747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-1747-400MAINTENANCE PLANNING DATA (MPD) DOCUMENTSECTION 9AIRWORTHINESS LIMITATIONS (AWLs) ANDCERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)D621U400-9JUNE 2014COMPILED AND PUBLISHED BY:MAINTENANCE PROGRAMS ENGINEERINGCOMMERCIAL AVIATION SERVICESBOEING COMMERCIAL AIRPLANE GROUPSEATTLE, WASHINGTONJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-2747-400 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3TABLE OF CONTENTSREVISIONS .................................................................................................................................................................................................................................. 9.0-5LIST OF EFFECTIVE PAGES .................................................................................................................................................................................................... 9.0-20A. SCOPE................................................................................................................................................................................................................................... 9.0-21B. AIRWORTHINESS LIMITATIONS (AWLS) – SYSTEMS........................................................................................................................................................ 9.0-22B.1 FUEL SYSTEM IGNITION PREVENTION ....................................................................................................................................................................... 9.0-27B.2 IMPACT-RESISTANT FUEL TANK ACCESS DOORS..................................................................................................................................................... 9.0-48B.3 NITROGEN GENERATION SYSTEM(NGS)................................................................................................................................................................... 9.0-49C. AWLS – STRUCTURAL INSPECTIONS................................................................................................................................................................................ 9.0-55C.1 LIMIT OF VALIDITY (LOV)............................................................................................................................................................................................... 9.0-56D. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs).............................................................................................................................................. 9.0-57E. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONS ...................................................................................................................... 9.0-65JUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4747-400 MAINTENANCE PLANNING DATATHIS PAGE INTENTIONALLY LEFT BLANKBLANK747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5REVISIONSREVISION AND REVISIONDESCRIPTION FAA APPROVALRevision 0 - January 1989Original IssueApproved by: D. L. Riggin(Seattle FAA ACO)Revision 1 - February 1989Removed requirements to check for Operative bus between EEC and EIU one flight prior to 150 hour check andchanged FADEC C2check from 150 hours to 500 flight hours.Approved by: D. L. Riggin(Seattle FAA ACO)Revision 2 - June 1989Added requirements to accomplish a 1000 hour operational test which checks that air conditioning pack 3 highflow mode is disabled with lower lobe cargo compartment conditioned air on.Added requirements to interrogate the CMC for engine position 2 turbine overspeed failure message every150 hours on RB211-524G or RB211-524G2.Revised requirements to check engine control system for Category 2 faults to 250 flight hours on RB211-524Gor RB211-524G2.Approved by: D. L. Riggin(Seattle FAA ACO)Revision 3 - June 1989Added requirement to Drain PW4000 Gearbox whenever cumulative oil addition totals 12 quarts.Approved by: D. L. Riggin(Seattle FAA ACO)JUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6747-400 MAINTENANCE PLANNING DATARevision 4 - June 1989Deleted CMR 22-Issue covered in FAA approved PW4000 Maintenance Manual via P&W Alert Service BulletinPW4 ENG A79-39.Approved by: D. L. Riggin(Seattle FAA ACO)Revision 5 - August 1989Revised CMR 12 to include in operationaltest the E&E Cooling System Bypass Valve.Revised CMR 13 from an operational test of the E&ECooling System Fan Check Valves to a detail visualinspection of the flapper doors and hinges.Added requirement to adjust/test the main deck air distribution shutoff valves on the Combi main deck fireprotection system.Approved by: D. L. Riggin(Seattle FAA ACO)Revision 6 - February 1991Revised CMR 3 RR effectivity to RR RB211-524 Series engines.Revised CMR 21 RR effectivity to RR RB211-524 seriesengines and excluded requirement to interrogate CMCfor engine 2 TOS on RB211 powered 747-400s equipped with EICAS Version RR004.Approved by: D. L. Riggin(Seattle FAA ACO)Revision 7 - March 1992Revised CMR 1 task description to Operational (Short) Test - 115-Volt Standby Power Generation.Revised CMR 16 to limit applicability to 747-400’sequipped with stabilizer fuel capability.Deleted CMR 21 because all RB211 powered 747-400s are now equipped with EICAS Software Version RR004or a later version.Approved by: D. L. Riggin(Seattle FAA ACO)Revision 8 - November 1992Revised CMR 3 to change the 250 FH check for RR RB211powered 747-400s to 500 FH in accordance with theupdated Type Certificate Data Sheet (TCDS No. E30NE, Rev date: June 5, 1992).Approved by: D. L. Riggin(Seattle FAA ACO)REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-7Revision 9 - January 1993Revised CMR 3 to change the 500 FH check for GE CF6-80C2B1F powered 747-400s to 1000 FH inaccordance with the FAA approved GE document GEK 98408, Rev. 6, dated September 1992.Approved by: D. L. Riggin(Seattle FAA ACO)Revision 10 - October 1993Revised CMRs 9, 10, 12, 14, and 15 to exclude the 747-400F due to addition of an E&E cooling system self-testdesign feature.Revised CMR 18 and 20 to exclude 747-400Fmodel applicability.Approved by: D. L. Riggin(Seattle FAA ACO)Revision 11 - January 1994Revised CMR 6 to change the 1000 FH check for the E&Ecooling system override mode function to 20,000 FHfor the 747-400F.Revised CMR 13 to exclude the 747-400F model applicability.Revised CMR 20 to change the1000 FH check of the lower lobe cargo compartment conditioned air system to7400 FH.Added 747-400 CMR-MPD/Task Card correlation list for reference.Approved by: D. L. Riggin(Seattle FAA ACO)Revision 12 - May 1994Revised CMR 3 to change the 500 FH check for the PW4000 engine to 1000 FH.Approved by: D. L. Riggin(Seattle FAA ACO)Revision 13 - June 1995Revised CMR 18 to revise the system description to note door #5 is not applicable on 747-400 Combi airplanesin the cargo mode and to add a noteto the task which specifies check isrequired immediately after conversionto passenger mode.Approved by: D. L. Riggin(Seattle FAA ACO)REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-8747-400 MAINTENANCE PLANNING DATARevision 14 - February 1997Revised CMR 18 to change the interval of part of the functional check procedure relating to the escapeslide/raft packs from 30 months to 36 months. The remainder of the check retains the interval of 30 months.Approved by: D. L. Riggin(Seattle FAA ACO)Revision 15 - May 1998Revised CMR 3 to change the 1000 FH check for GE CF6-80C2B1F powered 747-400’s to 2000 FH inaccordance with the FAA approved GE document GEK 98408, Rev 10, dated March 1996.Revised CMR 3 to change the 500 FH check for RR RB211 powered 747-400’s to 560 FH in accordance withthe updated Type Certificated Data Sheet (TCDS No. E30NE).Approved by: D. L. Riggin(Seattle FAA ACO)Revision 16 - July 2001Revised CMR 8B to change the interval from 6000 FH to10,000 FH based on revised High Lift System faulttree analysis.Revised CMR 9 and 10 to exclude 747-400F model applicability since the freighter airplane has the E/E Coolingautomatic system self test which occurs every tenth landing.Approved by: Liu-Nelson(Seattle FAA ACO)Revision 17 - September 2002Added requirements to replace door strike assembly at four-year intervals.Approved by: Liu-Nelson(Seattle FAA ACO)Revision 18 - October 2002Added CMR 25 applicable only to airplanes incorporating any of these Boeing Service Bulletins 747-25-3306and/or 747-25-3312. This amendedtype certificate complies with the new 14 CFR 25.795 and the amended14 CFR 25.772 as issued under FederalRegister Docket No. FAA-2001-11032.Approved by: Liu-Nelson(Seattle FAA ACO)REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-9747-400 MAINTENANCE PLANNING DATARevision 19 - February 2003Added CMR 26 applicable for line numbers 1320 and on except freighter models. This amended type certificatecomplies with the new 14 CFR 25.795 and the amended 14 CFR 25.772 as issued under Federal RegisterDocket No. FAA-2001-11032.Approved by: Liu-Nelson(Seattle FAA ACO)Revision 20 - March 2005Revised the format of MPD Section 9 to include the 747-400 Maintenance Planning Data (MPD) task referencesalongside each CMR task.Added standalone List of Effective Pages (LEP) to document.Added MPD Task Reference 52-051-08 to CMRs #24, #25 and #26.Revised MPD Item Numbers to reflect new item numbers as a result of transition to a new maintenancedocumentation publishing system.Approved by: Jeffrey Duven(Seattle FAA ACO)Revision 21 - August 2005Revised MPD Section 9 to add Airworthiness Limitations section.Added Nitrogen Generation System AWL and CDCCL.Revised Scope and CMR description section to explain and clarify.Approved by: (Seattle FAA ACO)Revision 22 - September 2005Revised MPD Section 9 to add Airworthiness Limitations Structures Inspection note for747-400 Special Freighter.Revised Certification Maintenance Requirements section to reflect 747-400 Special Freighter incorporation.Revised MPD item number for CMR 8 and 20 to correct reference.Revised CMR 18, Note 2 to specify that the task beaccomplished at 30 months rather than 36, whereas theremainder of the procedure can be performed at 36 months rather than 30.Revised procedure reference toremove E19 reference no longer required.Approved by: Jeffrey Duven(Seattle FAA ACO)REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-10747-400 MAINTENANCE PLANNING DATARevision 23 - March 2006Added new Fuel System Airworthiness Limitations whichinclude inspections and design limitations to satisfySFAR88 requirements.Revised Airworthiness Limitation 47-AWL-01 to add missing Step 3, and AWL 47-AWL-03 to correctATA reference.Revised CMR 10 AMM reference from 21-058-02 to 21-058-00 to correct reference.Revised CMR 20 MPD Item Number from 21-028-01 to 21-028-00 to correct reference.Approved by: A. J. Pasion(Seattle FAA ACO)Revision 24 - June 2006Revised tasks 47-AWL-01, 47-AWL-02,47-AWL-03, 47-AWL-04,47-AWL-05, 47-AWL-06to correct airplaneapplicability.Revised 28-AWL-9 and 28-AWL-10 to clarify the intentof the inspection and to clarify the location of thebonding measurements.Deleted 28-AWL-21, because production incorporationand service bulletin release have been postponedindefinitely.Added 28-AWL-24 which mandates an inspection for the horizontal stabilizer fuel boost pump autoshutoff system.Added new reserve tank fueling valve CDCCL AWL Number 28-AWL-25.Revised 47-AWL-05 and 47-AWL-06 to add Interval Note.Approved by: Jeffrey Duven(Seattle FAA ACO)November 2006Added a new operational check of the Main 2 and Main 3 override/jettison fuel pump uncommanded on systemAWL Number AWL 28-AWL-26.Approved by: Jeffrey Duven(Seattle FAA ACO)REVISION AND REVISIONDESCRIPTIONFAA APPROVALJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-11747-400 MAINTENANCE PLANNING DATADecember 2006Revised CMR-24, CMR-25, and CMR-26 intervals from 4 years to 6 years to reflect improved reliability data forthe Flight Deck Door Strike Assembly.Approved by: Jeffrey Duven(Seattle FAA ACO)December 2006 R1Revised to add Airworthiness Limitation Structures Inspection Note for 747-400 Large Cargo Freighter (LCF).Revised CMRs 15, 16, 20, 23, 24, 25, 26 to exclude 747-400 LCF derivative. Revised CMR 2 to exclude cargoand APU fire/overheat detection system for 747-400 LCF.Revised CMR 18 to “only applicable to door 1 L/H” for747-400 LCF.In Paragraph 1 of Section F, changed reference to 747 Supplemental Structural Inspection Document,D6-35022, Revision H to Revision G due to unknown release date for Revision H.Revised Airworthiness Limitations-fuel system section introduction toinclude revisions recommended by theSeattle FAA Flight Standards group.Revised airworthiness limitation number 28-AWL-24 to correct AMM procedure number from 28-22-00 to28-17-00 and to revise linenumber in the applicabilitycolumn from 1342 to 1343.Added Motor Operated Valve actuator Airworthiness Limitation. This AWL is applicable to airplane Line Position1382 and on, and airplanes modified per Service Bulletins 747-28A2292, and 747-28A2294.Approved by: Jeffrey Duven(Seattle FAA ACO)May 2007Added new CMR 27 to perform a functional check of theReserve Tank 2 and 3 VTO Secondary Shut-off Systemfor the 747-400 Large Cargo Freighter (LCF).Approved by: Jeffrey Duven(Seattle FAA ACO)REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-12747-400 MAINTENANCE PLANNING DATAOctober 2007Revised Section B. Airworthiness Limitations (AWLs) - Systems paragraph onExceptional Short-TermExtensions for AWLs to clarify notification requirements.Revised the title of Section C toread “Page Format: Fuel Systems Airworthiness Limitations" instead of“Page Format: Fuel Tank System Airworthiness Limitation”.Revised AWL Number 28-AWL-19 to add Ground Fault Interrupter (GFI) relays to the limitation that restrictsresetting of fuel pump circuit breakers.Added AWL Number 28-AWL-28, a yearly check of the MainFuel Tank Boost Pump GFI, applicable to airplaneLine Numbers 1394 and on and airplanes that have incorporated Service Bulletin 747-28A2261.Added AWL Number 28-AWL-29, a yearly check of the Center Wing Tank Electric Scavenge Pump GFI,applicable to airplanes with Electric Center Wing TankScavenge Systems, airplanes prior to Line Numbers 972that have incorporated Service Bulletin 747-28A2261.Added Section G. Certification Maintenance Requirements(CMRs) - Exception Short-Term Extensions to clarifynotification requirements.Revised CMR-24, CMR-25 and CMR-26 taskinterval from 6 years to 9 yearsto reflect improved reliability datafor the Flight DeckSecurity Door.Added Paragraph “I” to incorporate “Reporting Uncontrolled High Thrust Failure Conditions” per FAR 121.703and FAR 135.415.Approved by: Dorr Anderson for Jeffrey Duven(Seattle FAA ACO)November 2007Revised 28-AWL-25 bonding resistance value from0.015 ohms to 0.0015 ohms to correct a typo.(The correct valueis 1.5 milliohms).Revised CMR-27 to include Main FuelTanks 1 and 4 in VTO secondary shut-off system task for the 747-400Large Cargo Freighter.Approved by: Philip Forde for Jeffrey Duven(Seattle FAA ACO)REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-13747-400 MAINTENANCE PLANNING DATAFEBRUARY 2008Revised Paragraph F. AIRWORTHINESS LIMITATIONS (AWLs) - STRUCTURAL INSPECTIONS to addrestriction for 747-400 Special Freighters delivered after January 11, 2008.Approved by: Robert Breneman forJeffrey Duven (Seattle FAA ACO)MARCH 2008Revised Paragraph F. AIRWORTHINESS LIMITATIONS (AWLs) - STRUCTURAL INSPECTIONS to addrestriction for 747-400 Large Cargo Freighter (LCF) delivered after January 11, 2008 and to change end date ofDecember 1, 2007 to May 30, 2008 and add the text “appendix” per FAA letter dated July 16, 2007.Revised 28-AWL-01 by removing the 36000FH task interval limitation based upon engineering review andoperator maintenance practice.Revised 28-AWL-03 to reflect the new maximum loop resistance values associatedwith the lightning protectionof the unpressurized FQIS wire bundle installations so asto satisfy the Airworthiness Limitation Instructionsrequired by SFAR 88. Also removed the joint resistance values and 36000FH task interval limitation based uponengineering review and operator maintenance practice.Revised 28-AWL-10 by removing the 36000FH task interval limitation based upon engineering review andoperator maintenance practice.Revised 28-AWL-16 to change the term "grease" to "Corrosion Inhibiting Compound (CIC)" in Step 2 to reflectcorrect consumable type.Added AWLs 28-AWL-30, 28-AWL-31, and 28-AWL-32 toadd the Electronic Fuel Level Indication System(EFLI) CDCCL requirement for the 747-400 (910K).Approved by: Dorr Anderson for Jeffrey Duven(Seattle FAA ACO)APRIL 2008Revised the Procedure Reference for CMR 27 to remove incorrect Task number and reflect the correct PageBlock number.Approved by: Philip Forde for Jeffrey Duven(Seattle FAA ACO)REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-14747-400 MAINTENANCE PLANNING DATAMARCH 2009Revised Paragraph F., AIRWORTHINESS LIMITATIONS (AWLs) - STRUCTURAL INSPECTIONS to removeoperational limits on 747-400 airplanes converted to the Special Freighter configuration, as established forcompliance to 14 CFR § 26.45 (c), and confer standards for continued compliance to the specifications of 747Supplemental Structural Inspection Document, D6-35022.Approved by: Jeffrey Duven(Seattle FAA ACO)DECEMBER 2009Revised 28-AWL-03 by adding maximum loop resistancevalues, associated with thelightning protection of theFQIS wire bundle installations, specific to the 747-400 LCFderivative. Also specified that the existing values areapplicable to all 747-400 airplanes except 747-400 LCF, and clarified the wire bundlereferences as supplier partnumbers. Also added conditional dependency of installation for resistance measurements of ConnectorsX01014 and X01015, and listed additional wire bundles associated with Connector X01014.Revised 28-AWL-11 to clarify component of concern asFQIS processor unit and identify the componentmanufacturer (Goodrich).Revised 28-AWL-12, 28-AWL-13, 28-AWL-18, and 28-AWL-32 to identify the component manufacturers.(Continued on next page)SIGNATURE ON FILESEATTLE FAA ACO1/12/2010REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-15747-400 MAINTENANCE PLANNING DATADECEMBER 2009, ContinuedRevised 28-AWL-14 to identify the component manufacturer(Goodrich) and correct Revision identification forComponent Maintenance Manual 28-40-59 from "5" to "E".Revised 28-AWL-20 by adding note stating that the maintenance requirements are only applicable to areas thathave been disturbed. Also clarified airplane applicability.Revised 28-AWL-22 by changing terminology in item references from "bonding strap" to "bonding jumper" toclarify the item of concern.Revised 28-AWL-23 by changing terminology in item references from "bonding strap" to "bonding jumper" toclarify the item of concern.Also corrected resistancelimit from 0.25 milliohms to2.5 milliohms and clarifiedairplane applicability.Revised 28-AWL-24 to noteconditional dependencyof Horizontal Stabilizer FuelBoost Pump Automatic ShutoffSystem installation for AWL applicability.Also clarified airplane applicability.Revised 28-AWL-31 to correct spellingof the acronymfor Electronic Fuel Level Indication System (EFLI) andidentify the component manufacturer (Parker).Revised 28-AWL-05, 28-AWL-25, 28-AWL-26, 28-AWL-27, and 28-AWL-28 toclarify the airplane applicability.Revised Section F., AIRWORTHINESSLIMITATIONS (AWLs) - STRUCTURALINSPECTIONS to include noticeof the additional and revised inspection requirementsfor 747-400 Large Cargo Freighter (LCF) airplanesimposed by Service Bulletins 747-00-2120 and 747-53A2817, respectively; updated the document reference forthe 747-400 LCF Supplemental Structural Inspection Document, and removed operational limits on 747-400LCF airplanes delivered after January 11, 2008, originally established for compliance to 14 CFR § 26.45 (c).(Continued from previous page)REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-16747-400 MAINTENANCE PLANNING DATAJULY 2010Revised introduction to Section E: Airworthiness Limitations - Nitrogen Generation System tasks to identify andupdate the FAA regulations corresponding to the compliance measures provided in the subsequent AWLs.Revised description for 47-AWL-01 by adding Service Bulletin specifications to the airplane applicability. Alsoadded instructions and a note to clarify the procedure and parameters for the maintenance action.Revised 47-AWL-02 by changing the airplane applicability to add Service Bulletin specification and remove LineNumbers which are no longer affected.Deleted 47-AWL-03, 47-AWL-04, 47-AWL-05, and 47-AWL-06 because they are no longer applicable to thesubject airplanes.Added AWL 47-AWL-07, a 25,000 Flight Hour inspection of the Nitrogen Enriched Air distribution ducting.Added AWL 47-AWL-08, a 25,000 Flight Hour check ofthe Nitrogen Generation Cross-Vent Check Valve.Added AWL 47-AWL-09, an identification of the maintenance standard for the Nitrogen Generation System andnotice of potential future compliance requirements associated with decreased aircraft descent rates.SIGNATURE ON FILESEATTLE FAA ACO7/16/2010NOVEMBER 2010Revised 47-AWL-07 and 47-AWL-08 by updating the Intervalfrom 25,000 Flight Hours (FH) to 21,250 FH, basedon updated analysis.SIGNATURE ON FILESEATTLE FAA ACO2/3/2011JULY 2011Revised 47-AWL-02 to incorporate NGS performance features to show compliance with 14 CFR 26.33.SIGNATURE ON FILESEATTLE FAA ACO8/17/2011OCTOBER 2011Added AWL 47-AWL-10, a 54,000 Flight Hour removal and replacement of the Thermal Switch.SIGNATURE ON FILESEATTLE FAA ACO11/30/2011JULY 2012Added a new Section F.1 Limit of Validity (LOV) as required by Title 14 Code of Federal Regulations (CFR)Section 26.21 (Amendment 26-6).SIGNATURE ON FILEFAA BASOO8/8/2012REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-17AUGUST 2012Revised the title of Section B by adding “Fuel” and replaced the “Airworthiness Limitations - Fuel Systems”subheading with "Introduction" to be consistent with other Section 9 documents.Revised Section C, making it a subheading of Section B, to be consistent with other Section 9 documents.Revised Section D to become Section B.1, and revised thetitle from “Airworthiness Limitations – Fuel Systems”to “AWLs – Fuel System Ignition Prevention” tobe consistent with other Section 9 documents.Added Section B.2, Impact-Resistant Fuel Tank Access Doors.Revised Section E, making it Section B.3 and replaced“Airworthiness Limitations – Nitrogen Generation SystemTasks” with “AWLs – Nitrogen GenerationSystem (NGS)”. Also added “Airworthiness Limitations – NitrogenGeneration System” subheading to be consistent with other Section 9 documents.Revised Section F and Section F.1, making it Section C and C.1 respectively and replacing the old Section F titlefrom "Airworthiness Limitations (AWLs) - StructuralInspections" to "AWLs -Structural Inspections".Revised Section G, making it SectionD and revised Section H, making it asubheading of Section D and revisedthe title to "CMR Tasks" to be consistent with other Section 9 documents.Revised the lettering of the remaining section to be sequential with the previous heading revisions.SIGNATURE ON FILEFAA BASOO10/02/2012JUNE 2014Revised Section A, Scope, to defineFAA Oversight Office and replaced all references to "Seattle FAA ACO"with "FAA Oversight Office" throughout the entire document.Replaced the word "per" with "in accordance with" throughout the entire section except for the "per" in the AWL28-AWL-20, 28-AWL-24, and28-AWL-27 applicability. Theword "per" in the AWL 28-AWL-23, 28-AWL-24, and28-AWL-27 applicability was replacedwith "that haveincorporated".References to FAA regulations were changed to include "Title 14 CFR §" to accurately reflect FAA regulationcitations throughout the document and for consistency.The following revisions were made in Section B front matter:Replaced the first paragraph under "Introduction" with the information on FAA approved AirworthinessLimitations required under Title 14 CFR § 43.16 and § 91.403.Deleted the "Deviations From CMMor AMM Instructions" subheading.(Continued on next page)SIGNATURE ON FILEFAA BASOO08/29/2014REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-18747-400 MAINTENANCE PLANNING DATAJUNE 2014, ContinuedRevised the "Use of Alternate Tools" subheading to "Useof Alternate or Equivalent Tools, Test Equipment orMaterials". Clarified that the use of alternate tools or equivalent tools, test equipment or materials not listed inthe AWL requires approval from FAA Oversight Office. Also clarified that the CMM cited as "in accordance with"and not "refer to" are FAA approved and the alternate tools or equivalent tools, test equipment or materials notlisted in the CMM require FAA Oversight Office approval.Deleted “For AWLS” from the "Exceptional Short-Term Extensions For AWLs" subheading. Changed referencesto "fuel system AWL" to "system AWL" to apply the front matter to all AWLs in Section B. Revised "(e.g., aPrincipal Maintenance Inspector)" to "or a Principal Maintenance Inspector" and the Flight Standards Handbookreference from "8300.10" to "8900.1 FSIMS".Added the "Accomplishment Instructions –General Information" section to clarify the use of "in accordance with"and "refer to" verbiage when referencing other Instructions for Continued Airworthiness documents and addedreference to SWPM 20-20 for electrical bonding and grounding requirements.Added new subparagraphs "Definitions", to provide further clarification on accomplishment instructions, and"Supporting Documentation", to clarify that strict adherence to the methods, techniques and practices, asprescribed, is required to ensure the ALI or CDCCL is complied with.Revised the "Page Format: Fuel Systems AirworthinessLimitations" subheading to "Page Format: SystemsAirworthiness Limitations" to apply thefront mater to all AWLs in Section B.The following changes were made to Section B.1:Added "Amendment 25-102" to the Title 14 CFR § 25.981 regulations and a statement that the auxiliary tankcomply with these regulations.Revised 28-AWL-07 to clarify when new repairs or alterations involving penetrations tothe fuel tanks need to bereviewed by the FAA Oversight Officeand added when a repair or alteration does not require additional FAAOversight Office approval.Added 28-AWL-33 (ALI), Teflon Sleeving – Out-of-TankWire Bundle, for the inspection of Teflon sleeving andclamps around the wire bundle in clamp locations specified in Service Bulletin 747-57A2327 and 747-28A2324.Added 28-AWL-34 (CDCCL), Teflon Sleeving – Out-of-Tank WireBundle, to verify thatthe Teflon sleeving is notdamaged around the wire bundle in clamp locations specified in Service Bulletin 747-57A2327 and 747-28A2324.(Continued on next page)(Continued from previous page)REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-19JUNE 2014, ContinuedAdded 28-AWL-35, Fuel Boost Pump Wires In Conduit Installation – In Fuel Tank (for all airplanes that haveincorporated SB 747-28A2306) for the verification of the conduit liner, Teflon sleeve, and jacketed and shieldedwiring is installed when the pump wiring or wiring in the conduit is removed or replaced.Added 28-AWL-36, Fuel Boost Pump Wires In Conduit Installation – In Fuel Tank (for all airplanes that haveincorporated SB 747-28A2204 but have not incorporatedSB 747-28A2306) for the verification of the Teflonsleeve is installed when the pump wiring or wiring in the conduit is removed or replaced.Added 28-AWL-37, Lightning, Fault Current or Hot Short Protection Features – In Tank Sealant Requirements torequire an inspection ofthe cap seals and fillet seals when maintenance is performed in the fuel tanks.Revised 57-AWL-01 to add reference to Boeing AMM 28-11-02.The following revisions were made in Section C front matter:Revised the MRBR section references in the third paragraph to reflect the correct titles for the MRBR.(Continued from previous page)REVISION AND REVISIONDESCRIPTION FAA APPROVALJUN 2014Section Page Date Section Page Date Section Page Date Section Page Date Section Page DateD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-20LIST OF EFFECTIVE PAGES747-400 MAINTENANCE PLANNING DATA9.0 1 JUN 20149.0 2 BLANK9.0 3 JUN 20149.0 4 BLANK9.0 5 JUN 20149.0 6 JUN 20149.0 7 JUN 20149.0 8 JUN 20149.0 9 JUN 20149.0 10 JUN 20149.0 11 JUN 20149.0 12 JUN 20149.0 13 JUN 20149.0 14 JUN 20149.0 15 JUN 20149.0 16 JUN 20149.0 17 JUN 20149.0 18 JUN 20149.0 19 JUN 20149.0 20 JUN 20149.0 21 JUN 20149.0 22 JUN 20149.0 23 JUN 20149.0 24 JUN 20149.0 25 JUN 20149.0 26 JUN 20149.0 27 JUN 20149.0 28 JUN 20149.0 29 JUN 20149.0 30 JUN 20149.0 31 JUN 20149.0 32 JUN 20149.0 33 JUN 20149.0 34 JUN 20149.0 35 JUN 20149.0 36 JUN 20149.0 37 JUN 20149.0 38 JUN 20149.0 39 JUN 20149.0 40 JUN 20149.0 41 JUN 20149.0 42 JUN 20149.0 43 JUN 20149.0 44 JUN 20149.0 45 JUN 20149.0 46 JUN 20149.0 47 JUN 20149.0 48 JUN 20149.0 49 JUN 20149.0 50 JUN 20149.0 51 JUN 20149.0 52 OCT 20119.0 53 JUN 20149.0 54 OCT 20119.0 55 JUN 20149.0 56 JUN 20149.0 57 JUN 20149.0 58 JUN 20149.0 59 JUN 20149.0 60 AUG 20129.0 61 APR 20089.0 62 APR 20089.0 63 APR 20089.0 64 APR 20089.0 65 JUN 20149.0 66 JUN 2014JUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-21A. SCOPEThe scheduled maintenance requirements described in this section result from Model 747-400 airplane certification activities with the U.S. Federal AviationAdministration (FAA). Accordingly, thisFAA approved Airworthiness Limitations (AWLs) and Certification Maintenance Requirements (CMRs) document iscross-referenced in the Model 747-400 Type Certificate Data Sheet. These maintenance actions are mandatory.This Airworthiness Limitations Section isFAA-approved and specifies maintenance required under Title 14 Code of Federal Regulations (CFR) § 43.16and § 91.403 of the Federal Aviation Regulations, unless an alternative program has been FAA approved.Where used in this document, the term “FAAOversight Office” is defined as the FAA office that currently has oversight responsibility for the type certificateof the Boeing model 747-400. At the timeof publication, the FAA office with oversight responsibility for the type certificateof the 747-400 is the FAABoeing Aviation Safety Oversight Office (BASOO).AIRWORTHINESS LIMITATIONS (AWLs)The Airworthiness Limitations may only be revisedwith the approval of the FAA Oversight Office.If the inspections cannot be accomplished due to repairs and/or modifications, an alternate inspection acceptable to the FAA Oversight Office mustbe used.CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)These scheduled maintenance tasks may only be revised by the FAA Oversight Office. PrincipalMaintenance Inspectors (local regulatory authority) maynot change these requirements or the intervals associated with these requirements.JUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-22747-400 MAINTENANCE PLANNING DATAB. AIRWORTHINESS LIMITATIONS (AWLs) – SYSTEMSINTRODUCTIONThe airplane systems maintenance requirements described in thisAWL document result from various 747-400 airplane certificationactivities with the FAA.This Airworthiness Limitations section is FAA-approved and specifies maintenance required under Title 14 CFR § 43.16 and § 91.403 of the FederalAviation Regulations, unless an alternative program has been FAA Oversight Office approved. The AWLs may only be revised withthe approval of theFAA Oversight Office. If the maintenance requirements cannot beaccomplished due to repairs and/or modifications, an alternateinspection, acceptable tothe FAA Oversight Office, must be used.An AWL may be an Airworthiness Limitation Instruction (ALI) or aCritical Design Configuration Control Limitation (CDCCL).CDCCLs are a means of identifying certain design configuration features intended to preclude a fuel tank ignition source for the operational life of theairplane as required under Special Federal Aviation Regulation No. 88 (SFAR 88) – Fuel Tank System Fault Tolerance Evaluation Requirements andTitle 14 CFR § 25.981 – Fuel Tank IgnitionPrevention. CDCCLs are mandatory and cannotbe changed or deleted without the approval of the FAAOversight Office. A critical fuel tank ignition source prevention feature may exist in the fuel system and its related installation or in systems that, if a failurecondition were to develop, could interact with the fuel systemin such a way that an unsafe condition would develop without this limitation. Strict adherenceto configuration, methods, techniques, and practices as prescribed is required to ensure compliance with the CDCCL. Any use ofparts, methods,techniques or practices not contained in the applicable CDCCL must be approved by the FAA Oversight Office. For each CDCCL, the word "maintenance"includes maintaining any installation during alterations; therefore, adherence to the CDCCL is required during maintenance or alterations.ALIs identify inspection tasks that mustbe done to maintain the design level of safety for the operational life of the airplane to prevent an unsafe condition.ALIs are mandatory and cannot be changed or deleted without theapproval of the FAA Oversight Office. Strict adherence to methods, techniques andpractices as prescribed is required to ensure the ALI is complied with. Any use of methods, techniques or practices not contained in these ALIs must beapproved by the FAA Oversight Office.JUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-23REGULATORY AGENCY APPROVALAny deviations from the published AWL instructions included in this document require approval from the FAA Oversight Office. This applies to operatorsunder the U.S. FAA jurisdiction only and toairplanes registered in the U.S. Operators who are not under the U.S. FAA jurisdiction should obtain approvalfrom their own local regulatory agency for anydeviations from the listed AWL instructions.AWL REVISION PROCESSIn the event that an AWL is revised, Boeing will prepare a revision tothis document that will be approved by the FAA OversightOffice. This revision willthen be forwarded to all 747-400 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 documents.• When a document is cited using the words "in accordance with"in an airworthiness limitation, the cited document (or documentsection) must be followedto ensure that the critical design feature is maintained. Any deviation from the cited document requires FAA Oversight Office approval.• When a document is cited using the words "refer to" in an airworthiness limitation, the cited document (or document section) represents one method ofcomplying with the airworthiness limitation.An alternative procedure may be developed by an operator in accordance with its procedures in itsmaintenance program/manual.For electrical bonding and grounding requirements, refer tothe Boeing Standard Wiring Practices Manual (SWPM) 20-20.USE OF ALTERNATE OR EQUIVALENT TOOLS, TEST EQUIPMENT OR MATERIALSFor AWLs which require the use of certain tools, test equipmentor materials, use of alternateor equivalent tools, test equipment or materials requires priorapproval 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 Oversight Office approved.If the CMM allows the use of alternate or equivalent tools, testequipment or materials, use ofan alternate or equivalent tool, test equipment or materialdoes not require further approval by the FAA Oversight Office.JUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-24747-400 MAINTENANCE PLANNING DATAEXCEPTIONAL SHORT-TERM EXTENSIONSSince AWL intervals are based on estimations of the probability ofan event, an exceptional short-term extension for each system AWL listed in thisdocument may be made without jeopardizing safety. The local regulatory authority or a Principal Maintenance Inspector must concur with any exceptionalshort-term extensions before they take place using procedures established with the local regulatory authority in the operators'manuals. The "exceptionalshort-term extension" process is applicable to AWL intervals. It should not be confused with the operator's "short-term escalation" program for normalmaintenance tasks described in the operators' manuals and in the Flight Standards Handbook 8900.1 FSIMS.The FAA Oversight Office has accepted that these exceptional short-term extensions may be granted without consultation with that office:1. The term “exceptional short-term extension” is defined as an increase in a system AWL interval that may be needed to cover anuncontrollable orunexpected situation. All AWLs listed in this section have been approved with an exceptional short-term extension of 30 days.2. Repeated use of extensions, either on the same airplane or onsimilar airplanes in an operator's fleet, should not be used asa substitute for goodmanagement practices. Exceptionalshort-term extensions must not beused for fleet AWL extensions.3. After a system AWL has experienced an exceptionalshort-term extension, the AWL interval will revert back to its interval listed in this document. TheFAA Oversight Office must approve, prior to its use,any desired extension notexplicitly listed above.NOTE: This exceptional short-term extension listed above applies toairlines that fall under the U.S. FAA jurisdiction only. Operators who are not under theU.S. FAA jurisdiction should obtain interval extension approvals from their local regulatory agency.JUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-25DEFINITIONSRemoved or Replaced: Defined as removal or replacement of a component, aswell 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 AirworthinessCertificate issuance or after thedate that the MPD Section 9, D621U400-9, was first incorporated into an operator's maintenance program, whichever is later.Sealant: Defined as sealant type BMS 5-45 or equivalent inaccordance with SRM 51-20-05 for inside of fuel tank, and sealant type BMS 5-95 orequivalent in accordance with SRM 51-20-05 for outside of the fuel tank.FAA Oversight Office: Defined as the FAAoffice that currently has oversight responsibility for the type certificate of the Boeing Model 747-400 aircraft. Atthe time of publication, the FAAOversight 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. Airlines must follow themanufacturer's maintenance procedures when performing maintenancethat has an effect on an ALI or CDCCL. If operators do not obey the procedures, itcan increase the risk of an unsafe condition.Any use of methods, techniques or practices not contained in these ALIs or CDCCLsmust be approved bythe FAA Oversight Office.JUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-26747-400 MAINTENANCE PLANNING DATAPAGE FORMAT: SYSTEMS AIRWORTHINESS LIMITATIONSCOLUMN EXPLANATIONAWL NUMBER Each task is given a unique AWL Item Number. The first and second digits are the ATA Chapter Number.TASK ALI = Airworthiness Limitation Instruction. These tasks are inspections that should be performed at the listed intervals.CDCCL = Critical Design Configuration Control LimitationsINTERVAL Task frequencies are specified in terms of a usage parameter such as flight hours, cycles or calendar time.APPLICABILITY Airplanemodel applicability.DESCRIPTION Description of the task to beperformed or critical design configurationsaspects that cannot be changed without violatingthe intent of the design.JUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-27B.1 FUEL SYSTEM IGNITION PREVENTIONThis section contains an FAA approved program of scheduled inspections and design limitations for operators to incorporate intotheir maintenanceprogram for this type design to meet the new standards and assumptions introduced by Title 14 CFR § 25.981 and SFAR 88. SFAR 88 – Fuel TankSystem Fault Tolerance Evaluation Requirements and Title 14 CFR § 25.981 – Fuel Tank Ignition Prevention require maintenance instructions, and controllimitations for certain fuel tankcritical 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) require certain design approvalholders of Type Certificates (TCs) and Supplemental Type Certificates (STCs) of large transport airplanes to conduct a safety review of the fuel tanksystems. The purpose of the safetyreview is to identify design features that may result in developmentof ignition sources inthe fuel tank. Fuel SystemAWLs are mandatory maintenance actions required to ensure that unsafe conditions identified by the SFAR 88 safety review do notoccur or are notintroduced into the fuel tank system as a result of configuration changes, repairs, alterations, or deficiencies in the maintenance program throughout theoperational life of the airplane.JUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-28747-400 MAINTENANCE PLANNING DATAAWLs – FUEL TANK IGNITION PREVENTIONAWL Number Task Interval Applicability Description28-AWL-01 ALI 12 YRS ALL ExternalWires Over Center Fuel TankConcern: Potential for chafing and arcing through center Fuel Tank Upper Panel.Perform a detailed inspection of the bundles routedon main deck over the center fuel tank andunder the main deck floor boards in accordance with Boeing AMM 28-11-00 to detect damagedor loose clamps, wire chafing, and that the wire bundle is not in contact with the surface of thecenter fuel tank. If discrepancies are found,ensure wires are installed in accordance with theapplicable wire installation drawings and repair in accordancewith the Boeing Standard WiringPractices Manual D6-54446.28-AWL-02 CDCCL N/AALL External Wires Over Center Fuel TankConcern: Potential for wire chafing and arcing to center Fuel Tank Upper Panel.If any maintenance is performed in the area under the main deck floor boards and over thecenter fuel tank, verify the following:1. Maintain the existing wire bundle routing and clamping.2. Installation of any new wire bundles mustbe in accordance with Boeing Standard WiringPractices Manual D6-54446.3. All wire bundles over the center fuel tank are inspected in accordance with 28-AWL-01.JUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-2928-AWL-03 ALI 12 YRSALL Fuel Quantity Indicating System (FQIS) – Out Of Tank Wiring Lightning Shield toGround TerminationConcern: Potential for Lightning induced voltages on the FQIS wiring to enter the fuel tank.Perform the following inspection to ensure the functional integrity of the FQIS wiring shield toground termination in accordance with Boeing AMM 5-55-54:1. Visually inspect all connectorsat the location being tested to ensure they are tight. Thisincludes connector plugs and backshells.2. Use a Loop Resistance Tester, P/N 906-10246-2or 906-10246-3, to measure and verifythe resistance of the shield to ground termination for the following items:The following applies to all 747-400 except 747-400 Large Cargo Freighter (LCF)Major Design Change:The loop resistance shall not exceed 40milliohms for ConnectorX01021 and the wirebundle supplier part number CN1036-151(Wing LE L/H Densitometer Main 1).The loop resistance shall not exceed 40milliohms for ConnectorX01025 and the wirebundle supplier part number CN1036-152 (Wing LE L/H Densitometer Main 2).The loop resistance shall not exceed 40milliohms for ConnectorX01031 and the wirebundle supplier part number CN1036-152 or -172 (Wing LE R/H Densitometer Main 3).The loop resistance shall not exceed 40milliohms for ConnectorX01037 and the wirebundle supplier part number CN1036-151 or -171 (Wing LE R/H Densitometer Main 4).The loop resistance shall not exceed 40milliohms for ConnectorX01019 and the wirebundle supplier part number CN1036-116 or -316 (Wing LE L/H Main Tank 1).The loop resistance shall not exceed 40milliohms for ConnectorX01023 and the wirebundle supplier part number CN1036-117 or -317 (Wing LE L/H Main Tank 2).The loop resistance shall not exceed 40milliohms for ConnectorX01030 and the wirebundle supplier part number CN1036-117, -317 or -327 (Wing LE R/H Main Tank 3).The loop resistance shall not exceed 40milliohms for ConnectorX01036 and the wirebundle supplier part number CN1036-116, -316 or -326 (Wing LE R/H Main Tank 4).The loop resistance shall not exceed 40milliohms for ConnectorX01028 and the wirebundle supplier part number CN1036-111 or -113 (Wing LE L/H Main 2 Single PointSensor).The loop resistance shall not exceed 40milliohms for ConnectorX01034 and the wirebundle supplier part number CN1036-111 (Wing LE R/H Main 3 Single Point Sensor).(Continued on next page)AWL Number Task Interval ApplicabilityDescriptionJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-30747-400 MAINTENANCE PLANNING DATA28-AWL-03(Continued)ALI 12 YRS ALL Fuel Quantity Indicating System (FQIS) – Out Of Tank WiringLightning Shield toGround Termination (Continued)The loop resistance shall not exceed 40milliohms for ConnectorX01008 and the wirebundle supplier part number CN1036-118, -318 or -518 (Center Wing Tank).The loop resistance shall not exceed 40milliohms for ConnectorX01012 and the wirebundle supplier part number CN1036-112 or -312 (Center Tank Single Point Sensor).The loop resistance shall not exceed 40milliohms for ConnectorX01009 and the wirebundle supplier part number CN1036-153 or -353 (Center Tank Densitometer).The loop resistance shall not exceed 40milliohms for ConnectorX01040 and the wirebundle supplier part number CN1036-115, -315 or -325 (Wing LE L/H Reserve Tank 2).The loop resistance shall not exceed 40milliohms for ConnectorX01042 and the wirebundle supplier part number CN1036-115, -315 or 325 (Wing LE R/H Reserve Tank 3).The loop resistance shall not exceed 61milliohms for ConnectorX01015 and the wirebundle supplier part number CN1036-154, -354 or -554 (Horizontal Stab Densitometer,if installed).The loop resistance shall not exceed 59milliohms for ConnectorX01014 and the wirebundle supplier part number CN1036-119, -319, -519 or -719 (Horizontal Stab Fuel Tank,if installed).The following applies only to 747-400 Large Cargo Freighter (LCF) Major DesignChange:The loop resistance shall not exceed 24milliohms for ConnectorX01021 and the wirebundle supplier part number CN1036-351(Wing LE L/H Densitometer Main 1).The loop resistance shall not exceed 22milliohms for ConnectorX01025 and the wirebundle supplier part number CN1036-352 (Wing LE L/H Densitometer Main 2).The loop resistance shall not exceed 22milliohms for ConnectorX01031 and the wirebundle supplier part number CN1036-355 (Wing LE R/H Densitometer Main 3).The loop resistance shall not exceed 24milliohms for ConnectorX01037 and the wirebundle supplier part number CN1036-356 (Wing LE R/H Densitometer Main 4).The loop resistance shall not exceed 17milliohms for ConnectorX01019 and the wirebundle supplier part number CN1036-516 (Wing LE L/H Main Tank 1).The loop resistance shall not exceed 15milliohms for ConnectorX01023 and the wirebundle supplier part number CN1036-517 (Wing LE L/H Main Tank 2).(Continued on next page)AWL Number Task Interval Applicability DescriptionJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3128-AWL-03(Continued)ALI 12 YRS ALL Fuel Quantity Indicating System (FQIS) – Out Of Tank WiringLightning Shield toGround Termination (Continued)The loop resistance shall not exceed 29milliohms for ConnectorX01008 and the wirebundle supplier part number CN1036-718 (Center Wing Tank).The loop resistance shall not exceed 15milliohms for ConnectorX01030 and the wirebundle supplier part number CN1036-522 (Wing LE R/H Main Tank 3).The loop resistance shall not exceed 17milliohms for ConnectorX01036 and the wirebundle supplier part number CN1036-521 (Wing LE R/H Main Tank 4).The loop resistance shall not exceed 34milliohms for ConnectorX01028 and the wirebundle supplier part number CN1036-311 (Wing LE L/H Main 2 Single Point Sensor).The loop resistance shall not exceed 34milliohms for ConnectorX01034 and the wirebundle supplier part number CN1036-313 (Wing LE R/H Main 3 Single Point Sensor).The loop resistance shall not exceed 27milliohms for ConnectorX01009 and the wirebundle supplier part number CN1036-557 (Center Tank Densitometer).The loop resistance shall not exceed 28milliohms for ConnectorX01040 and the wirebundle supplier part number CN1036-515 (Wing LE L/H Reserve Tank 2).The loop resistance shall not exceed 28milliohms for ConnectorX01042 and the wirebundle supplier part number CN1036-520 (Wing LE R/H Reserve Tank 3).28-AWL-04 CDCCL N/A ALL FQIS – Out Of Tank Wiring Lightning Shield to Ground TerminationConcern: Potential for Lightning induced voltages on the FQIS wiring to enter the fuel tank.If any maintenance is performed on the FQIS wire bundle in the un-pressurized zone at thespar pressure seal, verify the following:1. Verify presence of shielded wiring.2. Verify the shield ground is terminated inaccordance with Boeing SWPM 20-10-15.3. The installation is checked as specified in 28-AWL-03.AWL Number Task Interval Applicability DescriptionJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-32747-400 MAINTENANCE PLANNING DATA28-AWL-05 CDCCL N/A 747-400 airplanesLine Numbers 1272and on;or airplanes thathave incorporatedService Bulletin747-29A2104.Lightning Protection – HydraulicLine Fuel Tank PenetrationConcern: Potential for arcing or sparking inside the tank at the interface between the bulkheadfitting and the spar during a lightning strike event.The following design features must be maintained in accordance with Boeing AMM 29-11-22. Ifthe bulkhead fitting is removed and replaced:1. Verify electrical fay surface bond between the hydraulic fitting flange and the spar mustbe 0.001 ohms or less.2. Install fillet seal on the fitting tothe tank wall interface outside the tank.3. Install full bodied fillet sealencapsulating the fitting to the tank wall interface insidethe tank.4. Verify an electrostatic bonding jumper exists between the structure and the HydraulicHeat Exchanger inside the tank.5. Verify electrical bond from structure to theHydraulic Heat Exchanger inside the tank is0.005 ohms or less.28-AWL-06 CDCCL N/A ALL AC Pump and DC Pump MaintenanceConcern: Potential for maintenance error during pump overhaul. Fuel pump designs containignition source prevention means (i.e., flamearrestor, thermal fuses, materials, leadwireretention means, etc.) that must be maintained if pump is overhauled.Repair and overhaul of Fuel Pumps must be in accordance with the current manufacturerComponent Maintenance Manual (CMM) Numbers 28-22-07 Revision Number 1, 28-31-03Revision Number 3, 28-26-12 Revision Number 0, 28-26-14 Revision Number 0, 28-20-02Revision Number 9, or later revisions of these CMMs that have been approved by the FAAOversight Office.AWL Number Task Interval Applicability DescriptionJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3328-AWL-07 CDCCL N/AALL Lightning, Fault Current or Hot Short Protection – Fuel Tank PenetrationsConcern: Potential for arcing or sparking inside the tank at a conductive metal-to-groundstructure interface as a result of electrical fault currents or lightning strike events due toinsufficient bonding within the ground electrical path.Any repair or alteration involving new or altered penetrations to the fuel tanks (such as a repairwith fasteners, adding a bracket, bulkhead fitting or equipment, etc.) or change to the designfeatures of the existing equipment penetrations(such as fuel measuring sticks, sump drainvalves, fueling manifold, fueltemperature sensor, and motor operated fuel shutoff valveadaptor plate) requires approval from the FAA Oversight Office.However, no additional FAA Oversight Office approval is required if the repair or alteration isaccomplished in accordance with:1. Structural Repair Manual procedures, and/or2. Boeing Service Bulletins, and/or3. Boeing ODA approved repair/alteration instructions;where all the required procedures that relate to the new or altered fuel tank penetration includethe statement, "These data have been reviewedby the Boeing ODA for fuel tank ignitionprevention requirements, and no further approval from the FAA Oversight Office is required tosatisfy the requirements ofCDCCL 28-AWL-07 provided therepair or alteration isaccomplished in accordancewith these instructions."Note: Electrical bonding of fittings and brackets and/or capsealing of fasteners and/or filletsealing of component interface to structure insideand/or outside the fueltank will be required.28-AWL-08 CDCCL N/AALL Fuel Quantity Indicating System (FQIS) – Out Of TankWiring Installation SeparationRequirementConcern: Potential for hot shorts and EMI induced voltages on the FQIS wiring outside of thetank to enter the fuel tank.Routing and installation of any new wiring must use wire types BMS 13-48, BMS 13-60 orBMS 13 58, and not be within a 2-inch radius of the FQIS wiring. When a single clamp fails, aseparation greaterthan 1⁄2 inch must be maintained from FQIS wiring.AWL Number Task Interval ApplicabilityDescriptionJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-34747-400 MAINTENANCE PLANNING DATA28-AWL-09 CDCCL N/AALL Center Wing Tank Fueling Valve-Fault Current BondConcern: Potential for arcing or filament heating inside the center wing fuel tank.The following design features must be maintained in accordance with Boeing AMM 28-21-13when the center wing tank fueling valve is removed and replaced:1. Bonding jumper between the valve body and structure inside the tank.2. Measure the resistance from the valve bodyto the adjacent structure. Resistance mustbe 0.010 ohms (10 milliohms) or less.The following design features must be maintained in accordance with Boeing AMM 28-21-02when the center wing tank refuel valve control unit is removed and replaced:1. The bonding resistance from the exposed threads on the valve unit mounting stud (onelocation), to the refuel valve control unitAND the bonding resistance from the exposedthreads on the valve unit mounting stud (one location), to structure (spar) must not bemore than 0.010 ohms (10 milliohms).This installation is checked as specified in 28-AWL-10.28-AWL-10 ALI 12 YRSALL Center Wing Tank Fueling Valve-Fault Current BondConcern: Potential for arcing or filament heating inside the center wing fuel tank.This installation includes the following checks in accordance with Boeing AMM 28-21-13:1. The bonding resistance from the exposed threads on the valve unit mounting stud (onelocation), to the refuel valve control unitAND the bonding resistance from the exposedthreads on the valve unit mounting stud (one location), to structure (spar) must not bemore than 0.010 ohms (10 milliohms).28-AWL-11 CDCCL N/AALL Fuel Quantity Indicating System (FQIS) – Fuel Quantity Processor Unit (FQPU) RepairConcern: Potential for maintenance error during FQPU repair. The FQPU is designed to limitthe levels of energy, voltage, current, and powerallowed within the FQIS circuit to intrinsicallysafe levels in order to preclude the potentialof an ignition source within any fuel tank.Repair and overhaul of FQIS processor units must be in accordance withGoodrich (V89305)CMM 28-41-62 Revision 4, or later revisions ofthis CMM that have been approved by the FAAOversight Office.AWL Number Task Interval ApplicabilityDescriptionJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3528-AWL-12 CDCCL N/AALL Single Point Sensor (SPS) Control Card RepairConcern: Potential for maintenance error duringSPS control card repair. The SPS control cardis designed to limit the levelsof energy, voltage, current, and power allowed within the SPScircuit to intrinsically safe levels in order to preclude the potential of an ignition source withinany fuel tank.Repair and overhaul of Single Point Sensor Control Card must be in accordance with RagenData Systems (V58880) CMM 28-21-02 Revision 2,or later revisions of this CMM that havebeen approved by the FAA Oversight Office.Note: Ragen Data Systems is now Vibro-Meter Inc.28-AWL-13 CDCCL N/A All 747-400 with HST Remote Electronic Unit (REU) RepairConcern: Potential for maintenance error duringREU repair. The REU is designed to limit thelevels of energy, voltage, current, and power allowed within the REU circuit to intrinsically safelevels in order to preclude the potentialof an ignition source within any fuel tank.Repair and overhaul of REU must be in accordance withGoodrich (V89305) CMM28-41-63Revision 4, or later revisions of this CMMthat have been approved by the FAA OversightOffice.28-AWL-14 CDCCL N/AALL Fuel Quantity Indicating System (FQIS) – Repair ofIn-Tank Hardware (Tank Units,Densitometers, and Compensators)Concern: Potential for maintenance error during repair of in-tank hardware (tank units,compensators and densitometers). Arc gaps may develop that could result in an ignitionsource inside the fuel tank.Repair and overhaul of FQIS tank units, compensators, and densitometers must be inaccordance with Goodrich (V89305)CMM28-40-55 Revision 6, 28-40-56 Revision 4, 28-40-59Revision E, or later revisions of these CMMs that have been approved by the FAA OversightOffice.AWL Number Task Interval ApplicabilityDescriptionJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-36747-400 MAINTENANCE PLANNING DATA28-AWL-15 CDCCL N/AALL Fuel Quantity Indicating System (FQIS) – Repair of In-Tank Wire HarnessConcern: Potential for error during repair or replacement of in-tank wire harness. Arc gaps maydevelop that could result in an ignition source inside the fuel tank.Repair and overhaul of FQIS in-tank wire harness must be in accordance with SWPM20-14-12.Installation of FQIS in-tank wire harness must be in accordance with Boeing AMM 28-41-09.Verify the following when installing sparpenetrations in accordance with Boeing AMM28-41-09:1. A new O-ring is installed in the groove of the FQIS wire bundle connectors.2. The spar connector and the mating surface are clean3. The connector jamnut is tightened to a torque of 200-250 inch-pounds.Verify the following when installing the applicableairplane wire bundle connector to the in-tankwire harness spar penetration:1. The coupling connector is tightened to a torque of 60-70 inch-pounds.2. The between the bonding jumper on the airplane wire bundle and the airplane sparstructure is not more than 0.0005 ohm (0.5 milliohms) for HST tank and 0.010 ohm(10 milliohms) for all other tanks.28-AWL-16 CDCCL N/AALL Fuel Tank Access Doors ConfigurationConcern: Potential for arcing or sparking inside the tank at the interface between the door andthe tank structure as a result of a direct strike or conducting currents through the wing skin.The following must be maintained during fuel tank access door installation (Boeing AMM28-11-02, 28-11-03):NOTE: Not applicable to center wing tank access door.1. Verify presence of a molded rubber seal positioned around the outermost periphery of thedoor that mates with the wing skin inside the tank.2. Apply Corrosion Inhibiting Compound (CIC) toboth sides of the knitted aluminum meshgasket, and3. Install the knitted aluminum mesh gasket between the outside face of the door and thewing skin to establish the electrical conductivity between the access door and thewing skin.AWL Number Task Interval ApplicabilityDescriptionJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3728-AWL-17 ALI 18 monthsALL Fault Current Detector for CWT and Inboard Main Tank Override/Jettison Pumps andHST Transfer Fuel PumpsConcern: Potential burn through of pump case in the event of electrical ground fault infuel pumps.Verify the following in accordance with Boeing AMM 28-31-14 for CWT and inboard main tankpumps, 28-17-14 for HST transfer pumps.The ground fault detector for each pump is working properly.Use Fault Current Detector Test as specified in AMM.28-AWL-18 CDCCL N/AALL Fault Current Detectors Repair CMMConcern: Potential for maintenance error during Fault Current Detector repair. Fault currentmay be introduced to pumps creating an ignition source.Repair and overhaul of Fault Current Detectors must be in accordance withAutronics (V03972)CMM28-31-22 Revision 4, or later revisions ofthis CMM that have been approved by the FAAOversight Office.28-AWL-19 CDCCL N/AALLResetting Tripped Fuel Pump Circuit Breakers or Ground Fault Interrupters (GFIs)Concern: Potential for arcing or sparking inside the tank between fuel pumps and fuel pumphousings and outside the tank between pumpwiring and structure inflammability leakagezones.Verify it is safe to reset the circuit breaker(s) or GFI(s) by following the applicable OEMtroubleshooting procedures. Fault(s) that resultedin circuit breaker orGFI(s) relay trip mustbe isolated and corrected prior to reset.AWL Number Task Interval ApplicabilityDescriptionJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-38747-400 MAINTENANCE PLANNING DATA28-AWL-20 CDCCL N/A 747-400 airplanesLine Numbers 1284and on;or airplanes thathave incorporatedService Bulletin747-28A2239 or747-28A2245.Lightning Protection – Engine Fuel Feed Line Fuel Tank PenetrationConcern: Potential for arcing, sparking or filament heating inside the tank at the interfacebetween the bulkhead fitting and the spar during a lightning strike event.The following must be maintained in accordance with Boeing AMM 28-22-07 if the bulkheadfitting or attached tubing are removed and replaced (Note: Each of the following is onlyapplicable if the subject area has been disturbed):Verify electrical fay surfacebond between the bulkhead fittingand the front spar structureinside the tank must be 0.0005 ohms (0.5 milliohms) or less.Install full-bodied fillet seal encapsulating the bulkhead fitting tothe tank wall interface insidethe tank.Install full-bodied fillet sealencapsulating the first coupling interface inside the tank.Verify an electrostatic bonding jumper presencebetween the structure and the first tube matingwith the bulkhead fitting inside the tank.Verify the electrical bond fromstructure to first tube mating with the bulkhead fitting is0.010 ohm (10 milliohms) or less.28-AWL-21 Reserved for future SFAR 88 AWL.AWL Number Task Interval Applicability DescriptionJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-3928-AWL-22 CDCCL N/AALL AC Fuel Pump Fault Current Bonding PathConcern: Potential for fault current path through the pump housing to structure inside the tank.Electrical faults internal to the fuel pump motor impeller are by design routed through the motorimpeller assembly to the bonding jumpers on thefront face of the motor impeller assembly tostructure outside the tank. The bonding jumpers ensure that fault currents are conducted tostructure outside the tank until the circuit breaker and/or GFI has had time to remove powerfrom the pump.The following features must be maintained during pump replacement in accordance withBoeing AMM 28-22-03:For Hydro-Aire Pumps:1. The presence of two bonding jumpers.2. The motor impeller bonding resistance across the jumpers to structure for Center tank isnot more than 0.0002 ohms(0.2 milliohms). The motor impeller bonding resistanceacross the jumpers to structure for horizontalstabilizer tank pumpsand main tank boostpumps is not more than 0.0004 ohms (0.4 milliohms).For FR-HITEMP Pumps:1. The presence of one bonding jumper.2. The motor impeller bonding resistance across the jumpers to structure for Center tank isnot more than 0.0002ohms (0.2 milliohms).3. The motor impeller bonding resistance across the jumpers to structure for main tankboost pumps is not more than0.0005 ohms (0.5 milliohms).AWL Number Task Interval ApplicabilityDescriptionJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-40747-400 MAINTENANCE PLANNING DATA28-AWL-23 CDCCL N/A 747-400 airplanesLine Numbers 1368and on;or airplanes thathave incorporatedService Bulletin747-28A2266 and(if applicable)747-28A2267.Fuel Quantity Indicating System (FQIS) – Installation of Center and HST Fuel Tank Hot ShortProtector (HSP)Concern: Potential for wire to wire hot short voltages on the center tank fuel quantitydensitometer wiring to enter the fuel tank. This is applicable toairplanes with optionaldensitometer installed.The FQIS HSP is designed to prevent wire to wire external hot short voltages from entering thefuel tank where it may cause an ignition.The following features must be maintained duringreplacement of the HSP in accordance withBoeing AMM 28-41-24:1. Verify the bonding jumpers are installed in accordance with the AMM task.2. Verify the bonds from the HSP to stiffeners where the bonding jumpers are terminatedare equal to or less than0.0025 ohms (2.5 milliohms).3. A new unit must be used.The Hot Short Protector unit is not repairable.28-AWL-24 ALI 1 YR 747-400 airplanesLine Numbers 1343and on with HSTinstalled;or airplanes thathave incorporatedService Bulletin747-28A2262.Horizontal Stabilizer FuelBoost Pump Automatic Shutoff System (If Installed)Concern: Dry running the horizontal stabilizer tank fuel pumps has the potential for singlefailure ignition sources developing at the pump inlet due to either frictional heating or sparkingas a result of FOD contacting the pump rotating elements, rotating elements contactingstationary parts, or hot journal bearings due to bearing contamination or failure.The automatic shutoff system is installed and designed to limit continuousdry running conditionto 15 seconds.The following test is required in order to protect against latent faults:Functionally check the horizontalstabilizer tank fuel boost pump automatic shutoff system inaccordance with Boeing AMM 28-17-00.AWL Number Task Interval ApplicabilityDescriptionJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4128-AWL-25 CDCCL NA 747-400 airplanesLine Numbers 1378and on;or airplanes thathave incorporatedService Bulletin747-28A2291.Reserve Tank Fueling Valve-Induced Lightning Protection BondConcern: Potential for arcing or filament heating inside the center Left/Right wing Reservefuel tank.The following design features must be maintained in accordance with Boeing AMM 28-21-02when the reserve tank fueling valve controller is removed and replaced:1. Two bonding jumpers between the valve controller and structure outside the tank.2. The bonding resistance from the mounting bolt to structure (spar) must not be more than0.0015 ohms (1.5 milliohms).28-AWL-26 ALI 1 YR 747-400 airplanesLine Numbers 1380and on;or airplanes thathave incorporatedService Bulletin747-28A2280.Main Tank 2 and Main Tank 3 Override/Jettison Fuel Pump Uncommanded on SystemConcern: Dry running the main 2 and main 3 tank fuel override/jettison pumps has the potentialfor single failure ignition sources developing at the pump inlet due to either frictional heating orsparking as a result of FOD contacting the pump rotating elements, rotating elementscontacting stationary parts, or hot journal bearings due to bearing contamination or failure.Perform an operational test of the main2 and main 3 override/jettison fuel pumpuncommanded on system in accordance with Boeing AMM 28-31-00.AWL Number Task Interval Applicability DescriptionJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-42747-400 MAINTENANCE PLANNING DATA28-AWL-27 CDCCL NA 747-400 airplanesLine Numbers 1382and on;or airplanes thathave incorporatedService Bulletin747-28A2292 and747-28A2294.Fault Current Protection - Motor Operated Valve (MOV) ActuatorConcern: Potential for arcing or sparking inside the fuel tank at a conductive metal-to-groundstructure interface as a result of electrical fault current event.The following design features must be maintained in accordance with Boeing AMMs:28-14-21, 28-14-31, 28-14-41, 28-14-61, 28-16-01, 28-16-04, 28-17-01, 28-21-11, 28-22-01,28-22-02, 28-25-02, 28-31-04, and 28-31-05.I. If the MOV actuator is mounted to the spar with an adapter plate.1. Maintain the following if the adapter plate is removed and replaced:a. Verify electrical fay surface bond resistancebetween the adapter plate and the spar is0.0005 ohms (0.5milliohms) or less.b. Install fay surface seal between the adapter plate and the spar outside the tank.c. Cap seal the four bolts that attach the adapter plate to the spar inside the tank and filletseal around the edge of the hole and on the stationary part of the adapter plate insidethe tank.d. Install sealed electrical fay surface bond and fay surface seal between the serratedmating surfaces of the index plate and the adapter plate.e. Install sealed electrical fay surface bond and fay surface seal between the matingsurfaces of the actuator and the index plate.f. With the bonding jumper not installed, verify electrical bonding resistance between theactuator mounting feet and the spar is 0.0025 ohms(2.5 milliohms) or less.g. Prior to attachment of the bonding jumper to the actuator, verify electrical bondingresistance between the loose end of the bonding jumper and the spar is 0.0015 ohms(1.5 milliohms) or less.h. Attach the bonding jumper to the actuatorbonding tab using a sealed electrical faysurface bond.(Continued on next page)AWL Number Task Interval Applicability DescriptionJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4328-AWL-27 CDCCL NA 747-400 airplanesLine Numbers 1382and on;or airplanes thathave incorporatedService Bulletin747-28A2292 and747-28A2294.Fault Current Protection - Motor Operated Valve (MOV) Actuator (continued):2. Maintain the following if the index plate is removed and replaced:a. Install sealed electrical fay surface bond and fay surface seal between the serratedmating surfaces of the indexplate and the adapter plate.b. Install sealed electrical fay surface bond and fay surface seal between the matingsurfaces of the actuator and the index plate.c. With the bonding jumper not installed, verify electrical bonding resistance between theactuator mounting feet and the spar is 0.0025 ohms(2.5 milliohms) or less.d. Prior to attachment of the bonding jumper to the actuator, verify electrical bondingresistance between the loose end of the bonding jumper and the spar is 0.0015 ohms(1.5 milliohms) or less.e. Attach the bonding jumper to the actuatorbonding tab using a sealed electrical faysurface bond.3. Maintain the following If the MOV actuator is removed and replaced:a. Install sealed electrical fay surface bond and fay surface seal between the matingsurfaces of the actuator and the index plate.b. With the bonding jumper not installed, verify electrical bonding resistance between theactuator mounting feet and the spar is 0.0025 ohms(2.5 milliohms) or less.c. Prior to attachment of the bonding jumper to the actuator, verify electrical bondingresistance between the loose end of the bonding jumper and the spar is 0.0015 ohms(1.5 milliohms) or less,d. Attach the bonding jumper to the actuatorbonding tab using a sealed electrical faysurface bond.(Continued on next page)AWL Number Task Interval Applicability DescriptionJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-44747-400 MAINTENANCE PLANNING DATA28-AWL-27,ContinuedCDCCL NA 747-400 airplanesLine Numbers 1382and on;or airplanes thathave incorporatedService Bulletin747-28A2292 and747-28A2294.Fault Current Protection - Motor Operated Valve (MOV) Actuator (continued):II. If the MOV actuator is mounted without an adapter plate.1. Maintain the following If the MOV actuator is removed and replaced:a. Install sealed electrical fay surface bond between the mating surfaces of the actuatorand structure.b. With the bonding jumper not installed, verify electrical bonding resistance between theactuator mounting feet and the spar is 0.005 ohms (5 milliohms) or less.c. Prior to attachment of the bonding jumper to the actuator, verify electrical bondingresistance between the loose end of the bonding jumper and the spar is0.0015 ohms (1.5milliohms) or less,d. Attach the bonding jumper to the actuatorbonding tab using a sealed electrical faysurface bond.28-AWL-28 ALI 1 YR 747-400 airplanesLine Number 1394and on;or airplanes thathave incorporatedService Bulletin747-28A2261.Main Fuel Tank Boost Fuel Pump GroundFault Interruption (GFI) Control Relay SystemConcern: GFI is installed to protect against burn-through of the pump housing, and to protectagainst overheating of the pump cavity and/or auto ignition temperature on the outside surfaceof the housing, due to electrical arcing.Perform an Operational Test of all Main Fuel Tank Boost PumpsGFI Control relays inaccordance with Boeing AMM 28-22-00.28-AWL-29 ALI 1 YR 747-400 airplaneswith Electric CenterWing Tank ScavengeSystems, airplanesprior to Line Number972 that haveincorporatedService Bulletin747-28A2261.Center Wing Tank Electrical Scavenge Pump Ground Fault Interruption (GFI) Control RelaySystemConcern: GFI is installed to protect against burn-through of the pump housing, and to protectagainst overheating of the pump cavity and/or auto ignition temperature on the outside surfaceof the housing, due to electrical arcing.Perform an Operational Test ofall center wing tank scavengesystem GFI Control relays inaccordance with Boeing AMM 28-22-00.AWL Number Task Interval ApplicabilityDescriptionJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4528-AWL-30 CDCCL NA 747-400 (910K)with AuxiliaryFuel TankElectronic Fuel Level IndicationSystem (EFLI) – Out Of Tank Wiring Installation SeparationRequirementConcern: Potential for hot shorts and EMI induced voltages on the EFLI wiring outside of thetank to enter the fuel tank.Routing and installation of any new wiring must use wire types BMS 13-48, BMS 13-60 orBMS 13-58, and not be within a 2-inch radius ofthe EFLI wiring. When a single clamp fails, aseparation greater than 1⁄2 inch must be maintained from AUX Fuel tank EFLI wiring.28-AWL-31 CDCCL NA 747-400 (910K)with AuxiliaryFuel TankElectronic Fuel Level Indication System (EFLI) Processor Display Unit (PDU) or AUX tankEFLI – RepairConcern: Potential for maintenance error during PDU repair. The PDU AUX tank EFLI isdesigned to limit the levels of energy, voltage, current, and power allowed within the EFLIcircuit to intrinsically safe levels in order to preclude the potential of an ignition source within afuel tank.Repair and overhaul of PDU must be in accordance with Parker (V26055) CMM 28-41-81,Revision 0, or later revisions of this CMMthat have been approved by the FAA OversightOffice.28-AWL-32 CDCCL NA 747-400 (910K)with AuxiliaryFuel TankFuel Tank Electronic Fuel Level IndicationSystem (EFLI) – Repair of In-Tank HardwareConcern: Potential for maintenance error during repair of in-tank hardware. Arc gaps maydevelop that could result in an ignition source inside the fuel tank.EFLI probe repair and overhaul must be in accordance with Parker (V26055) CMM 28-41-70,Revision 1, or later revisions that have been approved by the FAA Oversight Office.28-AWL-33 ALI 12 YR All airplanes thathave incorporatedService Bulletins747-57A2327and 747-28A2324Teflon Sleeving – Out-of-Tank Wire BundleConcern: Potential for hot short induced voltages on out-of-tank spar wire bundle to enter thefuel tank due to chafing.Perform a visual (detailed) inspection and verify the following to ensure the integrity of the wirebundle Teflon sleeving:1. Teflon sleeving are installed around wire bundle in clamp locations specified in ServiceBulletins 747-57A2327 and 747-28A2324.2. Teflon sleeves are not damaged.3. Clamps are not missing or damaged.AWL Number Task Interval Applicability DescriptionJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-46747-400 MAINTENANCE PLANNING DATA28-AWL-34 CDCCL N/A All airplanes thathave incorporatedService Bulletins747-57A2327and 747-28A2324Teflon Sleeving – Out-of-Tank Wire BundleConcern: Potential for hot short induced voltages on out-of-tank spar wire bundle to enter thefuel tank due to chafing.The following design features must be verifiedwhen the out-of-tank spar wire bundle isremoved or replaced, in order to ensure the integrity of the wire bundle Teflon sleeving:1. The Teflon sleeving is installed around the wiring in the clamp locations specified inService Bulletins 747-57A2327 and 747-28A2324.2. Sleeving is not damaged.28-AWL-35 CDCCL N/A All airplanes thathave incorporatedService Bulletin747-28A2306Fuel Boost Pump Wires In Conduit Installation – In Fuel TankConcern: Potential for the boost pump wiring to chafe and arc to the conduit resulting in anignition source in the fuel tank. The boost pump wires that are in the conduits in the fuel tankshave incorporated a conduit liner and a Teflon sleeve to protect from wire chafing. The wiringalso has a shield (grounded at both ends) that ismonitored by the GFI for an additional layer ofprotection for a pump power wire short within the conduit.The following design features must be verified when the pump wiring or the wiring in theconduit is removed or replaced (refer to Boeing AMM 28-22-06):1. Jacketed and shielded (grounded at both ends) wiring is installed.2. A Teflon sleeve is installed.3. A Conduit Liner is installed.NOTE: The above requirement applies to the following Fuel Boost Pumps:Main Tank No.1 FWD Fuel Boost PumpMain Tank No. 1 AFT Fuel Boost PumpMain Tank No. 4 FWD Fuel Boost PumpMain Tank No. 4 AFT Fuel Boost Pump.AWL Number Task Interval ApplicabilityDescriptionJUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-4728-AWL-36 CDCCL N/A All airplanes thathave incorporatedService Bulletin747-28A2204 buthave notincorporatedService Bulletin747-28A2306Fuel Boost Pump Wires in Conduit Installation – In Fuel TankConcern: Potential for the boost pump wiring to chafe and arc to the conduit resulting in anignition source in the fuel tank.The following design features must be verified when the pump wiring or wiring in the conduit isremoved or replaced (refer to Boeing AMM 28-22-06):1. A Wiring Jacket and Teflon sleeve, PartNumber TFE 2X, are present and not chafed.NOTE: The Teflon sleeve is not repairable.NOTE: The above requirement applies to the following Fuel Boost Pumps:Main Tank No.1 FWD Fuel Boost PumpMain Tank No. 1 AFT Fuel Boost PumpMain Tank No. 4 FWD Fuel Boost PumpMain Tank No. 4 AFT Fuel Boost Pump28-AWL-37 CDCCL N/A ALL Lightning, Fault Current or Hot Short Protection Features – In Tank Sealant RequirementsConcern: Potential for arcing or sparking inside the tank at a conductive metal-to-groundstructure interface as a result of electrical fault currents or lightning strike events due toinsufficient bonding within the ground electricalpath. Sealant damage or lack of properadhesion could affect the fueltank ignition prevention features.If any maintenance, preventive maintenance, or alteration is performed inside the fuel tanks,verify the following in the affected areas (including the touchpoints during transit to and fromthe tank access point) where work is performed (refer to Boeing AMM 28-11-00):1. Fillet seals around the periphery of the equipment interfacewith structure inside the tankare not damaged such as peeling off or cracking.2. Cap seals installed on fasteners and fittings inside the tank are not damaged such aspeeling off or cracking.NOTE: Not all fasteners and fittings have cap seals. If fastener or fitting sealant isdamaged, there will be residual evidence of a previously installed cap seal on fasteners andfittings in areas where installation is required. In addition, all tank structural repairs andalterations require cap seals in accordance with AWL 28-AWL-07.AWL Number Task Interval Applicability DescriptionJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-48747-400 MAINTENANCE PLANNING DATAB.2 IMPACT-RESISTANT FUEL TANK ACCESS DOORSINTRODUCTIONThe 747 Fuel Tank Access Doors are compliant with FAA Title 14 CFR § 25.963. Specifically, the 747 Impact-Resistant Access Doors meet Title 14 CFR§ 25.963(e)(1) which requires that all covers located in an areawhere experience or analysis indicates a strike is likely mustbe shown by analysis or teststo minimize penetration and deformation bytire fragments, low energy engine debris,or other likely debris. All 747-400 airplanes were delivered withimpact-resistant access doorsexcept for two locations retrofitted by Service Bulletin 747-28-2236. The following stencil, “IMPACT-RESISTANT DOOR”, isalso required on each door. Additionally, the adjacent lower wingsurface is stenciled “CAUTION: INSTALL ONLY IMPACT-RESISTANTDOOR AT THISLOCATION”.Boeing chose to use a CDCCL for the AWL of the Impact-Resistant Fuel Tank Access Doors. CDCCLs are commonly used and understoodby operatorsto define a design feature that must be maintained throughout the life of the airplane.AWLNUMBER TASK INTERVAL APPLICABILITY DESCRIPTION57-AWL-01 CDCCL N/A ALL Impact-Resistant Fuel Tank Access DoorsConcern: A potential exists for non-impact-resistant doors to be installed in locations thatrequire impact-resistant doors. A high energyimpact on a non-impact-resistant Fuel TankAccess Door may cause a fuel leak, and in the presence of an ignition source, may result in acatastrophic fire.Immediately prior to the installation of eachof the Fuel Tank Access Doors 544AB, 644AB,545AB, 645AB, 545BB, 645BB, 546AB, 646AB, 546BB, 646BB, 552AB, 652AB, 552BB,652BB, 552CB, 652CB, 552DB, 652DB, 552EB, 652EB, perform the following:1. Verify that the Fuel Tank Access Door isimpact-resistant. Impact-resistant doors have asmooth inner surface. Doors with visible machined stiffening ribs on the inner surface arenot impact-resistant (refer to Boeing AMM 28-11-02).JUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-49B.3 NITROGEN GENERATION SYSTEM (NGS)The following list of AWLs (ALIs and CDCCLs)contains FAA approved scheduled inspections for operators to incorporate into their maintenance programfor this type design to meet the requirements for the introduction of the Flammability Rule Reduction Means (FRM) Nitrogen Generation System (NGS).The FAA operational rulechange E8-16084 Final Flammability Rule requires maintenance instructionsand control limitations forcertain NGS criticaldesign configurations. Title 14 CFR § 25.981(d) also requires AWLs to preclude ignition sources inside the fuel tank that maybe introduced by theaddition of NGS.E8-16084, Final Flammability Rule, Paragraph III(F), Section 7,Identification of AirworthinessLimitations: Paragraph M25.4(a)requires that if the FRM isused to comply with Paragraph M25.1, AWLs must be identified for all maintenance or inspection tasks required to identify failures of components withinthe FRM that are needed to meet Paragraph M25.1. NGS AWLs aremandatory maintenance actions that ensure that unsafe conditionsthat arise due toNGS failures do not occur or are not introduced into the airplane as a result of configuration changes, repairs, alterations, or deficiencies in the NGSmaintenance program throughout the operational life of the airplane.JUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-50747-400 MAINTENANCE PLANNING DATAAWLs – NITROGEN GENERATION SYSTEMAWLNUMBER TASK INTERVAL APPLICABILITYDESCRIPTION47-AWL-01 CDCCL N/A 747-400 airplaneLine Numbers 1363through 1419 or747-400 LineNumbers 1362 andprior that haveincorporated all or partof Service Bulletin747-47-2006Lightning Protection – NGS NEA Description Line Fuel Tank PenetrationConcern: Potential for arcing, sparking of filament heating inside the tank at the interfacebetween the bulkhead fitting and the spar during a lightning strike event.The following must be maintained if the bulkhead fitting or attached tubing are removed andreplaced, or reinstalled (refer to Boeing AMM 47-21-06):1. Install the same part number bulkhead fitting.2. Verify electrical fay surface bond between the bulkhead fitting and the front sparstructure inside the tank is 0.0005 ohms (0.5 milliohms) or less,3. Install full-bodied fillet seal encapsulating the bulkhead fitting and jam nut on bothinside and outside surfaces of the front spar, and the first coupling connecting the tubeto the bulkhead fitting inside the tank,4. Install full-bodied fillet seal encapsulating the first coupling interface inside the tank,and5. Verify electrical bond from structure to first tube mating with the bulkhead fitting is0.010 ohms or less.Note: The bulkhead fitting is a special part which has an integral flame arrestor. Anychanges to this part require approval by the FAA Oversight Office.JUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5147-AWL-02 CDCCL N/A 747-400 airplanesthat haveincorporatedService Bulletin747-47-2006Nitrogen Generation System (NGS) – Flammability Exposure and PerformanceConcern: Airplane alterations may impact the performance of the NGS and hence theflammability of the Center Wing Fuel Tank.Background: The NGS is designed to provide the proper level of nitrogen to the centerwing tank in order to reducethe flammability exposure byreducing the oxygen content ofthe ullage. The flammability exposure is also affected bythe temperature ofthe fuel. Thefollowing are critical features of the airplanethat, if altered, cannegatively affect theperformance of the NGS whichin turn may increase the center fuel tankflammabilityexposure beyond the limits ofTitle 14 CFR § 25.981 at Amendment 25-125, utilizing theequivalent level of safety finding described in FAA Memorandum PS05-0177-P-2.1. Transferring air (20.9% oxygen) to the center fuel tank will dilute the nitrogen richatmosphere created by the NGS in the fuel tank. Some Auxiliary Fuel Tank installationstransfer air to the center wing tank as part of venting and fuel transfer.2. NGS performance depends on bleed air pressure in the bleed air cross-over manifoldsupplied by the engines.3. Certification of theNGS depends on the inherent flammability of the center fuel tankwithout NGS installed. Center tank flammability is a direct function of fuel tanktemperature. Any heat sources around the tank, heat sources introduced into the tank(such as warm fuel or new heat exchangers),or changes that would cause heat to beretained (such installation of blankets adjacent to tank walls) could affect fuel tankflammability in anegativemanner.CDCCL: Any design change that affects the vent system by adding air to the center tank,reduces the bleed pressure in the cross-over manifold during any phase of flight orground operations, or adds any heat to the center wing fuel tank or increases heatretention of the center wing fuel tank is not allowed without an FAA approved analysis toshow that the change, or combination of changes, does not affect the NGS performanceper the requirements of Title 14 CFR § 25.981(b), Amendment 25-125 utilizing theequivalent level of safety finding described in FAA Memorandum PS05-0177-P-2See Boeing AMM Chapter 28 for a description of the Fuel System. See Boeing AMMChapter 47 for a description of the NGS.AWLNUMBER TASK INTERVAL APPLICABILITY DESCRIPTIONJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-52747-400 MAINTENANCE PLANNING DATA47-AWL-03DELETEDALI1200 FlightHours747-400 airplaneLine Numbers 1363,1366Nitrogen Generation System – Functional Check Performance InspectionConcern: Latent failure of the Hollow FiberMembranes that make up the Air SeparationModules (ASMs) will reduce the percentage of nitrogen in the nitrogen enrichedair enteringthe center wing fuel tank.Perform the inspection procedure listed in Boeing AMM 47-00-01.1. Measure the oxygen concentration of the NEA at the output of the ASM per BoeingAMM 47-00-01.2. Verify the NEA purity is in the satisfactory zone (shaded area) of the ASMperformance charts published in Boeing AMM 47-00-01.If the nitrogen content is not satisfactory, troubleshoot per Boeing Fault Isolation Manual andperform the recommended repairs per Boeing AMM 47-00-01.47-AWL-04DELETEDALI9675 FlightHours747-400 airplaneLine Numbers 1363,1366Nitrogen Generation System – Thermal Switch Functional and Operational TestConcern: Latent failure of the Thermal Switchremoves a layer of protection against fuel tankignition by hot bleed air.The NGS uses engine bleed air from the bleed system cross-over manifold to generatenitrogen to reduce theflammability of thecenter fuel tank. The NGS has features to preventdirectly feeding hot bleed air into the fueltank. The Thermal Switch provides a redundantbackup to the NGS controller to protect the ASMs and prevent hot bleed air from entering thefuel tank. The Thermal Switch backup feature is a latent (not detected) failure and must betested to maintain certification of the NGS.Perform a functional and operational test of the thermal switch per Boeing AMM 47-43-02 toensure the integrity of the thermal switch.47-AWL-05DELETEDALI1500 Cyclesor 7500Flight HoursNote747-400 airplaneLine Numbers 1363,1366Nitrogen Generation System – Thermal Control Unit (TCU) and Interconnect DuctReplacement/UpgradeConcern: The TCU pallet failed vibration testing during qualification. The interconnect ductvibration analysis demonstrates limited life capability. The TCU andinterconnect duct mayfail in service if not replaced or upgraded.Replace the TCU Assembly P/N 5848740-1 orDuct Assembly P/N 5849522-1 (componentof TCU)Replace the interconnect duct P/N 5849599-1.Interval Note: Whichever comes first.AWLNUMBER TASK INTERVAL APPLICABILITY DESCRIPTIONOCT 2011747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-5347-AWL-06DELETEDALI3000 Cyclesor 15000Flight HoursNote747-400 airplaneLine Numbers 1363,1366Nitrogen Generation System – Air Separation Unit (ASU) Replacement/UpgradeConcern: The ASU pallet failed vibration testing during qualification. The ASU may fail in service if notreplaced or upgraded.Replace ASU Assembly P/N 5848760-1 or the following combination of ASU components:- Overtemperature Shutoff Valve Bracket P/N 5849542-41- Nitrogen Enriched Air Bracket P/N 5849542-25- Two ASM Inlet Ducts P/N 5849548-1 (oneon the primary ASM and one on the adjacentsecondary ASM)- Supply Air Primary Duct Assembly P/N 5849557-1.Interval Note: Whichever comes first.47-AWL-07 ALI 21,250 FlightHours747-400 airplanes thathave incorporatedService Bulletin747-47-2006Nitrogen Generation System – Nitrogen Enriched Air (NEA) Distribution Ducting InspectionConcern: The NEA Distribution System ducting outside the fuel tank may fail latently allowing NEA toleak without reaching the fuel tank, resulting inthe fuel tank not reaching required inert levels.Inspect the NEA distribution lines from the ASM tothe fuel tank front spar for damage and leaks.47-AWL-08 ALI 21,250 FlightHours747-400 airplanes thathave incorporatedService Bulletin747-47-2006Nitrogen Generation System – Cross-Vent Check Valve – Functional CheckConcern: The Cross-Vent Check Valve may fail openlatently allowing air to flow through the centertank diluting the nitrogen rich environment created by the Nitrogen Generation System.Functionally check the Cross-Vent Check Valveby accessing the Center Wing Tank to remove andinspect the Cross-Vent Check Valve.47-AWL-09 CDCCL N/A 747-400 airplanes thathave incorporatedService Bulletin747-47-2006Industry Fleet Average Flammability ExposureConcern: NGS performance is dependent on industry descent times. Industry efforts to reduce descenttime may result in NGS performancethat does not meet FAA requirements.Fleet Average flammability exposure for the fuel tanks with flammability reduction of this airplane typemust be maintained in accordance with Title 14 CFR Part 25, Appendix M. Boeing will monitor U.S.descent statistics and, if necessary to maintain compliance, will publish service information. If Boeingpublishes such service information, this CDCCL requires that operators either implement these FAAapproved design changes or that operators implementother design changes or operational proceduralchanges approved by the FAA Oversight Office tomaintain compliance with Title 14 CFR Part 25,Appendix M.NOTE: This CDCCL does not require individual operators to monitor descent rates of their fleets.Boeing will monitor U.S. descent statistics and provide any needed service instructions to operators.To prevent increasing flammability exposure abovepermissible levels, this CDCCL requires operatorsto incorporate future Boeing published service instructions denoted to maintain compliance with thisCDCCL, or other approved actions, within the compliance times stated in the service instructions.AWLNUMBER TASK INTERVAL APPLICABILITY DESCRIPTIONJUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-54747-400 MAINTENANCE PLANNING DATANOTE: SHADED AWLs HAVE BEEN DELETED.47-AWL-10 ALI 54,000 FH 747-400 airplanes thathave incorporatedService Bulletin747-47-2006NGS – Thermal Switch Functional CheckConcern: Latent failure of the Thermal Switch removes a layer of protection against fuel tank ignition byhot bleed air.The NGS uses engine bleed air from the bleed system cross-over manifold to generate nitrogen toreduce the flammability of the centerfuel tank. The NGS has featuresto prevent directly feeding hotbleed air into the fuel tank. The Thermal Switch provides a redundant backup to the NGS controller toprotect the Air Separation Modules (ASMs) and prevent hot bleed air from entering the fuel tank. TheThermal Switch backup feature is a latent (not detected) failure.Remove and replace the NGS Thermal Switch with a new unit.(Refer to Boeing AMM 47-42-04 for removal and installation).AWLNUMBER TASK INTERVAL APPLICABILITYDESCRIPTIONOCT 2011747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-55C. AWLs – STRUCTURAL INSPECTIONSThe 747-400 passenger airplane can be operated in a 747-400 Special Freighter (SF) configuration if modified in accordance withspecific Boeing servicebulletins. These service bulletins are identified (with associated effectivity) in Boeing Service Bulletin 747-00-2004. Airplanes converted by incorporationof Boeing service bulletin(s) to the 747-400 SF configuration require existing supplemental structural inspections identified for the 747-400, and newsupplemental structural inspections specific to the 747-400SF configuration. For the 747-400SF configuration, all of these supplemental inspections areshown in the 747 Supplemental StructuralInspection Document D6-35022, beginning withRevision G (and on) of that document.After reaching the threshold specified in the 747 Supplemental Structural Inspection Document, D6-35022, 747-400SF aircraft modified as notedabove must limit all repeat intervals in MPD Section 2, Structural Maintenance Program, to the values shown therein.Airplanes converted to a 747-400 Large Cargo Freighter (LCF) configuration by incorporation of Boeing Service Bulletins 747-00-0008, 747-00-0018,747-00-0033, or 747-00-2120require additional supplemental structural inspections specific to the 747-400LCF configuration.These supplementalinspections are shown in the 747-400 LCF Supplemental Structural Inspection Document– Appendix A, D6-35022-1, dated January 2010, or later FAAapproved revision. For these supplemental fatigue related inspections, after theairplane reaches the threshold specified in D6-35022-1, issuedJanuary 2010, or later FAA approved revision, the repeat intervals of the C-Checks and D-Checks specified by the MPD must be limited by flight cycles inaddition to the required limitation for flight hours and calendartime. For MRBR Section 3, Structural Maintenance Program, and MRBR Section 4, ZonalMaintenance Program, the check intervals must not exceed the following:C-Check – 1,500 flight cycles2C-Check – 3,000 flight cyclesD-Check – 6,000 flight cycles2D-Check – 12,000 flight cyclesAircraft converted to the 747-400 LCF configuration also require the revised inspection and modification requirements listed inBoeing Service Bulletin747-53A2817 Rev. 00, or a later revision approved by the Manager of the FAA Oversight Office, in order to adequately address differences in aircraftstructure and internal loads/stresses. WhenBoeing Service Bulletin 747-53A2817 statesto contact the Boeing Company for modification data, thatmodification data must be approved by the manager of the FAA Oversight Office.JUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-56747-400 MAINTENANCE PLANNING DATAC.1 LIMIT OF VALIDITY (LOV)This section provides the Limit of Validity (LOV) in accordance with the requirements ofTitle 14 CFR § 26.21 (Amendment 26-6).This regulation requiresthe establishment of an airplane level limit of validity of the engineering data that supports the structural maintenance program that corresponds to theperiod of time, stated as a number of total accumulated flightcycles or flight hours or both,during which itis demonstratedthat widespread fatigue damagewill not occur in the airplane. The LOVs listed in the following table support operator compliance with Title 14 CFR § 121.1115and § 129.115 for the747-400s.LIMIT OF VALIDITY FOR THE 747-400MODEL FLIGHT CYCLE LOV FLIGHT HOUR LOV747-400, 747-400D, 747-400F,747-400SF(BCF), 747-400LCF35,000 165,000JUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-57D. CERTIFICATION MAINTENANCE REQUIREMENTS (CMRs)SELECTION OF CMRsIn order to grant operators of the 747-400 airplane an opportunity to participate in the evaluation and selection of CMRs in anintegrated process with MRBtasks and intervals, a Certification Maintenance Coordination Committee (CMCC) was convened to review all of the 747-400 CMRs.The CMRs listed inthis document are the result of applying the CMCC process as described in AC 25-19.CMR DEFINITIONAs defined by AC 25-19, a CMR is a required periodic task, established during the design certification of the airplane as an operating limitation of the typecertificate. CMRs usually result froma formal, numerical analysis conducted to show compliance with catastrophic and hazardous failure conditions.Additional notes concerning the definition of CMRs:1. A CMR is intended to detect safety-significant latent (hidden) failures that would, in combination with one or more specificfailures or events, result in ahazardous or catastrophic failure condition.2. It is important to note that CMRs are derived from a fundamentally different analysis process than the maintenance tasks andintervals thatresult fromthe Maintenance Steering Group (MSG-3) Analysis associated withMaintenance Review Board (MRB) activities. MSG-3 Analysis activity producesmaintenance tasks that are performed for safety, operational, or economic reasons, involving both preventative maintenance tasks, which are performedbefore failure occurs (andare intended to prevent failures), as well as failure-finding tasks.CMRs, on the other hand, are failure-finding tasks only, andexist solely to limit the exposure to otherwise hidden failures. Although CMR Tasks are failure-finding tasks, use of potential failure-finding tasks, suchas functional checks and inspections, may also be appropriate.3. CMRs are designed to verify that a certain failure has or has not occurred, and donotprovide any preventative maintenance function. CMRs “restartthe failure clock to zero” for latent failures by verifyingthat the item has not failed, or cause repair if it has failed. Because the exposure time to a latentfailure is a key element in the calculationsused in a safety analysis performed to show compliance with Title 14 CFR § 25.1309, limiting the exposuretime will have a significant effect on theresultant overall failure probability of the system. The CMR task interval should be designated in terms of flighthours, cycles, or calendar time, as appropriate.JUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-58747-400 MAINTENANCE PLANNING DATA4. The type certification process assumes that the airplanewill be maintained in a conditionof airworthiness at least equal toits certified or properly alteredcondition. The process described in AC 25-19 is not intended toestablish normal maintenance tasks that should be defined through the MSG-3analysis process. Also, this process is not intended to establish CMRs for the purpose of providing supplemental margins of safety for concerns arisinglate in the type design approval process.5. CMRs should not be confused with required structural inspection programs that are developedby the type certificate applicantto meet the inspectionrequirements for damage tolerance, as required by Title 14 CFR § 25.571 or § 25.1529, Appendix H25.4 (Airworthiness Limitationssection). CMRs areto be developed and administered separately from any structural inspection programs.EXCEPTIONAL SHORT-TERM EXTENSIONS FOR CMRsSince CMR intervals are based on statistical averages and reliability rates, an exceptional short-term extension of 90 days forCMRs 24, 25, and 26 listedin this document may be made without jeopardizing safety. The local regulatory authority or a Principle Maintenance Inspectormust concur with anyexceptional short-term extensions before they take place using procedures established with the local regulatory authority in the operators’ manuals. The“exceptional short-term extension” process is applicable to CMRintervals. It should not be confused with the operator’s “short-term escalation” programfor normal maintenance tasks described in the operators’ manuals and in the Flight Standards Handbook 8900.1 FSIMS.The FAA Oversight Office has accepted that these exceptional short-term extensions may be granted without consultation with that office:1. The term “exceptional short-term extension” is defined as an increase in a CMR interval that may be needed to cover an uncontrollable or unexpectedsituation. CMRs 24, 25, and 26 listed inthis document have been approved with an exceptional short-term extension of 90 days.2. Repeated use of extensions, either on the same airplane or onsimilar airplanes in an operator’s fleet, should not be used asa substitute for goodmanagement practices. Exceptionalshort-term extensions must not beused for fleet CMR extensions.3. After a CMR has experienced anexceptional short-term extension,the CMR interval will revert back to its interval listed inthis document. The FAAOversight 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 United States FAA jurisdictiononly. Operators who are notunder the U.S. FAA jurisdiction should obtain intervalextension approvals from their local regulatory agency.JUN 2014747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-59POST-CERTIFICATION CHANGES TO CMRSAny post certification changes to CMRs should be reviewed by the 747-400 CMCCand approved by the FAA Oversight Office:1. Since the purpose of a CMR is to limit the exposure time to agiven significant latent failure as part of an engineering analysis of overall system reliability,instances of a CMR task repeatedly finding that no failure hasoccurred may not be sufficient justification for deleting the task.2. The introduction of a new CMR should be reviewed by the sameprocess used during initial certification. It is important thatoperators be afforded thesame opportunity to participate that they received during theoriginal certificationof the airplane, in order to allow the operators to manage their ownmaintenance programs.3. In the event that later data provide sufficient basis for relaxation of a CMR (less restrictive actions to be required), thechange may be documented by anFAA Oversight Office approved change to this CMR document.4. If the requirements of an existing CMR must be decreased (more restrictiveactions to be performed), it will be implemented by a change to this CMRdocument and enforced by an FAA Airworthiness Directive (AD).5. After initial aircraft certification, the only basis for addinga new CMR is in association with the certification of designchanges.6. A new CMR created as part of a design change should be partof the approved data for that change and added to this CMR document.In the event that a CMR is revised, Boeing will document it by preparing a revision to this document that will be approved by the FAA Oversight Office.This revision will then beforwarded to all 747-400 operators and the FAA Oversight Office.JUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-60747-400 MAINTENANCE PLANNING DATACMR TASKSNUMBER SYSTEM INTERVAL TASKPROCEDUREREFERENCEMPDITEMNUMBER1 Standby Power System Daily Operational (Short) Test – 115-Volt AC StandbyPower GenerationMaintenance ManualD633U101Subject 24-29-00Page Block 50024-029-012 Cargo, Engine and APU Fire/OverheatDetection System.(Only applicable to Engine Fire/OverheatDetection System for 747-400 LCF)Daily Operational Test forFire/Overheat DetectionSystemsMaintenance ManualD633U101Subject 26-10-00Page Block 50026-010-003 FADEC C2Failures2000 FH(GE CF6-80C2B1F)1000 FH(PW4000)560 FH(RR RB211-524)Check Engine Control System for Category 2Faults using the CMCMaintenance ManualD633U101Subject 73-21-00Page Block 20073-121-0073-221-0073-321-034 Generator Control Unit and Bus Control Unit 500 FH Operational Test - Generator and Bus Control Units Maintenance ManualD633U101Subject 24-23-01Page Block 50024-023-015 Lavatory Waste Compartment1000 FH Lavatory WasteCompartment Inspection Check Maintenance ManualD633U101Subject 25-41-00Page Block 60025-040-01AUG 2012747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-616 E&E Cooling SystemOverride ModeFunction1000 FH(Not Applicableto 747-400F or747-400SF)20,000 FH(Applicable to747-400F and747-400SF)Override Mode – Operational Test Maintenance ManualD633U101Subject 21-58-00Page Block 50021-058-037 High Lift Control SystemA. Trailing Edge Electric ControlB. Leading Edge Electric Control1200 FH1200 FHPrimary Electric Operational Test of LE and TEFlap Systems.Maintenance ManualD633U101Subject 27-51-11Page Block 50027-081-018 High Lift Control SystemA. Alternate Arm SwitchB. Alternate Control1200 FH10,000 FHAlternate Electrical Operational Test of LE andTE Flap System.Maintenance ManualD633U101Subject 27-51-11Page Block 50027-051-019 E&E Cooling SystemFlow Detectors(Not Applicable to 747-400F or 747-400SF)2000 FH Remove Clean and Install Low Flow Detectors. Maintenance ManualD633U101Subject 21-58-00Page Block 20021-058-2210 E&E Cooling System Smoke & FlowDetection(Not Applicable to 747-400F or 747-400SF)2000 FH Equipment Cooling Detector Ground Test Maintenance ManualD633U101Subject 21-058-00Page Block 50021-058-0411 E&E Cooling System E30-2 Shelf 2000FH System Test-E30 Rack Pressure(Equipment Cooling System)Maintenance ManualD633U101Subject 21-58-00Page Block 50021-058-1612 E&E Cooling SystemFans & Bypass Valve(Not applicable to 747-400F or 747-400SF)2000 FH Fan and Bypass Valve Operational Test(Normal Mode)Maintenance ManualD633U101Subject 21-58-00Page Block 50021-058-01NUMBER SYSTEM INTERVAL TASKPROCEDUREREFERENCEMPDITEMNUMBERAPR 2008D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-62747-400 MAINTENANCE PLANNING DATA13 E&E Cooling SystemFan Check Valves(Not Applicable to 747-400F or 747-400SF)6250 FH Check Valve – Detail Visual Inspection Maintenance ManualD633U101Subject 21-58-03Page Block 60021-058-2314 E&E Cooling System Clean Mode(Not Applicable to 747-400F or 747-400SF)6250 FH Clean Cycle – Operational Test (EquipmentCooling Card CMC initiated BIT)Maintenance ManualD633U101Subject 21-58-00Page Block 50021-058-0215 E6/E9 Equipment Cooling Valve(Not applicable to 747-400F, 747-400SF or747-400 LCF)6250 FH Cargo Fire Switch Test Maintenance ManualD633U101Subject 21-58-00Page Block 50021-058-1916 Horizontal Stabilizer Fuel Tank Installation(Only applicable to 747-400’s equipped withhorizontal stabilizer fuel capability.)(Not applicable to 747-400 LCF)6250 FH Inspection of Horizontal Stabilizer BondingJumpers (Applicable only to airplanes withhorizontal stabilizer fuelquantity gageand controlson Fuel Control Panel)Maintenance ManualD633U101Subject 55-10-04Page Block 60055-010-0417 Upper Rudder System 6250 FH Test Upper Rudder Hinge Bearing and RudderPower Control Package Bearing PlayMaintenance ManualD633U101Subject 27-21-02Page Block 60027-021-02NUMBER SYSTEM INTERVAL TASKPROCEDUREREFERENCEMPDITEMNUMBERAPR 2008747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-6318 Main Entry Door Escape System (NotApplicable to 747-400F,747-400SF or Door #5 on Combi Airplanesin Cargo Mode. See Note (1).(Only applicable to Door #1 L/H for747-400 LCF)30 months/36 months -See Note (2)Main Entry Door Escape System Functional CheckNote (1): On Combi airplanes, the check is alsorequired on Door #5 immediately after conversionto passenger modeNote (2): The reference functional checkprocedure covering examination of the escapeslide or slide/raft packs, may be accomplished at30 month intervals, (the remainder of the procedureat 36 month intervals)Service LetterSL-747-SL52-44Maintenance ManualD633U101Subject 52-11-07Page Block 600 -Para 2Emergency LinkageInspectionMaintenance ManualD633U101Subject 52-11-07Page Block 600 -Emergency LinkageInspection - Para 2.Examine the escapeslide or slide/raft pack.52-011-1819 Engine Strut Spring Beam 12500 FH Spring Beam Bearing Movement Check Maintenance ManualD633U101Subject 54-51-03Page Block 60054-051-0320 Lower Lobe Cargo CompartmentConditioned Air System (Non-Standard, ifinstalled)(Not Applicable to 747-400F, 747-400SF or747-400 LCF)7400 FH Check for Air Conditioning Pack Number 3 FlowControl Valve High Flow Disable with Lower LobeCargo Compartment Conditioned Air OnMaintenance ManualD633U101Subject 21-28-00Page Block 50021-028-0021Engine Position 2 Turbine OverspeedSystem (RR RB211-524 series engines)Note: For RB 211 powered 747-400’sequipped with EICAS version RR004, CMRNo. 21 is not applicable.DELETED150 FHInterrogate CMC fault history (ATA 73) and look forCMCS message 72663 Turbine OverspeedDisabled. If found, do fault isolation per 71 CMCSmessage index.Maintenance ManualD633U101Subject 45-71-00Page Block 201NUMBERSYSTEMINTERVALTASKPROCEDUREREFERENCEMPDITEMNUMBERAPR 2008D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-64747-400 MAINTENANCE PLANNING DATA22Engine Oil Servicing (P&W 4000)DELETEDEvery 12 quartsaddedDrain residual oil from gearbox.Maintenance ManualD633U101Subject 12-13-03Page Block 30023 Combi Main Deck Fire Protection SystemZones D and E Air Distribution ShutoffValves, V532 and V533.(Not applicable to 747-400 LCF)6250 FH Main Deck Air Distribution Flapper ValveAdjustment/Test.Maintenance ManualD633U101Subject 26-24-05Page Block 50026-024-1024 Flight Deck Security Doors Installed perService Bulletin 747-25-3302(Not applicable to 747-400 LCF)9 Years Discard the Adams Rite strike mechanism. Maintenance ManualD633U101Subject 52-51-02Page Block 40052-051-0825 Flight Deck Security Doors Installed perService Bulletin 747-25-3306 and/or747-25-3312.(Not applicable to 747-400 LCF)9 Years Discard the Adams Rite strike mechanism. Maintenance ManualD633U101Subject 52-51-02Page Block 40052-051-0826 Flight Deck Security Doors Installedbeginning at the line number 1320 and on(except freighter models).(Not applicable to 747-400 LCF)9 Years Discard the Adams Rite strike mechanism. Maintenance ManualD633U101Subject 52-51-02Page Block 40052-051-0827 Fuel main tanks 1 & 4 and fuel reserve tanks2 & 3 VTO secondary shut-off system(Applicable to 747-400 LCF only)15000 FH Functional Check of the fuel main tanks 1 & 4 andfuel reserve tanks 2 & 3 VTO secondary shut-offsystem.Maintenance ManualD633U101Subject 28-21-00Page Block 50028-021-09NOTE: SHADED CMRs HAVE BEEN DELETED.NUMBER SYSTEM INTERVAL TASKPROCEDUREREFERENCEMPDITEMNUMBERAPR 2008747-400 MAINTENANCE PLANNING DATAD621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-65E. REPORTING UNCONTROLLABLE HIGH THRUST FAILURE CONDITIONSTitle 14 CFR § 121.703 and § 135.415 state that “each certificate holder shall report any failure, malfunction, or defect in anaircraft, system, component,or powerplant that occurs or is detected at any time if, inits opinion, that failure, malfunction, or defect has endangered ormay endanger the safeoperation of an aircraft”. Title 14 CFR § 125.409 also requiresreporting of failures, malfunctions or defects. In many casesa reportable failure ormalfunction will be obvious, butthere are some failure modes related to uncontrolled high thrustthat are reportable but may not be obvious. The followinginformation is provided, as required by FAA Exemption No. 8518, toassist the operators in identifying reportable malfunctionsrelated to uncontrolledhigh thrust.The FAA has concluded that the loss of capability to control thrust dueto a failure of the enginethrust control system may endanger the aircraft. Thisincludes any malfunctions having one ormore of the following characteristics:• Auto-acceleration or uncommanded thrust change to higher power• Stuck thrust lever above idle power• Inability to reduce thrustAlthough some of these incidents may not appear to be safety related, documenting the events is important to ensure the presentlevel of safety ismaintained and/or to identify failureconditions that must be corrected.When filing a report of such an event with the FAA, the operatoris requested to include in the description of the event one ormore of the followingphrases:• “thrust control”• “no response to thrust lever”• “auto-acceleration”• “uncontrolled high thrust”JUN 2014D621U400-9BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 9.0-66747-400 MAINTENANCE PLANNING DATAIn addition, the following information should be included in the report:• Event description• Flight Crew action• Maintenance action• List of affected or removed componentsReports should be submitted to the local representative of the FAA Administrator that handles the appropriate reporting responsibility for Title 14 CFR§ 121.703, § 125.409, and § 135.415. In addition to filing reports with the FAA, it is recommended that a copy be sent to Boeingand to the enginemanufacturer.JUN 2014