747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-1747-8/8FAIRWORTHINESS LIMITATIONS (AWLs)D011U721-02-01SEPTEMBER 2015This document has EAR data with an Export Control Classification Number (ECCN) of 9E991.Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used fordevelopment, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws.Boeing claims copyright in each page of thisdocument on to the extent that the pagecontains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collectivework. This document includes proprietary information owned by the Boeing Company and/or one or more third parties. Treatment ofthe document and the information it contains is governed by contract withBoeing. For more information, contact the Boeing Company, P.O.Box 3707, Seattle WA 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, BBJ, DC-8,DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the red-white-blue Boeing livery are all trademarks owned by The Boeing Company; no trademark license is granted in connection with thisdocument unless provided in writing by Boeing.COMPILED AND PUBLISHED BY:MAINTENANCE PROGRAMS ENGINEERINGCOMMERCIAL AVIATION SERVICESBOEING COMMERCIAL AIRPLANE GROUPSEATTLE, WASHINGTONSEP 2015D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-2747-8/8F AIRWORTHINESS LIMITATIONSTHIS PAGE INTENTIONALLY LEFT BLANKBLANK747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-3TABLE OF CONTENTSREVISIONS .................................................................................................................................................................................................................................. 1.0-4LIST OF EFFECTIVE PAGES ...................................................................................................................................................................................................... 1.0-7A. SCOPE..................................................................................................................................................................................................................................... 1.0-8B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS....................................................................................................................................... 1.0-9C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE-LIFEPARTS ............................................................................................................................ 1.0-108D. AIRWORTHINESS LIMITATIONS – SYSTEMS LIFE-LIMITED PARTS ...............................................................................................................................1.0-110E. AIRWORTHINESS LIMITATIONS – SYSTEMS ....................................................................................................................................................................1.0-111MAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-4747-8/8F AIRWORTHINESS LIMITATIONSREVISIONSREVISION AND REVISIONDESCRIPTION FAA APPROVALAUGUST 2011Original ReleaseApproved by: Robert D. Breneman(Seattle FAA ACO)SIGNATURE ON FILE8/12/2011SEPTEMBER 2011Revised seven model references of either "747-8" or "747-8F" to"747-8/8F" in the document to be consistent with the model applicability of747-8/8F.Deleted “(Section 9)” from Item 1 in the Removal of Excess Sealant When Inspecting section because it is no longer applicable in thisstatement.Revised the systems life-limited part applicability in the Applicability Specifications column of the table in Section D from "Applicable to all747-8F and 747-8I Airplanes" to "Applicable to all 747-8 and 747-8F Airplanes”.Approved by: Gary Oltman(Seattle FAA ACO)SIGNATURE ON FILE12/06/2011DECEMBER 2011Revised the Systems Life-Limited Parts Table in Section D by removing the 5 year life limit ofthe Inboard Aileron Power Control Unit (PCU)1579100-7. This revision is based on ST-TSR-272 Rev F, 11/08/2011 Qualification Report for 747-8Inboard Aileron PCU Assy andCertification Plan #11624, Revision B: Certification of 747-8/747-8FInboard Aileron PCU - Elimination of Life Limit.Approved by: Gary Oltman(Seattle FAA BASOO)SIGNATURE ON FILE2/22/2012APRIL 2012Revised the table of Supplemental Structural Inspection Requirements by addingSSI Numbers 57-20-W11 R3 and 54-50-002d R3.Approved by: Angelos Xidias(Seattle FAA BASOO)SIGNATURE ON FILE4/11/2012JULY 2012Revised the fuel tank sealant removal and restoration reference for fuel tank inspectionin Item 3, General Notes by replacingthe reference toMPD Section 9 with a reference to the 747-8 Special Compliance Items/Airworthiness Limitations Document, D011U721-02-04.Revised Section D, Airworthiness Limitations – Systems Life-limited Parts, by revising the life limit flight cycles for the Engine Primary ExhaustNozzle from 2,800 to 9,000flight cycles, from 1,200 to 4,650flight cycles for the Engine Primary Exhaust Forward Plug, and 1,900 to 4,300flight cycles for the Engine Primary Exhaust Aft Plug.Revised the title of System Airworthiness Limitation Number 2 inSection E by deleting the word"Center", as this limitation also pertains to theleft and right inboard main fuel tanks.Approved by: Gary Oltman(Seattle FAA BASOO)SIGNATURE ON FILE7/24/2012SEP 2015747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-5JANUARY 2013Revised Section D, Airworthiness Limitations -Systems Life Limited Parts deleting item 8.Deleted Ram Air Turbine Pump life limit on the basis of the completion of the certification endurance testing of this item.Revised the Notes section in the AWL Structural Inspection Requirements Table in Section B by changing AMM 54-05-03-212-829 to AMM54-05-03-211-801 and AMM 54-05-03-212-832 to AMM 54-05-03-211-802.Approved by: Gary Oltman(Seattle FAA BASOO)SIGNATURE ON FILE2/28/2013JULY 2013Revised Section E – Systems AirworthinessLimitation 2 toadd flight cycle data inaccordance with Regulatory Docket Number FAA-2010-1268 Exemption Number 10267B.SIGNATURE ON FILEFAA BASOO11/19/2013NOVEMBER 2013Revised Section B. Airworthiness Limitations - Structural Inspections by adding SSI Number 54-50-003 Forward Engine Mount AWL forUltrasonic Inspection of Barrel Nuts for cracked nutsin accordance with Boeing Service Bulletin 747-71A2329.Revised Section D, Airworthiness Limitations- Systems Life Limited Parts Table by revising the Life Limit for the Nozzle and Forward Plug,adding Note 1 regarding installation of Item 5, adding Item Number 6 Assy - AftPlug, Primary Exhaust030-22229-3, and renumbering theremaining table items accordingly.Revised Section E - Airworthiness Limitations - Systems by adding System Airworthiness Limitation No. 5 ENGINE OPERATINGLIMITATIONS FOR ICE CRYSTAL ICING.SIGNATURE ON FILEFAA BASOO12/04/2013JANUARY 2014The Applicability Specifications statement for Item Numbers 1 and 2 in Section D, ‘AIRWORTHINESS LIMITATIONS – SYSTEMS LIFELIMITED PARTS’ was revised to delete any reference to airplane linenumber. The AWL of 5000 flightcycles is applicable to the734-19150-09 and 734-19150-10 Hydraulic Control Modules (HCM) regardless ofwhich line number airplane they are installed on. The 5000 flight cycleAWL for the HCMs was included in the original release of this document, but was subsequently revised in error to include a reference 'prior toL/N 1467' in the Applicability Specifications column. This line number reference has now been deleted.Added the following footnote for clarification of Items 3, 4, and 6: “Published life limits are applicable to primary exhaust assemblies installedon all 747-8F or 747-8 airplanes with any of the certified GEnx-2B67 engine models identified in FAA Type Certificate Data Sheet No.A20WE”.SIGNATURE ON FILEFAA BASOO2/03/2014APRIL 2014Revised Section A to define “FAA Oversight Office” and replacedall references to "Seattle FAA ACO” with "FAA Oversight Office"throughoutthe entire document.Deleted AWL 54-50-003 implemented in theNOV 2013 revision that required UT inspection of Forward Engine Mount Barrel NutSL4081C14SP1 per Service Bulletin 747-71A2329.Added AWL 54-50-003c applicable to production airplanes with Barrel Nut SL4750NA, and all airplanes that have accomplished ServiceBulletin 747-71-2332, which replacedBarrel Nut SL4081C14SP1 with SL4750NA.SIGNATURE ON FILEFAA BASOO5/14/2014REVISION AND REVISIONDESCRIPTIONFAA APPROVALSEP 2015D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-6747-8/8F AIRWORTHINESS LIMITATIONSMAY 2014References to FAA regulations were changed to “Title 14 CFR"throughout the document to accurately reflect FAA regulation citations.Revised terminology in Section A, Scope, by adding “or alteration” to instructions regardingrepairs and added additional Title14 CFRreferences to Item 2.The following changes were made to Section B, Airworthiness Limitations – Structural Inspections:Added fatigue based supplemental inspections to meet the requirements of Title 14 CFR § 25.571. Also added a list of baseline programintervals and other related information applicable to certain Structures and Zonal Tasks that havereached the implementation threshold. Withthis, the operational limit has been raisedto the inspection threshold values until required NDI inspection procedures are validated, publishedin the appropriate manual, and accepted by the FAA.Added a new subsection of information for Post-Threshold Intervals for Structures and Zonal Tasks, including a table of AirworthinessLimitations – Structural Inspection Thresholds.Revised the instructions for removing excess sealant and added the Excess Sealant Table for Structural Significant Items (SSIs)requiringfastener cap, fillet or brush sealant.Revised the figure references in Section C from “Figure 1” to “Figure 3” because of the two new figures added to Section B.SIGNATURE ON FILEFAA BASOO7/14/2014JULY 2014The following changes were made to the Airworthiness Limitations – Structural Inspections Threshold Table:Added “All except L/N 1505” in the Notes column for SSI No. 53-00-F64A for clarification.Added SSI No. 53-00-F64A.1 for L/N 1505 only.SIGNATURE ON FILEFAA BASOO9/16/2014OCTOBER 2014Deleted the Boeing submittal signature columnfrom the Revision Log to improve the layout and provide consistency across all Section9/AWL/CMR/SCI documents. A submittal signature will no longer beincluded in the revision log; only the FAA BASOO approval date willbe shown.Revised the compliance date for System Airworthiness Limitationnumber 2, item 4 from December 31, 2016 to September 30, 2017regarding implementation of a flight crewindication of gross fuel contamination.Revised System Airworthiness Limitation 5 to delete the word "rigid" in reference to the kind of borescope to be used for the HPC Stage 1blade airfoils inspection.Added System Airworthiness Limitation 6 in reference to flight-deck annunciation modification regarding operation of the enginevariablebleed valve ice protection system.SIGNATURE ON FILEFAA BASOO11/12/2014SEPTEMBER 2015Deleted three conditions from the A. SCOPE front matter regarding exceptions to the FAA Oversight Office's approval requirementofalternate inspections for modified or repaired structure wherestandard configuration airworthiness limitation inspections cannot be performed.Revised Notes column for SSIs 53-00-F64A and 53-00-F64A.1 to include L/N 1526.SIGNATURE ON FILEFAA BASOO9/24/2015REVISION AND REVISIONDESCRIPTIONFAA APPROVALSEP 2015Section Page Date Section Page Date Section Page Date Section Page Date Section Page DateD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-7LIST OF EFFECTIVE PAGES747-8/8F AIRWORTHINESS LIMITATIONS1.0 1 SEP 20151.0 2 BLANK1.0 3 MAY 20141.0 4 SEP 20151.0 5 SEP 20151.0 6 SEP 20151.0 7 SEP 20151.0 8 SEP 20151.0 9 MAY 20141.0 10 MAY 20141.0 11 MAY 20141.0 12 MAY 20141.0 13 MAY 20141.0 14 MAY 20141.0 15 MAY 20141.0 16 MAY 20141.0 17 MAY 20141.0 18 MAY 20141.0 19 MAY 20141.0 20 MAY 20141.0 21 MAY 20141.0 22 MAY 20141.0 23 MAY 20141.0 24 MAY 20141.0 25 MAY 20141.0 26 MAY 20141.0 27 MAY 20141.0 28 MAY 20141.0 29 MAY 20141.0 30 MAY 20141.0 31 MAY 20141.0 32 MAY 20141.0 33 MAY 20141.0 34 MAY 20141.0 35 MAY 20141.0 36 MAY 20141.0 37 MAY 20141.0 38 MAY 20141.0 39 MAY 20141.0 40 MAY 20141.0 41 MAY 20141.0 42 MAY 20141.0 43 MAY 20141.0 44 MAY 20141.0 45 MAY 20141.0 46 MAY 20141.0 47 MAY 20141.0 48 MAY 20141.0 49 MAY 20141.0 50 MAY 20141.0 51 MAY 20141.0 52 MAY 20141.0 53 MAY 20141.0 54 MAY 20141.0 55 MAY 20141.0 56 MAY 20141.0 57 MAY 20141.0 58 MAY 20141.0 59 MAY 20141.0 60 MAY 20141.0 61 MAY 20141.0 62 MAY 20141.0 63 MAY 20141.0 64 MAY 20141.0 65 MAY 20141.0 66 MAY 20141.0 67 MAY 20141.0 68 MAY 20141.0 69 MAY 20141.0 70 MAY 20141.0 71 MAY 20141.0 72 MAY 20141.0 73 MAY 20141.0 74 MAY 20141.0 75 MAY 20141.0 76 MAY 20141.0 77 MAY 20141.0 78 MAY 20141.0 79 MAY 20141.0 80 MAY 20141.0 81 MAY 20141.0 82 SEP 20151.0 83 MAY 20141.0 84 MAY 20141.0 85 MAY 20141.0 86 MAY 20141.0 87 MAY 20141.0 88 MAY 20141.0 89 MAY 20141.0 90 MAY 20141.0 91 MAY 20141.0 92 MAY 20141.0 93 MAY 20141.0 94 MAY 20141.0 95 MAY 20141.0 96 MAY 20141.0 97 MAY 20141.0 98 MAY 20141.0 99 MAY 20141.0 100 MAY 20141.0 101 MAY 20141.0 102 MAY 20141.0 103 MAY 20141.0 104 MAY 20141.0 105 MAY 20141.0 106 MAY 20141.0 107 MAY 20141.0 108 MAY 20141.0 109 MAY 20141.0 110 APR 20141.0 111 MAY 20141.0 112 JUL 20131.0 113 OCT 20141.0 114 MAY 20141.0 115 OCT 20141.0 116 BLANKSEP 2015D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-8747-8/8F AIRWORTHINESS LIMITATIONSA. SCOPEThe scheduled maintenance requirements described in this document result from Model 747-8/8F airplane certification activitieswith the U.S. FederalAviation Administration (FAA). Accordingly, this FAA approved Airworthiness Limitations document D011U721-02-01 is cross-referenced in the Model747-8/8F Type Certificate Data Sheet.These maintenance actions are mandatory.This Airworthiness Limitations Document D011U721-02-01 is FAA approved and specifies maintenance required under Title 14 Code of FederalRegulations (Title 14 CFR) § 43.16 and § 91.403, unless an alternative program has been FAA Oversight Office approved.Where used in this document, the term “FAAOversight Office” is defined as the FAA office that currentlyhas oversight responsibility for the type certificateof the Boeing model 747-8/8F. At the timeof publication, the FAA office with oversight responsibility for the type certificate of the 747-8/8F is the FAA BoeingAviation Safety Oversight Office (BASOO).AIRWORTHINESS LIMITATIONS– STRUCTURAL INSPECTIONSThe Airworthiness Limitations may only be revised with the approval of the FAA Oversight Office.If the inspections cannot beaccomplished due to repairsand/or alterations, an alternate inspection approved by the FAA Oversight Office must be used.SEP 2015747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-9B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONSINTRODUCTIONThe Structural Inspection Program and the Zonal Inspection Program approved in the 747-8/8F Maintenance Review Board Report (MRBR) D011U721-01and contained in the 747-8/8F MaintenancePlanning Document (MPD) D011U721-02, describe an initial baseline Structural Maintenance Program for allStructurally Significant Items (SSIs). These programs were developed in accordance with the guidelines of MSG-3, Revision 2007.1, and partially satisfythe requirements of Title 14 CFR § 25.571 by providing accidental and environmental damage detection opportunity for all SSIs,and in some cases, fatiguedamage detection opportunity. The supplemental structural inspections listed in the Airworthiness Limitations are for those SSIs that do not receiveadequate fatigue damage detection opportunity from the initial baseline structural andzonal programs that are listed in the 747-8/8F MPD. Thesupplemental inspections shown in this Airworthiness Limitations document are to be accomplished in addition to the baseline program.The Supplemental Structural Inspection Program (SSIP) uses theDTR system to determine the inspections (and repeat intervals) necessary to provideadequate fatigue damage detection. The DTR system defines a requiredDTR (a numerical value) that must be achieved for each SSI. DTR Check Formswhich define the inspection options and the required DTR are contained in Document D011U721-05. At least one form is shown foreach SSI.THRESHOLD (747-8/8F AIRPLANES)The fatigue inspection requirements apply after the accumulationof a certain number of flightsand/or hours (threshold). Theinitial fatigue inspections mustbe accomplished prior to the flight cycle and/or flight hour threshold listed,whichever comes first. The threshold for each of the 747-8/8F aircraft fatigueinspections are defined in the Airworthiness Limitations – Structural Inspections Threshold Table. No airplane may be operatedbeyond the threshold (oroperational limit) statedin the Airworthiness Limitations – Structural Inspections Threshold Table until any required NDI inspection procedures are validated,published in the appropriate manual, and accepted by the FAA.MAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-10747-8/8F AIRWORTHINESS LIMITATIONSSince Boeing will not have the DTR Check Forms and inspection procedures published at the time of theissuance of the Amended Type Certificate (ATC),the FAA has agreed to the following three-staged approach. Thisapproach will substitute a Temporary Operational Limitation inlieu of an InspectionThreshold until the damage tolerance procedures are completely published atthe end of Stage 3. Thisapproach is illustrated for the 747-8/8F in thetable below:The Airworthiness Limitations listed in this AWL document coverstructure for which the requiredDTR is not met by the baselinestructural or zonalinspections of the 747-8/8F MPD. Any continued escalation beyond the MPD baseline Structures and Zonal Programs may result in additional structure notmeeting the required DTR which is the basisof certification and thus must be de-escalated to the MPD baseline Structures and Zonal intervals at Thresholdand beyond.Stage Description Published Completion Date Details of Publication ThresholdTemporary OperationalLimit1 Baseline Inspection ProgramData published. (Complete)Prior to issuance of the747-8/8F ATC.MPD Structures and ZonalProgram at time of certificationNot Applicable Three years from delivery,or 7,500 total flight cycles,whichever comes first.2 Supplemental structuralfatigue inspection thresholdsand DTR Check Formspublished.(Complete)Three years or 7,500 total flightcycles from issuance of 747-8FATC, whichever comes first.Thresholds and DTR CheckForms for all PSEs / InspectionMethods (visual, HFEC, LFEC,UT, etc.) identified.Thresholds are tabulated foreach PSE requiringsupplemental inspection.No airplane may beoperated beyond thethreshold (or operationallimit) stated in theAirworthiness Limitations –Structural InspectionsThreshold Table until anyrequired NDI inspectionprocedures are validated,published in theappropriate manual, andaccepted by the FAA.3 NDT Manual Procedurespublished.To Be Determined (TBD), prior toStage 2 operational limit.NDT Manual: Inspectionprocedure details (includinginspection equipment, standards,probes, etc.) are developed anddocumented and are available tothe operators.Same as Stage 2. None.MAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-11In addition to the threshold described above, a calendar threshold of 20 years applies unless an initial inspection of an FAA approved Corrosion Preventionand Control Program (CPCP) has occurred, constituting CPCP implementation. The CPCP identifiedwithin the Structural Maintenance Program of the 747Maintenance Review Board Report (D011U721-01) is FAA approved.The Airworthiness Limitations – StructuralInspections Threshold Table defines the Inspection Implementation Threshold for the747-8/8F. Items that aresensitive to flight length are identifiedby "FLS" or flight hoursper cycle utilization of the airplane (e.g., "< 7 hrs", ">=7 hrs", etc.) in the Threshold column ofthis table. These Flight Length Sensitive (FLS) Items requireboth flight hours and flight cycles to determine the Implementation Threshold.Refer to theAirworthiness Limitations – Structural Inspections Threshold Table,Figure 1, or Figure 2, as indicated, to determine the threshold for these FLS Items.Initial inspections (thresholds) and intervals are measured in flight cycles or flight hours that a particular SSI detail has accumulated regardless of what theairframe as a whole has accumulated. Most SSI details have neverbeen replaced and therefore haveaccumulated the same flight cycles and flight hours asthe airframe. Some SSI details are replaced,such as when installing Removable Structural Components(repairable/rotable/expendables) or installing usedstructural parts as a repair. In these cases, the SSI details have accumulated flight cycles andflight hours that may be different than the airframe. Theoperator must account for this in determining when inspections must be done.REPORTING RESULTS OFSTRUCTURAL INSPECTIONSAll cracks found during these inspections shall be reported within ten (10) days directly to the Manager of the FAA Oversight Office, the Transport AirplaneDirectorate, the FAA, and to the Boeing Commercial Airplane Group using the Discrepant Structure Report Form. Refer to Document D011U721-05 for therequired report form (any suitable alternative which contains the same information may be used).MAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-12747-8/8F AIRWORTHINESS LIMITATIONSUSE OF THE FLS THRESHOLD CURVE (747-8/8F)For FLS Items only, all non-FLS SSIs have thresholds as listed inthe Airworthiness Limitations – Structural Inspections Threshold Table.1. Determine the FLS status and threshold from the Threshold column in the Airworthiness Limitations – Structural Inspections Threshold Table.2. Determine the total number of flight cycles and flight hours experienced by the SSI.3. If the threshold is defined by Figure 1 or 2, locate the intersection (point) of the Flight Hours and Flight Cycles in the appropriate figure as defined in theThreshold column in the Airworthiness Limitations – Structural Inspections Threshold Table.4. If the point determined by Step 3 lies below the Threshold Curves (in either Figure 1 or Figure 2 as defined by the Airworthiness Limitations – StructuralInspections Threshold Table), then the SSI has not reached theInspection Implementation Threshold. If the point determined byStep 3 is on, above, tothe right, or outside the Threshold Curve for the SSI, thenthe Inspection Implementation Threshold has been reached.MAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-13REPEAT INSPECTION INTERVALA Repeat Interval for the Fatigue Inspectionof an SSI is established from its respective DTR Check Form. The DTR Check Forms are the result of theDamage Tolerance assessment/evaluation documented during certification of the airplane. Revisions to the required DTR Check Form or the DTR Curve isnot allowed without the prior approval from the FAA Oversight Office.If the Threshold box for the item includes an “FLS” designation,the average airplane hours per flight should be calculated forthe airplane and the repeatinspection interval should be based on the DTR Check Form with the corresponding“hrs” utilization in theModel-Series field, if applicable. If the currentaverage hours per flight is longer than the prior average hours per flight, the current average hours per flight should be usedfor determining which DTRCheck Form should be utilized and theinspection performed within the current interval since the last inspection.POST-THRESHOLD INTERVALS FOR STRUCTURES AND ZONAL TASKSThe Post-Threshold Intervals Table was created to provide operators with the intervals for selected zonal and structures tasksthat must be used upon theairplane reaching the de-escalation threshold in order to ensure the maintenance program complies with the damage tolerance requirements for the747-8/8F aircraft. The baseline Structures and Zonal Program Tasks included in the Post-Threshold Intervals Table provide credit towards theTitle 14 CFR § 25.571 damage tolerance evaluation. As such, whenreaching the de-escalation threshold listed for a given inspection, the repeat interval forthat inspection must be the lesser of:• that published in the Structural and Zonal Inspection Requirementsin the FAA approved 747-8/8F MRBR at the time threshold isreached.• that shown in the Post-Threshold Intervals Table, which represents baseline maintenance intervalsat the time of certification.This means that any operator, who may have escalated these Structures or Zonal Program tasks by changing task intervals, must reduce the repeatfrequencies as defined above once the threshold listed in the Post-Threshold Intervals Table is reached. For FLS items, the de-escalation threshold mayalso be defined by the same Figure 1 or 2,as noted, that is used to define thresholds in the Airworthiness Limitations – Structural Inspections ThresholdTable as discussed.MAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-14747-8/8F AIRWORTHINESS LIMITATIONSAirplane applicability is listed as shown below:• 747-8 = All 747-8 Passenger Airplanes, including the 747-8 Intercontinental and 747-8 VIP• 747-8F = All 747-8 Freighter AirplanesPOST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8F52-410-00Nose Cargo DoorINTERNAL – DETAILED: Nose Cargo DoorDetailed Inspection of the nose cargo door internal structure toinclude:Frames.Stop beams.Ribs, stiffeners & intercostal.Skins.Stop fittings.Stop pins.Latch fittings support structure.Hinge fittings and support structure.Hinge beam from BS 234 to BS 280.Linear actuator support structure.Tension beam attachment to BS 234 frame.Frame inner chord from stringer S-6 to S-14A.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect with doorlinings and insulation blanketsremoved.INTERNAL – DETAILEDN/A20,000 FC6 YR7200 FCSee Note (2)MAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-1552-415-00Forward Lower LobeCargo CompartmentDoorINTERNAL – DETAILED: Forward Lower Lobe Cargo CompartmentDoorDetailed Inspection of the forward lower lobe cargo compartmentdoor internal structure to include:FramesStiffeners and intercostalsSkinsLatch cam fittings support structureDoor hinge, intermediate hinges and support structureINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect with doorlining removed and rain baffleremoved for access to door frame at hinge with door open.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)52-420-00Aft Lower LobeCargo CompartmentDoorINTERNAL – DETAILED: Aft LowerLobe Cargo Compartment DoorDetailed Inspection of the aft lower lobe cargo compartment doorinternal structure to include:FramesStiffeners and intercostalsSkinsLatch cam fittings support structureDoor hinge, intermediate hinges and support structureINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect with doorlining removed and rain baffleremoved for access to door frame at hinge with door open.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)52-425-00Bulk CargoCompartment DoorINTERNAL – DETAILED: Bulk Cargo Compartment DoorDetailed Inspection of the bulk cargo compartment door internalstructure to include:FramesStop beamsStiffeners and intercostalsSkinsINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect withdoor linings removed.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-16747-8/8F AIRWORTHINESS LIMITATIONS52-430-00Main and UpperDeck Entry DoorsINTERNAL – DETAILED: Main and Upper Deck Entry DoorsDetailed Inspection of main deck entry & upper deck doors internalstructure to include:FramesStop beamsStiffeners and intercostalsSkinsUpper and lower gatesINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect withdoor linings removed.INTERNAL – DETAILED20,000 FCN/A6 YR7200 FCSee Note (2)52-435-00Main Deck EntryDoor StopsEXTERNAL – DETAILED: Main Deck Entry Door StopsDetailed Inspection of main deck entry door stops to include:Stop fittingsStop pinsINTERVAL NOTE: Whichever comes first.EXTERNAL – DETAILED20,000 FC20,000 FC2 YR2400 FCSee Note (2)52-440-00Main DeckSide CargoCompartment DoorINTERNAL – DETAILED: Main Deck Side Cargo Compartment DoorDetailed Inspection of the main deck side cargo compartment doorinternal structure to include:FramesStiffeners and intercostalsSkinsDoor hinge and support structureINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect with door linings removed and rain baffleremoved for access to door frame at hinge with door open.INTERNAL – DETAILEDN/A20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-1752-450-00Upper Deck CrewService Door andMain DeckEntry Door 1LINTERNAL – DETAILED: Upper Deck Crew Service Door and MainDeck Entry Door 1LDetailed Inspection of the upper deck crew service door and the maindeck entry door 1L internal structure to include:FramesStop beamsStiffeners and intercostalSkinsUpper and lower gatesINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect withdoor linings removed.INTERNAL – DETAILEDN/A20,000 FC6 YR7200 FCSee Note (2)52-804-01NOSE CARGODOOREXTERNAL – ZONAL (GVI): NOSE CARGO DOORGeneral Visual Inspection of the nose cargo door.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL(GVI)N/A20,000 FC4 YR4800 FCSee Note (2)52-806-01CARGOCOMPARTMENTDOOR – FORWARDEXTERNAL – ZONAL (GVI): CARGO COMPARTMENT DOOR –FORWARDGeneral Visual Inspection of the forward cargo containercompartment door.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL(GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)52-808-01CARGOCOMPARTMENTDOOR – AFTEXTERNAL – ZONAL (GVI): CARGO COMPARTMENT DOOR –AFTGeneral Visual Inspection of the aft cargo container compartmentdoor.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL(GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)52-810-01CARGOCOMPARTMENTDOOR – BULKEXTERNAL – ZONAL (GVI): CARGO COMPARTMENT DOOR –BULKGeneral Visual Inspection of the bulk cargo compartment door.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL(GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-18747-8/8F AIRWORTHINESS LIMITATIONS52-811-01MAIN DECKENTRY DOORNO. 1, 2, 3, 4, 5 –LEFT SIDEEXTERNAL – ZONAL (GVI): MAINDECK ENTRY DOOR NO. 1, 2,3, 4, 5 – LEFT SIDEGeneral Visual Inspection of the leftmain deck entry door no. 1, 2, 3,4, 5.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL(GVI)20,000 FCN/A4 YR4800 FCSee Note (2)52-812-01MAIN DECK ENTRYDOOR NO. 1 –LEFT SIDEEXTERNAL – ZONAL (GVI): MAINDECK ENTRY DOOR NO. 1 –LEFT SIDEGeneral Visual Inspection of the main deck entry door no. 1.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL(GVI)N/A20,000 FC4 YR4800 FCSee Note (2)52-813-01MAIN DECKENTRY DOORNO. 1, 2, 3, 4, 5 –RIGHT SIDEEXTERNAL – ZONAL (GVI): MAINDECK ENTRY DOOR NO. 1, 2,3, 4, 5 – RIGHT SIDEGeneral Visual Inspection of the right main deck entry door no. 1, 2,3, 4, 5.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL(GVI)20,000 FCN/A4 YR4800 FCSee Note (2)52-814-01MAIN DECK SIDECARGO DOOREXTERNAL – ZONAL (GVI): MAIN DECK SIDE CARGO DOORGeneral Visual Inspection of the main deck side cargo door.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL(GVI)N/A20,000 FC4 YR4800 FCSee Note (2)52-816-01UPPER DECKEMERGENCYDOOR – LEFTand RIGHTEXTERNAL – ZONAL (GVI): UPPER DECK EMERGENCY DOOR –LEFT and RIGHTGeneral Visual Inspection of the upper deck side emergency door,left and right.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)20,000 FCN/A4 YR4800 FCSee Note (2)52-822-01UPPER DECKCREW SERVICEDOOREXTERNAL – ZONAL (GVI): UPPER DECK CREWSERVICE DOORGeneral Visual Inspection of the upper deck crew service door.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)N/A20,000 FC4 YR4800 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-1953-400-00Area Forward ofNose Wheel WellINTERNAL – DETAILED: Area Forward of Nose Wheel WellDetailed Inspection of the nose cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplish visualinspection.INTERNAL – DETAILEDN/A20,000 FC6 YR7200 FCSee Note (2)53-405-00Area Forward ofNose Wheel WellEXTERNAL – DETAILED: Area Forward of Nose Wheel WellDetailed Inspection of the nose cargo door latch fittingsINTERVAL NOTE: Whichever comes first.ACCESS NOTE: With door open.EXTERNAL – DETAILEDN/A20,000 FC4 YR4800 FCSee Note (2)53-410-00Nose Wheel WellEXTERNAL – DETAILED: Nose Wheel WellDetailed Inspection of the fittings in the nose wheel well to include:Nose gear drag Strut fittingNose gear actuator fittingNose gear trunnion fittingINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Access as visible with landing gear doors open.EXTERNAL – DETAILED20,000 FC20,000 FC4 YR4800 FCSee Note (2)53-410-01Area Outboard ofNose Wheel WellINTERNAL – GENERAL VISUAL: Area Outboard of Nose WheelWellGeneral Visual Inspection of the fuselage structure to include:Structure & Skin – BS 260 to BS 400BS 260 Canted BulkheadNose Wheel Well StructureBS 340 BulkheadBS 400 BulkheadINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplish visualinspection.INTERNAL –GENERAL VISUAL20,000 FC20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-20747-8/8F AIRWORTHINESS LIMITATIONS53-410-02Body Station 400 toBody Station 1000INTERNAL – GENERAL VISUAL: Body Station 400 to Body Station1000General Visual Inspection of the fuselage structure from BS 400 toBS 1000INTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplish visualinspection.INTERNAL –GENERAL VISUAL20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-415-00Forward CargoContainerCompartmentForward HalfINTERNAL – DETAILED: Forward Cargo Container CompartmentForward HalfDetailed Inspection of the forward cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplish visualinspection.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-420-00Forward CargoContainerCompartmentForward HalfEXTERNAL – DETAILED: Forward Cargo Container CompartmentForward HalfDetailed Inspection of the forward cargo door latch supportsINTERVAL NOTE: Whichever comes first.EXTERNAL – DETAILED20,000 FC20,000 FC2 YR2400 FCSee Note (2)53-420-01Area Aft of theForward CargoContainerCompartmentINTERNAL – GENERAL VISUAL: Area Aft of the Forward CargoContainer CompartmentGeneral Visual Inspection of the BS 1000 bulkheadINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplish visualinspection.INTERNAL –GENERAL VISUAL20,000 FC20,000 FC4 YR4800 FCSee Note (2)53-425-00Pressurized Areafrom bottom of MainCabin Floor toPressure Deck(Sta 1000 to 1241)INTERNAL – DETAILED: Pressurized Area from bottom of MainCabin Floor to Pressure Deck (Sta 1000 to 1241)Detailed Inspection of the BS 1241 BulkheadINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove floor panels.INTERNAL – DETAILEDFLS, SeeFigure 2FLS, SeeFigure 26 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-2153-430-00Wing and BodyLanding GearWheel WellEXTERNAL – DETAILED: Wing and Body Landing Gear Wheel WellDetailed Inspection of the main landing gear wheel wells to include:Landing gear trunnion support fittings and attachment to BS 1480bulkheadLanding gear side strut support fitting and attachment to BS 1350bulkheadLanding gear drag and jury strut fittings and attachmentsINTERVAL NOTE: Whichever comes first.EXTERNAL – DETAILED20,000 FC20,000 FC4 YR4800 FCSee Note (2)53-430-01Body Station 1480 toBody Station 2360INTERNAL – GENERAL VISUAL: Body Station 1480 to Body Station2360General Visual Inspection of the fuselage structure to include:BS 1480 cargo bay stop beam & bulkheadStructure and skin – BS 1480 to BS 2360BS 2360 aft pressure bulkhead – Fwd face below main deck floorINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplish visualinspection.INTERNAL –GENERAL VISUAL20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-435-00Aft Cargo ContainerCompartmentINTERNAL – DETAILED: Aft Cargo Container CompartmentDetailed Inspection of the aft cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplish visualinspection.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-440-00Aft Cargo ContainerCompartmentEXTERNAL – DETAILED: Aft Cargo Container CompartmentDetailed Inspection of the aft cargo door latch supportsINTERVAL NOTE: Whichever comes first.EXTERNAL – DETAILED20,000 FC20,000 FC2 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-22747-8/8F AIRWORTHINESS LIMITATIONS53-445-00Bulk CargoCompartmentINTERNAL – DETAILED: Bulk Cargo CompartmentDetailed Inspection of the bulk cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplish visualinspection.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-450-00Bulk CargoCompartmentEXTERNAL – DETAILED: Bulk Cargo CompartmentDetailed Inspection of the bulk cargo door stop fittingsINTERVAL NOTE: Whichever comes first.EXTERNAL – DETAILED20,000 FC20,000 FC2 YR2400 FCSee Note (2)53-455-00Keel Beam(BS 1235 to 1520)INTERNAL – GENERAL VISUAL: Keel Beam (BS 1235 to 1520)General Visual Inspection of the chords and splices of the keel beambetween BS 1265 and BS 1480INTERVAL NOTE: Whichever comes first.INTERNAL –GENERAL VISUAL20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-460-00Wing-to-BodyFairing, Forward andAft Lower HalfINTERNAL – DETAILED: Wing-to-Body Fairing, Forward and AftLower HalfDetailed Inspection under the wing-to-body fairing of the underwinglongeronINTERVAL NOTE: Whichever comes first.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-465-00Upper Halfof FuselageINTERNAL – DETAILED: Upper Half of FuselageDetailed Inspection of the tension ties with frames and attachmentsINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove ceiling panels.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-470-00Main and UpperDeck DoorCutout StopsEXTERNAL – DETAILED: Main and Upper Deck Door Cutout StopsDetailed Inspection of the stops onthe main entry door cutout andupper deck door cutouts.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: As visible with doors open.EXTERNAL – DETAILED20,000 FC20,000 FC2 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-2353-475-00Main DeckINTERNAL – DETAILED: Main DeckDetailed Inspection of the nose cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplishvisual inspection.INTERNAL – DETAILEDN/A20,000 FC6 YR7200 FCSee Note (2)53-480-00Main and UpperDeck Door CutoutsINTERNAL – DETAILED: Main and Upper Deck Door CutoutsDetailed Inspection of the main and upper deck entry door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplish visualinspection.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-485-00Control CompartmentBody BS 240 to 380EXTERNAL – DETAILED: Control Compartment Body BS 240 to 380Detailed Inspection of the crewcompartment window structureand skinINTERVAL NOTE: Whichever comes first.EXTERNAL – DETAILED20,000 FC20,000 FC4 YR4800 FCSee Note (2)53-490-00Control CompartmentBody BS 240 to 380INTERNAL – DETAILED: Control Compartment Body BS 240 to 380Detailed Inspection of the Crew Compartment Window Structureand SkinINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplishvisual inspection.INTERNAL – DETAILED20,000 FC20,000 FC8 YR9600 FCSee Note (2)53-495-00Main DeckEXTERNAL – DETAILED: Main DeckDetailed Inspection of the latch fittings on the main deck side cargodoor cutoutINTERVAL NOTE: Whichever comes first.EXTERNAL – DETAILEDN/A20,000 FC2 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-24747-8/8F AIRWORTHINESS LIMITATIONS53-500-00Main DeckINTERNAL – DETAILED: Main DeckDetailed Inspection of the main deck side cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplishvisual inspection.INTERNAL – DETAILEDN/A20,000 FC6 YR7200 FCSee Note (2)53-505-00Main Deck andUpper AreaAbove CeilingINTERNAL – DETAILED: Main Deck and Upper Area Above CeilingDetailed Inspection of the BS 2360 pressure bulkhead andattachments – Forward SideINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access removeor displace all systems,equipment and interior furnishings as necessary to accomplishvisual inspection.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-510-00Wing-to-BodyFairing, Forward andAft Upper HalfINTERNAL – DETAILED: Wing-to-Body Fairing, Forward and AftUpper HalfDetailed Inspection under the wing-to-body fairing of the overwinglongeron and spliceINTERVAL NOTE: Whichever comes first.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-515-00Area Aft of PressureBulkheadEXTERNAL – DETAILED: Area Aft of Pressure BulkheadDetailed Inspection of the BS 2360 pressure bulkhead and stringerend fittingsINTERVAL NOTE: Whichever comes first.EXTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-520-00Stabilizer TorsionBox CompartmentEXTERNAL – DETAILED: Stabilizer Torsion Box CompartmentDetailed Inspection of the horizontal stabilizer jack screwattachments and supportstructure and the upper and lower stabilizerlongeron splice fittingsINTERVAL NOTE: Whichever comes first.EXTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-2553-525-00Stabilizer TorsionBox Compartmentand Area Aft ofStabilizer BoxCompartmentEXTERNAL – DETAILED: Stabilizer Torsion Box Compartment andArea Aft of Stabilizer Box CompartmentDetailed Inspection of the BS 2598 bulkheadINTERVAL NOTE: Whichever comes first.EXTERNAL – DETAILED20,000 FC20,000 FC,SeeNote (1)6 YR7200 FCSee Note (2)53-530-00APU CompartmentEXTERNAL – DETAILED: APU CompartmentDetailed Inspection of the APU support structure and attachmentsINTERVAL NOTE: Whichever comes first.EXTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-804-01LOWER HALF OFFUSELAGEEXTERNAL – ZONAL (GVI):LOWER HALF OF FUSELAGEGeneral Visual Inspection of the lower half of the fuselage, includingradome, service doors, wing-to-body fairings, and doorways.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: With FWD andcenter EE bay doors open.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)53-806-01RADOME WITHRADOME OPENINTERNAL – ZONAL (GVI): RADOME WITH RADOME OPENGeneral Visual Inspection of the radome with radome open.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC4 YR4800 FCSee Note (2)53-808-01AREA INSIDE OFFUSELAGEFORWARD OFNOSE GEAR WELLINTERNAL – ZONAL (GVI):AREA INSIDE OF FUSELAGEFORWARD OF NOSE GEAR WELLGeneral Visual Inspection of the area inside of fuselage forward ofnose gear well. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Insulating blankets removed or displacedas required.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-812-01NOSE GEAR WELLEXTERNAL – ZONAL (GVI): NOSE GEAR WELLGeneral Visual Inspection of the nose gear well. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: NLG doors open.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-26747-8/8F AIRWORTHINESS LIMITATIONS53-814-01AREA INSIDEFUSELAGE, ABOVEAND OUTBOARDOF NLG WELLINTERNAL – ZONAL (GVI): AREA INSIDE FUSELAGE, ABOVEAND OUTBOARD OF NLG WELLGeneral Visual Inspection of thearea inside of fuselage above andoutboard of nose gear well. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Insulation blankets removed or displaced asrequired. Remove rubber mat for access to structural boxes locatedforward of BS 400. Remove cabin floor panels as required to getaccess to area above NLG wheel well.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-816-01E/ECOMPARTMENTEXTERNAL – ZONAL (GVI): E/E COMPARTMENTGeneral Visual Inspection of the interior of E/E compartment. (EZAP)INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)53-818-01E/ECOMPARTMENTINTERNAL – ZONAL (GVI): E/E COMPARTMENTGeneral Visual Inspection of the interior of E/E compartment.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Insulating blankets removed or displaced asrequired, without removing electrical/electronics panels.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-822-01FORWARD CARGOCONTAINERCOMPARTMENTINTERNAL – ZONAL (GVI):FORWARD CARGO CONTAINERCOMPARTMENTGeneral Visual Inspection of the interior of forward cargo containercompartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Sidewall and ceiling panels removed. Insulatingblankets removed or displaced as required.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-824-01AREA BELOWFORWARD CARGOCONTAINERCOMPARTMENTEXTERNAL – ZONAL (GVI): AREA BELOW FORWARD CARGOCONTAINER COMPARTMENTGeneral Visual Inspection of the area below forward cargo containercompartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Floor panels removed as required.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC4 YR4800 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-2753-826-01AFT OF FWDCARGOCONTAINERCOMPARTMENTINTERNAL – ZONAL (GVI): AFT OF FWD CARGO CONTAINERCOMPARTMENTGeneral Visual Inspection of the areainside of fuselage aft of forwardcargo container compartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Linings removed and insulation blankets removedor displaced as required.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-827-01KEEL BEAMINTERNAL – ZONAL (GVI): KEEL BEAMGeneral Visual Inspection of the Keel Beam. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-828-01BOTTOM OF MAINFLOOR TOPRESSURE DECKINTERNAL – ZONAL (GVI): BOTTOM OF MAIN FLOOR TOPRESSURE DECKGeneral Visual Inspection of the area inside of fuselage from bottomof main cabin floor to pressure deck. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove floor panels.INTERNAL – ZONAL (GVI)FLS, SeeFigure 2FLS, SeeFigure 26 YR7200 FCSee Note (2)53-830-01AIR CONDITIONINGEQUIPMENT BAYINTERNAL – ZONAL (GVI): AIRCONDITIONING EQUIPMENT BAYGeneral Visual Inspection of the air conditioning equipment bay.(EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC4 YR4800 FCSee Note (2)53-832-01AIR CONDITIONINGEQUIPMENT BAYINTERNAL – ZONAL (GVI): AIRCONDITIONING EQUIPMENT BAYGeneral Visual Inspection of the air conditioning equipment bay.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-835-01WING LANDINGGEAR WELL – LEFTEXTERNAL – ZONAL (GVI): WING LANDING GEAR WELL – LEFTGeneral Visual Inspection of the left wing landing gear wheel well.(EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Left WLG doors open.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-28747-8/8F AIRWORTHINESS LIMITATIONS53-836-01BOTTOM OF MAINDECK FLOOR TOPRESSURE DECKINTERNAL – ZONAL (GVI): BOTTOM OF MAIN DECK FLOOR TOPRESSURE DECKGeneral Visual Inspection of the area inside of fuselage from bottomof main cabin floor to pressure deck. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove floor panels.INTERNAL – ZONAL (GVI)FLS, SeeFigure 2FLS, SeeFigure 26 YR7200 FCSee Note (2)53-840-01WING LANDINGGEAR WELL –RIGHTEXTERNAL – ZONAL (GVI): WING LANDING GEAR WELL –RIGHTGeneral Visual Inspection of the right wing landing gear wheel well.(EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Right WLG doors open.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)53-844-01BODYLANDING GEARWHEEL WELL –LEFTEXTERNAL – ZONAL (GVI): BODYLANDING GEAR WHEEL WELL– LEFTGeneral Visual Inspection of the left body landing gear wheel well.(EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Left BLG doors open.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)53-848-01BODYLANDING GEARWHEEL WELL –RIGHTEXTERNAL – ZONAL (GVI): BODYLANDING GEAR WHEEL WELL– RIGHTGeneral Visual Inspection of the right body landing gear wheel well.(EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Right BLG doors open.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-2953-852-01AFT CARGOCONTAINERCOMPARTMENTINTERNAL – ZONAL (GVI):AFT CARGO CONTAINERCOMPARTMENTGeneral Visual Inspection of the interior of aft cargo containercompartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Sidewall and ceiling panels removed. Insulatingblankets removed or displaced as required.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-854-01AREA BELOW AFTCARGOCONTAINERCOMPARTMENTEXTERNAL – ZONAL (GVI):AREA BELOW AFT CARGOCONTAINER COMPARTMENTGeneral Visual Inspection of the area inside of fuselage below aftcargo container compartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Floor panels removed as required.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC4 YR4800 FCSee Note (2)53-858-01BULK CARGOCOMPARTMENTINTERNAL – ZONAL (GVI): BULK CARGO COMPARTMENTGeneral Visual Inspection of the interior of bulk cargo compartment.(EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Sidewall and ceiling panels removed. Insulationblankets removed or displaced as required.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-860-01AREA BELOWBULK CARGOCOMPARTMENTINTERNAL – ZONAL (GVI): AREA BELOW BULKCARGO COMPARTMENTGeneral Visual Inspection of thearea inside of fuselage below bulkcargo compartment. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to theIntercontinental only. For the Freighter, this task is classifiedexclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Two (2) center floor panels removed.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-30747-8/8F AIRWORTHINESS LIMITATIONS53-862-01AREA AFT OFBULK CARGOCOMPARTMENTINTERNAL – ZONAL (GVI): AREA AFT OF BULKCARGO COMPARTMENTGeneral Visual Inspection of the area inside of fuselage aft of bulkcargo compartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove floor panels from BS 2280 throughBS 2360 of main cabin. Insulating blankets removed.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-864-01FWD LOWER WINGTO-BODY-FAIRING– LEFTINTERNAL – ZONAL (GVI):FWD LOWER WING-TO-BODYFAIRING – LEFTGeneral Visual Inspection of the area inside of forward lower wing-tobody fairing, left side. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-866-01FWD LOWER WINGTO-BODY-FAIRING– RIGHTINTERNAL – ZONAL (GVI):FWD LOWER WING-TO-BODYFAIRING – RIGHTGeneral Visual Inspection of the area inside of forward lower wing-tobody fairing, right side. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-868-01AFT LOWER WINGTO-BODY-FAIRING– LEFTINTERNAL – ZONAL (GVI):AFT LOWER WING-TO-BODYFAIRING – LEFTGeneral Visual Inspection of the area inside of aft lower wing-to-bodyfairing, left side. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to theIntercontinental only. For the Freighter, this task is classifiedexclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-3153-870-01AFT LOWER WINGTO-BODY-FAIRING– RIGHTINTERNAL – ZONAL (GVI):AFT LOWER WING-TO-BODYFAIRING – RIGHTGeneral Visual Inspection of the area inside of aft lower wing-to-bodyfairing, right side. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to theIntercontinental only. For the Freighter, this task is classifiedexclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-874-01UPPER HALFOF FUSELAGEEXTERNAL – ZONAL (GVI): UPPER HALF OF FUSELAGEGeneral Visual Inspection of the upper half of fuselage, includingwindows and wing-to-body fairings.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: As visible with doors open.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC4 YR4800 FCSee Note (2)53-880-01FUSELAGEMAIN DECKCOMPARTMENTINTERNAL – ZONAL (GVI):FUSELAGE MAIN DECKCOMPARTMENTGeneral Visual Inspection of the interior of fuselage main deckcompartment – (nose to BS 854 for freighter, nose to BS 1101 forpassenger). (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove ceiling panels as required to performinspection.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-882-01FUSELAGEMAIN DECKCOMPARTMENT –NOSE TO BS 2360INTERNAL – ZONAL (GVI):FUSELAGE MAIN DECKCOMPARTMENT – NOSE TO BS 2360General Visual Inspection of the interior of fuselage main deckcompartment – nose to BS 2360. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Sidewall panels and insulating blankets removedor displaced.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-32747-8/8F AIRWORTHINESS LIMITATIONS53-884-01INTERIOR OFFLIGHT DECKCOMPARTMENTEXTERNAL – ZONAL (GVI): INTERIOR OF FLIGHTDECK COMPARTMENTGeneral Visual Inspection ofthe flight deck compartment.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)53-886-01FLIGHT DECKCOMPARTMENTINTERNAL – ZONAL (GVI): FLIGHT DECK COMPARTMENTGeneral Visual Inspection of the flight deck compartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove side wall panels, insulation and interiorfurnishings as necessary to accomplish visual inspection withoutdisplacing flight control panels/consoles, electrical panels or dripshield. Windshield/window removal is not required unless there is anindication of corrosion in the interface area.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-888-01INTERIOR OFFUSELAGEUPPER DECKCOMPARTMENTEXTERNAL – ZONAL (GVI): INTERIOR OF FUSELAGE UPPERDECK COMPARTMENTGeneral Visual Inspection of the interior of fuselage upper deckcompartment (BS 380 to BS 633).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)53-888-02INTERIOR OFFUSELAGE AFTUPPER DECKCOMPARTMENTINTERNAL – ZONAL (GVI): INTERIOR OF FUSELAGE AFT UPPERDECK COMPARTMENTGeneral Visual Inspection of the interior of fuselage aft upper deckcompartment – BS 633 to BS 1101.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FCN/A2 YR2400 FCSee Note (2)53-890-01INTERIOR OFFUSELAGEUPPER DECKINTERNAL – ZONAL (GVI): INTERIOR OF FUSELAGE UPPERDECKGeneral Visual Inspection of the interior of fuselage upper deck(BS 380 to BS 633). (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove sidewall/ceiling panelsas required.Insulating blankets removed or displaced as required.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-3353-890-02INTERIOR OFFUSELAGE AFTUPPER DECKCOMPARTMENTINTERNAL – ZONAL (GVI): INTERIOR OF FUSELAGE AFT UPPERDECK COMPARTMENTGeneral Visual Inspection of the interior of fuselage aft upper deckcompartment – BS 633 to BS 1101. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove sidewall/ceiling panelsas required.Insulating blankets removed or displaced as required.INTERNAL – ZONAL (GVI)20,000 FCN/A6 YR7200 FCSee Note (2)53-892-01AREA AFT OFUPPER DECKCOMPARTMENTINTERNAL – ZONAL (GVI):AREA AFT OF UPPERDECK COMPARTMENTGeneral Visual Inspection of the area aft of upper deck compartment,(BS 633 to BS 854). (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove ceiling panels as required.INTERNAL – ZONAL (GVI)N/A20,000 FC6 YR7200 FCSee Note (2)53-894-01AREA ABOVECEILING INSIDEFUSELAGE,BS 854 to BS 2360INTERNAL – ZONAL (GVI): AREA ABOVE CEILING INSIDEFUSELAGE, BS 854 to BS 2360General Visual Inspection of the area inside of fuselage aboveceiling, BS 854 to BS 2360. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove ceiling panels as required.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-900-01AFT ELECTRONICEQUIPMENT BAYINTERNAL – ZONAL (GVI): AFT ELECTRONIC EQUIPMENT BAYGeneral Visual Inspection of the interior of aft electrical/electronicequipment bay. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove sidewall/ceiling panelsas required.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC4 YR4800 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-34747-8/8F AIRWORTHINESS LIMITATIONS53-902-01INTERIOR OFOVERHEAD CREWREST AREAINTERNAL – ZONAL (GVI): INTERIOR OF OVERHEAD CREWREST AREAGeneral Visual Inspection of the interior of overhead crew rest area.(EZAP)AIRPLANE NOTE: Applicable to aircraft with overhead crew restinstalled.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FCN/A2 YR2400 FCSee Note (2)53-906-01UPPER WING-TOBODY FAIRING –FWD LEFTINTERNAL – ZONAL (GVI): UPPER WING-TO-BODY FAIRING –FWD LEFTGeneral Visual Inspection of the area inside of forward upper wingto-body fairing, left side. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to theIntercontinental only. For the Freighter, this task is classifiedexclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-908-01UPPER WING-TOBODY FAIRING –FWD RIGHTINTERNAL – ZONAL (GVI): UPPER WING-TO-BODY FAIRING –FWD RIGHTGeneral Visual Inspection of the area inside of forward upper wingto-body fairing, right side. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to theIntercontinental only. For the Freighter, this task is classifiedexclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-910-01UPPER WING-TOBODY FAIRING –AFT LEFTINTERNAL – ZONAL (GVI): UPPER WING-TO-BODY FAIRING –AFT LEFTGeneral Visual Inspection of thearea inside of aftupper wing-to-bodyfairing, left side. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to theIntercontinental only. For the Freighter, this task is classifiedexclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-3553-912-01UPPER WING -TOBODY FAIRING –AFT RIGHTINTERNAL – ZONAL (GVI): UPPER WING -TO – BODY FAIRING –AFT RIGHTGeneral Visual Inspection of thearea inside of aftupper wing-to-bodyfairing, right side. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to theIntercontinental only. For the Freighter, this task is classifiedexclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-916-01FUSELAGE BS 2360TO BS 2792EXTERNAL – ZONAL (GVI): FUSELAGE BS 2360 TO BS 2792General Visual Inspection of the fuselage from BS 2360 to BS 2792(Section 48).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC4 YR4800 FCSee Note (2)53-918-01AREA AFT OF REARPRESSUREBULKHEADEXTERNAL – ZONAL (GVI): AREA AFT OF REAR PRESSUREBULKHEADGeneral Visual Inspection of the area inside of fuselage aft of rearpressure bulkhead (BS 2360 to BS 2484), including access door.(EZAP)INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)53-919-01AREA UNDERVERTICAL ANDHORIZONTALSTABILIZERFAIRINGSINTERNAL – ZONAL (GVI): AREA UNDER VERTICAL ANDHORIZONTAL STABILIZER FAIRINGSGeneral Visual Inspection of the area under the vertical andhorizontal stabilizer fuselage fairings.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Vertical and Horizontal Stabilizer Fairings.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)53-920-01STABILIZERTORSION BOXCOMPARTMENTEXTERNAL – ZONAL (GVI):STABILIZER TORSION BOXCOMPARTMENTGeneral Visual Inspection of the horizontal stabilizer torsion boxcompartment. (EZAP)INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-36747-8/8F AIRWORTHINESS LIMITATIONS53-922-01AFT OFHORIZONTALSTABILIZERTORSION BOXCOMPARTMENTEXTERNAL – ZONAL (GVI): AFTOF HORIZONTAL STABILIZERTORSION BOX COMPARTMENTGeneral Visual Inspection of the area inside of fuselage aft ofhorizontal stabilizer torsion box compartment. (EZAP)INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FCSeeNote (1)2 YR2400 FCSee Note (2)53-924-01INTERIOR OF APUCOMPARTMENTEXTERNAL – ZONAL (GVI): INTERIOR OF APU COMPARTMENTGeneral Visual Inspection of the interior of APU compartment,including APU and APU doors. (EZAP)INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)54-405-00Forward Fairing –Strut No. 1, 2, 3, 4EXTERNAL – DETAILED: Forward Fairing – Strut No. 1, 2, 3, 4Detailed Inspection of the strut to wing attachments to include:Upper link, upper link pins, and the lugs of the adjacent strut andwing fittingsINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Upper link orpin removal not required.EXTERNAL – DETAILEDFLS,< 7 hrs15,000 FC≥7 hrs10,000 FCFLS,< 7 hrs15,000 FC≥7 hrs10,000 FC4 YR4800 FC24000 FHSee Note (2)54-410-00Torque Box –Strut No. 1, 2, 3, 4INTERNAL – GENERAL VISUAL: Torque Box – Strut No. 1, 2, 3, 4General Visual Inspection of the torque box to include:Upper spar assemblyLower spar assemblyForward engine mount bulkheadAft engine mount bulkheadFrames.INTERVAL NOTE: Whichever comes first.INTERNAL –GENERAL VISUALFLS,< 7 hrs15,000 FC≥7 hrs10,000 FCFLS,< 7 hrs15,000 FC≥7 hrs10,000 FC4 YR4800 FC24000 FHSee Note (2)54-415-00Torque Box –Strut No. 1, 2, 3, 4INTERNAL – GENERAL VISUAL: Torque Box – Strut No. 1, 2, 3, 4General Visual Inspection of the torque box side skins.INTERVAL NOTE: Whichever comes first.INTERNAL –GENERAL VISUALFLS,< 7 hrs15,000 FC≥7 hrs10,000 FCFLS,< 7 hrs15,000 FC≥7 hrs10,000 FC2 YR2400 FC12000 FHSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-3754-420-00Aft Fairing –Strut No. 1, 2, 3, 4INTERNAL – DETAILED: Aft Fairing – Strut No. 1, 2, 3, 4Detailed Inspection of the strut to wing attachments to include:Side links, side link pins, and the lugs of the adjacent strut fittingsDiagonal brace, diagonal brace pins, and the lugs of the adjacentstrut and wing fittingsFuse pins and the lugs of the aft upper spar fittings.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Side links, diagonal brace, or pin removalnot required.INTERNAL – DETAILEDFLS,< 7 hrs15,000 FC≥7 hrs10,000 FCFLS,< 7 hrs15,000 FC≥7 hrs10,000 FC4 YR4800 FC24000 FHSee Note (2)54-425-00Aft Fairing andTorque Box –Strut No. 1 & 4INTERNAL – DETAILED: Aft Fairing and Torque Box – StrutNo. 1 & 4Detailed inspection of the aft upper spar fittings to include:Lugs of the aft upper spar fittingsPins of the aft upper spar fittingsHorizontal flange of theaft upper spar fittingsVertical flange of the aft upper spar fittingsINTERVAL NOTE: Whichever comes first.INTERNAL – DETAILED20,000 FC20,000 FC2 YR2400 FCSee Note (2)54-804-00STRUT NO. 1, 2, 3, 4INCLUDINGFAIRINGSEXTERNAL – ZONAL (GVI): STRUTNO. 1, 2, 3, 4 INCLUDINGFAIRINGSGeneral Visual Inspection of the strut no. 1, 2, 3, 4 including fairings.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)54-806-00AREA INSIDEFORWARD FAIRINGNO. 1, 2, 3, 4INTERNAL – ZONAL (GVI): AREA INSIDE FORWARD FAIRINGNO. 1, 2, 3, 4General Visual Inspection of thearea inside forward fairing. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)54-808-00INTERIOROF STRUTNO. 1, 2, 3, 4TORQUE BOXINTERNAL – ZONAL (GVI): INTERIOR OF STRUT NO. 1, 2, 3, 4TORQUE BOXGeneral Visual Inspection of the interior of strut no. 1, 2, 3, 4 torquebox. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-38747-8/8F AIRWORTHINESS LIMITATIONS54-812-00AREA INSIDE OFAFT STRUTNO. 1, 2, 3, 4FAIRINGINTERNAL – ZONAL (GVI): AREA INSIDE OF AFT STRUT NO. 1, 2,3, 4 FAIRINGGeneral Visual Inspection ofthe area inside of aft strutno. 1, 2, 3, 4 fairing. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)55-400-00RudderINTERNAL – SPECIAL DETAILED: RudderSpecial Detailed Inspection of the upper rudder, lower rudder andrudder tab internal structure.NOTE: Borescope/Videoscope required to do this internal inspection.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Disassembly is not required.INTERNAL –SPECIAL DETAILEDFLS, SeeFigure 1FLS, SeeFigure 116 YR19200 FCSee Note (2)55-405-00Horizontal StabilizerINTERNAL – GENERAL VISUAL: Horizontal StabilizerGeneral Visual Inspection of the horizontal stabilizerinternal structure.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Disassembly is not required.INTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 1,SeeNote (1)16 YR19200 FCSee Note (2)55-410-00ElevatorINTERNAL – GENERAL VISUAL: ElevatorGeneral Visual Inspection of the inboard elevator hinges & supportstructure on elevator.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Disassembly is not required.INTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)55-415-00ElevatorINTERNAL – GENERAL VISUAL: ElevatorGeneral Visual Inspection of the elevator internal structure.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Disassembly is not required.INTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 116 YR19200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-3955-801-01FIN AND RUDDEREXTERNAL – ZONAL (GVI): FIN AND RUDDERGeneral Visual Inspection of the fin and rudder.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect visual portions of closure ribs when ruddersare at maximum opposite displacement.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)55-802-01FIN REMOVABLELEADING EDGEINTERNAL – ZONAL (GVI):FIN REMOVABLE LEADING EDGEGeneral Visual Inspection of the fin removable leading edge. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)55-803-01FIN AUXILIARYSPAR TOFRONT SPARINTERNAL – ZONAL (GVI): FINAUXILIARY SPAR TO FRONTSPARGeneral Visual Inspection of thefin auxiliary spar to front spar.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)55-805-01FIN – FRONT SPARTO REAR SPARINTERNAL – ZONAL (GVI): FIN – FRONT SPAR TO REAR SPARGeneral Visual Inspection of the fin front spar to rear spar. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)55-806-01FIN REAR SPAR TOTRAILING EDGEINTERNAL – ZONAL (GVI): FIN REAR SPAR TO TRAILING EDGEGeneral Visual Inspection of the fin rear spar to rudders front sparincluding front spar of the lower rudder tab. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)55-808-01FIN REAR SPAR TOTE CAVITYINTERNAL – ZONAL (GVI): FIN REAR SPAR TO TE CAVITYGeneral Visual Inspection of the fin rear spar to rudders front spar.(EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)55-809-01FIN TIPINTERNAL – ZONAL (GVI): FIN TIPGeneral Visual Inspection of the fin tip. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-40747-8/8F AIRWORTHINESS LIMITATIONS55-812-01HORIZONTAL STABAND ELEVATOR –LEFTEXTERNAL – ZONAL (GVI): HORIZONTAL STAB AND ELEVATOR– LEFTGeneral Visual Inspection ofthe left horizontal stabilizerand elevator.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 1,SeeNote (1)4 YR4800 FCSee Note (2)55-814-01HORIZONTAL STABREAR SPAR TOELEVATOR FRONTSPAR – LEFTINTERNAL – ZONAL (GVI): HORIZONTAL STAB REAR SPAR TOELEVATOR FRONT SPAR – LEFTGeneral Visual Inspection of the lefthorizontal stabilizer rear spar toelevator front spar.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 1,SeeNote (1)2 YR2400 FCSee Note (2)55-816-01HORIZONTAL STABREAR SPAR TOELEVATOR FRONTSPAR – LEFTINTERNAL – ZONAL (GVI): HORIZONTAL STAB REAR SPAR TOELEVATOR FRONT SPAR – LEFTGeneral Visual Inspection of the lefthorizontal stabilizer rear spar toelevator front spar. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 1,SeeNote (1)6 YR7200 FCSee Note (2)55-820-01HORIZONTAL STABAND ELEVATOR –RIGHTEXTERNAL – ZONAL (GVI): HORIZONTAL STAB AND ELEVATOR– RIGHTGeneral Visual Inspection of the right horizontal stabilizerand elevator.INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 1,SeeNote (1)4 YR4800 FCSee Note (2)55-822-01HORIZONTAL STABREAR SPAR TOELEVATOR FRONTSPAR – RIGHTINTERNAL – ZONAL (GVI): HORIZONTAL STAB REAR SPAR TOELEVATOR FRONT SPAR – RIGHTGeneral Visual Inspection of the righthorizontal stabilizer rear spar toelevator front spar.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 1,SeeNote (1)2 YR2400 FCSee Note (2)55-824-01HORIZONTAL STABREAR SPAR TOELEVATOR FRONTSPAR – RIGHTINTERNAL – ZONAL (GVI): HORIZONTAL STAB REAR SPAR TOELEVATOR FRONT SPAR – RIGHTGeneral Visual Inspection of the righthorizontal stabilizer rear spar toelevator front spar. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 1,SeeNote (1)6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-4155-828-01HORIZONTAL STABCENTER SECTIONTORSION BOXINTERNAL – ZONAL (GVI):HORIZONTAL STAB CENTERSECTION TORSION BOXGeneral Visual Inspection of the horizontal stabilizer center sectiontorsion box. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to theIntercontinental only. For the Freighter, this task is classifiedexclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 1,SeeNote (1)6 YR7200 FCSee Note (2)55-830-01LEFT HORIZONTALSTABILIZER –FRONT SPAR TOREAR SPARINTERNAL – ZONAL (GVI): LEFTHORIZONTAL STABILIZER –FRONT SPAR TO REAR SPARGeneral Visual Inspection of theleft horizontal stabilizer – stab.BL 43.5 to stab. STA 285. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1N/A8 YR9600 FCSee Note (2)55-832-01RIGHTHORIZONTALSTABILIZER –FRONT SPAR TOREAR SPARINTERNAL – ZONAL (GVI): RIGHT HORIZONTALSTABILIZER –FRONT SPAR TO REAR SPARGeneral Visual Inspection of theright horizontal stabilizer – stab.BL 43.5 to stab. STA 285. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1N/A8 YR9600 FCSee Note (2)57-400-00Center SectionWing BoxINTERNAL – DETAILED: Center Section Wing BoxDetailed Inspection of the internalstructure of the center section wingbox to include:Access cutouts in front spar – aft faceUpper stringer splice fittingsUpper chord flangesLower stringer splice fittingsLower chord flangesKeel beam attachment fittings.INTERVAL NOTE: Whichever comes first.INTERNAL – DETAILEDFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-42747-8/8F AIRWORTHINESS LIMITATIONS57-405-00Wing-to-Body FairingLower HalfINTERNAL – DETAILED: Wing-to-Body Fairing Lower HalfDetailed Inspection under the wing-to-body fairing to include:Access cutouts in center section front spar – forward faceINTERVAL NOTE: Whichever comes first.INTERNAL – DETAILEDFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-410-00Raked Wing TipINTERNAL – SPECIAL DETAILED: Raked Wing TipSpecial Detailed Inspection of the internal structure of the raked wingtip to include:LE beamRoot ribClosure ribTension ribFront sparRear sparUpper panelsLower panelsNOTE: Borescope/Videoscope requiredto do this internal inspectionof the raked wing tip.INTERVAL NOTE: Whichever comes first.INTERNAL –SPECIAL DETAILEDFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-410-01Raked Wing TipEXTERNAL – GENERAL VISUAL: Raked Wing TipGeneral Visual Inspection of the upper and lower skin panels of theraked wing tips.INTERVAL NOTE: Whichever comes first.EXTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-415-00Front Spar toRear Spar fromWBL 128.5 toWS 1244INTERNAL – DETAILED: Front Spar to Rear Spar from WBL 128.5to WS 1244Detailed Inspection of the outer wing lower skin access cutoutsINTERVAL NOTE: Whichever comes first.INTERNAL – DETAILEDFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-4357-420-00Inboard Main Tank –Front Spar toRear SparINTERNAL – DETAILED: Inboard Main Tank – Front Spar toRear SparDetailed Inspection of the splicejoint between the center and outerwing box to include:Side-of-body upper stringer splice fittingsSide-of-body upper chord flangesSide-of-body lower stringer splice fittingsSide-of-body lower chord flanges.INTERVAL NOTE: Whichever comes first.INTERNAL – DETAILEDFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-425-00Outboard Main Tank– Front Spar toRear SparINTERNAL – DETAILED: Outboard Main Tank – Front Spar toRear SparDetailed Inspection of the dry bays above the outboard pylonINTERVAL NOTE: Whichever comes first.INTERNAL – DETAILEDFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-425-01Wing UpperSkin PanelsEXTERNAL – GENERAL VISUAL: Wing Upper Skin PanelsGeneral Visual Inspection of the wing upper skin panels to include:Upper wing skin upper surface – forward of leading edge sparUpper wing skin upper surface – front spar to rear sparUpper wing skin upper surface – aft of rear sparINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Upper wing skin uppersurface – visible in leadingedge bays with leading edge devices extendedUpper wing skin upper surface – visible in trailing edge bays withflaps, speed brakes and spoilers extendedEXTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-44747-8/8F AIRWORTHINESS LIMITATIONS57-425-02Wing LowerSkin PanelsEXTERNAL – GENERAL VISUAL: Wing Lower Skin PanelsGeneral Visual Inspection of the wing lower skin panels to include:Lower skin panel lower surface – forward of front sparLower skin panel lower surface – front spar to rear sparLower skin panel lower surface – aft of rear sparINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Lower skin panel lower surface – visible in leadingedge bays with leading edge devices extendedLower skin panel lower surface – visible in trailing edge bays withtrailing edge devices extendedLower skin panel lower surface – under pylon fairingsEXTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-430-00Flap Track FairingsINTERNAL – DETAILED: Flap Track FairingsDetailed Inspection of the internal area of the flap track fairingsto include:Flap track #1 and #8Flap track #2 and #7Flap track #3 and #6Flap track #4 and #5Inboard flap – tracks #3, #4, #5,& #6 carriage assembliesInboard flap – transmission mount structureOutboard flap – tracks #1, #2, #7,& #8carriage assembliesOutboard Flap – Transmission Mount Structure.INTERVAL NOTE: Whichever comes first.INTERNAL – DETAILED20,000 FC20,000 FC,SeeNote (1)6 YR7200 FCSee Note (2)57-435-00Rear Spar to LandingGear Support BeamEXTERNAL – DETAILED: Rear Sparto Landing Gear Support BeamDetailed Inspection of the walking beam end fitting on the rear spar,and the walking beam end fitting on the landing gear beam.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: As visible from the wheel well.EXTERNAL – DETAILEDFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-4557-440-00Landing GearSupport Beam &Rear Spar to TrailingEdgeEXTERNAL – DETAILED: Landing Gear Support Beam & Rear Sparto Trailing EdgeDetailed Inspection of the spoiler beam fittings and attachment to flaptracks #3, #4, #5 & #6INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Spoilers and Flaps deployedEXTERNAL – DETAILEDFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-445-00Rear Spar to InboardAileron Leading EdgeINTERNAL – GENERAL VISUAL: Rear Spar to Inboard AileronLeading EdgeGeneral Visual Inspection of the fixed trailing edge and inboardaileron to include:Fixed trailing edge hinge ribs & bearing linksAileron hinge fittings.INTERVAL NOTE: Whichever comes first.INTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-450-00Rear Spar to InboardAileron Leading EdgeINTERNAL – GENERAL VISUAL: Rear Spar to Inboard AileronLeading EdgeGeneral Visual Inspection of the fixed trailing edge and inboardaileron to include:Fixed trailing edge actuator ribsAileron actuator rib – lug areaforward of aileron front sparAileron front spar – forward surface.INTERVAL NOTE: Whichever comes first.INTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-450-01Flight Spoiler InboardEXTERNAL – GENERAL VISUAL:Flight Spoiler InboardGeneral Visual Inspection of the spoilerINTERVAL NOTE: Whichever comes first.EXTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-450-02Flight SpoilerOutboardEXTERNAL – GENERAL VISUAL:Flight Spoiler OutboardGeneral Visual Inspection of the spoilerINTERVAL NOTE: Whichever comes first.EXTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-46747-8/8F AIRWORTHINESS LIMITATIONS57-455-00Inboard Main FlapINTERNAL – DETAILED: Inboard Main FlapDetailed Inspection of the inboard main flap to include:Gimbal & carriage support fittingsTracks A, B, C&D and tracks A,B, C&D attachment to main flapINTERVAL NOTE: Whichever comes first.INTERNAL – DETAILED20,000 FC20,000 FC,SeeNote (1)6 YR7200 FCSee Note (2)57-455-01Inboard Main FlapINTERNAL – SPECIAL DETAILED: Inboard Main FlapSpecial Detailed Inspection of the inboard main flap to include:Main support ribsSparsSkin panelsNOTE: Borescope/Videoscope requiredto do this internal inspectionof the inboard main flap box.INTERVAL NOTE: Whichever comes first.INTERNAL –SPECIAL DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)57-460-00Inboard Aft FlapINTERNAL – DETAILED: Inboard Aft FlapDetailed Inspection of the inboard aft flap to include:Inboard aft flap – track A roller assemblyInboard aft flap – track B&C carriage assembliesInboard aft flap – track D carriage assembly.INTERVAL NOTE: Whichever comes first.INTERNAL – DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)57-465-00Inboard Aft FlapINTERNAL – GENERAL VISUAL: Inboard Aft FlapGeneral Visual Inspection of the track D carriage attachment toaft flapINTERVAL NOTE: Whichever come first.INTERNAL –GENERAL VISUAL20,000 FC20,000 FC6 YR7200 FCSee Note (2)57-465-01Inboard Aft FlapINTERNAL – SPECIAL DETAILED: Inboard Aft FlapSpecial Detailed Inspection of the inboard aft flap to include:Support ribsSparsSkin panelsNOTE: Borescope/Videoscope requiredto do this internal inspectionof the aft flap.INTERVAL NOTE: Whichever comes first.INTERNAL –SPECIAL DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-4757-470-00Inboard AileronINTERNAL – SPECIAL DETAILED: Inboard AileronSpecial Detailed Inspection of theinternal structure of the inboardaileron to include:Actuator ribSparsRibsSkin panelsNOTE: Borescope/Videoscope requiredto do this internal inspectionof the inboard aileron.INTERVAL NOTE: Whichever comes first.INTERNAL –SPECIAL DETAILEDFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-470-01Inboard AileronEXTERNAL – GENERAL VISUAL: Inboard AileronGeneral Visual Inspection of theexterior surfaces of the aileronskin panelsINTERVAL NOTE: Whichever comes first.EXTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-470-02Inboard andOutboard Flap TrackSupportsEXTERNAL – GENERAL VISUAL: Inboard and Outboard Flap TrackSupportsGeneral Visual Inspection of the inboard and outboard flap tracksupports to include:Aft support, flap track #1 and #8Aft support, flap track #2 and #7Aft support, flap track #3 and #6Aft support, flap track #4 and #5Forward support, flap track #1 and #8Forward support, flap track #2 and #7Forward support, flap track #3 and #6Forward support, flap track #4 and #5INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Flaps fully extended. Fairing removal not required.EXTERNAL –GENERAL VISUAL20,000 FC20,000 FC,See Note(1)6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-48747-8/8F AIRWORTHINESS LIMITATIONS57-475-00Rear Spar toTrailing Edge fromWBL 515 to WBL 849INTERNAL – DETAILED: Rear Spar to Trailing Edge from WBL 515to WBL 849Detailed Inspection of the trailing edge structure to include:Outboard flap – inboard aux trackOutboard flap – inboard aux track linkOutboard flap – outboard aux trackOutboard flap – outboard aux track linkOutboard flap – inboard aux track carriage assemblyOutboard flap – outboard aux track carriage assembly.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Flaps fully extended.INTERNAL – DETAILEDFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-480-00Outboard FlapINTERNAL – GENERAL VISUAL: Outboard FlapGeneral Visual Inspection of theinternal structure of the outboardflap to include:Gimbal & carriage support fittingsInboard aux track carriage attachment to outboard flapOutboard aux track carriage attachment to outboard flap.INTERVAL NOTE: Whichever comes first.INTERNAL –GENERAL VISUAL20,000 FC20,000 FC,SeeNote (1)6 YR7200 FCSee Note (2)57-480-01Outboard FlapINTERNAL – SPECIAL DETAILED: Outboard FlapSpecial Detailed Inspection of the outboard flap to include:Main support ribsSparsSkin panelsNOTE: Borescope/Videoscope requiredto do this internal inspectionof the outboard flap box.INTERVAL NOTE: Whichever comes first.INTERNAL –SPECIAL DETAILED20,000 FC20,000 FC6 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-4957-485-00Rear Spar toTrailing Edge andOutboard AileronINTERNAL – GENERAL VISUAL: Rear Spar to Trailing Edge andOutboard AileronGeneral Visual Inspection of the trailing edge and outboard aileronto include:Trailing edge hinge ribs & bearing linksAileron hinge fittings.INTERVAL NOTE: Whichever comes first.INTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-490-00Rear Spar toTrailing Edge andOutboard AileronINTERNAL – GENERAL VISUAL: Rear Spar to Trailing Edge andOutboard AileronGeneral Visual Inspection of the trailing edge and outboard aileronto include:Trailing edge PCU support fittingsAileron actuator fittingAileron balance towersAileron front spar – forward surface.INTERVAL NOTE: Whichever comes first.INTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-495-00Outboard AileronINTERNAL – SPECIAL DETAILED: Outboard AileronSpecial Detailed Inspection of the internal structure of outboardaileron to include:SparRibsSkin panels.NOTE: Borescope/Videoscope requiredto do this internal inspectionof the outboard aileron box.INTERVAL NOTE: Whichever comes first.INTERNAL –SPECIAL DETAILEDFLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-500-00Outboard AileronEXTERNAL – GENERAL VISUAL: Outboard AileronGeneral Visual Inspection of theexterior surfaces of the aileronskin panelsINTERVAL NOTE: Whichever comes first.EXTERNAL –GENERAL VISUALFLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLETASK DESCRIPTIONINSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-50747-8/8F AIRWORTHINESS LIMITATIONS57-802-01CENTER SECTIONWING BOX –INTERIORINTERNAL – ZONAL (GVI): CENTER SECTIONWING BOX –INTERIORGeneral Visual Inspection of the interior of center section wing box.(EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-808-01WING LE TO FRONTSPAR – LEFT WINGEXTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR –LEFT WINGGeneral Visual Inspection of the left wing leading edge to front spar(WBL 128.5 to WBL 470).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-810-01WING LE TO FRONTSPAR CAVITY –LEFT WINGEXTERNAL – ZONAL (GVI): WINGLE TO FRONT SPAR CAVITY –LEFT WINGGeneral Visual Inspection of the left wing leading edge to front sparcavity. (ILES 302 to ILES 630.72).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-812-01WING LE TOFRONT SPARCOMPARTMENT –LEFT WINGINTERNAL – ZONAL (GVI):WING LE TO FRONT SPARCOMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front sparcompartment. (ILES 630.72 to WBL 470). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-814-01WING LE TOFRONT SPARCOMPARTMENT –LEFT WINGINTERNAL – ZONAL (GVI):WING LE TO FRONT SPARCOMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front sparcompartment. (WBL 128.5 to ILES 302 and ILES 630.72 toWBL 470).INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-5157-816-01LEFT WINGKRUEGER FLAP(11 THRU 13)EXTERNAL – ZONAL (GVI): LEFT WING KRUEGER FLAP(11 THRU 13)General Visual Inspection of the left wing Krueger flaps –(11 through 13).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)57-818-01WING LE TO FRONTSPAR – LEFT WINGEXTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR –LEFT WINGGeneral Visual Inspection of the left wing leading edge to front spar.(WBL 470 to WBL 834).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-820-01WING LE TO FRONTSPAR CAVITY –LEFT WINGEXTERNAL – ZONAL (GVI): WINGLE TO FRONT SPAR CAVITY –LEFT WINGGeneral Visual Inspection of the left wing leading edge to front sparcavity (ILES 693.5 to ILES 1116).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flap extended.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-822-01WING LE TO FRONTSPARCOMPARTMENT –LEFT WINGINTERNAL – ZONAL (GVI):WING LE TO FRONT SPARCOMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front sparcompartment (WBL 470 to ILES 693.5). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-824-01WING LE TO FRONTSPAR CAVITY –LEFT WINGINTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR CAVITY –LEFT WINGGeneral Visual Inspection of the left wing leading edge to front sparcompartment (ILES 1116.0 to WBL 834). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-52747-8/8F AIRWORTHINESS LIMITATIONS57-826-01LEFT WINGVARIABLE CAMBERFLAP(6 THRU 10)EXTERNAL – ZONAL (GVI): LEFT WING VARIABLE CAMBERFLAP (6 THRU 10)General Visual Inspection of the left wing variable camber flaps(6 through 10). (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)57-828-01WING LEADINGEDGE TO FRONTSPAR – LEFT WINGEXTERNAL – ZONAL (GVI): WINGLEADING EDGE TO FRONTSPAR – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front spar(WBL 834 to tip).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-830-01WING LE TO FRONTSPAR CAVITY –LEFT WINGEXTERNAL – ZONAL (GVI): WINGLE TO FRONT SPAR CAVITY –LEFT WINGGeneral Visual Inspection of the left wing leading edge to front sparcavity (OLES 1185 to OLES 1617.6). (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE Flaps extended.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-832-01WING LE TOFRONT SPARCOMPARTMENT –LEFT WINGINTERNAL – ZONAL (GVI):WING LE TO FRONT SPARCOMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front sparcompartment (WBL 834 to OLES 1185 and OLES 1617.6 to tip).INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-834-01LEFT WINGVARIABLE CAMBERFLAP(1E THRU 5)EXTERNAL – ZONAL (GVI): LEFT WING VARIABLE CAMBERFLAP (1E THRU 5)General Visual Inspection of the left wing variable camber flaps(1E through 5).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-5357-836-01RAKED WING TIP –LEFT WINGINTERNAL – ZONAL (GVI): RAKED WING TIP – LEFT WINGGeneral Visual Inspection of the left raked wing tip. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-838-01INBOARD MAINFUEL TANK –LEFT WINGINTERNAL – ZONAL (GVI): INBOARD MAIN FUEL TANK –LEFT WINGGeneral Visual Inspection of the left inboard main fuel tank (no. 2).(EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open accesspanels as required toperform inspection.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-840-01OUTBOARD MAINFUEL TANK – LEFTINTERNAL – ZONAL (GVI): OUTBOARD MAIN FUEL TANK – LEFTGeneral Visual Inspection of the left outboard main fuel tank (no. 1).(EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open accesspanels as required toperform inspection.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-844-01WING RESERVEFUEL TANK –LEFT WINGINTERNAL – ZONAL (GVI): WING RESERVE FUEL TANK –LEFT WINGGeneral Visual Inspection of the left wing reserve fuel tank. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open accesspanels as required toperform inspection.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-850-01WINGSURGE TANK –LEFT WINGINTERNAL – ZONAL (GVI): WING SURGE TANK – LEFT WINGGeneral Visual Inspection of the left wing surge tank.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-852-01WING DRY BAY –LEFT WINGINTERNAL – ZONAL (GVI): WING DRY BAY – LEFT WINGGeneral Visual Inspection of the left wing dry bay. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-54747-8/8F AIRWORTHINESS LIMITATIONS57-853-01FLAP TRACKFAIRING –LEFT WINGINTERNAL – ZONAL (GVI): FLAP TRACK FAIRING – LEFT WINGGeneral Visual Inspection of the left wing flap track fairing includingflap track and carriage.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC,See Note(1)2 YR2400 FCSee Note (2)57-854-01WINGREAR SPAR TOTRAILING EDGE –LEFT WINGEXTERNAL – ZONAL (GVI): WINGREAR SPAR TO TRAILINGEDGE – LEFT WINGGeneral Visual Inspection of the left wing rear spar to trailing edge(WBL 128.5 to WBL 515).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 1,SeeNote (1)2 YR2400 FCSee Note (2)57-856-01WING REAR SPARTO LG SUPPORTBEAM – LEFT WINGEXTERNAL – ZONAL (GVI): WINGREAR SPAR TO LG SUPPORTBEAM – LEFT WINGGeneral Visual Inspection of the left wing rear spar to landing gearsupport beam cavity (WBL 128.5 to inboard track of inboard trailingedge flap).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended and WLG doors open.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-858-01WING REAR SPARTO LG BEAMCOMPARTMENT –LEFT WINGINTERNAL – ZONAL (GVI): WINGREAR SPAR TO LG BEAMCOMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing rear spar to landing gearsupport beam compartment (Inboardtrack of inboard trailing edgeflap to WS 586.62). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-860-01WING LG SUPPORTBEAM ANDTE CAVITY –LEFT WINGEXTERNAL – ZONAL (GVI): WING LG SUPPORT BEAM AND TECAVITY – LEFT WINGGeneral Visual Inspection of theleft wing landing gear support beamand rear spar to trailing edge cavity (WBL 128.5 to WBL 445).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flap extended and spoilers raised.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-5557-862-01WING LG BEAM,REAR SPAR TO TECOMPARTMENT –LEFT WINGINTERNAL – ZONAL (GVI): WINGLG BEAM, REAR SPAR TO TECOMPARTMENT – LEFT WINGGeneral Visual Inspection of theleft wing landing gear support beamand rear spar to trailing edge compartment (WBL 128.5 to WBL 445).(EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-864-01WING REAR SPARTO INBOARDAILERON LE –LEFT WINGINTERNAL – ZONAL (GVI): WINGREAR SPAR TO INBOARDAILERON LE – LEFT WINGGeneral Visual Inspection of the left wing rear spar to inboard aileronleading edge (WBL 445 to WBL 515). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-866-01LEFT WINGINBOARD TE FLAPSEXTERNAL – ZONAL (GVI): LEFT WING INBOARD TE FLAPSGeneral Visual Inspection of the left wing inboard trailing edge flaps.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC,SeeNote (1)2 YR2400 FCSee Note (2)57-870-01WING REAR SPARTO TRAILING EDGE– LEFT WINGEXTERNAL – ZONAL (GVI): WINGREAR SPAR TO TRAILINGEDGE – LEFT WINGGeneral Visual Inspection of the left wing rear spar to trailing edge(WBL 515 to WBL 849).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-872-01WING REAR SPARTO TE CAVITY –LEFT WINGEXTERNAL – ZONAL (GVI): WINGREAR SPAR TO TE CAVITY –LEFT WINGGeneral Visual Inspection of the left wing rear spar to trailing edgecavity (WBL 515 to WBL 849).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended and spoilers raised.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-876-01LEFT WINGOUTBOARDTE FLAPEXTERNAL – ZONAL (GVI): LEFT WING OUTBOARD TE FLAPGeneral Visual Inspection of the left wing outboard trailing edge flap.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flap extended.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC,SeeNote (1)2 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-56747-8/8F AIRWORTHINESS LIMITATIONS57-878-01WINGREAR SPAR TOTRAILING EDGE –LEFT WINGEXTERNAL – ZONAL (GVI): WINGREAR SPAR TO TRAILINGEDGE – LEFT WINGGeneral Visual Inspection of the left wing rear spar to trailing edge(WBL 849 to WBL 1244).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-880-01WINGREAR SPAR TO TECOMPARTMENT –LEFT WINGINTERNAL – ZONAL (GVI):WING REAR SPAR TOTE COMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing rear spar to trailing edgecompartment (WBL 849 to WBL 1244).INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-882-01WINGREAR SPAR TO TECOMPARTMENT –LEFT WINGINTERNAL – ZONAL (GVI):WING REAR SPAR TOTE COMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing rear spar to trailing edgecompartment (WBL 849 to WBL 1244). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-888-01WING LE TO FRONTSPAR – RIGHTWINGEXTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR –RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front spar(WBL 128.5 to WBL 470).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-890-01WING LE TO FRONTSPAR CAVITY –RIGHT WINGEXTERNAL – ZONAL (GVI): WINGLE TO FRONT SPAR CAVITY –RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front sparcavity (ILES 302 to ILES 630.72) and including ram air turbinecompartment.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-5757-892-01WING LE TOFRONT SPARCOMPARTMENT –RIGHT WINGINTERNAL – ZONAL (GVI):WING LE TO FRONT SPARCOMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front sparcompartment (ILES 630.72 to WBL 470). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-894-01WING LE TOFRONT SPARCOMPARTMENT –RIGHT WINGINTERNAL – ZONAL (GVI):WING LE TO FRONT SPARCOMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front sparcompartment (WBL 128.5 to ILES 302 and ILES 630.72 toWBL 470).INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-896-01RIGHT WINGKRUEGER FLAP(14 THRU 16)EXTERNAL – ZONAL (GVI): RIGHT WING KRUEGER FLAP(14 THRU 16)General Visual Inspection of the right wing Krueger flaps(14 through 16).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)57-898-01WING LE TO FRONTSPAR – RIGHTWINGEXTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR –RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front spar(WBL 470 to WBL 834).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-900-01WING LE TO FRONTSPAR CAVITY –RIGHT WINGEXTERNAL – ZONAL (GVI): WINGLE TO FRONT SPAR CAVITY –RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front sparcavity (ILES 693.5 to ILES 1116).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE Flaps extended.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-58747-8/8F AIRWORTHINESS LIMITATIONS57-902-01WING LE TOFRONT SPARCOMPARTMENT –RIGHT WINGINTERNAL – ZONAL (GVI):WING LE TO FRONT SPARCOMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front sparcompartment (WBL 470 to ILES 693.5). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-904-01WING LE TO FRONTSPAR CAVITY –RIGHT WINGINTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR CAVITY –RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front sparcavity (ILES 1116.0 to WBL 834). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-906-01RIGHT WINGVARIABLE CAMBERFLAP (17 THRU 21)EXTERNAL – ZONAL (GVI): RIGHT WING VARIABLE CAMBERFLAP (17 THRU 21)General Visual Inspection of the right wing variable camber flaps(17 through 21). (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)57-908-01WINGLEADING EDGE TOFRONT SPAR –RIGHT WINGEXTERNAL – ZONAL (GVI): WINGLEADING EDGE TO FRONTSPAR – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front spar(WBL 834 to Tip).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-910-01WING LE TO FRONTSPAR CAVITY –RIGHT WINGEXTERNAL – ZONAL (GVI): WINGLE TO FRONT SPAR CAVITY –RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front sparcavity (OLES 1185 to OLES 1617.6). (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-5957-912-01WING LE TOFRONT SPARCOMPARTMENT –RIGHT WINGINTERNAL – ZONAL (GVI):WING LE TO FRONT SPARCOMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front sparcompartment (WBL 834 to OLES 1185 and OLES 1617.6 to tip).INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-914-01RIGHT WINGVARIABLE CAMBERFLAP (22 THRU26E)EXTERNAL – ZONAL (GVI): RIGHT WING VARIABLE CAMBERFLAP (22 THRU 26E)General Visual Inspection of the right wing variable camber flaps(22 through 26E).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)57-916-01RAKED WING TIP –RIGHT WINGINTERNAL – ZONAL (GVI): RAKED WING TIP – RIGHT WINGGeneral Visual Inspection of the right raked wing tip. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-918-01INBOARD MAINFUEL TANK(NO. 3) –RIGHT WINGINTERNAL – ZONAL (GVI): INBOARD MAIN FUEL TANK (NO. 3) –RIGHT WINGGeneral Visual Inspection of the right inboard main fuel tank (no. 3).(EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open accesspanels as required toperform inspection.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-920-01OUTBOARD MAINFUEL TANK (NO. 4)– RIGHT WINGINTERNAL – ZONAL (GVI): OUTBOARD MAIN FUEL TANK (NO. 4)– RIGHT WINGGeneral Visual Inspection of the right outboard main fuel tank (no. 4).(EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open accesspanels as required toperform inspection.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-60747-8/8F AIRWORTHINESS LIMITATIONS57-924-01WING RESERVEFUEL TANK –RIGHT WINGINTERNAL – ZONAL (GVI): WING RESERVE FUEL TANK –RIGHT WINGGeneral Visual Inspection of the right wing reserve fuel tank. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open accesspanels as required toperform inspection.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-930-01WINGSURGE TANK –RIGHT WINGINTERNAL – ZONAL (GVI): WING SURGE TANK – RIGHT WINGGeneral Visual Inspection of the right wing surge tank.INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-932-01WING DRY BAY –RIGHT WINGINTERNAL – ZONAL (GVI): WING DRY BAY – RIGHT WINGGeneral Visual Inspection of the right wing dry bay. (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 16 YR7200 FCSee Note (2)57-933-01FLAP TRACKFAIRING –RIGHT WINGINTERNAL – ZONAL (GVI): FLAP TRACK FAIRING – RIGHT WINGGeneral Visual Inspection of the right wing flap track fairingsincluding flap tracks.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: With TE flaps extended.INTERNAL – ZONAL (GVI)20,000 FC20,000 FC,SeeNote (1)2 YR2400 FCSee Note (2)57-934-01WINGREAR SPAR TOTRAILING EDGE –RIGHT WINGEXTERNAL – ZONAL (GVI): WINGREAR SPAR TO TRAILINGEDGE – RIGHT WINGGeneral Visual Inspection of the right wing rear spar to trailing edge(WBL 128.5 to WBL 515).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-936-01WING REAR SPARTO LG SUPPORTBEAM –RIGHT WINGEXTERNAL – ZONAL (GVI): WINGREAR SPAR TO LG SUPPORTBEAM – RIGHT WINGGeneral Visual Inspection of the right wing rear spar to landing gearsupport beam cavity (WBL 128.5 to inboard track of inboard trailingedge flap).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended and WLG doors open.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-6157-938-01WING REAR SPARTO LG BEAMCOMPARTMENT –RIGHT WINGINTERNAL – ZONAL (GVI): WINGREAR SPAR TO LG BEAMCOMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing rear spar to landing gearsupport beam compartment (Inboardtrack of inboard trailing edgeflap to WS 586.62). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-940-01WING LG SUPPORTBEAM ANDTE CAVITY –RIGHT WINGEXTERNAL – ZONAL (GVI): WING LG SUPPORT BEAM ANDTE CAVITY – RIGHT WINGGeneral Visual Inspection of the right wing landing gear supportbeam and rear spar to trailing edge cavity (WBL 128.5 to WBL 445).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended and spoilers raised.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-942-01WING LGBEAM&REAR SPARTO TECOMPARTMENT –RIGHT WINGINTERNAL – ZONAL (GVI): WING LG BEAM&REAR SPAR TOTE COMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing landing gear supportbeam and rear spar to trailingedge compartment (WBL 128.5 toWBL 445). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-944-01WING REAR SPARTO INBOARDAILERON LE –RIGHT WINGINTERNAL – ZONAL (GVI): WINGREAR SPAR TO INBOARDAILERON LE – RIGHT WINGGeneral Visual Inspection of theright wing to inboard aileron leadingedge (WBL 445 to WBL 515). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-946-01RIGHT WINGINBOARD TE FLAPSEXTERNAL – ZONAL (GVI): RIGHT WING INBOARD TE FLAPSGeneral Visual Inspection of the right wing inboard trailing edge flap.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC,SeeNote (1)2 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-62747-8/8F AIRWORTHINESS LIMITATIONS57-948-01WINGREAR SPAR TOTRAILING EDGE –RIGHT WINGEXTERNAL – ZONAL (GVI): WINGREAR SPAR TO TRAILINGEDGE – RIGHT WINGGeneral Visual Inspection of the right wing rear spar to trailing edge(WBL 515 to WBL 849).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-950-01WING REAR SPARTO TE CAVITY –RIGHT WINGEXTERNAL – ZONAL (GVI): WINGREAR SPAR TO TE CAVITY –RIGHT WINGGeneral Visual Inspection of the right wing rear spar to trailing edgecavity (WBL 515 to WBL 849).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended and spoilers raised.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)57-954-01RIGHT WINGOUTBOARDTE FLAPEXTERNAL – ZONAL (GVI): RIGHT WING OUTBOARD TE FLAPGeneral Visual Inspection of the right wing outboard trailing edgeflap.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flap extended.EXTERNAL – ZONAL (GVI)20,000 FC20,000 FC2 YR2400 FCSee Note (2)57-956-01WINGREAR SPAR TOTRAILING EDGE –RIGHT WINGEXTERNAL – ZONAL (GVI): WINGREAR SPAR TO TRAILINGEDGE – RIGHT WINGGeneral Visual Inspection of the right wing rear spar to trailing edge(WBL 849 to WBL 1244).INTERVAL NOTE: Whichever comes first.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)57-958-01WING REAR SPARTO TECOMPARTMENT –RIGHT WINGINTERNAL – ZONAL (GVI):WING REAR SPAR TOTE COMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing rear spar to trailing edge,compartment (WBL 849 to WBL 1244).INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 12 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-6357-960-01WINGREAR SPAR TO TECOMPARTMENT –RIGHT WINGINTERNAL – ZONAL (GVI):WING REAR SPAR TOTE COMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing rear spar to trailing edgecompartment (WBL 849 to WBL 1244). (EZAP)INTERVAL NOTE: Whichever comes first.INTERNAL – ZONAL (GVI)FLS, SeeFigure 1FLS, SeeFigure 14 YR4800 FCSee Note (2)71-804-01NOSE COWL,ENGINENO. 1, 2, 3, 4EXTERNAL – ZONAL (GVI): NOSE COWL, ENGINE NO. 1, 2, 3, 4General Visual Inspection of the nose cowl, engine no. 1, 2, 3, 4.(EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open fan cowls.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 2FLS, SeeFigure 22 YR2400 FCSee Note (2)71-806-00ENGINEINSTALLATIONNO. 1, 2, 3, 4EXTERNAL – ZONAL (GVI): ENGINEINSTALLATION NO. 1, 2, 3, 4General Visual Inspection of the engine no. 1, 2, 3, 4. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open fancowls and T/R cowls.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 2FLS, SeeFigure 22 YR2400 FCSee Note (2)71-808-01INNER FACE OFFAN COWL ENGINENO. 1, 2, 3, 4EXTERNAL – ZONAL (GVI): INNERFACE OF FAN COWL ENGINENO. 1, 2, 3, 4General Visual Inspection of the inner face of fan cowl no. 1, 2, 3, 4.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open fan cowls.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 2FLS, SeeFigure 22 YR2400 FCSee Note (2)71-810-01INNER FACE OFT/R COWL ENGINENO. 1, 2, 3, 4EXTERNAL – ZONAL (GVI): INNERFACE OF T/R COWL ENGINENO. 1, 2, 3, 4General Visual Inspection of the inner face of thrust reverser cowlno. 1, 2, 3, 4. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open T/R cowls.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 2FLS, SeeFigure 22 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-64747-8/8F AIRWORTHINESS LIMITATIONSTABLE NOTES:1. For L/N 1420 airplane, use de-escalation threshold of 16,000 flight cycles.2. See "TASK DESCRIPTION" for note(s) related to access and/or interval requirements.71-812-01THRUSTREVERSER ANDCOWL ENGINE NO.1, 2, 3, 4EXTERNAL – ZONAL (GVI): THRUST REVERSER AND COWLENGINE NO. 1, 2, 3, 4General Visual Inspection of the thrust reverser and cowl no. 1, 2,3, 4.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Deploy T/R and open fan cowl.EXTERNAL – ZONAL (GVI)FLS, SeeFigure 2FLS, SeeFigure 22 YR2400 FCSee Note (2)71-816-01EXHAUST NOZZLEINNER AND FWDFACES INCLUDINGTHE CENTERVENT TUBEEXTERNAL – ZONAL (GVI): EXHAUST NOZZLE INNER AND FWDFACES INCLUDING THE CENTER VENT TUBEGeneral Visual Inspection of the inner and forward faces of exhaustnozzle including the center venttube engine no. 1, 2, 3, 4.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open TR cowlsEXTERNAL – ZONAL (GVI)FLS, SeeFigure 2FLS, SeeFigure 22 YR2400 FCSee Note (2)POST-THRESHOLD INTERVAL TABLEMPD ITEMNUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVELDE-ESCALATIONTHRESHOLDPOSTTHRESHOLDINTERVAL747-8747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-65REMOVAL OF EXCESS SEALANT WHEN INSPECTING1. In areas where a Supplemental Structural Inspection DTR Check Form visual inspection is prevented due to sealant, remove anyfastener cap, fillet orbrush sealant that extends beyond 0.20" around the fastener at locations that are to be inspected. Remove any additional sealant which impairs visibilityof the structure adjacentto the fastener cap,fillet or brush sealant.2. To remove the excess sealant or remove and re-apply the sealant, use the appropriate procedure,including application of proper tools per747 AMM 51-31-01 (or 28-11-00 for fuel tank). Do not use a metal blade or knife. Check to make sure that scoring of the part did not occur.3. The following Structural Significant Items (SSIs) require fastener cap, fillet or brush sealantthat extends beyond 0.20" tobe removed for baselinemaintenance visual inspections (see 747-8/-8F MPD Sections 2 and 3) at or prior to reaching the listed thresholds, as noted inthe Excess Sealanttable below.4. Figures 1 and 2 are the same as for the FLS Threshold Curve.EXCESS SEALANT TABLESSI TITLE MPD ITEM NO. THRESHOLDINSTALLATION DRAWINGDESCRIPTION OF AREA WHERE INSPECTIONS NEEDTO BE PERFORMEDNUMBERTITLEFuselage –Bulkhead BS 100053-420-0153-864-0153-866-0120,000 FC 110U0210 Wing to Body Attachment Installation Remove excess sealant extending more than 0.2" beyond thefastener head or nut which may obstruct Pickle Fork andlower chord inspection.Fuselage –Bulkhead BS 148053-430-0153-852-0120,000 FC 65B15085 Bulkhead Installation – Aft Wheel WellLower STA 1480Remove excess sealant extending more than 0.2" beyond thefastener head or nut which may obstruct upper chord andlower cap fitting inspection.Fuselage – UnderWing Longeron53-460-00 20,000 FC 65B11581 Drag Fitting Installation – Lower Panel,Wing Center SectionRemove excess sealant extending more than 0.2" beyond thefastener head or nut which may obstruct Pickle Fork andlower chord inspection.Fuselage – OverWing LongeronExtensions Forwardof BS 1000 and Aftof BS 148053-460-00 20,000 FC 65B15255 Longeron Extension Fitting Installation Remove excess sealant extending more than 0.2" beyond thefastener head or nut which may obstruct the over wheel welllongeron extension inspection.MAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-66747-8/8F AIRWORTHINESS LIMITATIONSHorizontal Stab.Upper Skin –Stringer55-830-0155-832-01FLS,See Figure 1182U3000 PANEL MINOR ASSY – OTBD UPR,TORQUE BOX, HORIZ STAB.Along Stringer 1 to 4 between Rib 2 to Rib 5Along Stringer 6 & 7 (vent stringer) from Rib 3 to Rib 955-828-01 FLS,See Figure 1181U3000 Upper Skin Instl – Center Sect,Horiz StabZ-stringers 1-4 in center sectionHorizontal Stab.Front Spar55-828-01 FLS,See Figure 1181U2010 FRONT SPAR INSTL –CENTER SECT.Center section front spar upper chord to skin joint betweenBL 0.0 to SOBHorizontal Stab.Rear Spar55-828-0153-920-01FLS,See Figure 1182U1000 SPAR INSTL, REAR –HORIZONTAL STAB.Center Section Rear Spar Upper chord - skin to chord andweb to chord joints - sealant common to spar chord flanges -internal and external- from BL 14.5 to BL 29Horizontal Stab.Side of Body Splice55-816-0155-824-01FLS,See Figure 1182U5200 Hinge Rib Assy – OUTBDHORIZ STABOutboard SOB upper Joint between the rear spar chord, weband splice fitting - web flange from outside the stabilizer55-828-01 FLS,See Figure 1Center section upper Front Spar Chord and skin splice joint55-830-0155-832-01FLS,See Figure 1Outboard upper Front Spar Chord and skin splice jointFLS,See Figure 1All outboard upper stringer terminations between Rib 2 andRib 3.55-830-0155-832-0155-828-01FLS,See Figure 1Outboard and inboard splice stringer terminationsWing Center SectionLower Panel57-802-01 FLS,See Figure 1111U4000 LOWER PANEL INSTL –WING CENTER SECTIONSkin-to-stringer fasteners & filletseals at stringers 2-4, 6-9,11-13, 16-18, 20-23. Skin-to-chord fasteners & fillet sealalong front spar chordWing Center SectionUpper Panel57-802-01 FLS,See Figure 1111U3000 UPPER PANEL INSTALLATION –WING CENTER SECTIONSkin-to-stringer fasteners & fillet seals at stringers 1-13,15-19, 21-27, 29-33, exceptnot required at floor beamconnectionEXCESS SEALANT TABLESSI TITLE MPD ITEM NO. THRESHOLDINSTALLATION DRAWINGDESCRIPTION OF AREA WHERE INSPECTIONS NEEDTO BE PERFORMEDNUMBERTITLEMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-67Outboard WingLower Panel57-425-0057-840-0157-920-0157-844-0157-924-0157-838-0157-918-0157-850-0157-930-0157-852-0157-932-01FLS,See Figure 1112U4300 PANEL INSTALLATION, INSPARWING, LOWER LHAll Skin-to-stringer fasteners & fillet seals at stringers locatedunder the outboard strut fairingAll Skin-to-stringer fasteners& fillet seals at stringersadjacent to spar chord in exposed panel area.Skin-to-stringer fasteners & filletseals at stringers outboardof Rib 45Skin-to-chord fasteners & fillet seal along front spar chord atlongitudinal splicesOutboard WingUpper Panel57-838-0157-918-0157-840-0157-920-0157-844-0157-924-0157-850-0157-930-0157-852-0157-932-01FLS,See Figure 1112U3300 PANEL INSTALLATION, INSPARWING, UPPERSkin-to-stringer fasteners & fillet seals at stringers 1-13,15-26, 28-33, excludes fuel baffles and seal damsOutboard WingRear Spar57-838-0157-918-0157-856-0157-936-01FLS,See Figure 1112U1101 REAR SPAR ASSEMBLY Fillet seal at edge of fuel doubler, WS 390 and WS 425.EXCESS SEALANT TABLESSI TITLE MPD ITEM NO. THRESHOLDINSTALLATION DRAWINGDESCRIPTION OF AREA WHERE INSPECTIONS NEEDTO BE PERFORMEDNUMBER TITLEMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-68747-8/8F AIRWORTHINESS LIMITATIONS5. General Notes:Refer to AMM 51-31-01 for general sealant removal and application.Refer to AMM 28-11-00 (Task 28-11-300-802) for sealant (BMS 5-45) inside the fuel tank removal and application.Refer to AMM 28-11-00 (Task 28-11-300-803) for secondary fuel barrier sealant (BMS 5-81, Type II) outside the fuel tank removaland application.If sealant is removed inside the fuel tank for inspection, care must be taken to remove any sealant debris in the fuel tank. Locations where sealantis removed for inspections must have the sealant restored todrawing or AMM requirements (andany applicable Service Bulletinsor repairinstructions) after completion ofthe inspections. Sealant of fuel tank fastenersmust comply with maintenance requirements setforth in the 747-8Special Compliance Items/Airworthiness Limitations document D011U721-02-04, as applicable.MAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-69SUPPLEMENTAL STRUCTURALINSPECTION REQUIREMENTSThe table below lists the Airworthiness Limitation Supplemental Structural Inspection requirements. Each item is listed by SSINumber, DTR Check FormTitle, DTR Location, and Airplane Applicability/Threshold. There are corresponding DTR Check Forms in D011U721-05 for each itemlisted in the tablewhere a DTR Check Form title is specified.Where there is more than one listing for a given SSI Number, the DTR Check Form Model-Series is theunique identifier.Airplane applicability is listed as shown below:• 747-8 = All 747-8 Passenger Airplanes, including the 747-8 Intercontinental and 747-8 VIP• 747-8F = All 747-8 Freighter AirplanesAirworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8F27-41-F70B Horizontal Stabilizer Trim Actuator Ballscrew and Ballnut 20,000 20,00052-13-F34A Upper Deck Emergency Exit Doors Stop Fittings 20,000 N/A52-23-F34A Crew Service Door Stop Fittings N/A 20,00052-31-F38A Nose Cargo Door Hinge Fittings Hinge Fitting LugN/A20,000(3)52-31-F38B Nose Cargo Door, C-2 & BS 234Closure FramesOuter Chords N/A20,000(3)52-31-F38C Nose Cargo Door LatchesLatchFitting to Intercostal Attachment N/A20,000(3)52-31-F38D Nose Cargo Door, C-2 & BS 234Closure FramesInner Chords N/A20,000(3)52-31-F38E Nose Cargo Door Tension Tie Connection to Body Station 234 Frame N/A20,000(3)52-32-F37A.3 Main Deck Side Cargo DoorOuter Skin and fasteners aroundPressure Vent Panel andWindow CutoutsN/A20,000MAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-70747-8/8F AIRWORTHINESS LIMITATIONS52-32-F37B.2 Main Deck Side Cargo DoorOuter Skin and Frame Outer Chordat HingeN/A20,000(3)52-32-F37C.1 Main Deck Side Cargo DoorLatch Support Fitting Lugs All10 locationsN/A20,000(3)52-32-F37C.3 Main Deck Side Cargo DoorLatch Frame Inner Chord at LatchSupport Fitting Splice IntercostalN/A20,000(3)52-32-F37C.4 Main Deck Side Cargo DoorCam LatchesN/A20,000(3)52-34-F31A.4 Forward and Aft Lower LobeCargo DoorsOuter skin Lap Splice, LowerFastener Row20,000(3)20,000(3)52-34-F31B.2 Forward and Aft Lower LobeCargo DoorsOuter Skin and Frame Outer Chords atattachments to Main Hinge Segments20,000(3)20,000(3)52-34-F31B.3 Forward and Aft Lower LobeCargo DoorsOuter Skin at Upper Beam attachment,Lowest Row of Fasteners20,000(3)20,000(3)52-34-F31B.4 NONEFwd and Aft Lower Lobe Cargo DoorHinge Segments20,00020,000 From the exterior of the airplane,perform a detailed inspection of theattachment bolts common to theforward and aft lower lobe cargodoor upper hinge segments attachedto the cargo door. Apply between 10in-lbs and 20 in-lbs of torque to eachfastener head common to the hingesegments. If any discrepancies arefound, such as loose or failedfasteners, contact Boeing forinstructions before further flight.Repeat this inspection every 7,200Flight Cycles52-34-F31C.1 Forward and Aft Lower LobeCargo DoorsLatch Support Fitting Lugs20,000(3)20,000(3)52-34-F31C.3 Forward and Aft Lower LobeCargo DoorsLatch Frame Inner Chord at Splice withLatch support Fitting20,000(3)20,000(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-7152-34-F31C.4 Forward and Aft Lower LobeCargo DoorsCam Latches20,000(3)20,000(3)52-36-F32A Bulk Cargo DoorStop Fittings and Latch Probes20,00020,00053-00-F01A Bulkhead BS 140Web20,00020,00053-00-F01B Bulkhead BS 140Vertical Beam20,00020,00053-00-F02A Bulkhead BS 260Outer Chord from S-39 to S-45 L & R N/A20,000(3)53-00-F02B Bulkhead BS 260Outer Chord from S-39 to S-45 L & R20,000(3)N/A53-00-F02D Bulkhead BS 260Periphery of NGWW Forward CornerReinforcing Doubler – LHS and RHS20,000(3)20,000(3)53-00-F02G Bulkhead BS 260BS 260, Below S-2220,00020,00053-00-F03 Bulkhead BS 340BS 340, Below S-2220,00020,00053-00-F04A Bulkhead BS 400Nose Gear Wheel Well Cutout AftCorners BS 380 to BS 400, S-44to S-46.520,000(3)20,000(3)53-00-F04B Bulkhead BS 400Nose Gear Wheel Well Cutout, BS 400Bulkhead Outer Chord from S-41Lto S-41R20,000(3)20,000(3)53-00-F04C Bulkhead BS 400BS 400, WL 173, BL 10 to BL 1620,00020,00053-00-F04D Bulkhead BS 400BS 400, LBL and RBL 40, fromWL 124 to WL 130FLS,See Figure 2(3)FLS,See Figure 2(3)53-00-F04E Bulkhead BS 400BS 400, below S-2220,00020,00053-00-F05A Nose Gear Wheel Well – Top andSide PanelsFloor Beam Connections, BS 360 andBS 380, and Sidewall Panels fromBS 340 to BS 40020,00020,00053-00-F05B Nose Gear Wheel Well – Top andSide PanelsConnection Between Top and SidePanels, BS 260 Bulkhead to BS 340Bulkhead20,00020,000Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-72747-8/8F AIRWORTHINESS LIMITATIONS53-00-F05C Nose Gear Wheel Well – Top andSide PanelsTorque Box, BS 340 to BS 400 20,000 20,00053-00-F06A BS 1000 Bulkhead Lower Chord at S-45L & S-45R Splice20,000(3)20,000(3)53-00-F06B BS 1000 BulkheadLower Chord below main deck floor 20,00020,00053-00-F06C BS 1000 BulkheadLower lobe skin below main deck floor 20,00020,00053-00-F08 Stub Beams (Overwing and OverWheel Well)Stub Beam to Frame Attachment,BS 1020 through BS 1460, LHSand RHS20,00020,00053-00-F09A BS 1241 BulkheadPickle Fork Fitting Inner Chord atCargo Intercostal Attachment at S-26N/A20,000(3)53-00-F09B BS 1241 BulkheadStrap from S-23 to Longeron Splice atWing Upper Surface20,000(3)20,000(3)53-00-F09C BS 1241 BulkheadOuter Chord from S-23 to LongeronSplice At Wing Upper Surface20,000(3)20,000(3)53-00-F09D BS 1241 BulkheadPickle Fork Outer Chord/Strap underWing Upper Chord Kick Fitting,WL 164.920,000(3)20,000(3)53-00-F09E Bulkhead BS 1241Over Wheel Well Longeron at WL 17320,000(3)20,000(3)53-00-F09F Bulkhead BS 1241Over Wheel Well Longeron at WL 17320,000(3)20,000(3)53-00-F10B.1 Bulkhead BS 1350Lower Side Frame Joint at WL 15820,00020,00053-00-F10B.2 Bulkhead BS 1350Lower Side Frame from S-21 TO S-28 20,00020,00053-00-F11A BS 1480 BulkheadLower Cap Fitting from S-34 to S-3920,000(3)20,000(3)53-00-F11B BS 1480 BulkheadUpper Chord between BL 98.6 andBL 57.520,00020,00053-00-F11C BS 1480 BulkheadUpper Chord Vertical Flangeat BL 75.9N/A20,000(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-7353-00-F11D.1 Bulkhead BS 1480Bulkhead Outer Chord, from S-32to S-3420,000(3)20,000(3)53-00-F11D.2 Bulkhead BS 1480Bulkhead Outer Chord Splices,from S-32 to S-3420,00020,00053-00-F16C Over Wheel Well LongeronOver Wheel Well Longeron SpliceBetween BS 1200 and BS 128520,00020,00053-00-F17C Crew Cab Window Posts, Sillsand Skins#1 Post Typical(Upper Sill to Lower Sill)20,000(3)20,000(3)53-00-F17D Crew Cab Window Posts, Sillsand Skins#1 Post at Upper Sill Intersection20,000(3)20,000(3)53-00-F17E Crew Cab Window Posts, Sillsand Skins#2 Post at Upper and Lower SillIntersections20,000(3)20,000(3)53-00-F17F Crew Cab Window Posts, Sillsand Skins#3 Post at Upper and Lower SillIntersections20,000(3)20,000(3)53-00-F18A Nose Gear Wheel Well Cutout BS 340 Corner at Side Paneland Bulkhead20,000(3)20,000(3)53-00-F19A Upper Deck Floor Beams, Stanchionsand Tension TiesBS 1120 to BS 1220 Tension Ties20,000(3)N/A53-00-F19B.1 Upper Deck Floor Beams, Stanchionsand Tension TiesBS 1120 to BS 1220 Tension Tie atFrame Joint LHS & RHS20,000(3)N/A53-00-F19B.2 Upper Deck Floor Beams, Stanchionsand Tension TiesBS 1120 to BS 1220 Frame at TensionTie LHS & RHS20,000 N/A53-00-F19C Upper Deck Floor Beams, Stanchionsand Tension TiesBS 720 to BS 940 Tension Ties N/A20,000(3)53-00-F19D Upper Deck Floor Beams, Stanchionsand Tension TiesBS 720 to BS 940 Tension Ties N/A20,000(3)53-00-F19E Upper Deck Floor Beams, Stanchionsand Tension TiesBS 720 to BS 940 Tension Ties N/A 20,000Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-74747-8/8F AIRWORTHINESS LIMITATIONS53-00-F19F Upper Deck Floor Beams, Stanchionsand Tension TiesUpper Chord Mid-Span AlongFloor Beam20,000(3)20,000(3)53-00-F19G Upper Deck Floor Beams, Stanchionsand Tension TiesUpper Deck Floor Beams 20,000 20,00053-00-F19H Upper Deck Floor Beams, Stanchionsand Tension TiesFloor Beam Upper ChordOutboard Span20,000(3)20,000(3)53-00-F19I Upper Deck Floor Beams, Stanchionsand Tension TiesConnection to Frame, BS 460 toBS 840 and BS 880 to BS 92020,000(3)N/A53-00-F19J Upper Deck Floor Beams, Stanchionsand Tension TiesConnection to Frame, BS 540 toBS 700N/A20,000(3)53-00-F19K Upper Deck Floor Beams, Stanchionsand Tension TiesFloor Beam Upper Chord at FrameConnection, BS 540 to BS 700N/A 20,00053-00-F20A.1 Upper Deck Floor Cutout Shear Websand IntercostalsUpper and Lower Chord Mid-Spans ofUpper Deck Floor Beams20,000(3)N/A53-00-F20A.2 Upper Deck Floor Cutout Shear Websand IntercostalsUpper and Lower Chord Mid-Spans ofUpper Deck Floor BeamsN/A20,000(3)53-00-F20B Upper Deck Floor Cutout Shear Websand IntercostalsUpper Deck Floor Beam Upper Chordat Frame Connection20,000(3)N/A53-00-F20C.1 Upper Deck Floor Cutout Shear Websand IntercostalsUpper Deck Floor Beam Upper Chordat Strap/Frame Connection BS 480and BS 520N/A20,000(3)53-00-F20C.2 Upper Deck Floor Cutout Shear Websand IntercostalsUpper Deck Floor Beam Upper Chordat Strap/Frame Connection BS 480and BS 520N/A20,000(3)53-00-F20D.1 Upper Deck Floor Cutout Shear Websand IntercostalsHeader Beam Upper Chord Mid-SpanBS 480 and BS 520N/A20,000(3)53-00-F20D.2 Upper Deck Floor Cutout Shear Websand IntercostalsHeader Beam Upper Chord at MidSpan BS480 and BS520 at Floor PanelClipnutsN/A20,000(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-7553-00-F20E Upper Deck Floor Cutout Shear Websand IntercostalsBS 480 Upper Chord of Upper DeckFloor Beam at Floor CutoutsN/A20,000(3)53-00-F21D.1 Side Skin PanelsFrames Above S-26 (Top of Main DeckFloor), from BS 160 to BS 52030,00030,00053-00-F21D.2 Side Skin PanelsFrames Above S-26 (Top of Main DeckFloor), from BS 520 to BS 98025,000N/A53-00-F21D.3 Side Skin PanelsFrames Above S-26 (Top of Main DeckFloor), from BS 520 to BS 980+160N/A22,00053-00-F21D.4 Side Skin PanelsFrames Above S-26 (Top of Main DeckFloor), from BS 1480+20 to BS 236025,00025,00053-00-F22 Crown Skin Crease Panel andBack-Up StructureBS 940 to 980+20, S-8L to S-8R (747-8F) BS 1220 to 1283, S-8L to S-8R(747-8)20,00020,00053-00-F23A.3 Crown Skin PanelsCrown Skins Under Large AntennaRadomes20,00020,00053-00-F23B.9 Crown Skin Panels747-8: BS1101 to BS2360747-8F: BS633 to BS236020,00020,00053-00-F23C.1 Crown Skin PanelsStringers in Sections 42, 44, and 4622,000(3)22,000(3)53-00-F23C.2 Crown Skin PanelsBS 340 to BS 520, S-4 through S-5A25,000(3)25,000(3)53-00-F23C.3 Crown Skin PanelsBS 200 to BS 220, S-14 through S-14D N/A25,000(3)53-00-F23C.4 Crown Skin PanelsBS 200 to BS 220, S-13A throughS-14D25,000(3)N/A53-00-F24D.1 Lower Lobe Skin Panels Frames Below S-26 (Top of Main DeckFloor), Section 4130,000 30,00053-00-F24D.2 Lower Lobe Skin Panels Frames Below S-26 (Top of M/DFloor), Sections 42 and 4620,000 20,00053-00-F24E Lower Lobe Skin Panels Section 4220,000(3)20,000(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-76747-8/8F AIRWORTHINESS LIMITATIONS53-00-F25A.1 Skin Longitudinal SplicesSplice Outer Skin, Upper Row SpliceFasteners (Section 41)20,000(3)20,000(3)53-00-F25A.2 Skin Longitudinal SplicesSplice Outer Skin, Upper Row SpliceFasteners (Section 42)20,000(3)20,000(3)53-00-F25A.3 Skin Longitudinal SplicesSplice Outer Skin, Upper Row SpliceFasteners (Section 46)N/A20,000(3)53-00-F25A.4 Skin Longitudinal SplicesSplice Outer Skin, Upper Row SpliceFasteners (Section 46)20,000(3)N/A53-00-F25B.1 Skin Longitudinal Splices Splice Inner Skin, Lower Row SpliceFasteners (Section 41)20,000(3)20,000(3)53-00-F25B.2 Skin Longitudinal SplicesSplice Inner Skin, Lower Row SpliceFasteners (Section 42)20,000(3)20,000(3)53-00-F25B.3 Skin Longitudinal SplicesSplice Inner Skin, Lower Row SpliceFasteners (Section 46)N/A20,000(3)53-00-F25B.4 Skin Longitudinal SplicesSplice Inner Skin, Lower Row SpliceFasteners (Section 46)20,000(3)N/A53-00-F25C.1 Skin Longitudinal Splices S-4L from BS 1635 to BS 1880 N/A20,000(3)53-00-F25C.2 Skin Longitudinal SplicesS-4L from BS 1880 to BS 1960N/A20,000(3)53-00-F25D Skin Longitudinal SplicesRadius of Chem-mill Step Adjacent toSkin Longitudinal SpliceN/A22,000(3)53-00-F26A Skin-Stringer Circumferential Splices BS 1000 to BS 218120,000(3)20,000(3)53-00-F26B Skin-Stringer Circumferential Splices BS 1220 to BS 218120,000(3)20,000(3)53-00-F26C Skin-Stringer Circumferential Splices BS 1000 to BS 166020,000(3)20,000(3)53-00-F26D Skin-Stringer Circumferential Splices BS 1000 to BS 2181(747-8) andBS 980+20 to BS 2181 (747-8F)20,000 20,00053-00-F26E Skin-Stringer Circumferential Splices BS 1283, S-6L to S-6R (Internally)20,000(3)N/AAirworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-7753-00-F26F Skin-Stringer CircumferentialSplices BS 1283, S-6L to S-6R (Externally)20,000(3)N/A53-00-F27A Typical FramesSection 41 Frames at Upper DeckFloor Beam Interface: BS 260 toBS 52020,00020,00053-00-F27B NONEBS320 Crown Frame Affected by747-8-SRP-53-044114,000(6)14,000(6)See Service Bulletin 747-53-287553-00-F30A BS 2360 Circumferential Splice Fwd Side of BS 2360 Splice, from S-7Lto S-7R and S-13 to S-16 LHS and20,000 20,00053-00-F39A Lower Lobe Cargo Door Cutouts Edge Frames – Inner Chord20,000(3)20,000(3)53-00-F39B.2 Lower Lobe Cargo Door Cutouts Edge Frames – Outer Chord20,000(3)20,000(3)53-00-F39B.3 Lower Lobe Cargo Door Cutouts Edge Frames – Outer Chords20,000(3)20,000(3)53-00-F39B.4 Lower Lobe Cargo Door Cutouts Edge Frames – Outer Chords20,000(3)20,000(3)53-00-F39C.1 Lower Lobe Cargo Door Cutouts Skin and Strap at Hinge Support &Hinge Back-up Structure20,000(3)20,000(3)53-00-F39C.2 Lower Lobe Cargo Door Cutouts Hinge Support & Hinge Back-upStructure20,000 20,00053-00-F39D Lower Lobe Cargo Door Cutouts Latch Fittings at All Latch Locations inFwd and Aft LLCD Cutouts20,000 20,00053-00-F39E Lower Lobe Cargo Door Cutouts Fwd and Aft Lower Lobe Cargo DoorCutout Corners20,000(3)20,000(3)53-00-F39H Lower Lobe Cargo Door Cutouts Inner Chord of Main Sills20,000(3)20,000(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-78747-8/8F AIRWORTHINESS LIMITATIONS53-00-F39I NONEFwd and Aft Lower Lobe Cargo DoorHinge Segments20,00020,000 From the exterior of the airplane,perform a detailed inspection of theattachment bolts common to theforward and aft lower lobe cargodoor upper hinge segments attachedto the cargo door cutout upper sill.Apply between 10 in-lbs and 20 inlbs of torque to each fastener headcommon to the hinge segments. Ifany discrepancies are found, suchas loose or failed fasteners, contactBoeing for instructions before furtherflight. Repeat this inspection every7,200 Flight Cycles.53-00-F40A.1 Lower Lobe Bulk Cargo DoorCutout Edge Frame Inner Chord, BS 203420,000(3)20,000(3)53-00-F40A.2 Lower Lobe Bulk Cargo DoorCutout Edge Frame Inner Chord, BS 1980,Between S-39R and S-42R20,000(3)20,000(3)53-00-F40A.3 Lower Lobe Bulk Cargo DoorCutout Edge Frame Inner Chord, BS 1980Near S-37R20,000(3)N/A53-00-F40B Lower Lobe Bulk Cargo Door Cutout Edge Frame Outer Chord at BS 1980and BS 203420,000(3)20,000(3)53-00-F40C Lower Lobe Bulk Cargo Door Cutout Cutout Corners20,000(3)20,000(3)53-00-F40E Lower Lobe Bulk Cargo Door Cutout Upper Main Sill – Inner Chord20,000(3)20,000(3)53-00-F41 Main Deck Entry Door Cutouts Main Entry Door #1 Cutout20,00020,00053-00-F41A.1 Main Deck Entry Door Cutouts Edge Frame Inner Chords at BS 434,488, 854, 1664, 1720, and 228520,000(3)20,000(3)53-00-F41A.2 Main Deck Entry Door Cutouts Edge Frame Inner Chord at BS 800and BS 223120,000(3)N/A53-00-F41A.3 Main Deck Entry Door Cutouts Edge Frame Inner Chord at BS 80020,000(3)N/AAirworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-7953-00-F41B.1 Main Deck Entry Door Cutouts Edge Frame Outer Chord, BS 434from S-16 to S-2320,000(3)20,000(3)53-00-F41B.2 Main Deck Entry Door Cutouts Edge Frame Outer Chord, BS 434at S-1920,000(3)20,000(3)53-00-F41B.3 Main Deck Entry Door Cutouts Edge Frame Outer Chords at BS 800,BS 1664, and BS 223120,000(3)N/A53-00-F41C.1 Main Deck Entry Door Cutouts Main Entry Door #1, #2, #4, and #5Cutout Corners20,000(3)20,000(3)53-00-F41C.2 NONEMain Entry Door #1 Lower ForwardCutout Corner12,000(5)12,000(5)See Service Bulletin 747-53-286753-00-F41C.3 Main Deck Entry Door Cutouts Main Entry Door #3 Skin CutoutCornersFLS,See Figure 2(3)N/A53-00-F41D Main Deck Entry DoorCutouts Door Stop Backup Structure20,000(3)N/A53-00-F42A Upper Deck Crew Service Door CutoutStructureFrame Inner Chord and Web, BS 390and BS 420 from S-11R to S-14RN/A20,000(3)53-00-F42B Upper Deck Crew Service DoorCutout StructureSkin and Strap at Frame Outer Chord,BS 390 and BS 420 from S-6Rto S-12RN/A20,000(3)53-00-F42C.1 Upper Deck Crew Service DoorCutout StructureUpper Forward Skin Cutout Corner N/A20,000(3)53-00-F42C.2 Upper Deck Crew Service DoorCutout StructureUpper Aft, Lower Forward, and LowerAft Skin Cutout CornersN/A20,000(3)53-00-F43A Crew Emergency (Exit) HatchCutout StructureFrame Inner Chord at BS 360 andBS 380 from Str-0 to Str-4L20,000(3)20,000(3)53-00-F43B Crew Emergency (Exit) HatchCutout StructureSkin and Strap at Frame Outer ChordBS 360 and BS 380 from Str-1Lto Str-3L20,000(3)20,000(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-80747-8/8F AIRWORTHINESS LIMITATIONS53-00-F44A Electronic and Equipment AccessDoor CutoutsCutout Corners and EdgesAlong Frames20,000(3)20,000(3)53-00-F45B Main Deck Side Cargo Door Cutout Edge Frame Outer Chords, BS 1700and BS 1840N/A20,000(3)53-00-F45C Main Deck Side Cargo Door Cutout Latch Support FittingsN/A20,00053-00-F45F Main Deck Side Cargo Door Cutout Cutout CornersN/A20,000(3)53-00-F45H Main Deck Side Cargo Door Cutout Upper Main Sill Inner ChordN/A20,000(3)53-00-F45K.1 Main Deck Side Cargo Door Cutout Skin at S-9L between BS 1580 andBS 1640 and between BS 1900 andBS 1960N/A20,000(3)53-00-F45K.2 Main Deck Side Cargo Door Cutout S-9L between BS 1580 - 1640 andBS 1900 - 1960; S-27L between BS1580 - 1600 and BS 1900 - 1960N/A20,000(3)53-00-F45K.3 Main Deck Side Cargo Door Cutout S-4L from BS 1949 to BS 1979N/A20,000(3)53-00-F46 Section 48 Jackscrew Support Clevis Fitting20,000(3)20,000(3)53-00-F48A Section 48 Aft Pressure Bulkhead Web at Circumferential Y-ChordAttachment above WL 19420,000(3)20,000(3)53-00-F48B Section 48 Aft Pressure Bulkhead Aft Pressure Bulkhead Web20,00020,00053-00-F48C Section 48 Aft Pressure Bulkhead Y-Chord at Circumferential WebAttachment below WL 18920,000(3)20,000(3)53-00-F48D Section 48 Aft Pressure Bulkhead Radial Web Splices – Visible Detail20,000(3)20,000(3)53-00-F48E Section 48 Aft Pressure Bulkhead Radial Web Splices – Hidden Detail20,000(3)20,000(3)53-00-F48F Section 48 Aft Pressure Bulkhead Regular and Super Tear Strap SplicesVisible detail from bulkhead aft side20,000(3)20,000(3)53-00-F48G Section 48 Aft Pressure Bulkhead Regular and Super Tear Strap SplicesHidden detail from bulkhead aft side20,000(3)20,000(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-8153-00-F49A BS 2598 BulkheadUpper Bulkhead Web at Shear DeckChord, Outboard of Diagonal BraceAttachment20,00020,000(4)53-00-F49B BS 2598 BulkheadSide Frame Inner Chords betweenWL 305 and WL 31720,000(3)20,000(3) (4)53-00-F49C BS 2598 BulkheadPivot Fitting and LongeronAttachments to BS 2598 Bulkhead,WL 265 to 32020,000(3)20,000(3) (4)53-00-F49F BS 2598 BulkheadDiagonal Brace Strut, Rod End InnerSleeve (Upper Struts only)20,000(3)20,000(3) (4)53-00-F49G BS 2598 BulkheadDiagonal Brace Strut Attachment Lugsat WL 31720,000(3)20,000(3) (4)53-00-F49H BS 2598 BulkheadDiagonal Brace Strut Rod EndClevises at WL 31720,000(3)20,000(3) (4)53-00-F51 Section 48 LongeronsUpper Longeron from BS 2557 to 2579 20,00020,000(4)53-00-F53A Nose Landing Gear Support Structure Trunnion Fitting Stem: BS390, fromWL 129 to WL18320,000(3)20,000(3)53-00-F53B.1 Nose Landing Gear Support Structure Drag Brace Lug: BS350, WL164,+/- BL3.75FLS,See Figure 2(3)FLS,See Figure 2(3)53-00-F53B.2 Nose Landing Gear Support Structure Drag Brace: Flange at NGWW TopPanel BS 340 - BS360, WL187,+/- BL3.75FLS,See Figure 2(3)FLS,See Figure 2(3)53-00-F53B.3 Nose Landing Gear Support Structure Drag Brace: Diagonal Arm –BS 352 - BS 357, WL167 - WL177,+/- BL3.7520,000(3)20,000(3)53-00-F53C.1 Nose Landing Gear Support Structure Transverse Brace: Lower FlangeBS 362.5, WL 17720,000(3)20,000(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-82747-8/8F AIRWORTHINESS LIMITATIONS53-00-F53C.2 Nose Landing Gear Support Structure Transverse Brace: Forward Edge ofLower Flange – BS 360, WL 17720,000(3)20,000(3)53-00-F55C Underwing LongeronBS 990 at S-38L/R20,000(3)20,000(3)53-00-F57A Section 48 Skin Panels Forward ofBS 2658Upper Lobe Doubler at Fuselage toVertical Stabilizer Attachment20,000(3)20,000(3)53-00-F58A Section 48 - Stabilizer Hinges andSupport FittingsPivot Hinge Inboard Lugs – BS 2598,WL 292.50, LBL/RBL 43.520,000(3)20,000(3) (4)53-00-F58B Section 48 - Stabilizer Hinges andSupport FittingsPivot Hinge Outboard Lugs – BS 2598,WL 292.50, LBL/RBL 43.520,000(3)20,000(3) (4)53-00-F58C Section 48 - Stabilizer Hinges andSupport FittingsDiagonal Brace Lugs, BS 259820,000(3)20,000(3) (4)53-00-F59B Nose Cargo Door CutoutFuselage (C-3) Closure FrameOuter ChordsN/A20,000(3)53-00-F59C Nose Cargo Door CutoutFuselage (C-3) Closure FrameBack-up FittingsN/A20,000(3)53-00-F59D Nose Cargo Door CutoutFuselage (C-3) Closure FrameInner ChordsN/A20,000(3)53-00-F59G Nose Cargo Door CutoutFuselage (C-3) Closure FrameUpper FittingN/A20,000(3)53-00-F61A Miscellaneous Fuselage Cutouts Drain Mast Cutouts at BS 1830 andBS 2130 between S-51L and S-51R20,000(3)N/A53-00-F61B Miscellaneous Fuselage Cutouts Lavatory Service Pan Cutouts 20,000 20,00053-00-F62A.1 Outflow Valve Outlet Cutout Cutout Corners20,000(3)20,000(3)53-00-F64A Antenna CutoutsSkin Under ADF Antennas20,000(3)20,000(3)All except L/N 1505, 1526.53-00-F64A.1 Antenna CutoutsSkin Under ADF AntennasN/A20,000(3)L/N 1505, 1526 only.53-00-F64B Antenna Cutouts Skin Under Blade Antennas in Bilgeand Crown20,000(3)20,000(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FSEP 2015747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-8353-00-F64C Antenna CutoutsSkin Around Blade Antennas in Bilgeand Crown20,000(3)20,000(3)53-00-F64D Antenna CutoutsBS 510 and BS 610 in the Crown20,00020,00053-00-F64E Antenna CutoutsSkinat TCAS and ADF Antennas inBilge and Crown20,000(3)20,000(3)53-00-F65A.1 Equipment Cooling Outlet Cutout Skin at Doubler Periphery BetweenBS 520 - 580 and S46L - S44R20,000(3)N/A53-00-F67A Over Wheel Well Longeron Extension BS 1480 to BS 1480+20, S-32 to S-34 20,000 20,00053-00-F67E Over Wheel Well Longeron Extension Skin from BS 1480 to 1480+20 atS-32L/R and from BS 1480 to 1480+60at S-33L/R20,000(3)20,000(3)53-00-F71A Upper Deck Emergency Exit DoorCutout StructureFrame Inner Chord and Web,BS 666.25 and BS 713.75 from S-12to S-1520,000(3)N/A53-00-F71B Upper Deck Emergency Exit DoorCutout StructureSkin and Strap at Frame Outer Chord,BS 666.25 and BS713.75 from S-3to S-1320,000(3)N/A53-00-F71C Upper Deck Emergency Exit DoorCutout StructureSkin Cutout Corners20,000(3)N/A54-50-001 Strut to Wing Attachment Fittings –Inboard StrutAll Strut to Wing Fittings FLS,< 7hrs 15,000≥7hrs 10,000FLS,< 7hrs 15,000≥7hrs 10,00054-50-002 Strut to Wing Attachment Fittings –Outboard StrutAll Strut to Wing Fittings FLS,See Figure 2 FLS, See Figure 2Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-84747-8/8F AIRWORTHINESS LIMITATIONS54-50-002d_R3(8)NONEStrut Outboard Aft Upper Spar Fittingson Outboard Struts2,400Flight Cycles afterAirplane Deliveryor UponDisassembly ofthe Joint,whicheveroccurs first2,400Flight Cycles afterAirplane Deliveryor UponDisassembly ofthe Joint,whicheveroccurs firstPerform Detailed Inspection of theStrut and Wing Fittings includingtheir Flanges and Lugs, and theFuse Pin, including the retainingfeatures, for missing or damagedparts. Do not disassemble the joint.If any discrepancies are found,contact Boeing for instruction beforefurther flight. Repeat inspectionevery 2,400 Flight Cycles (FCs) orupon disassembly of the joint,whichever occurs first. Refer toAMM 54-05-03-211-801 (#1 Strut)and 54-05-03-211-802 (#4 Strut).54-50-003DELETEDNONEForward Engine Mount AssembliesWithin 200 FlightCycles from thedate of issuanceof the originalcertificate ofairworthiness orthe original exportcertificate ofairworthiness, orwithin 30 calendardays of theNovember 2013release of thisdocument(D011U721-02-01), whicheveroccurs later.Repeat intervalnot to exceed 200Flight Cycles.(9)Within 200 FlightCycles from thedate of issuance ofthe originalcertificate ofairworthiness or theoriginal exportcertificate ofairworthiness, orwithin 30 calendardays of theNovember 2013release of thisdocument(D011U721-02-01),whichever occurslater. Repeatinterval not toexceed 200 FlightCycles.(9)Perform Ultrasonic (UT) Inspectionof the Barrel Nuts on the ForwardEngine Mount for cracked nuts inaccordance with Boeing ServiceBulletin 747-71A2329.Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-8554-50-003c NONEForward Engine Mount Assemblies All 747-8Airplanes withbarrel nutSL4750NA at theforward enginemount, includingairplanes thathaveaccomplished thebarrel nutreplacement perBoeing ServiceBulletin747-71-2332.All 747-8FAirplanes withbarrel nutSL4750NA at theforward enginemount, includingairplanes that haveaccomplished thebarrel nutreplacement perBoeing ServiceBulletin747-71-2332.At engine installation if reuse offorward engine mount barrel nutSL4750NA is desired, prior to engineinstallation, the barrel nut SL4750NAmust be dye penetrant inspectedper SRM 51-10-04 Section 4.B.2.band AMS 2644 except:(1) Inspector must have acertification in fluorescent dyepenetrant inspection techniques;(2) Do not remove solid filmlubricant; (3) Solvent clean bolts andnuts and air dry bolts and nutsbefore application of penetrant;(4) Inspection to be Type I,sensitivity Level 3 per AMS 2644.NOTE: Installation of barrel nutP/N SL4081C14SP1 at the forwardengine mount assemblies isprohibited on airplanes line number1435, 1487, 1489, 1493, and 1499and on as it is not an approvedtype design.54-50-005a-01a Upper Spar Assembly – InboardEngine PylonR1/Web Attachment, R1 EdgeNSTA 204-NSTA 27820,000(3)20,000(3)54-50-005a-01b Upper Spar Assembly – InboardEngine PylonR1/Web Attachment, Fastener HolesNSTA 204-NSTA 278FLS,See Figure 2(3)FLS,See Figure 2(3)54-50-005a-05a Upper Spar Assembly – InboardEngine PylonWeb/Chord/Skin Joint, Fastener HolesNSTA 200-NSTA 300FLS,See Figure 1(3)FLS,See Figure 1(3)54-50-005a-05b Upper Spar Assembly – InboardEngine PylonWeb/Chord/Skin Joint, RH SystemShroud Support BracketsFLS,See Figure 1(3)FLS,See Figure 1(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-86747-8/8F AIRWORTHINESS LIMITATIONS54-50-005a-09 Upper Spar Assembly – InboardEngine PylonWeb Cutouts, NSTA 200-NSTA 240 FLS,See Figure 1FLS,See Figure 154-50-005b-04a Lower Spar Assembly – InboardEngine PylonWeb/Chord/Skin Joint, Web CutoutEdge, NSTA 216-273FLS,< 7hrs 15,000(3)≥7hrs 10,000(3)FLS,< 7hrs 15,000(3)≥7hrs 10,000(3)54-50-005b-04b Lower Spar Assembly – InboardEngine PylonWeb/Chord/Skin Joint, Chord Edge,NSTA 218-289, 300-329FLS,< 7hrs 15,000(3)≥7hrs 10,000(3)FLS,< 7hrs 15,000(3)≥7hrs 10,000(3)54-50-005b-04c Lower Spar Assembly – InboardEngine PylonHeat Shield Attachment, NSTA 310.5 FLS,< 7hrs 15,000(3)≥7hrs 10,000(3)FLS,< 7hrs 15,000(3)≥7hrs 10,000(3)54-50-005b-04d Lower Spar Assembly – InboardEngine PylonAEMB/Web/Chord/Skin, Chord HolesCommon to AEMBFLS,< 7hrs 15,000(3)≥7hrs 10,000(3)FLS,< 7hrs 15,000(3)≥7hrs 10,000(3)54-50-005d-01 Forward Engine Mount Bulkhead –Inboard Engine PylonEngine Mount Tension Bolt Holes 20,000 20,00054-50-005d-02 Forward Engine Mount Bulkhead –Inboard Engine PylonShear Pin20,000(3)20,000(3)54-50-005e-01 Aft Engine Mount Bulkhead – InboardEngine PylonEngine Mount Tension Bolt Holes 20,000 20,00054-50-005e-03 Aft Engine Mount Bulkhead – InboardEngine PylonShear Pin20,000(3)20,000(3)54-50-005e-04 Aft Engine Mount Bulkhead – InboardEngine PylonShear Pin Boss 20,000 20,00054-50-005f-01 Aft Strut Bulkhead – Inboard EnginePylonCutout, Cutout Stiffener andR2 AttachmentFLS,See Figure 1(3)FLS,See Figure 1(3)54-50-006a-05a Upper Spar Assembly – OutboardEngine PylonWeb/Chord/Skin Joint, RH SystemShroud Support Brackets20,000(3)20,000(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-8754-50-006a-05b Upper Spar Assembly – OutboardEngine PylonWeb/Chord/Skin Joint, NSTA 200-NSTA 260FLS,< 7hrs 15,000(3)≥7hrs 10,000(3)FLS,< 7hrs 15,000(3)≥7hrs 10,000(3)54-50-006a-05c Upper Spar Assembly – OutboardEngine PylonWeb/Chord/Skin Joint, Chord EdgeNSTA 280-NSTA 30020,000(3)20,000(3)54-50-006a-07 Upper Spar Assembly – OutboardEngine PylonAft Upper Spar Fitting/Web/Skin Joint FLS,See Figure 2(3)FLS,See Figure 2(3)54-50-006b-04a Lower Spar Assembly – OutboardEngine PylonWeb/Chord/Skin Joint, Fastener HolesNSTA 216-NSTA 290FLS,See Figure 2(3)FLS,See Figure 2(3)54-50-006b-04b Lower Spar Assembly – OutboardEngine PylonWeb/Chord/Skin Joint, At GSE FittingNSTA 281-NSTA 28420,000(3)20,000(3)54-50-006b-04c Lower Spar Assembly – OutboardEngine PylonWeb/Chord/Skin Joint, Chord EdgeNSTA 216-NSTA 29520,000(3)20,000(3)54-50-006d-01 Forward Engine Mount Bulkhead –Outboard Engine PylonEngine Mount Tension Bolt Holes 20,000 20,00054-50-006d-02 Forward Engine Mount Bulkhead –Outboard Engine PylonShear Pin20,000(3)20,000(3)54-50-006e-01 Aft Engine Mount Bulkhead –Outboard Engine PylonEngine Mount Tension Bolt Holes 20,000 20,00054-50-006e-03 Aft Engine Mount Bulkhead –Outboard Engine PylonShear Pin20,000(3)20,000(3)54-50-006e-04 Aft Engine Mount Bulkhead –Outboard Engine PylonShear Pin Boss 20,000 20,00054-50-006f-01 Aft Strut Bulkhead – OutboardEngine PylonCutout, Cutout Stiffener andR2 AttachmentFLS,See Figure 1(3)FLS,See Figure 1(3)54-50-006g-01 Frames – Outboard Engine Pylon Frame 5 Tension Bolt Holes N/A 20,000 Production L/N 1420-1429 OnlyAirworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-88747-8/8F AIRWORTHINESS LIMITATIONS55-10-E01A.1 Horizontal Stabilizer Upper PanelZ-StringerRib 9 &10, S-1 thru S-11;Rib 10 & 11, S-1120,00020,000(4)55-10-E01A.7 Horizontal Stabilizer Upper PanelZ-StringerRib 2 to 5, S-1 thru S-4;Rib 5 to 8, S-6 & S-720,00020,000(4)55-10-E01A.8 Horizontal Stabilizer Upper PanelZ-StringerRib 2 to 3, S-1 thru S-2; Rib 4 to 7, S-1thru S-4; Rib 7 to 8, S-420,000(3)20,000(3) (4)55-10-E01A.11 Horizontal Stabilizer Upper PanelZ-StringerRib 1 to 2 (BL14.5 outbd to edge ofsplice), S-1 & S-220,00020,000(4)55-10-E01B.1 Horizontal Stabilizer Typ Stringer atBL 14.5 Splice StrapS-9 to S-16, BL 14.520,000(3)20,000(3) (4)55-10-E01F Horizontal Stabilizer Upper PanelZ StrgAft Torque Box Internal BL 43.5 toStab Sta 285N/A FLS,See Figure 1(4a)55-10-E04E.2 Horiz Stabilizer, Center Upper FrontSpar Chord to SkinAt BBL 14.50 (at Actuator Rib - 1)20,000(3)20,000(3) (4)55-10-E04E.3 Horiz Stabilizer, Center Upper FrontSpar Chord to SkinAt BBL 14.50 (at Actuator Rib - 1)20,000(3)20,000(3) (4)55-10-E05A.2 Horiz Stabilizer, Outboard Upper RearSpar Chord to SkinStab Sta 172.4 to Stab sta 235 FLS,See Figure 1FLS,See Figure 1(4a)55-10-E05A.3 Horiz Stabilizer, Outboard Upper RearSpar Chord to SkinSkin between Rib 3 & Rib 7 FLS,See Figure 1FLS,See Figure 1(4a)55-10-E05B.2 Horiz Stabilizer, Outboard Upper RearSpar Chord to SkinChord at Ribs 3 to 7 FLS,See Figure 1(3)FLS,See Figure 1(3) (4a)55-10-E05F.1 Horiz Stabilizer, Center Box UpperRear Spar Chord to SkinB/t BBL 29 & BL 43.5Splice FittingFLS,See Figure 1(3)FLS,See Figure 1(3) (4a)55-10-E05F.3 Horiz Stabilizer, Center Box UpperRear Spar Chord to SkinSkin B/t BBL 29 & BL 43.5 Splice Plate FLS,See Figure 1(3)FLS,See Figure 1(3) (4a)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-8955-10-E05G.1 Horiz Stabilizer, Center Box UpperRear Spar Chord to SkinAt BL 14.5 Rib Shear Tie FLS,See Figure 1(3)FLS,See Figure 1(3) (4a)55-10-E05H.1 Horiz Stabilizer, Center Box UpperRear Spar Chord to WebBetween BBL 14.5 - 43.5 at stiffener FLS,See Figure 1(3)FLS,See Figure 1(3) (4a)55-10-E05H.2 Horiz Stabilizer, Center Box UpperRear Spar Chord to WebBetween BBL 14.5 and BBL 43.5 FLS,See Figure 1(3)FLS,See Figure 1(3) (4a)55-10-E05H.3 Horiz Stabilizer, Center Box UpperRear Spar Chord to WebBetween BBL 14.5 - 43.5(Left and Right)FLS,See Figure 1(3)FLS,See Figure 1(3) (4a)55-10-E06B.1 BL 14.5 Splice Plate at JackscrewFittingInner Lower SplicePlate at jackscrewfitting attachment20,000(3)20,000(3) (4)55-10-E08A.1 Horizontal Stabilizer, Center BoxUpper Rear Spar Chord to Skinat S.O.B.Inbd of Rib -2 (SOB) c/t upr splice ftngAt Inbd-most .375" dia fastener pair20,000(3)20,000(3) (4)55-10-E08A.2 Horiz Stabilizer, Outboard Upper RearSpar Chord to Skin at S.O.B.Betn Rib-2 (SOB Rib) & Rib-3 AtOutbd-most .375" dia fastener pair20,000(3)20,000(3) (4)55-10-E08B.1a Horiz Stabilizer, Center-Box UpperRear Spar Chord to Skin at S.O.B.Inbd of Rib-2 (SOB) c/t upr splice ftngAt Inbd-most .375" dia fastener pair20,000(3)20,000(3) (4)55-10-E08B1.b Horiz Stabilizer, Center-Box UpperRear Spar Chord to Skin at S.O.B.Inbd of Rib-2 (SOB) c/t upr splice ftngAt Inbd-most .4375" dia fastener pair20,000(3)20,000(3) (4)55-10-E08B2.a Horiz Stabilizer, Outboard Upper RearSpar Chord to Skin at S.O.B.Betn Rib-2 (SOB Rib) & Rib-3At Outbd-most .375" dia fastener pair20,000(3)20,000(3) (4)55-10-E08B2.b Horiz Stabilizer, Outboard Upper RearSpar Chord to Skin at S.O.B.Betn Rib-2 (SOB Rib) & Rib-3At Outbd-most .4375" dia fastener pair20,000(3)20,000(3) (4)55-10-E08H.3a Horizontal Stabilizer Side ofBody SpliceFront Spar Terminal Fitting 20,00020,000(4)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-90747-8/8F AIRWORTHINESS LIMITATIONS55-10-E08J.1 Horizontal Stabilizer, Center BoxTypical Upper Stringer to Skinat S.O.B.Stringer S-1 termination, at inbd-most.375" dia fastnr c/t inner splice pl20,000(3)20,000(3) (4)55-10-E08J.2 Horiz Stabilizer, Outboard TypicalUpper Stringer to Skin at S.O.B.Stringer S-1 termination, at outbd-most.375" dia fastnr c/t inner splice pl20,000(3)20,000(3) (4)55-10-E08K.1 Horiz Stab, Inboard Upper AftSOB Splice – Splice Plates-to-StringerInbd of Rib-2 (SOB) at S-2 termination20,000(3)20,000(3) (4)55-10-E08K.2 Horiz Stab, Inboard Upper AftSOB Splice – Splice Plates-to-StringerOutbd of Rib-2 (SOB) at S-2termination20,000(3)20,000(3) (4)55-10-E08L.1 Horiz Stab, Inboard Upper AftSOB Splice – Splice Plates-to-SkinInbd of Rib-2 (SOB) c/t upr splice ftngSecond-most outbd .4375" dia fast pair20,000(3)20,000(3) (4)55-10-E08L.2 Horiz Stab, Inboard Upper AftSOB Splice – Splice Plates-to-SkinBetn Rib-2 (SOB Rib) & Rib-3 Atsecond-most inbd .4375" dia fast pair20,000(3)20,000(3) (4)55-10-E08O.1 Horizontal Stabilizer Side ofBody SpliceHinge Rib Web – BL 43.5 20,00020,000(4)55-10-E08P.1a Horizontal Stabilizer Side ofBody SpliceRear Spar Upper Splice FittingForward Flange20,00020,000(4)55-10-E08P.2a Horizontal Stabilizer Side ofBody SpliceHinge Rib Upper Chord Web Flange atRear Spar20,000(3)20,000(3) (4)55-10-E08Q.1 Horizontal Stabilizer Side ofBody SpliceSplice Fitting Inboard / OutboardWeb Flange20,000(3)20,000(3) (4)55-10-E08R.1 Horizontal Stabilizer Side ofBody SpliceRear Spar Upper Splice FittingSkin Flange20,000(3)20,000(3) (4)55-10-E09 Jackscrew Support Fitting AttachmentArmsFitting Back to Back Lug FLS,See Figure 1(3)FLS, See Figure 1(3) (4a)55-10-E10A Pivot Fitting Attachment Structure Outer Pin – Horizontal Stabilizer20,000(3)20,000(3) (4)55-10-E10B1 Pivot Fitting Attachment Structure Inner Spliceat Pivot Fitting UpperFlange - Outboard Side Attachment20,000(3)20,000(3) (4)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-9155-10-E10B2 Pivot Fitting Attachment Structure Inner Spliceat Pivot Fitting UpperFlange - Inboard Side Attachment20,000(3)20,000(3) (4)55-10-E10C.1 Pivot Fitting Attachment Structure Pivot fitting upper flange to spliceplates attachment20,000(3)20,000(3) (4)55-10-E10E Back to Back Lug Horizontal Stabilizer H. Stab Pivot Fitting Lug20,000(3)20,000(3) (4)55-20-E01 Inbd & Outbd Elevator Hinges Horizontal StabilizerActuator & Elevator Hinges20,00020,000(4)55-30-E03A.2 Vertical Fin Front SparChord to Skin at Fin Sta 117 Rib ShearTie attach fastener20,000(3)20,000(3)55-30-E03D.2 Vertical Fin Front SparWeb adjacent to chord from Fin Sta98.5 to Fin Sta 11720,000(3)20,000(3)55-30-E04B.1 Vertical Fin Rear SparRearSpar Chord / Skin at Fin Sta 163to 270-Lower 7 rib to skin/spar chord20,000(3)20,000(3)55-30-E07B.3 Vertical Fin toBody Attachment Rear Spar Root Ftg to Web at rootsplice joint20,000(3)20,000(3)55-30-E07B.4 Vertical Fin toBody Attachment Rear Spar Root Ftg to Skin at rootsplice joint20,000(3)20,000(3)55-30-E07C.3 Vertical Fin to Body Attachment Front Spar Root Ftg to Web at rootsplice joint20,000(3)20,000(3)55-30-E07C.4 Vertical Fin to Body Attachment Front Spar Root Ftg to Skin at rootsplice joint20,000(3)20,000(3)55-40-E01 Vertical Fin, Lower Rudder,Control RodsUpper, Lower Control rods andattachments at Rudder Sta 82.792and 107.75720,000 20,00055-40-E02 Upper Rudder Hinges Fin and Rudder Hinges 20,000 20,00055-40-E03 Lower Rudder and Tab Hinges Fin, Rudder and Tab Hinges 20,000 20,000Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-92747-8/8F AIRWORTHINESS LIMITATIONS57-10-W01A.1 Side of Body Splice, Upper Surface Lead Crack in Double Plus ChordFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W01A.2 Side of Body Splice, Upper Surface Lead Crack in Double Plus ChordFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W01B.1 Side of Body Splice, Upper Surface Skin crack on intact stringer atStringer 1 Joint, Section 12FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W01C.1 Side of Body Splice, Upper Surface Paddle Fitting Crack at Double PlusChord JointFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W01D.1 Side of Body Splice, Upper Surface Stringer Crack at JointFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W02A.1 Side of Body Splice, Lower Surface Inner Splice Plate, Section 12FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W02A.2 Side of Body Splice, Lower Surface Lead Crack in skinFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W02A.3 Side of Body Splice, Lower Surface Lead Crack in Paddle Fitting S1 Jointnear Rear SparFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W02A.4 Side of Body Splice, Lower Surface Lead Crack in StringerFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W02A.5 Side of Body Splice, Lower Surface Lead Crack in Splice StringerFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W02B.1 Side of Body Splice, Lower Surface Inner Splice Plate, Section 11FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W03A.1 Side of Body Splice, Front Spar Outboard Upper Front Spar Chord,Web and Upper SkinFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W03A.2 Side of Body Splice, Front Spar Center Section Lower Front SparChord and WebFLS,See Figure 1(3)FLS,See Figure 1(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-9357-10-W03B Side of Body Splice, Front Spar Terminal Fitting Joint at Upper Chord FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W03C Side of Body Splice, Front Spar Outboard Upper Front Spar Chord,Web and Upper SkinFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W03D Side of Body Splice, Front Spar Internal & External Splice Tee Fittings FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W04B Side of Body Splice, Rear Spar Center Section Chord and SkinUpper and LowerFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W04C Side of Body Splice, Rear Spar Outboard Chord and Skin Upperand LowerFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W04D Side of Body Splice, Rear Spar Center Section & Outboard, Upper &Lower External Splice Plate, Tee andTerminal FittingFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W04E Side of Body Splice, Rear Spar Outboard Upper External Splice Plate,Tee and Terminal FtgFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W05A.1 Side of Body RibWeb at Chord AttachmentFLS,See Figure 2(3)FLS,See Figure 2(3)57-10-W05A.2 Side of Body RibWeb at Chord Attachment CrackHidden by StiffenerFLS,See Figure 2(3)FLS,See Figure 2(3)57-10-W06A.3 Center Section Rear SparLower Chord to Web Attachment Nearthe Pickle Fork FittingFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W06B.1 Center Section Rear SparUpper Chord to Web AttachmentAt StiffenerFLS,See Figure 2(3)FLS,See Figure 2(3)57-10-W06B.2 Center Section Rear SparUpper Chord to Web AttachmentBetween StiffenersFLS,See Figure 2FLS,See Figure 257-10-W07A.1 Center Section Front SparLower Chord to Web Attachment FilletRadius of Web PocketsFLS,See Figure 1(3)FLS,See Figure 1(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-94747-8/8F AIRWORTHINESS LIMITATIONS57-10-W07A.2 Center Section Front SparLower Chord to Web AttachmentBetween StiffenersFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W07A.3 Center Section Front SparLower Chord to Web AttachmentHidden by ext. & int. stiffenersFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W07B.1 Center Section Front SparRing Chord to Web AttachmentBetween StiffenersFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W07B.2 Center Section Front SparRing Chord to Web Attachment Hiddenby ring chord & int. stiffenersFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W12A.4 Wing Center Section Lower Panel Typical Stringer with shear tie at BL9Keel beam upper chord attachmentFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W12A.9 Wing Center Section Lower Panel Typical Stringers with skin hiddenFLS,See Figure 1FLS,See Figure 157-10-W12A.10 Wing Center Section Lower Panel BL0 aft of Midspar, typical stringerFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W12A.11 Wing Center Section Lower Panel Stringer 6 BL 9(keel beam attachment)FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W12A.14 Wing Center Section LowerPanel Stringer adjacent to spar chordStringer 1FLS,See Figure 1FLS,See Figure 157-10-W12A.15 Wing Center Section Lower Panel Stringer adjacent to spar chord –stringer 1FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W12A.17 Wing Center Section Lower Panel Stringer 14 & 19 at stiffener locations FLS,See Figure 1FLS,See Figure 157-10-W12B.1 Wing Center Section Lower Panel Splice Stringer - Exposed Areas FLS,See Figure 1FLS,See Figure 157-10-W12B.2 Wing Center Section Lower Panel –Splice StringersSplice Stringer 10 (Midspar Chord) atstiffener locationsFLS,See Figure 1(3)FLS,See Figure 1(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-9557-10-W12C.1 Wing Center Section Lower Panel Rear Spar Chord Exposed areas FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W12C.4 Wing Center Section Lower Panel Front Spar Chordat stiffeners FLS,See Figure 1FLS,See Figure 157-10-W12C.6 Wing Center SectionLower Panel Rear Spar ChordFLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W13A.3 Wing Center Section Upper Panel Typical Stringer at BL 0FLS,See Figure 2(3)FLS,See Figure 2(3)57-10-W13A.4 Wing Center Section UpperPanel Typical Stringer at floorbeams FLS,See Figure 2(3)FLS,See Figure 2(3)57-10-W13A.5 Wing Center Section Upper Panel Typical Stringer at BL 0 at stiffenersFLS,See Figure 2FLS,See Figure 257-10-W13B.2 Wing Center Section Upper Panel Stringer 14 at stiffeners at BL 113FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W13B.3 Wing Center Section Upper Panel Stringer 14FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W13B.7 Wing Center Section Upper Panel Stringer 14 at floorbeamFLS,See Figure 1FLS,See Figure 157-10-W13B.9 Wing Center Section Upper Panel Stringer 14 from LBL11 to RBL11FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W13C.1 Wing Center Section Upper PanelRear Spar Chord at Exposed Areas FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W13C.3 Wing Center SectionUpper Panel Rear Spar Chord FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W13C.4 Wing Center Section Upper PanelFront Spar Chord at floorbeams chordcompletely hiddenFLS,See Figure 1FLS,See Figure 1Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-96747-8/8F AIRWORTHINESS LIMITATIONS57-10-W13C.5 Wing Center Section Upper Panel Rear Spar Chord at floorbeam FLS,See Figure 1(3)FLS,See Figure 1(3)57-10-W13C.7 Wing Center SectionUpper Panel Rear Spar Chord FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W01A.3 Lower PanelTypical Stringer under InbdStrut FairingsFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W01A.5 Lower PanelTypical Stringer under Track Fairings FLS,See Figure 2FLS,See Figure 257-20-W01A.6 Lower PanelTypical Stringer at Strut SupportFittings of Inbd and Outbd NacellesFLS,See Figure 2FLS,See Figure 257-20-W01A.8 Lower PanelTypical Stringer under Strut and FlapFairingsFLS,See Figure 2FLS,See Figure 257-20-W01A.9 Lower PanelTypical Stringer at Strut SupportFittingsFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W01A.10 Lower PanelTypical Stringer at Flap Track ForwardSupport FittingsFLS,See Figure 2FLS,See Figure 257-20-W01A.14 Lower PanelLower Panel at Access DoorsFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W01B.2 Lower PanelAt Splice Stringer 10 under FairingsFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W01B.3 Lower PanelSplice Stringer under Fairings(S-5 and S-15)FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W01B.5 Lower PanelSplice Stringer at Rib Posts (Mid SparOnly) of Ribs 16 and 17FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W01B.6 Lower PanelMidspar Chord at Rib Posts – InsparRibs other than 16 and 17FLS,See Figure 1(3)FLS,See Figure 1(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-9757-20-W01B.7 Lower PanelSplice Stringer at Major Fittings (Inbd& Outbd Nacelles – R2, R3, R4)FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W01C.3 Lower PanelFront / Rear Spars at Inspar Rib Posts FLS,See Figure 1FLS,See Figure 157-20-W01C.4 Lower PanelFront and Rear Spar between InsparRib Posts Spar ChordFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W01C.6 Lower PanelFront and Rear Spar Chord(Spar Chord completely hidden)FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W01C.7 Lower PanelSpar Chord at Longitudinal SplicesFLS,See Figure 1FLS,See Figure 157-20-W02A.2 Outboard Wing Upper PanelStringer Adjacent to Spar Chord –Stringer 1FLS,See Figure 2FLS,See Figure 257-20-W02A.4 Outboard Wing Upper PanelStringer Adjacent to Spar Chord –Stringer 1FLS,See Figure 2FLS,See Figure 257-20-W02A.5 Outboard Wing Upper PanelStringer adjacent to spar chord atfuel bafflesFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W02B.1 Outboard Wing Upper PanelExposed Areas of Panel atSplice Stringer 27FLS,See Figure 2FLS,See Figure 257-20-W02B.3 Outboard Wing Upper PanelSplice Stringer 14 at Rib bay 12FLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W02C.1 Outboard Wing Upper PanelRearSpar Upper Chord (Visible Areas) FLS,See Figure 2FLS,See Figure 257-20-W02C.4 Outboard Wing Upper PanelRear Spar Chord at Major Fittings(Chord not visible externally)FLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W02C.5 Outboard Wing Upper PanelRear Spar at rib postFLS,See Figure 2(3)FLS,See Figure 2(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-98747-8/8F AIRWORTHINESS LIMITATIONS57-20-W02C.6 Outboard Wing Upper PanelFront and Rear Spar ChordFLS,See Figure 2FLS,See Figure 257-20-W02C.7 Outboard Wing Upper PanelRear Spar Chord at rib 8 postFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W02C.8 Outboard Wing Upper PanelFront Spar Chord at rib post SparChord completely hiddenFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W02D.1B Outboard Wing Upper PanelR1 Tab, Outboard EngineFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W02D.2B Outboard Wing Upper PanelR1 Tab, Inboard EngineFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W03A.2 Wing Rear SparUpper Chord to Web AttachmentHidden by TE stiffenerFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W03A.4 Wing Rear SparUpper Chord to Web AttachmentHidden by Inspar Rib Post or stiffenerFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W03D.1 Wing Rear SparLower Spar to Web Attachment Hiddenby TE StiffenerFLS,See Figure 2FLS,See Figure 257-20-W03D.1.1 Wing Rear SparLowerSpar to Web Attachment Hiddenby TE Stiffener & Fuel DoublerFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W03D.4 Wing Rear SparLower Chord to Web AttachmentHidden by Inspar RibpostFLS,See Figure 2FLS,See Figure 257-20-W03D.4.1 Wing Rear SparWS411.42 (outbd ribpost) Hidden byInspar Ribpost & Fuel DoublerFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W03D.8 Wing Rear SparLower Chord to Web Attachment Rib20 Hidden by TE Stiffener & InsparRib PostFLS,See Figure 2FLS,See Figure 257-20-W03D.10 Wing Rear SparChord to Web Attachment Rib Bay 11(WS 528.22 - 557.42) Hidden byTE StiffenerFLS,See Figure 2(3)FLS,See Figure 2(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-9957-20-W03D.11 Wing Rear SparRib Bay 11 (WS 528.22 to WS 557.42)Hidden by Inspar Rib Post or StiffenerFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W03E.1 Wing Rear SparRib Bay 11 (WS 528.22 to WS 557.42)Hidden by Major FittingsFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W03E.2 Wing Rear SparChord to Web Attachment Hidden byMajor FittingsFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W03E.3 Wing Rear SparChord to Web Attachment Hidden byMajor Ftg. & Inspar Rib PostFLS,See Figure 2FLS,See Figure 257-20-W03E.5 Wing Rear SparChord to Web Attachment Hidden byMajor Ftg. & Inspar Rib PostFLS,See Figure 2(3)FLS,See Figure 2(3)57-20-W04G.4 Front SparHidden byLE Rib Post or StiffenerFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W04H.4 Front SparWeb hidden by Inspar Rib PostFLS,See Figure 1FLS,See Figure 157-20-W04I.2 Front SparRib 34; hidden by Inspar Rib Post &LE StiffenerFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W04J.4 Front SparAt attachment of Nacelle FittingsFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W04J.6 Front SparRib Bay 37 at attachment of Jack PadFitting and Rib 38FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W07A.1 Shear-Tied RibsFlap Track Back Up Ftg: Aft Ribs 24& 3020,000(3)20,000(3)57-20-W07A.2 Shear-Tied RibsFlap Track Back Up Ftgs 1 & 3 –Aft Rib 1320,000(3)20,000(3)57-20-W07A.9 Shear-Tied RibsBackup Fitting at Inboard NacelleFLS,See Figure 1FLS,See Figure 1Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-100747-8/8F AIRWORTHINESS LIMITATIONS57-20-W07A.11 Shear-Tied RibsR4 Back Up Fittings 3 & 5 – FwdRib 16FLS,See Figure 1FLS,See Figure 157-20-W07A.12 Shear-Tied RibsBack Up Fittings - Fwd Rib 16 & 33FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W07A.14 Shear-Tied RibsRear Spar Ribpost - Aft Rib 13FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W08A.3 Wingbox Extension JointBoltHole Crack in Splice Plate, FrontSpar Joint at Inboard Rib 47,MSS 1558.7FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W08A.4 Wingbox Extension JointLower Front Spar Joint at Rib 47,MSS 1558.7FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W08B.4 Wingbox Extension JointLower Chord at Stringer Joint ofInboard Side Rib 47, MSS 1558.7FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W08C.1 Wingbox Extension JointLower Skin & Splice Stringer #5 Jointto Inboard Side of Rib 47, MSS 1558.7FLS,See Figure 1FLS,See Figure 157-20-W08C.2 Wingbox Extension JointSkin & Paddle Fitting Joint to SpliceStringer #5 of Rib 47, Inboard SideFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W08C.4 Wingbox Extension JointLower Chord at Stringer #5 Joint ofInboard Side Rib 47, MSS 1558.7FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W08D.3 Wingbox Extension JointLower Rear Spar Joint at Rib 47,MSS 1558.7FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W08D.4 Wingbox Extension JointLower Rear Spar Joint at Rib 47,MSS 1558.7FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W09A.4 Raked WingTip JointLower Chord at Stringer #6 & #8 JointInboard Side Rib 52 at WBL 1243.8FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W09B.1 Raked WingTip JointLower Chord at Front Spar JointInboard Side Rib 52 at WBL 1243.8FLS,See Figure 1(3)FLS,See Figure 1(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-10157-20-W09E.1 Raked WingTip JointLower Chord at Rear Spar JointInboard Side Rib 52 at WBL 1243.8FLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W10B.1 Wing LandingGear Support Fittings Rear Spar Gate Support Fitting AssyUpper and Lower Horizontal FlangeFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W10B.2 Wing Landing Gear Support Fittings Rear Spar Gate Supt Ftg - Rear SparWeb JointFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W10B.3 Wing LandingGear Support Fittings Rear Spar Gate Support Fitting AssyUpper and Lower Horizontal FlangeFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W10B.4 Wing Landing Gear Support Fittings Vertical Flange Open Hole Rear SparGate Support Fitting AssyFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W11A Nacelle Support FittingsR1 Upper Link Pitch FittingsFLS,See Figure 1FLS,See Figure 157-20-W11B Nacelle Support FittingsR2 Diagonal Brace FittingFLS,See Figure 1FLS,See Figure 157-20-W11C.1 Nacelle Support FittingsR3 Nacelle Support Outbd Fitting atInboard EngineFLS,See Figure 1FLS,See Figure 157-20-W11C.2 Nacelle Support FittingsR4 Nacelle Support Inbd FittingFLS,See Figure 1FLS,See Figure 157-20-W11D Nacelle Support FittingsR3 Front Spar Backup FittingsFLS,See Figure 1FLS,See Figure 157-20-W11E Nacelle Support FittingsR7/ R8 Side Load Link FittingsFLS,See Figure 1FLS,See Figure 1Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-102747-8/8F AIRWORTHINESS LIMITATIONS57-20-W11_R3(8)NONEStrut Outboard Aft Upper Spar Fittingson Outboard Struts2,400Flight Cycles afterAirplane Deliveryor UponDisassembly ofthe Joint,whicheveroccurs first2,400Flight Cyclesafter AirplaneDeliveryor UponDisassembly ofthe Joint,whicheveroccurs firstPerform Detailed Inspection of theStrut and Wing Fittings includingtheir Flanges and Lugs, and theFuse Pin, including the retainingfeatures, for missing or damagedparts. Do not disassemble the joint.If any discrepancies are found,contact Boeing for instruction beforefurther flight. Repeat inspectionevery 2,400 Flight Cycles (FCs) orupon disassembly of the joint,whichever occurs first. Refer toAMM 54-05-03-211-801 (#1 Strut)and 54-05-03-211-802 (#4 Strut).57-20-W11H.3 Nacelle Support FittingsOutboard Engine R3 Nacelle SupportOutboard Fitting – LugFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W11H.4 Nacelle Support FittingsOutboard Engine R3 Nacelle SupportOutboard Fitting – LugFLS,See Figure 1(3)FLS,See Figure 1(3)57-20-W11H.5 Nacelle Support FittingsOutboard Engine R3 Nacelle SupportOutbd Fitting – Tension BoltsFLS,See Figure 1(3)FLS,See Figure 1(3)57-51-W01C.3 Wing Landing Gear Beam Assembly Flap Track 4 Aft Attach – Wing LandingGear Beam JointsFLS,See Figure 2FLS,See Figure 257-51-W01E.1 Wing Landing Gear Beam Assembly IB Flap Displacement Fitting WebJoints hidden by the Fitting LowerChordFLS,See Figure 2(3)FLS,See Figure 2(3)57-51-W01E.2 Wing Landing Gear Beam Assembly Web Joints located below upper chordand above lower chordFLS,See Figure 2(3)FLS,See Figure 2(3)57-51-W01E.3 Wing Landing Gear Beam Assembly Lower Chord between Aft Trunnionand BS 1350 BulkheadFLS,See Figure 2(3)FLS,See Figure 2(3)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-10357-51-W01F.2 Wing Landing Gear Beam Assembly Actuator Rib Joint on 1350 Bulkhead atSide-of-Body – Lower ChordFLS,See Figure 2(3)FLS,See Figure 2(3)57-51-W01I Wing Landing Gear Beam Assembly Actuator Rib Joint on 1350 Bulkhead atBL 109.4 – Lower ChordFLS,See Figure 2(3)FLS,See Figure 2(3)57-51-W02A Gate FittingFuse Pin - WLG Beam End FittingOutbd Bearing Double Shear Fuse PinFLS,See Figure 1(3)FLS,See Figure 1(3)57-51-W02B Gate FittingFuse Pin - Rear Spar Gate FittingSingle Shear Fuse PinsFLS,See Figure 1(3)FLS,See Figure 1(3)57-51-W03A Gear Beam End FittingLug HoleFLS,See Figure 1(3)FLS,See Figure 1(3)57-51-W03B Gear Beam End FittingFitting JointFLS,See Figure 1(3)FLS,See Figure 1(3)57-51-W03C Gear Beam End FittingFitting Surface EdgeFLS,See Figure 1(3)FLS,See Figure 1(3)57-53-W01A.3.1 Flap Track #1 and #8Track Section – at hole, Fastener Holeattaching to Failsafe Bar20,000(3)20,000(3) (4)57-53-W01A.3.2 Flap Track #1 and #8Track Section – At Track Edge AtTrack Lower Flange Corners20,000(3)20,000(3) (4)57-53-W01C Flap Track #1 and #8Track Forward Support Lug – Clevison 747-8/-8F Tracks/Failsafe Bar #1/820,000(3)20,000(3) (4)57-53-W02A.3.1 Flap Track #2 and #7Track Section – At hole attaching toFailsafe Bar20,000(3)20,000(3) (4)57-53-W02A.3.2 Flap Track #2 and #7Track Section – At Track Lower FlangeCorner20,000(3)20,000(3) (4)57-53-W02C Flap Track #2 and #7Track Forward Support Lug – Clevison 747-8/-8F Tracks/Failsafe Bar #2/720,000(3)20,000(3) (4)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-104747-8/8F AIRWORTHINESS LIMITATIONS57-53-W03A.3.1 Flap Track #3 and #6Track Section - At hole, Fastener Holeattaching to Failsafe Bar20,000(3)20,000(3) (4)57-53-W03A.3.2 Flap Track #3 and #6Track Section - At Hole attaching toESB at lower flange outboard edge20,000(3)20,000(3) (4)57-53-W03C Flap Track #3 and #6Track Forward Support Lug – Clevison 747-8/-8F Tracks/Failsafe Bar #3/620,000(3)20,000(3) (4)57-53-W04A.3.1 Flap Track #4 and #5Track Section - at Hole, Fastener Holeattaching to Failsafe Bar20,000(3)20,000(3) (4)57-53-W04A.3.2 Flap Track #4 and #5TrackSection - Hole attach to FSB, AtLower Flange Outboard Edge20,000(3)20,000(3) (4)57-53-W05 Outbd Flap - Inbd Aux. track and Aux.Track LinkAux Track, Link and joints. 20,00020,000(4)57-53-W06 Outbd Flap - Outbd Aux. track andAux. Track LinkAux Track, Link and joints. 20,00020,000(4)57-53-W07A.1 Inboard Flap– Tracks #3, #4, #5, and#6 Carriage AssembliesAt Inboard / Outboard Sideplates20,000(3)20,000(3) (4)57-53-W07A.2 Inboard Flap– Tracks #3, #4, #5, and#6 Carriage AssembliesFwd Bogie Pivot Pin Boss / Lug atInboard/Outboard Sideplates20,000(3)20,000(3) (4)57-53-W07A.3 Inboard Flap– Tracks #3, #4, #5, and#6 Carriage AssembliesAft Bogie Pivot Pin Boss / Lug atInboard/Outboard Sideplates20,000(3)20,000(3) (4)57-53-W07B Inboard Flap– Tracks #3, #4, #5, and#6 Carriage AssembliesFwd \ AFT Fittings 20,00020,000(4)57-53-W07C Inboard Flap– Tracks #3, #4, #5, and#6 Carriage AssembliesEdge of fitting bridge at Aft SupportFitting20,000(3)20,000(3) (4)57-53-W07P Inboard Flap– Tracks #3, #4, #5, and#6 Carriage AssembliesAft Bogie Pivot Pin20,000(3)20,000(3) (4)57-53-W08 Inboard Flap Track TransmissionSupport StructuresTrack #3/#6 and #4/#5 20,00020,000(4)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-10557-53-W09A Outboard Flap– Tracks #1, #2, #7,and #8 Carriage AssembliesSideplates at Flap Tracks 1/8 and 2/720,000(3)20,000(3) (4)57-53-W09B Outboard Flap– Tracks #1, #2, #7,and #8 Carriage AssembliesFwd \ AFT Fittings 20,00020,000(4)57-53-W09C Outboard Flap – Tracks #1, #2, #7,and #8 Carriage AssembliesEdge of fitting bridge at Aft SupportFitting20,000(3)20,000(3) (4)57-53-W09D Outboard Flap – Tracks #1, #2, #7,and #8 Carriage AssembliesBogie Assembly - Pivot Pin20,000(3)20,000(3) (4)57-53-W10A Outboard Flap – Transmission MountStructureTrack #2/#7 and #1/#8 20,00020,000(4)57-53-W11 Outboard Flap – Inboard Aux. TrackCarriage AssemblyCarriage Assembly 20,00020,000(4)57-53-W12 Outboard Flap – Outboard Aux. TrackCarriage AssemblyCarriage Assembly 20,00020,000(4)57-53-W13D Aft Support, Flap Track #1 and #8 Side Load Fitting, Track #1 /#820,000(3)20,000(3) (4)57-53-W14D Aft Support, Flap Track #2 and #7 Side Load Fitting, Track #2 /#720,000(3)20,000(3) (4)57-53-W15D Aft Support, Flap Track #3 and #6 Side Load Fitting, Track #3 /#620,000(3)20,000(3) (4)57-53-W16A Aft Support, Flap Track #4 and #5 Fitting Assy - Center Holeaccommodating Shear Pin20,000(3)20,000(3) (4)57-53-W17A Forward Support, Flap Track #1and #8Track #1 and #8 Fwd Joint 20,00020,000(4)57-53-W17BB Forward Support, Flap Track #1and #8Radius along lug base20,000(3)20,000(3) (4)57-53-W17BC Forward Support, Flap Track #1and #8Fastener holes of Fwd Ftg attachment20,000(3)20,000(3) (4)57-53-W18A Forward Support, Flap Track #2and #7Track #2 and #7 Fwd Joint 20,00020,000(4)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-106747-8/8F AIRWORTHINESS LIMITATIONS57-53-W18BB Forward Support, Flap Track #2and #7Radius along lug base20,000(3)20,000(3) (4)57-53-W18BC Forward Support, Flap Track #2and #7Fastener holes of Fwd Ftg attachment20,000(3)20,000(3) (4)57-53-W19A1 Forward Support, Flap Track #3and #6Track #3 and #6 Fwd Joint 20,00020,000(4)57-53-W19BB Forward Support, Flap Track #3and #6Radius along lug base20,000(3)20,000(3) (4)57-53-W19BC Forward Support, Flap Track #3and #6Fastener holes of Fwd Ftg attachment20,000(3)20,000(3) (4)57-53-W20C Forward Support, Flap Track #4and #5Forward Support Fitting – Web to FwdFlange intersection20,000(3)20,000(3) (4)57-53-W20D Forward Support, Flap Track #4and #5Forward Support Fitting – Aft FlangeEdge20,000(3)20,000(3) (4)57-53-W20G Forward Support, Flap Track #4and #5Forward Support Fitting to Track Joint 20,00020,000(4)57-53-W24 Inboard Main Flap Gimbal andCarriage Support FittingsGimbal, Spigot, Failsafe link and Aftlink joints20,00020,000(4)57-53-W32 Outboard Flap Gimbal and CarriageSupport FittingsGimbal, Spigot and Aft Link Joints 20,00020,000(4)57-53-W33 Outboard Flap Inboard Aux. TrackCarriage AttachmentAux. Track Carriage pin housing 20,00020,000(4)57-53-W34 Outboard Flap Outboard Aux. TrackCarriage AttachmentAux. Track Carriage pin housing andsupport structure20,00020,000(4)Airworthiness Limitations – Structural Inspections Threshold TableSSI No.(1)DTR Check Form Title(7)DTR LocationThresholds(2)Notes747-8 747-8FMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-107TABLE NOTES:1. Multiple listings under a single SSI # are uniquely identifiedby Check Form Title, Location, and Model-Series information. All inspections listed under asingle SSI # for a given model must be performed.2. Listed threshold in flight cycles unless otherwise noted. Figure 1 and Figure 2 refer to FLS threshold curves.3. No airplane may be operated beyond the stated threshold requirements (or operational limit) until the applicable inspection procedures are validated,published in the appropriate manual, and accepted by the FAA.4. For L/N 1420 airplane, use threshold of 16,000 flight cycles.4a. For L/N 1420 airplane, use a threshold of 16,000 flights and/or 92,000 flight hours, whichever comes first.5. A conservative threshold for inspection for this item has been established as 12,000 flight cycles for L/N 1420 to 1507. Thiswill act as an operationallimit, compliant with Title 14 CFR § 25.571,until the Service Bulletin inspection program is released. Please refer to the future Service Bulletin (SB) forthe required inspections. See Service Bulletin (SB)747-53-2867 at the latest revision level.6. A conservative threshold for inspection for this item has been established as 14,000flight cycles. This will act as an operational limit, compliant withTitle 14 CFR § 25.571, until the Service Bulletin inspection program is released. Pleaserefer to the future Service Bulletin (SB) for the requiredinspections. See Service Bulletin (SB) 747-53-2875 at the latest revision level.7. L/N in a DTR Check Form Effectivity identifies certain forms as pertinent to specific airplane line numbers.8. To comply with FAA SC/25-388A and EASA CRI C-18 for the 747-8/-8F Amended Type Certificate, thisinspection was included in the AWL and hasnow been incorporated into the Airworthiness Limitations – Structural Inspections Threshold Table.9. This inspection only pertains to 747-8/747-8F Airplanes with GEnx-2B67/P Engines.MAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-108747-8/8F AIRWORTHINESS LIMITATIONSC. AIRWORTHINESS LIMITATIONS– STRUCTURAL SAFE-LIFE PARTSThe following Nose Landing Gear parts are subject to the Safe-Life Limits defined by Figure 3.Part NumberPart NamePart NumberPart Name162U0211Drag Strut, Upper162U2605Torsion Link, Lower162U0212Drag Strut, Lower162U2607Tripod Apex Pin162U0213Drag Strut Pivot Shaft162U2608Tripod Upper Bolt162U0215Drag Strut Apex Bolt162U2609Side Brace Upper Bolt162U2501Outer Cylinder162U2610Tripod Lower Bolt162U2502Inner Cylinder162U2621Torsion Link Apex Pin162U2504Axle162U2624SteeringActuator Support, Upper162U2507Restrictor Support Tube162U2625Steering Actuator Support, Lower162U2508Restrictor Plate162U2626Torsion Link Bolt162U2511Metering Pin162U2627Trunnion Pin162U2513Metering Pin Retaining Tube162U2628Side Brace Lower Bolt162U2601Side Brace162U2631Steering Collar Half, Fwd162U2602Tripod Brace, Upper162U2632Steering Collar Half, Aft162U2603Tripod Brace, Lower162U2633Steering Collar Pin162U2604Torsion Link, UpperMAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-109Figure 3 – 747-8/8F Nose Landing Gear Safe-Life LimitsInstructions for using the Safe-Life Chart:1. For each Safe-Life component, determine theaccumulated flight cycles and flight hours.2. Enter the Safe-Life Limit Chart at the appropriatenumbers of flight cycles and flight hours and locatethe intersection.3. If the point determined in Step 2 lies below theappropriate Safe-Life Limit Curve, the componenthas not reached its Safe-Life Limit. If the point is on,above, or to the right of the appropriate Safe-LifeLimit Curve, then its Safe-Life Limit has beenreached and the component shall be removedfrom service.MAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-110747-8/8F AIRWORTHINESS LIMITATIONSD. AIRWORTHINESS LIMITATIONS– SYSTEMS LIFE-LIMITED PARTSThe replacement times established for the life-limited parts result from Model 747-8/8F airplane certification activities withthe U.S. FAA and are part of theAirworthiness Limitations section of the Instructions for Continued Airworthiness.These maintenance actions are mandatory. These life limits may only berevised with the approval of the FAA Oversight Office.1The installation of a 030-22229-1 Assy – Aft Plug, Primary Exhaust ona GEnx-2B67/P Engine or Airplane Line Numbers 1483 and onis prohibited. This is not a Part 25Type Certified Configuration.2Published life limits are applicable to primary exhaust assemblies installed on all 747-8F or 747-8 airplanes with any of thecertified GEnx-2B67 engine models identifiedin FAA Type Certificate Data Sheet No. A20WE.ITEMNUMBER LIFE-LIMITED PART PART NUMBER PART DESCRIPTION APPLICABILITY SPECIFICATIONS LIFE LIMITQUANTIYPERAIRPLANE1 Hydraulic Control Module 734-19150-09 Inboard Trailing Edge Flap PowerDrive Unit Hydraulic Control ModuleApplicable to all 747-8 and 747-8FAirplanes5,000 Flight Cycles12 Hydraulic Control Module 734-19150-10 Outboard Trailing Edge Flap PowerDrive Unit Hydraulic Control ModuleApplicable to all 747-8 and 747-8FAirplanes5,000 Flight Cycles13 Assy – Primary Nozzle,Primary Exhaust2030-22132-1 Engine Primary Exhaust Nozzle Applicable to all 747-8 and 747-8FAirplanes9,700 Flight Cycles44 Assy – Fwd Plug, PrimaryExhaust2030-22222-1 Engine Primary Exhaust Fwd PlugAssemblyApplicable to all 747-8 and 747-8FAirplanes4,400 Flight Cycles45 Assy – Aft Plug, PrimaryExhaust1030-22229-1 Engine Primary Exhaust Aft PlugAssemblyApplicable to all 747-8 and 747-8FAirplanes4,300 Flight Cycles46 Assy – Aft Plug, PrimaryExhaust2030-22229-3 Engine Primary Exhaust Aft PlugAssemblyApplicable to all 747-8 and 747-8FAirplanes7,350 Flight Cycles47 Light Assy, Anti-Collision andPosition-Integrated LeadingEdge – LH0204544-101 Left Integrated Wingtip LightAssemblyApplicable to all 747-8 and 747-8FAirplanes9,000 Flight Hours18 Light Assy, Anti-Collision andPosition-Integrated LeadingEdge – RH0204544-102 Right Integrated Wingtip LightAssemblyApplicable to all 747-8 and 747-8FAirplanes9,000 Flight Hours1APR 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-111E. AIRWORTHINESS LIMITATIONS – SYSTEMSThese System Airworthiness Limitations are a result of Model 747-8/8F airplane certification activities with the U.S. FAA and are part of the AirworthinessLimitations section of the Instructions for Continued Airworthiness. These maintenance actions are mandatory. These Airworthiness Limitations may onlybe revised with the approvalof the FAA Oversight Office.SYSTEM AIRWORTHINESS LIMITATION 1ENGINE OIL CONSUMPTION RATES – GEnx-2BThe approved maximum normal oil consumption rate for the GEnx-2B engine installed on the model 747-8/8F has been established as0.45 quart (0.43 liter)per hour.The maximum oil consumption rate is used to show compliance with Title 14 CFR § 25.1011(b), and is a limitation to ensure the maximum airplane fuelendurance does not exceed each installed engine’s usable oil quantity, thereby preventing a common mode loss of all engine thrust. The maximum airplanefuel endurance is 24.93 flight hours and is calculated with the minimum crew, minimum equipment, no payload and the maximum quantity of usable fuelwithout reserves. The engine oil consumptionrate is normally calculated over a period of 10 to 20 flights by dividing the total quantity of oil consumed by thetotal number of flight hours; oil consumption calculationsover less than 10 flights can give an incorrect value.Operation of the models 747-8/8F with an engine oil consumption rate higher than these limits is not authorized, except as allowed under a special flightpermit authorized under Title14 CFR § 21.197 and § 21.199.MAY 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-112747-8/8F AIRWORTHINESS LIMITATIONSSYSTEM AIRWORTHINESS LIMITATION 2INSPECTION OF THE FUEL PUMP STRAINER FOLLOWING FUEL TANK ENTRY – FAA EXEMPTION 102671. Following center wing tank purging and maintenance activity inside the center wing fuel tank, perform the following tasks iffuel has been added to thecenter tank:a. After the next flight check for the presence of the ENG X FUELSTR EICAS Status message; interrogate the CMC to check for thepresence of theENG-X FUEL STRAINER IMPENDING BYPASS OR BYPASSED 'COLLECTOR' message. Troubleshoot the source ofthe fuel systemcontamination if the messages are present.b. Prior to accumulating 20 flight hours after fuel has been addedto the center tank, or 2 flight cycles after fuel has been added to the center tank,whichever comes later, perform the Main Fuel Pump Strainer Inspection/Check procedure on the right outboard engine per AMM 73-11-04, Task73-11-04-200-802-G00. Collect any material removed from the fuel pump strainer to troubleshoot the source of the fuel system contamination.One flight cycle may be added to these limits in the event of an unscheduled landing.c. Prior to accumulating 40 flight hours after fuel has been addedto the center tank, or 4 flight cycles after fuel has been added to the center tank,whichever comes later, perform the Main Fuel Pump Strainer Inspection/Check procedure on the left outboard engine per AMM 73-11-04, Task 73-11-04-200-802-G00. Collect any material removed from the fuel pumpstrainer to troubleshoot the source of the fuel system contamination. Oneflight cycle may be added to these limits in the event of an unscheduled landing.If the ENG X FUEL STR EICAS status messageor the ENG-X FUEL STRAINER IMPENDINGBYPASS OR BYPASSED 'COLLECTOR' CMC message ispresent, or if abnormal or significant contamination is found onthe fuel pump strainer, troubleshoot the source of the fuel system contamination. Fuelsystem contamination troubleshooting requires removal of the IDGFuel/Oil Heat Exchanger per AMM 24-11-13, Task 24-11-13-000-801, and visualinspection for signs of contamination of the fuel circuit.2. Following a left inboard main fuel tank purging and maintenance activity inside the left inboard main fuel tank, perform thefollowing tasks:a. After the next flight check for the presence of the ENG X FUEL STR EICAS status message, interrogate the CMC to check for thepresence of theENG-X FUEL STRAINER IMPENDING BYPASS OR BYPASSED 'COLLECTOR' message. Troubleshoot the source ofthe fuel systemcontamination if the messages are present.JUL 2013747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-113b. Prior to accumulating 20 flight hours after fuel tank entry, or 2 flight cycles after fuel tank entry, whichever comes later,perform the Main Fuel PumpStrainer Inspection/Check procedure on the left inboard engineper AMM 73-11-04, Task 73-11-04-200-802-G00. Collect any material removedfrom the fuel pump strainer totroubleshoot the source of the fuel system contamination. One flight cycle may be added to these limits in the eventof an unscheduled landing.3. Following a right inboard main fuel tank purging and maintenance activity inside the right inboard main fuel tank, perform the following tasks:a. After the next flight check for the presence of the ENG X FUEL STR EICAS status message, interrogate the CMC to check for thepresence of theENG-X FUEL STRAINER IMPENDING BYPASS OR BYPASSED 'COLLECTOR' message. Troubleshoot the source ofthe fuel systemcontamination if the messages are present.b. Prior to accumulating 20 flight hours after fuel tank entry, or 2 flight cycles after fuel tank entry, whichever comes later,perform the Main Fuel PumpStrainer Inspection/Check procedure on theright inboard engine per AMM 73-11-04, Task 73-11-04-200-802-G00. Collect any material removedfrom the fuel pump strainer totroubleshoot the source of the fuel system contamination. One flight cycle may be added to these limits in the eventof an unscheduled landing.4. Operation of a Model 747-8/8F Series airplane after September 30, 2017 is prohibited unless a modification to provide indication to the flight crew ofgross fuel contamination is installed in accordance with a method approved by the FAA Oversight Office. The FAA approval must specifically referencethis airworthiness limitation.SYSTEM AIRWORTHINESS LIMITATION 3ENGINE POST-SHUTDOWN FUEL VAPOR VENTINGOperation of a Model 747-8/8F Series airplane after December 31,2014 is prohibited unless a modification to eliminate Engine Post-shutdown Fuel VaporVenting is installed in accordance with a method approved by the FAA Oversight Office.The FAA approval must specifically reference thisairworthiness limitation.OCT 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-114747-8/8F AIRWORTHINESS LIMITATIONSSYSTEM AIRWORTHINESS LIMITATION 4REPORTING 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, orpowerplant that occurs or is detected at any time if, in its opinion, that failure, malfunction, or defect has endangered or may endanger the safe operation ofan aircraft”. Title 14 CFR § 125.409 also requires reporting offailures, malfunctions, or defects. In many cases a reportable failure or malfunction will beobvious, but there are some failure modes related to uncontrolledhigh thrust that are reportable but may not be obvious. Thefollowing information isprovided, as required by FAA Exemption No. 8518, to assist the operators in identifying reportable malfunctions related to uncontrolled high thrust.The FAA has concluded that the loss of capability to control thrust due to a failure of the engine thrust control system may endanger the aircraft. Thisincludes any malfunctions having one ormore of the following characteristics:• Stuck thrust lever above idle power.• No response to thrust lever, with the cause being a mechanical failure in the thrustlever mechanism or resolver.Although some 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 failure conditions that must be corrected. When filing a report of such an event with the FAA, the operator is requested toinclude in the description of the event one or more of the following phrases:• “thrust control”• “no response to thrust lever”• “auto-acceleration”• “uncontrolled high thrust”MAY 2014747-8/8F AIRWORTHINESS LIMITATIONSD011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-115In 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 isrecommended that a copy be sent to Boeing and to theengine manufacturer.SYSTEM AIRWORTHINESS LIMITATION 5747-8/8F ENGINE OPERATING LIMITATION FOR ICE CRYSTAL ICINGFor GEnx-2B powered airplanes, following flight crew reportof Engine Rollback, or ENG X THRUST EICAS Caution message in Ice Crystal Icing conditions,perform borescope of all HPC Stage 1 bladeairfoils with borescope prior to the nextrevenue service flight for all affected engines, and other engines asrequired so that no more than one engine is left uninspected. Reference Boeing 747-8 AMM TASK 71-00-00-200-816-G00.SYSTEM AIRWORTHINESS LIMITATION 6747-8/8F FLIGHT DECK ANNUNCIATION OF ENGINE VARIABLE BLEED VALVE ICE PROTECTION SYSTEMOperation of a Model 747-8/8F Series airplane after March 31, 2016 is prohibited unless a modification to provide flight-deck annunciation of operation ofthe engine variable bleed valve ice protection system is installed in accordance with a method approved by the FAA Oversight Office. The FAA OversightOffice approval must specifically reference this airworthiness limitation.OCT 2014D011U721-02-01BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details Page 1.0-116747-8/8F AIRWORTHINESS LIMITATIONSTHIS PAGE INTENTIONALLY LEFT BLANKBLANK