) Fasteners on the LHS upbulkhead between NSTA 30spar chord is not visible.

Engine Strut – Rolls Royce(777-200/200IGW/300)

P: 40,000 FC 

F: 25,000 FC 

311W5110 (Fwd) Spar Assy – Fwd 

Upper

Fasteners on the upper spaengine mount bulkhead betexcept where spar chord is 

Horizontal Stabilizer – BL 0, Upper External Splice Plate (777 All)

P: 40,000 FC 

F: 25,000 FC 

182W7000 Splice Instl – 

Centerline, Horiz Stab

Fasteners on the Upper Extthe Rear Spar Terminal FittExternal Splice Fitting within 

Horizontal Stabilizer – BL 0, Upper Rear Spar External Splice Fitting (777 All)

P: 40,000 FC 

F: 25,000 FC 

182W7000 Splice Instl – 

Centerline, Horiz Stab

Fasteners on the Upper Recommon to the Rear Spar TExternal Splice Plate within 

Horizontal Stabilizer – BL 0, Rear Spar Terminal Fitting (777 All)

P: 40,000 FC 

F: 25,000 FC 

182W7500 Terminal Fitting 

Instl – Rear Spar, Horiz Stab

Fasteners on the Rear Spathe Upper Rear Spar ExternExternal Splice Plate within 

Wing – Side of Body Splice Upper Surface (777 All)

P: 40,000 FC 

or 120,000 FH 

whichever 

comes first.

F: 25,000 FC 

or 120,000 FH 

whichever 

comes first

110W1653 

(Inboard)

112W3301 

(Outboard)

Upper Panel Instl Integration – BBL 122.45Rib Chord Instl – Upper Panel, BBL 122.45

Fastener row on the Rib Chpanels both inboard and ouBBL 122.45.Note: Does not require seal

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3. 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 remo

If sealant is removed inside the fuel tank for inspection, care must 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 Bulletins or repair instructions) after completion of the inspections. Sealant of fuel tank fasteners must comply with MPD Sect

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SUPPLEMENTAL STRUCTURAL INSPECTION REQUIREMENTSThe table starting on the next page lists the Airworthiness Limitation supplemental structural inspection requirements. Each itDTR Check Form Title, DTR Location, and Airplane Applicability/Threshold. There are corresponding DTR Check Forms in Dlisted in the table. Where there is more than one listing for a given SSI Number, the DTR Check Form title and location is the 

Airplane applicability is listed as shown below (no entry implies 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, PW4098

GE = General Electric GE90 = 75B/76B/85B/90B/94B/110B/115B

NOTE: C/L or L/N = Airplane Cumulative Line Number, where mentioned with DTR Check Form Title, ide

DTR Check Forms to specific airplane line numbers.

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AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

27-41-I01 Safety Rod, Horizontal Stabilizer 

Trim Actuator

Zone 310, Section 48 1 30,000 30,000 30,000 30

27-41-I01 Safety Rod, Horizontal Stabilizer 

Trim Actuator

Zone 310, Section 48 1 

28-00-I01A Auxiliary Body Fuel Tanks Internal 

Corner Angles

Outer Angle around periphery of Forward Panel & Lower Side Panel Edges

1 

28-00-I01B Auxiliary Body Fuel Tank Inner Skin At Fastener Holes of Panels 

Connecting to Diaphragms

1 

52-10-I02 Passenger Doors Outer Skin and 

Structure

Outer Skin Between Handle and Window Cutouts

2 40,000 40,000 40,000 40

52-34-I03A Large Cargo Door Latch Support 

Frame Fittings

Latch Cam Support Fitting Lug Bore

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

52-34-I03B Large Cargo Door Latch Support 

Frame Fitting (135W1191)

Outer Chord 2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

52-34-I05A Large Cargo Door Latch Frame 

Inner Chord

Splice to Latch Support Fitting 1 30,000 

(8)

30,000 

(7)

30,000 

(7)

30

52-34-I05B Large Cargo Door Outer Skin at 

Attachment to Main Hinges

Outer Skin and Latch Frame Outer Chord

1 30,000 

(8)

30,000 

(7)

30,000 

(7)

30

52-37-I03A Large Cargo Door Latch Support 

Frame Fittings

Latch Cam Support Fitting Lug Bore

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

52-37-I03B Large Cargo Door Latch Support 

Frame Fitting (135W1191)

Outer Chord 2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

52-37-I05A Large Cargo Door Latch Frame 

Inner Chord

Splice to Latch Support Fitting 1 30,000 

(8)

30,000 

(7)

30,000 

(7)

30

52-37-I05B Large Cargo Door Outer Skin at 

Attachment to Main Hinges

Outer Skin and Latch Frame Outer Chord

1 30,000 

(8)

30,000 

(7)

30,000 

(7)

30

52-38-I01 Main Deck Cargo Door – Main 

Latch Cam Assemblies

Main Rotary Cam Latch – Cam Shaft

1 

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52-38-I03A Main Deck Cargo Door – Latch 

Cam and Roller Support Fittings

Latch Cam Support Fitting Lug Bore

2 

52-38-I03B Main Deck Cargo Door – Latch 

Cam and Roller Support Fittings

Latch Cam Support Fitting – Outer Chord

2 

52-38-I05A Main Deck Cargo Door – Latch 

Cam and Roller Support Fittings

Latch Cam Support Fitting – Latch Frame Inner Chord Splice to Latch Support Fitting

1 

52-38-I05B Main Deck Cargo Door – Skin and 

Door Structure

Outer Skin at Attachment to Main Hinges: Outer Skin and Latch Frame Outer Chord.

1 

53-00-I01 Upper Lobe Skin Panels Entire Fuselage – Skin BS 

132.5 to BS 2150 Above WL 200 Except Under Fairings

2 40,000 40,000 40,000 

53-00-I02 Lower Lobe Skin Panels Entire Fuselage – Skin BS 

132.5 to BS 2150 Below WL 200 Except Under Fairings

2 40,000 40,000 40,000 

53-00-I03 Upper and Lower Lobe Skin Panels Sections 43, 46, 47 – Skin 

Under Fairings

2 30,000 30,000 30,000 

53-10-I02A Crown Skin Antenna Installation – 

TCAS

Body Station 455.5 @ B.L. 0 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-10-I02B ACL Installation External Doubler Crown Skin STA 602, BL 0 

Under Stringer

2 30,000 

(8)

30,000 

(7)

30,000 

(7)

53-10-I02C ACL Installation External Doubler Crown Skin STA 602, BL 0 at 

Cutout

2 30,000 

(8)

30,000 

(7)

30,000 

(7)

53-10-I02D Crown Skin Production ACL 

Installation

Crown Skin STA 602.5, BL 0 2 40,000 40,000 40,000 

53-10-I06 Ground Maneuver Camera 

Installation

Lower Lobe STA 604.06 @ BL 0

2 40,000 

53-10-I07A Longitudinal Skin Lap Splices Inner 

Skin

Typical – All Section 41 Lap Splices

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

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53-10-I07B Longitudinal Skin Lap Splices Outer 

Skin

Typical – All Section 41 Lap Splices

2 40,000 40,000 40,000 40

53-10-I09A Passenger Entry Door #1 – Cutout Upper Corner @ STA 332.5 

and Lower Corner @ STA 382

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-10-I09B Passenger Entry Door #1 – Cutout Edge Frames @ STA 332.5 

and STA 382

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

53-10-I09C Passenger Entry Door #1 – Cutout Bear Strap 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-10-I09D Passenger Entry Door #1 – Cutout 

Upper Sill

Sta 309.5 to Sta 357.25 2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

53-10-I11A Forward Large Cargo Door – Cutout Upper Corner @ STA 501 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-10-I11B FWD Large Cargo Door – Cutout 

Outer Chord – Upper Sill

Body Station 592 to 613 1 30,000 

(8)

30,000 

(7)

30,000 

(7)

30

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

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

53-10-I14 Forward Equipment Bay Access 

Hatch Cutout Structure

STA 143.5 to 172.5 Forward of NLG Well

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-10-I16 E/E Bay Access Hatch Cutout 

Structure

STA 360 to 382 Aft of NLG Well 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-10-I18 NO. 1 Crew Window Cutout 

Structure

Lower Window Sill, Left and Right

2 40,000 40,000 40,000 40

53-10-I20 NO. 3 Crew Window Cutout 

Structure

EF Window Post Between Windows 2 & 3, Left & Right

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

53-10-I24 NLG Well Top Panel STA 246.2 Step Beam at BL 0 1 30,000 

(8)

30,000 

(7)

30,000 

(7)

30

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

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53-10-I25 WL 152 Beam (C/L 1 to 40) Nose Wheel Well Aft Bulkhead 

@ STA 332.5 LBL and RBL 30

1 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 30

1 30,000 

(8)

30,000 

(7)

30,000 

(7)

53-10-I26-1 Nose Wheel Well Cutout Structure

(C/L 1 to 40)

Forward End of Cutout LBL 30 to RBL 30

2 40,000 

(7)

53-10-I26-1 Nose Wheel Well Cutout Structure 

(C/L 41 and on)

Forward End of Cutout LBL 30 to RBL 30

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-10-I26-2 Nose Landing Gear Well Cutout 

(C/L 1 to 40)

STA 332.5 Aft End of Cutout 2 40,000 

(7)

53-10-I26-2 Nose Landing Gear Well Cutout 

(C/L 41 and on)

STA 332.5 Aft End of Cutout 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-10-I26-2 Nose Landing Gear Well Cutout STA 332.5 Aft End of Cutout 2 

53-10-I29-1 Nose Wheel Well Trunnion Support 

Fitting (C/L 1 to 40)

BS 320.5, WL 121 to WL 133, Left & Right Side Free Flange

2 40,000 

(8)

53-10-I29-1 Nose Wheel Well Trunnion Support 

Fitting (C/L 41 and on)

BS 320.5, WL 121 to WL 133, Left & Right Side Free Flange

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-10-I29-2 Nose Wheel Well Trunnion Support 

Fitting (C/L 1 to 40)

BS 320.5, Left and Right Side, WL 181, Side Panel to Top Panel Joint

2 40,000 

(8)

53-10-I29-2 Nose Wheel Well Trunnion Support 

Fitting (C/L 41 and on)

BS 320.5, Left and Right Side, WL 181, Side Panel to Top Panel Joint

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-10-I30 NLG Drag Brace Fitting – Lug and 

Bushing Interface

STA 260, WL 173, RBL/LBL 30 1 30,000 

(8)

30,000 

(7)

30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

53-30-I01A Crown Panel Skin/Stringer Cracking 

Under Radome

S-3L to S-3R, BS 755.5 to 846 2 40,000 40,000 40,000 40

53-30-I01B Longitudinal Skin Crack Under 

Radome

BS 755.5 to 846, S-3L to S-3R 2 30,000 30,000 30,000 30

53-30-I01C Longitudinal Skin Crack Under 

Antenna Attach Angle or Skin Lug Fittings

BS 755.5 to 846, BTWN S-3L and S-3R

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-30-I03 Fuselage Skin adjacent to Strakelet 

Attach Fitting (L/N 1-218)

STA 930 S-28 to S-30, STA 972 S-27 to S-29

2 30,000 

(8)

30,000 

(7)

30,000 

(7)

53-30-I03 Fuselage Skin adjacent to Strakelet 

Attach Fitting (L/N 219 and on)

STA 930 S-28 to S-30, STA 972S-27 to S-29

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

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)

53-30-I05-1 Fuselage Circumferential Skin/

Stringer Splice

BS 1035, Bulkhead Outer Chord

1 30,000 

(7)

30

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)

53-30-I05-2 Fuselage Circumferential Skin/

Stringer Splice

BS 1035, Stringer End Fasteners

2 40,000 

(7)

40

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)

53-30-I05-3 Fuselage Circumferential Skin/

Stringer Splice

BS 1035, Paddle Fitting End Fasteners

2 40,000 

(7)

40

53-30-I06A Longitudinal Skin Lap Splices Inner 

Skin (L/N 1-422)

Section 43 Lap Splices at S-14 2 30,000 

(8)

30,000 

(7)

30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

53-30-I06A Longitudinal Skin Lap Splices Inner 

Skin (L/N 423 and on)

Section 43 Lap Splices at S-14 2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-30-I06A Longitudinal Skin Lap Splices

Inner Skin

All Section 43 Lap Splices except S-14

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-30-I06B Longitudinal Skin Lap Splices

Outer Skin – Except Lower Row (S45)

Typical – All Section 43 Lap Splices

2 40,000 40,000 40,000 

53-30-I12A Passenger Entry Door #2 – Cutout Upper Corner @ STA 739 and 

Lower Corner @ STA 788.5

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-30-I12B Passenger Entry Door #2 – Cutout Edge Frames @ STA 739 and 

STA 788.5

2 40,000 

(8)

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)

53-30-I12D Passenger Entry Door #2 – Cutout 

Upper Sill

Upper Sill, STA 718 to STA 755.5

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-30-I12E Passenger Entry Door #2 – Cutout Lower Main Sill, STA 772 to 

STA 804

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-30-I13 Passenger Entry Door #2 – Cutout 

Door Stop Backup Fitting

Fittings #7A & 8A, #1A & #2A, 

STA 788.5

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-40-I01 Satcom Antenna – Circumferential 

Cracking with Broken Stringer

STA 1077 to STA 1119 at Stringer 10 to 12

1 30,000 

(8)

30,000 

(7)

53-40-I01 Skin and Stringer at SATCOM 

antenna installation

STA 1077 to STA 1119 at Stringer 10 to 12

2 40,000

53-40-I01 Crown Panel, Skin and Stringer 

Section 44

At Skin to Stringer Fastener Locations

2 

53-40-I03A Longitudinal Skin Lap Splices Inner 

Skin (L/N 1-450)

Section 44 Lap Splices at S-14 2 30,000 

(8)

30,000 

(7)

40,000 

(7)

53-40-I03A Longitudinal Skin Lap Splices Inner 

Skin (L/N 451 and on)

Section 44 Lap Splices at S-14 2 40,000 

(8)

40,000 

(7)

40,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

53-40-I03A Longitudinal Skin Lap Splices

Inner Skin

All Section 44 Lap Splices except at S-14

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

53-40-I03B Longitudinal Skin Lap Splices

Outer Skin

Typical – All Section 44 Lap Splices

2 40,000 40,000 40,000 40

53-40-I05 Front Spar Side Fitting Inner Chord 

Splice

BS 1035, Upper Crown Splice at Top Centerline and Stringer 21

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

53-40-I06-1 Rear Spar Side Fitting Inner Chord 

Splice

BS 1245, Ring Frame Splice at Stringer 12.5 and Stringer 21

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-40-I06-2 Rear Spar Side Fitting BS 1245, Inner Chord at 

Stringer 26

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-40-I06-3 Rear Spar Side Fitting at Seat 

Track Attachment

BS 1245 at Stringer 27, Fastener in Inner Chord

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-40-I07 Aft Wheel Well Bulkhead Inner 

Chord Splice

BS 1434, Upper Crown Slice at Top Centerline

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-40-I14A Passenger Entry Overwing Door 

#3 Cutout

Upper and Lower corners at 

STA 1154 and 1204

1 30,000 

(7)

30

53-40-I14B Passenger Entry Overwing Door 

#3 Cutout

Edge Frame Inner Chord and Web at STA 1154.4 and 1204

2 40,000 

(7)

40

53-40-I14C Passenger Entry Overwing Door 

#3 Cutout

Edge Frame Inner Chord at STA 1154.4 and 1204

2 40,000 

(7)

40

53-40-I14D Passenger Entry Overwing Door 

#3 Cutout

Edge Frame Straps at STA 1154.4 and 1204

2 40,000 

(7)

40

53-40-I14E Passenger Entry Overwing Door 

#3 Cutout Upper Main Sill

Upper Main Sill, STA 1140 to 1180

2 40,000 

(7)

40

53-50-I04-1 Aft Wheel Well Bulkhead Side 

Fitting Inner Chord Splice

BS 1434, Splice at Stringer 21 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-50-I04-2 Aft Wheel Well Bulkhead Side 

Fitting Outer Chord

BS 1434 From Stringer 28 to Stringer 45

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

53-50-I04-3 Aft Wheel Well Bulkhead Side 

Fitting Outer Chord

BS 1434 Lower Splice at Stringer 35 Strap and Outer Chord at Fasteners

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-50-I04-4 Aft Wheel Well Bulkhead Side 

Fitting Outer Chord

BS 1434 Lower Splice at Stringer 35 Outer Chord at Fasteners

1 30,000 

(8)

30,000 

(7)

30,000 

(7)

53-50-I04-5 Aft Wheel Well Bulkhead Horizontal 

Stiffeners (L/N 1-33)

Horizontal Stiffeners at WL 109 through 153, LBL5 – RBL5

2 30,000 

(8)

53-50-I04-5 Aft Wheel Well Bulkhead Horizontal 

Stiffeners (L/N 34 and on)

Horizontal Stiffeners at WL 109 through 153, LBL5 – RBL5

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-60-I01 Crown Panel, Skin and Stringer 

Section 46

At Skin to Stringer Fastener Locations

2 40,000 

(7)

40,000 

(7)

53-60-I01 Crown Panel, Skin and Stringer 

Section 46

At Skin to Stringer Fastener Locations

2 

53-60-I06-1 Fuselage Circumferential Skin/

Stringer Splice (L/N 75 – and on)

BS 1434, Bulkhead Outer Chord

1 30,000 

(8)

30,000 

(7)

53-60-I06-1 Fuselage Circumferential Skin/

Stringer Splice

BS 1434, Bulkhead Outer Chord

1 30,000 

(7)

53-60-I06-1 Fuselage Circumferential Skin/

Stringer Splice

BS 1434, Bulkhead Outer Chord

1 

53-60-I06-2 Fuselage Circumferential Skin/

Stringer Splice (L/N 75 – and on)

BS 1434, Stringer End Fasteners

2 40,000 

(7)

40,000

(7)

53-60-I06-2 Fuselage Circumferential Skin/

Stringer Splice

BS 1434, Stringer End Fasteners

2 40,000 

(7)

53-60-I06-2 Fuselage Circumferential Skin/

Stringer Splice

BS 1434, Stringer End Fasteners

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

53-60-I06-3 Fuselage Circumferential Skin/

Stringer Splice (L/N 75 – and on)

BS 1434, Paddle Fitting End Fasteners

2 40,000 

(8)

40,000 

(7)

53-60-I06-3 Fuselage Circumferential Skin/

Stringer Splice

BS 1434, Paddle Fitting End Fasteners

2 40,000 

(7)

40

53-60-I06-3 Fuselage Circumferential Skin/

Stringer Splice

BS 1434, Paddle Fitting End Fasteners

2 

53-60-I07A Longitudinal Skin Lap Splices Inner 

Skin (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 Inner 

Skin (L/N 423 and on)

Section 46 Lap Splices at S-5 2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

53-60-I07A Longitudinal Skin Lap Splices Inner 

Skin

All Section 46 Lap Splices except at S-5

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

53-60-I07B Longitudinal Skin Lap Splices

Outer Skin

Typical – All Section 46 Lap Splices

2 40,000 40,000 40,000 40

53-60-I12A Passenger Entry Door #3 (-200)/#4 

(-300) – Cutout

Section 46, Lower Corner @ STA 1497 and Upper Corner @ STA 1546.5

2 30,000 

(8)

40,000 

(7)

53-60-I12A Passenger Entry Door #3 (-

200IGW) Cutout

Section 46, Lower Corner @ STA 1497 and Upper Corner @ STA 1546.5

1 <= 7 Hrs, 

FLS, See 

Figure 1

 (7)

53-60-I12A Passenger Entry Door #3 (-200LR)/

#4 (-300ER) – Cutout

Section 46, Lower Corner @ STA 1497 and Upper Corner @ STA 1546.5

2 <= 7 

FLS

Fig

53-60-I12A Passenger Entry Door #3 (-

200IGW/200LR) / #4 (-300ER) 

Cutout

Section 46, Lower Corner @ 

STA 1497 and Upper Corner @ STA 1546.5

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

> 7 

FLS

Fig

 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

53-60-I12B Passenger Entry Door #3 (-200)/#4 

(-300) Cutout

Edge Frames @ STA 1497 and STA 1546.5

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-60-I12C Passenger Entry Door #3 (-200)/#4 

(-300) Cutout

Bear Strap 2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-60-I12D Passenger Entry Door #3 (-200)/#4 

(-300) – Cutout

Upper Main Sill, STA 1540 to STA 1567

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-60-I12E Passenger Entry Door #3 (-200)/#4 

(-300) – Cutout

Lower Main Sill, STA 1476 to STA 1513.5

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-60-I14A Small Cargo Door – Cutout Lower 

Main Sill

Body Station 1678.5 2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-60-I14B Small Cargo Door – Cutout Upper 

Main Sill

Body Station 1740 to 1769 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-60-I14C Small Cargo Door – Cutout Inner 

Chord – Edge Frames – STA 1678.5 and STA 1754.5

Stringers at Door Stop Fittings 2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-60-I14D Small Cargo Door – Cutout Inner 

Chord – Edge Frames – STA 1678.5 and STA 1754.5

Stringers away from Door Stop Fittings

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-60-I14E Small Cargo Door – Cutout Outer 

Chord – Edge Frames – STA 1678.5 and STA 1754.5

Stringers at Backup Fittings 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-60-I14F Small Cargo Door – Cutout Bear Strap 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-60-I16A Aft Large Cargo Door – Cutout Upper Corner @ STA 1790 2 30,000 

(8)

30,000 

(7)

30,000 

(7)

53-60-I16B Aft Large Cargo Door – Cutout 

Outer Chord – Upper Sill

Body Station 1683 to 1694 1 30,000 

(7)

30,000 

(7)

30,000 

(7)

53-60-I16C Aft Large Cargo Door – Upper Main 

Sill

STA 1769 to STA 1811 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

53-60-I20A Main Deck Cargo Door – Cutout – 

Corners

Upper Corner, STA 1790 Upper Corner, STA 1637.5Lower Corner STA 1637.5

1 

53-60-I20D Main Deck Cargo Door – Cutout 

Outer Chord Upper Sill

BS 1648 – 1673 & BS 1756 – 1780, S-6L

1 

53-70-I01 Crown Panel, Skin and Stringer 

Section 47

At Skin to Stringer Fastener Locations

2 

53-70-I04A Longitudinal Skin Lap Splices

Inner 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 Splices

Inner Skin (L/N 423 and on)

Section 47 Lap Splices at S-5 2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

53-70-I04A Longitudinal Skin Lap Splices

Inner Skin

All Section 47 Lap Splices except at S-5

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

53-70-I04B Longitudinal Skin Lap Splices

Outer Skin

Typical – All Section 47 Lap Splices

2 40,000 40,000 40,000 40

53-70-I07A Passenger Entry Door #4 (-200)/#5 

(-300) – Cutout

Edge Frames @ STA 2017 and STA 2067

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

53-70-I07B Passenger Entry Door #4 (-200)/#5 

(-300) – Cutout

Bear Strap 2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

53-70-I07C Passenger Entry Door #4 (-200)/#5 

(-300) – Cutout

Section 47, Upper Sill, STA 2050 to STA 2087

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-70-I07D Passenger Entry Door #4 (-200)/#5 

(-300) – Cutout

Section 47, Lower Sill, STA 2000 to STA 2017

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

40

53-70-I09 Bulk Cargo Door – Cutout Edge 

Frames

STA 1895 from Stringer S-33R to S-40R, STA 1937 from Stringer S-33R to S-35R

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

40

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

53-80-I13A Pressure Bulkhead at STA 2150; 

Sec 48 Lap Splice (L/N 1-3)(5 of 12 Lap Splices)

Gore Lap Splices – Web Surface Hidden Crack Fastener Row at Stiffener

1 30,000 

(8)

53-80-I13A Pressure Bulkhead at STA 2150; 

Sec 48 Lap Splice (L/N 1-422)

Gore Lap Splices – Web Surface Visible Crack Fastener Row at Stiffener

2 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 – Web Surface Visible Crack Fastener Row at Stiffener

2 40,000 

(8)

40,000 

(7)

40,000 

(7)

53-80-I13B Pressure Bulkhead at STA 2150; 

Sec 48 Circumferential Crack in Web at Radial Stiffener

Entire Dome Between Super Tear Straps

2 40,000 40,000 40,000 

53-80-I13C Pressure Bulkhead, STA 2150, 

Dome Web Attachment to Y-Ring (L/N 1-422)

Entire Dome Web Between Stiffeners

2 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 Between Stiffeners

2 40,000 

(8)

40,000 

(7)

40,000 

(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)

53-80-I14B Stabilizer Pivot Bulkhead STA 2370 

– Vertical Stiffeners

LH/RH Upper/Lower corner of cutout, BS 2370, LBL/RBL 15, WL 230/280

1 30,000 30,000 30,000 

53-80-I15 Stabilizer Pivot Fitting Lug; Section 

48

Station 2365 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

53-80-I17 Jackscrew Support Fitting Lug Section 48 Fin Support – 

Station 2245

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

54-51-I02A Aft Upper Spar Chord Splice (PW) Fasteners Common to the 

Chord, Splice and Side Skin from NSTA 298-308

1 30,000 

(8)

30,000 

(7)

30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

54-51-I02D Strut Upper Spar (PW) Upper Spar Left and Right 

Sides From NSTA 245 – NSTA 292

1 30,000 

(8)

54-51-I02D Strut Upper Spar (PW) Upper Spar Left and Right 

Sides From NSTA 245 – NSTA 292

1 30,000 

(7)

54-51-I02D Strut Upper Spar (PW) Forward Chords between NSTA 

245 and 292 Left and Right

1 30,000 

(7)

54-51-I03B Strut Side Skin (PW) Cutout at NSTA 317 to NSTA 

330 on Left and Right Side Skins

1 30,000 

(8)

54-51-I03B Strut Side Skin (PW) Cutout at NSTA 317 to NSTA 

330 on Left and Right Side Skins

1 <= 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I03B Strut Side Skin (PW) Cutout at NSTA 317 to NSTA 

330 on Left and Right Side Skins

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I03B Strut Side Skin (PW) Pressure Relief Door Cutout 

between NSTA 317 and 330

1 30,000 

(7)

54-51-I04A Lower Spar Chord (PW) Spar Chord from NSTA 242 to 

NSTA 248

1 30,000 

(8)

54-51-I04A Lower Spar Chord (PW) Spar Chord from NSTA 242 to 

NSTA 248

1 30,000 

(7)

54-51-I04A Lower Spar (PW) Spar Chord from NSTA 242 to 

NSTA 248

1 30,000 

(7)

54-51-I04D Lower Spar (PW) Fastener Locations on Lower 

Spar Common to Web and Chord, NSTA 261-281

1 30,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

54-51-I04D Lower Spar (PW) Fastener Locations on Lower 

Spar Common to Web and Chord, NSTA 261-281

1 30,000 

(7)

54-51-I04D Lower Spar (PW) Fastener Locations on Lower 

Spar Common to Web and Chord, NSTA 261-281

1 30,000 

(7)

54-51-I04F Lower Spar @ AEMB (PW) At Fasteners Common to 

Chord, Web, AEMB – Fwd and Aft of the Mount Attach Holes

1 30,000 

(8)

54-51-I04F Lower Spar @ AEMB (PW) At Fasteners Common to 

Chord, Web, AEMB – Fwd and Aft of the Mount Attach Holes

1 30,000 

(7)

54-51-I04F Strut Lower Spar (PW) Spar Chord at Aft Engine Mount 

Bulkhead between NSTA 298 and 310

1 30,000 

(7)

54-51-I05D Forward Engine Mount Bulkhead 

(PW)

Forward Flange @ 1.188 IN. Diameter GSE Holes, T = .45

1 30,000 

(8)

54-51-I05D Forward Engine Mount Bulkhead 

(PW)

Forward Flange @ 1.188 IN. Diameter GSE Holes, T = .60

1 30,000 

(8)

54-51-I05D Forward Engine Mount Bulkhead 

(PW)

Forward Flange at GSE Holes; T =.60

1 30,000 

(7)

54-51-I05D Strut Forward Engine Mount 

Bulkhead Assembly (PW)

Front Flange at open GSE Holes

1 30,000 

(7)

54-51-I08B Strut Aft Bulkhead (PW) At Fastener Common to the Aft 

Upper Spar Fitting, WL 153.46 to WL 164.99

1 30,000 

(7)

54-51-I09I PW4090 and PW4098 Forward 

Engine Mount Assembly (PW)

Forward Mount Thrust Link 1 30,000

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

54-51-I02B Upper Spar Bay 3 (GE) Upper Spar Between NSTA 230 

and NSTA 245

1 30,000 

(7)

<= 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I02B Upper Spar Bay 3 (GE) Upper Spar Between NSTA 230 

and NSTA 245

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I02E Strut Upper Spar Bay 5/6 at Cutout 

(GE)

Upper Spar in Bay 5/6 at Cutout NSTA 268 to NSTA 293

1 30,000 

(7)

54-51-I02E Strut Upper Spar Bay 5/6 at Cutout 

(GE)

Upper Spar in Bay 5/6 at Cutout NSTA 268 to NSTA 293

1 <= 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I02E Strut Upper Spar Bay 5/6 at Cutout 

(GE)

Upper Spar in Bay 5/6 at Cutout NSTA 268 to NSTA 293

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I02F Strut Upper Spar Bay 5 at Cutout 

(GE)

Side Skin in Bay 5 at Cutout NSTA 268 to NSTA 277

1 30,000 

(7)

54-51-I02F Strut Upper Spar Bay 5 at Cutout 

(GE)

Side Skin in Bay 5 at Cutout NSTA 268 to NSTA 277

1 <= 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I02F Strut Upper Spar Bay 5 at Cutout 

(GE)

Side Skin in Bay 5 at Cutout NSTA 268 to NSTA 277

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I02T Strut Upper Spar Bay 6 at Cutout 

(GE)

Side Skin in Bay 6 at Cutout NSTA 283 to NSTA 293 

1 30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

54-51-I02T Strut Upper Spar Bay 6 at Cutout 

(GE)

Side Skin in Bay 6 at Cutout NSTA 283 to NSTA 293

1 <= 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I02T Strut Upper Spar Bay 6 at Cutout 

(GE)

Side Skin in Bay 6 at Cutout NSTA 283 to NSTA 293 

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I02R Upper Spar (GE) Fasteners Common to Upper 

Chord, Web, Frames, @ NSTA213/230/245/265/280/295

1 30,000 

(7)

54-51-I02R Upper Spar (GE) Fasteners Common to Upper 

Chord, Web, Frames, @ NSTA213/230/245/265/280/295

1 30,000 

(7)

54-51-I02S Upper Spar (GE) Fastener Common to the Upper 

Chord and Web Between Frames at NSTA 245 and NSTA 265

1 30,000 

(7)

30,000 

(7)

54-51-I03B Side Skin Cutout (GE) Side Skin Cutout, NSTA 310 to 

NSTA 325

1 30,000 

(7)

<= 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I03B Side Skin Cutout (GE) Side Skin Cutout, NSTA 310 to 

NSTA 325

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I04A Lower Spar Bay 3 (GE) Bay 3 Fasteners Common to 

the Chord Between Frames at NSTA 230 and 245

1 30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

54-51-I04A Lower Spar Bay 3 (GE) Bay 3 Fasteners Common to 

the Chord Between Frames at NSTA 230 and 245

1 <= 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I04A Lower Spar Bay 3 (GE) Bay 3 Fasteners Common to 

the Chord Between Frames at NSTA 230 and 245

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I04B Lower Outboard Spar Chord at Aft 

Engine Mount Bulkhead (GE)

Lower Spar at Aft Engine Mount, NSTA 303 to NSTA 317

1 30,000 

(7)

30,000 

(7)

54-51-I04J Lower Spar @ Cutout (GE) Bay 2 Fasteners Common to 

the Chord and Web Between NSTA 212 and NSTA 230

1 30,000 

(7)

30,000 

(7)

54-51-I04M Lower Spar (GE) Frames NSTA 213, 230, 245, 

265, 280, and 295, LH and RH Sides

1 30,000 

(7)

54-51-I04M Lower Spar (GE) Frame NSTA 213, 230, 245, 

265, 280, and 295, LH and RH Side

1 30,000 

(7)

54-51-I05A Forward Engine Mount Bulkhead 

(GE)

Tension Fitting Gusset at NSTA 186.65

1 30,000 

(7)

30,000 

(7)

54-51-I01i Aft Upper Spar Fitting R4 (GE) Horizontal Flange First 

Fastener

1 > 7 

FLS

Fig

54-51-I02a Strut Upper Spar Bay 2 (GE) RH Web/Chord/Skin Between 

NS 213-230

1 30

54-51-I02b Strut Upper Spar Bay 3 (GE) LH and RH Chord and Web, 

NSTA 232-240

1 30

54-51-I02B Strut Upper Spar Bay 3 (GE) LH and RH Chord and Web, 

NSTA 232-240

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

54-51-I02c Strut Upper Spar Bay 3 (GE) Web Cutout at Sta 235-240 1 

54-51-I02e Strut Upper Spar Bay 5 (GE) Bay 5 Cutout Between NSTA 

268 and NSTA 277

1 

54-51-I02e Strut Upper Spar Bay 5 (GE) Bay 5 Cutout Between NSTA 

268 and NSTA 277

1 

54-51-I02e Strut Upper Spar Bay 5 (GE) Bay 5 Cutout Between NSTA 

268 and NSTA 277

1 

54-51-I02e Strut Upper Spar Bay 5 (GE) Bay 5 Cutout Between NSTA 

268 and NSTA 277

1 

54-51-I02f Strut Upper Spar Bay 6 (GE) Side Skin Between NSTA 281 

and NSTA 292

1 

54-51-I02f Strut Upper Spar Bay 6 (GE) Side Skin Between NSTA 281 

and NSTA 292

1 

54-51-I02f RHS Upper Spar Bay 6 (GE) Side Skin Between NSTA 281 

and NSTA 292

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

54-51-I02f RHS Upper Spar Bay 6 (GE) Side Skin Between NSTA 281 

and NSTA 292

1 

54-51-I02i Strut Upper Spar (GE) Upper Chord Splice Between 

NSTA 305 and NSTA 315

1 30

54-51-I02i Strut Upper Spar (GE) Upper Chord Splice Between 

NSTA 305 and NSTA 315

1 

54-51-I02m Strut Upper Spar (GE) R3/R4 Fitting Inboard Flange 1 <= 7 

FLS

Fig

54-51-I02m Strut Upper Spar (GE) R3/R4 Fitting Inboard Flange 1 > 7 

FLS

Fig

54-51-I02m Strut Aft Upper Spar (GE) R3/R4 Fitting Inboard Flange 1 

54-51-I02m Strut Aft Upper Spar (GE) R3/R4 Fitting Inboard Flange 1 

54-51-I02p Strut Upper Spar (GE) R1 Fitting Attachment NSTA 

225 to NSTA 268

1 30

54-51-I02p Pylon R1/Web Interface (GE) R1 Fitting – NSTA 188 to NSTA 

314

1 

54-51-I02u Pylon R1/Web Interface (GE) R1 Fitting – NSTA 188 to NSTA 

314

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

54-51-I02v Pylon R1/Web Interface (GE) R1 Fitting – NSTA 188 to NSTA 

314

1 

54-51-I02w Pylon R1/Web Interface (GE) R1 Fitting – NSTA 188 to NSTA 

314

1 

54-51-I02r Upper Spar Assembly (GE) Upper Spar Common to 

Frames/Bulkheads

1 

54-51-I02r Upper Spar Assembly (GE) Upper Spar Common to 

Frames/Bulkheads

1 

54-51-I02s Upper Spar Assembly (Bay 4) (GE) NSTA 245 to NSTA 264.6 1 

54-51-I02s Upper Spar Assembly (Bay 4) (GE) NSTA 245 to NSTA 264.6 1 

54-51-I02s Upper Spar Assembly (Bay 4) (GE) NSTA 245 to NSTA 265 1 

54-51-I03a Side Skin Cutout, Bay 8 (GE) Cutout at Bay 8 1 54-51-I03b Side Skin Cutout, Bay 8 (GE) NSTA 310 to NSTA 325 1 54-51-I03b Side Skin Cutout, Bay 8 (GE) Cutout at Bay 8 1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

54-51-I03b Side Skin Cutout, Bay 8 (GE) Cutout at Bay 8 1 

54-51-I03c Side Skin Cutout, Bay 8 (GE) NSTA 310 to NSTA 325 1 > 7 

FLS

Fig

54-51-I03C Side Skin Cutout, Bay 8 (GE) Cutout at Bay 8 1 

54-51-I03e Pylon Side Skin (GE) Side Skin Between NSTA 267 

and NSTA 278

1 

54-51-I03v Pylon Side Skin (GE) Side Skin Between NSTA 267 

and NSTA 278

1 

54-51-I03g Strut Side Skin Bay 4 (GE) NSTA 245 to NSTA 264.6 1 <= 7 

FLS

Fig

54-51-I03g Strut Side Skin Bay 4 (GE) NSTA 245 to NSTA 264.6 1 > 7 

FLS

Fig

54-51-I03g Pylon Side Skin (GE) Side Skin Between NSTA 247 

and NSTA 263

1 

54-51-I03w Pylon Chord (GE) Upper Spar Chord Between 

NSTA 247 and NSTA 263

1 

54-51-I03x Pylon Side Skin (GE) Side Skin Between NSTA 247 

and NSTA 263

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

54-51-I03i Side Skin Cutout (Bay 3) (GE) NSTA 230 to 245 1 

54-51-I03i Side Skin Cutout (Bay 3) (GE) NSTA 230 to 245 1 

54-51-I03I GE90-115B Side Skin Cutout (Bay 

3) (GE)

NSTA 230 to NSTA 245 1 

54-51-I03j Side Skin Cutout (Bay 2) (GE) NSTA 213.5 to NSTA 230 1 54-51-I03j Side Skin Cutout (Bay 2) (GE) NSTA 213.5 to NSTA 230 1 

54-51-I03j Side Skin Cutout Bay 2 (GE) NSTA 213.5 to NSTA 230.0, 

Skin and Upper Spar Chord

1 

54-51-I03j Side Skin Cutout Bay 2 (GE) NSTA 213.5 to NSTA 230.0, 

Skin and Upper Spar Chord

1 

54-51-I03k Side Skin Cutout (Bay 2) (GE) NSTA 213.5 to NSTA 230 1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

54-51-I03k Side Skin Cutout Bay 2 (GE) NSTA 213.5 to NSTA 230.0, 

Skin and Upper Spar Chord

1 

54-51-I03k Side Skin Cutout Bay 2 (GE) NSTA 213.5 to NSTA 230.0, 

Skin and Upper Spar Chord

1 

54-51-I03s Strut LH Side Skin Bay 4 (GE) NSTA 245 to NSTA 264.6, LHS 1 <= 7 

FLS

Fig

54-51-I03s Strut LH Side Skin Bay 4 (GE) NSTA 245 to NSTA 264.6, LHS 1 > 7 

FLS

Fig

54-51-I03s Bay 4 Upper Spar (GE) LHS NSTA 245 to NSTA 264 1 

54-51-I04a Strut Lower Chord (GE) Bays 2 and 3 RH Chord/Web, 

NSTA at 213-245

1 <= 7 

FLS

Fig

54-51-I04a Strut Lower Chord (GE) Bays 2 and 3 RH Chord/Web, 

NSTA at 213-245

1 > 7 

FLS

Fig

54-51-I04a Lower Spar Bay 3 (GE) Lower Spar Between NSTA 230 

and 245

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

54-51-I04a Lower Spar Bay 3 (GE) Lower Spar Between NSTA 230 

and 245

1 

54-51-I04b Strut Lower Chord Bay 3 (GE) LH Chord Between NSTA 230 

and 245

1 

54-51-I04b Strut Lower Chord Bay 3 (GE) LH Chord Between NSTA 230 

and NSTA 245

1 

54-51-I04b Strut Lower Chord Bay 3 (GE) LH Chord Between NSTA 230 

and NSTA 245

1 

54-51-I04c Strut Lower Spar (GE) Bay 3 Lower Spar Web Cutout 1 54-51-I04c Strut Lower Spar (GE) Bay 3 Lower Spar Web Cutout 1 

54-51-I04d Strut Lower Spar (GE) Bays 5, 6 and 7 LH Chord/Web, 

NSTA 264-309

1 

54-51-I04d Pylon Lower Spar (GE) LH Chord/Skin/Web Joint 

Between NSTA 266 and NSTA 278.5

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

54-51-I04s Pylon Side Skin (GE) LH Chord/Skin/Web Joint 

Between NSTA 266 and NSTA 278.5

1 

54-51-I04s Pylon Side Skin (GE) LH Chord/Skin/Web Joint 

Between NSTA 266 and NSTA 278.5

1 

54-51-I04e Pylon Lower Spar (GE) RH Chord/Skin/Web Joint 

Between NSTA 266 and NSTA 278.5

1 

54-51-I04e Pylon Lower Spar (GE) RH Chord/Skin/Web Joint 

Between NSTA 266 and NSTA 278.5

1 

54-51-I04t Pylon Side Skin (GE) RH Chord/Skin/Web Joint 

Between NSTA 266 and NSTA 278.5

1 

54-51-I04t Pylon Side Skin (GE) RH Chord/Skin/Web Joint 

Between NSTA 266 and NSTA 278.5

1 

54-51-I04f Pylon Lower Spar (GE) Bay 5 Lwr Spar Web Cutout 1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

54-51-I04f Pylon Lower Spar (GE) Bay 5 Lwr Spar Web Cutout 1 

54-51-I04g Strut Lower Spar (GE) Chord at Aft Engine Mount 

Bulkhead NSTA 303 to NSTA 317

1 

54-51-I04h RHS Lower Spar Chord-Web-Skin 

Joint (GE)

Bay 2, STA 213 to STA 230 1 

54-51-I04h RHS Lower Spar Chord-Web-Skin 

Joint (GE)

Bay 2, STA 213 to STA 230 1 

54-51-I04j Strut Lower Spar (GE) Bays 2 and 3 LH Chord 

NSTA 213-245

1 

54-51-I04j Strut Lower Spar (GE) Bays 2 and 3 LH Chord 

NSTA 213-245

1 

54-51-I04j LHS Lower Spar Chord-web-skin 

Joint (GE)

Bay 2 1 

54-51-I04j LHS Lower Spar Chord-web-skin 

Joint (GE)

Bay 2 1 

54-51-I04l Strut Lower Spar Bay 4 (GE) NSTA 245 to NSTA 264LHS 

and RHS Lower Spar

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

54-51-I04l Lower Spar Bay 4 (GE) NSTA 245 to NSTA 264LHS 

and RHS Lower Spar

1 

54-51-I04l Lower Spar Bay 4 (GE) NSTA 245 to NSTA 264LHS 

and RHS Lower Spar

1 

54-51-I04u Lower Spar Bay 4 (GE) NSTA 245 to NSTA 264LHS 

and RHS Lower Spar

1 

54-51-I04u Lower Spar Bay 4 (GE) NSTA 245 to NSTA 264LHS 

and RHS Lower Spar

1 

54-51-I04m Strut Lower Spar (GE) Chord STA at Bulkhead 1 <= 7 

FLS

Fig

54-51-I04m Strut Lower Spar (GE) Chord STA at Bulkhead 1 > 7 

FLS

Fig

54-51-I04r Strut Lower Spar (GE) Bays 5, 6, and 7 NSTA 264-309 1 <= 7 

FLS

Fig

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

54-51-I04r Lower Spar Chords/Web Bays 6-7 

(GE)

Lower Spar Chord Joint Between NSTA 280 and NSTA 308

1 

54-51-I04r Lower Spar Chords/Web Bays 6-7 

(GE)

Lower Spar Chord Joint Between NSTA 280 and NSTA 308

1 

54-51-I05a Strut Fwd Engine Mount Bulkhead 

(GE)

Gusset Edge 1 

54-51-I05a Strut Fwd Engine Mount Bulkhead 

(GE)

Gusset Upper Edge 1 

54-51-I05b Strut Fwd Engine Mount Bulkhead 

(GE)

Tension Fitting 1 

54-51-I05b Fwd Engine Mount Bulkhead (GE) Tension Fitting 1 54-51-I06a Strut Mid Bulkhead STA 295 (GE) Flange 1 

54-51-I06a Strut Mid Bulkhead STA 295 (GE) Flange 1 

54-51-I06b Strut Mid Bulkhead STA 295 (GE) R1 Attachment Pad @ Bolt 

Hole

1 

54-51-I07a Strut Aft Engine Mount Bulkhead 

(GE)

R1 Fitting Attachment 1 

54-51-I07a Aft Engine Mount Bulkhead (GE) R1 Fitting Fastener Attachment 1 

54-51-I07b Aft Engine Mount Bulkhead (GE) Engine Mount Tension Fitting 1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

54-51-I07d Strut Aft Engine Mount Bulkhead 

(GE)

Cutout Flange 1 <= 7 

FLS

Fig

54-51-I07d Strut Aft Engine Mount Bulkhead 

(GE)

Cutout Flange 1 > 7 

FLS

Fig

54-51-I07d Strut Aft Engine Mount Bulkhead 

(GE)

Cutout Flange 1 

54-51-I08b Aft Strut Bulkhead (GE) Aft Bulkhead from NWL 147 to 

NWL 162

1 

54-51-I08b Aft Strut Bulkhead (GE) Aft Bulkhead from NWL 147 to 

NWL 162

1 

54-51-I08d Aft Strut Bulkhead (GE) Forward Upper Flange NSTA 

325.33

1 <= 7 

FLS

Fig

54-51-I08d Aft Strut Bulkhead (GE) Forward Upper Flange NSTA 

325.33

1 > 7 

FLS

Fig

54-51-I08d Aft Strut Bulkhead (GE) Forward Upper Flange NSTA 

325.33

1 

54-51-I02A Upper Spar Chord (RR) Upper Spar Chord Splice Plate 

at NSTA 313 to NSTA 323

1 30,000 

(7)

30,000 

(7)

30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

54-51-I02C Forward Upper Spar (RR) Upper Spar at Frame/

Bulkheads

1 30,000 

(7)

30,000 

(7)

30,000 

(7)

54-51-I02D Forward Upper Spar (RR) Fasteners Common to the 

Upper Chord and Web, NSTA 223 to NSTA 294, non-frame locations

1 30,000 

(7)

30,000 

(7)

30,000 

(7)

54-51-I04A Lower Chord (RR) Lower Chord, Web at Aft 

Engine Mount Attachment Bolt Holes atNSTA 307.7, 309.9, 313.3, and 315.5

1 30,000 

(7)

30,000 

(7)

30,000 

(7)

54-51-I04B Aft Lower Chord at Aft Engine 

Mount Bulkhead (RR)

Fasteners Common to Chord and Web under Engine Mount Fitting, NSTA 305 to NSTA 317

1 30,000 

(7)

30,000 

(7)

54-51-I04B Aft Lower Spar Chord Under Engine 

Mount Bulkhead (RR)

Fasteners Common to Chord and Web under Engine Mount Fitting, NSTA 305 to NSTA 317

1 30,000 

(7)

54-51-I05A Forward Engine Mount Bulkhead 

(RR)

Fwd Engine Mount Bulkhead Tension Fitting End Pad

1 30,000 

(7)

30,000 

(7)

54-51-I05A Forward Engine Mount Bulkhead 

(RR)

Fwd Engine Mount Bulkhead Tension Fitting End Pad

1 30,000 

(7)

54-51-I06A Aft Engine Mount Bulkhead (RR) R1 Fitting Attach Tension 

Fitting

1 30,000 

(7)

54-51-I06A Aft Engine Mount Bulkhead (RR) R1 Fitting Attach Tension 

Fitting

1 30,000 

(7)

54-51-I06A Aft Engine Mount Bulkhead (RR) Upper Tension (Bathtub) Fitting 

End Pad

1 30,000 

(7)

54-51-I07B Strut Aft Bulkhead (RR) At Fastener Common to the Aft 

Upper Spar Fitting WL 148.26 to WL 159.29

1 30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

54-51-I07A,B Aluminum Aft Strut Bulkhead (RR) At Fasteners Common to the 

Aft Upper Spar from WL 148.26 to WL 159.29 and the Two Uppermost Fasteners Common to the R2 Fitting

1 30,000 

(7)

54-51-I07A,B Aluminum Aft Strut Bulkhead (RR) At Fastener Common to the Aft 

Upper Spar from WL 148.26 to WL 159.29 and the Two Uppermost Fasteners Common to the R2 Fitting

1 30,000 

(7)

54-51-I07C Aluminum Aft Strut Bulkhead (RR) Forward Upper Flange NSTA 

344.00

1 <= 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I07C Aluminum Aft Strut Bulkhead (RR) Forward Upper Flange NSTA 

344.00

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

54-51-I07C Aluminum Aft Strut Bulkhead (RR) Forward Upper Flange NSTA 

344.00

1 30,000 

(7)

55-12-I03 Upper Double Plus Chord 

Horizontal Stabilizer

BL 0.0 Skin/Stringer Splice 1 30,000 

(8)

30,000 

(7)

30,000 

(7)

55-12-I03 Upper Double Plus Chord 

Horizontal Stabilizer

BL 0.0 Skin/Stringer Splice 1 30

55-12-I03 Upper Double Plus Chord 

Horizontal Stabilizer

BL 0.0 Skin/Stringer Splice 1 

55-12-I07 Splice Fitting – F/S Upper Chord 

Horizontal Stabilizer

Inboard Jackscrew Attach Fastener at BL 4.2

1 30,000 

(8)

30,000 

(7)

30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

55-12-I07 Splice Fitting – F/S Upper Chord 

Horizontal Stabilizer

Inboard Jackscrew Attach Fastener at BL 4.2

1 

55-12-I07 Splice Fitting – F/S Upper Chord 

Horizontal Stabilizer

Inboard Jackscrew Attach Fastener at BL 4.2

1 

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 

55-17-I03A Pivot Fitting Lugs BL +/- 42 and Pivot Hinge Line 1 55-17-I03B Pivot Fitting Straps (Both Pairs – 

Upper and Lower)

BL +/- 42, WL 246 and 263, BS 2365

1 30,000 

(8)

30,000 

(7)

30,000 

(7)

55-17-I03B Pivot Fitting Straps Lower Strap BL +/- 42, WL 255, BS 2365 1 

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 

55-17-I03C Pivot Fitting Pins Outer Pin BL 42 and Pivot Hinge Line 1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

55-18-I01 Jackscrew Fitting, Lugs Dwg. 

182W7402

Back-to-Back Lugs BL +/- 5.0 WL 256.32

1 30,000 

(8)

55-18-I01 Jackscrew Fitting, Lugs Dwg. 

182W7402

Back-to-Back Lugs BL +/- 5.0 WL 256.32

1 30,000 

(7)

55-18-I01 Jackscrew Fitting, Lugs Dwg. 

182W7402

Back-to-Back Lugs BL +/- 5.0 WL 256.32

1 30,000 

(7)

55-18-I01 Jackscrew Fitting, Lugs Dwg. 

182W7402

Back-to-Back Lugs BL +/- 5.0 WL 256.32

1 30

55-18-I01 Jackscrew Fitting, Lugs Dwg. 

182W7402

Back-to-Back Lugs BL +/- 5.0 WL 256.32

1 

55-27-I03 Elevator Actuator Fitting 

183W1312,L/N 718 and on, and all retrofitted airplanes

Upper Middle Flange 1 30,000 

(8)

30,000 

(7)

30,000 

(7)

30

57-10-I02A SOB Splice, Lower Surface, TChord INBD and OBD Flanges of T- Chord 1 30,000 (8) 30,000 (7)

57-10-I02A SOB Splice, Lower Surface, TChord INBD and OBD Flanges of T- Chord 1 30,000 (7)

57-10-I02A SOB Splice, Lower Surface, TChord INBD and OBD Flanges of T- Chord 1 <= 7 

FLS

Fig

57-10-I02A SOB Splice, Lower Surface, TChord INBD and OBD Flanges of T- Chord 1 > 7 

FLS

Fig

57-10-I02A Side of Body Splice, Lower Surface Inboard and outboard flanges of 

the T-Chord at Stringer L-1

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-10-I02A Side of Body Splice, Lower Surface Inboard and outboard flanges of 

the T-Chord at Stringer L-1

1 

57-10-I02B SOB Splice, Lower Surface, TChord All Fasteners locations not covered by splice plate 1 30,000 (8) 30,000 (7)

57-10-I02B SOB Splice, Lower Surface, TChord All Fasteners locations not covered by splice plate 1 30,000 (7)

57-10-I02B SOB Splice, Lower Surface, TChord All Fasteners locations not covered by splice plate 1 

57-10-I02B SOB Splice, Lower Surface, TChord All Fasteners locations not covered by splice plate 1 

57-10-I02B Side of Body Splice, Lower Surface Inspect at all fastener locations 

not covered by the splice plate

1 

57-10-I02B Side of Body Splice, Lower Surface Inspect at all fastener locations 

not covered by the splice plate

1 

57-10-I02C SOB Splice, Lower Surface, TChord INBD 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, TChord INBD and OBD Flanges of T- chord @ Splice Plate (Str L1,L10,L14,L-20 and L-23) 1 30,000 (7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-10-I02C SOB Splice, Lower Surface, TChord INBD and OBD Flanges of T- chord @ Splice Plate (Str L1,L10,L14,L-20 and L-23) 1 <= 7 

FLS

Fig

57-10-I02C SOB Splice, Lower Surface, TChord INBD and OBD Flanges of T- chord @ Splice Plate (Str L1,L10,L14,L-20 and L-23) 1 > 7 

FLS

Fig

57-10-I02C Side of Body Splice, Lower Surface Inboard and Outboard flanges 

of T-chord at splice plate locations (Str L1,L-10,L14,L-20 and L-23)

1 

57-10-I02C Side of Body Splice, Lower Surface Inboard and Outboard flanges 

of T-chord at splice plate locations (Str L1,L-10,L14,L-20 and L-23)

1 

57-10-I03A SOB Splice, Front Spar, Chord Upper and Lower Front Spar 

Chords (INBD and OBD of SOB rib)

1 30,000 

(8)

<= 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-10-I03A SOB Splice, Front Spar, Chord Upper and Lower Front Spar 

Chords (INBD and OBD of SOB rib)

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-10-I03A SOB Splice, Front Spar, Chord Upper and Lower Front Spar 

Chords (INBD and OBD of SOB rib)

1 30,000 

(7)

57-10-I03A SOB Splice, Front Spar, Chord Upper and Lower Front Spar 

Chords (INBD and OBD of SOB rib)

1 <= 7 

FLS

Fig

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-10-I03A SOB Splice, Front Spar, Chord Upper and Lower Front Spar 

Chords (INBD and OBD of SOB rib)

1 

57-10-I03A Side of Body Splice, Front Spar Chords, Front Spar Lower and 

Upper Chords (Inboard and Outboard of SOB rib)

1 

57-10-I03A Side of Body Splice, Front Spar, 

Chord

Chords, Front Spar Lower and Upper Chords (Inboard and Outboard of SOB rib)

1 

57-10-I03B Side of Body Splice, Front Spar Skin, Front Spar Lower and 

Upper Chords (Inboard and Outboard of SOB rib)

1 

57-10-I03B Side of Body Splice, Front Spar Skin, Front Spar Lower and 

Upper Chords (Inboard and Outboard of SOB rib)

1 

57-10-I04A SOB Splice, Rear Spar, Chord Upper and Lower Rear Spar 

Chords (INBD and OBD of SOB rib)

1 30,000 

(8)

<= 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-10-I04A SOB Splice, Rear Spar, Chord Upper and Lower Rear Spar 

Chords (INBD and OBD of SOB rib)

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-10-I04A SOB Splice, Rear Spar, Chord Upper and Lower Rear Spar 

Chords (INBD and OBD of SOB rib)

1 30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-10-I04A SOB Splice, Rear Spar, Chord Upper and Lower Rear Spar 

Chords (INBD and OBD of SOB rib)

1 <= 7 

FLS

Fig

57-10-I04A SOB Splice, Rear Spar, Chord Upper and Lower Rear Spar 

Chords (INBD and OBD of SOB rib)

1 > 7 

FLS

Fig

57-10-I04A Side of Body Splice, Rear Spar Chords, Rear Spar Lower and 

Upper Chords (Inboard and Outboard of SOB rib)

1 

57-10-I04A Side of Body Splice, Rear Spar Chords, Rear Spar Lower and 

Upper Chords (Inboard and Outboard of SOB rib)

1 

57-10-I04B Side of Body Splice, Rear Spar Skin, Rear Spar Lower and 

Upper Chords (Inboard and Outboard of SOB rib)

1 

57-10-I04B Side of Body Splice, Rear Spar Skin, Rear Spar Lower and 

Upper Chords (Inboard and Outboard of SOB rib)

1 

57-12-I02-1 Body Chord Inspection at Stringer 

36 to 41

Front Spar Bulkhead, Station 1035, Stringer 36 to 41

1 30,000 

(8)

30,000 

(7)

30,000 

(7)

30

57-12-I02-2 Body Chord Inspection at Splice 

Plate

Front Spar Bulkhead, Station 1035 Stringer 38 to 39

1 30,000 

(8)

30,000 

(7)

30,000 

(7)

30

57-15-I01A Wing Center Section (WCS), Lower 

Panel Typical Stringer

Typical stringer on Lower Panel (WCS from SOB to SOB)

2 40,000 40,000

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-15-I01A Wing Center Section (WCS), Lower 

Panel Typical Stringer

Typical stringer on Lower Panel (WCS from SOB to SOB)

2 40,000

57-15-I01A Wing Center Section (WCS), Lower 

Panel Typical Stringer

Typical stringer on Lower Panel (WCS from SOB to SOB)

2 

57-15-I01A Wing Center Section (WCS), Lower 

Panel Typical Stringer

Typical stringer on Lower Panel (WCS from SOB to SOB)

2 

57-15-I01A Wing Center Section – Lower Panel 

– Typical Stringer

All WCS Lower Panel Typical Stringers from SOB to SOB

2 

57-15-I01A Wing Center Section – Lower Panel 

– Typical Stringer

All WCS Lower Panel Typical Stringers from SOB to SOB

2 

57-15-I01B Wing Center Section (WCS), Lower 

Panel Splice Stringer

Splice stringer on Lower Panel (WCS @ L10,L14, L20 from SOB to SOB)

2 40,000 40,000 40,000

57-15-I01B Wing Center Section (WCS), Lower 

Panel Splice Stringer

Splice stringer on Lower Panel (WCS @ L10,L14, L20 from SOB to SOB)

2 

57-15-I01B Wing Center Section – Lower Panel 

– Splice Stringer

All WCS Lower Panel Splice Stringers

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-15-I01B Wing Center Section – Lower Panel 

– Splice Stringer

All WCS Lower Panel Splice Stringers

2 > 7 

FLS

Fig

57-15-I01C Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Chord

Rear Spar Lower Chord (WCS from SOB to SOB)

2 40,000

57-15-I01C Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Chord

Rear Spar Lower Chord(WCS from SOB to SOB)

2 <= 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-15-I01C Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Chord

Rear Spar Lower Chord (WCS from SOB to SOB)

2 > 7 hrs 

FLS, See 

Figure 1 

(7)

57-15-I01C Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Chord

Rear Spar Lower Chord(WCS from SOB to SOB)

2 40,000 

(7)

57-15-I01C Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Chord

Rear Spar Lower Chord(WCS from SOB to SOB)

2 <= 7 

FLS

Fig

57-15-I01C Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Chord

Rear Spar Lower Chord (WCS from SOB to SOB)

2 > 7 

FLS

Fig

57-15-I01C Wing Center Section – Lower Panel 

Rear Spar Lower Chord

Chord, WCS Lower Panel Rear Spar Chord from SOB to SOB

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-15-I01C Wing Center Section – Lower Panel 

Rear Spar Lower Chord

Chord, WCS Lower Panel Rear Spar Chord from SOB to SOB

2 

57-15-I01D Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Skin

Rear Spar Lower Chord (WCS from SOB to SOB)

2 40,000

57-15-I01D Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Skin

Rear Spar Lower Chord (WCS from SOB to SOB)

2 <= 7 Hrs, 

FLS, See 

Figure 1

57-15-I01D Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Skin

Rear Spar Lower Chord(WCS from SOB to SOB)

2 > 7 hrs 

FLS, See 

Figure 1

57-15-I01D Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Skin

Rear Spar Lower Chord(WCS from SOB to SOB)

2 40,000 

(7)

57-15-I01D Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Skin

Rear Spar Lower Chord(WCS from SOB to SOB)

2 

57-15-I01D Wing Center Section (WCS), Lower 

Rear Spar Chord, Lower Skin

Rear Spar Lower Chord (WCS from SOB to SOB)

2 

57-15-I01D Wing Center Section – Lower Panel 

Rear Spar Lower Chord

Skin, WCS Lower Panel Rear Spar Chord from SOB to SOB

2 

57-15-I01D Wing Center Section – Lower Panel 

Rear Spar Lower Chord

Skin, WCS Lower Panel Rear Spar Chord from SOB to SOB

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-15-I01E Wing Center Section (WCS), Lower 

Panel Keel Beam Chord, Lower Skin

Lower Skin at Rear Spar Chord/Keel Attachment (LBL 15 to RBL 15)

1 30,000

57-15-I01E Wing Center Section (WCS), Lower 

Panel Keel Beam Chord, Lower Skin

Lower Skin at Rear Spar Chord/Keel Attachment (LBL 15 to RBL 15)

1 <= 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-15-I01E Wing Center Section (WCS), Lower 

Panel Keel Beam Chord, Lower Skin

Lower Skin at Rear Spar Chord/Keel Attachment (LBL 15 to RBL 15)

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-15-I01E Wing Center Section (WCS), Lower 

Panel Keel Beam Chord, Lower Skin

Lower Skin at Rear Spar Chord/Keel Attachment (LBL 15 to RBL 15)

1 30,000 

(7)

57-15-I01E Wing Center Section (WCS), Lower 

Panel Keel Beam Chord, Lower Skin

Lower Skin at Rear Spar Chord/Keel Attachment (LBL 15 to RBL 15)

1 <= 7 

FLS

Fig

57-15-I01E Wing Center Section (WCS), Lower 

Panel Keel Beam Chord, Lower Skin

Lower Skin at Rear Spar Chord/Keel Attachment (LBL 15 to RBL 15)

1 > 7 

FLS

Fig

57-15-I01E Wing Center Section Lower Panel – 

Keel Beam Chord Attachment

Skin, WCS Lower Panel Keel Beam Chord Attachment at the Rear Spar Chord

1 

57-15-I01E Wing Center Section Lower Panel – 

Keel Beam Chord Attachment

Skin, WCS Lower Panel Keel Beam Chord Attachment at the Rear Spar Chord

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-15-I01F Wing Center Section (WCS), Lower 

Panel Keel Beam Chord, Lower Chord

Rear Spar Chord at Keel Attachment (LBL 15 to RBL 15)

2 40,000 

(7)

40,000 

(7)

57-15-I01F Wing Center Section, Lower Panel 

– Keel Beam Chord, Lower Chord

Rear Spar Chord at Keel Attachment (LBL 15 to RBL 15)

2 40,000 

(7)

57-15-I01F Wing Center Section, Lower Panel 

– Keel Beam Chord, Lower Chord

Rear Spar Chord at Keel Attachment (LBL 15 to RBL 15)

2 

57-15-I01F Wing Center Section Lower Panel – 

Keel Beam Chord Attachment

Chord, WCS Lower Panel Keel Beam Chord Attachment at the Rear Spar Chord

2 

57-15-I01F Wing Center Section Lower Panel – 

Keel Beam Chord Attachment

Chord, WCS Lower Panel Keel Beam Chord Attachment at the Rear Spar Chord

2 

57-15-I01G Wing Center Section (WCS) Lower 

Front Spar Chord Lower Chord

Front Spar Lower Chord (WCS from BL 67 to BL103)

2 40,000 40,000 40,000 

57-20-I01A Wing Outboard, Typical Rear Spar 

Attachment, Lower Chord

Rear Spar Attachment from SOB to Rib 12 (Mid Rib)

2 40,000 

(8)

<=7hrs 

FLS See 

Figure 1 

(7)

57-20-I01A Wing Outboard, Typical Rear Spar 

Attachment, Lower Chord

Rear Spar Attachment from SOB to Rib 12 (Mid Rib)

2 >7hrs 

FLS See 

Figure 1 

(7)

57-20-I01A Wing Outboard, Typical Rear Spar 

Attachment, Lower Chord

Rear Spar Attachment from SOB to Rib 12 (Mid Rib)

2 40,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-20-I01A Wing Outboard, Typical Rear Spar 

Attachment, Lower Chord

Rear Spar Attachment from SOB to Rib 15 (Mid Rib)

2 <= 7 

FLS

Fig

57-20-I01A Wing Outboard, Typical Rear Spar 

Attachment, Lower Chord

Rear Spar Attachment from SOB to Rib 15 (Mid Rib)

2 > 7 

FLS

Fig

57-20-I01A Wing Outboard – Lower Panel Rear 

Spar Lower Chord

Chord, O/B Wing Lower Panel Rear Spar Chord from SOB to Rib 15 except at Ribpost locations

2 

57-20-I01A Wing Outboard – Lower Panel Rear 

Spar Lower Chord

Chord, O/B Wing Lower Panel Rear Spar Chord from SOB to Rib 15 except at Ribpost locations

2 

57-20-I01B Wing Outboard, Typical Rear Spar 

Attachment, Lower Chord

Rear Spar Chord Attachment from Rib 15 to Wingtip (Mid Rib)

2 <= 7 

FLS

Fig

57-20-I01B Wing Outboard, Typical Rear Spar 

Attachment, Lower Chord

Rear Spar Chord Attachment from Rib 15 to Wingtip (Mid Rib)

2 > 7 

FLS

Fig

57-20-I01B Wing Outboard – Lower Panel Rear 

Spar Lower Chord

Chord, O/B Wing Lower Panel Rear Spar Chord from SOB to Rib 15 except at Ribpost locations

2 

57-20-I01B Wing Outboard – Lower Panel Rear 

Spar Lower Chord

Chord, O/B Wing Lower Panel Rear Spar Chord from SOB to Rib 15 except at Ribpost locations

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-20-I01C Wing Outboard, Typical Rear Spar 

Attachment, Lower Skin

Rear Spar Chord Attachment at Trailing Edge fairing locations

2 

57-20-I01C Wing Outboard, Typical Rear Spar 

Attachment, Lower Skin

Rear Spar Chord Attachment at Trailing Edge fairing locations

2 

57-20-I01C Wing Outboard – Lower Panel Rear 

Spar Lower Chord

Skin, O/B Wing Lower Panel Rear Spar Chord at the trailing edge fairing locations

2 

57-20-I01C Wing Outboard – Lower Panel Rear 

Spar Lower Chord

Skin, O/B Wing Lower Panel Rear Spar Chord at the trailing edge fairing locations

2 

57-20-I01D Wing Outboard, Typical Splice 

Stringer

Stringer L10-L14 from SOB to Rib 36, L20 From Rib 8 to Rib 18

2 40,000 

(7)

57-20-I01D Wing Outboard, Typical Splice 

Stringer

Stringer L10-L14 from SOB to Rib 36, L20 From Rib 8 to Rib 18

2 <= 7 Hrs, 

FLS, See 

Figure 1

57-20-I01D Wing Outboard, Typical Splice 

Stringer

Stringer L10-L14 from SOB to Rib 36, L20 From Rib 8 to Rib 18

2 > 7 hrs 

FLS, See 

Figure 1

57-20-I01D Wing Outboard, Typical Splice 

Stringer

Stringer L10-L14 from SOB to Rib 36, L20 From Rib 8 to Rib 18

2 40,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-20-I01E Wing Outboard, Typical Splice 

Stringer

Stringer L10-L14 at Nacelle Fitting and Dry Bay Locations

2 <= 7 

FLS

Fig

57-20-I01E Wing Outboard, Typical Splice 

Stringer

Stringer L10-L14 at Nacelle Fitting and Dry Bay Locations

2 > 7 

FLS

Fig

57-20-I01E Outboard Wing – Lower Panel 

Splice Stringer

O/B Wing Lower Splice Stringers at the nacelle fairing and dry bay locations

2 

57-20-I01E Outboard Wing – Lower Panel 

Splice Stringer

O/B Wing Lower Splice Stringers at the nacelle fairing and dry bay locations

2 

57-20-I01F Wing Outboard, Typical Splice 

Stringer

Stringer L1 0- L14 at Nacelle Fitting, and L10 at Rib 30, 21 and 12

2 40,000 

(7)

57-20-I01F Wing Outboard, Typical Splice 

Stringer

Stringer L10 - L14 at Nacelle Fitting, and L10 at Rib 30, 21 and 12

2 <= 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-20-I01F Wing Outboard, Typical Splice 

Stringer

Stringer L10 - L14 at Nacelle Fitting, and L10 at Rib 30, 21 and 12

2 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-20-I01G Wing Outboard, Lower Panel Rear 

Spar Chord, Lower Chord

Rear Spar Chord Attachment from SOB to Rib 12 at Rib Post

1 30,000 

(8)

<= 7 Hrs, 

FLS, See 

Figure 1 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-20-I01G Wing Outboard, Lower Panel Rear 

Spar Chord, Lower Chord

Rear Spar Chord Attachment from SOB to Rib 12 at Rib Post

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-20-I01G Wing Outboard, Lower Panel Rear 

Spar Chord, Lower Chord

 Rear Spar Chord Attachment from SOB to Rib 12 at Rib Post

1 30,000 

(7)

57-20-I01G Wing Outboard, Lower Panel Rear 

Spar Chord, Lower Chord

Rear Spar Chord Attachment from SOB to Rib 15 at Rib Post

1 

57-20-I01G Wing Outboard, Lower Panel Rear 

Spar Chord, Lower Chord

 Rear Spar Chord Attachment from SOB to Rib 15 at Rib Post

1 

57-20-I01G Wing Outboard, Lower Panel Rear 

Spar Lower Chord

O/B Wing Lower Panel Rear Spar Chord from Rib 15 to wingtip at all ribpost locations

1 

57-20-I01G Wing Outboard, Lower Panel Rear 

Spar Lower Chord

O/B Wing Lower Panel Rear Spar Chord from Rib 15 to wingtip at all ribpost locations

1 

57-20-I01H Wing Outboard, Lower Panel Rear 

Spar Chord, Lower Chord

Skin and Rear Spar Web Attachment from Rib 15 to Wingtip at Rib Post

1 

57-20-I01H Wing Outboard, Lower Panel Rear 

Spar Chord, Lower Chord

Skin and Rear Spar Web Attachment from Rib 15 to Wingtip at Rib Post

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-20-I01H Wing Outboard, Lower Panel Front 

Spar Lower Chord

O/B Wing Lower Panel Front Spar Chord from Rib 15 to wingtip at all ribpost locations

1 

57-20-I01H Wing Outboard, Lower Panel Front 

Spar Lower Chord

O/B Wing Lower Panel Front Spar Chord from Rib 15 to wingtip at all ribpost locations

1 

57-20-I01J Wing Outboard, Lower Panel Front 

Spar Chord, Lower Chord

Skin to F/Spar Chord Attachment at Nacelle Fitting

1 30,000 

(8)

30,000 

(7)

57-20-I01J Wing Outboard, Lower Panel Front 

Spar Chord, Lower Chord

Skin to F/Spar Chord Attachment at Nacelle Fitting

1 30,000 

(7)

57-20-I01J Wing Outboard, Lower Panel Front 

Spar Chord, Lower Chord

Skin to F/Spar Chord Attachment at Nacelle Fitting

1 <= 7 

FLS

Fig

57-20-I01J Wing Outboard, Lower Panel Front 

Spar Chord, Lower Chord

Skin to F/Spar Chord Attachment at Nacelle Fitting

1 > 7 

FLS

Fig

57-20-I01J Wing Outboard, Lower Panel Front 

Spar Lower Chord

Chord, O/B Wing Lower Panel Front Spar Chord at the nacelle fitting attachment locations

1 

57-20-I01J Wing Outboard, Lower Panel Front 

Spar Lower Chord

Chord, O/B Wing Lower Panel Front Spar Chord at the nacelle fitting attachment locations

1 

57-20-I01K Wing Outboard, Lower Panel Front 

Spar Chord, Lower Skin

Skin to F/Spar Chord Attachment at Nacelle Fitting

1 <= 7 

FLS

Fig

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-20-I01K Wing Outboard, Lower Panel Front 

Spar Chord, Lower Skin

Skin to F/Spar Chord Attachment at Nacelle Fitting

1 

57-20-I01K Wing Outboard, Lower Panel Front 

Spar Lower Chord

Skin, O/B Wing Lower Panel Front Spar Chord at the nacelle fitting attachment locations

1 

57-20-I01K Wing Outboard, Lower Panel Front 

Spar Lower Chord

Skin, O/B Wing Lower Panel Front Spar Chord at the nacelle fitting attachment locations

1 

57-20-I01L1 Wing Outboard, Lower Panel Front 

Spar Chord, Lower Chord

Skin to F/Spar Chord Attachment from SOB to Wingtip except between Rib 30 to 44 and at Nacelle Fitting and Rib Post

2 

57-20-I01L2 Wing Outboard, Lower Panel Front 

Spar Chord, Lower Chord

Skin to F/Spar Chord Attachment from Rib 30 to Rib 44, except at Rib Post

2 

57-20-I01L Wing Outboard, Lower Panel Front 

Spar Chord, Lower Chord

Skin to F/Spar Chord Attachment from SOB to Wingtip except at Nacelle Fitting Attachment and Rib Post

2 

57-20-I01L Wing Outboard, Lower Panel Front 

Spar Lower Chord

Chord, O/B Wing Lower Panel Front Spar Chord from SOB to Wingtip except at ribpost locations

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-20-I01L Wing Outboard, Lower Panel Front 

Spar Lower Chord

Chord, O/B Wing Lower Panel Front Spar Chord from SOB to Wingtip except at ribpost locations

2 

57-20-I01M Wing Outboard, Lower Panel Front 

Spar Chord, Lower Chord

Skin to F/Spar Chord Attachment from SOB to Wingtip at all Rib Post

1 <= 7 

FLS

Fig

57-20-I01M Wing Outboard, Lower Panel Front 

Spar Chord, Lower Chord

Skin to F/Spar Chord Attachment from SOB to Wingtip at all Rib Post

1 > 7 

FLS

Fig

57-20-I01M Wing Outboard, Lower Panel Front 

Spar Lower Chord

Chord, O/B Wing Lower Panel Front Spar Chord from SOB to Wingtip at all ribpost locations

1 

57-20-I01M Wing Outboard, Lower Panel Front 

Spar Lower Chord

Chord, O/B Wing Lower Panel Front Spar Chord from SOB to Wingtip at all ribpost locations

1 

57-20-I01N Wing Outboard, MLG Beam 

Support Fitting, Mid Rib, Lower Skin

Wing Skin Tab-Out btwn Ribs 11 and 12 at MLG Beam Support Fitting

2 40,000 

(8)

40,000 

(7)

57-20-I01N Wing Outboard, MLG Beam 

Support Fitting, Mid Rib, Lower Skin

Wing Skin Tab-Out btwn Ribs 11 and 12 at MLG Beam Support Fitting

2 40,000 

(7)

57-20-I01N Wing Outboard, MLG Beam 

Support Fitting, Mid Rib, Lower Skin

Wing Skin Tab-Out btwn Ribs 11 and 12 at MLG Beam Support Fitting

2 <= 7 

FLS

Fig

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-20-I01N Wing Outboard, MLG Beam 

Support Fitting, Mid Rib, Lower Skin

Wing Skin Tab-Out btwn Ribs 11 and 12 at MLG Beam Support Fitting

2 

57-20-I01N Lower Panel – MLG Beam 

Outboard Support Fitting Attachment

All fastener locations common to the O/B Wing Lower Panel Skin tab and the MLG Beam Outboard Support Fitting

2 

57-20-I01N Lower Panel – MLG Beam 

Outboard Support Fitting Attachment

All fastener locations common to the O/B Wing Lower Panel Skin tab and the MLG Beam Outboard Support Fitting

2 

57-20-I01P Wing Outboard, Typical Stringer 

Attachment at Nacelle FTG

Typical stringers at Nacelle Fitting locations

2 40,000 

(7)

<= 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-20-I01P Wing Outboard, Typical Stringer 

Attachment at Nacelle FTG

Typical stringers at Nacelle Fitting locations

2 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-20-I01P Wing Outboard, Typical Stringer 

Attachment at Nacelle FTG

Typical stringers at Nacelle Fitting locations

2 40,000 

(7)

57-20-I01P Wing Outboard, Typical Stringer 

Attachment at Nacelle FTG

Typical stringers at Nacelle Fitting locations

2 

57-20-I01P Wing Outboard, Typical Stringer 

Attachment at Nacelle FTG

Typical stringers at Nacelle Fitting locations

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-20-I01P Outboard Wing – Lower Panel 

Typical Skin-Stringer Attachment

O/B Wing Lower Panel Typical Stringers at Nacelle Fairing Location

2 

57-20-I01P Outboard Wing – Lower Panel 

Typical Skin-Stringer Attachment

O/B Wing Lower Panel Typical Stringers at Nacelle Fairing Location

2 

57-20-I01Q Wing Outboard, Typical Rail 

Stringer at Access Door

Typical Rail Stringers at Access door from SOB to Wingtip except at Nacelle Fairing

2 40,000

57-20-I01Q Wing Outboard, Typical Rail 

Stringer at Access Door

Typical Rail Stringers at Access door from SOB to Wingtip except at Nacelle Fairing

2 > 7 

FLS

Fig

57-20-I01Q Outboard Wing – Lower Panel 

Typical Attachment at Access Door/Hole

Stringer, O/B Wing Lower Panel Rail Stringer from SOB to Wingtip except at the nacelle fairing

2 

57-20-I01Q Outboard Wing – Lower Panel 

Typical Attachment at Access Door/Hole

Stringer, O/B Wing Lower Panel Rail Stringer from SOB to Wingtip except at the nacelle fairing

2 

57-20-I01R Wing Outboard, Typical Rail 

Stringer at Access Door

Typical Rail Stringers at Access door at Nacelle Fairing

2 <= 7 

FLS

Fig

57-20-I01R Wing Outboard, Typical Rail 

Stringer at Access Door

Typical Rail Stringers at Access door at Nacelle Fairing

2 > 7 

FLS

Fig

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-20-I01R Outboard Wing – Lower Panel 

Typical Attachment at Access Door/Hole

Stringer, O/B Wing Lower Panel Rail Stringer at the Nacelle Fairing

2 

57-20-I01R Outboard Wing – Lower Panel 

Typical Attachment at Access Door/Hole

Stringer, O/B Wing Lower Panel Rail Stringer at the Nacelle Fairing

2 

57-20-I01S Outboard Wing – Lower Panel 

Splice at Rib 46

Fastener locations (inboard and outboard of Rib 46) common to the Lower Rib Chord and Lower Rear Spar Chord

2 

57-20-I01S Outboard Wing – Lower Panel 

Splice at Rib 46

Fastener locations (inboard and outboard of Rib 46) common to the Lower Rib Chord and Lower Rear Spar Chord

2 

57-20-I01T Outboard Wing – Lower Panel 

Splice at Rib 46

Fastener locations (inboard and outboard of Rib 46) common to the Lower Rib Chord and Paddle Fittings

1 

57-20-I01T Outboard Wing – Lower Panel 

Splice at Rib 46

Fastener locations (inboard and outboard of Rib 46) common to the Lower Rib Chord and Paddle Fittings

1 

57-20-I02A Wing Outboard, Upper Panel, MLG 

Beam Support Fitting, Upper Skin

Fastener locations C/T Upper Panel Skin Tab and MLG Beam SPRT FTG

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

57-20-I02A Wing Outboard, Upper Panel, MLG 

Beam Support Fitting, Upper Skin

Fastener locations C/T Upper Panel Skin Tab and MLG Beam SPRT FTG

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-20-I02A Upper Panel – MLG Beam 

Outboard Support Fitting Attachment

Fastener locations common to the O/B Wing Upper panel Skin Tab and the MLG Beam Outboard Support Fitting

2 

57-20-I02A Upper Panel – MLG Beam 

Outboard Support Fitting Attachment

Fastener locations common to the O/B Wing Upper panel Skin Tab and the MLG Beam Outboard Support Fitting

2 

57-20-I02B Wing Outboard, Upper Panel, Front 

Spar Upper Chord

F/Spar Upper Chord from Rib 8 to Rib 11 (MidRib)

2 40,000 <= 7 Hrs, 

FLS, See 

Figure 1

40,000

57-20-I02B Wing Outboard, Upper Panel, Front 

Spar Upper Chord

F/Spar Upper chords from SOB to Wingtip (MidRib)

2 > 7 Hrs, 

FLS, See 

Figure 1 

57-20-I02B Wing Outboard, Upper Panel, Front 

Spar Upper Chord

F/Spar Upper Chord from Rib 7 to Rib 11 (MidRib)

2 <= 7 

FLS

Fig

57-20-I02B Wing Outboard, Upper Panel, Front 

Spar Upper Chord

F/Spar Upper chords from SOB to Wingtip at Mid Rib except at F/Spar Splice between Rib 43 and Rib 44

2 > 7 

FLS

Fig

57-20-I02B Wing Outboard – Upper Panel, 

Front Spar Upper Chord

O/B Wing Upper Panel Front Spar Chord from SOB to Wingtip except at Ribpost locations

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-20-I02C Wing Outboard, Upper Panel, Front 

Spar Upper Chord

Front Spar Upper chords from SOB to Wingtip at Rib Post Location

1 

57-20-I02C Wing Outboard, Upper Panel, Front 

Spar Upper Chord

Front Spar Upper chords from SOB to Wingtip at Rib Post Location

1 

57-20-I02C Wing Outboard, Upper Panel, Front 

Spar Upper Chord

O/B Wing Upper Panel Front Spar Chord from SOB to Wingtip at all Ribpost Locations

1 

57-20-I02C Wing Outboard, Upper Panel, Front 

Spar Upper Chord

O/B Wing Upper Panel Front Spar Chord from SOB to Wingtip at all Ribpost Locations

1 

57-20-I02D Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

Rear Spar Upper Chord from SOB to Wingtip at Rib Post Location

1 30,000 

(8)

57-20-I02D Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

Rear Spar Upper Chord from SOB to Wingtip at Rib Post Location

1 <= 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-20-I02D Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

Rear Spar Upper Chord from SOB to Wingtip at Rib Post Location

1 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

57-20-I02D Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

Rear Spar Upper Chord from SOB to Wingtip at Rib Post Location

1 30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-20-I02D Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

Rear Spar Upper Chord from SOB to Wingtip at Rib Post Location

1 <= 7 

FLS

Fig

57-20-I02D Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

Rear Spar Upper Chord from SOB to Wingtip at Rib Post Location

1 > 7 

FLS

Fig

57-20-I02D Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

O/B Wing Upper Panel Rear Spar Chord from SOB to Wingtip at all Ribpost Locations

1 

57-20-I02D Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

O/B Wing Upper Panel Rear Spar Chord from SOB to Wingtip at all Ribpost Locations

1 

57-20-I02E Wing Outboard, Upper Panel, Rear 

Spar Upper Chord, Upper Skin

Rear Spar Upper Chord from Rib 8 to Rib 12

2 > 7 

FLS

Fig

57-20-I02E Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

O/B Wing Upper Panel Rear Spar Chord from Rib 8 to Rib 12 only

2 

57-20-I02E Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

O/B Wing Upper Panel Rear Spar Chord from Rib 8 to Rib 12 only

2 

57-20-I02F Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

Rear Spar Upper Chord from Rib 8 to Rib 11 (Mid Rib)

2 40,000 <= 7 Hrs, 

FLS, See 

Figure 1

40,000

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-20-I02F Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

Rear Spar Upper Chord from SOB to Wingtip (Mid Rib)

2 > 7 Hrs, 

FLS, See 

Figure 1 

57-20-I02F Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

Rear Spar Upper Chord from Rib 7 to Rib 11 (Mid Rib)

2 

57-20-I02F Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

Rear Spar Upper Chord from SOB to Wingtip (Mid Rib)

2 

57-20-I02F Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

O/B Wing Upper Panel Rear Spar Chord from SOB to Wingtip except at Ribpost

2 

57-20-I02F Wing Outboard, Upper Panel, Rear 

Spar Upper Chord

O/B Wing Upper Panel Rear Spar Chord from SOB to wingtip except at Ribpost

2 

57-20-I02G Wing Outboard, Upper Skin Tab Upper Skin Tab at fastener 

locations C/T Skin and R1 Fitting

2 40,000 40,000 40,000

57-20-I02H Wing Outboard, Upper Skin Nacelle 

Attachment Tab

Upper Skin Tab at fastener locations C/T Skin and F/Spar Chord

2 

57-20-I02H Upper Panel – Nacelle Attachment 

Tab

Fastener locations common to the O/B Wing Upper Panel Skin and Front Spar Upper Chord

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-20-I02H Upper Panel – Nacelle Attachment 

Tab

Fastener locations common to the O/B Wing Upper Panel Skin and Front Spar Upper Chord

2 

57-20-I02J Wing Outboard, Upper Panel, 

Typical Splice Stringer

Upper Panel Splice Stringers @ U-10, U24 from Rib 3 to Rib 15

2 40,000 40,000 40,000 40

57-20-I03A Wing Outboard, Rear Spar Web at 

FWD Trunnion Fitting

All Fastener locations C/T Rear Spar Chords and FWD Trunnion SPRT Fitting btwn Ribs 7 and 8

1 30,000 

(8)

30,000 

(7)

57-20-I03A Wing Outboard, Rear Spar Web at 

FWD Trunnion Fitting

All Fastener locations C/T Rear Spar Chords and FWD Trunnion SPRT Fitting btwn Ribs 7 and 8

1 30,000 

(7)

57-20-I03A Wing Outboard, Rear Spar Web at 

FWD Trunnion Fitting

All Fastener locations C/T Rear Spar Chords and FWD Trunnion SPRT Fitting btwn Ribs 7 and 8

1 <= 7 

FLS

Fig

57-20-I03A Wing Outboard, Rear Spar Web at 

FWD Trunnion Fitting

All Fastener locations C/T Rear Spar Chords and FWD Trunnion SPRT Fitting btwn Ribs 7 and 8

1 > 7 

FLS

Fig

57-20-I03A Rear Spar Web at Fwd Trunnion 

Support Fitting attachment

Fasteners at the Lower Rear Spar Chord and the Upper Rear Spar Chord common to the Rear Spar Web between Ribs 7 and 8

1 

57-20-I03A Rear Spar Web at Fwd Trunnion 

Support Fitting attachment

Fasteners at the Lower Rear Spar Chord and the Upper Rear Spar Chord common to the Rear Spar Web between Ribs 7 and 8

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-20-I04A Outboard Wing – Front Spar Splice 

between Ribs 43 and 44

Front Spar Splice between Ribs 43 and 44

1 

57-20-I04A Outboard Wing – Front Spar Splice 

between Ribs 43 and 44

Front Spar Splice between Ribs 43 and 44

1 

57-20-I06A Wing Box Flap Support FTG, Shear 

Tie Ribs

All Fastener locations C/T Flap Support Back-up Fittings and Shear Tie Ribs 12, 21, 30

2 

57-20-I06A Wing Box Flap Support Fitting at 

Shear Tie Rib #30

Fastener locations common to the Flap Support Back-up Fittings and Shear Tied Ribs

2 

57-20-I06A Wing Box Flap Support Fitting at 

Shear Tie Rib #30

Fastener locations common to the Flap Support Back-up Fittings and Shear Tied Ribs

2 

57-20-I11 112W5093 Back-up Fitting Typical 

Rib #9

Wing Station 414.5 2 

57-30-I01A Lower Panel- Wing Tip Splice at Rib 

50

Tension Bolts at Rear Spar 1 

57-30-I01B Lower Panel- Wing Tip Splice at Rib 

50

Tension Bolts at Front Spar 1 

57-30-I01C Lower Panel- Wing Tip Splice at Rib 

50

Fitting Pad at Front Spar 1 

57-30-I01D Lower Panel- Wing Tip Splice at Rib 

50

Lower Skin Attachment at Rear Spar

2 

57-53-I07A Inboard Main Flap Outboard 

Closeout Rib

Aft Access Hole 2 40,000 

(7)

40,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-53-I07A Inboard Main Flap Outboard 

Closeout Rib

Aft Access Hole 2 40,000 

(7)

57-53-I07A Inboard Main Flap Outboard 

Closeout Rib

Aft Access Hole 2 40

57-53-I07A Inboard Main Flap Outboard 

Closeout Rib

Aft Access Hole 2 

57-53-I07B Inboard Main Flap Outboard Ribs Aft Carrier Beam Attachments 2 40,000 

(7)

40,000 

(7)

40,000 

(7)

57-53-I07B Inboard Main Flap Outboard Ribs Aft Carrier Beam Attachments 2 

57-53-I10 Inboard Main Flap Torque Tube Cross-section just Outboard of 

Closeout Rib Splines

1 30,000 30,000 30,000 30

57-53-I10 Inboard Main Flap Torque Tube Cross-section just Outboard of 

Closeout Rib Splines

1 

57-53-I11A Inboard Main Flap Inboard Closeout 

Rib

Section thru Lower Chord at Forward Track Support

1 30,000 

(8)

57-53-I11A Inboard Main Flap Inboard Closeout 

Rib

Section thru Lower Chord at Forward Track Support

1 30,000 

(7)

57-53-I11A Inboard Main Flap Inboard Closeout 

Rib

Section thru Lower Chord at Forward Track Support

1 30,000 

(7)

57-53-I11A Inboard Main Flap Inboard Closeout 

Rib

Section thru Lower Chord at Forward Track Support

1 30

57-53-I11A Inboard Main Flap Inboard Closeout 

Rib

Section thru Lower Chord at Forward Track Support

1 

57-53-I11B Inboard Main Flap Inboard Closeout 

Rib

Section through Torque Tube Access Hole

1 30,000 

(8)

57-53-I11B Inboard Main Flap Inboard Closeout 

Rib

Section through Torque Tube Access Hole

1 30,000 

(7)

57-53-I11B Inboard Main Flap Inboard Closeout 

Rib

Section through Torque Tube Access Hole

1 30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-53-I11B Inboard Main Flap Inboard Closeout 

Rib

Section through Torque Tube Access Hole

1 

57-53-I11B Inboard Main Flap Inboard Closeout 

Rib

Section through Torque Tube Access Hole

1 

57-53-I11C Inboard Main Flap Inboard Closeout 

Rib Fitting

Spline Region 1 30,000 30,000 30,000 

57-53-I11C Inboard Main Flap Inboard Closeout 

Rib Fitting

Spline Region 1 

57-53-I16A No. 3 (and No. 6) Inboard Flap 

Support Underwing Fitting

Lugs, Outer Lug 1 30,000 

(8)

57-53-I16A No. 3 (and No. 6) Inboard Flap 

Support Underwing Fitting

Lugs, Outer Lug 1 30,000 

(7)

57-53-I16A No. 3 (and No. 6) Inboard Flap 

Support Underwing Fitting

Lugs, Outer Lug 1 30,000 

(7)

57-53-I16A No. 3 (and No. 6) Inboard Flap 

Support Underwing Fitting

Lugs, Outer Lug 1 

57-53-I16B No. 3 (and No. 6) Inboard Flap 

Support Underwing Fitting

Lugs, Inner Lug 1 30,000 

(8)

57-53-I16B No. 3 (and No. 6) Inboard Flap 

Support Underwing Fitting

Lugs, Inner Lug 1 30,000 

(7)

57-53-I16B No. 3 (and No. 6) Inboard Flap 

Support Underwing Fitting

Lugs, Inner Lug 1 30,000 

(7)

57-53-I16C No. 3 (and No. 6) Inboard Flap 

Support Underwing Fitting

Section at Aft Main Attach Bolt (Section C-C)

1 30,000 

(8)

57-53-I16C No. 3 (and No. 6) Inboard Flap 

Support Underwing Fitting

Section at Aft Main Attach Bolt (Section C-C)

1 30,000 

(7)

57-53-I16C No. 3 (and No. 6) Inboard Flap 

Support Underwing Fitting

Section at Aft Main Attach Bolt (Section C-C)

1 30,000 

(7)

57-53-I16C No. 3 (and No. 6) Inboard Flap 

Support Underwing Fitting

Section at Aft Main Attach Bolt (Section C-C)

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-53-I18A No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Aft Clevis Fillet, Inboard Lug 1 30,000 

(8)

57-53-I18A No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Aft Clevis Fillet, Inboard Lug 1 30,000 

(7)

57-53-I18B No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Center Section 2 40,000 

(8)

57-53-I18B No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Center Section 2 40,000 

(7)

57-53-I18B No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Center Section 2 40,000 

(7)

57-53-I18B No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Center Section 2 40

57-53-I18C No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Lugs 2 30,000 

(8)

57-53-I18C No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Lugs 2 30,000 

(7)

57-53-I18C No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Lugs 2 30,000 

(7)

57-53-I18C No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Lugs 2 30

57-53-I20A No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

Forward and Aft Lugs 2 40,000 

(8)

57-53-I20A No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

Forward and Aft Lugs 2 40,000 

(7)

57-53-I20A No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

Forward and Aft Lugs 2 40,000 

(7)

57-53-I20A No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

Forward and Aft Lugs 2 40

57-53-I20A No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

Aft Lug – Pin D (Forward and Aft Lugs)

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-53-I20B No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

General Section 2 40,000 

(8)

57-53-I20B No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

General Section 2 40,000 

(7)

57-53-I20B No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

General Section 2 40,000 

(7)

57-53-I20B,C No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

General Section (includes area around compression rod attachment point)

2 

57-53-I20C No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

Aft Section of Beam, area around compression rod attachment point

2 40,000 

(8)

57-53-I20C No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

Aft Section of Beam, area around compression rod attachment point

2 40,000 

(7)

57-53-I20C No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

Aft Section of Beam, area around compression rod attachment point

2 40,000 

(7)

57-53-I20C No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

Aft Section of Beam 2 

57-53-I21A No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Lug Cross-Sections 2 30,000 

(8)

57-53-I21A No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Lug Cross-Sections 2 30,000 

(7)

57-53-I21A No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Lug Cross-Sections 2 30,000 

(7)

57-53-I21A No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Lug Cross-Sections 2 

57-53-I21B No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Center Section thru Fastener 1 30,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-53-I21B No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Center Section thru Fastener 1 30,000 

(7)

57-53-I21B No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Center Section thru Fastener 1 30,000 

(7)

57-53-I21B No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Center Section thru Fastener 1 30

57-53-I23 No. 3 (and No. 6) Inboard Flap 

Support Drive Arm Assembly

3rd Fastener Row from Forward Inboard Side

1 30,000 

(8)

57-53-I23 No. 3 (and No. 6) Inboard Flap 

Support Drive Arm Assembly

3rd Fastener Row from Forward Inboard Side

1 30,000 

(7)

57-53-I24A No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Inboard Forward Arm 2 40,000 

(8)

57-53-I24A No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Inboard Forward Arm 2 40,000 

(7)

57-53-I24A No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Inboard Forward Arm 2 40,000 

(7)

57-53-I24A No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Inboard Forward Arm 2 40

57-53-I24B No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Cross-Over Beam 1 30,000 

(8)

57-53-I24B No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Cross-Over Beam 1 30,000 

(7)

57-53-I24B No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Cross-Over Beam 1 30,000 

(7)

57-53-I24C No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Flap Forward Attachment 1 30,000 

(8)

57-53-I24C No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Flap Forward Attachment 1 30,000 

(7)

57-53-I24C No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Flap Forward Attachment 1 30,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-53-I24C No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Flap Forward Attachment 1 

57-53-I24D No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Flap Aft Attachment 1 30,000 

(8)

57-53-I24D No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Flap Aft Attachment 1 30,000 

(7)

57-53-I24D No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Flap Aft Attachment 1 30,000 

(7)

57-53-I24D No.3 (and No. 6) Inboard Flap 

Support Carrier Beam

Flap Aft Attachment 1 

57-53-I24F No. 3 (and No. 6 Inboard Flap 

Support Carrier Beam

'B' Point Lug 1 30,000 

(8)

30,000 

(7)

30,000 

(7)

57-53-I24G No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

'C' Point Lug 1 30,000 

(8)

30,000 

(7)

57-53-I24G No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

'C' Point Lug 1 30,000 

(7)

57-53-I24G No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

'C' Point Lug 1 

57-53-I24G No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

'C' Point Lug 1 

57-53-I26A No. 3 (and No. 6) Inboard Flap 

Support 113W1027

Outer Pins A, B, and W 1 30,000 30,000 30,000 

57-53-I26B No. 3 (and No. 6) Inboard Flap 

Support 113W1027

Outer Pins C, D, X, and Y 1 30,000 30,000 30,000 

57-53-I27A No. 4 (and No. 5) Inboard Flap 

Support Drive Arm

Joint 'A' Pivot Hole 2 40,000 

(8)

57-53-I27A No. 4 (and No. 5) Inboard Flap 

Support Drive Arm

Joint 'A' Pivot Hole 2 40,000 

(7)

57-53-I27A No. 4 (and No. 5) Inboard Flap 

Support Drive Arm

Joint 'A' Pivot Hole 2 40,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-53-I27A No. 4 (and No. 5) Inboard Flap 

Support Drive Arm

Joint 'A' Pivot Hole 2 40

57-53-I27B No. 4 (and No. 5) Inboard Flap 

Support Drive Arm

'B' Point Lugs 2 40,000 

(8)

40,000 

(7)

57-53-I27B No. 4 (and No. 5) Inboard Flap 

Support Drive Arm

'B' Point Lugs 2 40,000 

(7)

57-53-I27B No. 4 (and No. 5) Inboard Flap 

Support Drive Arm

'B' Point Lugs 2 40

57-53-I28A No. 4 (and No. 5) Inboard Flap 

Support Actuator Support Fitting

Outboard Beam at 9.88 inches Aft of Point 'A'

2 40,000 

(8)

57-53-I28A No. 4 (and No. 5) Inboard Flap 

Support Actuator Support Fitting

Outboard Beam at 9.88 inches Aft of Point 'A'

2 40,000 

(7)

57-53-I28A No. 4 (and No. 5) Inboard Flap 

Support Actuator Support Fitting

Outboard Beam at 9.88 inches Aft of Point 'A'

2 40,000 

(7)

57-53-I28A No. 4 (and No. 5) Inboard Flap 

Support Actuator Support Fitting

Outboard Beam at 9.88 inches Aft of Point 'A'

2 40

57-53-I28B No. 4 (and No. 5) Inboard Flap 

Support Actuator Support Fitting

Point 'A' Lugs 2 40,000 

(8)

40,000 

(7)

57-53-I28B No. 4 (and No. 5) Inboard Flap 

Support Actuator Support Fitting

Point 'A' Lugs 2 40,000 

(7)

57-53-I28B No. 4 (and No. 5) Inboard Flap 

Support Actuator Support Fitting

Point 'A' Lugs 2 40

57-53-I29A No. 4 (and No. 5) Inboard Flap 

Support Carrier Beam

Section at Torque Tube Attachment Fitting

1 30,000 

(8)

57-53-I29A No. 4 (and No. 5) Inboard Flap 

Support Carrier Beam

Section at Torque Tube Attachment Fitting

1 30,000 

(7)

57-53-I29A No. 4 (and No. 5) Inboard Flap 

Support Carrier Beam

Section at Torque Tube Attachment Fitting

1 30,000 

(7)

57-53-I29A No. 4 (and No. 5) Inboard Flap 

Support Carrier Beam

Section at Torque Tube Attachment Fitting

1 30

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-53-I29B No. 4 (and No. 5) Inboard Flap 

Support Pillow Block

Section at Aft Fasteners 1 30,000 

(8)

57-53-I29B No. 4 (and No. 5) Inboard Flap 

Support Pillow Block

Section at Aft Fasteners 1 30,000 

(7)

57-53-I29B No. 4 (and No. 5) Inboard Flap 

Support Pillow Block

Section at Aft Fasteners 1 30,000 

(7)

57-53-I29B No. 4 (and No. 5) Inboard Flap 

Support Pillow Block

Section at Aft Fasteners 1 

57-53-I33 No. 4 (and No. 5) Inboard Flap 

Support Pins

Inner and Outer Pin B 1 30,000 30,000 30,000 

57-53-I34 No. 1 (and No. 8) Outboard Flap 

Support and No.2 (and No. 7) Outboard Flap Support

Underwing Fitting Inner and Outer Pins

1 30,000 

(8)

30,000 

(7)

30,000 

(7)

57-54-I17A MLG FWD Trunnion Sideload 

Fitting

All fastener locations C/T Sideload Fitting and Sideload Straps

2 40,000 

(7)

40,000 

(7)

57-54-I17A MLG FWD Trunnion Sideload 

Fitting

All fastener locations C/T Sideload Fitting and Sideload Straps

2 40,000 

(7)

57-54-I17B MLG FWD Trunnion Sideload 

Straps

All Fastener Locations C/T Upper/Lower Strap and INBD O/B Vertical Support Fitting

2 40,000 40,000

57-54-I17B MLG FWD Trunnion Sideload 

Straps

All Fastener Locations C/T Upper/Lower Strap and INBD O/B Vertical Support Fitting

2 40,000

57-54-I17C MLG FWD Trunnion Outboard 

Support Fitting, R/S Attach Fitting Flange

All Fasteners Locations C/T 112W1702 and 112W1704 FTG and R/Spar Web

2 40,000 <= 7 Hrs, 

FLS, See 

Figure 1

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-54-I17C MLG FWD Trunnion Outboard 

Support Fitting, R/S Attach Fitting Flange

All Fasteners Locations C/T 112W1702 and 112W1704 FTG and R/Spar Web

2 > 7 Hrs, 

FLS, See 

Figure 1 

(7)

40,000 

(7)

57-54-I17C MLG FWD Trunnion Outboard 

Support Fitting, R/S Attach Fitting Flange

All Fasteners Locations C/T 112W1702 and 112W1704 FTG and R/Spar Web

2 <= 7 

FLS

Fig

57-54-I17C MLG FWD Trunnion Outboard 

Support Fitting, R/S Attach Fitting Flange

All Fasteners Locations C/T 112W1702 and 112W1704 FTG and R/Spar Web

2 > 7 

FLS

Fig

57-54-I17C 112W1704, MLG FWD Trunnion 

Support Fitting

Section A-A, Spar Flange Crack 2 

57-54-I17C 112W1704, MLG FWD Trunnion 

Support Fitting

Section A-A, Spar Flange Crack 2 

57-54-I18A MLG Beam OBD Support FTG, Lwr 

Skin Flange

All fastener holes locations C/T Lower flange and Lower Skin Panel

2 40,000 40,000

57-54-I18A MLG Beam OBD Support FTG, Lwr 

Skin Flange

All fastener holes locations C/T Lower flange and Lower Skin Panel

2 40,000 

(7)

57-54-I18B MLG Beam OBD Support FTG, 

Fitting

Lower Horizontal Rib of MLG Beam Support Fitting @ Fastener Hole

2 40

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-54-I18B 112W1722, MLG Beam Outboard 

Support Fitting

Lower Horizontal Rib, Section A-A Lead crack at fastener hole

2 

57-54-I18B 112W1722, MLG Beam Outboard 

Support Fitting

Lower Horizontal Rib, Section A-A Lead crack at fastener hole

2 

57-54-I18C MLG Beam OBD Support FTG, 

Fitting

Lower Horizontal Rib of MLG Beam Support Fitting @ Free Edge

2 

57-54-I18C 112W1722, MLG Beam Outboard 

Support Fitting

Lower Horizontal Rib, Section A-A Lead Crack at Free Edge

2 

57-54-I18C 112W1722, MLG Beam Outboard 

Support Fitting

Lower Horizontal Rib, Section A-A Lead Crack at Free Edge

2 

57-54-I19A MLG Drag Brace Support Fitting Section A-A Fitting Flange 2 40,000 

(8)

40,000 

(7)

57-54-I19A MLG Drag Brace Support Fitting Section A-A Fitting Flange 2 40,000 

(7)

57-54-I19A MLG Drag Brace Support Fitting Section A-A Fitting Flange 2 

57-54-I19A 112W1752, MLG Drag Brace 

Support Fitting

Section A-A Flange Crack 2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-54-I19A 112W1752, MLG Drag Brace 

Support Fitting

Section A-A Flange Crack 2 

57-54-I19B MLG Drag Brace Support Fitting, 

Base of Fitting

Section A-A Fastener Locations C/T Base of fitting and Rear Spar Web

2 40,000 

(7)

40,000 

(7)

40,000 

(7)

57-54-I19B MLG Drag Brace Support Fitting, 

Base of Fitting

Section A-A Fastener Locations C/T Base of fitting and Rear Spar Web

2 40

57-54-I19B 112W1752, MLG Drag Brace 

Support Fitting

Section A-A Base Crack 2 

57-54-I19B 112W1752, MLG Drag Brace 

Support Fitting

Section A-A Base Crack 2 

57-54-I19C MLG Drag Brace Internal Backup 

Fitting

Entire Fitting C/T SOB Rib and Rear Spar, including Stiffening Ribs

2 40,000

57-54-I19C MLG Drag Brace Internal Backup 

Fitting

Entire Fitting C/T SOB Rib and Rear Spar, including Stiffening Ribs

2 <= 7 

FLS

Fig

57-54-I19C MLG Drag Brace Internal Backup 

Fitting

Entire fitting c/t SOB Rib and Rear Spar, including Stiffening Ribs

2 > 7 

FLS

Fig

57-54-I19C 112W1756, MLG Drag Brace 

Support Back-up Fitting

Section A-A, Lead Crack in Base

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/THR

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 -30

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-54-I19C 112W1756, MLG Drag Brace 

Support Back-up Fitting

Section A-A, Lead Crack in Base

2 

57-54-I20 Retraction Actuator Support Fitting, 

Fitting Attach Flange

Rear Spar Attach Flange 2 40,000 40,000 40,000 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/

SSI # (2) DTR CHECK FORM TITLE (3) DTR LOCATION -200 -200IGW -300 

JAN 2010
777 MAINTENANCE PLANNING DATA

D622W001-9

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

TABLE 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 identified by Check Form Title, Location, and Model-Series Information. All i

single 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., “> 7 Hrs, FLS, See Figure 1 or Figure 2”) are sensitive to flight le

shown are in flight cycles.

7. No airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedures are v

appropriate 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 that 

inspection procedures can be accomplished and the inspection has been accomplished per the stated threshold requirements

published inspection procedure can not be accomplished, an alternative procedure must be used which the FAA has accepted 

JAN 2010
D622W001-9

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

777 MAINTENANCE PLANNING DATA

INDIVIDUAL AIRPLANE SPECIFIC AIRWORTHINESS LIMITATIONSPURPOSEThe purpose of this section is to identify additional or revised Supplemental Structures Airworthiness Limitation (AWL) Structuunique to a specific airplane serial number. Only those individual airplanes listed in this section have these additional or revis

or 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 air

Production Line/Serial Number, SSI Number, DTR Check Form Title, DTR Location, Inspection Requirements and Threshold

LINE 

NUMBER/

SERIAL 

NUMBER SSI NUMBER DTR CHECK FORM TITLE

DTR 

LOCATION INSPECTION REQUIREMEN

L/N 740

S/N 37666

53-80-I13-MRB1 Pressure Bulkhead STA 

2150; Section 48; Material Review Board Web Disposition for Nonconformance Record (NCR): N1780061195; Aft Side Doubler/Filler

STA 2190,

WL 264, 

BL LBL 27 

1. Inspect the pressure bulkhead web at al

common to web and NCR doubler/filler frside (except at radial stiffener) with HFEDestructive Test (NDT) Manual, Part 6, 51-00-01 every 16,000 flight cycles.

2. Inspect the NCR doubler/filler at all faste

to pressure bulkhead web and NCR douthe aft side with HFEC per 777 NDT Man51-00-01 every 16,000 flight cycles.

3. All other Supplemental Inspections requ

80-I13 in the preceding section must stilexcept at the fastener locations common doubler and filler.

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C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE LIFE LIMITS

C.1 STRUCTURAL SAFE LIFE PARTS

LANDING GEAR: See Note LAN

777-200/-200IGW/-300 Nose Landing Gear 7 Except: Inner Cylinder 7

777-200/-200IGW/-300 Main Landing Gear, 8 Except: Outer Cylinder, 161W1110-3 S/N 5JHW and 161W1110-4 S/N 1JHW 1

 Outer Cylinder, 161W1110-3 S/N 4JHW and 161W1110-4 S/N 6JAN 1

 Outer Cylinder, 161W1110-3 S/N 1JJW and 161W1110-4 S/N 3JRW 1

 Outer Cylinder, 161W1110-3, -4, -9, -10 1

 Outer Cylinder, Other Part Numbers 6

 Lower Drag Strut, 161W4003 and 161W4103 7

 Upper Side Strut Spindle, 161W0100 8

 Lower Actuator Attach Pin, 161W1020 8

 Spacer Tube, 161W1159 8 Aft Trunnion Pin, 161W1301 8

 Lower Side Strut Spindle, 161W1310 8

777-200/-200IGW/-300 Main Landing Gear Support Structure 8 Except: Load Distribution Plate – Outboard Gear Beam Support 112W1725-1, -3, -4, -19, -21, -22 4

 112W1725-7, -8, -9, -10 9

 112W1725-13, -14, -15, -16 7

 Pin – Fuse, Outboard Gear Beam Support, 112W1728-3, -9 2

 112W1728-4, -5 9

 112W1728-7 7

 Pin – Fuse Retract Actuator, 112W1769 2

 Hanger Pin Details (Fwd & Aft), 115W1510 8

 Pin – Stabilizer Brace, MLG Beam, 115W1671 8

* Shown 

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777 MAINTENANCE PLANNING DATA

NOTE: Component Interchangeability Lists 161W0003 (Main Landing Gear) and 162W0002 (Nose Landing Gear) provide c

777-200/200IGW/200LR/300/300ER/777F landing gear related components subject to life limitations. 

C.2 LIFE LIMITED PARTSNOTE: Component Interchangeability Lists 161W0003 (Main Landing Gear) and 162W0002 (Nose Landing Gear) provides 

777-200/200 IGW/200LR/300/300ER/777F landing gear related components subject to life limitations.

LANDING GEAR: 

777-200LR/300ER/777F Main Landing Gear 777-200LR/300ER/777F Main Landing Gear Support Structure 777-200LR/300ER/777F Nose Landing Gear 

COMPONENT: 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 a

19-29. Incorporation of SB 777-32-0028 (reference Service Letters 777-SL-32-006 and 777-SL-001-E) removes thlimit and re-identifies it as a -7 Actuator.

777-200/-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.

777-200LR Optional Auxiliary Body Fuel Tanks

NOTE: This limit is based on fatigue test cycles completed to date and this limit will be increased or removed after addition

test cycles are completed.

777-300ER Semi Lever Gear Hydraulic Strut (P/N 293W4201-2). 

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Instructions for using Safe Life Charts:

1. For each safe life component, determine the accumulated flight cycles and flight hours.

2. Enter the Safe Life Limit Curve at the appropriate flight cycles and flight hours 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 

to the right of the the safe life curve, then the safe life limit has been reached.

FIGURE 3. 777-200LR/300ER/777F MAIN LANDING GEAR SAFE-LIFE LIMITS

Main Landing Gear Safe-Life Limits

265.60, 33.20

99.90, 66.60

124.95, 83.30

129.30, 86.20

114.45, 76.30

0

102030405060708090

100

0 50 100 150 200 250 300

Flight Hours (x 1,000)

Flight Cycles (x 1,000) Outer Cylinder

All Other Components

Aft Trunnion PinSpacer TubeLower Retract PinSide Strut Spindles

Lower Drag Strut

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777 MAINTENANCE PLANNING DATA

FIGURE 4. 777-200LR/300ER/777F MAIN LANDING GEAR SUPPORT FITTINGS SAFE-L

Main Landing Gear Support Fittings Safe-Life Limits

124.95, 83.30

320

182.40, 121.60

129.30, 86.20

111.30, 74.20

0

20406080

100120140

0 50 100 150 200 250 300 

Flight Hours (x 1,000)

Flight Cycles (x 1,000)

All Other Components

Load Distribution PlateFuse Pin B

 Upper and Lower Stabilizer Aft Pins Hanger Link Fwd and Aft Pins

Outboard Gear Beam Fuse Pin

Retract Actuator Fuse Pin

(40K cycles for all Flight Hours)

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FIGURE 5. 777-200LR/300ER/777F NOSE LANDING GEAR SAFE-LIFE LIMITS

Nose Landing Gear Safe-Life Limits

348.00

109.95, 73.30

116.25, 77.50

286.40, 35.80

66.00, 44.00

0

102030405060708090

0 50 100 150 200 250 300 350 

Flight Hours (x 1,000)

Flight Cycles (x 1,000)

All Other Components

 Inner Cylinder

777-300ER Upper Floating Piston,Upper Cylinder, Lower Cylinder,Metering Pin, and Orifice Plate

JAN 2009
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777 MAINTENANCE PLANNING DATA

D. AIRWORTHINESS LIMITATIONS – SYSTEMS

FUEL SYSTEMS AIRWORTHINESS LIMITATIONSThis section contains an FAA approved program of Airworthiness Limitations (AWLs) for operators to incorporate into their ma

type design to meet the new standards and assumptions introduced by § 25.981 and Special Federal Aviation Regulation (SF

Tank System Fault Tolerance Evaluation Requirements and Title 14 Code of Federal Regulations § 25.981 – Fuel Tank Ignitimaintenance instructions, and control limitations for certain fuel tank critical design configurations. Note: The auxiliary fuel ta

shown to comply with CFR 25.981 at Amendment 25-102.

Paragraph 2(a) of SFAR 88 and Paragraph (b) of the new standard introduced by § 25.981 requires certain design approval ho(TCs) and Supplemental Type Certificates (STCs) of large transport airplanes to conduct a safety review of the fuel tank systemreview is to identify design features that may result in development of ignition sources in the fuel tank systems. Fuel system A(AWLs) are mandatory maintenance actions required to ensure that unsafe conditions identified by the SFAR 88 safety review introduced into the fuel tank system as a result of configuration changes, repairs, alterations, or deficiencies in the maintenancoperational life of the airplane. An AWL may be an Airworthiness Limitation Instruction (ALI) or a Critical Design Configuration CDCCLs are a means of identifying certain design configuration features intended to preclude a fuel tank ignition source for th

airplane. CDCCLs are mandatory and cannot be changed or deleted without the approval of the Seattle FAA ACO that is resp

model Type Certificate, or applicable regulatory agency. A critical fuel tank ignition source prevention feature may exist in the installation or in systems that, if a failure condition were to develop, could interact with the fuel system in such a way that an udevelop without this limitation. Strict adherence to configuration, methods, techniques, and practices as prescribed is required 

the CDCCL. Any use of parts, methods, techniques or practices not contained in the applicable CDCCL must be approved by 

applicable regulatory agency.

DEC 2007
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ALIs identify inspection tasks related to fuel tank ignition source prevention which must be done to maintain the design level of saf

life of the airplane. These ALIs are mandatory and cannot be changed or deleted without the approval of the Seattle FAA ACO thaairplane model Type Certificate, or applicable regulatory agency. Strict adherence to methods, techniques and practices as presc

ensure the ALI is complied with. Any use of methods, techniques or practices not contained in these ALIs must be approved by th

applicable 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 of an event, an exceptional short-term extension for each fuel sysdocument may be made without jeopardizing safety. The local regulatory authority (e.g. a Principal Maintenance Inspector) must exceptional short-term extensions before they take place using procedures established with the local regulatory authority in the op“exceptional short-term extension” process is applicable to AWL intervals. It should not be confused with the operators “short-term 

normal 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 of1. The term “exceptional short-term extension” is defined as an increase in a fuel system AWL interval that may be needed to co

unexpected 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 on similar airplanes in an operator’s fleet, should not be used as a 

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

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

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

SEP 2007
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777 MAINTENANCE PLANNING DATA

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

under the U.S. FAA jurisdiction only and to airplanes registered in the U.S. All other operators should obtain approval from th

agency for any deviations from the listed AWL instructions.AWL REVISION PROCESSIn the event that an AWL is revised, Boeing will prepare a revision to this document that will be approved by the Seattle FAA A

be forwarded to all 777 operators and the Seattle FAA ACO.

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E. PAGE FORMAT: SYSTEMS AIRWORTHINESS LIMITATIONS

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

intervals.CDCCL = Critical Design Configuration Control Limitation.

INTERVAL Task frequencies are specified in terms of a usage parameter such as flight hours, cycles or calend

APPLICABILITY Airplane model applicability.DESCRIPTION Description of the task to be performed or critical design configurations aspects that cannot be chan

violating the intent of the design.

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AIRWORTHINESS LIMITATIONS – FUEL SYSTEMS

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

28-AWL-01 ALI 16,000 FC/ 

3,000 DYS

NOTE

ALL External Wires Over Center Fuel Tank

Concern: Potential for Wire Chafing and Arcing to Center Fuel Tank UppPerform a detailed inspection of the wire bundles routed over the center deck floor boards per Boeing AMM 28-11-00 to detect damaged clampsbundle is not in contact with surface of the center fuel tank. If discrepanBoeing Standard Wiring Practices Manual D6-54446 (SWPM Section 20Interval Note: Whichever comes first.

28-AWL-02 CDCCL N/A ALL External Wires Over Center Fuel Tank 

Concern: Potential for Wire Chafing and Arcing to Center Fuel Tank UpIf any maintenance is performed in the area under the main deck floor btank, verify the following:1. Maintain the existing wire bundle routing and clamping.2. Perform a detailed inspection of the wire bundles routed over the cen

deck floor boards in the areas of the performed maintenance to deteand that the wire bundle is not in contact with the surface of the centfound, repair per the Boeing Standard Wiring Practices Manual, D6-5

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28-AWL-03 ALI 16,000 FC/ 

3,000 DYS 

NOTE

ALL Fuel Quantity Indicating System (FQIS) – Out Tank Wiring Lightning Shield to 

Concern: Potential for Lightning induced voltages on the FQIS wiring to enteUsing a Loop Resistance Tester, P/N 906-10246-2 or 906-10246-3, perform trepair as necessary to ensure the functional integrity of the FQIS wiring shield Boeing AMM 05-55-54:1. Measure and verify the resistance of the shield to ground termination for 

• The loop resistance shall not exceed 40 milliohms for Connector D281

Tank Rear Spar) Wire Bundle W8073.

• The loop resistance shall not exceed 54 milliohms for Connector D281

Tank Rear Spar) Wire Bundle W8072.

• The loop resistance shall not exceed 40 milliohms for Connector D281

Front Spar) Wire Bundle W8010.

• The loop resistance shall not exceed 40 milliohms for Connector D282

Front Spar) Wire Bundle W8020.

• The loop resistance shall not exceed 53 milliohms for Connector D282

Tank Rear Spar) Wire Bundle W8077.

• The loop resistance shall not exceed 40 milliohms for Connector D282

Tank Rear Spar) Wire Bundle W8078.

Interval Note: Whichever comes first.

28-AWL-04 CDCCL N/A ALL FQIS – Out Tank Wiring Lightning Shield to Ground Termination 

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

If any maintenance is performed on the FQIS wire bundle in the unpressurizeand outside the fuel tank, verify the following:1. Presence of shielded wiring.2. Presence of bonding jumper between receptacle at the rear spar and grou

resistance between red end of the jumper and the structure is no more tha

3. Presence of sealant at the bonding jumper terminal and the ground stud o

is 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 w

integral) is repaired or replaced.

Use Loop Resistance Tester as specified in Boeing AMM 05-55-54.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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777 MAINTENANCE PLANNING DATA

28-AWL-05 CDCCL N/A 777 airplanes 

Line Numbers 498 

and on; or all 

airplanes that 

have incorporated 

Service Bulletin 

777-28-0044.

Lightning Protection – Engine Fuel Feed Line Fuel Tank PenetrationConcern: Potential for arcing, sparking or filament heating inside the tanbulkhead fitting and the spar during a lightning strike event.The following must be maintained per Boeing AMM 28-22-15 if the bulkh

removed and replaced:1. Verify electrical fay surface bond from bulkhead fitting to structure is 2. Install full-bodied fillet seal encapsulating the bulkhead fitting to the t3. Install full bodied fillet seal encapsulating the first coupling interface i4. Verify an electrostatic bonding jumper presence between the structu

the bulkhead fitting inside the tank.

5. Verify electrical bond from structure to first tube mating with the bulk

(10 milliohms) or less.

28-AWL-06 CDCCL N/A ALL Lightning Protection – Hydraulic Line Fuel Tank Penetration

Concern: Potential for arcing or sparking inside the tank at the interface bthe spar during a lightning strike event.When the bulkhead fitting or attached tubing are removed and replacedconfiguration of hydraulic line fuel tank penetration at interface between Boeing AMM 29-11-60. This configuration has the following CDCCLs:1. Fay Surface bond at the bulkhead fitting. Bonding resistance betwee

0.001 ohm (1 milliohm) or less.

2. A bonding jumper from the hydraulic heat exchanger to structure ins

resistance between the heat exchanger and the bonding jumper is 0

3. Apply full bodied cap seal at the fitting to the tank wall interface insid

28-AWL-07 CDCCL N/A ALL AC and DC Pump Maintenance

Concern: Potential for maintenance error during pump overhaul. Fuel psource prevention means (i.e., flame arrestor, thermal fuses, materials, that must be maintained if pump is overhauled. Repair and overhaul of Fuel Pumps must be per Eaton (VK2523) Comp(CMM) 28-20-42 Revision 7, CMM 28-20-44 Revision 6, CMM 28-20-45 Revision 2, or later revisions of these CMMs that have been approved b

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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28-AWL-08 CDCCL N/A All 777-200 “A” 

market airplanes 

Line Numbers 523 

and on; or 

airplanes modified 

per Boeing 

Service Bulletin 

777-28-0045.

Center Wing Tank Sump Drain Valve Concern: Potential for arcing or sparking inside the tank at the interface betwand the lower skin in the center wing tank during a lightning strike event.

The following must be maintained per Boeing AMM 28-11-06 if the drain valv1. 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 ALL Lightning, Fault Current, or Hot Short Protection – Fuel Tank Penetrations

Concern: Potential for arcing or sparking inside the tank at a conductive metinterface as a result of electrical fault currents or lightning strike events due to 

the ground electrical path. Addition of any new penetrations to the fuel tanks (such as adding a bracket equipment) or change to the design features of the existing equipment pene

measuring sticks, sump drain valves, fueling manifold, fuel temperature sensoshutoff valve adaptor plate) requires approval by the FAA Seattle ACO.

28-AWL-10 CDCCL N/A ALL AC Fuel Pump Fault Current Bonding Jumper Installation

Concern: Potential for fault current path through the pump housing to structuElectrical faults internal to the fuel pump motor impeller are by design routed 

assembly to the bonding jumpers on the front face of the motor impeller assethe tank. The bonding jumpers ensure that fault currents are conducted to stuntil the circuit breaker and/or GFI has had time to remove power from the puThe following must be maintained during pump replacement per Boeing AMM 1. Installation of the bonding jumper between the pump motor impeller and s2. Motor Impeller bonding resistance to structure less than or equal to 0.000

28-AWL-11 CDCCL N/A ALL Fuel Quantity Indicating System (FQIS) and Auxiliary Fuel Tank Electronic Fu

(EFLI) – Out of Tank Wiring Installation Separation RequirementConcern: Potential for hot shorts and EMI induced voltages on the FQIS or Awiring outside of the tank to enter the fuel tank.Routing and installation of any new wiring must use wire types BMS 13-48, B

and not be within a 2 inch radius of the FQIS or Auxiliary Fuel Tank EFLI wirifails, a separation greater than 1⁄2 inch must be maintained from Auxiliary Fue

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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777 MAINTENANCE PLANNING DATA

28-AWL-12 CDCCL N/A ALL Center Wing Tank Fueling Valve and Aux Tank Refuel Valve V28001 – 

Concern: Potential for arcing or filament heating inside the center wing fFor the CWT and Auxiliary Tank Refuel Valve V28001, the following muAMM 28-21-02 or AMM 28-21-21 if the refueling valve is removed and r1. Fay Surface bond between the valve body and the rear spar inside th

(2.5 milliohms).

2. Fillet seal around valve body and gask-o-seal perimeter inside the ta

28-AWL-13 CDCCL N/A ALL Fuel Quantity Indicating System (FQIS) – Fuel Quantity Processor Unit 

Fuel Tank Electronic Fuel Level indication System (EFLI) RepairConcern: Potential for maintenance error during FQPU or Auxiliary Fueand Auxiliary Fuel Tank EFLI is designed to limit the levels of energy, voallowed within the FQIS / EFLI circuit to intrinsically safe levels in order ignition source within any fuel tank.Repair and overhaul of FQPU must be per GE Aviation (VK5294) Comp

(CMM) Volume 1, 28-47-69 Revision1, and CMM Volume 2 (IPC) 28-4728-47-65 Revision 3 and CMM Volume 2 (IPC) 28-47-65 Revision 4, or that have been approved by the FAA Seattle ACO.NOTE: Prior to repair and overhaul of FQPU Part Number 0310KPU02

per Smiths Industries Service Bulletin 0310KPU-28-400.Repair and overhaul of EFLI must be per Parker (V26055) CMM 28-41-that have been approved by the FAA Seattle ACO.

28-AWL-14 CDCCL N/A ALL Fuel Quantity Indicating System (FQIS) and Auxiliary Fuel Tank Electron

(EFLI) – Repair of In-Tank Hardware (Tank Units, Densitometers, WateConcern: Potential for maintenance error during repair of in-tank hardwadensitometers). Arc gaps may develop that could result in an ignition soRepair and overhaul of FQIS tank units and densitometers must be per Component Maintenance Manual (CMM) 28-47-58 Revision 4, CMM 28

60 Revision 4, CMM 28-48-03 Revision 2, CMM 28-47-71 Revision 5, o

that have been approved by the Seattle FAA ACO.Repair and overhaul of EFLI probe must be per Parker (V26055) CMM 2

revisions of this CMM that have been approved by the Seattle FAA ACO

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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28-AWL-15 CDCCL N/A ALL Fuel Quantity Indicating System (FQIS) – Repair or Replacement of In-Tank 

Concern: Potential for error during repair or replacement of in-tank wire harnethat could result in an ignition source inside the fuel tank.Repair and overhaul of FQIS in-tank wire harness must be per Boeing SWPM is accomplished on the airplane, or per GE Aviation(VK5294) CMM 28-47-61 revisions of this CMM that have been approved by the Seattle FAA ACO wheaccomplished in the shop.Installation of FQIS in-tank wire harness must be per Boeing AMM 28-41-05. between 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 clea

in the Boeing AMM 28-41-05.

2. New O-ring(s) are installed.3. The Jamnuts are tightened to a torque as specified in the Boeing AMM Ta

4. Sealant is installed on the threads and the bonding jumper terminal and th

instruction in the Boeing AMM Task 28-41-05.

5. Verify the bonding resistance between the adapter and the structure is no

(0.5 milliohms).

After installation of the airplane wire connector, verify that the bonding resista

and the spar is not more than 0.0005 ohm (0.5 milliohms).

28-AWL-16 CDCCL N/A ALL Fuel Tank Access Doors Configuration

Concern: Potential for arcing or sparking inside the tank at the interface betwstructure as a result of a direct strike or conducting currents through the wing The following must be maintained during installation of fuel tank access doors skin. (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 around the outermost periphery the wing skin inside the tank, do a check of the knitted aluminum mesh gaskereplace if necessary, and apply grease or anti-corrosion compound to both sid

mesh gasket. Install the prepared knitted aluminum mesh gasket between thand the wing skin to establish the electrical conductivity between the access using the clamp ring and fasteners torqued to that specified in the applicable 

For the surge tank access door with vent scoop, verify the installation of a boupper duct and the door; 0.010 ohm (10 milliohms) or less.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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777 MAINTENANCE PLANNING DATA

28-AWL-17 CDCCL N/A ALL Resetting Tripped Fuel Pump Circuit Breakers

Concern: Potential for arcing or sparking inside the tank between fuel pand outside the tank between pump wiring and structure in flammable leVerify it is safe to reset the circuit breaker(s) by following the applicable procedures. Fault(s) that resulted in circuit breaker trip must be isolated 

28-AWL-18 ALI 375 DYS ALL

NOTE

AC Fuel Pump Ground Fault Interrupter (GFI)Concern: Potential for pump housing burn-through, either internal or extof major arcing due to electrical failure (i.e., damaged electrical connectohousing/end cap shorting).The GFI is designed to detect electrical faults and open the circuit prior The following maintenance check is required in order to ensure continueOperationally check the GFI of Center Tank Override/Jettison Pumps, A

Jettison Pumps and Main Tank Boost Pumps per AMM 28-22-00 or AMApplicability Note:a. Center Tank Override/Jettison Pumps and Main Tank Jettison Pump

Positions 423, 429, 454 and on.

b. Center Tank Override/Jettison Pumps and Main Tank Jettison Pump

Position 454, except 423 and 429 that have incorporated Service Bul

c. All Main Tank Boost Pumps on airplanes starting with Line Position 6d. All Main Tank Boost Pumps on airplanes prior to Line Position 662 th Service Bulletin 777-28A0038.e. Auxiliary Tank Pumps on 777-200LRs only if equipped with Auxiliary 

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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28-AWL-19 CDCCL N/A Airplane Line 

Position 552 and 

on; or airplanes 

modified per 

SB 777-28A0034 

or 

SB 777-28A0059 

as noted.

Lightning and Fault Current Protection – Motor Operated Valve (MOV) ActuaConcern: Potential for arcing or sparking inside the fuel tank at a conductive interface as a result of electrical fault currents event.The following design features must be maintained per Boeing AMMs 28-22-022-04, 28-26-01, 28-26-02, 28-31-02, 28-31-03, 28-31-04, 28-31-05, 28-14-2

14-25, 28-21-23, 28-21-24, 28-14-11, 28-14-12 during actuator, adapter plate replacement (Only AMM 28-31-03 is applicable 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 

tank cell wall structure) is 0.0005 ohms (0.5 milliohms) or less. Install periphery 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 t

fillet seal around the edge of the hole and on the stationary part of the 

tank.

c. Install sealed electrical fay surface bond between the serrated mating 

and the adapter plate. Wet install the index plate screws using same s

d. Install sealed electrical fay surface bond between the mating surfaces 

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

e. With the bonding jumper not installed, verify electrical bonding resistan

bond strap attachment point and the spar/(auxiliary fuel tank cell wall s(2.5 milliohms) or less.

f. Prior to attachment of the bonding jumper to the actuator, verify electr

between the loose end of the bonding jumper and the spar/(auxiliary fu

is 0.0015 ohms (1.5 milliohms) or less.

g. Attach the bonding jumper to the upper housing of the actuator using a 

surface bond and verify electrical bonding resistance between the actuattached bonding jumper terminal is 0.001 ohms (1 milliohm) or less.

(Continued on next page)

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

FEB 2009
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777 MAINTENANCE PLANNING DATA

28-AWL-19

(Cont.)

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

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

and the adapter plate. Wet install the index plate screws using sa

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

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

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

housing of the actuator and the spar is 0.0025 ohm (2.5 milliohms

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

between the loose end of the bonding jumper and the spar/(auxilis 0.0015 ohms (1.5 milliohms) or less.

e. Attach the bonding jumper to the upper housing of the actuator u

surface bond and verify electrical bonding resistance between the 

attached bonding jumper terminal is 0.001 ohm (1 milliohm) or les

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

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

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

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

housing of the actuator and the spar/(auxiliary fuel tank cell wall smilliohms) or less.

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

between the loose end of the bonding jumper and the spar/(auxilis 0.0015 ohms (1.5 milliohms) or less.

d. Attach the bonding jumper to the upper housing of the actuator u

surface bond and verify electrical bonding resistance between the 

attached bonding jumper terminal is 0.001 ohms (1 milliohm) or le

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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28-AWL-20 CDCCL N/A ITT actuators

(P/N MA20A2027 

or MA30A1001)

installed on 

Airplane Line 

Position 552 and 

on; or airplanes 

modified per 

SB 777-28A0034 

or

SB 777-28A0059.

Motor Operated Valve (MOV) Actuator – RepairConcern: Potential for arcing or sparking inside the fuel tank at a conductive interface as a result of lightning or electrical fault current event. An electrical 

output shaft is intended to disconnect the output shaft electrically from the mocircuitry and ground path structure.To verify the integrity of the electrical isolation feature, conduct the following (V73760) CMM 28-20-21:A Dielectric Strength test on the completed actuator assembly shall be performRMS, 60 Hz for one (1) minute between any mounting foot of the actuator anThere shall be no evidence of disruptive discharge in the form of leakage curamps. The 3000V test is a bench test only and must not be performed on the 

28-AWL-21 ALI 4500 DYS 777-200LR with 

Auxiliary Fuel 

Tank

External Wires Over Auxiliary Fuel TankConcern: Potential for Arching or Wire Chafing to Auxiliary Fuel Tank.Perform a detailed inspection of the wire bundles routed over the auxiliary fue

deck floor boards to detect damaged clamps, chafing wires, and a wire bundstructure. If discrepancies are found, repair per the Boeing Standard Wiring P(SWPM Section 20-10).

28-AWL-22 CDCCL N/A 777-200LR with 

Auxiliary Fuel 

Tank

External 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 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 

deck floor boards in the areas of the performed maintenance to detect dam

and a wire bundle that is in contact with structure. If discrepancies are foStandard Wiring Practices Manual D6-54446 (SWPM Section 20-10).

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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28-AWL-23 CDCCL N/A 777-200LR with 

Auxiliary Fuel 

Tank

Auxiliary Tank Bonding Jumper InstallationConcern: Potential for fault current path through to structure inside the the fuel pump motor impeller are, by design, routed through the motor imjumpers on the front face of the motor impeller assembly to the tank strubonding jumpers which provide a path from the tank to airplane structur

that fault currents are conducted to structure outside of the tank until the had time to remove power.The following must be maintained during pump replacement per Boeing Aerospace (VK3784) CMM 28-14-02:1. The installation of the bonding jumper between the pump motor impe

2. Perform the following resistance checks:

a. Fuel pump motor-impeller unit to the pump housing bonding resist

(0.002 ohm).

b. Fuel Pump motor-impeller to the tank structure bonding resistance 

(0.0025 ohm).

The following must be maintained during tank replacement / installation 1. On the right side of the cell the resistance between the tank bonding 

less than or equal to 10 milliohms.

2. The electrical fay surface bond resistance between the stanchions an

or equal to 10 milliohms.

28-AWL-24 CDCCL N/A 777-200LR with 

Auxiliary Fuel 

Tank

Auxiliary Tank Thermal ProtectionConcern: Potential for heating of the auxiliary tank structure as a result If any maintenance is performed on or around the auxiliary tanks, verify components:i. Cargo Liners which separate the cargo compartment from the auxiliaii. 9G Thermal Impact Barrier is installed on the auxiliary fuel tank barriiii. The Thermal Insulation Blanket located between the end wall cargo 

barrier is installed.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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28-AWL-25 CDCCL N/A 777-200LR with 

Auxiliary Fuel 

Tank

Auxiliary Tank Lightning ProtectionConcern: Potential for arcing or sparking inside the tank at a conductive metinterface as a result of lightning strike events to aux tank drains.If any maintenance is performed on or around the auxiliary tank drain systemi. Aeroquip Low Pressure Teflon Lightning Safe Hoses are installed on the aii. Flame Arrestors are installed in fuel tank drains.iii. Foil backed fairing panels and associated bonding located below drain line STA 1530 are installed.

28-AWL-26 ALI 375 DYS 777-200LR with 

Auxiliary Fuel 

Tank

Auxiliary Fuel Tank AC Fuel Pump Uncommanded ON /Automatic Shutoff CiConcern: Potential for failure of fuel pump power control circuit in the energizrunning of fuel pump with a potential ignition threat due to pump overheat or 

The Pump Uncommanded ON/Automatic Shutoff Circuit provides redundant from the Auxiliary Tank Pump if pump pressure is low for >15 seconds.The following maintenance check is required in order to ensure continued fun

1. Operationally check the Pump Uncommanded ON/Automatic Shutoff Circ

28-14-05.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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777 MAINTENANCE PLANNING DATA

F. AIRWORTHINESS LIMITATIONS – NITROGEN GENERATION SYSTEMS TASKS

The following list of AWLs (ALIs and CDCCLs) contain FAA approved scheduled inspections and design limitations for operat

maintenance program for this type design to meet the requirements for the introduction of the Flammability Reduction Means 

System (NGS). The FAA operational rule change E8-16084 Final Flammability Rule requires maintenance instructions and co

NGS critical design configurations. § 25.981 also requires CDCCLs to preclude ignition sources inside the fuel tank that may 

of NGS.Final Flammability Rule, Paragraph III(F), Section 7, Paragraph M25.4(a) requires that if FRM is used to comply with Paragra

limitations must be identified for all maintenance or inspection tasks required to identify failures of components within the FRM Paragraph M25.1. NGS AWLs are mandatory maintenance actions that ensure that unsafe conditions that arise due to NGS f

not introduced into the airplane as a result of configuration changes, repairs, alterations, or deficiencies in the NGS Maintena

operational life of the airplane.

AUG 2010
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AIRWORTHINESS LIMITATIONS – NITROGEN GENERATION SYSTEM (NGS)

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

47-AWL-01 CDCCL N/A All Airplanes 

Line Number 

772 and on, 

or airplanes

that have 

incorporated 

Service Bulletin 

777-47-0002

Lightning Protection – NGS NEA Distribution Line Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interface betwflame arrestor and the spar during a lightning strike event. The following mubulkhead fitting or attached tubing is removed and replaced or reinstalled (re

06):1. Install the same part number bulkhead fitting.2. Verify electrical fay surface bond between the bulkhead fitting and the fro

tank is 0.0005 ohm (0.5 milliohms) or less.

3. Install full-bodied fillet seal between the front spar structure and bulkhead 

the tank.

4. Install full-bodied fillet seal encapsulating the first coupling interface inside 

fitting between the flareless fitting nut and tube and between the flareless fitting.

5. Verify electrical bond from structure to first tube mating with the bulkhead NOTE: The bulkhead fitting is a special part which has an integral flame arre part requires approval by the Seattle FAA ACO.

47-AWL-02 CDCCL N/A All Airplanes 

Line Number 

772 and on, 

or airplanes

that have 

incorporated 

Service Bulletin 

777-47-0002

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

dielectric isolator hose and the NEA tubing during a lightning strike event.The NGS installation is designed to prevent lightning currents from entering t

adding a dielectric isolator hose in the forward leading edge fairing area NEA 

isolator must be maintained if the dielectric isolator hose or attached tubing is 

reinstalled (refer to Boeing AMM 47-21-00).

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47-AWL-03 CDCCL N/A All Airplanes 

Line Number 

772 and on, 

or airplanes

that have 

incorporated 

Service Bulletin 

777-47-0002

Nitrogen Generation System (NGS) – Flammability Exposure and PerfoConcern: Airplane alterations may impact the performance of the NGS a

Center Wing Fuel Tank.Background: The NGS is designed to provide the proper level of nitrog

order to reduce the flammability exposure by reducing the oxygen conteflammability exposure is also affected by the temperature of the fuel. Tof the airplane that, if altered, can negatively affect the performance of tincrease the center fuel tank flammability exposure beyond the limits of Section 25.981 at Amendment 25-125, utilizing the equivalent level of s

Memorandum PS05-0177-P-2.1. Transferring air (20.9% oxygen) to the center fuel tank will dilute the 

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

2. NGS performance depends on bleed air pressure in the bleed air cro

the engines.

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

installed. Center tank flammability is a direct function of fuel tank temaround the tank, heat sources introduced into the tank (such as warm changes that would cause heat to be retained (such installation of blcould affect fuel tank flammability in a negative manner.

CDCCL: Any design change that affects the vent system by adding air bleed pressure in the cross-over manifold during any phase of flight or gheat to the center wing fuel tank or increases heat retention of the centewithout an FAA approved analysis to show that the change, or combinathe NGS performance per the requirements of 14 CFR Section 25.981(bthe equivalent level of safety finding described in FAA Memorandum PSSee Boeing AMM Chapter 28 for a description of the Fuel System. See description of the NGS.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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47-AWL-04 ALI 108,000 FH All Airplanes 

Line Number 

772 and on, 

or airplanes

that have 

incorporated 

Service Bulletin 

777-47-0002

Nitrogen Generation System – Thermal Switch Functional and Operational CConcern: Latent Failure of the Thermal Switch removes a layer of protection 

hot bleed air.The NGS uses engine bleed air from the engine bleed system cross-over mato reduce the flammability of the center fuel tank. The NGS has features to pbleed air into the fuel tank. The Thermal Switch provides a redundant backuprotect the Air Separation Module (ASM) and prevent hot bleed air from enteThermal Switch backup feature is a latent (not detected) failure and must be certification of the NGS.Perform a functional and operational check of the Thermal Switch to ensure Switch (refer to Boeing AMM 47-42-04).

47-AWL-05 ALI 10,682 FH All Airplanes 

Line Number 

772 and on, 

or airplanes

that have 

incorporated 

Service Bulletin 

777-47-0002

Nitrogen Generation System – Cross-Vent Check Valve – Operational Check

Concern: The Cross-Vent Check Valve may fail open latently allowing air to f

diluting the nitrogen rich environment created by the Nitrogen Generation SyOperationally check the Cross-Vent Check Valve by accessing left wing surg

checking the operation of the Cross-Vent Check Valve (refer to Boeing AMM valve opens against spring force and closes by spring force.

47-AWL-06 ALI 10,682 FH All Airplanes 

Line Number 

772 and on, 

or airplanes

that have 

incorporated 

Service Bulletin 

777-47-0002

Nitrogen Generation System – NEA Distribution Ducting Inspection

Concern: The NEA Distribution System ducting outside the fuel tank may faileak without reaching the fuel tank, resulting in the fuel tank not reaching req

Inspect the NEA distribution lines from the ASM to the fuel tank front spar for Boeing AMM ATA 47-21-00).

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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777 MAINTENANCE PLANNING DATA

47-AWL-07 CDCCL N/A All Airplanes 

Line Number 

772 and on, 

or airplanes

that have 

incorporated 

Service Bulletin 

777-47-0002

Industry Fleet Average Flammability ExposureConcern: NGS performance is dependent on industry descent times. Intime may result in NGS performance that does not meet FAA requireme

Fleet Average flammability exposure for the fuel tanks with flammability must be maintained in accordance with 14 CFR Part 25, Appendix M. Bstatistics and, if necessary to maintain compliance, will publish service isuch service information, this CDCCL requires either that operators imp

design changes or that operators implement other design changes or opapproved by the Seattle FAA ACO to maintain compliance with 14 CFR NOTE: This CDCCL does not require individual operators to monitor de Boeing will monitor US descent statistics and provide any need

 operators. To prevent increasing flammability exposure above  requires operators to incorporate future Boeing published servic maintain compliance with this CDCCL, or other approved action stated in the service instructions.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

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777 MAINTENANCE PLANNING DATA

G. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)

SELECTION OF CMRsIn order to grant operators of the 777 airplane an opportunity to participate in the evaluation and selection of CMRs in an integrate

tasks and intervals, a Certification Maintenance Coordination Committee (CMCC) was convened to review all of the 777 CMRs. Tdocument 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 operatcertificate. CMRs usually result from a formal, numerical analysis conducted to show compliance with catastrophic and hazardous 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 specific failu

hazardous or catastrophic failure condition.

2. It is important to note that CMRs are derived from a fundamentally different analysis process than the maintenance tasks and 

the Maintenance Steering Group (MSG-3) Analysis associated with Maintenance Review Board (MRB) activities. MSG-3 Ana

maintenance tasks that are performed for safety, operational, or economic reasons, involving both preventative maintenance tabefore failure occurs (and are intended to prevent failures), as well as failure-finding tasks. CMRs, on the other hand, are failuexist solely to limit the exposure to otherwise hidden failures. Although CMR tasks are failure-finding tasks, use of potential fa

as functional checks and inspections, may also be appropriate.

3. CMRs are designed to verify that a certain failure has or has not occurred, and do not provide any preventative maintenance 

the failure clock to zero” for latent failures by verifying that the item has not failed, or cause repair if it has failed. Because the 

failure is a key element in the calculations used in a safety analysis performed to show compliance with FAR 25.1309, limiting 

have a significant effect on the resultant overall failure probability of the system. The CMR Task Interval should be designated 

cycles, or calendar time, as appropriate.

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4. The type certification process assumes that the airplane will be maintained in a condition of airworthiness at least equal to 

condition. The process described in AC 25-19 is not intended to establish normal maintenance tasks that should be defin

Analysis process. Also, this process is not intended to establish CMRs for the purpose of providing supplemental margins late in the type design approval process.

5. CMRs should not be confused with required structural inspection programs that are developed by the type certificate app

requirements for damage tolerance, as required by FAR 25.571 or 25.1529, Appendix H25.4 (Airworthiness Limitations se

developed 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 witho

Seattle FAA ACO.

2. Two Star CMRs (**) – Task intervals may be adjusted in accordance with each operator’s approved escalation program o

program 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 as any MRB Report task; however, they can not be deleted 

without prior Seattle FAA ACO approval. For operators with approved escalation practices or an approved reliability program

analytical techniques are used to make adjustments to an operator’s maintenance program. It has been demonstrated that thmaintenance program does not give rise to undue escalations; consequently, the escalation of Two Star CMR (**) intervals wmaintenance program will be properly managed by the operator subject to local regulatory authority approval.

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EXCEPTIONAL SHORT-TERM EXTENSIONSSince CMR intervals are based on statistical averages and reliability rates, an exceptional short-term extension of 10% for each Cdocument may be made, except as noted in Item 1, without jeopardizing safety. The local regulatory authority (e.g. a Principle Ma

must concur with any exceptional short-term extensions before they take place using procedures established with the local regulaoperators’ manuals. The “exceptional short-term extension” process is applicable to CMR intervals. It should not be confused witterm escalation” program for normal maintenance tasks described in the operators’ manuals and in the Flight Standards Handboo

The Seattle FAA ACO has accepted that these exceptional short-term extensions may be granted without consultation with that of1. The term “exceptional short-term extension” is defined as an increase in a CMR interval that may be needed to cover an unco

situation. All CMRs listed in this section have been approved for an exceptional short-term extension of 10%, except as noted • CMR 52-CMR-01, which has been approved for a short-term extension, is restricted to a maximum of 90 days.

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

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

After a CMR has experienced an exceptional short-term extension, the CMR interval will revert back to its interval listed in this doc

ACO must approve, prior to its use, any desired extension not explicitly listed above.

This exceptional short-term extension listed above applies to airlines that fall under the United States FAA jurisdiction only. Opera

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

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POST-CERTIFICATION CHANGES TO CMRsAny post-certification changes to CMRs should 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 a given significant latent failure as part of an engineering analys

instances of a CMR task repeatedly finding that no failure has occurred may not be sufficient justification for deleting the tbetween repetitive performances of the CMR task. In general, * CMRs are not good candidates for escalation under an o

A * CMR task change or interval escalation can only be made if world fleet service experience indicates that certain assumfailure rates made early during the engineering analysis were overly conservative, and a re-calculation of system reliabilit

certain 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 

important that operators be afforded the same opportunity to participate that they received during the original certification 

allow 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), the chan

FAA-ACO approved change to this CMR document.

4. If the requirements of an existing CMR must be increased (more restrictive actions to be performed), it will be implemente

document and enforced by an FAA Airworthiness Directive (AD).

5. After initial aircraft certification, the only basis for adding a new CMR is in association with the certification of design chan

6. A new CMR created as part of a design change should be part of the approved data for that change and added to this CM

In the event that a CMR is revised, Boeing will document it by preparing a revision to this document that will be approved by t

revision will then be forwarded to all 777 operators and the Seattle FAA ACO offices.

MAY 1998
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FIGURE 6. PAGE FORMAT CERTIFICATION MAINTENANCE REQUIREMENTS

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H. PAGE FORMAT – CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)

COLUMN EXPLANATIONCMR ITEM NUMBER

Each 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.

TYPE CMR TYPE

CMRs are categorized into one or two star CMRs based on whether or not they can be escalated by the operator 

approval.* 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 

 surveillance; however, these tasks cannot be deleted without prior Seattle ACO approval.

RELATED MRB ITEM NUMBER

This column is for the related MRB Item Number, if there is an applicable MRB Item Number. Not all CMRs have 

MRB Item Number.

TASK MSG-3 TASK CATEGORIES

OP = OPERATIONAL CHECK A failure finding task to determine if an item is fulfilling 

not require quantitative tolerances.

CMR INTERVAL Task frequencies are specified in terms of a usage parameter such as flight hours, cycles or calendar time.

APPLICABILITY APL ENG

Applicable Airplane Model and Engine.AIRPLANEALL = All Airplanes300 = 777-300777F = 777 Freighter

ENGINEALL = All Engines4000 = PW4074, PW4077, PW4084, PW4090, PWGE90 = GE90 (75B/76B/85B/90B/94B/110B/115B)TRENT = TRENT 800 (875-17, 877-17, 884-17, 890-

TASK DESCRIPTION

Description of the task to be performed.

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777 MAINTENANCE PLANNING DATA

I. CERTIFICATION MAINTENANCE REQUIREMENTS TASKS

CMR

ITEM

NUMBER

T

YPE

RELATED 

MRB 

ITEM 

NUMBER

T

A

S

K

CMR 

INTERVAL

APPLICABILITY

777

CERTIFICATION MAINTENANCE REQ

APL ENG TASK DESCRIPTION

21-CMR-01 ** 21-33 OP 7500 Hrs 777F ALL Operationally check the manual and automatic activation o

System.

26-CMR-01 * --- IN 6000 Hrs or

18 Mos, 

whichever 

occurs first

ALL

NOTE

ALL Inspect Cargo Fire Bottles, supplier Part Numbers 473474

and 473876-2, for leaks using a Halide Leak Detector. ApCompound to burst disc (inside fill fitting).AIRPLANE NOTE: Applicable to airplanes with -2 bottles applicable to -3 bottles).

27-CMR-01 * 27-140 OP 500 Hrs ALL ALL Operationally check PRIMARY FLIGHT CONTROL ACTU

actuation confidence tests.

27-CMR-02 * 27-160 OP 250 Hrs ALL ALL Operationally check ACTUATOR CONTROL ELECTRON

Functions of Flight Controls System (use ACE self-test).

27-CMR-04 * 27-360 OP 12000 Hrs ALL ALL Operationally check LE SLAT SKEW/LOSS CABLE SYST27-CMR-05 * IN 5000 FC 777F ALL Conduct a visual inspection of the 24 Horizontal Stabilizer 

Karon lined bushings and pins common to the Jackscrew Section 48 and Section 82 Fittings. Inspect for Karon lineliner delamination

27-CMR-06 * 12-002 LUB 5000 Hrs or 

500 Dys 

whichever 

comes first

777F ALL Lubricate the Elevator Power Control Units (PCUs) and El

27-CMR-07 * 12-004 LUB 5000 Hrs or 

500 Dys 

whichever 

comes first

777F ALL Lubricate the Rudder and Rudder Tab Hinge Bearings, Ru

(PCUs) Reaction Link Rod Ends and PCU Rod Ends.

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27-CMR-08 * 27-240 FC 12000 Hrs or 

1125 Dys, 

whichever 

comes first

777F ALL Functionally Check Elevator Surface Freeplay.

27-CMR-09 * 27-430 FC 12000 Hrs or 

1125 Dys, 

whichever 

comes first

777F ALL Functionally Check Rudder/Rudder Tab Surface Free

28-CMR-01 * --- IN 6000 Hrs 300 ALL Conduct a visual inspection of the center fuel tank FQ

29-CMR-01 * 29-030 FC 12000 Hrs ALL ALL Functionally check the GROSS INTERNAL LEAKAG

System.

29-CMR-02 * 29-130 OP 12000 Hrs ALL ALL Operationally check CENTER HYDRAULIC ISOLATI29-CMR-03 * 29-150 OP 6000 Hrs ALL ALL Operationally check RAT System (using RAT checko

and Manual Deployment Systems. 

31-CMR-01 * 31-100 OP 24 Hrs

NOTE

ALL ALL Operationally check FIRE WARNING SYSTEM using 

(if not checked by crew).INTERVAL NOTE: Under exceptional operational cir

extended beyond 24 hours (elapsed clock hours) but time).

32-CMR-01 * 12-081 LUB 50 FC or 

25 DYS, 

whichever 

occurs later

NOTE ALL Lubricate the left and right Main Landing Gear truck b

joints.AIRPLANE NOTE: Applicable to airplanes productioairplanes that have incorporated Service Bulletin 777

52-CMR-01 * --- DS 3375 Dys NOTE ALL Discard the Flight Deck Door Strike Assembly.

AIRPLANE NOTE: Applicable to airplanes productioincorporation of Service Bulletin 777-25-0216.

CMR

ITEM

NUMBER

T

YPE

RELATED 

MRB 

ITEM 

NUMBER

T

A

S

K

CMR 

INTERVAL

APPLICABILITY

777

CERTIFICATION MAINTENANCE 

APL ENG TASK DESCRIPTI

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72-CMR-01

DELETED

*

--- IN 24 Hrs

NOTE

NOTE TRENT

NOTE

Inspect (Detailed) STEP-ASIDE-GEARBOX (SAGB) HOUGEARBOX LOWER BEVEL BOX (LBB) HOUSING for evicracking per RR Non-Modification Service Bulletin 72-C12INTERVAL NOTE: Under exceptional operational circumsextended beyond 24 hours (clock time) but not to exceed 4AIRPLANE NOTE: Applicable to all Increased Gross Weigto any 777-200 with Rolls-Royce Trent engines capable of ENGINE NOTE: Applicable to all Rolls-Royce Trent enginthrust rating and to all Trent engines installed on Increased 

72-CMR-02

DELETED

*

--- IN 10 Cyc NOTE TRENT

NOTE

Inspect (Special Detailed) STEP-ASIDE-GEARBOX (SAGfluorescent penetrant for evidence of cracking per RR NonBulletin 72-C129, Issue 3. AD 97-06-13.AIRPLANE NOTE: Applicable to all Increased Gross Weigto any 777-200 with Rolls-Royce Trent engines capable of ENGINE NOTE: Applicable to all Rolls-Royce Trent enginthrust rating and to all Trent engines installed on Increased 

72-CMR-03 * --- IN 1000 Cyc

NOTE

300 TRENT Inspect (Special Detailed) MAIN FAN BLADES with ultraso

blade root cracking per Rolls-Royce Non-Modification ServRev. 1.INTERVAL NOTE: Repeat inspections at 500 cycles.

78-CMR-01 * 78-025

78-22078-365

OP 5000 Hrs ALL ALL Operationally check Thrust Reverser SYNC LOCK on left 

78-CMR-02

DELETED

* 78-035 

78-040

- NOTE ALL GE90 PRECOOLER INLET DUCT ASSEMBLY KISS SEAL

INTERVAL NOTE: For Part Number S315W134-2 and -1Service 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 Sectio

CMR

ITEM

NUMBER

T

YPE

RELATED 

MRB 

ITEM 

NUMBER

T

A

S

K

CMR 

INTERVAL

APPLICABILITY

777

CERTIFICATION MAINTENANCE REQ

APL ENG TASK DESCRIPTION

JAN 2011
D622W001-9

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

777 MAINTENANCE PLANNING DATA

J. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS

Title 14 Code of Federal Regulations Sections 121.703 and 135.415 state that “each certificate holder shall report any failure, 

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

may endanger the safe operation of an aircraft”. Section 125.409 also requires reporting of failures, malfunctions, or defects. failure or malfunction will be obvious, but there are some failure modes related to uncontrolled high thrust that are reportable 

following information is provided, as required by FAA Exemption No. 7955, to assist the operators in identifying reportable mauncontrolled high thrust.The FAA has concluded that the loss of capability to control thrust due to a failure of the engine thrust control system may endincludes any malfunctions having one or more 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 thrust lever mechanism or resolver• Although some or these incidents may not appear to be safety related, documenting the events is important to ensure the 

maintained and/or to identify failure conditions that must be corrected.

FEB 2009
777 MAINTENANCE PLANNING DATA

D622W001-9

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

When filing a report of such an event with the FAA, the operator is requested to include in the description of the event one or more 

following 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 the FAA Administrator that handles the appropriate reporting responsibi

and 135.415. In addition to filing reports with the FAA, it is recommended that a copy be sent to Boeing and to the engine manufa

SEP 2007
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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