747-8/8F AIRWORTHINESS LIMITATIONS

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747-8/8F

AIRWORTHINESS LIMITATIONS (AWLs)

D011U721-02-01

SEPTEMBER 2015

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COMPILED AND PUBLISHED BY:

MAINTENANCE PROGRAMS ENGINEERING

COMMERCIAL AVIATION SERVICES

BOEING COMMERCIAL AIRPLANE GROUP

SEATTLE, WASHINGTON

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TABLE OF CONTENTS

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

C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE-LIFE PARTS .....................................................................................

D. AIRWORTHINESS LIMITATIONS – SYSTEMS LIFE-LIMITED PARTS .......................................................................................

E. AIRWORTHINESS LIMITATIONS – SYSTEMS ............................................................................................................................

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REVISIONS 

REVISION AND REVISION DESCRIPTION 

AUGUST 2011Original Release

A 

SEPTEMBER 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 of 747-8/8F.Deleted “(Section 9)” from Item 1 in the Removal of Excess Sealant When Inspecting section because it is no longer applicable in this 

statement.Revised the systems life-limited part applicability in the Applicability Specifications column of the table in Section D from "Applicable to all 

747-8F and 747-8I Airplanes" to "Applicable to all 747-8 and 747-8F Airplanes”.

A 

DECEMBER 2011Revised the Systems Life-Limited Parts Table in Section D by removing the 5 year life limit of the Inboard Aileron Power Control Unit (PCU) 

1579100-7. This revision is based on ST-TSR-272 Rev F, 11/08/2011 Qualification Report for 747-8 Inboard Aileron PCU Assy and

Certification Plan #11624, Revision B: Certification of 747-8/747-8F Inboard Aileron PCU - Elimination of Life Limit. 

A 

APRIL 2012Revised the table of Supplemental Structural Inspection Requirements by adding SSI Numbers 57-20-W11 R3 and 54-50-002d R3.

A 

JULY 2012Revised the fuel tank sealant removal and restoration reference for fuel tank inspection in Item 3, General Notes by replacing the reference to 

MPD 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 Exhaust Nozzle from 2,800 to 9,000 flight cycles, from 1,200 to 4,650 flight cycles for the Engine Primary Exhaust Forward Plug, and 1,900 to 4,300 

flight cycles for the Engine Primary Exhaust Aft Plug.Revised the title of System Airworthiness Limitation Number 2 in Section E by deleting the word "Center", as this limitation also pertains to the left and right inboard main fuel tanks.

A 

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JANUARY 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 AMM 

54-05-03-211-801 and AMM 54-05-03-212-832 to AMM 54-05-03-211-802.

A 

JULY 2013Revised Section E – Systems Airworthiness Limitation 2 to add flight cycle data in accordance with Regulatory Docket Number FAA-2010-

1268 Exemption Number 10267B.

NOVEMBER 2013Revised Section B. Airworthiness Limitations - Structural Inspections by adding SSI Number 54-50-003 Forward Engine Mount AWL for 

Ultrasonic Inspection of Barrel Nuts for cracked nuts in 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 - Aft Plug, Primary Exhaust 030-22229-3, and renumbering the remaining table items accordingly.Revised Section E - Airworthiness Limitations - Systems by adding System Airworthiness Limitation No. 5 ENGINE OPERATING LIMITATIONS FOR ICE CRYSTAL ICING.

JANUARY 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 line number. The AWL of 5000 flight cycles is applicable to the 734-19150-

09 and 734-19150-10 Hydraulic Control Modules (HCM) regardless of which line number airplane they are installed on. The 5000 flight cycle AWL for the HCMs was included in the original release of this document, but was subsequently revised in error to include a reference 'prior to 

L/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 installed on 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”.

APRIL 2014Revised Section A to define “FAA Oversight Office” and replaced all references to "Seattle FAA ACO” with "FAA Oversight Office" throughout the entire document.Deleted AWL 54-50-003 implemented in the NOV 2013 revision that required UT inspection of Forward Engine Mount Barrel Nut SL4081C14SP1 per Service Bulletin 747-71A2329.Added AWL 54-50-003c applicable to production airplanes with Barrel Nut SL4750NA, and all airplanes that have accomplished Service Bulletin 747-71-2332, which replaced Barrel Nut SL4081C14SP1 with SL4750NA.

REVISION AND REVISION DESCRIPTION 

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MAY 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 regarding repairs and added additional Title 14 CFR 

references 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 program 

intervals and other related information applicable to certain Structures and Zonal Tasks that have reached the implementation threshold. With 

this, the operational limit has been raised to the inspection threshold values until required NDI inspection procedures are validated, published in 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 Airworthiness 

Limitations – Structural Inspection Thresholds.Revised the instructions for removing excess sealant and added the Excess Sealant Table for Structural Significant Items (SSIs) requiring 

fastener 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.

JULY 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.

OCTOBER 2014Deleted the Boeing submittal signature column from the Revision Log to improve the layout and provide consistency across all Section 

9/AWL/CMR/SCI documents. A submittal signature will no longer be included in the revision log; only the FAA BASOO approval date will 

be shown.Revised the compliance date for System Airworthiness Limitation number 2, item 4 from December 31, 2016 to September 30, 2017 regarding implementation of a flight crew indication 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 1 blade airfoils inspection.Added System Airworthiness Limitation 6 in reference to flight-deck annunciation modification regarding operation of the engine variable 

bleed valve ice protection system.

SEPTEMBER 2015Deleted three conditions from the A. SCOPE front matter regarding exceptions to the FAA Oversight Office's approval requirement of alternate inspections for modified or repaired structure where standard 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.

REVISION AND REVISION DESCRIPTION 

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747-8/8F AIRWORTHINESS LIMITATIONS

A. SCOPE

The scheduled maintenance requirements described in this document result from Model 747-8/8F airplane certification activitie

Aviation Administration (FAA). Accordingly, this FAA approved Airworthiness Limitations document D011U721-02-01 is cross-r

747-8/8F 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 

Regulations (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 “FAA Oversight Office” is defined as the FAA office that currently has oversight responsof the Boeing model 747-8/8F. At the time of publication, the FAA office with oversight responsibility for the type certificate of the 

Aviation 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 be aand/or alterations, an alternate inspection approved by the FAA Oversight Office must be used.

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B. AIRWORTHINESS LIMITATIONS – STRUCTURAL INSPECTIONS

INTRODUCTIONThe Structural Inspection Program and the Zonal Inspection Program approved in the 747-8/8F Maintenance Review Board Re

and contained in the 747-8/8F Maintenance Planning Document (MPD) D011U721-02, describe an initial baseline Structural Ma

Structurally Significant Items (SSIs). These programs were developed in accordance with the guidelines of MSG-3, Revision 2

the requirements of Title 14 CFR § 25.571 by providing accidental and environmental damage detection opportunity for all SSIsdamage detection opportunity. The supplemental structural inspections listed in the Airworthiness Limitations are for those SSIadequate fatigue damage detection opportunity from the initial baseline structural and zonal programs that are listed in the 747supplemental inspections shown in this Airworthiness Limitations document are to be accomplished in addition to the baseline The Supplemental Structural Inspection Program (SSIP) uses the DTR system to determine the inspections (and repeat interva

adequate fatigue damage detection. The DTR system defines a required DTR (a numerical value) that must be achieved for eawhich define the inspection options and the required DTR are contained in Document D011U721-05. At least one form is shown 

THRESHOLD (747-8/8F AIRPLANES)The fatigue inspection requirements apply after the accumulation of a certain number of flights and/or hours (threshold). The ini

be accomplished prior to the flight cycle and/or flight hour threshold listed, whichever comes first. The threshold for each of the 

inspections are defined in the Airworthiness Limitations – Structural Inspections Threshold Table. No airplane may be operated operational limit) stated in the Airworthiness Limitations – Structural Inspections Threshold Table until any required NDI inspectiopublished in the appropriate manual, and accepted by the FAA.

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Since Boeing will not have the DTR Check Forms and inspection procedures published at the time of the issuance of the Amen

the FAA has agreed to the following three-staged approach. This approach will substitute a Temporary Operational Limitation i

Threshold until the damage tolerance procedures are completely published at the end of Stage 3. This approach is illustrated f

table below:The Airworthiness Limitations listed in this AWL document cover structure for which the required DTR is not met by the baselininspections of the 747-8/8F MPD. Any continued escalation beyond the MPD baseline Structures and Zonal Programs may resu

meeting the required DTR which is the basis of certification and thus must be de-escalated to the MPD baseline Structures and 

and beyond.

Stage Description Published Completion Date Details of Publication Threshold

1 Baseline Inspection Program 

Data published. (Complete)

Prior to issuance of the 747-8/8F ATC.

MPD Structures and Zonal Program at time of certification

Not Applicable 

2 Supplemental structural 

fatigue inspection thresholds and DTR Check Forms published.(Complete)

Three years or 7,500 total flight cycles from issuance of 747-8F ATC, whichever comes first.

Thresholds and DTR Check Forms for all PSEs / Inspection Methods (visual, HFEC, LFEC, UT, etc.) identified.

Thresholds are tabulated each PSE requiring supplemental inspection

3 NDT Manual Procedures 

published.

To Be Determined (TBD), prior to Stage 2 operational limit.

NDT Manual: Inspection procedure details (including inspection equipment, standards, probes, etc.) are developed and documented and are available to the operators.

Same as Stage 2. 

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In addition to the threshold described above, a calendar threshold of 20 years applies unless an initial inspection of an FAA app

and Control Program (CPCP) has occurred, constituting CPCP implementation. The CPCP identified within the Structural Main

Maintenance Review Board Report (D011U721-01) is FAA approved.The Airworthiness Limitations – Structural Inspections Threshold Table defines the Inspection Implementation Threshold for the 

sensitive to flight length are identified by "FLS" or flight hours per cycle utilization of the airplane (e.g., "< 7 hrs", ">= 7 hrs", etc.this table. These Flight Length Sensitive (FLS) Items require both flight hours and flight cycles to determine the Implementation 

Airworthiness Limitations – Structural Inspections Threshold Table, Figure 1, or Figure 2, as indicated, to determine the thresho

Initial inspections (thresholds) and intervals are measured in flight cycles or flight hours that a particular SSI detail has accumu

airframe as a whole has accumulated. Most SSI details have never been replaced and therefore have accumulated the same fligthe airframe. Some SSI details are replaced, such as when installing Removable Structural Components (repairable/rotable/expstructural parts as a repair. In these cases, the SSI details have accumulated flight cycles and flight hours that may be different operator must account for this in determining when inspections must be done.REPORTING RESULTS OF STRUCTURAL INSPECTIONSAll cracks found during these inspections shall be reported within ten (10) days directly to the Manager of the FAA Oversight Of

Directorate, the FAA, and to the Boeing Commercial Airplane Group using the Discrepant Structure Report Form. Refer to Docrequired report form (any suitable alternative which contains the same information may be used).

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747-8/8F AIRWORTHINESS LIMITATIONS

USE OF THE FLS THRESHOLD CURVE (747-8/8F)For FLS Items only, all non-FLS SSIs have thresholds as listed in the Airworthiness Limitations – Structural Inspections Thresh

1. Determine the FLS status and threshold from the Threshold column in the Airworthiness Limitations – Structural Inspection2. 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 approp

Threshold 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 Airworthin

Inspections Threshold Table), then the SSI has not reached the Inspection Implementation Threshold. If the point determine

the right, or outside the Threshold Curve for the SSI, then the Inspection Implementation Threshold has been reached.

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REPEAT INSPECTION INTERVALA Repeat Interval for the Fatigue Inspection of an SSI is established from its respective DTR Check Form. The DTR Check For

Damage Tolerance assessment/evaluation documented during certification of the airplane. Revisions to the required DTR Chec

not 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 for thinspection interval should be based on the DTR Check Form with the corresponding “hrs” utilization in the Model-Series field, if average hours per flight is longer than the prior average hours per flight, the current average hours per flight should be used foCheck Form should be utilized and the inspection 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 tasks tairplane reaching the de-escalation threshold in order to ensure the maintenance program complies with the damage tolerance 747-8/8F aircraft. The baseline Structures and Zonal Program Tasks included in the Post-Threshold Intervals Table provide creTitle 14 CFR § 25.571 damage tolerance evaluation. As such, when reaching the de-escalation threshold listed for a given inspe

that inspection must be the lesser of:• that published in the Structural and Zonal Inspection Requirements in the FAA approved 747-8/8F MRBR at the time thresh• that shown in the Post-Threshold Intervals Table, which represents baseline maintenance intervals at the time of certificatio

This means that any operator, who may have escalated these Structures or Zonal Program tasks by changing task intervals, m

frequencies as defined above once the threshold listed in the Post-Threshold Intervals Table is reached. For FLS items, the dealso be defined by the same Figure 1 or 2, as noted, that is used to define thresholds in the Airworthiness Limitations – StructuTable as discussed.

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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 Airplanes

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

52-410-00 Nose Cargo Door INTERNAL – DETAILED: Nose Cargo Door

Detailed Inspection of the nose cargo door internal structure to include: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 door linings and insulation blankets removed.

INTERNAL – DETAILED N/

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52-415-00 Forward Lower Lobe 

Cargo Compartment Door

INTERNAL – DETAILED: Forward Lower Lobe Cargo Compartment DoorDetailed Inspection of the forward lower lobe cargo compartment door 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 door lining removed and rain baffle 

removed for access to door frame at hinge with door open.

INTERNAL – DETAILED 20,00

52-420-00 Aft Lower Lobe 

Cargo Compartment Door

INTERNAL – DETAILED: Aft Lower Lobe Cargo Compartment DoorDetailed Inspection of the aft lower lobe cargo compartment door 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 door lining removed and rain baffle 

removed for access to door frame at hinge with door open.

INTERNAL – DETAILED 20,00

52-425-00 Bulk Cargo 

Compartment Door

INTERNAL – DETAILED: Bulk Cargo Compartment DoorDetailed Inspection of the bulk cargo compartment door internal structure to include:FramesStop beamsStiffeners and intercostalsSkinsINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect with door linings removed.

INTERNAL – DETAILED 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

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52-430-00 Main and Upper 

Deck Entry Doors

INTERNAL – DETAILED: Main and Upper Deck Entry DoorsDetailed Inspection of main deck entry & upper deck doors internal structure to include:FramesStop beamsStiffeners and intercostalsSkinsUpper and lower gatesINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect with door linings removed.

INTERNAL – DETAILED 20,00

52-435-00 Main Deck Entry 

Door Stops

EXTERNAL – DETAILED: Main Deck Entry Door StopsDetailed Inspection of main deck entry door stops to include:Stop fittingsStop pinsINTERVAL NOTE: Whichever comes first.

EXTERNAL – DETAILED 20,00

52-440-00 Main Deck 

Side Cargo Compartment Door

INTERNAL – DETAILED: Main Deck Side Cargo Compartment DoorDetailed Inspection of the main deck side cargo compartment door internal structure to include:FramesStiffeners and intercostalsSkinsDoor hinge and support structureINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect with door linings removed and rain baffle removed for access to door frame at hinge with door open.

INTERNAL – DETAILED N/

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

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52-450-00 Upper Deck Crew 

Service Door and Main Deck Entry Door 1L

INTERNAL – DETAILED: Upper Deck Crew Service Door and Main Deck Entry Door 1LDetailed Inspection of the upper deck crew service door and the main deck entry door 1L internal structure to include:FramesStop beamsStiffeners and intercostalSkinsUpper and lower gatesINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect with door linings removed.

INTERNAL – DETAILED N/

52-804-01 NOSE CARGO 

DOOR

EXTERNAL – ZONAL (GVI): NOSE CARGO DOORGeneral Visual Inspection of the nose cargo door.INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL 

(GVI)

N/

52-806-01 CARGO 

COMPARTMENT DOOR – FORWARD

EXTERNAL – ZONAL (GVI): CARGO COMPARTMENT DOOR – FORWARDGeneral Visual Inspection of the forward cargo container compartment door.INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL 

(GVI)

20,00

52-808-01 CARGO 

COMPARTMENT DOOR – AFT

EXTERNAL – ZONAL (GVI): CARGO COMPARTMENT DOOR – AFTGeneral Visual Inspection of the aft cargo container compartment door.INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL 

(GVI)

20,00

52-810-01 CARGO 

COMPARTMENT DOOR – BULK

EXTERNAL – ZONAL (GVI): CARGO COMPARTMENT DOOR – BULKGeneral Visual Inspection of the bulk cargo compartment door.INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL 

(GVI)

20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

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52-811-01 MAIN DECK 

ENTRY DOOR NO. 1, 2, 3, 4, 5 – LEFT SIDE

EXTERNAL – ZONAL (GVI): MAIN DECK ENTRY DOOR NO. 1, 2, 3, 4, 5 – LEFT SIDEGeneral Visual Inspection of the left main deck entry door no. 1, 2, 3, 4, 5.INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL 

(GVI)

20,00

52-812-01 MAIN DECK ENTRY 

DOOR NO. 1 – LEFT SIDE

EXTERNAL – ZONAL (GVI): MAIN DECK 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/

52-813-01 MAIN DECK 

ENTRY DOORNO. 1, 2, 3, 4, 5 – RIGHT SIDE

EXTERNAL – ZONAL (GVI): MAIN DECK 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)

20,00

52-814-01 MAIN DECK SIDE 

CARGO DOOR

EXTERNAL – 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/

52-816-01 UPPER DECK 

EMERGENCY DOOR – LEFT and RIGHT

EXTERNAL – 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) 20,00

52-822-01 UPPER DECK 

CREW SERVICE DOOR

EXTERNAL – ZONAL (GVI): UPPER DECK CREW SERVICE DOORGeneral Visual Inspection of the upper deck crew service door.INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL (GVI) N/

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-400-00 Area Forward of 

Nose Wheel Well

INTERNAL – DETAILED: Area Forward of Nose Wheel WellDetailed Inspection of the nose cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – DETAILED N/

53-405-00 Area Forward of 

Nose Wheel Well

EXTERNAL – 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 – DETAILED N/

53-410-00 Nose Wheel Well EXTERNAL – DETAILED: Nose Wheel Well

Detailed 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 – DETAILED 20,00

53-410-01 Area Outboard of 

Nose Wheel Well

INTERNAL – GENERAL VISUAL: Area Outboard of Nose Wheel WellGeneral 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 remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – 

GENERAL VISUAL

20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-410-02 Body Station 400 to 

Body Station 1000

INTERNAL – GENERAL VISUAL: Body Station 400 to Body Station 1000General Visual Inspection of the fuselage structure from BS 400 to BS 1000INTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – 

GENERAL VISUAL

20,00

53-415-00 Forward Cargo 

Container Compartment Forward Half

INTERNAL – DETAILED: Forward Cargo Container Compartment Forward HalfDetailed Inspection of the forward cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – DETAILED 20,00

53-420-00 Forward Cargo 

Container Compartment Forward Half

EXTERNAL – DETAILED: Forward Cargo Container Compartment Forward HalfDetailed Inspection of the forward cargo door latch supportsINTERVAL NOTE: Whichever comes first.

EXTERNAL – DETAILED 20,00

53-420-01 Area Aft of the 

Forward Cargo Container Compartment

INTERNAL – GENERAL VISUAL: Area Aft of the Forward Cargo Container CompartmentGeneral Visual Inspection of the BS 1000 bulkheadINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – 

GENERAL VISUAL

20,00

53-425-00 Pressurized Area 

from bottom of Main Cabin Floor to Pressure Deck (Sta 1000 to 1241)

INTERNAL – DETAILED: Pressurized Area from bottom of Main Cabin 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 – DETAILED FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-430-00 Wing and Body 

Landing Gear Wheel Well

EXTERNAL – 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 1480 bulkheadLanding gear side strut support fitting and attachment to BS 1350 bulkheadLanding gear drag and jury strut fittings and attachmentsINTERVAL NOTE: Whichever comes first.

EXTERNAL – DETAILED 20,00

53-430-01 Body Station 1480 to 

Body Station 2360

INTERNAL – GENERAL VISUAL: Body Station 1480 to Body Station 2360General 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 remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – 

GENERAL VISUAL

20,00

53-435-00 Aft Cargo Container 

Compartment

INTERNAL – DETAILED: Aft Cargo Container CompartmentDetailed Inspection of the aft cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – DETAILED 20,00

53-440-00 Aft Cargo Container 

Compartment

EXTERNAL – DETAILED: Aft Cargo Container CompartmentDetailed Inspection of the aft cargo door latch supportsINTERVAL NOTE: Whichever comes first.

EXTERNAL – DETAILED 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-445-00 Bulk Cargo 

Compartment

INTERNAL – DETAILED: Bulk Cargo CompartmentDetailed Inspection of the bulk cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – DETAILED 20,00

53-450-00 Bulk Cargo 

Compartment

EXTERNAL – DETAILED: Bulk Cargo CompartmentDetailed Inspection of the bulk cargo door stop fittingsINTERVAL NOTE: Whichever comes first.

EXTERNAL – DETAILED 20,00

53-455-00 Keel 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 beam between BS 1265 and BS 1480INTERVAL NOTE: Whichever comes first.

INTERNAL – 

GENERAL VISUAL

20,00

53-460-00 Wing-to-Body 

Fairing, Forward and Aft Lower Half

INTERNAL – DETAILED: Wing-to-Body Fairing, Forward and Aft Lower HalfDetailed Inspection under the wing-to-body fairing of the underwing longeronINTERVAL NOTE: Whichever comes first.

INTERNAL – DETAILED 20,00

53-465-00 Upper Half 

of Fuselage

INTERNAL – DETAILED: Upper Half of FuselageDetailed Inspection of the tension ties with frames and attachmentsINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove ceiling panels.

INTERNAL – DETAILED 20,00

53-470-00 Main and Upper 

Deck Door Cutout Stops

EXTERNAL – DETAILED: Main and Upper Deck Door Cutout StopsDetailed Inspection of the stops on the main entry door cutout and upper deck door cutouts.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: As visible with doors open.

EXTERNAL – DETAILED 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-475-00 Main Deck INTERNAL – DETAILED: Main Deck

Detailed Inspection of the nose cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – DETAILED N/

53-480-00 Main and Upper 

Deck Door Cutouts

INTERNAL – 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 remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – DETAILED 20,00

53-485-00 Control Compartment 

Body BS 240 to 380

EXTERNAL – DETAILED: Control Compartment Body BS 240 to 380Detailed Inspection of the crew compartment window structure and skinINTERVAL NOTE: Whichever comes first.

EXTERNAL – DETAILED 20,00

53-490-00 Control Compartment 

Body BS 240 to 380

INTERNAL – DETAILED: Control Compartment Body BS 240 to 380Detailed Inspection of the Crew Compartment Window Structure and SkinINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – DETAILED 20,00

53-495-00 Main Deck EXTERNAL – DETAILED: Main Deck

Detailed Inspection of the latch fittings on the main deck side cargo door cutoutINTERVAL NOTE: Whichever comes first.

EXTERNAL – DETAILED N/

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-500-00 Main Deck INTERNAL – DETAILED: Main Deck

Detailed Inspection of the main deck side cargo door cutoutINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – DETAILED N/

53-505-00 Main Deck and 

Upper Area Above Ceiling

INTERNAL – DETAILED: Main Deck and Upper Area Above CeilingDetailed Inspection of the BS 2360 pressure bulkhead and attachments – Forward SideINTERVAL NOTE: Whichever comes first.ACCESS NOTE: For access remove or displace all systems, equipment and interior furnishings as necessary to accomplish visual inspection.

INTERNAL – DETAILED 20,00

53-510-00 Wing-to-Body 

Fairing, Forward and Aft Upper Half

INTERNAL – DETAILED: Wing-to-Body Fairing, Forward and Aft Upper HalfDetailed Inspection under the wing-to-body fairing of the overwing longeron and spliceINTERVAL NOTE: Whichever comes first.

INTERNAL – DETAILED 20,00

53-515-00 Area Aft of Pressure 

Bulkhead

EXTERNAL – DETAILED: Area Aft of Pressure BulkheadDetailed Inspection of the BS 2360 pressure bulkhead and stringer end fittingsINTERVAL NOTE: Whichever comes first.

EXTERNAL – DETAILED 20,00

53-520-00 Stabilizer Torsion 

Box Compartment

EXTERNAL – DETAILED: Stabilizer Torsion Box CompartmentDetailed Inspection of the horizontal stabilizer jack screw attachments and support structure and the upper and lower stabilizer longeron splice fittingsINTERVAL NOTE: Whichever comes first.

EXTERNAL – DETAILED 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-525-00 Stabilizer Torsion 

Box Compartment and Area Aft of Stabilizer Box Compartment

EXTERNAL – DETAILED: Stabilizer Torsion Box Compartment and Area Aft of Stabilizer Box CompartmentDetailed Inspection of the BS 2598 bulkheadINTERVAL NOTE: Whichever comes first.

EXTERNAL – DETAILED 20,00

53-530-00 APU Compartment EXTERNAL – DETAILED: APU Compartment

Detailed Inspection of the APU support structure and attachmentsINTERVAL NOTE: Whichever comes first.

EXTERNAL – DETAILED 20,00

53-804-01 LOWER HALF OF 

FUSELAGE

EXTERNAL – ZONAL (GVI): LOWER HALF OF FUSELAGEGeneral Visual Inspection of the lower half of the fuselage, including radome, service doors, wing-to-body fairings, and doorways.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: With FWD and center EE bay doors open.

EXTERNAL – ZONAL (GVI) 20,00

53-806-01 RADOME WITH 

RADOME OPEN

INTERNAL – ZONAL (GVI): RADOME WITH RADOME OPENGeneral Visual Inspection of the radome with radome open.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

53-808-01 AREA INSIDE OF 

FUSELAGE FORWARD OF NOSE GEAR WELL

INTERNAL – ZONAL (GVI): AREA INSIDE OF FUSELAGE FORWARD OF NOSE GEAR WELLGeneral Visual Inspection of the area inside of fuselage forward of nose gear well. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Insulating blankets removed or displaced as required.

INTERNAL – ZONAL (GVI) 20,00

53-812-01 NOSE GEAR WELL EXTERNAL – ZONAL (GVI): NOSE GEAR WELL

General Visual Inspection of the nose gear well. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: NLG doors open.

EXTERNAL – ZONAL (GVI) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-814-01 AREA INSIDE 

FUSELAGE, ABOVE AND OUTBOARD OF NLG WELL

INTERNAL – ZONAL (GVI): AREA INSIDE FUSELAGE, ABOVE AND OUTBOARD OF NLG WELLGeneral Visual Inspection of the area inside of fuselage above and outboard of nose gear well. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Insulation blankets removed or displaced as required. Remove rubber mat for access to structural boxes located 

forward of BS 400. Remove cabin floor panels as required to get access to area above NLG wheel well.

INTERNAL – ZONAL (GVI) 20,00

53-816-01 E/E 

COMPARTMENT

EXTERNAL – ZONAL (GVI): E/E COMPARTMENTGeneral Visual Inspection of the interior of E/E compartment. (EZAP)INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL (GVI) 20,00

53-818-01 E/E 

COMPARTMENT

INTERNAL – 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 as required, without removing electrical/electronics panels.

INTERNAL – ZONAL (GVI) 20,00

53-822-01 FORWARD CARGO 

CONTAINER COMPARTMENT

INTERNAL – ZONAL (GVI): FORWARD CARGO CONTAINER COMPARTMENTGeneral Visual Inspection of the interior of forward cargo container compartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Sidewall and ceiling panels removed. Insulating blankets removed or displaced as required.

INTERNAL – ZONAL (GVI) 20,00

53-824-01 AREA BELOW 

FORWARD CARGO CONTAINER COMPARTMENT

EXTERNAL – ZONAL (GVI): AREA BELOW FORWARD CARGO CONTAINER COMPARTMENTGeneral Visual Inspection of the area below forward cargo container compartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Floor panels removed as required.

EXTERNAL – ZONAL (GVI) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-826-01 AFT OF FWD 

CARGO CONTAINER COMPARTMENT

INTERNAL – ZONAL (GVI): AFT OF FWD CARGO CONTAINER COMPARTMENTGeneral Visual Inspection of the area inside of fuselage aft of forward cargo container compartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Linings removed and insulation blankets removed or displaced as required.

INTERNAL – ZONAL (GVI) 20,00

53-827-01 KEEL BEAM INTERNAL – ZONAL (GVI): KEEL BEAM

General Visual Inspection of the Keel Beam. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

53-828-01 BOTTOM OF MAIN 

FLOOR TO PRESSURE DECK

INTERNAL – ZONAL (GVI): BOTTOM OF MAIN FLOOR TO PRESSURE DECKGeneral Visual Inspection of the area inside of fuselage from bottom of main cabin floor to pressure deck. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove floor panels.

INTERNAL – ZONAL (GVI) FLS, 

Figu

53-830-01 AIR CONDITIONING 

EQUIPMENT BAY

INTERNAL – ZONAL (GVI): AIR CONDITIONING EQUIPMENT BAYGeneral Visual Inspection of the air conditioning equipment bay. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

53-832-01 AIR CONDITIONING 

EQUIPMENT BAY

INTERNAL – ZONAL (GVI): AIR CONDITIONING EQUIPMENT BAYGeneral Visual Inspection of the air conditioning equipment bay.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

53-835-01 WING LANDING 

GEAR WELL – LEFT

EXTERNAL – 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) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-836-01 BOTTOM OF MAIN 

DECK FLOOR TO PRESSURE DECK

INTERNAL – ZONAL (GVI): BOTTOM OF MAIN DECK FLOOR TO PRESSURE DECKGeneral Visual Inspection of the area inside of fuselage from bottom of main cabin floor to pressure deck. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove floor panels.

INTERNAL – ZONAL (GVI) FLS, 

Figu

53-840-01 WING LANDING 

GEAR WELL – RIGHT

EXTERNAL – 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) 20,00

53-844-01 BODY 

LANDING GEAR WHEEL WELL – LEFT

EXTERNAL – ZONAL (GVI): BODY LANDING 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) 20,00

53-848-01 BODY 

LANDING GEAR WHEEL WELL – RIGHT

EXTERNAL – ZONAL (GVI): BODY LANDING 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) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-852-01 AFT CARGO 

CONTAINER COMPARTMENT

INTERNAL – ZONAL (GVI): AFT CARGO CONTAINER COMPARTMENTGeneral Visual Inspection of the interior of aft cargo container compartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Sidewall and ceiling panels removed. Insulating blankets removed or displaced as required.

INTERNAL – ZONAL (GVI) 20,00

53-854-01 AREA BELOW AFT 

CARGO CONTAINER COMPARTMENT

EXTERNAL – ZONAL (GVI): AREA BELOW AFT CARGO CONTAINER COMPARTMENTGeneral Visual Inspection of the area inside of fuselage below aft cargo container compartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Floor panels removed as required.

EXTERNAL – ZONAL (GVI) 20,00

53-858-01 BULK CARGO 

COMPARTMENT

INTERNAL – 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. Insulation blankets removed or displaced as required.

INTERNAL – ZONAL (GVI) 20,00

53-860-01 AREA BELOW 

BULK CARGO COMPARTMENT

INTERNAL – ZONAL (GVI): AREA BELOW BULK CARGO COMPARTMENTGeneral Visual Inspection of the area inside of fuselage below bulk cargo compartment. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to the Intercontinental only. For the Freighter, this task is classified exclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Two (2) center floor panels removed.

INTERNAL – ZONAL (GVI) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-862-01 AREA AFT OF 

BULK CARGO COMPARTMENT

INTERNAL – ZONAL (GVI): AREA AFT OF BULK CARGO COMPARTMENTGeneral Visual Inspection of the area inside of fuselage aft of bulk cargo compartment. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove floor panels from BS 2280 through BS 2360 of main cabin. Insulating blankets removed.

INTERNAL – ZONAL (GVI) 20,00

53-864-01 FWD LOWER WINGTO-BODY-FAIRING 

– LEFT

INTERNAL – 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) 20,00

53-866-01 FWD LOWER WINGTO-BODY-FAIRING 

– RIGHT

INTERNAL – 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) 20,00

53-868-01 AFT LOWER WINGTO-BODY-FAIRING 

– LEFT

INTERNAL – ZONAL (GVI): AFT LOWER WING-TO-BODYFAIRING – LEFTGeneral Visual Inspection of the area inside of aft lower wing-to-body fairing, left side. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to the Intercontinental only. For the Freighter, this task is classified exclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-870-01 AFT LOWER WINGTO-BODY-FAIRING 

– RIGHT

INTERNAL – ZONAL (GVI): AFT LOWER WING-TO-BODYFAIRING – RIGHTGeneral Visual Inspection of the area inside of aft lower wing-to-body fairing, right side. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to the Intercontinental only. For the Freighter, this task is classified exclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

53-874-01 UPPER HALF 

OF FUSELAGE

EXTERNAL – ZONAL (GVI): UPPER HALF OF FUSELAGEGeneral Visual Inspection of the upper half of fuselage, including windows and wing-to-body fairings.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: As visible with doors open.

EXTERNAL – ZONAL (GVI) 20,00

53-880-01 FUSELAGE 

MAIN DECK COMPARTMENT

INTERNAL – ZONAL (GVI): FUSELAGE MAIN DECK COMPARTMENTGeneral Visual Inspection of the interior of fuselage main deck compartment – (nose to BS 854 for freighter, nose to BS 1101 for passenger). (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove ceiling panels as required to perform inspection.

INTERNAL – ZONAL (GVI) 20,00

53-882-01 FUSELAGE 

MAIN DECK COMPARTMENT – NOSE TO BS 2360

INTERNAL – ZONAL (GVI): FUSELAGE MAIN DECK COMPARTMENT – NOSE TO BS 2360General Visual Inspection of the interior of fuselage main deck compartment – nose to BS 2360. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Sidewall panels and insulating blankets removed or displaced.

INTERNAL – ZONAL (GVI) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-884-01 INTERIOR OF 

FLIGHT DECK COMPARTMENT

EXTERNAL – ZONAL (GVI): INTERIOR OF FLIGHT DECK COMPARTMENTGeneral Visual Inspection of the flight deck compartment.INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL (GVI) 20,00

53-886-01 FLIGHT DECK 

COMPARTMENT

INTERNAL – 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 interior furnishings as necessary to accomplish visual inspection without displacing flight control panels/consoles, electrical panels or drip shield. Windshield/window removal is not required unless there is an indication of corrosion in the interface area.

INTERNAL – ZONAL (GVI) 20,00

53-888-01 INTERIOR OF 

FUSELAGE UPPER DECK COMPARTMENT

EXTERNAL – ZONAL (GVI): INTERIOR OF FUSELAGE UPPER DECK COMPARTMENTGeneral Visual Inspection of the interior of fuselage upper deck compartment (BS 380 to BS 633).INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL (GVI) 20,00

53-888-02 INTERIOR OF 

FUSELAGE AFT UPPER DECK COMPARTMENT

INTERNAL – ZONAL (GVI): INTERIOR OF FUSELAGE AFT UPPER DECK COMPARTMENTGeneral Visual Inspection of the interior of fuselage aft upper deck compartment – BS 633 to BS 1101.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

53-890-01 INTERIOR OF 

FUSELAGE UPPER DECK

INTERNAL – ZONAL (GVI): INTERIOR OF FUSELAGE UPPER DECKGeneral 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 panels as required. Insulating blankets removed or displaced as required.

INTERNAL – ZONAL (GVI) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-890-02 INTERIOR OF 

FUSELAGE AFT UPPER DECK COMPARTMENT

INTERNAL – ZONAL (GVI): INTERIOR OF FUSELAGE AFT UPPER DECK COMPARTMENTGeneral Visual Inspection of the interior of fuselage aft upper deck compartment – BS 633 to BS 1101. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove sidewall/ceiling panels as required. Insulating blankets removed or displaced as required.

INTERNAL – ZONAL (GVI) 20,00

53-892-01 AREA AFT OF 

UPPER DECK COMPARTMENT

INTERNAL – ZONAL (GVI): AREA AFT OF UPPER DECK 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/

53-894-01 AREA ABOVE 

CEILING INSIDE FUSELAGE, BS 854 to BS 2360

INTERNAL – ZONAL (GVI): AREA ABOVE CEILING INSIDE FUSELAGE, BS 854 to BS 2360General Visual Inspection of the area inside of fuselage above ceiling, BS 854 to BS 2360. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove ceiling panels as required.

INTERNAL – ZONAL (GVI) 20,00

53-900-01 AFT ELECTRONIC 

EQUIPMENT BAY

INTERNAL – ZONAL (GVI): AFT ELECTRONIC EQUIPMENT BAYGeneral Visual Inspection of the interior of aft electrical/electronic equipment bay. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Remove sidewall/ceiling panels as required.

INTERNAL – ZONAL (GVI) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-902-01 INTERIOR OF 

OVERHEAD CREW REST AREA

INTERNAL – ZONAL (GVI): INTERIOR OF OVERHEAD CREW REST AREAGeneral Visual Inspection of the interior of overhead crew rest area. (EZAP)AIRPLANE NOTE: Applicable to aircraft with overhead crew rest installed.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

53-906-01 UPPER WING-TOBODY FAIRING – 

FWD LEFT

INTERNAL – 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 the Intercontinental only. For the Freighter, this task is classified exclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

53-908-01 UPPER WING-TOBODY FAIRING – 

FWD RIGHT

INTERNAL – 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 the Intercontinental only. For the Freighter, this task is classified exclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

53-910-01 UPPER WING-TOBODY FAIRING – 

AFT LEFT

INTERNAL – ZONAL (GVI): UPPER WING-TO-BODY FAIRING – AFT LEFTGeneral Visual Inspection of the area inside of aft upper wing-to-body fairing, left side. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to the Intercontinental only. For the Freighter, this task is classified exclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-912-01 UPPER WING -TOBODY FAIRING – 

AFT RIGHT

INTERNAL – ZONAL (GVI): UPPER WING -TO – BODY FAIRING – AFT RIGHTGeneral Visual Inspection of the area inside of aft upper wing-to-body fairing, right side. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to the Intercontinental only. For the Freighter, this task is classified exclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

53-916-01 FUSELAGE BS 2360 

TO BS 2792

EXTERNAL – 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) 20,00

53-918-01 AREA AFT OF REAR 

PRESSURE BULKHEAD

EXTERNAL – ZONAL (GVI): AREA AFT OF REAR PRESSURE BULKHEADGeneral Visual Inspection of the area inside of fuselage aft of rear pressure bulkhead (BS 2360 to BS 2484), including access door. (EZAP)INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL (GVI) 20,00

53-919-01 AREA UNDER 

VERTICAL AND HORIZONTAL STABILIZER FAIRINGS

INTERNAL – ZONAL (GVI): AREA UNDER VERTICAL AND HORIZONTAL STABILIZER FAIRINGSGeneral Visual Inspection of the area under the vertical and horizontal stabilizer fuselage fairings.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Vertical and Horizontal Stabilizer Fairings.

INTERNAL – ZONAL (GVI) 20,00

53-920-01 STABILIZER 

TORSION BOX COMPARTMENT

EXTERNAL – ZONAL (GVI): STABILIZER TORSION BOX COMPARTMENTGeneral Visual Inspection of the horizontal stabilizer torsion box compartment. (EZAP)INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL (GVI) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-922-01 AFT OF 

HORIZONTAL STABILIZER TORSION BOX COMPARTMENT

EXTERNAL – ZONAL (GVI): AFT OF HORIZONTAL STABILIZER TORSION BOX COMPARTMENTGeneral Visual Inspection of the area inside of fuselage aft of horizontal stabilizer torsion box compartment. (EZAP)INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL (GVI) 20,00

53-924-01 INTERIOR OF APU 

COMPARTMENT

EXTERNAL – 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) 20,00

54-405-00 Forward Fairing – 

Strut No. 1, 2, 3, 4

EXTERNAL – 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 and wing fittingsINTERVAL NOTE: Whichever comes first.ACCESS NOTE: Upper link or pin removal not required.

EXTERNAL – DETAILED FL

< 7 

15,00

≥ 7 

10,00

54-410-00 Torque Box – 

Strut No. 1, 2, 3, 4

INTERNAL – 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 VISUAL

FL

< 7 

15,00

≥ 7 

10,00

54-415-00 Torque Box – 

Strut No. 1, 2, 3, 4

INTERNAL – 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 VISUAL

FL

< 7 

15,00

≥ 7 

10,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

54-420-00 Aft Fairing – 

Strut No. 1, 2, 3, 4

INTERNAL – 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 adjacent strut 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 removal not required.

INTERNAL – DETAILED FL

< 7 

15,00

≥ 7 

10,00

54-425-00 Aft Fairing and 

Torque Box – Strut No. 1 & 4

INTERNAL – DETAILED: Aft Fairing and Torque Box – Strut No. 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 the aft upper spar fittingsVertical flange of the aft upper spar fittingsINTERVAL NOTE: Whichever comes first.

INTERNAL – DETAILED 20,00

54-804-00 STRUT NO. 1, 2, 3, 4 

INCLUDING FAIRINGS

EXTERNAL – ZONAL (GVI): STRUT NO. 1, 2, 3, 4 INCLUDING FAIRINGSGeneral Visual Inspection of the strut no. 1, 2, 3, 4 including fairings.INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL (GVI) 20,00

54-806-00 AREA INSIDE 

FORWARD FAIRING NO. 1, 2, 3, 4

INTERNAL – ZONAL (GVI): AREA INSIDE FORWARD FAIRING NO. 1, 2, 3, 4General Visual Inspection of the area inside forward fairing. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

54-808-00 INTERIOR 

OF STRUT NO. 1, 2, 3, 4 TORQUE BOX

INTERNAL – ZONAL (GVI): INTERIOR OF STRUT NO. 1, 2, 3, 4 TORQUE BOXGeneral Visual Inspection of the interior of strut no. 1, 2, 3, 4 torque box. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

54-812-00 AREA INSIDE OF 

AFT STRUTNO. 1, 2, 3, 4 FAIRING

INTERNAL – ZONAL (GVI): AREA INSIDE OF AFT STRUT NO. 1, 2, 3, 4 FAIRINGGeneral Visual Inspection of the area inside of aft strut no. 1, 2, 3, 4 fairing. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) 20,00

55-400-00 Rudder INTERNAL – SPECIAL DETAILED: Rudder

Special Detailed Inspection of the upper rudder, lower rudder and rudder 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 DETAILED

FLS, 

Figu

55-405-00 Horizontal Stabilizer INTERNAL – GENERAL VISUAL: Horizontal Stabilizer

General Visual Inspection of the horizontal stabilizer internal structure.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Disassembly is not required.

INTERNAL – 

GENERAL VISUAL

FLS, 

Figu

55-410-00 Elevator INTERNAL – GENERAL VISUAL: Elevator

General Visual Inspection of the inboard elevator hinges & support structure on elevator.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Disassembly is not required.

INTERNAL – 

GENERAL VISUAL

FLS, 

Figu

55-415-00 Elevator INTERNAL – GENERAL VISUAL: Elevator

General Visual Inspection of the elevator internal structure.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Disassembly is not required.

INTERNAL – 

GENERAL VISUAL

FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

55-801-01 FIN AND RUDDER EXTERNAL – ZONAL (GVI): FIN AND RUDDER

General Visual Inspection of the fin and rudder.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Inspect visual portions of closure ribs when rudders are at maximum opposite displacement.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

55-802-01 FIN REMOVABLE 

LEADING EDGE

INTERNAL – ZONAL (GVI): FIN REMOVABLE LEADING EDGEGeneral Visual Inspection of the fin removable leading edge. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

55-803-01 FIN AUXILIARY 

SPAR TO FRONT SPAR

INTERNAL – ZONAL (GVI): FIN AUXILIARY SPAR TO FRONT SPARGeneral Visual Inspection of the fin auxiliary spar to front spar.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

55-805-01 FIN – FRONT SPAR 

TO REAR SPAR

INTERNAL – 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, 

Figu

55-806-01 FIN REAR SPAR TO 

TRAILING EDGE

INTERNAL – ZONAL (GVI): FIN REAR SPAR TO TRAILING EDGEGeneral Visual Inspection of the fin rear spar to rudders front spar including front spar of the lower rudder tab. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

55-808-01 FIN REAR SPAR TO 

TE CAVITY

INTERNAL – 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, 

Figu

55-809-01 FIN TIP INTERNAL – ZONAL (GVI): FIN TIP

General Visual Inspection of the fin tip. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

55-812-01 HORIZONTAL STAB 

AND ELEVATOR – LEFT

EXTERNAL – ZONAL (GVI): HORIZONTAL STAB AND ELEVATOR – LEFTGeneral Visual Inspection of the left horizontal stabilizer and elevator.INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

55-814-01 HORIZONTAL STAB 

REAR SPAR TO ELEVATOR FRONT SPAR – LEFT

INTERNAL – ZONAL (GVI): HORIZONTAL STAB REAR SPAR TO ELEVATOR FRONT SPAR – LEFTGeneral Visual Inspection of the left horizontal stabilizer rear spar to elevator front spar.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

55-816-01 HORIZONTAL STAB 

REAR SPAR TO ELEVATOR FRONT SPAR – LEFT

INTERNAL – ZONAL (GVI): HORIZONTAL STAB REAR SPAR TO ELEVATOR FRONT SPAR – LEFTGeneral Visual Inspection of the left horizontal stabilizer rear spar to elevator front spar. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

55-820-01 HORIZONTAL STAB 

AND ELEVATOR – RIGHT

EXTERNAL – ZONAL (GVI): HORIZONTAL STAB AND ELEVATOR – RIGHTGeneral Visual Inspection of the right horizontal stabilizer and elevator.INTERVAL NOTE: Whichever comes first.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

55-822-01 HORIZONTAL STAB 

REAR SPAR TO ELEVATOR FRONT SPAR – RIGHT

INTERNAL – ZONAL (GVI): HORIZONTAL STAB REAR SPAR TO ELEVATOR FRONT SPAR – RIGHTGeneral Visual Inspection of the right horizontal stabilizer rear spar to elevator front spar.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

55-824-01 HORIZONTAL STAB 

REAR SPAR TO ELEVATOR FRONT SPAR – RIGHT

INTERNAL – ZONAL (GVI): HORIZONTAL STAB REAR SPAR TO ELEVATOR FRONT SPAR – RIGHTGeneral Visual Inspection of the right horizontal stabilizer rear spar to elevator front spar. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

55-828-01 HORIZONTAL STAB 

CENTER SECTION TORSION BOX

INTERNAL – ZONAL (GVI): HORIZONTAL STAB CENTER SECTION TORSION BOXGeneral Visual Inspection of the horizontal stabilizer center section torsion box. (EZAP)AIRPLANE NOTE: The (EZAP) label for this task is applicable to the Intercontinental only. For the Freighter, this task is classified exclusively as a Zonal task.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

55-830-01 LEFT HORIZONTAL 

STABILIZER – FRONT SPAR TO REAR SPAR

INTERNAL – ZONAL (GVI): LEFT HORIZONTAL STABILIZER – FRONT SPAR TO REAR SPARGeneral Visual Inspection of the left horizontal stabilizer – stab. BL 43.5 to stab. STA 285. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

55-832-01 RIGHT 

HORIZONTAL STABILIZER – FRONT SPAR TO REAR SPAR

INTERNAL – ZONAL (GVI): RIGHT HORIZONTAL STABILIZER – FRONT SPAR TO REAR SPARGeneral Visual Inspection of the right horizontal stabilizer – stab. BL 43.5 to stab. STA 285. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-400-00 Center Section 

Wing Box

INTERNAL – DETAILED: Center Section Wing BoxDetailed Inspection of the internal structure of the center section wing box 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 – DETAILED FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-405-00 Wing-to-Body Fairing 

Lower Half

INTERNAL – 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 – DETAILED FLS, 

Figu

57-410-00 Raked Wing Tip INTERNAL – SPECIAL DETAILED: Raked Wing Tip

Special Detailed Inspection of the internal structure of the raked wing tip to include:LE beamRoot ribClosure ribTension ribFront sparRear sparUpper panelsLower panelsNOTE: Borescope/Videoscope required to do this internal inspection of the raked wing tip.INTERVAL NOTE: Whichever comes first.

INTERNAL – 

SPECIAL DETAILED

FLS, 

Figu

57-410-01 Raked Wing Tip EXTERNAL – GENERAL VISUAL: Raked Wing Tip

General Visual Inspection of the upper and lower skin panels of the raked wing tips.INTERVAL NOTE: Whichever comes first.

EXTERNAL – 

GENERAL VISUAL

FLS, 

Figu

57-415-00 Front Spar to 

Rear Spar from WBL 128.5 to WS 1244

INTERNAL – DETAILED: Front Spar to Rear Spar from WBL 128.5 to WS 1244Detailed Inspection of the outer wing lower skin access cutoutsINTERVAL NOTE: Whichever comes first.

INTERNAL – DETAILED FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-420-00 Inboard Main Tank – 

Front Spar to Rear Spar

INTERNAL – DETAILED: Inboard Main Tank – Front Spar to Rear SparDetailed Inspection of the splice joint between the center and outer wing 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 – DETAILED FLS, 

Figu

57-425-00 Outboard Main Tank 

– Front Spar to Rear Spar

INTERNAL – DETAILED: Outboard Main Tank – Front Spar to Rear SparDetailed Inspection of the dry bays above the outboard pylonINTERVAL NOTE: Whichever comes first.

INTERNAL – DETAILED FLS, 

Figu

57-425-01 Wing Upper 

Skin Panels

EXTERNAL – 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 upper surface – visible in leading edge bays with leading edge devices extendedUpper wing skin upper surface – visible in trailing edge bays with flaps, speed brakes and spoilers extended

EXTERNAL – 

GENERAL VISUAL

FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-425-02 Wing Lower 

Skin Panels

EXTERNAL – 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 leading edge bays with leading edge devices extendedLower skin panel lower surface – visible in trailing edge bays with trailing edge devices extendedLower skin panel lower surface – under pylon fairings

EXTERNAL – 

GENERAL VISUAL

FLS, 

Figu

57-430-00 Flap Track Fairings INTERNAL – DETAILED: Flap Track Fairings

Detailed Inspection of the internal area of the flap track fairings to 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,& #8 carriage assembliesOutboard Flap – Transmission Mount Structure.INTERVAL NOTE: Whichever comes first.

INTERNAL – DETAILED 20,00

57-435-00 Rear Spar to Landing 

Gear Support Beam

EXTERNAL – DETAILED: Rear Spar to 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 – DETAILED FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-440-00 Landing Gear 

Support Beam & Rear Spar to Trailing Edge

EXTERNAL – DETAILED: Landing Gear Support Beam & Rear Spar to Trailing EdgeDetailed Inspection of the spoiler beam fittings and attachment to flap tracks #3, #4, #5 & #6INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Spoilers and Flaps deployed

EXTERNAL – DETAILED FLS, 

Figu

57-445-00 Rear Spar to Inboard 

Aileron Leading Edge

INTERNAL – GENERAL VISUAL: Rear Spar to Inboard Aileron Leading EdgeGeneral Visual Inspection of the fixed trailing edge and inboard aileron to include:Fixed trailing edge hinge ribs & bearing linksAileron hinge fittings.INTERVAL NOTE: Whichever comes first.

INTERNAL – 

GENERAL VISUAL

FLS, 

Figu

57-450-00 Rear Spar to Inboard 

Aileron Leading Edge

INTERNAL – GENERAL VISUAL: Rear Spar to Inboard Aileron Leading EdgeGeneral Visual Inspection of the fixed trailing edge and inboard aileron to include:Fixed trailing edge actuator ribsAileron actuator rib – lug area forward of aileron front sparAileron front spar – forward surface.INTERVAL NOTE: Whichever comes first.

INTERNAL – 

GENERAL VISUAL

FLS, 

Figu

57-450-01 Flight Spoiler Inboard EXTERNAL – GENERAL VISUAL: Flight Spoiler Inboard

General Visual Inspection of the spoilerINTERVAL NOTE: Whichever comes first.

EXTERNAL – 

GENERAL VISUAL

FLS, 

Figu

57-450-02 Flight Spoiler 

Outboard

EXTERNAL – GENERAL VISUAL: Flight Spoiler OutboardGeneral Visual Inspection of the spoilerINTERVAL NOTE: Whichever comes first.

EXTERNAL – 

GENERAL VISUAL

FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-455-00 Inboard Main Flap INTERNAL – DETAILED: Inboard Main Flap

Detailed 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 – DETAILED 20,00

57-455-01 Inboard Main Flap INTERNAL – SPECIAL DETAILED: Inboard Main Flap

Special Detailed Inspection of the inboard main flap to include:Main support ribsSparsSkin panelsNOTE: Borescope/Videoscope required to do this internal inspection of the inboard main flap box.INTERVAL NOTE: Whichever comes first.

INTERNAL – 

SPECIAL DETAILED

20,00

57-460-00 Inboard Aft Flap INTERNAL – DETAILED: Inboard Aft Flap

Detailed 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 – DETAILED 20,00

57-465-00 Inboard Aft Flap INTERNAL – GENERAL VISUAL: Inboard Aft Flap

General Visual Inspection of the track D carriage attachment to aft flapINTERVAL NOTE: Whichever come first.

INTERNAL – 

GENERAL VISUAL

20,00

57-465-01 Inboard Aft Flap INTERNAL – SPECIAL DETAILED: Inboard Aft Flap

Special Detailed Inspection of the inboard aft flap to include:Support ribsSparsSkin panelsNOTE: Borescope/Videoscope required to do this internal inspection of the aft flap.INTERVAL NOTE: Whichever comes first.

INTERNAL – 

SPECIAL DETAILED

20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-470-00 Inboard Aileron INTERNAL – SPECIAL DETAILED: Inboard Aileron

Special Detailed Inspection of the internal structure of the inboard aileron to include:Actuator ribSparsRibsSkin panelsNOTE: Borescope/Videoscope required to do this internal inspection of the inboard aileron.INTERVAL NOTE: Whichever comes first.

INTERNAL – 

SPECIAL DETAILED

FLS, 

Figu

57-470-01 Inboard Aileron EXTERNAL – GENERAL VISUAL: Inboard Aileron

General Visual Inspection of the exterior surfaces of the aileron skin panelsINTERVAL NOTE: Whichever comes first.

EXTERNAL – 

GENERAL VISUAL

FLS, 

Figu

57-470-02 Inboard and 

Outboard Flap Track Supports

EXTERNAL – GENERAL VISUAL: Inboard and Outboard Flap Track SupportsGeneral Visual Inspection of the inboard and outboard flap track supports 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 VISUAL

20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-475-00 Rear Spar to 

Trailing Edge from WBL 515 to WBL 849

INTERNAL – DETAILED: Rear Spar to Trailing Edge from WBL 515 to 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 – DETAILED FLS, 

Figu

57-480-00 Outboard Flap INTERNAL – GENERAL VISUAL: Outboard Flap

General Visual Inspection of the internal structure of the outboard flap 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 VISUAL

20,00

57-480-01 Outboard Flap INTERNAL – SPECIAL DETAILED: Outboard Flap

Special Detailed Inspection of the outboard flap to include:Main support ribsSparsSkin panelsNOTE: Borescope/Videoscope required to do this internal inspection of the outboard flap box.INTERVAL NOTE: Whichever comes first.

INTERNAL – 

SPECIAL DETAILED

20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-485-00 Rear Spar to 

Trailing Edge and Outboard Aileron

INTERNAL – GENERAL VISUAL: Rear Spar to Trailing Edge and Outboard AileronGeneral Visual Inspection of the trailing edge and outboard aileron to include:Trailing edge hinge ribs & bearing linksAileron hinge fittings.INTERVAL NOTE: Whichever comes first.

INTERNAL – 

GENERAL VISUAL

FLS, 

Figu

57-490-00 Rear Spar to 

Trailing Edge and Outboard Aileron

INTERNAL – GENERAL VISUAL: Rear Spar to Trailing Edge and Outboard AileronGeneral Visual Inspection of the trailing edge and outboard aileron to include:Trailing edge PCU support fittingsAileron actuator fittingAileron balance towersAileron front spar – forward surface.INTERVAL NOTE: Whichever comes first.

INTERNAL – 

GENERAL VISUAL

FLS, 

Figu

57-495-00 Outboard Aileron INTERNAL – SPECIAL DETAILED: Outboard Aileron

Special Detailed Inspection of the internal structure of outboard aileron to include:SparRibsSkin panels.NOTE: Borescope/Videoscope required to do this internal inspection of the outboard aileron box.INTERVAL NOTE: Whichever comes first.

INTERNAL – 

SPECIAL DETAILED

FLS, 

Figu

57-500-00 Outboard Aileron EXTERNAL – GENERAL VISUAL: Outboard Aileron

General Visual Inspection of the exterior surfaces of the aileron skin panelsINTERVAL NOTE: Whichever comes first.

EXTERNAL – 

GENERAL VISUAL

FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-802-01 CENTER SECTION 

WING BOX – INTERIOR

INTERNAL – ZONAL (GVI): CENTER SECTION WING BOX – 

INTERIORGeneral Visual Inspection of the interior of center section wing box. (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-808-01 WING LE TO FRONT 

SPAR – LEFT WING

EXTERNAL – 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, 

Figu

57-810-01 WING LE TO FRONT 

SPAR CAVITY – LEFT WING

EXTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR CAVITY – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front spar cavity. (ILES 302 to ILES 630.72).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

57-812-01 WING LE TO 

FRONT SPAR COMPARTMENT – LEFT WING

INTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR COMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front spar compartment. (ILES 630.72 to WBL 470). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-814-01 WING LE TO 

FRONT SPAR COMPARTMENT – LEFT WING

INTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR COMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front spar compartment. (WBL 128.5 to ILES 302 and ILES 630.72 to WBL 470).INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-816-01 LEFT WING 

KRUEGER 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) 20,00

57-818-01 WING LE TO FRONT 

SPAR – LEFT WING

EXTERNAL – 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, 

Figu

57-820-01 WING LE TO FRONT 

SPAR CAVITY – LEFT WING

EXTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR CAVITY – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front spar cavity (ILES 693.5 to ILES 1116).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flap extended.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

57-822-01 WING LE TO FRONT 

SPAR COMPARTMENT – LEFT WING

INTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR COMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front spar compartment (WBL 470 to ILES 693.5). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-824-01 WING LE TO FRONT 

SPAR CAVITY – LEFT WING

INTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR CAVITY – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front spar compartment (ILES 1116.0 to WBL 834). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-826-01 LEFT WING 

VARIABLE CAMBER FLAP (6 THRU 10)

EXTERNAL – ZONAL (GVI): LEFT WING VARIABLE CAMBER FLAP (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) 20,00

57-828-01 WING LEADING 

EDGE TO FRONT SPAR – LEFT WING

EXTERNAL – ZONAL (GVI): WING LEADING EDGE TO FRONT SPAR – 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, 

Figu

57-830-01 WING LE TO FRONT 

SPAR CAVITY – LEFT WING

EXTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR CAVITY – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front spar cavity (OLES 1185 to OLES 1617.6). (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE Flaps extended.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

57-832-01 WING LE TO 

FRONT SPAR COMPARTMENT – LEFT WING

INTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR COMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing leading edge to front spar compartment (WBL 834 to OLES 1185 and OLES 1617.6 to tip).INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-834-01 LEFT WING 

VARIABLE CAMBER FLAP(1E THRU 5)

EXTERNAL – ZONAL (GVI): LEFT WING VARIABLE CAMBER FLAP (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) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-836-01 RAKED WING TIP – 

LEFT WING

INTERNAL – 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, 

Figu

57-838-01 INBOARD MAIN 

FUEL TANK – LEFT WING

INTERNAL – 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 access panels as required to perform inspection.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-840-01 OUTBOARD MAIN 

FUEL TANK – LEFT

INTERNAL – 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 access panels as required to perform inspection.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-844-01 WING RESERVE 

FUEL TANK – LEFT WING

INTERNAL – 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 access panels as required to perform inspection.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-850-01 WING 

SURGE TANK – LEFT WING

INTERNAL – ZONAL (GVI): WING SURGE TANK – LEFT WINGGeneral Visual Inspection of the left wing surge tank.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-852-01 WING DRY BAY – 

LEFT WING

INTERNAL – 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, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-853-01 FLAP TRACK 

FAIRING – LEFT WING

INTERNAL – ZONAL (GVI): FLAP TRACK FAIRING – LEFT WINGGeneral Visual Inspection of the left wing flap track fairing including flap track and carriage.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended.

INTERNAL – ZONAL (GVI) 20,00

57-854-01 WING 

REAR SPAR TO TRAILING EDGE – LEFT WING

EXTERNAL – ZONAL (GVI): WING REAR SPAR TO TRAILING EDGE – 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, 

Figu

57-856-01 WING REAR SPAR 

TO LG SUPPORT BEAM – LEFT WING

EXTERNAL – ZONAL (GVI): WING REAR SPAR TO LG SUPPORT BEAM – LEFT WINGGeneral Visual Inspection of the left wing rear spar to landing gear support beam cavity (WBL 128.5 to inboard track of inboard trailing edge flap).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended and WLG doors open.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

57-858-01 WING REAR SPAR 

TO LG BEAM COMPARTMENT – LEFT WING

INTERNAL – ZONAL (GVI): WING REAR SPAR TO LG BEAM COMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing rear spar to landing gear support beam compartment (Inboard track of inboard trailing edge flap to WS 586.62). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-860-01 WING LG SUPPORT 

BEAM AND TE CAVITY – LEFT WING

EXTERNAL – ZONAL (GVI): WING LG SUPPORT BEAM AND TE CAVITY – LEFT WINGGeneral Visual Inspection of the left wing landing gear support beam and 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, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-862-01 WING LG BEAM, 

REAR SPAR TO TE COMPARTMENT – LEFT WING

INTERNAL – ZONAL (GVI): WING LG BEAM, REAR SPAR TO TE COMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing landing gear support beam and rear spar to trailing edge compartment (WBL 128.5 to WBL 445). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-864-01 WING REAR SPAR 

TO INBOARD AILERON LE – LEFT WING

INTERNAL – ZONAL (GVI): WING REAR SPAR TO INBOARD AILERON LE – LEFT WINGGeneral Visual Inspection of the left wing rear spar to inboard aileron leading edge (WBL 445 to WBL 515). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-866-01 LEFT WING 

INBOARD TE FLAPS

EXTERNAL – 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) 20,00

57-870-01 WING REAR SPAR 

TO TRAILING EDGE – LEFT WING

EXTERNAL – ZONAL (GVI): WING REAR SPAR TO TRAILING EDGE – 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, 

Figu

57-872-01 WING REAR SPAR 

TO TE CAVITY – LEFT WING

EXTERNAL – ZONAL (GVI): WING REAR SPAR TO TE CAVITY – LEFT WINGGeneral Visual Inspection of the left wing rear spar to trailing edge cavity (WBL 515 to WBL 849).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended and spoilers raised.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

57-876-01 LEFT WING 

OUTBOARD TE FLAP

EXTERNAL – 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) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-878-01 WING

REAR SPAR TO TRAILING EDGE – LEFT WING

EXTERNAL – ZONAL (GVI): WING REAR SPAR TO TRAILING EDGE – 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, 

Figu

57-880-01 WING 

REAR SPAR TO TE COMPARTMENT – LEFT WING

INTERNAL – ZONAL (GVI): WING REAR SPAR TO TE COMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing rear spar to trailing edge compartment (WBL 849 to WBL 1244).INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-882-01 WING 

REAR SPAR TO TE COMPARTMENT – LEFT WING

INTERNAL – ZONAL (GVI): WING REAR SPAR TO TE COMPARTMENT – LEFT WINGGeneral Visual Inspection of the left wing rear spar to trailing edge compartment (WBL 849 to WBL 1244). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-888-01 WING LE TO FRONT 

SPAR – RIGHT WING

EXTERNAL – 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, 

Figu

57-890-01 WING LE TO FRONT 

SPAR CAVITY – RIGHT WING

EXTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR CAVITY – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front spar cavity (ILES 302 to ILES 630.72) and including ram air turbine compartment.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-892-01 WING LE TO 

FRONT SPAR COMPARTMENT – RIGHT WING

INTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR COMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front spar compartment (ILES 630.72 to WBL 470). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-894-01 WING LE TO 

FRONT SPAR COMPARTMENT – RIGHT WING

INTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR COMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front spar compartment (WBL 128.5 to ILES 302 and ILES 630.72 to WBL 470).INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-896-01 RIGHT WING 

KRUEGER 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) 20,00

57-898-01 WING LE TO FRONT 

SPAR – RIGHT WING

EXTERNAL – 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, 

Figu

57-900-01 WING LE TO FRONT 

SPAR CAVITY – RIGHT WING

EXTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR CAVITY – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front spar cavity (ILES 693.5 to ILES 1116).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE Flaps extended.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-902-01 WING LE TO 

FRONT SPAR COMPARTMENT – RIGHT WING

INTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR COMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front spar compartment (WBL 470 to ILES 693.5). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-904-01 WING LE TO FRONT 

SPAR CAVITY – RIGHT WING

INTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR CAVITY – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front spar cavity (ILES 1116.0 to WBL 834). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-906-01 RIGHT WING 

VARIABLE CAMBER FLAP (17 THRU 21)

EXTERNAL – ZONAL (GVI): RIGHT WING VARIABLE CAMBER FLAP (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) 20,00

57-908-01 WING 

LEADING EDGE TO FRONT SPAR – RIGHT WING

EXTERNAL – ZONAL (GVI): WING LEADING EDGE TO FRONT SPAR – 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, 

Figu

57-910-01 WING LE TO FRONT 

SPAR CAVITY – RIGHT WING

EXTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR CAVITY – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front spar cavity (OLES 1185 to OLES 1617.6). (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: LE flaps extended.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-912-01 WING LE TO 

FRONT SPAR COMPARTMENT – RIGHT WING

INTERNAL – ZONAL (GVI): WING LE TO FRONT SPAR COMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing leading edge to front spar compartment (WBL 834 to OLES 1185 and OLES 1617.6 to tip).INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-914-01 RIGHT WING 

VARIABLE CAMBER FLAP (22 THRU 26E)

EXTERNAL – ZONAL (GVI): RIGHT WING VARIABLE CAMBER FLAP (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) 20,00

57-916-01 RAKED WING TIP – 

RIGHT WING

INTERNAL – 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, 

Figu

57-918-01 INBOARD MAIN 

FUEL TANK(NO. 3) – RIGHT WING

INTERNAL – 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 access panels as required to perform inspection.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-920-01 OUTBOARD MAIN 

FUEL TANK (NO. 4) – RIGHT WING

INTERNAL – 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 access panels as required to perform inspection.

INTERNAL – ZONAL (GVI) FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-924-01 WING RESERVE 

FUEL TANK – RIGHT WING

INTERNAL – 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 access panels as required to perform inspection.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-930-01 WING 

SURGE TANK – RIGHT WING

INTERNAL – ZONAL (GVI): WING SURGE TANK – RIGHT WINGGeneral Visual Inspection of the right wing surge tank.INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-932-01 WING DRY BAY – 

RIGHT WING

INTERNAL – 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, 

Figu

57-933-01 FLAP TRACK 

FAIRING – RIGHT WING

INTERNAL – ZONAL (GVI): FLAP TRACK FAIRING – RIGHT WINGGeneral Visual Inspection of the right wing flap track fairings including flap tracks.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: With TE flaps extended.

INTERNAL – ZONAL (GVI) 20,00

57-934-01 WING 

REAR SPAR TO TRAILING EDGE – RIGHT WING

EXTERNAL – ZONAL (GVI): WING REAR SPAR TO TRAILING EDGE – 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, 

Figu

57-936-01 WING REAR SPAR 

TO LG SUPPORT BEAM – RIGHT WING

EXTERNAL – ZONAL (GVI): WING REAR SPAR TO LG SUPPORT BEAM – RIGHT WINGGeneral Visual Inspection of the right wing rear spar to landing gear support beam cavity (WBL 128.5 to inboard track of inboard trailing edge flap).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended and WLG doors open.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-938-01 WING REAR SPAR 

TO LG BEAM COMPARTMENT – RIGHT WING

INTERNAL – ZONAL (GVI): WING REAR SPAR TO LG BEAM COMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing rear spar to landing gear support beam compartment (Inboard track of inboard trailing edge flap to WS 586.62). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-940-01 WING LG SUPPORT 

BEAM AND TE CAVITY – RIGHT WING

EXTERNAL – ZONAL (GVI): WING LG SUPPORT BEAM AND TE CAVITY – RIGHT WINGGeneral Visual Inspection of the right wing landing gear support beam 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, 

Figu

57-942-01 WING LG 

BEAM&REAR SPAR TO TE COMPARTMENT – RIGHT WING

INTERNAL – ZONAL (GVI): WING LG BEAM&REAR SPAR TO TE COMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing landing gear support beam and rear spar to trailing edge compartment (WBL 128.5 to WBL 445). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-944-01 WING REAR SPAR 

TO INBOARD AILERON LE – RIGHT WING

INTERNAL – ZONAL (GVI): WING REAR SPAR TO INBOARD AILERON LE – RIGHT WINGGeneral Visual Inspection of the right wing to inboard aileron leading edge (WBL 445 to WBL 515). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

57-946-01 RIGHT WING 

INBOARD TE FLAPS

EXTERNAL – 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) 20,00

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-948-01 WING 

REAR SPAR TO TRAILING EDGE – RIGHT WING

EXTERNAL – ZONAL (GVI): WING REAR SPAR TO TRAILING EDGE – 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, 

Figu

57-950-01 WING REAR SPAR 

TO TE CAVITY – RIGHT WING

EXTERNAL – ZONAL (GVI): WING REAR SPAR TO TE CAVITY – RIGHT WINGGeneral Visual Inspection of the right wing rear spar to trailing edge cavity (WBL 515 to WBL 849).INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flaps extended and spoilers raised.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

57-954-01 RIGHT WING 

OUTBOARD TE FLAP

EXTERNAL – ZONAL (GVI): RIGHT WING OUTBOARD TE FLAPGeneral Visual Inspection of the right wing outboard trailing edge flap.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: TE flap extended.

EXTERNAL – ZONAL (GVI) 20,00

57-956-01 WING 

REAR SPAR TO TRAILING EDGE – RIGHT WING

EXTERNAL – ZONAL (GVI): WING REAR SPAR TO TRAILING EDGE – 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, 

Figu

57-958-01 WING REAR SPAR 

TO TE COMPARTMENT – RIGHT WING

INTERNAL – ZONAL (GVI): WING REAR SPAR TO TE 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, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-960-01 WING 

REAR SPAR TO TE COMPARTMENT – RIGHT WING

INTERNAL – ZONAL (GVI): WING REAR SPAR TO TE COMPARTMENT – RIGHT WINGGeneral Visual Inspection of the right wing rear spar to trailing edge compartment (WBL 849 to WBL 1244). (EZAP)INTERVAL NOTE: Whichever comes first.

INTERNAL – ZONAL (GVI) FLS, 

Figu

71-804-01 NOSE COWL, 

ENGINE NO. 1, 2, 3, 4

EXTERNAL – 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, 

Figu

71-806-00 ENGINE 

INSTALLATION NO. 1, 2, 3, 4

EXTERNAL – ZONAL (GVI): ENGINE INSTALLATION NO. 1, 2, 3, 4General Visual Inspection of the engine no. 1, 2, 3, 4. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open fan cowls and T/R cowls.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

71-808-01 INNER FACE OF 

FAN COWL ENGINE NO. 1, 2, 3, 4

EXTERNAL – ZONAL (GVI): INNER FACE OF FAN COWL ENGINE NO. 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, 

Figu

71-810-01 INNER FACE OF 

T/R COWL ENGINE NO. 1, 2, 3, 4

EXTERNAL – ZONAL (GVI): INNER FACE OF T/R COWL ENGINE NO. 1, 2, 3, 4General Visual Inspection of the inner face of thrust reverser cowl no. 1, 2, 3, 4. (EZAP)INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open T/R cowls.

EXTERNAL – ZONAL (GVI) FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

TABLE 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.

71-812-01 THRUST 

REVERSER AND COWL ENGINE NO. 1, 2, 3, 4

EXTERNAL – ZONAL (GVI): THRUST REVERSER AND COWL ENGINE 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, 

Figu

71-816-01 EXHAUST NOZZLE 

INNER AND FWD FACES INCLUDING THE CENTER VENT TUBE

EXTERNAL – ZONAL (GVI): EXHAUST NOZZLE INNER AND FWD FACES INCLUDING THE CENTER VENT TUBEGeneral Visual Inspection of the inner and forward faces of exhaust nozzle including the center vent tube engine no. 1, 2, 3, 4.INTERVAL NOTE: Whichever comes first.ACCESS NOTE: Open TR cowls

EXTERNAL – ZONAL (GVI) FLS, 

Figu

POST-THRESHOLD INTERVAL TABLE

MPD ITEM 

NUMBER TASK TITLE TASK DESCRIPTION INSPECT LEVEL

DE

T

747

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

REMOVAL OF EXCESS SEALANT WHEN INSPECTING1. In areas where a Supplemental Structural Inspection DTR Check Form visual inspection is prevented due to sealant, remov

brush sealant that extends beyond 0.20" around the fastener at locations that are to be inspected. Remove any additional se

of the structure adjacent to 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 p

747 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 p

3. The following Structural Significant Items (SSIs) require fastener cap, fillet or brush sealant that extends beyond 0.20" to be 

maintenance visual inspections (see 747-8/-8F MPD Sections 2 and 3) at or prior to reaching the listed thresholds, as note

table below.

4. Figures 1 and 2 are the same as for the FLS Threshold Curve.

EXCESS SEALANT TABLE

SSI TITLE MPD ITEM NO. THRESHOLD

INSTALLATION DRAWING DESCRIPTION OF ARE

NUMBER TITLE TO BE 

Fuselage – Bulkhead BS 1000

53-420-0153-864-0153-866-01

20,000 FC 110U0210 Wing to Body Attachment Installation Remove excess sealant e

fastener head or nut whiclower chord inspection.

Fuselage – Bulkhead BS 1480

53-430-0153-852-01

20,000 FC 65B15085 Bulkhead Installation – Aft Wheel Well 

Lower STA 1480

Remove excess sealant efastener head or nut whiclower cap fitting inspectio

Fuselage – Under Wing Longeron

 53-460-00 20,000 FC 65B11581 Drag Fitting Installation – Lower Panel, 

Wing Center Section

Remove excess sealant efastener head or nut whiclower chord inspection.

Fuselage – Over Wing Longeron Extensions Forward of BS 1000 and Aft of BS 1480

 53-460-00 20,000 FC 65B15255 Longeron Extension Fitting Installation Remove excess sealant e

fastener head or nut whiclongeron extension inspec

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

Horizontal Stab. Upper Skin – Stringer

55-830-0155-832-01

FLS, 

See Figure 1

182U3000 PANEL MINOR ASSY – OTBD UPR, 

TORQUE BOX, HORIZ STAB.

Along Stringer 1 to 4 betwAlong Stringer 6 & 7 (vent 

55-828-01 FLS, 

See Figure 1

181U3000 Upper Skin Instl – Center Sect, 

Horiz Stab

 Z-stringers 1-4 in center s

Horizontal Stab. Front Spar

55-828-01 FLS, 

See Figure 1

181U2010 FRONT SPAR INSTL – 

CENTER SECT.

Center section front spar BL 0.0 to SOB

Horizontal Stab. Rear Spar

55-828-0153-920-01

FLS, 

See Figure 1

182U1000 SPAR INSTL, REAR – 

HORIZONTAL STAB.

Center Section Rear Spar web to chord joints - sealainternal and external- from 

Horizontal Stab. Side of Body Splice

55-816-0155-824-01

FLS, 

See Figure 1

182U5200 Hinge Rib Assy – OUTBD 

HORIZ STAB

Outboard SOB upper Joinand splice fitting - web fla

55-828-01 FLS, 

See Figure 1

Center section upper Fron

55-830-01

 55-832-01

FLS, 

See Figure 1

Outboard upper Front Spa

FLS, 

See Figure 1

All outboard upper stringeRib 3. 

55-830-01

 55-832-01

55-828-01

FLS, 

See Figure 1

Outboard and inboard spl

Wing Center Section Lower Panel

57-802-01 FLS, 

See Figure 1

111U4000 LOWER PANEL INSTL – 

WING CENTER SECTION

Skin-to-stringer fasteners 11-13, 16-18, 20-23. Skinalong front spar chord 

Wing Center Section Upper Panel

57-802-01 FLS, 

See Figure 1

111U3000 UPPER PANEL INSTALLATION – 

WING CENTER SECTION

Skin-to-stringer fasteners 15-19, 21-27, 29-33, exceconnection

EXCESS SEALANT TABLE

SSI TITLE MPD ITEM NO. THRESHOLD

INSTALLATION DRAWING DESCRIPTION OF ARE

NUMBER TITLE TO BE 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

Outboard Wing Lower Panel

57-425-0057-840-0157-920-0157-844-0157-924-0157-838-0157-918-0157-850-0157-930-0157-852-0157-932-01

FLS, 

See Figure 1

112U4300 PANEL INSTALLATION, INSPAR 

WING, LOWER LH

All Skin-to-stringer fasteneunder the outboard strut fAll Skin-to-stringer fasteneadjacent to spar chord in Skin-to-stringer fasteners 

of Rib 45Skin-to-chord fasteners & longitudinal splices

Outboard Wing Upper Panel

57-838-0157-918-0157-840-0157-920-0157-844-0157-924-0157-850-0157-930-0157-852-0157-932-01

FLS, 

See Figure 1

112U3300 PANEL INSTALLATION, INSPAR 

WING, UPPER

Skin-to-stringer fasteners 15-26, 28-33, excludes fu

Outboard Wing Rear Spar

57-838-0157-918-0157-856-0157-936-01

FLS, 

See Figure 1

112U1101 REAR SPAR ASSEMBLY Fillet seal at edge of fuel d

EXCESS SEALANT TABLE

SSI TITLE MPD ITEM NO. THRESHOLD

INSTALLATION DRAWING DESCRIPTION OF ARE

NUMBER TITLE TO BE 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

5. 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 r

If sealant is removed inside the fuel tank for inspection, care must be taken to remove any sealant debris in the fuel tank. Lis removed for inspections must have the sealant restored to drawing or AMM requirements (and any applicable Service Buinstructions) after completion of the inspections. Sealant of fuel tank fasteners must comply with maintenance requirements 

Special Compliance Items/Airworthiness Limitations document D011U721-02-04, as applicable.

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

SUPPLEMENTAL STRUCTURAL INSPECTION REQUIREMENTSThe table below lists the Airworthiness Limitation Supplemental Structural Inspection requirements. Each item is listed by SSI N

Title, DTR Location, and Airplane Applicability/Threshold. There are corresponding DTR Check Forms in D011U721-05 for eac

where a DTR Check Form title is specified. Where there is more than one listing for a given SSI Number, the DTR Check Form 

unique 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 Airplanes

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

27-41-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 Lug N/A 20,000 (3)

52-31-F38B Nose Cargo Door, C-2 & BS 234 

Closure Frames

Outer Chords N/A 20,000 (3)

52-31-F38C Nose Cargo Door Latches Latch Fitting to Intercostal Attachment N/A 20,000 (3)52-31-F38D Nose Cargo Door, C-2 & BS 234 

Closure Frames

Inner Chords N/A 20,000 (3)

52-31-F38E Nose Cargo Door Tension Tie Connection to Body Station 234 Frame N/A 20,000 (3)

52-32-F37A.3 Main Deck Side Cargo Door Outer Skin and fasteners around 

Pressure Vent Panel and Window Cutouts

N/A 20,000

MAY 2014
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BOEING PROPRIETARY - Copyright (c) - Unpublished Work - See title page for details 

747-8/8F AIRWORTHINESS LIMITATIONS

52-32-F37B.2 Main Deck Side Cargo Door Outer Skin and Frame Outer Chord 

at Hinge

N/A 20,000 (3)

52-32-F37C.1 Main Deck Side Cargo Door Latch Support Fitting Lugs All 

10 locations

N/A 20,000 (3)

52-32-F37C.3 Main Deck Side Cargo Door Latch Frame Inner Chord at Latch 

Support Fitting Splice Intercostal

N/A 20,000 (3)

52-32-F37C.4 Main Deck Side Cargo Door Cam Latches N/A 20,000 (3)

52-34-F31A.4 Forward and Aft Lower Lobe 

Cargo Doors

Outer skin Lap Splice, Lower Fastener Row

20,000 (3) 20,000 (3)

52-34-F31B.2 Forward and Aft Lower Lobe 

Cargo Doors

Outer Skin and Frame Outer Chords at attachments to Main Hinge Segments

20,000 (3) 20,000 (3)

52-34-F31B.3 Forward and Aft Lower Lobe 

Cargo Doors

Outer Skin at Upper Beam attachment, Lowest Row of Fasteners

20,000 (3) 20,000 (3)

52-34-F31B.4 NONE Fwd and Aft Lower Lobe Cargo Door 

Hinge Segments

20,000 20,000 F

pafodto infasefofainRF

52-34-F31C.1 Forward and Aft Lower Lobe 

Cargo Doors

Latch Support Fitting Lugs 20,000 (3) 20,000 (3)

52-34-F31C.3 Forward and Aft Lower Lobe 

Cargo Doors

Latch Frame Inner Chord at Splice with Latch support Fitting

20,000 (3) 20,000 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

52-34-F31C.4 Forward and Aft Lower Lobe 

Cargo Doors

Cam Latches 20,000 (3) 20,000 (3)

52-36-F32A Bulk Cargo Door Stop Fittings and Latch Probes 20,000 20,000

53-00-F01A Bulkhead BS 140 Web 20,000 20,000

53-00-F01B Bulkhead BS 140 Vertical Beam 20,000 20,000

53-00-F02A Bulkhead BS 260 Outer Chord from S-39 to S-45 L & R N/A 20,000 (3)

53-00-F02B Bulkhead BS 260 Outer Chord from S-39 to S-45 L & R 20,000 (3) N/A

53-00-F02D Bulkhead BS 260 Periphery of NGWW Forward Corner 

Reinforcing Doubler – LHS and RHS

20,000 (3) 20,000 (3)

53-00-F02G Bulkhead BS 260 BS 260, Below S-22 20,000 20,000

53-00-F03 Bulkhead BS 340 BS 340, Below S-22 20,000 20,000

53-00-F04A Bulkhead BS 400 Nose Gear Wheel Well Cutout Aft 

Corners BS 380 to BS 400, S-44 to S-46.5

20,000 (3) 20,000 (3)

53-00-F04B Bulkhead BS 400 Nose Gear Wheel Well Cutout, BS 400 

Bulkhead Outer Chord from S-41L to S-41R

20,000 (3) 20,000 (3)

53-00-F04C Bulkhead BS 400 BS 400, WL 173, BL 10 to BL 16 20,000 20,00053-00-F04D Bulkhead BS 400 BS 400, LBL and RBL 40, from 

WL 124 to WL 130

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

53-00-F04E Bulkhead BS 400 BS 400, below S-22 20,000 20,000

53-00-F05A Nose Gear Wheel Well – Top and 

Side Panels

Floor Beam Connections, BS 360 and BS 380, and Sidewall Panels from BS 340 to BS 400

20,000 20,000

53-00-F05B Nose Gear Wheel Well – Top and 

Side Panels

Connection Between Top and Side Panels, BS 260 Bulkhead to BS 340 Bulkhead

20,000 20,000

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-00-F05C Nose Gear Wheel Well – Top and 

Side Panels

Torque Box, BS 340 to BS 400 20,000 20,000

53-00-F06A BS 1000 Bulkhead Lower Chord at S-45L & S-45R Splice 20,000 (3) 20,000 (3)

53-00-F06B BS 1000 Bulkhead Lower Chord below main deck floor 20,000 20,000

53-00-F06C BS 1000 Bulkhead Lower lobe skin below main deck floor 20,000 20,000

53-00-F08 Stub Beams (Overwing and Over 

Wheel Well)

Stub Beam to Frame Attachment, BS 1020 through BS 1460, LHS and RHS

20,000 20,000

53-00-F09A BS 1241 Bulkhead Pickle Fork Fitting Inner Chord at 

Cargo Intercostal Attachment at S-26

N/A 20,000 (3)

53-00-F09B BS 1241 Bulkhead Strap from S-23 to Longeron Splice at 

Wing Upper Surface

20,000 (3) 20,000 (3)

53-00-F09C BS 1241 Bulkhead Outer Chord from S-23 to Longeron 

Splice At Wing Upper Surface

20,000 (3) 20,000 (3)

53-00-F09D BS 1241 Bulkhead Pickle Fork Outer Chord/Strap under 

Wing Upper Chord Kick Fitting, WL 164.9

20,000 (3) 20,000 (3)

53-00-F09E Bulkhead BS 1241 Over Wheel Well Longeron at WL 173 20,000 (3) 20,000 (3)

53-00-F09F Bulkhead BS 1241 Over Wheel Well Longeron at WL 173 20,000 (3) 20,000 (3)

53-00-F10B.1 Bulkhead BS 1350 Lower Side Frame Joint at WL 158 20,000 20,00053-00-F10B.2 Bulkhead BS 1350 Lower Side Frame from S-21 TO S-28 20,000 20,000

53-00-F11A BS 1480 Bulkhead Lower Cap Fitting from S-34 to S-39 20,000 (3) 20,000 (3)

53-00-F11B BS 1480 Bulkhead Upper Chord between BL 98.6 and 

BL 57.5

20,000 20,000

53-00-F11C BS 1480 Bulkhead Upper Chord Vertical Flange 

at BL 75.9

N/A 20,000 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-00-F11D.1 Bulkhead BS 1480 Bulkhead Outer Chord, from S-32 

to S-34

20,000 (3) 20,000 (3)

53-00-F11D.2 Bulkhead BS 1480 Bulkhead Outer Chord Splices, 

from S-32 to S-34

20,000 20,000

53-00-F16C Over Wheel Well Longeron Over Wheel Well Longeron Splice 

Between BS 1200 and BS 1285

20,000 20,000

53-00-F17C Crew Cab Window Posts, Sills 

and Skins

#1 Post Typical (Upper Sill to Lower Sill)

20,000 (3) 20,000 (3)

53-00-F17D Crew Cab Window Posts, Sills 

and Skins

#1 Post at Upper Sill Intersection 20,000 (3) 20,000 (3)

53-00-F17E Crew Cab Window Posts, Sills 

and Skins

#2 Post at Upper and Lower Sill Intersections

20,000 (3) 20,000 (3)

53-00-F17F Crew Cab Window Posts, Sills 

and Skins

#3 Post at Upper and Lower Sill Intersections

20,000 (3) 20,000 (3)

53-00-F18A Nose Gear Wheel Well Cutout BS 340 Corner at Side Panel 

and Bulkhead

20,000 (3) 20,000 (3)

53-00-F19A Upper Deck Floor Beams, Stanchions 

and Tension Ties

BS 1120 to BS 1220 Tension Ties 20,000 (3) N/A

53-00-F19B.1 Upper Deck Floor Beams, Stanchions 

and Tension Ties

BS 1120 to BS 1220 Tension Tie at Frame Joint LHS & RHS

20,000 (3) N/A

53-00-F19B.2 Upper Deck Floor Beams, Stanchions 

and Tension Ties

BS 1120 to BS 1220 Frame at Tension Tie LHS & RHS

20,000 N/A

53-00-F19C Upper Deck Floor Beams, Stanchions 

and Tension Ties

BS 720 to BS 940 Tension Ties N/A 20,000 (3)

53-00-F19D Upper Deck Floor Beams, Stanchions 

and Tension Ties

BS 720 to BS 940 Tension Ties N/A 20,000 (3)

53-00-F19E Upper Deck Floor Beams, Stanchions 

and Tension Ties

BS 720 to BS 940 Tension Ties N/A 20,000

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-00-F19F Upper Deck Floor Beams, Stanchions 

and Tension Ties

Upper Chord Mid-Span Along Floor Beam

20,000 (3) 20,000 (3)

53-00-F19G Upper Deck Floor Beams, Stanchions 

and Tension Ties

Upper Deck Floor Beams 20,000 20,000

53-00-F19H Upper Deck Floor Beams, Stanchions 

and Tension Ties

Floor Beam Upper Chord Outboard Span

20,000 (3) 20,000 (3)

53-00-F19I Upper Deck Floor Beams, Stanchions 

and Tension Ties

Connection to Frame, BS 460 to BS 840 and BS 880 to BS 920

20,000 (3) N/A

53-00-F19J Upper Deck Floor Beams, Stanchions 

and Tension Ties

Connection to Frame, BS 540 to BS 700

N/A 20,000 (3)

53-00-F19K Upper Deck Floor Beams, Stanchions 

and Tension Ties

Floor Beam Upper Chord at Frame Connection, BS 540 to BS 700

N/A 20,000

53-00-F20A.1 Upper Deck Floor Cutout Shear Webs 

and Intercostals

Upper and Lower Chord Mid-Spans of Upper Deck Floor Beams

20,000 (3) N/A

53-00-F20A.2 Upper Deck Floor Cutout Shear Webs 

and Intercostals

Upper and Lower Chord Mid-Spans of Upper Deck Floor Beams

N/A 20,000 (3)

53-00-F20B Upper Deck Floor Cutout Shear Webs 

and Intercostals

Upper Deck Floor Beam Upper Chord at Frame Connection

20,000 (3) N/A

53-00-F20C.1 Upper Deck Floor Cutout Shear Webs 

and Intercostals

Upper Deck Floor Beam Upper Chord at Strap/Frame Connection BS 480 and BS 520

N/A 20,000 (3)

53-00-F20C.2 Upper Deck Floor Cutout Shear Webs 

and Intercostals

Upper Deck Floor Beam Upper Chord at Strap/Frame Connection BS 480 and BS 520

N/A 20,000 (3)

53-00-F20D.1 Upper Deck Floor Cutout Shear Webs 

and Intercostals

Header Beam Upper Chord Mid-Span BS 480 and BS 520

N/A 20,000 (3)

53-00-F20D.2 Upper Deck Floor Cutout Shear Webs 

and Intercostals

Header Beam Upper Chord at MidSpan BS480 and BS520 at Floor Panel Clipnuts

N/A 20,000 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-00-F20E Upper Deck Floor Cutout Shear Webs 

and Intercostals

BS 480 Upper Chord of Upper Deck Floor Beam at Floor Cutouts

N/A 20,000 (3)

53-00-F21D.1 Side Skin Panels Frames Above S-26 (Top of Main Deck 

Floor), from BS 160 to BS 520

30,000 30,000

53-00-F21D.2 Side Skin Panels Frames Above S-26 (Top of Main Deck 

Floor), from BS 520 to BS 980

25,000 N/A

53-00-F21D.3 Side Skin Panels Frames Above S-26 (Top of Main Deck 

Floor), from BS 520 to BS 980+160

N/A 22,000

53-00-F21D.4 Side Skin Panels Frames Above S-26 (Top of Main Deck 

Floor), from BS 1480+20 to BS 2360

25,000 25,000

53-00-F22 Crown Skin Crease Panel and 

Back-Up Structure

BS 940 to 980+20, S-8L to S-8R (747-8F) BS 1220 to 1283, S-8L to S-8R (747-8)

20,000 20,000

53-00-F23A.3 Crown Skin Panels Crown Skins Under Large Antenna 

Radomes

20,000 20,000

53-00-F23B.9 Crown Skin Panels 747-8: BS1101 to BS2360

747-8F: BS633 to BS2360

20,000 20,000

53-00-F23C.1 Crown Skin Panels Stringers in Sections 42, 44, and 46 22,000 (3) 22,000 (3)

53-00-F23C.2 Crown Skin Panels BS 340 to BS 520, S-4 through S-5A 25,000 (3) 25,000 (3)53-00-F23C.3 Crown Skin Panels BS 200 to BS 220, S-14 through S-14D N/A 25,000 (3)53-00-F23C.4 Crown Skin Panels BS 200 to BS 220, S-13A through 

S-14D

25,000 (3) N/A

53-00-F24D.1 Lower Lobe Skin Panels Frames Below S-26 (Top of Main Deck 

Floor), Section 41

30,000 30,000

53-00-F24D.2 Lower Lobe Skin Panels Frames Below S-26 (Top of M/D 

Floor), Sections 42 and 46

20,000 20,000

53-00-F24E Lower Lobe Skin Panels Section 42 20,000 (3) 20,000 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-00-F25A.1 Skin Longitudinal Splices Splice Outer Skin, Upper Row Splice 

Fasteners (Section 41)

20,000 (3) 20,000 (3)

53-00-F25A.2 Skin Longitudinal Splices Splice Outer Skin, Upper Row Splice 

Fasteners (Section 42)

20,000 (3) 20,000 (3)

53-00-F25A.3 Skin Longitudinal Splices Splice Outer Skin, Upper Row Splice 

Fasteners (Section 46)

N/A 20,000 (3)

53-00-F25A.4 Skin Longitudinal Splices Splice Outer Skin, Upper Row Splice 

Fasteners (Section 46)

20,000 (3) N/A

53-00-F25B.1 Skin Longitudinal Splices Splice Inner Skin, Lower Row Splice 

Fasteners (Section 41)

20,000 (3) 20,000 (3)

53-00-F25B.2 Skin Longitudinal Splices Splice Inner Skin, Lower Row Splice 

Fasteners (Section 42)

20,000 (3) 20,000 (3)

53-00-F25B.3 Skin Longitudinal Splices Splice Inner Skin, Lower Row Splice 

Fasteners (Section 46)

N/A 20,000 (3)

53-00-F25B.4 Skin Longitudinal Splices Splice Inner Skin, Lower Row Splice 

Fasteners (Section 46)

20,000 (3) N/A

53-00-F25C.1 Skin Longitudinal Splices S-4L from BS 1635 to BS 1880 N/A 20,000 (3)

53-00-F25C.2 Skin Longitudinal Splices S-4L from BS 1880 to BS 1960 N/A 20,000 (3)

53-00-F25D Skin Longitudinal Splices Radius of Chem-mill Step Adjacent to 

Skin Longitudinal Splice

N/A 22,000 (3)

53-00-F26A Skin-Stringer Circumferential Splices BS 1000 to BS 2181 20,000 (3) 20,000 (3)53-00-F26B Skin-Stringer Circumferential Splices BS 1220 to BS 2181 20,000 (3) 20,000 (3)

53-00-F26C Skin-Stringer Circumferential Splices BS 1000 to BS 1660 20,000 (3) 20,000 (3)53-00-F26D Skin-Stringer Circumferential Splices BS 1000 to BS 2181(747-8) and 

BS 980+20 to BS 2181 (747-8F)

20,000 20,000

53-00-F26E Skin-Stringer Circumferential Splices BS 1283, S-6L to S-6R (Internally) 20,000 (3) N/A

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-00-F26F Skin-Stringer Circumferential Splices BS 1283, S-6L to S-6R (Externally) 20,000 (3) N/A

53-00-F27A Typical Frames Section 41 Frames at Upper Deck 

Floor Beam Interface: BS 260 to BS 520

20,000 20,000

53-00-F27B NONE BS320 Crown Frame Affected by 

747-8-SRP-53-0441

14,000 (6) 14,000 (6) S

53-00-F30A BS 2360 Circumferential Splice Fwd Side of BS 2360 Splice, from S-7L 

to S-7R and S-13 to S-16 LHS and 

20,000 20,000

53-00-F39A Lower Lobe Cargo Door Cutouts Edge Frames – Inner Chord 20,000 (3) 20,000 (3)

53-00-F39B.2 Lower Lobe Cargo Door Cutouts Edge Frames – Outer Chord 20,000 (3) 20,000 (3)53-00-F39B.3 Lower Lobe Cargo Door Cutouts Edge Frames – Outer Chords 20,000 (3) 20,000 (3)53-00-F39B.4 Lower Lobe Cargo Door Cutouts Edge Frames – Outer Chords 20,000 (3) 20,000 (3)

53-00-F39C.1 Lower Lobe Cargo Door Cutouts Skin and Strap at Hinge Support & 

Hinge Back-up Structure

20,000 (3) 20,000 (3)

53-00-F39C.2 Lower Lobe Cargo Door Cutouts Hinge Support & Hinge Back-up 

Structure

20,000 20,000

53-00-F39D Lower Lobe Cargo Door Cutouts Latch Fittings at All Latch Locations in 

Fwd and Aft LLCD Cutouts

20,000 20,000

53-00-F39E Lower Lobe Cargo Door Cutouts Fwd and Aft Lower Lobe Cargo Door 

Cutout Corners

20,000 (3) 20,000 (3)

53-00-F39H Lower Lobe Cargo Door Cutouts Inner Chord of Main Sills 20,000 (3) 20,000 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-00-F39I NONE Fwd and Aft Lower Lobe Cargo Door 

Hinge Segments

20,000 20,000 F

pafodto AlbcoaaBfl7

53-00-F40A.1 Lower Lobe Bulk Cargo Door Cutout Edge Frame Inner Chord, BS 2034 20,000 (3) 20,000 (3)

53-00-F40A.2 Lower Lobe Bulk Cargo Door Cutout Edge Frame Inner Chord, BS 1980, 

Between S-39R and S-42R

20,000 (3) 20,000 (3)

53-00-F40A.3 Lower Lobe Bulk Cargo Door Cutout Edge Frame Inner Chord, BS 1980

Near S-37R

20,000 (3) N/A

53-00-F40B Lower Lobe Bulk Cargo Door Cutout Edge Frame Outer Chord at BS 1980 

and BS 2034

20,000 (3) 20,000 (3)

53-00-F40C Lower Lobe Bulk Cargo Door Cutout Cutout Corners 20,000 (3) 20,000 (3)

53-00-F40E Lower Lobe Bulk Cargo Door Cutout Upper Main Sill – Inner Chord 20,000 (3) 20,000 (3)

53-00-F41 Main Deck Entry Door Cutouts Main Entry Door #1 Cutout 20,000 20,000

53-00-F41A.1 Main Deck Entry Door Cutouts Edge Frame Inner Chords at BS 434, 

488, 854, 1664, 1720, and 2285

20,000 (3) 20,000 (3)

53-00-F41A.2 Main Deck Entry Door Cutouts Edge Frame Inner Chord at BS 800 

and BS 2231

20,000 (3) N/A

53-00-F41A.3 Main Deck Entry Door Cutouts Edge Frame Inner Chord at BS 800 20,000 (3) N/A

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-00-F41B.1 Main Deck Entry Door Cutouts Edge Frame Outer Chord, BS 434 

from S-16 to S-23

20,000 (3) 20,000 (3)

53-00-F41B.2 Main Deck Entry Door Cutouts Edge Frame Outer Chord, BS 434 

at S-19

20,000 (3) 20,000 (3)

53-00-F41B.3 Main Deck Entry Door Cutouts Edge Frame Outer Chords at BS 800, 

BS 1664, and BS 2231

20,000 (3) N/A

53-00-F41C.1 Main Deck Entry Door Cutouts Main Entry Door #1, #2, #4, and #5 

Cutout Corners

20,000 (3) 20,000 (3)

53-00-F41C.2 NONE Main Entry Door #1 Lower Forward 

Cutout Corner

12,000 (5) 12,000 (5) S

53-00-F41C.3 Main Deck Entry Door Cutouts Main Entry Door #3 Skin Cutout 

Corners

FLS, 

See Figure 2 (3)

N/A

53-00-F41D Main Deck Entry Door Cutouts Door Stop Backup Structure 20,000 (3) N/A

53-00-F42A Upper Deck Crew Service Door Cutout 

Structure

Frame Inner Chord and Web, BS 390 and BS 420 from S-11R to S-14R

N/A 20,000 (3)

53-00-F42B Upper Deck Crew Service Door 

Cutout Structure

Skin and Strap at Frame Outer Chord,BS 390 and BS 420 from S-6R to S-12R

N/A 20,000 (3)

53-00-F42C.1 Upper Deck Crew Service Door 

Cutout Structure

Upper Forward Skin Cutout Corner N/A 20,000 (3)

53-00-F42C.2 Upper Deck Crew Service Door 

Cutout Structure

Upper Aft, Lower Forward, and Lower Aft Skin Cutout Corners

N/A 20,000 (3)

53-00-F43A Crew Emergency (Exit) Hatch 

Cutout Structure

Frame Inner Chord at BS 360 and BS 380 from Str-0 to Str-4L

20,000 (3) 20,000 (3)

53-00-F43B Crew Emergency (Exit) Hatch 

Cutout Structure

Skin and Strap at Frame Outer Chord BS 360 and BS 380 from Str-1L to Str-3L

20,000 (3) 20,000 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-00-F44A Electronic and Equipment Access 

Door Cutouts

Cutout Corners and Edges Along Frames

20,000 (3) 20,000 (3)

53-00-F45B Main Deck Side Cargo Door Cutout Edge Frame Outer Chords, BS 1700 

and BS 1840

N/A 20,000 (3)

53-00-F45C Main Deck Side Cargo Door Cutout Latch Support Fittings N/A 20,000

53-00-F45F Main Deck Side Cargo Door Cutout Cutout Corners N/A 20,000 (3)

53-00-F45H Main Deck Side Cargo Door Cutout Upper Main Sill Inner Chord N/A 20,000 (3)

53-00-F45K.1 Main Deck Side Cargo Door Cutout Skin at S-9L between BS 1580 and 

BS 1640 and between BS 1900 and BS 1960

N/A 20,000 (3)

53-00-F45K.2 Main Deck Side Cargo Door Cutout S-9L between BS 1580 - 1640 and 

BS 1900 - 1960; S-27L between BS 1580 - 1600 and BS 1900 - 1960

N/A 20,000 (3)

53-00-F45K.3 Main Deck Side Cargo Door Cutout S-4L from BS 1949 to BS 1979 N/A 20,000 (3)

53-00-F46 Section 48 Jackscrew Support Clevis Fitting 20,000 (3) 20,000 (3)

53-00-F48A Section 48 Aft Pressure Bulkhead Web at Circumferential Y-Chord 

Attachment above WL 194

20,000 (3) 20,000 (3)

53-00-F48B Section 48 Aft Pressure Bulkhead Aft Pressure Bulkhead Web 20,000 20,000

53-00-F48C Section 48 Aft Pressure Bulkhead Y-Chord at Circumferential Web 

Attachment below WL 189

20,000 (3) 20,000 (3)

53-00-F48D Section 48 Aft Pressure Bulkhead Radial Web Splices – Visible Detail 20,000 (3) 20,000 (3)

53-00-F48E Section 48 Aft Pressure Bulkhead Radial Web Splices – Hidden Detail 20,000 (3) 20,000 (3)

53-00-F48F Section 48 Aft Pressure Bulkhead Regular and Super Tear Strap Splices 

Visible detail from bulkhead aft side

20,000 (3) 20,000 (3)

53-00-F48G Section 48 Aft Pressure Bulkhead Regular and Super Tear Strap Splices 

Hidden detail from bulkhead aft side

20,000 (3) 20,000 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-00-F49A BS 2598 Bulkhead Upper Bulkhead Web at Shear Deck 

Chord, Outboard of Diagonal Brace Attachment

20,000 20,000 (4)

53-00-F49B BS 2598 Bulkhead Side Frame Inner Chords between 

WL 305 and WL 317

20,000 (3) 20,000 (3) (4)

53-00-F49C BS 2598 Bulkhead Pivot Fitting and Longeron 

Attachments to BS 2598 Bulkhead, WL 265 to 320

20,000 (3) 20,000 (3) (4)

53-00-F49F BS 2598 Bulkhead Diagonal Brace Strut, Rod End Inner 

Sleeve (Upper Struts only)

20,000 (3) 20,000 (3) (4)

53-00-F49G BS 2598 Bulkhead Diagonal Brace Strut Attachment Lugs 

at WL 317

20,000 (3) 20,000 (3) (4)

53-00-F49H BS 2598 Bulkhead Diagonal Brace Strut Rod End 

Clevises at WL 317

20,000 (3) 20,000 (3) (4)

53-00-F51 Section 48 Longerons Upper Longeron from BS 2557 to 2579 20,000 20,000 (4)

53-00-F53A Nose Landing Gear Support Structure Trunnion Fitting Stem: BS390, from 

WL 129 to WL183

20,000 (3) 20,000 (3)

53-00-F53B.1 Nose Landing Gear Support Structure Drag Brace Lug: BS350, WL164, 

+/- BL3.75

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

53-00-F53B.2 Nose Landing Gear Support Structure Drag Brace: Flange at NGWW Top 

Panel BS 340 - BS360, WL187, +/- BL3.75

FLS, 

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, +/- BL3.75

20,000 (3) 20,000 (3)

53-00-F53C.1 Nose Landing Gear Support Structure Transverse Brace: Lower Flange 

BS 362.5, WL 177

20,000 (3) 20,000 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

53-00-F53C.2 Nose Landing Gear Support Structure Transverse Brace: Forward Edge of 

Lower Flange – BS 360, WL 177

20,000 (3) 20,000 (3)

53-00-F55C Underwing Longeron BS 990 at S-38L/R 20,000 (3) 20,000 (3)

53-00-F57A Section 48 Skin Panels Forward of 

BS 2658

Upper Lobe Doubler at Fuselage to Vertical Stabilizer Attachment

20,000 (3) 20,000 (3)

53-00-F58A Section 48 - Stabilizer Hinges and 

Support Fittings

Pivot Hinge Inboard Lugs – BS 2598, WL 292.50, LBL/RBL 43.5

20,000 (3) 20,000 (3) (4)

53-00-F58B Section 48 - Stabilizer Hinges and 

Support Fittings

Pivot Hinge Outboard Lugs – BS 2598, WL 292.50, LBL/RBL 43.5

20,000 (3) 20,000 (3) (4)

53-00-F58C Section 48 - Stabilizer Hinges and 

Support Fittings

Diagonal Brace Lugs, BS 2598 20,000 (3) 20,000 (3) (4)

53-00-F59B Nose Cargo Door Cutout Fuselage (C-3) Closure Frame 

Outer Chords

N/A 20,000 (3)

53-00-F59C Nose Cargo Door Cutout Fuselage (C-3) Closure Frame 

Back-up Fittings

N/A 20,000 (3)

53-00-F59D Nose Cargo Door Cutout Fuselage (C-3) Closure Frame 

Inner Chords

N/A 20,000 (3)

53-00-F59G Nose Cargo Door Cutout Fuselage (C-3) Closure Frame 

Upper Fitting

N/A 20,000 (3)

53-00-F61A Miscellaneous Fuselage Cutouts Drain Mast Cutouts at BS 1830 and 

BS 2130 between S-51L and S-51R

20,000 (3) N/A

53-00-F61B Miscellaneous Fuselage Cutouts Lavatory Service Pan Cutouts 20,000 20,000

53-00-F62A.1 Outflow Valve Outlet Cutout Cutout Corners 20,000 (3) 20,000 (3)

53-00-F64A Antenna Cutouts Skin Under ADF Antennas 20,000 (3) 20,000 (3) A

53-00-F64A.1 Antenna Cutouts Skin Under ADF Antennas N/A 20,000 (3) L/

53-00-F64B Antenna Cutouts Skin Under Blade Antennas in Bilge 

and Crown

20,000 (3) 20,000 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

SEP 2015
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

53-00-F64C Antenna Cutouts Skin Around Blade Antennas in Bilge 

and Crown

20,000 (3) 20,000 (3)

53-00-F64D Antenna Cutouts BS 510 and BS 610 in the Crown 20,000 20,000

53-00-F64E Antenna Cutouts Skin at TCAS and ADF Antennas in 

Bilge and Crown

20,000 (3) 20,000 (3)

53-00-F65A.1 Equipment Cooling Outlet Cutout Skin at Doubler Periphery Between 

BS 520 - 580 and S46L - S44R

20,000 (3) N/A

53-00-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 at 

S-32L/R and from BS 1480 to 1480+60 at S-33L/R

20,000 (3) 20,000 (3)

53-00-F71A Upper Deck Emergency Exit Door 

Cutout Structure

Frame Inner Chord and Web, BS 666.25 and BS 713.75 from S-12 to S-15

20,000 (3) N/A

53-00-F71B Upper Deck Emergency Exit Door 

Cutout Structure

Skin and Strap at Frame Outer Chord, BS 666.25 and BS713.75 from S-3 to S-13

20,000 (3) N/A

53-00-F71C Upper Deck Emergency Exit Door 

Cutout Structure

Skin Cutout Corners 20,000 (3) N/A

54-50-001 Strut to Wing Attachment Fittings – 

Inboard Strut

All Strut to Wing Fittings FLS, 

< 7hrs 15,000 

≥ 7hrs 10,000

FLS,

< 7hrs 15,000

≥ 7hrs 10,000

54-50-002 Strut to Wing Attachment Fittings – 

Outboard Strut

All Strut to Wing Fittings FLS, See Figure 2 FLS, See Figure 2

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

54-50-002d_R3 (8) NONE Strut Outboard Aft Upper Spar Fittings 

on Outboard Struts

2,400 

Flight Cycles after 

Airplane Delivery 

or Upon 

Disassembly of 

the Joint, 

whichever 

occurs first

2,400 

Flight Cycles after 

Airplane Delivery 

or Upon 

Disassembly of 

the Joint, 

whichever 

occurs first

PSthFfepIf cofueuwAa

54-50-003

DELETED

NONE Forward Engine Mount Assemblies Within 200 Flight 

Cycles from the 

date of issuance 

of the original 

certificate of 

airworthiness or 

the original export 

certificate of 

airworthiness, or 

within 30 calendar 

days of the 

November 2013 

release of this 

document 

(D011U721-02-

01), whichever 

occurs later. 

Repeat interval 

not to exceed 200 

Flight Cycles. (9)

Within 200 Flight 

Cycles from the 

date of issuance of 

the original 

certificate of 

airworthiness or the 

original export 

certificate of 

airworthiness, or 

within 30 calendar 

days of the 

November 2013 

release of this 

document 

(D011U721-02-01), 

whichever occurs 

later. Repeat interval not to 

exceed 200 Flight 

Cycles. (9)

PoEaB

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

54-50-003c NONE Forward Engine Mount Assemblies All 747-8 

Airplanes with 

barrel nut 

SL4750NA at the 

forward engine 

mount, including 

airplanes that 

have 

accomplished the 

barrel nut 

replacement per 

Boeing Service 

Bulletin 

747-71-2332.

All 747-8F 

Airplanes with 

barrel nut 

SL4750NA at the 

forward engine 

mount, including 

airplanes that have 

accomplished the 

barrel nut 

replacement per 

Boeing Service 

Bulletin 

747-71-2332.

AfoSinmpa(1cep(2lunb(4seNPep1aty

54-50-005a-01a Upper Spar Assembly – Inboard 

Engine Pylon

R1/Web Attachment, R1 Edge NSTA 204-NSTA 278

20,000 (3) 20,000 (3)

54-50-005a-01b Upper Spar Assembly – Inboard 

Engine Pylon

R1/Web Attachment, Fastener Holes NSTA 204-NSTA 278

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

54-50-005a-05a Upper Spar Assembly – Inboard 

Engine Pylon

Web/Chord/Skin Joint, Fastener Holes NSTA 200-NSTA 300

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

54-50-005a-05b Upper Spar Assembly – Inboard 

Engine Pylon

Web/Chord/Skin Joint, RH System Shroud Support Brackets

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

54-50-005a-09 Upper Spar Assembly – Inboard 

Engine Pylon

Web Cutouts, NSTA 200-NSTA 240 FLS, 

See Figure 1

FLS, 

See Figure 1

54-50-005b-04a Lower Spar Assembly – Inboard 

Engine Pylon

Web/Chord/Skin Joint, Web Cutout Edge, NSTA 216-273

FLS,

< 7hrs 15,000 (3)

≥ 7hrs 10,000 (3)

FLS,

< 7hrs 15,000 (3)

≥ 7hrs 10,000 (3)

54-50-005b-04b Lower Spar Assembly – Inboard 

Engine Pylon

Web/Chord/Skin Joint, Chord Edge, NSTA 218-289, 300-329

FLS,

< 7hrs 15,000 (3)

≥ 7hrs 10,000 (3)

FLS,

< 7hrs 15,000 (3)

≥ 7hrs 10,000 (3)

54-50-005b-04c Lower Spar Assembly – Inboard 

Engine Pylon

Heat 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 – Inboard 

Engine Pylon

AEMB/Web/Chord/Skin, Chord Holes Common to AEMB 

FLS,

< 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 Pylon

Engine Mount Tension Bolt Holes 20,000 20,000

54-50-005d-02 Forward Engine Mount Bulkhead – 

Inboard Engine Pylon

Shear Pin 20,000 (3) 20,000 (3)

54-50-005e-01 Aft Engine Mount Bulkhead – Inboard 

Engine Pylon

Engine Mount Tension Bolt Holes 20,000 20,000

54-50-005e-03 Aft Engine Mount Bulkhead – Inboard 

Engine Pylon

Shear Pin 20,000 (3) 20,000 (3)

54-50-005e-04 Aft Engine Mount Bulkhead – Inboard 

Engine Pylon

Shear Pin Boss 20,000 20,000

54-50-005f-01 Aft Strut Bulkhead – Inboard Engine 

Pylon

Cutout, Cutout Stiffener and R2 Attachment

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

54-50-006a-05a Upper Spar Assembly – Outboard 

Engine Pylon

Web/Chord/Skin Joint, RH System Shroud Support Brackets

20,000 (3) 20,000 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

54-50-006a-05b Upper Spar Assembly – Outboard 

Engine Pylon

Web/Chord/Skin Joint, NSTA 200-NSTA 260

FLS,

< 7hrs 15,000 (3)

≥ 7hrs 10,000 (3)

FLS,

< 7hrs 15,000 (3)

≥ 7hrs 10,000 (3)

54-50-006a-05c Upper Spar Assembly – Outboard 

Engine Pylon

Web/Chord/Skin Joint, Chord Edge NSTA 280-NSTA 300

20,000 (3) 20,000 (3)

54-50-006a-07 Upper Spar Assembly – Outboard 

Engine Pylon

Aft Upper Spar Fitting/Web/Skin Joint FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

54-50-006b-04a Lower Spar Assembly – Outboard 

Engine Pylon

Web/Chord/Skin Joint, Fastener Holes NSTA 216-NSTA 290

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

54-50-006b-04b Lower Spar Assembly – Outboard 

Engine Pylon

Web/Chord/Skin Joint, At GSE Fitting NSTA 281-NSTA 284

20,000 (3) 20,000 (3)

54-50-006b-04c Lower Spar Assembly – Outboard 

Engine Pylon

Web/Chord/Skin Joint, Chord Edge NSTA 216-NSTA 295

20,000 (3) 20,000 (3)

54-50-006d-01 Forward Engine Mount Bulkhead – 

Outboard Engine Pylon

Engine Mount Tension Bolt Holes 20,000 20,000

54-50-006d-02 Forward Engine Mount Bulkhead – 

Outboard Engine Pylon

Shear Pin 20,000 (3) 20,000 (3)

54-50-006e-01 Aft Engine Mount Bulkhead – 

Outboard Engine Pylon

Engine Mount Tension Bolt Holes 20,000 20,000

54-50-006e-03 Aft Engine Mount Bulkhead – 

Outboard Engine Pylon

Shear Pin 20,000 (3) 20,000 (3)

54-50-006e-04 Aft Engine Mount Bulkhead – 

Outboard Engine Pylon

Shear Pin Boss 20,000 20,000

54-50-006f-01 Aft Strut Bulkhead – Outboard 

Engine Pylon

Cutout, Cutout Stiffener and R2 Attachment 

FLS, 

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 P

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

55-10-E01A.1 Horizontal Stabilizer Upper Panel 

Z-Stringer

Rib 9 &10, S-1 thru S-11; Rib 10 & 11, S-11

20,000 20,000 (4)

55-10-E01A.7 Horizontal Stabilizer Upper Panel 

Z-Stringer

Rib 2 to 5, S-1 thru S-4; Rib 5 to 8, S-6 & S-7

20,000 20,000 (4)

55-10-E01A.8 Horizontal Stabilizer Upper Panel 

Z-Stringer 

Rib 2 to 3, S-1 thru S-2; Rib 4 to 7, S-1 thru S-4; Rib 7 to 8, S-4

20,000 (3) 20,000 (3) (4)

55-10-E01A.11 Horizontal Stabilizer Upper Panel 

Z-Stringer 

Rib 1 to 2 (BL14.5 outbd to edge of splice), S-1 & S-2

20,000 20,000 (4)

55-10-E01B.1 Horizontal Stabilizer Typ Stringer at 

BL 14.5 Splice Strap

S-9 to S-16, BL 14.5 20,000 (3) 20,000 (3) (4)

55-10-E01F Horizontal Stabilizer Upper Panel 

Z Strg

Aft Torque Box Internal BL 43.5 to Stab Sta 285

N/A FLS, 

See Figure 1 (4a)

55-10-E04E.2 Horiz Stabilizer, Center Upper Front 

Spar Chord to Skin

At BBL 14.50 (at Actuator Rib - 1) 20,000 (3) 20,000 (3) (4)

55-10-E04E.3 Horiz Stabilizer, Center Upper Front 

Spar Chord to Skin

At BBL 14.50 (at Actuator Rib - 1) 20,000 (3) 20,000 (3) (4)

55-10-E05A.2 Horiz Stabilizer, Outboard Upper Rear 

Spar Chord to Skin

Stab Sta 172.4 to Stab sta 235 FLS, 

See Figure 1

FLS, 

See Figure 1 (4a)

55-10-E05A.3 Horiz Stabilizer, Outboard Upper Rear 

Spar Chord to Skin

Skin between Rib 3 & Rib 7 FLS, 

See Figure 1

FLS, 

See Figure 1 (4a)

55-10-E05B.2 Horiz Stabilizer, Outboard Upper Rear 

Spar Chord to Skin

Chord at Ribs 3 to 7 FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3) (4a)

55-10-E05F.1 Horiz Stabilizer, Center Box Upper 

Rear Spar Chord to Skin

B/t BBL 29 & BL 43.5 Splice Fitting FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3) (4a)

55-10-E05F.3 Horiz Stabilizer, Center Box Upper 

Rear Spar Chord to Skin

Skin 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 Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

55-10-E05G.1 Horiz Stabilizer, Center Box Upper 

Rear Spar Chord to Skin

At 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 Upper 

Rear Spar Chord to Web

Between 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 Upper 

Rear Spar Chord to Web

Between 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 Upper 

Rear Spar Chord to Web

Between 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 Jackscrew 

Fitting

Inner Lower Splice Plate at jackscrew fitting attachment

20,000 (3) 20,000 (3) (4)

55-10-E08A.1 Horizontal Stabilizer, Center Box 

Upper Rear Spar Chord to Skin at S.O.B.

Inbd of Rib -2 (SOB) c/t upr splice ftng At Inbd-most .375" dia fastener pair

20,000 (3) 20,000 (3) (4)

55-10-E08A.2 Horiz Stabilizer, Outboard Upper Rear 

Spar Chord to Skin at S.O.B.

Betn Rib-2 (SOB Rib) & Rib-3 At Outbd-most .375" dia fastener pair

20,000 (3) 20,000 (3) (4)

55-10-E08B.1a Horiz Stabilizer, Center-Box Upper 

Rear Spar Chord to Skin at S.O.B.

Inbd of Rib-2 (SOB) c/t upr splice ftng At Inbd-most .375" dia fastener pair

20,000 (3) 20,000 (3) (4)

55-10-E08B1.b Horiz Stabilizer, Center-Box Upper 

Rear Spar Chord to Skin at S.O.B.

Inbd of Rib-2 (SOB) c/t upr splice ftngAt Inbd-most .4375" dia fastener pair

20,000 (3) 20,000 (3) (4)

55-10-E08B2.a Horiz Stabilizer, Outboard Upper Rear 

Spar Chord to Skin at S.O.B.

Betn Rib-2 (SOB Rib) & Rib-3At Outbd-most .375" dia fastener pair

20,000 (3) 20,000 (3) (4)

55-10-E08B2.b Horiz Stabilizer, Outboard Upper Rear 

Spar Chord to Skin at S.O.B.

Betn Rib-2 (SOB Rib) & Rib-3At Outbd-most .4375" dia fastener pair

20,000 (3) 20,000 (3) (4)

55-10-E08H.3a Horizontal Stabilizer Side of 

Body Splice

Front Spar Terminal Fitting 20,000 20,000 (4)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

55-10-E08J.1 Horizontal Stabilizer, Center Box 

Typical Upper Stringer to Skin at S.O.B.

Stringer S-1 termination, at inbd-most .375" dia fastnr c/t inner splice pl

20,000 (3) 20,000 (3) (4)

55-10-E08J.2 Horiz Stabilizer, Outboard Typical 

Upper Stringer to Skin at S.O.B.

Stringer S-1 termination, at outbd-most .375" dia fastnr c/t inner splice pl

20,000 (3) 20,000 (3) (4)

55-10-E08K.1 Horiz Stab, Inboard Upper Aft 

SOB Splice – Splice Plates-to-Stringer

Inbd of Rib-2 (SOB) at S-2 termination 20,000 (3) 20,000 (3) (4)

55-10-E08K.2 Horiz Stab, Inboard Upper Aft 

SOB Splice – Splice Plates-to-Stringer

Outbd of Rib-2 (SOB) at S-2 termination

20,000 (3) 20,000 (3) (4)

55-10-E08L.1 Horiz Stab, Inboard Upper Aft 

SOB Splice – Splice Plates-to-Skin

Inbd of Rib-2 (SOB) c/t upr splice ftngSecond-most outbd .4375" dia fast pair

20,000 (3) 20,000 (3) (4)

55-10-E08L.2 Horiz Stab, Inboard Upper Aft 

SOB Splice – Splice Plates-to-Skin

Betn Rib-2 (SOB Rib) & Rib-3 At second-most inbd .4375" dia fast pair

20,000 (3) 20,000 (3) (4)

55-10-E08O.1 Horizontal Stabilizer Side of 

Body Splice

Hinge Rib Web – BL 43.5 20,000 20,000 (4)

55-10-E08P.1a Horizontal Stabilizer Side of 

Body Splice

Rear Spar Upper Splice Fitting Forward Flange

20,000 20,000 (4)

55-10-E08P.2a Horizontal Stabilizer Side of 

Body Splice

Hinge Rib Upper Chord Web Flange at Rear Spar

20,000 (3) 20,000 (3) (4)

55-10-E08Q.1 Horizontal Stabilizer Side of 

Body Splice

Splice Fitting Inboard / Outboard Web Flange

20,000 (3) 20,000 (3) (4)

55-10-E08R.1 Horizontal Stabilizer Side of 

Body Splice

Rear Spar Upper Splice Fitting Skin Flange

20,000 (3) 20,000 (3) (4)

55-10-E09 Jackscrew Support Fitting Attachment 

Arms

Fitting 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 Stabilizer 20,000 (3) 20,000 (3) (4)

55-10-E10B1 Pivot Fitting Attachment Structure Inner Splice at Pivot Fitting Upper 

Flange - Outboard Side Attachment

20,000 (3) 20,000 (3) (4)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

55-10-E10B2 Pivot Fitting Attachment Structure Inner Splice at Pivot Fitting Upper 

Flange - Inboard Side Attachment

20,000 (3) 20,000 (3) (4)

55-10-E10C.1 Pivot Fitting Attachment Structure Pivot fitting upper flange to splice 

plates attachment

20,000 (3) 20,000 (3) (4)

55-10-E10E Back to Back Lug Horizontal Stabilizer H. Stab Pivot Fitting Lug 20,000 (3) 20,000 (3) (4)

55-20-E01 Inbd & Outbd Elevator Hinges Horizontal Stabilizer

Actuator & Elevator Hinges

20,000 20,000 (4)

55-30-E03A.2 Vertical Fin Front Spar Chord to Skin at Fin Sta 117 Rib Shear 

Tie attach fastener

20,000 (3) 20,000 (3)

55-30-E03D.2 Vertical Fin Front Spar Web adjacent to chord from Fin Sta 

98.5 to Fin Sta 117

20,000 (3) 20,000 (3)

55-30-E04B.1 Vertical Fin Rear Spar Rear Spar Chord / Skin at Fin Sta 163 

to 270-Lower 7 rib to skin/spar chord

20,000 (3) 20,000 (3)

55-30-E07B.3 Vertical Fin to Body Attachment Rear Spar Root Ftg to Web at root 

splice joint

20,000 (3) 20,000 (3)

55-30-E07B.4 Vertical Fin to Body Attachment Rear Spar Root Ftg to Skin at root 

splice joint

20,000 (3) 20,000 (3)

55-30-E07C.3 Vertical Fin to Body Attachment Front Spar Root Ftg to Web at root 

splice joint

20,000 (3) 20,000 (3)

55-30-E07C.4 Vertical Fin to Body Attachment Front Spar Root Ftg to Skin at root 

splice joint

20,000 (3) 20,000 (3)

55-40-E01 Vertical Fin, Lower Rudder, 

Control Rods

Upper, Lower Control rods and attachments at Rudder Sta 82.792 and 107.757

20,000 20,000

55-40-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 20,000

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-10-W01A.1 Side of Body Splice, Upper Surface Lead Crack in Double Plus Chord FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W01A.2 Side of Body Splice, Upper Surface Lead Crack in Double Plus Chord FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W01B.1 Side of Body Splice, Upper Surface Skin crack on intact stringer at 

Stringer 1 Joint, Section 12

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W01C.1 Side of Body Splice, Upper Surface Paddle Fitting Crack at Double Plus 

Chord Joint

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W01D.1 Side of Body Splice, Upper Surface Stringer Crack at Joint FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W02A.1 Side of Body Splice, Lower Surface Inner Splice Plate, Section 12 FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W02A.2 Side of Body Splice, Lower Surface Lead Crack in skin FLS, 

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 Joint 

near Rear Spar

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W02A.4 Side of Body Splice, Lower Surface Lead Crack in Stringer FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W02A.5 Side of Body Splice, Lower Surface Lead Crack in Splice Stringer FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W02B.1 Side of Body Splice, Lower Surface Inner Splice Plate, Section 11 FLS, 

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 Skin

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W03A.2 Side of Body Splice, Front Spar Center Section Lower Front Spar 

Chord and Web

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-10-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 Skin 

FLS, 

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 Skin 

Upper and Lower

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W04C Side of Body Splice, Rear Spar Outboard Chord and Skin Upper 

and Lower

FLS, 

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 and Terminal Fitting

FLS, 

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 Ftg

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W05A.1 Side of Body Rib Web at Chord Attachment FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-10-W05A.2 Side of Body Rib Web at Chord Attachment Crack 

Hidden by Stiffener

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-10-W06A.3 Center Section Rear Spar Lower Chord to Web Attachment Near 

the Pickle Fork Fitting

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W06B.1 Center Section Rear Spar Upper Chord to Web Attachment 

At Stiffener

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-10-W06B.2 Center Section Rear Spar Upper Chord to Web Attachment 

Between Stiffeners

FLS, 

See Figure 2

FLS, 

See Figure 2

57-10-W07A.1 Center Section Front Spar Lower Chord to Web Attachment Fillet 

Radius of Web Pockets

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-10-W07A.2 Center Section Front Spar Lower Chord to Web Attachment 

Between Stiffeners

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W07A.3 Center Section Front Spar Lower Chord to Web Attachment 

Hidden by ext. & int. stiffeners

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W07B.1 Center Section Front Spar Ring Chord to Web Attachment 

Between Stiffeners

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W07B.2 Center Section Front Spar Ring Chord to Web Attachment Hidden 

by ring chord & int. stiffeners

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W12A.4 Wing Center Section Lower Panel Typical Stringer with shear tie at BL9 

Keel beam upper chord attachment

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W12A.9 Wing Center Section Lower Panel Typical Stringers with skin hidden FLS, 

See Figure 1

FLS, 

See Figure 1

57-10-W12A.10 Wing Center Section Lower Panel BL 0 aft of Midspar, typical stringer FLS, 

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 Lower Panel Stringer adjacent to spar chord 

Stringer 1

FLS, 

See Figure 1

FLS, 

See Figure 1

57-10-W12A.15 Wing Center Section Lower Panel Stringer adjacent to spar chord – 

stringer 1

FLS, 

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 1

FLS, 

See Figure 1

57-10-W12B.1 Wing Center Section Lower Panel Splice Stringer - Exposed Areas FLS, 

See Figure 1

FLS, 

See Figure 1

57-10-W12B.2 Wing Center Section Lower Panel – 

Splice Stringers

Splice Stringer 10 (Midspar Chord) at stiffener locations

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-10-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 Chord at stiffeners FLS, 

See Figure 1

FLS, 

See Figure 1

57-10-W12C.6 Wing Center Section Lower Panel Rear Spar Chord FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W13A.3 Wing Center Section Upper Panel Typical Stringer at BL 0 FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-10-W13A.4 Wing Center Section Upper Panel 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 stiffeners FLS, 

See Figure 2

FLS, 

See Figure 2

57-10-W13B.2 Wing Center Section Upper Panel Stringer 14 at stiffeners at BL 113 FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W13B.3 Wing Center Section Upper Panel Stringer 14 FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W13B.7 Wing Center Section Upper Panel Stringer 14 at floorbeam FLS, 

See Figure 1

FLS, 

See Figure 1

57-10-W13B.9 Wing Center Section Upper Panel Stringer 14 from LBL11 to RBL11 FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W13C.1 Wing Center Section Upper Panel Rear Spar Chord at Exposed Areas FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W13C.3 Wing Center Section Upper Panel Rear Spar Chord FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-10-W13C.4 Wing Center Section Upper Panel Front Spar Chord at floorbeams chord 

completely hidden

FLS, 

See Figure 1

FLS, 

See Figure 1

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-10-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 Section Upper Panel Rear Spar Chord FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W01A.3 Lower Panel Typical Stringer under Inbd 

Strut Fairings

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W01A.5 Lower Panel Typical Stringer under Track Fairings FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W01A.6 Lower Panel Typical Stringer at Strut Support 

Fittings of Inbd and Outbd Nacelles

FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W01A.8 Lower Panel Typical Stringer under Strut and Flap 

Fairings

FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W01A.9 Lower Panel Typical Stringer at Strut Support 

Fittings

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W01A.10 Lower Panel Typical Stringer at Flap Track Forward 

Support Fittings

FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W01A.14 Lower Panel Lower Panel at Access Doors FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W01B.2 Lower Panel At Splice Stringer 10 under Fairings FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W01B.3 Lower Panel Splice Stringer under Fairings 

(S-5 and S-15)

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W01B.5 Lower Panel Splice Stringer at Rib Posts (Mid Spar 

Only) of Ribs 16 and 17

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W01B.6 Lower Panel Midspar Chord at Rib Posts – Inspar 

Ribs other than 16 and 17

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-20-W01B.7 Lower Panel Splice 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 Panel Front / Rear Spars at Inspar Rib Posts FLS, 

See Figure 1

FLS, 

See Figure 1

57-20-W01C.4 Lower Panel Front and Rear Spar between Inspar 

Rib Posts Spar Chord

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W01C.6 Lower Panel Front and Rear Spar Chord 

(Spar Chord completely hidden)

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W01C.7 Lower Panel Spar Chord at Longitudinal Splices FLS, 

See Figure 1

FLS, 

See Figure 1

57-20-W02A.2 Outboard Wing Upper Panel Stringer Adjacent to Spar Chord – 

Stringer 1

FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W02A.4 Outboard Wing Upper Panel Stringer Adjacent to Spar Chord – 

Stringer 1

FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W02A.5 Outboard Wing Upper Panel Stringer adjacent to spar chord at 

fuel baffles

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W02B.1 Outboard Wing Upper Panel Exposed Areas of Panel at 

Splice Stringer 27

FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W02B.3 Outboard Wing Upper Panel Splice Stringer 14 at Rib bay 12 FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W02C.1 Outboard Wing Upper Panel Rear Spar Upper Chord (Visible Areas) FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W02C.4 Outboard Wing Upper Panel Rear 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 Panel Rear Spar at rib post FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-20-W02C.6 Outboard Wing Upper Panel Front and Rear Spar Chord FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W02C.7 Outboard Wing Upper Panel Rear Spar Chord at rib 8 post FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W02C.8 Outboard Wing Upper Panel Front Spar Chord at rib post Spar 

Chord completely hidden

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W02D.1B Outboard Wing Upper Panel R1 Tab, Outboard Engine FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W02D.2B Outboard Wing Upper Panel R1 Tab, Inboard Engine FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W03A.2 Wing Rear Spar Upper Chord to Web Attachment 

Hidden by TE stiffener

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W03A.4 Wing Rear Spar Upper Chord to Web Attachment 

Hidden by Inspar Rib Post or stiffener

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W03D.1 Wing Rear Spar Lower Spar to Web Attachment Hidden 

by TE Stiffener

FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W03D.1.1 Wing Rear Spar Lower Spar to Web Attachment Hidden 

by TE Stiffener & Fuel Doubler

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W03D.4 Wing Rear Spar Lower Chord to Web Attachment 

Hidden by Inspar Ribpost

FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W03D.4.1 Wing Rear Spar WS 411.42 (outbd ribpost) Hidden by 

Inspar Ribpost & Fuel Doubler

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W03D.8 Wing Rear Spar Lower Chord to Web Attachment Rib 

20 Hidden by TE Stiffener & Inspar Rib Post

FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W03D.10 Wing Rear Spar Chord to Web Attachment Rib Bay 11 

(WS 528.22 - 557.42) Hidden by TE Stiffener

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-20-W03D.11 Wing Rear Spar Rib Bay 11 (WS 528.22 to WS 557.42) 

Hidden by Inspar Rib Post or Stiffener

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W03E.1 Wing Rear Spar Rib Bay 11 (WS 528.22 to WS 557.42) 

Hidden by Major Fittings

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W03E.2 Wing Rear Spar Chord to Web Attachment Hidden by 

Major Fittings

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W03E.3 Wing Rear Spar Chord to Web Attachment Hidden by 

Major Ftg. & Inspar Rib Post

FLS, 

See Figure 2

FLS, 

See Figure 2

57-20-W03E.5 Wing Rear Spar Chord to Web Attachment Hidden by 

Major Ftg. & Inspar Rib Post

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-20-W04G.4 Front Spar Hidden by LE Rib Post or Stiffener FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W04H.4 Front Spar Web hidden by Inspar Rib Post FLS, 

See Figure 1

FLS, 

See Figure 1

57-20-W04I.2 Front Spar Rib 34; hidden by Inspar Rib Post & 

LE Stiffener

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W04J.4 Front Spar At attachment of Nacelle Fittings FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W04J.6 Front Spar Rib Bay 37 at attachment of Jack Pad 

Fitting and Rib 38

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W07A.1 Shear-Tied Ribs Flap Track Back Up Ftg: Aft Ribs 24 

& 30

20,000 (3) 20,000 (3)

57-20-W07A.2 Shear-Tied Ribs Flap Track Back Up Ftgs 1 & 3 – 

Aft Rib 13

20,000 (3) 20,000 (3)

57-20-W07A.9 Shear-Tied Ribs Backup Fitting at Inboard Nacelle FLS, 

See Figure 1

FLS, 

See Figure 1

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-20-W07A.11 Shear-Tied Ribs R4 Back Up Fittings 3 & 5 – Fwd 

Rib 16

FLS, 

See Figure 1

FLS, 

See Figure 1

57-20-W07A.12 Shear-Tied Ribs Back Up Fittings - Fwd Rib 16 & 33 FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W07A.14 Shear-Tied Ribs Rear Spar Ribpost - Aft Rib 13 FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W08A.3 Wingbox Extension Joint Bolt Hole Crack in Splice Plate, Front 

Spar Joint at Inboard Rib 47, MSS 1558.7

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W08A.4 Wingbox Extension Joint Lower Front Spar Joint at Rib 47, 

MSS 1558.7

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W08B.4 Wingbox Extension Joint Lower Chord at Stringer Joint of 

Inboard Side Rib 47, MSS 1558.7

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W08C.1 Wingbox Extension Joint Lower Skin & Splice Stringer #5 Joint 

to Inboard Side of Rib 47, MSS 1558.7

FLS, 

See Figure 1

FLS, 

See Figure 1

57-20-W08C.2 Wingbox Extension Joint Skin & Paddle Fitting Joint to Splice 

Stringer #5 of Rib 47, Inboard Side

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W08C.4 Wingbox Extension Joint Lower Chord at Stringer #5 Joint of 

Inboard Side Rib 47, MSS 1558.7

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W08D.3 Wingbox Extension Joint Lower Rear Spar Joint at Rib 47, 

MSS 1558.7

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W08D.4 Wingbox Extension Joint Lower Rear Spar Joint at Rib 47, 

MSS 1558.7

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W09A.4 Raked WingTip Joint Lower Chord at Stringer #6 & #8 Joint 

Inboard Side Rib 52 at WBL 1243.8

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W09B.1 Raked WingTip Joint Lower Chord at Front Spar Joint 

Inboard Side Rib 52 at WBL 1243.8

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-20-W09E.1 Raked WingTip Joint Lower Chord at Rear Spar Joint 

Inboard Side Rib 52 at WBL 1243.8

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W10B.1 Wing Landing Gear Support Fittings Rear Spar Gate Support Fitting Assy 

Upper and Lower Horizontal Flange

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W10B.2 Wing Landing Gear Support Fittings Rear Spar Gate Supt Ftg - Rear Spar 

Web Joint

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W10B.3 Wing Landing Gear Support Fittings Rear Spar Gate Support Fitting Assy 

Upper and Lower Horizontal Flange

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W10B.4 Wing Landing Gear Support Fittings Vertical Flange Open Hole Rear Spar 

Gate Support Fitting Assy

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W11A Nacelle Support Fittings R1 Upper Link Pitch Fittings FLS, 

See Figure 1

FLS, 

See Figure 1

57-20-W11B Nacelle Support Fittings R2 Diagonal Brace Fitting FLS, 

See Figure 1

FLS, 

See Figure 1

57-20-W11C.1 Nacelle Support Fittings R3 Nacelle Support Outbd Fitting at 

Inboard Engine

FLS, 

See Figure 1

FLS, 

See Figure 1

57-20-W11C.2 Nacelle Support Fittings R4 Nacelle Support Inbd Fitting FLS, 

See Figure 1

FLS, 

See Figure 1

57-20-W11D Nacelle Support Fittings R3 Front Spar Backup Fittings FLS, 

See Figure 1

FLS, 

See Figure 1

57-20-W11E Nacelle Support Fittings R7/ R8 Side Load Link Fittings FLS, 

See Figure 1

FLS, 

See Figure 1

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-20-W11_R3 (8) NONE Strut Outboard Aft Upper Spar Fittings 

on Outboard Struts

2,400 

Flight Cycles after 

Airplane Delivery 

or Upon 

Disassembly of 

the Joint, 

whichever 

occurs first

2,400

Flight Cycles 

after Airplane 

Delivery 

or Upon 

Disassembly of

 the Joint, 

whichever

occurs first

PSthFfepIf cofueuwAa

57-20-W11H.3 Nacelle Support Fittings Outboard Engine R3 Nacelle Support 

Outboard Fitting – Lug

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W11H.4 Nacelle Support Fittings Outboard Engine R3 Nacelle Support 

Outboard Fitting – Lug

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-20-W11H.5 Nacelle Support Fittings Outboard Engine R3 Nacelle Support 

Outbd Fitting – Tension Bolts

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-51-W01C.3 Wing Landing Gear Beam Assembly Flap Track 4 Aft Attach – Wing Landing 

Gear Beam Joints

FLS, 

See Figure 2

FLS, 

See Figure 2

57-51-W01E.1 Wing Landing Gear Beam Assembly IB Flap Displacement Fitting Web 

Joints hidden by the Fitting Lower Chord

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-51-W01E.2 Wing Landing Gear Beam Assembly Web Joints located below upper chord 

and above lower chord

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-51-W01E.3 Wing Landing Gear Beam Assembly Lower Chord between Aft Trunnion 

and BS 1350 Bulkhead

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

D011U721-02-01

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

57-51-W01F.2 Wing Landing Gear Beam Assembly Actuator Rib Joint on 1350 Bulkhead at 

Side-of-Body – Lower Chord

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-51-W01I Wing Landing Gear Beam Assembly Actuator Rib Joint on 1350 Bulkhead at 

BL 109.4 – Lower Chord

FLS, 

See Figure 2 (3)

FLS, 

See Figure 2 (3)

57-51-W02A Gate Fitting Fuse Pin - WLG Beam End Fitting 

Outbd Bearing Double Shear Fuse Pin

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-51-W02B Gate Fitting Fuse Pin - Rear Spar Gate Fitting 

Single Shear Fuse Pins

FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-51-W03A Gear Beam End Fitting Lug Hole FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-51-W03B Gear Beam End Fitting Fitting Joint FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-51-W03C Gear Beam End Fitting Fitting Surface Edge FLS, 

See Figure 1 (3)

FLS, 

See Figure 1 (3)

57-53-W01A.3.1 Flap Track #1 and #8 Track Section – at hole, Fastener Hole 

attaching to Failsafe Bar

20,000 (3) 20,000 (3) (4)

57-53-W01A.3.2 Flap Track #1 and #8 Track Section – At Track Edge At 

Track Lower Flange Corners

20,000 (3) 20,000 (3) (4)

57-53-W01C Flap Track #1 and #8 Track Forward Support Lug – Clevis 

on 747-8/-8F Tracks/Failsafe Bar #1/8

20,000 (3) 20,000 (3) (4)

57-53-W02A.3.1 Flap Track #2 and #7 Track Section – At hole attaching to 

Failsafe Bar

20,000 (3) 20,000 (3) (4)

57-53-W02A.3.2 Flap Track #2 and #7 Track Section – At Track Lower Flange 

Corner

20,000 (3) 20,000 (3) (4)

57-53-W02C Flap Track #2 and #7 Track Forward Support Lug – Clevis 

on 747-8/-8F Tracks/Failsafe Bar #2/7

20,000 (3) 20,000 (3) (4)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
D011U721-02-01

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

747-8/8F AIRWORTHINESS LIMITATIONS

57-53-W03A.3.1 Flap Track #3 and #6 Track Section - At hole, Fastener Hole 

attaching to Failsafe Bar

20,000 (3) 20,000 (3) (4)

57-53-W03A.3.2 Flap Track #3 and #6 Track Section - At Hole attaching to 

ESB at lower flange outboard edge

20,000 (3) 20,000 (3) (4)

57-53-W03C Flap Track #3 and #6 Track Forward Support Lug – Clevis 

on 747-8/-8F Tracks/Failsafe Bar #3/6

20,000 (3) 20,000 (3) (4)

57-53-W04A.3.1 Flap Track #4 and #5 Track Section - at Hole, Fastener Hole 

attaching to Failsafe Bar

20,000 (3) 20,000 (3) (4)

57-53-W04A.3.2 Flap Track #4 and #5 Track Section - Hole attach to FSB, At 

Lower Flange Outboard Edge

20,000 (3) 20,000 (3) (4)

57-53-W05 Outbd Flap - Inbd Aux. track and Aux. 

Track Link

Aux Track, Link and joints. 20,000 20,000 (4)

57-53-W06 Outbd Flap - Outbd Aux. track and 

Aux. Track Link

Aux Track, Link and joints. 20,000 20,000 (4)

57-53-W07A.1 Inboard Flap – Tracks #3, #4, #5, and 

#6 Carriage Assemblies

At Inboard / Outboard Sideplates 20,000 (3) 20,000 (3) (4)

57-53-W07A.2 Inboard Flap – Tracks #3, #4, #5, and 

#6 Carriage Assemblies

Fwd Bogie Pivot Pin Boss / Lug at Inboard/Outboard Sideplates

20,000 (3) 20,000 (3) (4)

57-53-W07A.3 Inboard Flap – Tracks #3, #4, #5, and 

#6 Carriage Assemblies

Aft Bogie Pivot Pin Boss / Lug at Inboard/Outboard Sideplates

20,000 (3) 20,000 (3) (4)

57-53-W07B Inboard Flap – Tracks #3, #4, #5, and 

#6 Carriage Assemblies

Fwd \ AFT Fittings 20,000 20,000 (4)

57-53-W07C Inboard Flap – Tracks #3, #4, #5, and 

#6 Carriage Assemblies

Edge of fitting bridge at Aft Support Fitting

20,000 (3) 20,000 (3) (4)

57-53-W07P Inboard Flap – Tracks #3, #4, #5, and 

#6 Carriage Assemblies

Aft Bogie Pivot Pin 20,000 (3) 20,000 (3) (4)

57-53-W08 Inboard Flap Track Transmission 

Support Structures

Track #3/#6 and #4/#5 20,000 20,000 (4)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

MAY 2014
747-8/8F AIRWORTHINESS LIMITATIONS

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57-53-W09A Outboard Flap – Tracks #1, #2, #7, 

and #8 Carriage Assemblies

Sideplates at Flap Tracks 1/8 and 2/7 20,000 (3) 20,000 (3) (4)

57-53-W09B Outboard Flap – Tracks #1, #2, #7, 

and #8 Carriage Assemblies

Fwd \ AFT Fittings 20,000 20,000 (4)

57-53-W09C Outboard Flap – Tracks #1, #2, #7, 

and #8 Carriage Assemblies

Edge of fitting bridge at Aft Support Fitting

20,000 (3) 20,000 (3) (4)

57-53-W09D Outboard Flap – Tracks #1, #2, #7, 

and #8 Carriage Assemblies

Bogie Assembly - Pivot Pin 20,000 (3) 20,000 (3) (4)

57-53-W10A Outboard Flap – Transmission Mount 

Structure

Track #2/#7 and #1/#8 20,000 20,000 (4)

57-53-W11 Outboard Flap – Inboard Aux. Track 

Carriage Assembly

Carriage Assembly 20,000 20,000 (4)

57-53-W12 Outboard Flap – Outboard Aux. Track 

Carriage Assembly

Carriage Assembly 20,000 20,000 (4)

57-53-W13D Aft Support, Flap Track #1 and #8 Side Load Fitting, Track #1 /#8 20,000 (3) 20,000 (3) (4)57-53-W14D Aft Support, Flap Track #2 and #7 Side Load Fitting, Track #2 /#7 20,000 (3) 20,000 (3) (4)57-53-W15D Aft Support, Flap Track #3 and #6 Side Load Fitting, Track #3 /#6 20,000 (3) 20,000 (3) (4)

57-53-W16A Aft Support, Flap Track #4 and #5 Fitting Assy - Center Hole 

accommodating Shear Pin

20,000 (3) 20,000 (3) (4)

57-53-W17A Forward Support, Flap Track #1 

and #8

Track #1 and #8 Fwd Joint 20,000 20,000 (4)

57-53-W17BB Forward Support, Flap Track #1 

and #8

Radius along lug base 20,000 (3) 20,000 (3) (4)

57-53-W17BC Forward Support, Flap Track #1 

and #8

Fastener holes of Fwd Ftg attachment 20,000 (3) 20,000 (3) (4)

57-53-W18A Forward Support, Flap Track #2 

and #7

Track #2 and #7 Fwd Joint 20,000 20,000 (4)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

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57-53-W18BB Forward Support, Flap Track #2 

and #7

Radius along lug base 20,000 (3) 20,000 (3) (4)

57-53-W18BC Forward Support, Flap Track #2 

and #7

Fastener holes of Fwd Ftg attachment 20,000 (3) 20,000 (3) (4)

57-53-W19A1 Forward Support, Flap Track #3 

and #6

Track #3 and #6 Fwd Joint 20,000 20,000 (4)

57-53-W19BB Forward Support, Flap Track #3 

and #6

Radius along lug base 20,000 (3) 20,000 (3) (4)

57-53-W19BC Forward Support, Flap Track #3 

and #6

Fastener holes of Fwd Ftg attachment 20,000 (3) 20,000 (3) (4)

57-53-W20C Forward Support, Flap Track #4 

and #5

Forward Support Fitting – Web to Fwd Flange intersection

20,000 (3) 20,000 (3) (4)

57-53-W20D Forward Support, Flap Track #4 

and #5

Forward Support Fitting – Aft Flange Edge

20,000 (3) 20,000 (3) (4)

57-53-W20G Forward Support, Flap Track #4 

and #5

Forward Support Fitting to Track Joint 20,000 20,000 (4)

57-53-W24 Inboard Main Flap Gimbal and 

Carriage Support Fittings

Gimbal, Spigot, Failsafe link and Aft link joints

20,000 20,000 (4)

57-53-W32 Outboard Flap Gimbal and Carriage 

Support Fittings

Gimbal, Spigot and Aft Link Joints 20,000 20,000 (4)

57-53-W33 Outboard Flap Inboard Aux. Track 

Carriage Attachment

Aux. Track Carriage pin housing 20,000 20,000 (4)

57-53-W34 Outboard Flap Outboard Aux. Track 

Carriage Attachment

Aux. Track Carriage pin housing and support structure

20,000 20,000 (4)

Airworthiness Limitations – Structural Inspections Threshold Table

SSI No. (1) DTR Check Form Title (7) DTR Location

Thresholds (2)

747-8 747-8F 

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TABLE NOTES:1. Multiple listings under a single SSI # are uniquely identified by Check Form Title, Location, and Model-Series information. A

single SSI # for a given model must be performed.

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 

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. This 

limit, compliant with Title 14 CFR § 25.571, until the Service Bulletin inspection program is released. Please refer to the fut

the 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 14,000 flight cycles. This will act as an operat

Title 14 CFR § 25.571, until the Service Bulletin inspection program is released. Please refer to the future Service Bulletin (

inspections. 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, this inspection was incl

now 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.

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C. AIRWORTHINESS LIMITATIONS – STRUCTURAL SAFE-LIFE PARTS

The following Nose Landing Gear parts are subject to the Safe-Life Limits defined by Figure 3.

Part Number Part Name Part Number 

162U0211 Drag Strut, Upper 162U2605 Torsion Link, L162U0212 Drag Strut, Lower 162U2607 Tripod Apex P

162U0213 Drag Strut Pivot Shaft 162U2608 Tripod Upper B162U0215 Drag Strut Apex Bolt 162U2609 Side Brace Up162U2501 Outer Cylinder 162U2610 Tripod Lower B

162U2502 Inner Cylinder 162U2621 Torsion Link A

162U2504 Axle 162U2624 Steering Actua

162U2507 Restrictor Support Tube 162U2625 Steering Actua

162U2508 Restrictor Plate 162U2626 Torsion Link B

162U2511 Metering Pin 162U2627 Trunnion Pin

162U2513 Metering Pin Retaining Tube 162U2628 Side Brace Low162U2601 Side Brace 162U2631 Steering Collar 

162U2602 Tripod Brace, Upper 162U2632 Steering Collar 

162U2603 Tripod Brace, Lower 162U2633 Steering Collar 162U2604 Torsion Link, Upper

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Figure 3 – 747-8/8F Nose Landing Gear Safe-Life LimitsInstructions for using the Safe-Life Chart:1. For each Safe-Life component, determine the accumulated flight cycles and flight hours.2. Enter the Safe-Life Limit Chart at the appropriate numbers of flight cycles and flight hours and locate the intersection.3. If the point determined in Step 2 lies below the appropriate Safe-Life Limit Curve, the component  has not reached its Safe-Life Limit. If the point is on, above, or to the right of the appropriate Safe-Life Limit Curve, then its Safe-Life Limit has been reached and the component shall be removed from service.

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D. AIRWORTHINESS LIMITATIONS – SYSTEMS LIFE-LIMITED PARTS

The replacement times established for the life-limited parts result from Model 747-8/8F airplane certification activities with the U

Airworthiness Limitations section of the Instructions for Continued Airworthiness. These maintenance actions are mandatory. T

revised with the approval of the FAA Oversight Office.

1 The installation of a 030-22229-1 Assy – Aft Plug, Primary Exhaust on a GEnx-2B67/P Engine or Airplane Line Numbers 1483 and on is pro

 Type Certified Configuration.

2 Published life limits are applicable to primary exhaust assemblies installed on all 747-8F or 747-8 airplanes with any of the certified GEnx-2

 in FAA Type Certificate Data Sheet No. A20WE.

ITEM 

NUMBER LIFE-LIMITED PART PART NUMBER PART DESCRIPTION APPLICABILITY SPECIFICATIONS 

1 Hydraulic Control Module 734-19150-09 Inboard Trailing Edge Flap Power 

Drive Unit Hydraulic Control Module 

Applicable to all 747-8 and 747-8F Airplanes

2 Hydraulic Control Module 734-19150-10 Outboard Trailing Edge Flap Power 

Drive Unit Hydraulic Control Module 

Applicable to all 747-8 and 747-8F Airplanes

3 Assy – Primary Nozzle, 

Primary Exhaust 2

030-22132-1 Engine Primary Exhaust Nozzle Applicable to all 747-8 and 747-8F 

Airplanes

4 Assy – Fwd Plug, Primary 

Exhaust 2

030-22222-1 Engine Primary Exhaust Fwd Plug 

Assembly

Applicable to all 747-8 and 747-8F Airplanes

5 Assy – Aft Plug, Primary 

Exhaust 1

030-22229-1 Engine Primary Exhaust Aft Plug 

Assembly

Applicable to all 747-8 and 747-8F Airplanes

6 Assy – Aft Plug, Primary 

Exhaust 2

030-22229-3 Engine Primary Exhaust Aft Plug 

Assembly

Applicable to all 747-8 and 747-8F Airplanes

7 Light Assy, Anti-Collision and 

Position-Integrated Leading Edge – LH

0204544-101 Left Integrated Wingtip Light 

Assembly

Applicable to all 747-8 and 747-8F Airplanes

8 Light Assy, Anti-Collision and 

Position-Integrated Leading Edge – RH

0204544-102 Right Integrated Wingtip Light 

Assembly

Applicable to all 747-8 and 747-8F Airplanes

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E. AIRWORTHINESS LIMITATIONS – SYSTEMS

These System Airworthiness Limitations are a result of Model 747-8/8F airplane certification activities with the U.S. FAA and ar

Limitations section of the Instructions for Continued Airworthiness. These maintenance actions are mandatory. These Airworthbe revised with the approval of 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 establisper 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 endurance does not exceed each installed engine’s usable oil quantity, thereby preventing a common mode loss of all engine thr

fuel endurance is 24.93 flight hours and is calculated with the minimum crew, minimum equipment, no payload and the maximuwithout reserves. The engine oil consumption rate is normally calculated over a period of 10 to 20 flights by dividing the total quatotal number of flight hours; oil consumption calculations over 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 allow

permit authorized under Title14 CFR § 21.197 and § 21.199.

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SYSTEM 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 if 

center tank:a. After the next flight check for the presence of the ENG X FUEL STR EICAS Status message; interrogate the CMC to c

ENG-X FUEL STRAINER IMPENDING BYPASS OR BYPASSED 'COLLECTOR' message. Troubleshoot the source o

contamination if the messages are present.

b. Prior to accumulating 20 flight hours after fuel has been added to the center tank, or 2 flight cycles after fuel has been 

whichever comes later, perform the Main Fuel Pump Strainer Inspection/Check procedure on the right outboard engine 73-11-04-200-802-G00. Collect any material removed from the fuel pump strainer to troubleshoot the source of the fue

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 added to the center tank, or 4 flight cycles after fuel has been 

whichever comes later, perform the Main Fuel Pump Strainer Inspection/Check procedure on the left outboard engine 11-04-200-802-G00. Collect any material removed from the fuel pump strainer to troubleshoot the source of the fuel sy

flight cycle may be added to these limits in the event of an unscheduled landing.

If the ENG X FUEL STR EICAS status message or the ENG-X FUEL STRAINER IMPENDING BYPASS OR BYPASSED 'COL

present, or if abnormal or significant contamination is found on the fuel pump strainer, troubleshoot the source of the fuel system 

system contamination troubleshooting requires removal of the IDG Fuel/Oil Heat Exchanger per AMM 24-11-13, Task 24-11-13inspection 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 the f

a. After the next flight check for the presence of the ENG X FUEL STR EICAS status message, interrogate the CMC to c

ENG-X FUEL STRAINER IMPENDING BYPASS OR BYPASSED 'COLLECTOR' message. Troubleshoot the source ocontamination if the messages are present.

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b. Prior to accumulating 20 flight hours after fuel tank entry, or 2 flight cycles after fuel tank entry, whichever comes later, p

Strainer Inspection/Check procedure on the left inboard engine per AMM 73-11-04, Task 73-11-04-200-802-G00. Coll

from the fuel pump strainer to troubleshoot the source of the fuel system contamination. One flight cycle may be adde

of an unscheduled landing.

3. Following a right inboard main fuel tank purging and maintenance activity inside the right inboard main fuel tank, perform th

a. After the next flight check for the presence of the ENG X FUEL STR EICAS status message, interrogate the CMC to c

ENG-X FUEL STRAINER IMPENDING BYPASS OR BYPASSED 'COLLECTOR' message. Troubleshoot the source ocontamination 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, p

Strainer Inspection/Check procedure on the right inboard engine per AMM 73-11-04, Task 73-11-04-200-802-G00. Cofrom the fuel pump strainer to troubleshoot the source of the fuel system contamination. One flight cycle may be adde

of an unscheduled landing.

4. Operation of a Model 747-8/8F Series airplane after September 30, 2017 is prohibited unless a modification to provide indic

gross fuel contamination is installed in accordance with a method approved by the FAA Oversight Office. The FAA approva

this 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 

Venting is installed in accordance with a method approved by the FAA Oversight Office. The FAA approval must specifically reairworthiness limitation.

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SYSTEM 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 an airc

powerplant that occurs or is detected at any time if, in its opinion, that failure, malfunction, or defect has endangered or may endan aircraft”. Title 14 CFR § 125.409 also requires reporting of failures, malfunctions, or defects. In many cases a reportable faobvious, but there are some failure modes related to uncontrolled high thrust that are reportable but may not be obvious. The fprovided, as required by FAA Exemption No. 8518, to assist the operators in identifying reportable malfunctions related to uncoThe FAA has concluded that the loss of capability to control thrust due to a failure of the engine thrust control system may enda

includes any malfunctions having one or more of the following characteristics:• Stuck thrust lever above idle power.• No response to thrust lever, with the cause being a mechanical failure in the thrust lever mechanism or resolver.Although some of these incidents may not appear to be safety related, documenting the events is important to ensure the prese

maintained and/or to identify failure conditions that must be corrected. When filing a report of such an event with the FAA, the oinclude 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”

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In addition, the following information should be included in the report:• Event description• Flight Crew action• Maintenance action• List of affected or removed componentsReports should be submitted to the local representative of the FAA Administrator that handles the appropriate reporting respon§ 121.703, § 125.409, and § 135.415. In addition to filing reports with the FAA, it is recommended that a copy be sent to Boein

engine manufacturer.SYSTEM AIRWORTHINESS LIMITATION 5747-8/8F ENGINE OPERATING LIMITATION FOR ICE CRYSTAL ICINGFor GEnx-2B powered airplanes, following flight crew report of Engine Rollback, or ENG X THRUST EICAS Caution message in perform borescope of all HPC Stage 1 blade airfoils with borescope prior to the next revenue service flight for all affected engin

required 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 an

the engine variable bleed valve ice protection system is installed in accordance with a method approved by the FAA Oversight Office approval must specifically reference this airworthiness limitation.

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