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Commercial Airplanes 717 Requirements Bulletin ALERT Number: 717-32A0043 RB Original Issue: February 12, 2025 ATA System: 3222 3221 SUBJECT: LANDING GEAR - Braces and Attachments - Nose Landing Gear Upper Lock Link Assembly Inspection and Replacement EXPORT CONTROLLED - This technology or software is subject to the U.S. Export Administration Regulations (EAR), (15 C.F.R. Parts 730-774). No authorization from the U.S. Department of Commerce is required for export, re-export, in-country transfer, or access EXCEPT to country group E:1 or E:2 countries/persons per Supp.1 to Part 740 of the EAR.
9E991ECCN:
Copyright © 2025 The Boeing Company Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.
Original Issue: February 12, 2025 717-32A0043 RB 1 of 15
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Export Controlled ECCN: 9E991 See page 1 for details Original Issue: February 12, 2025 717-32A0043 RB 2 of 15 REQUIREMENTS BULLETIN 717-32A0043
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Table of Contents
1. EFFECTIVITY5
A. Airplanes5
B. Spares Affected5
2. CONCURRENT REQUIREMENTS6
3. COMPLIANCE6
4. APPROVAL7
5. ACCOMPLISHMENT INSTRUCTIONS9
A. General Information9
B. Work Instructions10
FIGURE 1: NOSE LANDING GEAR - UPPER LOCK LINK ASSEMBLY - EDDY CURRENT HIGH
FREQUENCY (ETHF) INSPECTION13
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: February 12, 2025 717-32A0043 RB 3 of 15 REQUIREMENTS BULLETIN 717-32A0043
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Export Controlled ECCN: 9E991 See page 1 for details Original Issue: February 12, 2025 717-32A0043 RB 4 of 15 REQUIREMENTS BULLETIN 717-32A0043
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Commercial Airplanes 717 Requirements Bulletin ALERT Number: 717-32A0043 RB Original Issue: February 12, 2025 ATA System: 3222 3221 SUBJECT: LANDING GEAR - Braces and Attachments - Nose Landing Gear Upper Lock Link Assembly Inspection and Replacement
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS DOCUMENT TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS DOCUMENT TO THE NEW OWNER. THIS IS AN ENHANCED REQUIRED FOR COMPLIANCE DOCUMENT. THE BOEING
PROCESSES USED TO CREATE THE SERVICE BULLETIN (SB) AND THE REQUIREMENTS BULLETIN (RB) ENSURE THAT THE INFORMATION BETWEEN "RC START" AND "RC END" IN THE SB ARE IDENTICAL TO THE INFORMATION IN THE SAME SECTIONS (COMPLIANCE, WORK INSTRUCTIONS…) OF THE RB WHICH THE SB REFERS TO AS THE RELATED DOCUMENT.
1. Effectivity A. Airplanes This bulletin is applicable to 717-200 Airplane(s), line number(s) 5002-5156 in 1 Group(s). Where the effectivity is presented with hyphens between line numbers, the airplane applicability means "through" and "inclusive", e.g. line numbers 1-9 means line numbers 1 through 9 inclusive.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP All 717-200 airplanes.-1 Airplane Models:
717-200 GroupFuselage Number 15002 - 5156 GroupFuselage Number -- GroupFuselage Number -- B. Spares Affected Examine your spares supply for the parts or components identified below. If any parts or components are found, refer to Accomplishment Instructions for the recommended action.
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: February 12, 2025 717-32A0043 RB 5 of 15
Name/DescriptionPart Number LINK ASSY-UPPER LOCK3914464-505 LINK ASSY-UPPER LOCK3914464-505V LINK ASSY-UPPER LOCK3914464-509 LINK ASSY-UPPER LOCK3914464-509V
2. CONCURRENT REQUIREMENTS None.
3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Requirements Bulletin 717-32A0043 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 717-32A0043 RB mandatory.
Accomplish the required action(s), based on the applicable condition(s) in Table 1, in accordance with Accomplishment Instructions.
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION or an OPTION, do all of the ACTION numbers for that CONDITION or OPTION.
Table 1: Nose Landing Gear - Upper Lock Link Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time ActionCondition -Within 1,200 Upper Lock Link assembly flight cycles after the Original Issue date of Requirements Bulletin 717- 32A0043 RB.
OPTION 1:
Do an Eddy Current High Frequency (ETHF) inspection of the Upper Lock Link assembly for any crack.
All airplanes with an Upper Lock Link assembly that has not been overhauled, as of the Original Issue date of Requirements Bulletin 717-32A0043 RB, in accordance with OHM 32- 21-2, Revision No. 63 dated July 01, 2024 or later Boeing approved revisions published on New Maintenance Performance Toolbox (nMPT).
OPTION 2:
Replace the Upper Lock Link assembly with a serviceable Upper Lock Link assembly.
(a) Export Controlled ECCN: 9E991 See page 1 for details Original Issue: February 12, 2025 717-32A0043 RB 6 of 15 REQUIREMENTS BULLETIN 717-32A0043
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Table 1: Nose Landing Gear - Upper Lock Link Assembly Inspection and Replacement Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time ActionCondition --No further action is required.All airplanes with an Upper Lock Link assembly that has been overhauled, as of the Original Issue date of Requirements Bulletin 717- 32A0043 RB, in accordance with OHM 32-21-2, Revision No. 63 dated July 01, 2024 or later Boeing approved revisions published on New Maintenance Performance Toolbox (nMPT).
-Before further flight.Replace the Upper Lock Link assembly with a serviceable Upper Lock Link assembly.
(a) CONDITION 1:
ANY CRACK FOUND AS A RESULT OF OPTION 1
ETHF INSPECTION 4,800 Upper Lock Link assembly flight cycles.
-CONDITION 2 (OPTION 1):
Repeat the ETHF inspection of the Upper Lock Link assembly for any crack. (b) CONDITION 2:
NO CRACK FOUND AS A RESULT OF OPTION 1
ETHF INSPECTION -Before further flight.CONDITION 2 (OPTION 2):
Replace the Upper Lock Link assembly with a serviceable Upper Lock Link assembly.
(a)
(a) A serviceable Upper Lock Link assembly is defined as one that has been overhauled in accordance with OHM 32-21-2, Revision No. 63 dated July 01, 2024 or later Boeing approved revisions published on New Maintenance Performance Toolbox (nMPT).
(b) Replacement of the Upper Lock Link assembly with a serviceable Upper Lock Link assembly is the terminating action to the repeat ETHF inspection.
4. APPROVAL This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin.
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: February 12, 2025 717-32A0043 RB 7 of 15 REQUIREMENTS BULLETIN 717-32A0043
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5. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION NOTE: 1. This is an Enhanced Required for Compliance document. There will be a separate Service Bulletin (SB) and a separate Requirements Bulletin (RB). If an RB is mandated by an Airworthiness Directive (AD), then all applicable requirements specified in the RB must be done. In the RB, the "Refer to the listed procedures..." column of the table(s) in the Work Instructions is for reference only. The procedures in that column are not required by the AD and are for guidance only. For the related SB, some locations are marked RC Start and RC End to identify the requirements that are restated from the RB. For the related SB, the areas between RC Start and RC End, including sub-steps and any figures identified between RC Start and RC End, must be done to comply with the AD. Therefore, an Alternative Method of Compliance (AMOC) is required for any deviations to steps between RC Start and RC End, including substeps and identified figures. For the related SB, the steps not between RC Start and RC End may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC; this is provided that the steps between RC Start and RC End, including sub-steps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. Figures not required for compliance are omitted from the RB.
2. This is an Enhanced Required for Compliance document. The Boeing processes used to create the Service Bulletin (SB) and the Requirements Bulletin (RB) ensure that the information between "RC Start" and "RC End" in the SB are identical to the information in the same sections (Compliance, Work Instructions...) of the RB which the SB refers to as the related document.
3. The compliance times for the actions in WORK INSTRUCTIONS are in Compliance.
4. Use the approved fastener and process material substitutions, in accordance with 717 Structural Repair Manual (SRM) Chapter 51.
5. If the length of any fastener specified in this service bulletin does not meet installation standards given in Structural Repair Manual (SRM) Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. Refer to SOPM 20-50-01 for alternate full threaded fasteners (screws) needed for installation in this service bulletin.
6. Unless shown differently, these dimensions and tolerances are used:
– Linear dimensions are in inches – Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch.
– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch – Angular tolerance is plus or minus 2 degrees – Hole dimensions for standard solid rivets are in SRM Chapter 51.
– Torque Values:
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: February 12, 2025 717-32A0043 RB 9 of 15 REQUIREMENTS BULLETIN 717-32A0043
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— Values for structural fasteners are given in 717 Structural Repair Manual, Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 717 Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM).
— Values for engine maintenance tasks are included in Chapter 70 of 717 Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the applicable installation step.
7. These work instructions refer to procedures included in other Boeing documents.
When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "in accordance with" are included in the instruction, the procedure in the Boeing document must be used.
8. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed.
9. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200.
10. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When more than one ACTION is given for a CONDITION or an OPTION, do all of the ACTION numbers for that CONDITION or OPTION.
B. WORK INSTRUCTIONS Actions Required for Compliance
1. Requirements Export Controlled ECCN: 9E991 See page 1 for details Original Issue: February 12, 2025 717-32A0043 RB 10 of 15 REQUIREMENTS BULLETIN 717-32A0043
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Table 1: Nose Landing Gear - Upper Lock Link Assembly Inspection and Replacement Refer to the listed procedures in SB 717-32A0043 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition PART 1: PREPARATION-OPTION 1:All airplanes with an Upper Lock Link assembly that has not been overhauled, as of the Original Issue date of Requirements Bulletin 717-32A0043 RB, in accordance with OHM 32- 21-2, Revision No. 63 dated July 01, 2024 or later Boeing approved revisions published on New Maintenance Performance Toolbox (nMPT).
Do an Eddy Current High Frequency (ETHF) inspection of Upper Lock Link assembly for any crack.
-FIGURE 1 PART 1: PREPARATION-OPTION 2:
Replace the Upper Lock Link assembly with a serviceable Upper Lock Link assembly. (a) PART 2: UPPER LOCK
LINK ASSEMBLY RE- MOVAL - PART 3: UPPER LOCK
LINK ASSEMBLY INSTAL- LATION - PART 4: RESTORATION- --No further action is required.All airplanes with an Upper Lock Link assembly that has been overhauled, as of the Original Issue date of Requirements Bulletin 717- 32A0043 RB, in accordance with OHM 32-21- 2, Revision No. 63 dated July 01, 2024 or later Boeing approved revisions published on New Maintenance Performance Toolbox (nMPT).
PART 2: UPPER LOCK
LINK ASSEMBLY RE- MOVAL -Replace the Upper Lock Link assembly with a serviceable Upper Lock Link assembly. (a) CONDITION 1:
ANY CRACK FOUND
AS A RESULT OF OP- TION 1 ETHF INSPEC- TION PART 3: UPPER LOCKLINK ASSEMBLY INSTAL- LATION - PART 4: RESTORATION- Export Controlled ECCN: 9E991 See page 1 for details Original Issue: February 12, 2025 717-32A0043 RB 11 of 15 REQUIREMENTS BULLETIN 717-32A0043
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Table 1: Nose Landing Gear - Upper Lock Link Assembly Inspection and Replacement Refer to the listed procedures in SB 717-32A0043 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition PART 1: PREPARATION-CONDITION 2 (OPTION 1):CONDITION 2:
NO CRACK FOUND AS
A RESULT OF OPTION 1 ETHF INSPECTION Repeat the ETHF inspection of Upper Lock Link assembly for any crack. (b) -FIGURE 1 PART 2: UPPER LOCK
LINK ASSEMBLY RE- MOVAL -CONDITION 2 (OPTION 2):
Replace the Upper Lock Link assembly with a serviceable Upper Lock Link assembly. (a) PART 3: UPPER LOCK
LINK ASSEMBLY INSTAL- LATION - PART 4: RESTORATION-
(a) A serviceable Upper Lock Link assembly is defined as one that has been overhauled in accordance with OHM 32-21-2, Revision No. 63 dated July 01, 2024 or later Boeing approved revisions published on New Maintenance Performance Toolbox (nMPT).
(b) Replacement of the Upper Lock Link assembly with a serviceable Upper Lock Link assembly is the terminating action to the repeat ETHF inspection.
Export Controlled ECCN: 9E991 See page 1 for details Original Issue: February 12, 2025 717-32A0043 RB 12 of 15 REQUIREMENTS BULLETIN 717-32A0043