THIS PAGE INTENTIONALLY LEFT BLANK 
777 MAINTENANCE PLANNING DATA

D622W001-9

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

777

MAINTENANCE PLANNING DATA (MPD) DOCUMENT

SECTION 9

AIRWORTHINESS LIMITATIONS (AWLs) AND 

CERTIFICATION MAINTENANCE REQUIREMENTS (CM

D622W001-9

OCTOBER 2014

COMPILED AND PUBLISHED BY:

MAINTENANCE PROGRAMS ENGINEERING

COMMERCIAL AVIATION SERVICES

BOEING COMMERCIAL AIRPLANE GROUP

SEATTLE, WASHINGTON

OCT 2014
D622W001-9

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

777 MAINTENANCE PLANNING DATA

THIS PAGE INTENTIONALLY LEFT BLANK

BLANK
777 MAINTENANCE PLANNING DATA

D622W001-9

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

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

D.1 FUEL SYSTEMS IGNITION PREVENTION ...........................................................................................................................D.2 ENGINE SUCTION FEED SYSTEM.......................................................................................................................................

D.3 NITROGEN GENERATION SYSTEM (NGS)..........................................................................................................................D.4 PRATT AND WHITNEY FORWARD STRUT DRAIN LINE.....................................................................................................D.5 ROLLS ROYCE THRUST REVERSER THERMAL PROTECTION SYSTEM........................................................................

E. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs).....................................................................................................

F. CERTIFICATION MAINTENANCE REQUIREMENTS TASKS ......................................................................................................

G. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS .............................................................................

OCT 2014
D622W001-9

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

777 MAINTENANCE PLANNING DATA

THIS PAGE INTENTIONALLY LEFT BLANK

BLANK
777 MAINTENANCE PLANNING DATA

D622W001-9

BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

REVISIONS 

REVISION AND REVISION DESCRIPTION 

APRIL 1995 (Original Release) Approved 

D. L. Rigg Alvin Hafor D. Rig

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

Approved D. L. Rigg

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

Approved D. L. Rigg

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

Approved D. E. Gon

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

Approved D. L. Rigg

OCT 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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

Approved D. E. Gon

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.

Approved D. L. Rigg

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.

Approved D. L. Rigg

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.

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.

Approved D. L. Rigg

REVISION AND REVISION DESCRIPTION 

OCT 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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.

Approved D. L. Rigg

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 inservice airplanes and the accumulation of over 200,000 flight hours of in-service data.

Approved 

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. 

Approved 

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.

Approved 

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.

Approved A. Bahram

REVISION AND REVISION DESCRIPTION 

OCT 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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.

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.

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.

Approved 

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

Approved 

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.

Approved 

REVISION AND REVISION DESCRIPTION 

OCT 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

NOVEMBER 2003 (Revision 20)Added Section G which contains new airline operator reporting requirements for uncontrollable high thrust failure conditions orassociated 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.

Approved Jeffrey E. 

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 forthe 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.

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 Anti-Collision Light Installation.

Approved Jeffrey E. 

REVISION AND REVISION DESCRIPTION 

OCT 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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.

Approved Jeffrey E. 

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.

Approved Jeffrey E. 

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.

Approved Jeffrey E. 

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.

Approved Jeffrey E. 

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.

Approved Dorr M. A

REVISION AND REVISION DESCRIPTION 

OCT 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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.

Approved A. J. Pas

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.

Approved 

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.

Approved 

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.

Approved 

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

Approved 

REVISION AND REVISION DESCRIPTION 

OCT 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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.

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.

Approved 

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.

Approved 

REVISION AND REVISION DESCRIPTION 

OCT 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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.

Approved 

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

Approved 

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.

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.

Approved 

REVISION AND REVISION DESCRIPTION 

OCT 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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.

Approved 

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-AWL-06, 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.

Approved  

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.

Approved  

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

Approved  

REVISION AND REVISION DESCRIPTION 

OCT 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

FEBRUARY 2012Revised the Life Limit for the 777-200LR Optional Auxiliary Body Fuel Tank from 1,800 Landings to 15,000 Cycles, due to results of 

continued fatigue testing.Revised references to regulatory agencies, as needed, by adding “BASOO”, the acronym for the Boeing Aviation Safety Oversight Office.Revised Section D by moving the first two paragraphs pertaining to Fuel System Ignition Prevention into the new subsection D.1.Revised the “FUEL SYSTEMS AIRWORTHINESS LIMITATIONS” heading to “INTRODUCTION”, and added information on FAA approved Airworthiness Limitations required under Title 14 CFR § 43.16 and § 91.403.Revised “USE OF ALTERNATE TOOLS” heading in Section D to “USE OF ALTERNATE OR EQUIVALENT TOOLS, TEST EQUIPMENT OR MATERIALS"; revised requirements to include CMMs, and identified acceptable fuel tank sealants.

Revised the Exceptional Short-Term Extensions subparagraph, changing “fuel system AWL” to “system AWL” to accommodate the addition of 28-AWL-101 - Engine Suction Feed System. Revised “(e.g., a Principal Maintenance Inspector)” to “or a Principal Maintenance Inspector” and updated the Flight Standards Handbook reference from “8300.10” to “8900.1 FSIMS”. Revised the Regulatory Agency Approval subparagraph by updating the requirements for operators not operating under the jurisdiction of the U.S. FAA.Added new subparagraphs to Section D: "Definitions", to provide further clarification on accomplishment instructions, and "Supporting Documentation", to clarify that strict adherence to the methods, techniques and practices, as prescribed, is required to 

ensure the ALI or CDCCL is complied with.Revised the table heading in Section D from “Airworthiness Limitations – Fuel Systems” to “AWLs - Fuel Tank Ignition Prevention”.Revised certain AWLs by changing the word “per” in AWL references to “refer to”, as needed.Revised 28-AWL-01 by adding an inspection of the wire sleeving, if installed, and added statement for SWPM repairs to ensure 

wires are not in contact with the surface of the Center Fuel Tank. Revised SWPM reference from 20-10 to 20-10-11 and 20-10-13,for further clarification.Revised 28-AWL-03 by adding Step 1 for the loop resistance check between the receptacle and structure, added ohm values to Step 2, and Step 3 for restoring the electrical bond.Revised 28-AWL-04 to clarify which design features must be maintained, dependent on the disruption of the ground path of each 

specified connector.Revised 28-AWL-05, replacing "structure" with "front spar inside the tank" in Step 1, changing “first tube" to “fuel tube" in Steps 4 

and 5, and adding “if the bonding jumper was disturbed” to Step 5 for clarification.

Revised 28-AWL-06 by adding critical design features for the hydraulic bulkhead fitting, heat exchanger, and non-heat exchanger

hydraulic tubes due to the different hydraulic tube materials and types used.

(Continued on next page)

Approved  

REVISION AND REVISION DESCRIPTION 

OCT 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

FEBRUARY 2012, ContinuedRevised the Concern statement for 28-AWL-07 by deleting “during pump overhaul” to clarify that the potential for maintenance error is not limited to overhaul. Revised "Repair and overhaul" to "Maintenance" in the second paragraph to clarify the CDCCL intent. Revised the Applicability for 28-AWL-08 by deleting “A market” for clarification. Replaced “phenolic washer” with “insulating 

washer” in Step 1 and revised Step 2 to identify the interface location for the fillet seal that must be maintained if the drain valve is 

removed or replaced.Revised the Concern statement for 28-AWL-09 by adding a statement that electrical bonding of fitting and brackets and/or the cap 

sealing of fasteners, and fillet sealing of component interface will be necessary. Revised the second paragraph to clarify that any alteration, design change, or repair involving new penetrations requires approval by the Seattle FAA ACO or BASOO.Revised the Concern statement for 28-AWL-10, replacing “jumpers” with “jumper” and added “Ground Fault Interrupter” for “GFI”. Added reference to AMMs 28-22-05 and 28-31-01. Revised “a bonding jumper” to “one bonding jumper” in Step 1, and added “across the bonding jumper” to Step 2 for clarification.Revised the Concern statement for 28-AWL-11, replacing "EMI" with "EME" and deleting "outside of the tank". Added the definition/requirements for new wiring, and clarified the requirements for repaired/replaced wiring.Revised 28-AWL-12 to clarify that the Auxiliary Tank Refuel Valve controlled by the AWL is the Solenoid Actuator Refuel Valve on 

the Center Wing Tank Rear Spar. Clarified the Aux Tank Refuel Valve requirement of this CDCCL is only applicable to 777 airplanes with the Aux Tank Refuel Valve installed. Revised Step 2 to clarify that the fillet seal is applied around the entire perimeter of the valve body.Revised 28-AWL-13 by deleting the note for modifying/upgrading FQPU Part No. 0310KPU02 to eliminate redundancy, since the only CMMs that can be used for maintenance of the FQPU are already listed in the CDCCL.Revised 28-AWL-14 by adding “water detector” to the Concern statement and replaced “Repair and overhaul” with “Maintenance of”, where applicable.Revised 28-AWL-15 by changing Step 1.a.I. from "wire separation requirement of 0.125 in" to "wires not in contact with the 

structure". Further clarified the critical design features and precluded those already covered in 28-AWL-04.Revised the title of 28-AWL-16 by replacing “Configuration” with “Lightning Protection” for clarification. Revised Step 1 to clarify which door positions are required to have the phenolic strip and added more critical design features to the AWL that are required to 

be maintained.Revised 28-AWL-17 by adding “or GFIs” to the title, and clarified the steps required prior to resetting of GFIs and circuit breakers.Revised the title of 28-AWL-18 by adding “and Ground Fault Protector (GFP)” and added GFP to the task, as needed, for further clarification.

(Continued on next page)

Co

REVISION AND REVISION DESCRIPTION 

OCT 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

FEBRUARY 2012, ContinuedRevised the title of 28-AWL-19 from “Lightning and Fault Current Protection – Motor Operated Valve (MOV) Actuator” to “Motor Operated Valve (MOV) Actuator – Lightning and Fault Current Protection”. Deleted SB 777-28A0059 from the Applicability due to the SB cancellation. Revised the AWL by separating the critical design feature requirements for MOV with adapter plate and MOVwithout adapter plate.Revised the title of 28-AWL-20, replacing “Repair” with “Output Shaft Electrical Isolator” for clarification. Revised Applicability to 

“ALL/NOTE” and added the following Note for clarification: “Applies only to ITT actuators with Part Number MA20A2027 or MA30A1001”. Revised the second paragraph by adding “if the actuator was removed for bench testing or repair" to clarify the 

condition that requires a Dielectric Strength Test.Revised 28-AWL-21 by adding an inspection of the wire sleeving, if installed, and adding requirement to ensure wires are not in

contact with the surface of the auxiliary tank when repairing wires. Revised the SWPM reference from 20-10 to 20-10-11 and 20-10-13 for further clarification.Revised the title of 28-AWL-23 to “Auxiliary Tank AC Fuel Pump Fault Current Bonding Path”. Replaced “path to structure” in the 

Concern statement with “path through the motor impeller assembly” and added “from the pump” to the end of the last sentence for

clarification. The requirement for auxiliary tank installation/replacement was moved to new AWL 28-AWL-27. Revised Steps 2a 

and 2b to clarify the bonding resistance measurement location and value. Added Step 3 to ensure that fuel pump maintenance meets the requirements outlined in 28-AWL-07.Revised 28-AWL-24 by adding “must be maintained” to the first paragraph, and “are installed” to Step 1 for clarification.Revised 28-AWL-25, replacing “verify the following” with “the following must be maintained:”, and changed the numbering format of 

the listed items.Added AWL 28-AWL-27 for the auxiliary fuel tank replacement or installation which was previously part of 28-AWL-23 to further 

clarify the bonding resistance values and the critical design features that must be maintained.Added three new subsections to Section D: D.1 – Fuel Systems Ignition Prevention, D.2 – Engine Suction Feed System, and D.3 – Nitrogen Generation System (NGS).Added new ALI, 28-AWL-101 - Engine Fuel Suction Feed Operational Test, that is required to protect against engine flameout during suction feed operations.Added a new subheading for the table of AWLs – NGS Tasks in Section D.3.Revised the heading for Section E, making it a subparagraph of Section D, then relettered the remaining headings accordingly.

Co

MAY 2013Added Section D.4 - Rolls Royce Thrust Reverser Thermal Protection System. Added Airworthiness Limitation 78-AWL-01 for the Rolls Royce Thrust Reverser Thermal Protection System.Added Airworthiness Limitation 78-AWL-02 for the Rolls Royce Thrust Reverser Inner Wall.

REVISION AND REVISION DESCRIPTION 

OCT 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

JUNE 2013Added new CMR 25-CMR-01 to operationally check AMSAFE NexGen inflatable seat restraints, EMA Part Number 511959-XXXXX.MARCH 2014Revised the document to define FAA Oversight Office and replaced all references of "Seattle FAA ACO or BASOO" with "FAA 

Oversight Office" throughout the entire document.References to FAA regulations were changed to include "Title 14 CFR §" to accurately reflect FAA regulation citations throughout 

the document and for consistency.Revised the subparagraph title "Airworthiness Limitations - Structural Inspections" to "Airworthiness Limitations" under Section A 

"Scope".Revised Section D front matter with the following:Moved the subparagraph "Regulatory Agency Approval", "AWL Revision Process" and “Accomplishment Instructions - General 

Information” to after the "Introduction" subparagraph.Changed "per" to "in accordance with" throughout the entire Section D except for the "per" in the AWL 28-AWL-04 (Step 2), 28-AWL-15 (Step 2), 28-AWL-23 (Step 3), and 47-AWL-03. The word "per" in the AWL 28-AWL-04 (Step 2), 28-AWL-15 (Step 2), and 28-AWL-23 (Step 3) was changed to "as specified in". The word "per" in the AWL 47-AWL-03 was replaced with "as required by".Revised "Accomplishment Instructions - General Information" subparagraph to provide clarification of the use of "in accordance with" and "refer to" verbiage when referencing other Instructions for Continued Airworthiness documents.Revised the "Use of Alternate or Equivalent Tools, Test Equipment or Materials" subparagraph to delete the information on acceptable sealant type for fuel tank since the sealant type is defined in the "Definitions" subparagraph.Revised "Definitions" subparagraph to define FAA Oversight Office.Revised AWL 28-AWL-09 to provide clarification when a repair or alteration involving new or altered fuel tank penetrations requires 

FAA Oversight Office approval and when a repair or alteration does not require additional FAA Oversight Office approval. Added additional notation to require electrical bonding of fitting, brackets, cap sealing fasteners, and/or fillet sealing of component 

interface.Added Section D.4 Pratt and Whitney Forward Strut Drain Line and new Airworthiness Limitation 54-AWL-01 to address potential clogging of the Pratt and Whitney Forward Strut Drain Line.Renumbered Section D.4 Rolls Royce Thrust Reverser Thermal Protection System to Section D.5 to list AWLs in ATA sequence.Revised "Exceptional Short-Term Extensions" under Section E to change Flight Standards Handbook from "8300.10" to "8900.1 FSIMS".

REVISION AND REVISION DESCRIPTION 

OCT 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

MAY 2014Revised the Airworthiness Limitations - Structural Inspections section to clarify Front Matter and Table Notes.Added Front Matter to the Airworthiness Limitations – Structural Inspections section to clarify 777 airplane designations.Revised Front Matter in the Airworthiness Limitations – Structural Inspections section to clarify Removable Structural Components (RSC) requirements.Added Maintenance Review Board Report (MRBR) Task references associated with structural items requiring excess sealant to 

be removed.Revised the Excess Sealant inspection to the Wing Side of Body Splice Upper Surface (777 ALL) by providing an alternative inspection requirement.Revised excess sealant removal Table Notes to clarify optional inspections and NDT Procedure references that may be used in lieu of sealant removal.Revised the AMM procedure references for excess sealant removal and application.Revised Flag Note (7) to Flag Note (8) in the Airworthiness Limitations - Structural Inspections table, since the NDT Procedures for 

the corresponding SSIs are accepted by the FAA and published in the NDT Manual, D634W301.Revised 78-AWL-02 applicability to include Service Bulletin 777-78A0094 and P/N 315W5295-97/-98/-99/-100 and higher, and to clarify that this AWL applies to each thrust reverser half independently. Revised description for clarity and to correct color chip 

terminology.

OCTOBER 2014Deleted the Boeing submittal signature column from the Revision Log to improve the layout and provide consistency across all Section 9/AWL/CMR/SCI documents. A submittal signature will no longer be included in the revision log; only the FAA BASOO 

approval date will be shown.Revised CMR 25-CMR-01 interval from 285 DY to 375 DY based on updated System Safety Assessment.

REVISION AND REVISION DESCRIPTION 

OCT 2014
Section Page Date Section Page Date Section Page Date Section Page Date 

D622W001-9

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

LIST OF EFFECTIVE PAGES

777 MAINTENANCE PLANNING DATA

9.0 1 OCT 20149.0 2 BLANK9.0 3 OCT 20149.0 4 BLANK9.0 5 OCT 20149.0 6 OCT 20149.0 7 OCT 20149.0 8 OCT 20149.0 9 OCT 20149.0 10 OCT 20149.0 11 OCT 20149.0 12 OCT 20149.0 13 OCT 20149.0 14 OCT 20149.0 15 OCT 20149.0 16 OCT 20149.0 17 OCT 20149.0 18 OCT 20149.0 19 OCT 20149.0 20 OCT 20149.0 21 MAR 20149.0 22 MAY 20149.0 23 MAY 20149.0 24 MAY 20149.0 25 MAY 20149.0 26 MAY 20149.0 27 MAY 20149.0 28 MAY 20149.0 29 MAY 20149.0 30 MAY 20149.0 31 MAY 20149.0 32 MAY 20149.0 33 MAY 20149.0 34 MAY 20149.0 35 MAY 20149.0 36 MAY 20149.0 37 MAY 20149.0 38 MAY 20149.0 39 MAY 2014

9.0 40 MAY 20149.0 41 MAY 20149.0 42 MAY 20149.0 43 MAY 20149.0 44 MAY 20149.0 45 MAY 20149.0 46 MAY 20149.0 47 MAY 20149.0 48 MAY 20149.0 49 MAY 20149.0 50 MAY 20149.0 51 MAY 20149.0 52 MAY 20149.0 53 MAY 20149.0 54 MAY 20149.0 55 MAY 20149.0 56 MAY 20149.0 57 MAY 20149.0 58 MAY 20149.0 59 MAY 20149.0 60 MAY 20149.0 61 MAY 20149.0 62 MAY 20149.0 63 MAY 20149.0 64 MAY 20149.0 65 MAY 20149.0 66 MAY 20149.0 67 MAY 20149.0 68 MAY 20149.0 69 MAY 20149.0 70 MAY 20149.0 71 MAY 20149.0 72 MAY 20149.0 73 MAY 20149.0 74 MAY 20149.0 75 MAY 20149.0 76 MAY 20149.0 77 MAY 20149.0 78 MAY 2014

9.0 79 MAY 20149.0 80 MAY 20149.0 81 MAY 20149.0 82 MAY 20149.0 83 MAY 20149.0 84 MAY 20149.0 85 MAY 20149.0 86 MAY 20149.0 87 MAY 20149.0 88 MAY 20149.0 89 MAY 20149.0 90 MAY 20149.0 91 MAY 20149.0 92 MAY 20149.0 93 MAY 20149.0 94 MAY 20149.0 95 MAY 20149.0 96 MAY 20149.0 97 MAY 20149.0 98 MAY 20149.0 99 MAY 20149.0 100 MAY 20149.0 101 MAY 20149.0 102 MAY 20149.0 103 MAY 20149.0 104 MAY 20149.0 105 MAY 20149.0 106 MAY 20149.0 107 NOV 20089.0 108 MAY 20149.0 109 FEB 20129.0 110 FEB 20129.0 111 JAN 20099.0 112 JAN 20099.0 113 JAN 20099.0 114 MAR 20149.0 115 MAR 20149.0 116 MAR 20149.0 117 MAR 2014

9.0 118 FEB 20129.0 119 MAR 20149.0 120 MAR 20149.0 121 MAR 20149.0 122 MAR 20149.0 123 MAR 20149.0 124 MAR 20149.0 125 MAR 20149.0 126 MAR 20149.0 127 MAR 20149.0 128 MAR 20149.0 129 MAR 20149.0 130 MAR 20149.0 131 MAR 20149.0 132 MAR 20149.0 133 MAR 20149.0 134 MAR 20149.0 135 MAR 20149.0 136 FEB 20129.0 137 FEB 20129.0 138 MAR 20149.0 139 MAR 20149.0 140 MAR 20149.0 141 MAR 20149.0 142 MAR 20149.0 143 MAR 20149.0 144 MAR 20149.0 145 MAR 20149.0 146 MAY 20139.0 147 MAY 20149.0 148 MAR 20149.0 149 MAR 20149.0 150 MAR 20149.0 151 MAR 20149.0 152 MAR 20069.0 153 MAR 20149.0 154 OCT 20149.0 155 JAN 20119.0 156 JAN 2011

OCT 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

A. SCOPE

The scheduled maintenance requirements described in this document result from Model 777 airplane certification activities with 

Administration (FAA). Accordingly, this FAA approved Airworthiness Limitations and Certification Maintenance Requirements dreferenced in the Model 777 Type Certificate Data Sheet. These maintenance actions are mandatory. These Airworthiness Limitations sections are FAA approved and specifies maintenance required under Title 14 Code of Federa§ 43.16 and § 91.403 unless an alternative program has been FAA Oversight Office approved.Where used in this document, the term “FAA Oversight Office” is defined as the FAA office that currently has oversight responsof the Boeing model 777. At the time of publication, the FAA office with oversight responsibility for the type certificate of the 777 

Safety Oversight Office (BASOO).AIRWORTHINESS LIMITATIONSThe Airworthiness Limitations may only be revised with the approval of the FAA Oversight Office.If the inspections cannot be accomplished due to repairs and/or modifications, an alternate inspection approved by the FAA Ov

used.CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)These scheduled maintenance tasks may only be revised by the FAA Oversight Office. Principal Maintenance Inspectors (locanot change these requirements or the intervals associated with these requirements.

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

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

describes an initial baseline structural maintenance program for all Structural Significant Items (SSIs). This program was develoguidelines of MSG-3 and partially satisfies the requirements of Title 14 CFR § 25.571 by providing accidental and environmenta

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

supplemental structural inspections listed in this Section 9 "Airworthiness Limitations" are for those SSIs that do not receive adedetection opportunity from the initial baseline structural program that is listed in Section 2 and in Appendix L. The inspections sAppendix L are to be accomplished in conjunction with and not as a substitute for the existing structural maintenance program 

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

necessary to provide adequate fatigue damage detection. The DTR system defines a required DTR (a numerical value) that mu

SSI. DTR Check Forms which define the inspection options and the required DTR are contained in Document D622W001-DTRThe Airworthiness Limitations may only be revised with the approval of the FAA Oversight Office. If the inspections cannot be a

and/or modifications, an alternate inspection approved by the FAA Oversight Office must be used. An exception to this is allowinspections are for a condition where:1. An existing repair prevents proper accomplishment of the inspections required by sub-section B and2. The required damage tolerance inspections for the repair have been FAA-approved as meeting the damage tolerance requ

14 CFR § 25.571(b) and 14 CFR § 26.43(c) or 14 CFR § 26.43(d) and

3. The inspections required by Sub-section B are for a lead crack (as identified on the associated Damage Tolerance Rating (D

which is repaired.

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

For this condition, the inspection requirements approved for the repair plus the inspection requirements of Sub-section B for any 

acceptable alternative inspections.THRESHOLD (777-200/200LR/300/300ER Airplanes)NOTE: In this section, "777-200" includes airplanes sometimes referred to as 777-200ER or 777-200IGW because those airp

airplanes per the applicable FAA Type Certificate.

The fatigue inspection requirements apply after accumulation of a certain number of flights (threshold). The initial fatigue inspec

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

must be within one inspection interval of the threshold and must never exceed the Group 2 limit in Figure 1. “FLS” Group 2 item

Group 2 limit in Figure 1. The threshold for each of the 777-200/200LR/300/300ER aircraft fatigue inspections is defined in the 

Table.When reaching a threshold of 40,000 flight cycles, all MPD 4,000 flight cycle (or higher) structural inspection repeat intervals mu

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

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

for which the required DTR is not met by the baseline structural inspections of Section 2. Any continued escalation beyond the 

program may 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 apPrevention and Control Program (CPCP) has occurred, constituting CPCP implementation. The Corrosion Prevention and Cont

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

requirement if it has been fully incorporated into the operator's maintenance program.

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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

§ 25.571. As a result, at 40,000 flight cycles, the items listed in Appendix L are required to be returned to the interval in that aplisted in 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 it

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

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

For the 777-200/200LR/300/300ER, SSIs are also categorized as Group (1) or Group (2). Group 1 SSI Inspection Thresholds 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 fl

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 2of 11,250 flights for the 777-200LR airplanes that have the optional auxiliary fuel tank installations. All other 777-200LR/300ER 

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

minimum threshold for those items which are identified as flight length sensitive must be determined from Figure 1, based upon utilization.Initial inspection (threshold) and intervals are measured in flight cycles or flight hours that a particular SSI detail has accumulat

airframe as a whole has accumulated. Most SSI details have never been replaced and therefore have accumulated the same f

as the airframe. Some SSI details are replaced, such as when installing Removable Structural Components (repairable/rotable

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

be applied to the baseline structure.Inspection thresholds for fastener locations where the terminating action has been accomplished per AD 2000-11-11 or AD 200

time when the terminating action was accomplished.

FIGURE 1. FLIGHT LENGTH SENSITIVE (FLS) THRESHOLD CURVE (777-200/200LR/-300

NOTE: In Figure 1 and the discussion of flight length sensitive threshold that immediately follows this note, "777-200" includes 

as 777-200ER or 777-200IGW since those airplanes are certified as 777-200 airplanes per the applicable FAA Type C

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 I

point is on the Threshold Curve for the specified group, then the Inspection Threshold has been reached. If the point is aboThreshold Curve for the specified group, then the Inspection Threshold has been exceeded.

THRESHOLD (777F Airplanes)The fatigue inspection requirements apply after accumulation of a certain number of flights (threshold). The initial fatigue inspecaccomplished at the threshold defined in the Structural Inspections Table, or within an interval not to exceed 2,500 flight cycles “FLS” Group 1 items must be within one inspection interval of the threshold and must never exceed the Group 2 limit in Figure must never exceed the Group 2 limit in Figure 2. The threshold for 777F aircraft fatigue inspections is defined in the Structural When reaching a threshold of 25,000 flight cycles, all MPD 4,000 flight cycle (or higher) structural inspection repeat intervals mushown in the MPD Section 2. This means that any operator, who has escalated the structures program by changing task intervfrequencies back to the MPD baseline structures program intervals before accumulating 25,000 flight cycles. The reason for th

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

for which the required DTR is not met by the baseline structural inspections of Section 2. Any continued escalation beyond the 

program may 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 ap

Prevention and Control Program (CPCP) has occurred, constituting CPCP implementation. The CPCP identified within the StruProgram of the 777 Maintenance Review Board Report (D622W001-MRBR) is FAA approved and complies with this requiremeincorporated into the operator’s maintenance program.

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

§ 25.571. As a result, at 25,000 flight cycles, the items listed in Appendix L are required to be returned to the interval in that aplisted in 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 fli

by FLS in the Threshold column of the Structural Inspections Table (See Figure 2). Flight Length Sensitive (FLS) Items require cycles 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 Group 2 SSI Inspection Thresholds are limited to a maximum of 25,000 flight cycles.For those items which are not flight length sensitive, the lowest threshold shown in the Structural Inspections Table is 18,750 fl

which are not flight length sensitive have either a 18,750 flight threshold or 25,000 flight threshold depending upon whether the 

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.Initial inspection (threshold) and intervals are measured in flight cycles or flight hours that a particular SSI detail has accumulat

airframe as a whole has accumulated. Most SSI details have never been replaced and therefore have accumulated the same f

as the airframe. Some SSI details are replaced, such as when installing Removable Structural Components (repairable/rotable

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

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

be applied to the baseline structure.

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

FIGURE 2. FLIGHT LENGTH SENSITIVE (FLS) THRESHOLD CURVE (777F ONL

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 I

point is on the Threshold Curve for the specified group, then the Inspection Threshold has been reached. If the point is aboThreshold Curve for the specified group, then the Inspection Threshold has been exceeded.

FLIGHT HOURS ( x 1,000)

Group 1 & 2Threshold ExceGroup 1 Thresh

ÏÏÏExceeded ÏÏÏÓÓÓÓÓÓ

ÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏ ÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏ ÏÏÏÏÏÏÏÏÏÏÏÏÏ ÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÏÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓ ÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓ ÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓ ÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓÓ

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

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

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

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

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

should be used for determining which DTR Check Form should be utilized.NOTE: In the paragraph immediately preceding this note, "777-200" includes airplanes sometimes referred to as 777-200ER o

airplanes are certified as 777-200 airplanes per the applicable FAA Type Certificate.

REPORTING RESULTS OF STRUCTURAL INSPECTIONSAll cracks found during these inspections shall be reported within (10) days after the airplane is returned to service to the Mana

Office, the Transport Airplane Directorate, the FAA, and to Boeing Commercial Airplane Group using the Discrepant Structure 

D622W001-DTR for the required report 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 o

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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

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

Principle Structural Element 

(PSE) Threshold

Installation 

Drawing Drawing Title Notes

Fuselage – Underwing Longeron (777 All)

P: 40,000 FC

F: 25,000 FC

140W9250 Underwing Longeron 

Instl

1. Fasteners on the Underwing 

common to the Fuselage FroBulkhead Outer Chord within forward of the Wing Front Sparea, also remove excess filthe free edge of the longeroextends more than 0.25” frofuselage skin surface.

2. Fasteners on the Underwing 

common to the Wing Lower S3 inches aft of the Fuselage Bulkhead. In this area, also excess fillet seal at the free elongeron that extends more from the lower wing skin sur

NOTE: Does not require sealan

inside the fuel tank.

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 SidFitting within 6 inches above and the Wing Upper Surface. NOTE: Does not require seala

inside the fuel tank.

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 SidFitting within 6 inches above and the Wing Upper Surface. NOTE: Does not require seala

inside the fuel tank.

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 spacommon to upper spar webs betNSTA 245.0 and 255.0 and betwNSTA 319.0 and 333.0, except wchord is not visible.

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 uppe

chord common to upper spabetween NSTA 213.5 and 23fasteners on the RHS upper common to the forward engibulkhead between NSTA 18192.0, except where spar chnot visible.

2. Fasteners on the LHS uppe

chords common to the bulkhbetween NSTA 303.0 and 3except where spar chord is n

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 spar cho

common to forward engine moubulkhead between NSTA 187.0 aexcept where spar chord is not v

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 ExternaPlate common to the Rear Spar Fitting and Upper Rear Spar ExtSplice Fitting within 3 inches of B

Principle Structural Element 

(PSE) Threshold

Installation 

Drawing Drawing Title Notes

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 Rear SpExternal Splice Fitting common tRear Spar Terminal Fitting and UExternal Splice Plate within 3 incof BL 0.

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 Spar TerFitting common to the Upper ReExternal Splice Fitting and UppeSplice Plate within 3 inches of B

Principle Structural Element 

(PSE) Threshold

Installation 

Drawing Drawing Title Notes

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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)

Upper Panel Instl Integration – BBL 122.45

Outboard fastener row on the Ricommon to the upper skin panel inches of BBL 122.45.Inspect the Rib Chord upper surffollowing locations:1. At all field fasteners (fasten

are not common to upper ststub beams)

2. Between the forward fasten

common to Stringer 13 and fastener row common to Str

3. Between the forward fasten

common to Stringer 19 and fastener row common to Str

4. At one fastener location com

each vent stringer (Stringerand 21).

Cap seals and secondary fuel banot need to be removed at the inlocations above, provided that a dimension of 0.70" is visible betwadjacent cap seals in the forwardirection. If the minimum visible dimension of 0.70" is not met, caand secondary fuel barrier remorequired or surface HFEC inspebe performed per the Table NoteNOTE: Does not require seala

inside the fuel tank.

Principle Structural Element 

(PSE) Threshold

Installation 

Drawing Drawing Title Notes

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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

F: = 777F (Freighter) airplanesAs an option to sealant removal: Perform surface HFEC inspection 360 degrees around the fastener per N

sealant does not extend beyond 0.50" from the fastener, perform surface HFEC inspection 360 degrees a

fastener per NDT Part 6, 51-00-01 for aluminum parts, 51-00-05 for steel parts, or 51-00-06 for titanium pa

NOTE: In the immediately preceding Table Notes, airplanes identified as "777-200IGW" are 777-200 airplanes that have been 

capability of MTW>547,000 lbs. This includes airplanes sometimes called "777-200ER" airplanes. All of these airplan

series airplanes per the applicable FAA Type Certificate. 777-200LR airplanes are not included in the group of airplan777-200IGW.

3. General Notes:

Refer to AMM 51-31-01 for general sealant removal and application.Refer to AMM 28-11-00 for sealant (BMS 5-45) inside the fuel tank removal and application.Refer to AMM 28-11-00 for secondary fuel barrier sealant (BMS 5-81, Type II) outside the fuel tank removal and applicationIf 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 

Bulletins or repair instructions) after completion of the inspections. Sealant of fuel tank fasteners must comply with MPD S

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

112W3301 

(Outboard)

Rib Chord Instl – Upper Panel, BBL 122.45

Inboard fastener row on the Rib common to the upper skin paneloutboard within 2 inches of BBL NOTE: Does not require seala

inside the fuel tank.

Principle Structural Element 

(PSE) Threshold

Installation 

Drawing Drawing Title Notes

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

SUPPLEMENTAL STRUCTURAL INSPECTION REQUIREMENTSThe table starting on the next page lists the Airworthiness Limitation supplemental structural inspection requirements. Each iteDTR Check Form Title, DTR Location, and Airplane Applicability/Threshold. There are corresponding DTR Check Forms in D6listed in the table. Where there is more than one listing for a given SSI Number, the DTR Check Form title and location is the u

Airplane applicability is listed as shown below: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 certified for a structural capability greater than 547,000 lbs. MTW (also 777-200ER). This consists of all airplanes identified by Customer Variable Numbers (Manufacturer Block Nu

through WB500 and WC001 through WC999. If needed, refer to the 777 Structural Repair Manual front matAircraft “Manufacturer Block Number” to determine the associated Manufacturer Serial Numbers.

-200LR = 777-200LR (Longer Range)777F = 777 FreighterRR = Rolls Royce TRENT = TRENT 800 (875-17, 877-17, 884-17, 890-17, 892, 892B, 895)

PW = Pratt & Whitney PW4000 = PW4074, PW4077, PW4084, PW4090, PW4098GE = General Electric GE90 = 75B/76B/85B/90B/94B/110B/115BNOTE: C/L or L/N = Airplane Cumulative Line Number, where mentioned with DTR Check Form Title, identifies certain

 DTR Check Forms to specific airplane line numbers.NOTE: “777” without any suffix means the form applies to all 777 airplanes.

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

27-41-I01 Safety Rod, Horizontal Stabilizer 

Trim Actuator

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

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 

52-34-I03A Large Cargo Door Latch Support 

Frame Fittings

Latch Cam Support Fitting Lug Bore

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

52-34-I03B Large Cargo Door Latch Support 

Frame Fitting (135W1191)

Outer Chord 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

52-34-I05A Large Cargo Door Latch Frame 

Inner Chord

Splice to Latch Support Fitting 1 30,000 

(8)

30,000 

(8)

30,000 

(8)

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 

(8)

30,000 

(8)

52-37-I03A Large Cargo Door Latch Support 

Frame Fittings

Latch Cam Support Fitting Lug Bore

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

52-37-I03B Large Cargo Door Latch Support 

Frame Fitting (135W1191)

Outer Chord 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

52-37-I05A Large Cargo Door Latch Frame 

Inner Chord

Splice to Latch Support Fitting 1 30,000 

(8)

30,000 

(8)

30,000 

(8)

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 

(8)

30,000 

(8)

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

52-38-I01 Main Deck Cargo Door – Main Latch 

Cam Assemblies

Main Rotary Cam Latch – Cam Shaft

1 

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 

(8)

40,000 

(8)

40,000 

(8)

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

Stringer

2 30,000 

(8)

30,000 

(8)

30,000 

(8)

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

Cutout

2 30,000 

(8)

30,000 

(8)

30,000 

(8)

53-10-I02D Crown Skin Production ACL 

Installation

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

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(8)

40,000 

(8)

53-10-I07B Longitudinal Skin Lap Splices Outer 

Skin

Typical – All Section 41 Lap Splices

2 40,000 40,000 40,000 

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

Lower Corner @ STA 382

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

STA 382

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

(8)

40,000 

(8)

40,000 

(8)

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

Upper Sill

Sta 309.5 to Sta 357.25 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

(8)

40,000 

(8)

40,000 

(8)

53-10-I11B FWD Large Cargo Door – Cutout 

Outer Chord – Upper Sill

Body Station 592 to 613 1 30,000 

(8)

30,000 

(8)

30,000 

(8)

53-10-I11C Forward Large Cargo Door – Cutout Upper Sill, STA 487 to STA 508 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

53-10-I11D Forward Large Cargo Door – Cutout Lower Sill, STA 592 to STA 634 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

53-10-I14 Forward Equipment Bay Access 

Hatch Cutout Structure

STA 143.5 to 172.5 Forward of NLG Well

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

Structure

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

(8)

40,000 

(8)

40,000 

(8)

53-10-I18 NO. 1 Crew Window Cutout 

Structure

Lower Window Sill, Left and Right 2 40,000 40,000 40,000 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

53-10-I20 NO. 3 Crew Window Cutout 

Structure

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

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

(8)

30,000 

(8)

30,000 

(8)

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 

(8)

30,000 

(8)

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 

(8)

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 

(8)

40,000 

(8)

40,000 

(8)

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

(C/L 1 to 40)

STA 332.5 Aft End of Cutout 2 40,000 

(8)

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

(C/L 41 and on)

STA 332.5 Aft End of Cutout 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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 

(8)

40,000 

(8)

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 

(8)

40,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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

Bushing Interface

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

(8)

30,000 

(8)

30,000 

(8)

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 

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 

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 

(8)

40,000 

(8)

40,000 

(8)

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 

(8)

30,000 

(8)

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 

(8)

40,000 

(8)

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 

(8)

53-30-I05-1 Fuselage Circumferential Skin/

Stringer Splice

BS 1035, Bulkhead Outer Chord 1 30,000 

(8)

53-30-I05-2 Fuselage Circumferential Skin/

Stringer Splice, BS 1035 (L/N 75 – and on)

Stringer End Fasteners 2 40,000 

(8)

40,000 

(8)

53-30-I05-2 Fuselage Circumferential Skin/

Stringer Splice

BS 1035, Stringer End Fasteners 2 40,000 

(8)

53-30-I05-3 Fuselage Circumferential Skin/

Stringer Splice, BS 1035 (L/N 75 – and on)

Paddle Fitting End Fasteners 2 40,000 

(8)

40,000 

(8)

53-30-I05-3 Fuselage Circumferential Skin/

Stringer Splice

BS 1035, Paddle Fitting End Fasteners

2 40,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

(8)

30,000 

(8)

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 

(8)

40,000 

(8)

53-30-I06A Longitudinal Skin Lap Splices

Inner Skin

All Section 43 Lap Splices except S-14

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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 

(8)

40,000 

(8)

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

STA 788.5

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

53-30-I12C Passenger Entry Door #2 – Cutout Bear strap 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

Upper Sill

Upper Sill, STA 718 to STA 755.5 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

STA 804

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

Door Stop Backup Fitting

Fittings #7A & 8A, #1A & #2A, STA 788.5

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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 

(8)

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(8)

40,000 

(8)

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 

(8)

40,000 

(8)

53-40-I03A Longitudinal Skin Lap Splices

Inner Skin

All Section 44 Lap Splices except at S-14

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

53-40-I03B Longitudinal Skin Lap Splices

Outer Skin

Typical – All Section 44 Lap Splices

2 40,000 40,000 40,000 

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 

(8)

40,000 

(8)

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 

(8)

40,000 

(8)

40,000 

(8)

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

Stringer 26

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

Attachment

BS 1245 at Stringer 27, Fastener in Inner Chord

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

53-40-I07 Aft Wheel Well Bulkhead Inner 

Chord Splice

BS 1434, Upper Crown Slice at Top Centerline

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

53-40-I14A Passenger Entry Overwing Door 

#3 Cutout

Upper and Lower corners at STA 1154 and 1204

1 30,000 

(8)

53-40-I14B Passenger Entry Overwing Door 

#3 Cutout

Edge Frame Inner Chord and Web at STA 1154.4 and 1204

2 40,000 

(8)

53-40-I14C Passenger Entry Overwing Door 

#3 Cutout

Edge Frame Inner Chord at STA 1154.4 and 1204

2 40,000 

(8)

53-40-I14D Passenger Entry Overwing Door 

#3 Cutout

Edge Frame Straps at STA 1154.4 and 1204

2 40,000 

(7)

53-40-I14E Passenger Entry Overwing Door 

#3 Cutout Upper Main Sill

Upper Main Sill, STA 1140 to 1180

2 40,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

Inner Chord Splice

BS 1434, Splice at Stringer 21 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

Outer Chord

BS 1434 From Stringer 28 to Stringer 45

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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 

(8)

40,000 

(8)

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 

(8)

30,000 

(8)

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 

(8)

40,000 

(8)

53-60-I01 Crown Panel, Skin and Stringer 

Section 46

At Skin to Stringer Fastener Locations

2 40,000 

(8)

40,000 

(8)

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 

(8)

53-60-I06-1 Fuselage Circumferential Skin/

Stringer Splice

BS 1434, Bulkhead Outer Chord 1 30,000 

(8)

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 

(8)

40,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

53-60-I06-2 Fuselage Circumferential Skin/

Stringer Splice

BS 1434, Stringer End Fasteners 2 40,000 

(8)

53-60-I06-2 Fuselage Circumferential Skin/

Stringer Splice

BS 1434, Stringer End Fasteners 2 

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 

(8)

53-60-I06-3 Fuselage Circumferential Skin/

Stringer Splice

BS 1434, Paddle Fitting End Fasteners

2 40,000 

(8)

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 

(8)

30,000 

(8)

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 

(8)

40,000 

(8)

53-60-I07A Longitudinal Skin Lap Splices Inner 

Skin

All Section 46 Lap Splices except at S-5

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

53-60-I07B Longitudinal Skin Lap Splices

Outer Skin

Typical – All Section 46 Lap Splices

2 40,000 40,000 40,000 

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 

(8)

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

 (8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

#4 (-300ER) – Cutout

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

2 <

F

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 

(8)

F

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 

(8)

40,000 

(8)

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

(-300) Cutout

Bear Strap 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

(-300) – Cutout

Upper Main Sill, STA 1540 to STA 1567

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

(-300) – Cutout

Lower Main Sill, STA 1476 to STA 1513.5

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

53-60-I14A Small Cargo Door – Cutout Lower 

Main Sill

Body Station 1678.5 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

53-60-I14B Small Cargo Door – Cutout Upper 

Main Sill

Body Station 1740 to 1769 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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 

(8)

40,000 

(8)

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 

(8)

40,000 

(8)

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 

(8)

40,000 

(8)

40,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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

(8)

40,000 

(8)

40,000 

(8)

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

(8)

30,000 

(8)

30,000 

(8)

53-60-I16B Aft Large Cargo Door – Cutout Outer 

Chord – Upper Sill

Body Station 1683 to 1694 1 30,000 

(8)

30,000 

(8)

30,000 

(8)

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

Sill

STA 1769 to STA 1811 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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 

(8)

30,000 

(8)

30,000 

(8)

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 

(8)

40,000 

(8)

53-70-I04A Longitudinal Skin Lap Splices

Inner Skin

All Section 47 Lap Splices except at S-5

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

53-70-I04B Longitudinal Skin Lap Splices

Outer Skin

Typical – All Section 47 Lap Splices

2 40,000 40,000 40,000 

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

(-300) – Cutout

Edge Frames @ STA 2017 and STA 2067

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

(-300) – Cutout

Bear Strap 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

(-300) – Cutout

Section 47, Upper Sill, STA 2050 to STA 2087

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

(-300) – Cutout

Section 47, Lower Sill, STA 2000 to STA 2017

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

53-70-I09 Bulk Cargo Door – Cutout Edge 

Frames

STA 1895 from Stringer S-33R to S-40R, STA 1937 from Stringer S33R to S-35R

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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 

(8)

30,000 

(8)

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 

(8)

40,000 

(8)

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 

(8)

30,000 

(8)

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 

(8)

40,000 

(8)

53-80-I14A Stabilizer Pivot Bulkhead STA 2370 Vertical Stiffener at BL 36.5 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

53-80-I15 Stabilizer Pivot Fitting Lug; Section 

48

Station 2365 2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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

Station 2245

2 40,000 

(8)

40,000 

(8)

40,000 

(8)

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 

(8)

30,000 

(8)

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 

(8)

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

245 and 292 Left and Right

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 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 

(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 

(8)

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

between NSTA 317 and 330

1 30,000 

(8)

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)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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)

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

Common to Web and Chord, NSTA 261-281

1 30,000 

(8)

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

Common to Web and Chord, NSTA 261-281

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 

(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 

(8)

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

Bulkhead between NSTA 298 and 310

1 30,000 

(8)

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 

(8)

54-51-I05D Strut Forward Engine Mount 

Bulkhead Assembly (PW)

Front Flange at open GSE Holes 1 30,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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

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

and NSTA 245

1 30,000 

(8)

<= 7 Hrs, 

FLS, See 

Figure 1 

(8)

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

and NSTA 245

1 > 7 Hrs, 

FLS, See 

Figure 1 

(8)

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 

(8)

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 

(8)

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 

(8)

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 

(8)

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 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

(8)

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 

(8)

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 

(8)

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 

(8)

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

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

1 30,000 

(8)

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

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

1 30,000 

(8)

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 

(8)

<= 7 Hrs, 

FLS, See 

Figure 1 

(8)

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

NSTA 325

1 > 7 Hrs, 

FLS, See 

Figure 1 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
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) Bay 3 Fasteners Common to the 

Chord Between Frames at NSTA 230 and 245

1 30,000 

(8)

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 

(8)

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 

(8)

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 

(8)

30,000 

(8)

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 

(8)

30,000 

(8)

54-51-I04M Lower Spar (GE) Frames NSTA 213, 230, 245, 265, 

280, and 295, LH and RH Sides

1 30,000 

(8)

54-51-I04M Lower Spar (GE) Frame NSTA 213, 230, 245, 265, 

280, and 295, LH and RH Side

1 30,000 

(8)

54-51-I05A Forward Engine Mount Bulkhead 

(GE)

Tension Fitting Gusset at NSTA 186.65

1 30,000 

(8)

30,000 

(8)

54-51-I01i Aft Upper Spar Fitting R4 (GE) Horizontal Flange First Fastener 1 

F

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

NS 213-230

1 

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/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

NSTA 232-240

1 

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 <

F

54-51-I02e Strut Upper Spar Bay 5 (GE) Bay 5 Cutout Between NSTA 268 

and NSTA 277

1 

F

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 <

F

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

NSTA 292

1 

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

54-51-I02f RHS 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 

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

NSTA 305 and NSTA 315

1 

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 <

F

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

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

54-51-I02p Strut Upper Spar (GE) R1 Fitting Attachment NSTA 225 

to NSTA 268

1 

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 

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 <

F

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

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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

F

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

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 

F

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 <

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

F

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 

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

F

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

F

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 <

F

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

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 <

F

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 <

F

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

F

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

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

NSTA at 213-245

1 <

F

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

NSTA at 213-245

1 

F

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

and 245

1 

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 

F

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 <

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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

F

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

NSTA 264-309

1 

F

54-51-I04d Pylon Lower Spar (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-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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

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 <

F

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

NSTA 213-245

1 

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

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 <

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

F

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

F

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 <

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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

F

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 54-51-I07d Strut Aft Engine Mount Bulkhead 

(GE)

Cutout Flange 1 <

F

54-51-I07d Strut Aft Engine Mount Bulkhead 

(GE)

Cutout Flange 1 

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

325.33

1 <

F

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

325.33

1 

F

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 

(8)

30,000 

(8)

30,000 

(8)

54-51-I02C Forward Upper Spar (RR) Upper Spar at Frame/Bulkheads 1 30,000 

(8)

30,000 

(8)

30,000 

(8)

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 

(8)

30,000 

(8)

30,000 

(8)

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 

(8)

30,000 

(8)

30,000 

(8)

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 

(8)

30,000 

(8)

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 

(8)

54-51-I05A Forward Engine Mount Bulkhead 

(RR)

Fwd Engine Mount Bulkhead Tension Fitting End Pad

1 30,000 

(8)

30,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

54-51-I05A Forward Engine Mount Bulkhead 

(RR)

Fwd Engine Mount Bulkhead Tension Fitting End Pad

1 30,000 

(8)

54-51-I06A Aft Engine Mount Bulkhead (RR) R1 Fitting Attach Tension Fitting 1 30,000 

(8)

54-51-I06A Aft Engine Mount Bulkhead (RR) R1 Fitting Attach Tension Fitting 1 30,000 

(8)

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

End Pad

1 30,000 

(8)

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)

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)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

(8)

30,000 

(8)

55-12-I03 Upper Double Plus Chord Horizontal 

Stabilizer

BL 0.0 Skin/Stringer Splice 1 

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 

(8)

30,000 

(8)

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 

(8)

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 

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 

(8)

30,000 

(8)

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

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(8)

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 

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

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 

(8)

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 

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 

(8)

30,000 

(8)

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

T-Chord

1 30,000 

(8)

30,000 

(8)

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

T-Chord

1 30,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

T-Chord

1 <

F

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

T-Chord

1 

F

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

the T-Chord at Stringer L-1

1 

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, T-Chord All Fasteners locations not 

covered by splice plate

1 30,000 

(8)

30,000 

(8)

57-10-I02B SOB Splice, Lower Surface, T-Chord All Fasteners locations not 

covered by splice plate

1 30,000 

(8)

57-10-I02B SOB Splice, Lower Surface, T-Chord All Fasteners locations not 

covered by splice plate

1 <

F

57-10-I02B SOB Splice, Lower Surface, T-Chord All Fasteners locations not 

covered by splice plate

1 

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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, T-Chord INBD and OBD Flanges of 

T-chord @ Splice Plate (Str L1,L-10,L14,L-20 and L-23)

1 30,000 

(8)

30,000 

(8)

57-10-I02C SOB Splice, Lower Surface, T-Chord INBD and OBD Flanges of 

T-chord @ Splice Plate(Str L1,L-10,L14,L-20 and L-23)

1 30,000 

(8)

57-10-I02C SOB Splice, Lower Surface, T-Chord INBD and OBD Flanges of 

T-chord @ Splice Plate (Str L1,L-10,L14,L-20 and L-23)

1 <

F

57-10-I02C SOB Splice, Lower Surface, T-Chord INBD and OBD Flanges of 

T-chord @ Splice Plate (Str L1,L-10,L14,L-20 and L-23)

1 

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

(8)

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 

(8)

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

Chords (INBD and OBD of SOB rib)

1 30,000 

(8)

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

Chords (INBD and OBD of SOB rib)

1 <

F

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

Chords (INBD and OBD of SOB rib)

1 

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(8)

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 

(8)

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

Chords (INBD and OBD of SOB rib)

1 30,000 

(8)

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

Chords (INBD and OBD of SOB rib)

1 <

F

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

Chords (INBD and OBD of SOB rib)

1 

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

(8)

30,000 

(8)

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 

(8)

30,000 

(8)

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

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 <

F

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

Panel Typical Stringer

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

2 

F

57-15-I01A Wing Center Section – Lower Panel 

– Typical Stringer

All WCS Lower Panel Typical Stringers from SOB to SOB

2 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 <

F

57-15-I01B Wing Center Section – Lower Panel 

– Splice Stringer

All WCS Lower Panel Splice Stringers

2 

57-15-I01B Wing Center Section – Lower Panel 

– Splice Stringer

All WCS Lower Panel Splice Stringers

2 

F

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 

(8)

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 

(8)

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 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

Rear Spar Chord, Lower Chord

Rear Spar Lower Chord(WCS from SOB to SOB)

2 <

F

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

Rear Spar Chord, Lower Chord

Rear Spar Lower Chord (WCS from SOB to SOB)

2 

F

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-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 

(8)

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

Rear Spar Chord, Lower Skin

Rear Spar Lower Chord(WCS from SOB to SOB)

2 <

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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

Rear Spar Chord, Lower Skin

Rear Spar Lower Chord (WCS from SOB to SOB)

2 

F

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 

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 

(8)

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 

(8)

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 

(8)

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 <

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
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 

F

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 

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 

(8)

40,000 

(8)

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 

(8)

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(8)

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 

(8)

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)

57-20-I01A Wing Outboard, Typical Rear Spar 

Attachment, Lower Chord

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

2 <

F

57-20-I01A Wing Outboard, Typical Rear Spar 

Attachment, Lower Chord

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

2 

F

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 <

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-20-I01B Wing Outboard, Typical Rear Spar 

Attachment, Lower Chord

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

2 

F

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 

57-20-I01C Wing Outboard, Typical Rear Spar 

Attachment, Lower Skin

Rear Spar Chord Attachment at Trailing Edge fairing locations

2 <

F

57-20-I01C Wing Outboard, Typical Rear Spar 

Attachment, Lower Skin

Rear Spar Chord Attachment at Trailing Edge fairing locations

2 

F

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 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(8)

57-20-I01E Wing Outboard, Typical Splice 

Stringer

Stringer L10-L14 at Nacelle Fitting and Dry Bay Locations

2 <

F

57-20-I01E Wing Outboard, Typical Splice 

Stringer

Stringer L10-L14 at Nacelle Fitting and Dry Bay Locations

2 

F

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 

(8)

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 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

(8)

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 

(8)

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 

(8)

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)

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 <

F

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 

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 <

F

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 

F

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 

(8)

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)

57-20-I01J Wing Outboard, Lower Panel Front 

Spar Chord, Lower Chord

Skin to F/Spar Chord Attachment at Nacelle Fitting

1 <

F

57-20-I01J Wing Outboard, Lower Panel Front 

Spar Chord, Lower Chord

Skin to F/Spar Chord Attachment at Nacelle Fitting

1 

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 <

F

57-20-I01K Wing Outboard, Lower Panel Front 

Spar Chord, Lower Skin

Skin to F/Spar Chord Attachment at Nacelle Fitting

1 

F

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 <

F

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 <

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

F

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-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 <

F

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 

F

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 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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)

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 <

F

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 

F

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 

(8)

<= 7 Hrs, 

FLS, See 

Figure 1 

(8)

57-20-I01P Wing Outboard, Typical Stringer 

Attachment at Nacelle FTG

Typical stringers at Nacelle Fitting locations

2 > 7 Hrs, 

FLS, See 

Figure 1 

(8)

57-20-I01P Wing Outboard, Typical Stringer 

Attachment at Nacelle FTG

Typical stringers at Nacelle Fitting locations

2 40,000 

(7)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-20-I01P Wing Outboard, Typical Stringer 

Attachment at Nacelle FTG

Typical stringers at Nacelle Fitting locations

2 <

F

57-20-I01P Wing Outboard, Typical Stringer 

Attachment at Nacelle FTG

Typical stringers at Nacelle Fitting locations

2 

F

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 

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

57-20-I01R Wing Outboard, Typical Rail Stringer 

at Access Door

Typical Rail Stringers at Access door at Nacelle Fairing

2 <

F

57-20-I01R Wing Outboard, Typical Rail Stringer 

at Access Door

Typical Rail Stringers at Access door at Nacelle Fairing

2 

F

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 <

F

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 

F

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 <

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

F

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 

(8)

40,000 

(8)

40,000 

(8)

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 

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 <

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

F

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 

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

Spar Upper Chord

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

1 <

F

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

Spar Upper Chord

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

1 

F

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 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(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 30,000 

(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 <

F

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

Spar Upper Chord

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

1 

F

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 

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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

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 <

F

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

Spar Upper Chord

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

2 

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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-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 

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 

(8)

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 <

F

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 

F

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/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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-I04A Outboard Wing – Front Spar Splice 

between Ribs 43 and 44

Front Spar Splice between Ribs 43 and 44

1 <

F

57-20-I04A Outboard Wing – Front Spar Splice 

between Ribs 43 and 44

Front Spar Splice between Ribs 43 and 44

1 

F

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(8)

40,000 

(8)

57-53-I07A Inboard Main Flap Outboard 

Closeout Rib

Aft Access Hole 2 40,000 

(8)

57-53-I07A Inboard Main Flap Outboard 

Closeout Rib

Aft Access Hole 2 

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 

(8)

40,000 

(8)

40,000 

(8)

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 

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 

(8)

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 

57-53-I11A Inboard Main Flap Inboard Closeout 

Rib

Section thru Lower Chord at Forward Track Support

1 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

(8)

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 

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 

(8)

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 

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 

(8)

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

Support Underwing Fitting

Lugs, Inner Lug 1 30,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(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 

(8)

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

Support Underwing Fitting

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

1 

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 

(8)

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 

(8)

57-53-I18B No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Center Section 2 30,000 

(8)

57-53-I18B No. 3 (and No. 6) Inboard Flap 

Support Forward Tension Link

Center Section 2 

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 

(8)

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

(8)

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 

57-53-I20A No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

Aft Lug – Pin D (Forward and Aft Lugs)

2 

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 

(8)

57-53-I20B No. 3 (and No. 6) Inboard Flap 

Support Aft Tension Beam

General Section 2 40,000 

(8)

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 

(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 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(8)

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 

57-53-I21B No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Center Section thru Fastener 1 30,000 

(8)

57-53-I21B No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Center Section thru Fastener 1 30,000 

(8)

57-53-I21B No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Center Section thru Fastener 1 30,000 

(8)

57-53-I21B No. 3 (and No. 6) Inboard Flap 

Support Pivot Link

Center Section thru Fastener 1 

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 

(8)

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 

(8)

57-53-I24A No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Inboard Forward Arm 2 40,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-53-I24A No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Inboard Forward Arm 2 

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 

(8)

57-53-I24B No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

Cross-Over Beam 1 30,000 

(8)

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 

(8)

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 

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 

(8)

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 

57-53-I24F No. 3 (and No. 6 Inboard Flap 

Support Carrier Beam

'B' Point Lug 1 30,000 

(8)

30,000 

(8)

30,000 

(8)

57-53-I24G No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

'C' Point Lug 1 30,000 

(8)

30,000 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

57-53-I24G No. 3 (and No. 6) Inboard Flap 

Support Carrier Beam

'C' Point Lug 1 30,000 

(8)

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 

(8)

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 

57-53-I27B No. 4 (and No. 5) Inboard Flap 

Support Drive Arm

'B' Point Lugs 2 40,000 

(8)

40,000 

(8)

57-53-I27B No. 4 (and No. 5) Inboard Flap 

Support Drive Arm

'B' Point Lugs 2 40,000 

(8)

57-53-I27B No. 4 (and No. 5) Inboard Flap 

Support Drive Arm

'B' Point Lugs 2 

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 

(8)

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

57-53-I28B No. 4 (and No. 5) Inboard Flap 

Support Actuator Support Fitting

Point 'A' Lugs 2 40,000 

(8)

40,000 

(8)

57-53-I28B No. 4 (and No. 5) Inboard Flap 

Support Actuator Support Fitting

Point 'A' Lugs 2 40,000 

(8)

57-53-I28B No. 4 (and No. 5) Inboard Flap 

Support Actuator Support Fitting

Point 'A' Lugs 2 

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 

(8)

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 

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 

(8)

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 

57-53-I33 No. 4 (and No. 5) Inboard Flap 

Support Pins

Inner and Outer Pin B 1 30,000 30,000 30,000 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(8)

30,000 

(8)

57-54-I17A MLG FWD Trunnion Sideload Fitting All fastener locations C/T Sideload 

Fitting and Sideload Straps

2 40,000 

(8)

40,000 

(8)

57-54-I17A MLG FWD Trunnion Sideload Fitting All fastener locations C/T Sideload 

Fitting and Sideload Straps

2 40,000 

(8)

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

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 

(8)

40,000 

(8)

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 <

F

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 

F

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 

(8)

57-54-I19A MLG Drag Brace Support Fitting Section A-A Fitting Flange 2 40,000 

(8)

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 

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 

(8)

40,000 

(8)

40,000 

(8)

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 

AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

GROUP(4)

APPLICABILITY/TH

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

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 <

F

57-54-I19C MLG Drag Brace Internal Backup 

Fitting

Entire fitting c/t SOB Rib and Rear Spar, including Stiffening Ribs

2 

F

57-54-I19C 112W1756, MLG Drag Brace 

Support Back-up Fitting

Section A-A, Lead Crack in Base 2 

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/TH

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

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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. A

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 Number is provided to determine applicable plot in Figure 1 or 2 for items identified as "FLS”.5. Figure 1 is applicable to all 777-200 models (including 777-200IGW) for items identified as "FLS”.6. Thresholds that include "FLS" (e.g., "> 7 Hrs, FLS, See Figure 1 or Figure 2") are sensitive to flight length. All other values 7. No airplane may be operated beyond the stated threshold (or operational limit) until the applicable inspection procedures ar

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 th

inspection procedures can be accomplished and the inspection has been accomplished per the stated threshold requireme

published inspection procedure can not be accomplished, an alternative procedure must be used which the FAA has accep

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

INDIVIDUAL AIRPLANE SPECIFIC AIRWORTHINESS LIMITATIONSPURPOSEThe purpose of this section is to identify additional or revised Supplemental Structures Airworthiness Limitation (AWL) Structuraunique to a specific airplane serial number. Only those individual airplanes listed in this section have these additional or revise

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 airp

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 REQUIREMENT

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 all fa

common to web and NCR doubler/filler from side (except at radial stiffener) with HFEC pNon-Destructive Test (NDT) Manual, Part 6every 16,000 flight cycles.

2. Inspect the NCR doubler/filler at all fastene

pressure bulkhead web and NCR doubler/fiside with HFEC per the 777 NDT Manual, Pevery 16,000 flight cycles.

3. All other Supplemental Inspections required 

I13 in the preceding section must still be conat the fastener locations common to the NCfiller.

NOV 2008
D622W001-9

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

777 MAINTENANCE PLANNING DATA

C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE-LIFE LIMITS

NOTE: In this section, airplanes identified as "777-200IGW" are 777-200 airplanes that have been certified for a structural cap

This includes airplanes sometimes called "777-200ER" airplanes. All of these airplanes were certified as 777-200 serFAA Type Certificate. The airplanes identified as 777-200IGW airplanes in this section consist of all airplanes identified 

(Manufacturer Block Numbers) WB001 through WB500 and WC001 through WC999. If needed, refer to the 777 StrucEffective Aircraft “Manufacturer Block Number” to determine the associated Manufacturer Serial Numbers. 777-200LR 

group of airplanes identified as 777-200 or 777-200IGW.

C.1 STRUCTURAL SAFE-LIFE PARTS

LANDING GEAR: See Note L

777-200/-200IGW/-300 Nose Landing Gear  Except: Inner Cylinder 

777-200/-200IGW/-300 Main Landing Gear,  Except: Outer Cylinder, 161W1110-3 S/N 5JHW and 161W1110-4 S/N 1JHW 

 Outer Cylinder, 161W1110-3 S/N 4JHW and 161W1110-4 S/N 6JAN 

 Outer Cylinder, 161W1110-3 S/N 1JJW and 161W1110-4 S/N 3JRW 

 Outer Cylinder, 161W1110-3, -4, -9, -10 

 Outer Cylinder, Other Part Numbers 

 Lower Drag Strut, 161W4003 and 161W4103 

 Upper Side Strut Spindle, 161W0100 

 Lower Actuator Attach Pin, 161W1020 

 Spacer Tube, 161W1159  Aft Trunnion Pin, 161W1301 

 Lower Side Strut Spindle, 161W1310 

777-200/-200IGW/-300 Main Landing Gear Support Structure  Except: Load Distribution Plate – Outboard Gear Beam Support 112W1725-1, -3, -4, -19, -21, -22 

 112W1725-7, -8, -9, -10 

 112W1725-13, -14, -15, -16 

MAY 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

NOTE: Component Interchangeability Lists 161W0003 (Main Landing Gear) and 162W0002 (Nose Landing Gear) provide com

777-200/200IGW/200LR/300/300ER/777F landing gear related components subject to life limitations. 

 Pin – Fuse, Outboard Gear Beam Support, 112W1728-3, -9 

 112W1728-4, -5  112W1728-7 

 Pin – Fuse Retract Actuator, 112W1769 

 Hanger Pin Details (Fwd & Aft), 115W1510 

 Pin – Stabilizer Brace, MLG Beam, 115W1671 

* Sh

LANDING GEAR: L

777-200LR/300ER/777F Main Landing Gear 777-200LR/300ER/777F Main Landing Gear Support Structure 777-200LR/300ER/777F Nose Landing Gear 

FEB 2012
D622W001-9

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

777 MAINTENANCE PLANNING DATA

C.2 LIFE-LIMITED PARTSNOTE: Component Interchangeability Lists 161W0003 (Main Landing Gear) and 162W0002 (Nose Landing Gear) provides a 

777-200/200 IGW/200LR/300/300ER/777F landing gear related components subject to life limitations.

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 an

19-29. Incorporation of SB 777-32-0028 (reference Service Letters 777-SL-32-006 and 777-SL-001-E) removes the limit 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 additional 

test cycles are completed.

777-300ER Semi Lever Gear Hydraulic Strut (P/N 293W4201-2). 

FEB 2012
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 

the right of 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

JAN 2009
D622W001-9

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

777 MAINTENANCE PLANNING DATA

FIGURE 4. 777-200LR/300ER/777F MAIN LANDING GEAR SUPPORT FITTINGS SAFE-LI

Main Landing Gear Support Fittings Safe-Life Limits

124.95, 83.30

320.0

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)

JAN 2009
777 MAINTENANCE PLANNING DATA

D622W001-9

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

FIGURE 5. 777-200LR/300ER/777F NOSE LANDING GEAR SAFE-LIFE LIMITS

Nose Landing Gear Safe-Life Limits

348

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
D622W001-9

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

777 MAINTENANCE PLANNING DATA

D. AIRWORTHINESS LIMITATIONS – SYSTEMS

INTRODUCTIONThe airplane systems maintenance requirements described in this AWL document result from various 777 airplane certification 

Airworthiness Limitations section is FAA-approved and specifies maintenance required under Title 14 CFR § 43.16 and § 91.40

Regulations, unless an alternative program has been FAA Oversight Office approved. The AWLs may only be revised with the 

Oversight Office. If the maintenance requirements cannot be accomplished due to repairs and/or modifications, an alternate in

FAA Oversight Office, must be used.An AWL may be an Airworthiness Limitation Instruction (ALI) or a Critical Design Configuration Control Limitation (CDCCL).

CDCCLs are a means of identifying certain design configuration features intended to preclude a fuel tank ignition source for the 

airplane as required under Special Federal Aviation Regulation No. 88 (SFAR 88) - Fuel Tank System Fault Tolerance Evaluat

14 CFR § 25.981 - Fuel Tank Ignition Prevention. CDCCLs are mandatory and cannot be changed or deleted without the appro

Office. A critical fuel tank ignition source prevention feature may exist in the fuel system and its related installation or in system

were to develop, could interact with the fuel system in such a way that an unsafe condition would develop without this limitationconfiguration, methods, techniques, and practices as prescribed is required to ensure compliance with the CDCCL. Any use of or practices not contained in the applicable CDCCL must be approved by the FAA Oversight Office. For each CDCCL, the wor

maintaining any installation during alterations; therefore, adherence to the CDCCL is required during maintenance or alteration

ALIs identify inspection tasks that must be done to maintain the design level of safety for the operational life of the airplane to p

ALIs are mandatory and cannot be changed or deleted without the approval of the FAA Oversight Office. Strict adherence to m

practices as prescribed is required to ensure the ALI is complied with. Any use of methods, techniques or practices not containapproved by the FAA Oversight Office.

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

REGULATORY AGENCY APPROVALAny deviations from the published AWL instructions included in this document require approval from the FAA Oversight Office. 

under the U.S. FAA jurisdiction only and to airplanes registered in the U.S. Operators who are not under the U.S. FAA jurisdictfrom their own local regulatory 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 FAA Oversight 

then be forwarded to all 777 operators and the FAA Oversight Office.ACCOMPLISHMENT INSTRUCTIONS – GENERAL INFORMATIONThe listed AWLs may make reference to Instructions for Continued Airworthiness which are included in other Boeing document

• When a document is cited using the words "in accordance with" in an airworthiness limitation, the cited document (or docum

followed to ensure that the critical design feature is maintained. Any deviation from the cited document requires FAA Overs

• When a document is cited using the words "refer to" in an airworthiness limitation, the cited document (or document section

complying with the airworthiness limitation. An alternative procedure may be developed by an operator in accordance with 

maintenance program/manual.

For electrical bonding and grounding requirements, refer to the Boeing Standard Wiring Practices Manual (SWPM) 20-20.

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

USE OF ALTERNATE OR EQUIVALENT TOOLS, TEST EQUIPMENT OR MATERIALSFor AWLs which require use of certain tools, test equipment or material, the use of alternate or equivalent tools, test equipment approval from the FAA Oversight Office.The Component Maintenance Manuals (CMMs) listed in the AWLs as "in accordance with" and not "refer to" are currently FAA 

If the CMM allows the use of alternate or equivalent tools, test equipment or materials, use of an alternate or equivalent tool, tedoes not require further approval by the FAA Oversight Office.EXCEPTIONAL SHORT-TERM EXTENSIONSSince AWL intervals are based on estimations of the probability of an event, an exceptional short-term extension for each syste

document may be made without jeopardizing safety. The local regulatory authority or a Principal Maintenance Inspector must cshort-term extensions before they take place using procedures established with the local regulatory authority in the operators' m

short-term extension" process is applicable to AWL intervals. It should not be confused with the operators "short-term escalatio

maintenance tasks described in the operators' manuals and in the Flight Standards Handbook 8900.1 FSIMS.The FAA Oversight Office have accepted that these exceptional short-term extensions may be granted without consultation wit

1. The term "exceptional short-term extension" is defined as an increase in a system AWL interval that may be needed to cov

unexpected situation. All AWLs listed in this section have been approved with an exceptional short-term extension of 30 da

2. Repeated use of extensions, either on the same airplane or on similar airplanes in an operator's fleet, should not be used a

management practices. Exceptional short-term extensions must not be used for fleet AWL extensions.

3. After a system AWL has experienced an exceptional short-term extension, the AWL interval will revert back to its interval lis

FAA Oversight Office must approve, prior to its use, any desired extension not explicitly listed above.

NOTE: This exceptional short-term extension listed above applies to airlines that fall under the U.S. FAA jurisdiction only. Opera

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

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

DEFINITIONSRemoved or Replaced: Defined as removal or replacement of a component, as well as partial removals.Disturbed: Defined as interference, movement or change to the arrangement or order of the referenced component.New wiring: Defined as any alteration that installs wiring that is added to the airplane after initial Airplane Airworthiness Certificadate that the MPD Section 9, D622W001-9, was first incorporated into an operator's maintenance program, whichever is later.Sealant: Defined as sealant type BMS 5-45 or equivalent in accordance with SRM 51-20-05 for inside of fuel tank and sealant tequivalent, in accordance with SRM 51-20-05 for outside of the fuel tank.FAA Oversight Office: Defined as the FAA office that currently has oversight responsibility for the type certificate of the Boeing 

time of publication, the FAA Oversight Office is the FAA BASOO.SUPPORTING DOCUMENTATIONStrict adherence to methods, techniques and practices as prescribed is required to ensure the ALI or CDCCL is complied with. manufacturer's maintenance procedures when performing maintenance that has an effect on an ALI or CDCCL. If operators do can increase the risk of an unsafe condition. Any use of methods, techniques or practices not contained in these ALIs or CDCC

the FAA Oversight Office.PAGE FORMAT: SYSTEMS AIRWORTHINESS LIMITATIONS

COLUMN EXPLANATION

AWL NUMBER Each task is given a unique AWL Item Number. The first and second digits are the ATA Chapter Number.TASK ALI = Airworthiness Limitation Instruction. These tasks are inspections that should be performed at the listed inte

CDCCL = Critical Design Configuration Control Limitation

INTERVAL Task frequencies are specified in terms of a usage parameter such as flight hours, cycles or calendar time.

APPLICABILITY Airplane model applicability.DESCRIPTION Description of the task to be performed or critical design configurations aspects that cannot be changed without v

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

D.1 FUEL SYSTEMS IGNITION PREVENTION

This section contains an FAA-approved program of scheduled inspections and design limitations for operators to incorporate in

program for this type design to meet the standards and assumptions introduced by Title 14 CFR § 25.981 and Special Federal 

(SFAR 88). SFAR 88 – Fuel Tank System Fault Tolerance Evaluation Requirements and Title 14 CFR § 25.981 – Fuel Tank Ig

maintenance instructions and control limitations for certain fuel tank critical design configurations.

NOTE: The auxiliary fuel tank installation has been shown to comply with Title 14 CFR § 25.981 at Amendment 25-102.Paragraph 2(a) of SFAR 88 and Paragraph (b) of the standard introduced by Title 14 CFR § 25.981 (Amendment 25-102) requholders of Type Certificates (TCs) and Supplemental Type Certificates (STCs) of large transport airplanes to conduct a safety r

systems. The purpose of the safety review is to identify design features that may result in development of ignition sources in th

AWLs are mandatory maintenance actions required to ensure that unsafe conditions identified by the SFAR 88 safety review dintroduced into the fuel tank system as a result of configuration changes, repairs, alterations, or deficiencies in the maintenance 

operational life of the airplane.

FEB 2012
777 MAINTENANCE PLANNING DATA

D622W001-9

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

AWLs – FUEL TANK IGNITION PREVENTION

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 Upper Perform a detailed inspection of the wire bundles routed over the center fu

floor boards to detect damaged clamps, wire chafing, and that the wire bu

surface of the center fuel tank (refer to Boeing AMM 28-11-00).Inspect the sleeving (if installed) over the wire bundles for signs of visible damaged, remove the sleeving and inspect the wiring for chafing.Repair any discrepancies found (refer to Boeing Standard Wiring Practiceand 20-10-13) and ensure that the wires are not in contact with the surfacInterval 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 Upper If any maintenance is performed in the area under the main deck floor boatank, 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 detect and that the wire bundle is not in contact with the surface of the centefound, repair in accordance with the Boeing Standard Wiring PracticeSection 20-10.

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

28-AWL-03 ALI 16,000 FC/ 

3,000 DYS 

NOTE

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

Concern: Potential for lightning-induced voltages on the FQIS wiring to en

Using a Loop Resistance Tester, P/N 906-10246-2 or 906-10246-3, perfoensure the functional integrity of the FQIS wiring shield to ground termina05-55-54):1. Measure the joint resistance of the FQIS receptacle to structure (spa

0.003 ohm (3 milliohms) or less.

2. Measure and verify the resistance of the shield to ground termination 

a. The loop resistance is 0.040 ohm (40 milliohms) or less for Conn

Main Tank Rear Spar) Wire Bundle W8073.

b. The loop resistance is 0.054 ohm (54 milliohms) or less for Conn

Main Tank Rear Spar) Wire Bundle W8072.

c. The loop resistance is 0.040 ohm (40 milliohms) or less for Conn

Tank Front Spar) Wire Bundle W8010.

d. The loop resistance is 0.040 ohm (40 milliohms) or less for Conn

Tank Front Spar) Wire Bundle W8020.

e. The loop resistance is 0.053 ohm (53 milliohms) or less for Conn

Main Tank Rear Spar) Wire Bundle W8077.

f. The loop resistance is 0.040 ohm (40 milliohms) or less for Conn

Main Tank Rear Spar) Wire Bundle W8078.

3. Restore the bonds if the measured loop resistance value is greater th

(refer to Boeing AMM 05-55-54).

Interval Note: Whichever comes first.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 en1. If maintenance, preventative maintenance, or alteration is performed 

receptacle from the spar or opens an FQIS wire bundle shield to groucheck for the type of ground path opened as listed below (refer to Bo20-20-00): a. For the electrical joint between the plug's backshell and structure 

connectors D28102P, D28103P, D28202P and D28203P and the D28101P and D28201P, the following design feature must be maairplanes) (refer to Boeing AMM 28-41-05):I. For the FQIS spar receptacle:

A. A bonding jumper is installed between the FQIS spar rece

structure near the front spar with the red end of the jumpe

B. The mounting bolt for the bonding jumper is tightened to 

(3.8 - 4.5 N-m).

C. After installation of the bonding jumper, the electrical bon

FQIS spar receptacle and the spar is 0.003 ohm (3 millioh

II. For the out tank wire bundle plug to the FQIS spar receptacle

A. For the electrical joint between the out tank plug's backsh

bonding resistance is 0.003 ohm (3.0 milliohms) or less.

b. Based on the installation, only one of the following configurations 

AMM 05-55-54):I. Configuration 1 (airplanes with out of tank wire bundle with P 

A. For the electrical joint between the connector backshell an

well out of tank wire bundle end for Connectors D28113PD28213P, and at the forward cargo out of tank wire bundand D28111P, the following design feature must be main1). The resistance between the connector backshell and 

(2.5 milliohms) or less.

(Continued on next page)

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

28-AWL-04,

Continued

CDCCL N/A ALL FQIS – Out Tank Wiring Lightning Shield to Ground Termination, Continu

II. Configuration 2 (airplanes with out of tank wire bundle with J 

A. For the electrical joint between the connector backshell an

well out of tank wire bundle end for Connectors D28113JD28213J, and at the forward cargo out of tank wire bundlD28211P and D28111P, the following design features mu1). The resistance between the connector backshell and 

well is 0.002 ohm (2.0 milliohms) or less.

2). The resistance between the connector backshell and 

cargo is 0.0025 ohm (2.5 milliohms) or less.

2. If any FQIS out-tank wire bundle is replaced or the FQIS wire bundle

reconnected to the connector backshell (except as noted in Steps 1.A particular wire bundle shall be inspected as specified in AWL 28-AWL

28-AWL-05 CDCCL N/A 777 airplanes 

Line Numbers 498 

and on.

Airplanes that 

have incorporated 

Service Bulletin 

777-28-0044.

Lightning Protection – Engine Fuel Feed Line Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interface bthe spar during a lightning strike event.The following design features must be maintained if the bulkhead fitting or replaced (refer to Boeing AMM 28-22-15):1. The electrical fay surface bond between the bulkhead fitting and the f

0.001 ohm (1 milliohm) or less.

2. A full-bodied fillet seal encapsulates the bulkhead fitting to the tank w3. A full-bodied fillet seal encapsulates the coupling interface inside the 

4. An electrostatic bonding jumper exists between the structure and the 

bulkhead fitting inside the tank.

5. The electrical bonding resistance from the structure to the fuel tube m

0.010 ohm (10 milliohms) or less, if the bonding jumper was disturbed

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 rear spar, the hydraulic bulkhead fitting and the heat exchanger, or answaged sleeve during a lightning strike event.1. The following design features must be maintained if the hydraulic bul

replaced (refer to Boeing AMM 29-11-55):a. The electrical bonding resistance between the bulkhead fitting an

(1 milliohm) or less.

b. Full bodied cap seal is present at the fitting to the tank wall interf

fuel tank.

c. The electrical bonding resistance between the hydraulic tube in t

in the fuel tank must be 0.004 ohm (4 milliohms) or less.

2. The following design features must be maintained when the hydraulic 

replaced (refer to Boeing AMM 29-11-60):a. The electrical bonding resistance between the structure and the 

(2.5 milliohms) or less.

b. A bonding jumper must be installed from the hydraulic heat exch

the tank.

c. The electrical bonding resistance between the heat exchanger a

0.0025 ohm (2.5 milliohms) or less.

d. The electrical bonding resistance between the heat exchanger a

0.004 ohm (4 milliohms) or less.

3. The following design feature must be maintained when a non-heat ex

Wing Fuel Tank is removed or replaced (refer to Boeing AMM 20-10-a. The electrical bonding resistance across the in-line fittings (tube-

(4 milliohms) or less.

28-AWL-07 CDCCL N/A ALL AC and DC Pump Maintenance

Concern: Potential for maintenance error. Fuel pump designs contain ign(i.e., flame arrestor, thermal fuses, materials, leadwire retention means, eMaintenance of Fuel Pumps must be in accordance with Eaton (VK2523) C

28-20-44 Revision 6, CMM 28-20-45 Revision 3, CMM 28-20-47 Revision CMMs that have been approved by the FAA Oversight Office.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

28-AWL-08 CDCCL N/A All 777-200 

airplanes 

Line Numbers 523 

and on.

Airplanes that 

have incorporated 

Boeing 

Service Bulletin 

777-28-0045.

Center Wing Tank Sump Drain ValveConcern: Potential for arcing or sparking inside the tank at the interface bethe lower skin in the center wing tank during a lightning strike event.The following design features must be maintained if the drain valve is remBoeing AMM 28-11-06):1. The presence of an insulating washer at the sump drain valve inside 2. The presence of a fillet seal at the interface between the jam nut and 

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 minterface as a result of electrical fault currents or lightning strike events duthe ground electrical path.Any repair or alteration involving new or altered penetrations to the fuel tafasteners, adding a bracket, bulkhead fitting or equipment, etc.) or change existing equipment penetrations (such as fuel measuring sticks, sump drai

temperature sensor, and motor operated fuel shutoff valve adaptor plate) FAA Oversight Office.However, no additional FAA Oversight Office approval is required if the reaccomplished in accordance with:1. SRM procedures, and/or2. Boeing Service Bulletins, and/or3. Boeing ODA approved repair/alteration instructions;

where all the required repair/alteration instructions and other procedures tfuel tank penetration include the statement, "These data have been reviewtank ignition prevention requirements, and no further approval from the FAto satisfy the requirements of CDCCL 28-AWL-09 provided the repair or aaccordance with these instructions.Note: Electrical bonding of fittings and brackets and/or cap sealing of fast

component interface to structure inside and/or outside the fuel tank will be 

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 stru

faults internal to the fuel pump motor impeller are, by design, routed throuto the bonding jumper on the front face of the motor impeller assembly to 

bonding jumper ensures that fault currents are conducted to structure outbreaker and/or Ground Fault Interrupter (GFI) has had time to remove powThe following design features must be maintained during pump replaceme28-22-05, 28-22-06, and 28-31-01):1. The presence of one bonding jumper between the pump motor impel

2. The Motor Impeller bonding resistance across the bonding jumper to 

(0.25 milliohm) or less.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

28-AWL-11 CDCCL N/A ALL FQIS and Auxiliary Fuel Tank Electronic Fuel Level Indication (EFLI) Syst

Installation Separation RequirementConcern: Potential for hot shorts and Electromagnetic Effects (EME)-indu

or Auxiliary Fuel Tank EFLI wiring to enter the tank.New wiring is defined as any new alteration that installs wiring, Electrical W

(EWIS) that is added to the airplane after initial Airplane Airworthiness Ce

date 28-AWL-11 was first incorporated into an operator’s maintenance pro

Routing and installation of any new wiring within 6.5 inches of the FQIS wwiring must meet one of the following requirements:

1. Use wire types BMS 13-48, BMS 13-60 or BMS 13-58, and wire mus

the FQIS wiring or Auxiliary Fuel Tank EFLI wiring and also not be witwiring or Auxiliary Fuel Tank EFLI wiring under any single failure of a 

2. Meet the criteria for intrinsically safe wiring as defined by FAA Adviso

Sections 8 and 9. New wiring that does not meet the requirements foand is shown to be intrinsically safe, must be identified as part of the approved by the FAA.

3. The new wiring installation has been found by the FAA to be complia

Section 25.981(a)(3) at Amendment 25-102 or later.

Repair or replacement of existing wiring is not considered new wiring. Rep

wiring that is installed within 6.5 inches of FQIS wiring or Auxiliary Fuel Ta

existing wire routing.NOTE: Refer to the Boeing Wire Diagrams to identify FQIS wiring or Aux

wiring bundles.

The following are FAA-accepted practices for repair or replacement of exi1. For wire type substitutes, refer to Boeing SWPM 20-00-14.2. For wire assembly and installation, refer to Boeing SWPM 20-10-11.3. For repair procedures, refer to Boeing SWPM 20-10-13.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

28-AWL-12 CDCCL N/A ALL

NOTE

Center Wing Tank (CWT) Refuel Valve and Aux Tank Refuel Valve – FauConcern: Potential for arcing inside the CWT.For the CWT and Auxiliary Tank Refuel Valve (Solenoid Actuator located following design features must be maintained when the refueling valve is Boeing AMM 28-21-02 or 28-21-21):1. The Fay Surface bond between the valve body and the rear spar insi

(2.5 milliohms) or less.

2. A fillet seal is applied around the entire perimeter of the valve body aAPPLICABILITY NOTE: The Aux Tank Refuel Valve requirement of this C

 airplanes with the Aux Tank Refuel Valve install

28-AWL-13 CDCCL N/A ALL FQIS – Fuel Quantity Processor Unit (FQPU) Repair and Auxiliary Fuel T

Concern: Potential for maintenance error during FQPU or Auxiliary Fuel TAuxiliary Fuel Tank EFLI is designed to limit the levels of energy, voltage, within the FQIS / EFLI circuit to intrinsically safe levels in order to precludsource within any fuel tank.1. Maintenance of the FQPU must be in accordance with GE Aviation (V

69 Revision 1, and CMM Volume 2 (IPC) 28-47-69 Revision 2, CMM and CMM Volume 2 (IPC) 28-47-65 Revision 4, or later revisions of thapproved by the FAA Oversight Office.

2. Maintenance of the EFLI must be in accordance with Parker (V26055

later revisions that have been approved by the FAA Oversight Office.

28-AWL-14 CDCCL N/A ALL FQIS and Auxiliary Fuel Tank EFLI System – Repair of In-Tank Hardware 

Water Detector)Concern: Potential for maintenance error during repair of in-tank hardware water detectors). Arc gaps may develop that could result in an ignition soMaintenance of the FQIS tank units, densitometers and water detectors m

Aviation (VK5294) CMM 28-47-58 Revision 4, CMM 28-47-59 Revision 1, CMM 28-48-03 Revision 2, CMM 28-47-71 Revision 5, or later revisions o

approved by the FAA Oversight Office.Maintenance of the EFLI probe must be in accordance with Parker (V2605later revisions of this CMM that have been approved by the FAA Oversig

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

28-AWL-15 CDCCL N/A ALL FQIS – Repair or Replacement of In-Tank Wire Harness

Concern: Potential for error during repair or replacement of in-tank wire ha

that could result in an ignition source inside the fuel tank.1. Repair and overhaul of the FQIS in-tank wire harness must be in acc

14-12 when the repair is accomplished on the airplane, or in accorda

CMM 28-47-61 Revision 7, or later revisions of this CMM that have bOversight Office when the repair is accomplished in the shop.a. The following design features must be maintained during installa

in-tank wire harness (refer to Boeing AMM 28-41-05):I. Wires are not in contact with the structure.

2. The in-tank wire harnesses affected by repair or replacement must al

28-AWL-04, as applicable.

28-AWL-16 CDCCL N/A ALL Fuel Tank Access Doors – Lightning Protection

Concern: Potential for arcing or sparking inside the tank at the interface bstructure as a result of a direct strike or conducting currents through the w

The following design features must be maintained during installation of futhe lower wing skin (refer to Boeing AMMs 28-11-01, 28-11-02, 28-11-07, 

1. A phenolic strip is positioned around the outermost periphery of the do

inside the tank, except for the impact-resistant door positions listed ba. 777-200/200ER/300: Door Positions 531AB, 631AB, 531BB, 63

633AB, 533BB, 633BB, 533CB, 633CB, 533DB, 633DB, 533EB, 633GB, 541AB, 641AB.

b. 777-200LR/300ER/F: Door Positions 533FB, 633FB, 533GB, 63

2. No presence of corrosion on the access door, clamp ring, and lower w

surfaces.

(Continued on next page)

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

28-AWL-16,

Continued

Fuel Tank Access Doors – Lightning Protection, Continued3. A new knitted aluminum mesh gasket is installed. If a new gasket is 

meeting the following criteria may be installed:a. No fastener holes are torn.b. The gasket is not elongated or out of shape.c. The gasket rubber seals around the inner and outer periphery m

0.015 inches thick.

d. No more than 10% of strands in all three layers are broken throu

NOTE: A gasket not meeting Items a through c criteria may be 

30 days and then must be replaced with a gasket that m

4. Grease or anti-corrosion compound is applied to both sides of the knit

required for a new knitted aluminum mesh gasket that is less than fivNOTE: If the new knitted aluminum mesh gasket is greater than five 

date, de-grease and re-impregnate with 0.5-1 ounce of MILequivalent) grease (applicable to all doors except for machUse anti-corrosion compound BMS 3-38 (CorBan 27L Comimpact-resistant doors on 777-300ER/200LR/F.

5. A torque of 35 ±5 in-lb (4 ±1 N-m) is applied on the fasteners for all do

machined impact-resistant doors (531AB, 631AB, 531BB, 631BB, 53

533BB, 633BB, 533CB, 633CB, 533DB, 633DB, 533EB, 633EB). Fodoors installed on 777-300ER/200LR/F, a torque of 65 ±5 in-lb (7 ±1 

6. Surge Tank Access Door with Vent Scoop:

a. A bonding jumper exists between the upper duct and the door.b. The electrical bonding resistance between the door and skin pan

or less.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

28-AWL-17 CDCCL N/A ALL Resetting Tripped Fuel Pump Circuit Breakers or GFIs

Concern: Potential for arcing or sparking inside the tank between fuel pumoutside the tank between pump wiring and structure in flammable leakage Before resetting the circuit breaker(s) or GFIs, the following must be perfo1. Accomplish the troubleshooting procedures (refer to Boeing Fault Iso

28-22 and 28-31).

2. The fault(s) that resulted in circuit breaker or GFI tripping must be iso

to reset.

28-AWL-18 ALI 375 DYS ALL

NOTE

AC Fuel Pump GFI and Ground Fault Protector (GFP)Concern: Potential for pump housing burn-through, either internal or exteof major arcing due to electrical failure (i.e., damaged electrical connectorhousing/end cap shorting). The GFI/GFP is designed to detect electrical f

to pump housing burn-through. The following maintenance check is required in order to ensure continued 

circuit:Operationally check the GFI and/or GFP, if installed, of the Center Tank OAuxiliary Tank Pumps, Main Tank Jettison Pumps and Main Tank Boost Pu

28-22-00 or AMM 28-14-05.APPLICABILITY NOTE:a. Center Tank Override/Jettison Pumps and Main Tank Jettison Pumps o

423, 429, 454 and on.

b. Center Tank Override/Jettison Pumps and Main Tank Jettison Pumps o

Position 454, except 423 and 429 that have incorporated Service Bulle

c. All Main Tank Boost Pumps on airplanes with Line Position 662 and ond. All Main Tank Boost Pumps on airplanes prior to Line Position 662 tha Service Bulletin 777-28A0038.e. Auxiliary Tank Pumps on 777-200LRs only if equipped with Auxiliary F

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

28-AWL-19 CDCCL N/A Airplane 

Line Position 552 

and on.

Airplanes that 

have incorporated 

Service Bulletin

777-28A0034

Motor Operated Valve (MOV) Actuator – Lightning and Fault Current Prot

Concern: Potential for arcing or sparking inside the fuel tank at a conductinterface as a result of electrical fault.1. The following design features must be maintained when the MOV Ac

spar with an adapter plate are removed or replaced (refer to Boeing A14-21, 28-14-22, 28-14-24, 28-14-25, 28-14-43, 28-14-44, 28-21-23, 

28-22-03, 28-22-04, 28-26-01, 28-26-02, 28-31-02, 28-31-03, 28-31-0a. An electrical fay sealed bond exists between the adapter plate a

cell wall structure) (only required if adapter plate is removed or re

b. An electrical fay sealed bond exists between the index plate and 

if the index plate is removed or replaced).

c. An electrical fay sealed bond exists between the actuator mounti

required if actuator is removed or replaced).

d. With one or both ends of the bonding jumper disconnected, the e

between the actuator mounting feet and the structure is 0.0025 o

e. Prior to attachment of the bonding jumper to the actuator, the ele

between the loose end of the bonding jumper and the spar (auxiis 0.0015 ohm (1.5 milliohms) or less.

f. A bonding jumper exists between the actuator and the structure.

2. The following design features must be maintained if the MOV Actuato

without an adapter plate are removed or replaced (refer to Boeing AMAPU Valves and 28-31-03 for Jettison Nozzle Valve:a. APU Valves (Shut-Off and Isolation)

I. An electrical fay surface seal bond exists between the actuat

mounting bolts.

II. With the bonding jumper not installed, the electrical bonding 

mounting feet and the spar is 0.005 ohm (5 milliohms) or less

III. Prior to attachment of the bonding jumper to the actuator, the 

between the loose end of the bonding jumper and the spar is or less.

IV. An electrical fay surface seal bond exists between the bondin

bonding tab.

(Continued on next page)

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

28-AWL-19,

Continued

Motor Operated Valve (MOV) Actuator – Lightning and Fault Current Prot

b. Jettison Nozzle Valve (Applicable to the 777-200/200ER/300)

I. An electrical fay surface seal bond exists between the actuat

valve body.

II. With the bonding jumper not installed, the electrical bonding 

mounting feet and the structure is 0.005 ohm (5 milliohms) o

III. Prior to attachment of the bonding jumper to the actuator, the 

between the loose end of the bonding jumper and the structuor less.

IV. An electrical fay surface seal bond exists between the bondin

bonding tab.NOTE: Not applicable to the Air Transfer Valve/Actuator; th

Auxiliary Tank.

28-AWL-20 CDCCL N/A ALL

NOTE

MOV Actuator – Output Shaft Electrical IsolatorConcern: Potential for arcing or sparking inside the fuel tank at a conductinterface as a result of lightning or electrical fault current event. An electr

output shaft is intended to disconnect the output shaft electrically from the and ground path structure.To verify the integrity of the electrical isolation feature, conduct the followiremoved for bench testing or repair (refer to ITT (V73760) CMM 28-20-21A Dielectric Strength Test on the completed actuator assembly shall be peRMS, 60 Hz for one (1) minute between any mounting foot of the actuator 

There shall be no evidence of disruptive discharge in the form of leakage amps. The 3000V test is a bench test only and must not be performed on APPLICABILITY NOTE: Applies only to ITT actuators with Part Number M

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

28-AWL-21 ALI 4500 DYS 777-200LR with 

Auxiliary Fuel 

Tank

External Wires Over Auxiliary Fuel TankConcern: Potential for arcing or wire chafing to Auxiliary Fuel Tank.Perform a detailed inspection of the wire bundles routed over the Auxiliary deck floor boards to detect damaged clamps, chafing wires, and that the w

the surface of the Auxiliary Fuel Tank (refer to Boeing AMM 28-11-00).Inspect the sleeving (if installed) over the wire bundles for signs of visible 

damaged, remove the sleeving and inspect the wiring for chafing.Repair any discrepancies found (refer to Boeing SWPM 20-10-11 and 20-are not in contact with the surface of the Auxiliary Fuel Tank.

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 boa

verify the following:1. Maintain the existing wire bundle routing and clamping.2. Perform a detailed inspection of the wire bundles routed over the aux

main deck floor boards in the areas of the performed maintenance to d

wires, and a wire bundle that is in contact with structure. If discrepancaccordance with Boeing Standard Wiring Practices Manual (SWPM), 

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

28-AWL-23 CDCCL N/A 777-200LR with 

Auxiliary Fuel 

Tank

Auxiliary Tank AC Fuel Pump Fault Current Bonding PathConcern: Potential for fault current path through the motor impeller assem

tank. Electrical faults internal to the fuel pump motor impeller are, by des

impeller assembly to the bonding jumpers on the front face of the motor imstructure. The bonding jumpers ensure that fault currents are conducted t

the circuit breaker and/or GFI has had time to remove power from the pumThe following design features must be maintained during pump replaceme15 or Marshall Aerospace (VK3784) CMM 28-14-02 (off-airplane)):1. The installation of a bonding jumper between the pump motor impelle2. The following bonding resistance is maintained:

a. The electrical bonding resistance between the fuel pump motor-i

housing assembly (MW2-05-1046/1, commonly referred to as the (0.6 milliohm) or less.

b. The electrical bonding resistance between the fuel pump housing 

assembly (MW2-05-1046/1) is 0.0025 ohm (2.5 milliohms) or les

3. Maintenance of the fuel pump must be as specified in 28-AWL-07.

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 o

If any maintenance is performed on or around the auxiliary tanks, the follocomponents must be maintained:1. Cargo Liners which separate the cargo compartment from the auxilia2. A 9G Thermal Impact Barrier is installed on the auxiliary fuel tank bar3. The Thermal Insulation Blanket located between the end wall cargo l

barrier is installed.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 minterface as a result of lightning strike events to aux tank drains.If any maintenance is performed on or around the auxiliary tank drain sysbe maintained:1. Aeroquip Low Pressure Teflon Lightning Safe Hoses are installed on t2. Flame Arrestors are installed in fuel tank drains.

3. Foil backed fairing panels and associated bonding located below dra

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 Shutof

Concern: Potential for failure of fuel pump power control circuit in the enerunning of fuel pump with a potential ignition threat due to pump overheat 

The Pump Uncommanded ON/Automatic Shutoff Circuit provides redundafrom the Auxiliary Tank Pump if pump pressure is low for >15 seconds.The following maintenance check is required in order to ensure continued 

1. Operationally check the Pump Uncommanded ON/Automatic Shutoff C

AMM 28-14-05.

28-AWL-27 CDCCL N/A 777-200LR with 

Auxiliary Fuel 

Tank

Auxiliary Fuel Tank Replacement or InstallationConcern: Potential for fault current to the inside of the Auxiliary Fuel Tank

jumpers which provide a path from the tank to airplane structure. The boncurrents are conducted to structure outside the tank.The following design features must be maintained during tank replacemen

Fuel Tank (refer to Boeing AMM 28-14-01):1. The installation of a bonding jumper between the Auxiliary Tank and 2. The following bonding resistances are maintained:

a. On the right side of the cell, the electrical bonding resistance bet

stanchion is 0.006 ohm (6 milliohms) or less.

b. The electrical fay surface bond resistance between the stanchion

(6 milliohms) or less.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

D.2 ENGINE SUCTION FEED SYSTEM

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

to meet Title 14 CFR § 25.951.The 777 Engine Fuel Feed System was type certificated as being compliant to Title 14 CFR § 25.951(b) when performing suctiEngine Suction Feed System AWL results from service experience of loss of fuel system suction feed capability due to air leaks system. The AWL is required maintenance needed to detect and correct failure of the engine fuel feed system to reduce the po

resulting from air ingestion into the engine fuel feed system during low fuel level operation with boost pumps inoperative.

The Engine Suction Feed System AWL is mandatory maintenance to ensure that the system retains the performance of the En

by Title 14 CFR § 25.951(b) that arise due to air leaks in the engine fuel feed system do not result in flameout of both engines.

FEB 2012
D622W001-9

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

777 MAINTENANCE PLANNING DATA

AWLs – ENGINE SUCTION FEED SYSTEM

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

28-AWL-101 ALI 7,500 FH ALL Engine Fuel Suction Feed Operational Test

An Engine Fuel Suction Feed Operational Test must be accomplished sucindividually. This test is required in order to protect against engine flameouand must meet the following requirements (refer to Boeing AMM 28-22-00Fuel Tank Quantity Limitations:Engine No. 1a. The Center Tank Fuel Quantity must not exceed 5,000 lbs (2,270 kg)b. The Main Tank No. 1 Fuel Quantity must be between 1,400 lbs – 1,60NOTE: Excess fuel can be transferred to Main Tank No. 2.Engine No. 2a. The Center Tank Fuel Quantity must not exceed 5,000 lbs (2,270 kg)b. The Main Tank No. 2 Fuel Quantity must be between 1,400 lbs – 1,60NOTE: Excess fuel can be transferred to Main Tank No. 1.Test Procedural Limitations:1. The Fuel Cross-Feed Valve must be CLOSED.2. The APU Selector Switch must be OFF.3. Idle Engine Warm-up time of minimum two minutes with Boost Pump 4. Idle Engine Suction Feed (Boost Pump OFF) operation for a minimum NOTE: APU may be used to start the engines provided the Fuel Tank Q

Limitations are met.

The test is considered a success if engine operation is maintained during 

engine parameters (N1, N2, and Fuel Flow) do not decay relative to those A suction feed system that fails the operational test must be repaired or ma

the Engine Suction Feed Operational Test prior to further flight.

FEB 2012
D622W001-9

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

777 MAINTENANCE PLANNING DATA

D.3 NITROGEN GENERATION SYSTEM (NGS)

The following list of AWLs (ALIs and CDCCLs) contain FAA approved scheduled inspections and design limitations for operato

maintenance program for this type design to meet the requirements for the introduction of the Flammability Reduction Means (F

System (NGS). The FAA operational rule change E8-16084 Final Flammability Rule requires maintenance instructions and con

NGS critical design configurations. Title 14 CFR § 25.981 also requires CDCCLs to preclude ignition sources inside the fuel tan

the addition of NGS.Final Flammability Rule, Paragraph III(F), Section 7, Paragraph M25.4(a) requires that if FRM is used to comply with Paragraph 

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 fa

not introduced into the airplane as a result of configuration changes, repairs, alterations, or deficiencies in the NGS Maintenanc

operational life of the airplane.

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

AWLs – 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 bflame arrestor and the spar during a lightning strike event. The following bulkhead fitting or attached tubing is removed and replaced or reinstalled 

1. Install the same part number bulkhead fitting.2. Verify electrical fay surface bond between the bulkhead fitting and th

tank is 0.0005 ohm (0.5 milliohm) or less.

3. Install full-bodied fillet seal between the front spar structure and bulkh

the tank.

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

fitting between the flareless fitting nut and tube and between the flarefitting.

5. Verify electrical bond from structure to first tube mating with the bulkh

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

requires approval by the FAA Oversight Office.

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 dielectric isolator hose and the NEA tubing during a lightning strike event.The NGS installation is designed to prevent lightning currents from enteriadding a dielectric isolator hose in the forward leading edge fairing area Nmust be maintained if the dielectric isolator hose or attached tubing is rem(refer to Boeing AMM 47-21-00).

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

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 PerformConcern: Airplane alterations may impact the performance of the NGS anCenter Wing Fuel Tank.Background: The NGS is designed to provide the proper level of nitrogen to reduce the flammability exposure by reducing the oxygen content of th

exposure is also affected by the temperature of the fuel. The following ar

that, if altered, can negatively affect the performance of the NGS which in 

fuel tank flammability exposure beyond the limits of Title 14 CFR, Section 

utilizing the equivalent level of safety finding described in FAA Memorand1. Transferring air (20.9% oxygen) to the center fuel tank will dilute the n

by the NGS in the fuel tank. Some Auxiliary Fuel Tank installations traas 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 or changes that would cause heat to be retained (such installation of could affect fuel tank flammability in a negative manner.

CDCCL: Any design change that affects the vent system by adding air to bleed pressure in the cross-over manifold during any phase of flight or groheat to the center wing fuel tank or increases heat retention of the center without an FAA approved analysis to show that the change, or combinatio

NGS performance as required by Title 14 CFR Section 25.981(b), Amendequivalent level of safety finding described in FAA Memorandum PS05-0See Boeing AMM Chapter 28 for a description of the Fuel System. See Bdescription of the NGS.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 OperationaConcern: Latent Failure of the Thermal Switch removes a layer of protecthot bleed air.The NGS uses engine bleed air from the engine bleed system cross-over 

reduce the flammability of the center fuel tank. The NGS has features to pair into the fuel tank. The Thermal Switch provides a redundant backup to the Air Separation Module (ASM) and prevent hot bleed air from entering 

Switch backup feature is a latent (not detected) failure and must be tested the NGS.Perform a functional and operational check of the Thermal Switch to ensur(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 Ch

Concern: The Cross-Vent Check Valve may fail open latently allowing air 

diluting the nitrogen rich environment created by the Nitrogen Generation Operationally check the Cross-Vent Check Valve by accessing left wing s

checking the operation of the Cross-Vent Check Valve (refer to Boeing Avalve 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 InspectionConcern: The NEA Distribution System ducting outside the fuel tank may without reaching the fuel tank, resulting in the fuel tank not reaching requInspect the NEA distribution lines from the ASM to the fuel tank front spar Boeing AMM ATA 47-21-00).

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
D622W001-9

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

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. Indtime may result in NGS performance that does not meet FAA requiremen

Fleet Average flammability exposure for the fuel tanks with flammability remust be maintained in accordance with Title 14 CFR Part 25, Appendix Mdescent statistics and, if necessary to maintain compliance, will publish se

publishes such service information, this CDCCL requires either that operaapproved design changes or that operators implement other design chanchanges approved by the FAA Oversight Office to maintain compliance wAppendix M.NOTE: This CDCCL does not require individual operators to monitor des

will monitor US descent statistics and provide any needed servicprevent increasing flammability exposure above permissible leveoperators to incorporate future Boeing published service instructcompliance with this CDCCL, or other approved actions, within tservice instructions.

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

D.4 PRATT AND WHITNEY FORWARD STRUT DRAIN LINE

This section contains an FAA approved program of Forward Strut Drain Line Scheduled inspections. Operators should incorpo

their maintenance programs to meet Title 14 CFR § 25.901(b)(2) for those strut drains that are identified as applicable. In revenue service, excessive temperatures combined with draining fluids have contributed to clogging of the forward strut drain 

pooled in the strut flammable leakage zone, the left systems electrical bay, in the strut forward dry bay, and forward engine momount is susceptible to hydrogen embrittlement when exposed to hydraulic fluid. The addition of drain line insulation (see Serv

reduces the temperatures experienced by the drain lines minimizing the clogging of the drain such that periodic inspection will pflammable fluids between inspections. The Forward Strut Drain Line functional check AWL is mandatory maintenance to ensure safe operation of the strut drainage sy

Title 14 CFR § 25.901(b)(2). The Forward Strut Drain Line functional check verifies the drain will be functional until the next sc

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

AWLs – DRAIN LINE

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

54-AWL-01 ALI 2,000 FC/

1,500 DY

NOTE

777 Airplanes 

Line Number 

1118 and on 

with PW4000 

engines

777 Airplanes 

Line Numbers

1 through 1117 

with PW4000 

engines 

that have 

incorporated 

Service Bulletin 

777-71-0055

Forward Strut Drain LineConcern: Potential for hydraulic fluid clogging the Forward Strut drain line 

the Left Systems Disconnect, Strut Forward Lower Spar Inlet and Forward result in pooled flammable fluid in a flammable leakage zone which poses Hydraulic Fluid can also back up into the strut forward dry bay and cause forward engine mount fittings that could cause cracks that lead to the loss forward engine mount.Perform a Forward Strut Drain Line Functional Check (refer to Boeing AMhas sufficient flow.1. Apply 381oz (11.27 l) to 387 oz (11.44 l) of water into the strut discon

period.

2. Verify a minimum of 354 oz (10.47 l) is collected within two minutes a3. If the flow requirement is not met, then additional checks are required 

a. Verify that the three drain lines that connect to the Forward Strut 

blockage from the drain outlet to the following inlets: Left SystemLower Spar Inlet and Forward Fire Seal Pan Inlet.

b. Verify that there is no evidence of hydraulic fluid contamination i

NOTE: Access is through 432AR or 442AR. The Boeing Service accepted practices for inspection, cleaning and refinishing of the 

Interval Note: Whichever comes first.

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

D.5 ROLLS ROYCE THRUST REVERSER THERMAL PROTECTION SYSTEM

This section contains an FAA approved program of Thrust Reverser (T/R) scheduled inspections. Operators should incorporat

their maintenance program to meet Title 14 CFR § 25.901(b)(2) for those T/R configurations that are identified as applicable.

In revenue service, excessive temperatures have contributed to the failures of the 777 Rolls Royce T/R inner wall. The T/R Th

(TPS) limits the temperatures experienced by the inner wall minimizing new/additional thermal distress. The replacement of thother design improvements (see SB 777-78-0082) eliminates the potential for additional thermal distress. The Rolls Royce Thrust Reverser Inner Wall AWL is mandatory maintenance to ensure safe operation of the T/R installation as § 25.901(b)(2). The T/R TPS inspection verifies the proper functionality of the TPS. The Color Chip inspection demonstrates t

exposed to excessive temperatures by checking for any discoloration of the engine side inner wall primer. 

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

AWLs – THRUST REVERSER TPS

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

78-AWL-01 ALI 1125 DYS/

6000 FC

NOTE

777 Airplanes

Line Number 

922 and on with 

Trent 800 

engines.

777 Airplanes

Line Numbers

1 through 921 

with Trent 800 

engines that 

have 

incorporated 

SB 777-78-0071 

or 

SB 777-78-0082

Thrust Reverser Thermal Protection SystemConcern: Potential for latent failure of the thrust reverser inner wall thermresult in thermal exposure which reduces the strength of the inner wall painsulation protects against thermal damage.Inspect (Detailed) the Thrust Reverser Thermal Protection System on botto Boeing AMM 78-31-07).Prior to Insulation Blanket Removal:1. The 4 upper and 4 lower cooling holes/bushings are blockage free (fa2. The insulation blankets are undamaged, securely attached, and clickAfter Insulation Blanket Removal: 3. The insulation blanket perimeter sealing foam is firmly attached and 4. For drag link fittings that have cooling tubes attached:

a. Air exit holes are blockage free.b. A fillet seal exists between the cooling tubes and the drag link fitc. For the left thrust reverser, a fillet seal exists around the base of d. For the right thrust reverser, a fillet seal exists between the land 

flanges of the drag link fittings. 

5. The clickbond studs are present and firmly attached.Interval Note: Whichever comes first.

MAY 2013
777 MAINTENANCE PLANNING DATA

D622W001-9

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

78-AWL-02 ALI 1125 DYS/ 

6000 FC

NOTE

777 Airplanes 

with Trent 800 

engines. 

NOTE

Thrust Reverser Inner Wall Concern: Thermal protective system failures can result in the inner wall p

exposed to high temperatures which can reduce the strength of the inner thermally induced damage such as disbonds and delaminations on the in

inner walls can collapse in flight.Inspect (Detailed) the thrust reverser inner wall (refer to Boeing AMM 78-

P/N 315W5110-7, to ensure the inner wall has not been exposed to tempestrength.1. Verify that the thrust reverser inner wall primer color is not darker tha

315W5110-5) from the Color Chip Kit, P/N 315W5110-7.

2. If the thrust reverser inner wall primer color appears darker than the 

non-destructive test (refer to Boeing AMM 78-31-01) to ensure the cono disbonds or delaminations. 

INTERVAL NOTE: Whichever comes first. Interval to be applied to each 

independently.APPLICABILITY NOTE:1. For individual thrust reverser halves that have incorporated Service 

Package 1 or Work Package 2, or 

2. For individual thrust reverser halves that have incorporated Service B

Package 3 or Work Package 4, or

3. For individual thrust reverser halves with thrust reverser, PN 315W52

AWL

NUMBER TASK INTERVAL APPLICABILITY DESCRIPTION

MAY 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

E. 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 integr

tasks and intervals, a Certification Maintenance Coordination Committee (CMCC) was convened to review all of the 777 CMRsdocument 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 opecertificate. CMRs usually result from a formal, numerical analysis conducted to show compliance with catastrophic and hazardAdditional 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 f

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 a

the Maintenance Steering Group (MSG-3) Analysis associated with Maintenance Review Board (MRB) activities. MSG-3 A

maintenance tasks that are performed for safety, operational, or economic reasons, involving both preventative maintenance before failure occurs (and are intended to prevent failures), as well as failure-finding tasks. CMRs, on the other hand, are faexist solely to limit the exposure to otherwise hidden failures. Although CMR tasks are failure-finding tasks, use of potentia

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 maintenan

the failure clock to zero” for latent failures by verifying that the item has not failed, or cause repair if it has failed. Because t

failure is a key element in the calculations used in a safety analysis performed to show compliance with Title 14 CFR § 25.

time will have a significant effect on the resultant overall failure probability of the system. The CMR Task Interval should be 

hours, cycles, or calendar time, as appropriate.

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

4. The type certification process assumes that the airplane will be maintained in a condition of airworthiness at least equal to its 

condition. The process described in AC 25-19 is not intended to establish normal maintenance tasks that should be define

Analysis process. Also, this process is not intended to establish CMRs for the purpose of providing supplemental margins olate in the type design approval process.

5. CMRs should not be confused with required structural inspection programs that are developed by the type certificate applic

requirements for damage tolerance, as required by Title 14 CFR § 25.571 or § 25.1529, Appendix H25.4 (Airworthiness Lim

to be 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 without 

Oversight Office.

2. Two Star CMRs (**) – Task intervals may be adjusted in accordance with each operator’s approved escalation program or a

program in a like manner for any MRB Report task, but may not be deleted without prior FAA Oversight Office 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 f

without prior FAA Oversight Office approval. For operators with approved escalation practices or an approved reliability progra

analytical techniques are used to make adjustments to an operator’s maintenance program. It has been demonstrated that the maintenance program does not give rise to undue escalations; consequently, the escalation of Two Star CMR (**) intervals withmaintenance program will be properly managed by the operator subject to local regulatory authority approval.

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

EXCEPTIONAL SHORT-TERM EXTENSIONSSince CMR intervals are based on statistical averages and reliability rates, an exceptional short-term extension of 10% for each document may be made, except as noted in Item 1, without jeopardizing safety. The local regulatory authority or a Principle Maconcur with any exceptional short-term extensions before they take place using procedures established with the local regulatormanuals. The “exceptional short-term extension” process is applicable to CMR intervals. It should not be confused with the opescalation” program for normal maintenance tasks described in the operators’ manuals and in the Flight Standards Handbook 8

The FAA Oversight Office has accepted that these exceptional short-term extensions may be granted without consultation with 1. The term “exceptional short-term extension” is defined as an increase in a CMR interval that may be needed to cover an un

situation. All CMRs listed in this section have been approved for an exceptional short-term extension of 10%, except as no• 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 a

management practices. Exceptional short-term extensions must not be used for fleet CMR extensions.

3. After a CMR has experienced an exceptional short-term extension, the CMR interval will revert back to its interval listed in t

Oversight Office must approve, prior to its use, any desired extension not explicitly listed above.

NOTE: This exceptional short-term extension listed above applies to airlines that fall under the U.S. FAA jurisdiction only. Op

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

MAR 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

POST-CERTIFICATION CHANGES TO CMRsAny post-certification changes to CMRs should be reviewed by the 777 CMCC and approved by the FAA Oversight Office:

1. Since the purpose of a CMR is to limit the exposure time to a given significant latent failure as part of an engineering analysis 

instances of a CMR task repeatedly finding that no failure has occurred may not be sufficient justification for deleting the tabetween repetitive performances of the CMR task. In general, * CMRs are not good candidates for escalation under an op

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 reliability 

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 in

important that operators be afforded the same opportunity to participate that they received during the original certification o

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 change 

FAA Oversight Office 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 implemented 

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 change

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 CMR 

In the event that a CMR is revised, Boeing will document it by preparing a revision to this document that will be approved by the 

This revision will then be forwarded to all 777 operators and the FAA Oversight Office.

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

FIGURE 6. PAGE FORMAT CERTIFICATION MAINTENANCE REQUIREMENTS

MAR 2006
777 MAINTENANCE PLANNING DATA

D622W001-9

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

PAGE FORMAT – 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 with

approval.* Cannot be escalated or deleted without prior FAA Oversight Office approval.** Can be escalated based on the operator’s approved program for continued airworthiness based on continuous a however, these tasks cannot be deleted without prior FAA Oversight Office 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 a MRB Item Number.

TASK MSG-3 TASK CATEGORIES

OP = OPERATIONAL CHECK A failure finding task to determine if an item is fulfilling it

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, PW40GE90 = GE90 (75B/76B/85B/90B/94B/110B/115B)

TRENT = TRENT 800 (875-17, 877-17, 884-17, 890-17

TASK DESCRIPTION

Description of the task to be performed.

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

F. CERTIFICATION MAINTENANCE REQUIREMENTS TASKS

CMR

ITEM

NUMBER

T

YPE

RELATED 

MRB 

ITEM 

NUMBER

T

A

S

K

CMR 

INTERVAL

APPLICABILITY

777

CERTIFICATION MAINTENANCE R

APL ENG TASK DESCRIPTIO

21-CMR-01 ** 21-33 OP 7500 Hrs 777F ALL Operationally check the manual and automatic activatio

System.

25-CMR-01 * 25-056 OP 375 DY ALL

NOTE

ALL Perform an operational check of the Inflatable Seat Re

AIRPLANE NOTE: If installed. Applicable to AMSAFE installations, EMA P/N 511959-XXX-XX.

26-CMR-01 * --- IN 6000 Hrs or

18 Mos, 

whichever 

occurs first

ALL

NOTE

ALL Inspect Cargo Fire Bottles, supplier Part Numbers 4734

473876-2, for leaks using a Halide Leak Detector. Appto burst disc (inside fill fitting).AIRPLANE NOTE: Applicable to airplanes with -2 bottapplicable to -3 bottles).

27-CMR-01 * 27-140 OP 500 Hrs ALL ALL Operationally check PRIMARY FLIGHT CONTROL AC

actuation confidence tests.

27-CMR-02 * 27-160 OP 250 Hrs ALL ALL Operationally check ACTUATOR CONTROL ELECTRO

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 SY27-CMR-05 * IN 5000 FC 777F ALL Conduct a visual inspection of the 24 Horizontal Stabili

lined bushings and pins common to the Jackscrew Upp48 and Section 82 Fittings. Inspect for Karon liner or pdelamination

27-CMR-06 * 12-002 LUB 5000 Hrs or 

500 Dys 

whichever 

comes first

777F ALL Lubricate the Elevator Power Control Units (PCUs) and 

27-CMR-07 * 12-004 LUB 5000 Hrs or 

500 Dys 

whichever 

comes first

777F ALL Lubricate the Rudder and Rudder Tab Hinge Bearings, 

(PCUs) Reaction Link Rod Ends and PCU Rod Ends.

OCT 2014
777 MAINTENANCE PLANNING DATA

D622W001-9

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

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 Freep

28-CMR-01 * --- IN 6000 Hrs 300 ALL Conduct a visual inspection of the center fuel tank FQIS 29-CMR-01 * 29-030 FC 12000 Hrs ALL ALL Functionally check the GROSS INTERNAL LEAKAGE 

System.

29-CMR-02 * 29-130 OP 12000 Hrs ALL ALL Operationally check CENTER HYDRAULIC ISOLATIO29-CMR-03 * 29-150 OP 6000 Hrs ALL ALL Operationally check RAT System (using RAT checkout 

and Manual Deployment Systems. 

31-CMR-01 * 31-100 OP 24 Hrs

NOTE

ALL ALL Operationally check FIRE WARNING SYSTEM using t

(if not checked by crew).INTERVAL NOTE: Under exceptional operational circu

extended beyond 24 hours (elapsed clock hours) but n

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 bea

AIRPLANE NOTE: Applicable to airplanes production airplanes that have incorporated Service Bulletin 777-3

52-CMR-01 * --- DS 3375 Dys NOTE ALL Discard the Flight Deck Door Strike Assembly.

AIRPLANE NOTE: Applicable to airplanes production incorporation 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 R

APL ENG TASK DESCRIPTIO

JAN 2011
D622W001-9

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

777 MAINTENANCE PLANNING DATA

72-CMR-01

DELETED

*

--- IN 24 Hrs

NOTE

NOTE TRENT

NOTE

Inspect (Detailed) STEP-ASIDE-GEARBOX (SAGB) HGEARBOX LOWER BEVEL BOX (LBB) HOUSING for cracking per RR Non-Modification Service Bulletin 72-CINTERVAL NOTE: Under exceptional operational circuextended beyond 24 hours (clock time) but not to exceAIRPLANE NOTE: Applicable to all Increased Gross Wany 777-200 with Rolls-Royce Trent engines capable oENGINE NOTE: Applicable to all Rolls-Royce Trent enthrust rating and to all Trent engines installed on Increa

72-CMR-02

DELETED

*

--- IN 10 Cyc NOTE TRENT

NOTE

Inspect (Special Detailed) STEP-ASIDE-GEARBOX (SApenetrant for evidence of cracking per RR Non-ModificIssue 3. AD 97-06-13.AIRPLANE NOTE: Applicable to all Increased Gross Wany 777-200 with Rolls-Royce Trent engines capable oENGINE NOTE: Applicable to all Rolls-Royce Trent enthrust rating and to all Trent engines installed on Increa

72-CMR-03 * --- IN 1000 Cyc

NOTE

300 TRENT Inspect (Special Detailed) MAIN FAN BLADES with ult

blade root cracking per Rolls-Royce Non-Modification SINTERVAL 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 l

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 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 Se

CMR

ITEM

NUMBER

T

YPE

RELATED 

MRB 

ITEM 

NUMBER

T

A

S

K

CMR 

INTERVAL

APPLICABILITY

777

CERTIFICATION MAINTENANCE R

APL ENG TASK DESCRIPTIO

JAN 2011
777 MAINTENANCE PLANNING DATA

D622W001-9

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

G. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS

Title 14 CFR § 121.703 and § 135.415 state that “each certificate holder shall report any failure, malfunction, or defect in an air

or powerplant that occurs or is detected at any time if, in its opinion, that failure, malfunction, or defect has endangered or may 

operation of an aircraft”. Title 14 CFR § 125.409 also requires reporting of failures, malfunctions, or defects. In many cases a remalfunction will be obvious, but there are some failure modes related to uncontrolled high thrust that are reportable but may noinformation is provided, as required by FAA Exemption No. 7955, to assist the operators in identifying reportable malfunctions r

thrust.The FAA has concluded that the loss of capability to control thrust due to a failure of the engine thrust control system may endaincludes 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 p

maintained and/or to identify failure conditions that must be corrected.

MAR 2014
D622W001-9

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

777 MAINTENANCE PLANNING DATA

When filing a report of such an event with the FAA, the operator is requested to include in the description of the event one or m

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 respon

§ 121.703, 125.409, and 135.415. In addition to filing reports with the FAA, it is recommended that a copy be sent to Boeing an

manufacturer.

MAR 2014