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Commercial BOEING Airplanes 767 Requirements Bulletin
- ALERT Number: 767-53A0337 RB Original Issue: October 17, 2025 ATA System: 5301 2557 SUBJECT: FUSELAGE - Floor - Cargo Track Crown Fittings 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.
ECCN: 9E991 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: October 17, 2025 767-53A0337 RB 1 of 65
3.0
REQUIREMENTS BULLETIN 767-53A0337
ALERT ALERT
BLANK PAGE Original Issue: October 17, 2025 Export Controlled ECCN: 9E991 67-53A0337 RE See page 1 for details • ot 65
REQUIREMENTS BULLETIN 767-53A0337
ALERT ALERT Table of Contents
1. EFFECTIVITY 5 A. Airplanes 5 B. Spares Affected 5
2. CONCURRENT REQUIREMENTS . 6 COMPLIANCE 6
4. APPROVAL 8
5. ACCOMPLISHMENT INSTRUCTIONS 9 A. General Information . 9 B. Work Instructions 10 FIGURE 1: FUSELAGE - SECTION 43 - ALL CARGO TRACK CROWN FITTINGS REPLACEMENT 13 FIGURE 2: FUSELAGE - SECTION 43 - CARGO TRACK CROWN FITTINGS INSPECTION 24 FIGURE 4: FUSELAGE - SECTION 43 - AFFECTED CARGO TRACK CROWN FITTINGS REPLACEMENT 26 FIGURE 5: FUSELAGE - SECTION 46 - ALL CARGO TRACK CROWN FITTINGS REPLACEMENT . 37 FIGURE 6: FUSELAGE - SECTION 46 - CARGO TRACK CROWN FITTINGS INSPECTION . 47 FIGURE 8: I FUSELAGE - SECTION 46 - AFFECTED CARGO TRACK CROWN FITTINGS REPLACEMENT 49 APPENDIX A: PROCEDURE FOR X-RAY FLUORESCENCE INSPECTION . 60 Original Issue: October 17, 2025 767-53A0337 RB Export Controlled ECCN: 9E991 See page 1 for details 3 of 65
REQUIREMENTS BULLETIN 767-53A0337
ALERT ALERT
BLANK PAGE Original Issue: October 17, 2025 Export Controlled ECCN: 9E991 767-53A0337 RB See page 1 for details 4 of 65
Commercial A BOEING Airplanes 767 Requirements Bulletin
• ALERT Number: 767-53A0337 RB Original Issue: October 17, 2025 ATA System: 5301 2557 SUBJECT: FUSELAGE - Floor - Cargo Track Crown Fittings Inspection and Replacement
THIS DOCUMENT IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN 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 767-300F Airplane(s), line number(s) 1206, 1208-1209, 1211-1212, 1214-1215, 1217-1218, 1220-1222, 1224-1225, 1227-1229, 1231-1233, 1235, 1237, 1239-1240, 1242, 1244-1245, 1247, 1249, 1251, 1253, 1255-1256, 1258, 1260, 1262-1263, 1265-1266, 1268, 1270, 1272, 1274, 1276, 1278-1279 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.
The Variable Numbers and Group Information for the applicable airplanes is given below.
GROUP CONFIGURATION DESCRIPTION 1 767-300F Airplanes.
Airplane Models:
767-300F Variable Number Group Variable Number Group Variable Number Group VR299 - VR305 VT638 - VT671 1 VT731 - VT735 1 B. Spares Affected Original Issue: October 17, 2025 Export Controlled ECCN: 9E991 767-53A0337 RB See page 1 for details 5 of 65
REQUIREMENTS BULLETIN 767-53A0337
ALERT ALERT Examine spares supply for the parts or components identified below. If any parts or components are found, refer to Work Instructions for the recommended action.
Part Number Name 146T5223-4 FITTING-TRACK CROWN 146T5223-5 FITTING-TRACK CROWN 146T5223-6 FITTING-TRACK CROWN
2. CONCURRENT REQUIREMENTS None.
3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Requirements Bulletin 767-53A0337 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 767-53A0337 RB mandatory.
Accomplish the required action(s), based on the applicable condition(s) in Table 1 and Table 2, 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: Fuselage - Section 43 - Cargo Track Crown Fitting Inspection and Replacement Condition Action Boeing Recommended Repeat Interval (Not to Compliance Time Exceed) All Airplanes OPTION 1: Replace all Within 24 months after the Cargo Track Crown Fit- Original Issue date of Retings with new Cargo Track quirements Bulletin 767- Crown Fittings (Ti-6Al-4V 53A0337 RB.
alloy material).
OPTION 2: Do an X-Ray Within 24 months after the - Fluorescence (XRF) in- Original Issue date of Respection to identify the quirements Bulletin 767- material composition of the 53A0337 RB.
Cargo Track Crown Fittings.
CONDITION 1: ANY CAR- No further action required. -
GO TRACK CROWN FIT-
TING FOUND THAT HAS
A MATERIAL COMPOSI-
TION CONSISTENT WITH Ti-6AI-4V.
Original Issue: October 17, 2025 Export Controlled ECCN: 9E991 767-53A0337 RB See page 1 for details 6 of 65
REQUIREMENTS BULLETIN 767-53A0337
ALERT ALERT Table 1: Fuselage - Section 43 - Cargo Track Crown Fitting Inspection and Replacement Condition Action Boeing Recommended Repeat Interval (Not to Compliance Time Exceed) CONDITION 2: ANY CAR- Replace the affected Car- Before further flight.
GO TRACK CROWN FIT- go Track Crown Fitting TING FOUND THAT with a new Cargo Track DOES NOT HAVE A MA- Crown Fitting (Ti-6A1-4V TERIAL COMPOSITION alloy material).
CONSISTENT WITH Ti- 6AI-4V OR MATERIAL
CANNOT BE DETER- MINED.
Table 2: Fuselage - Section 46 - Cargo Track Crown Fitting Inspection and Replacement Condition Action Boeing Recommended Repeat Interval (Not to Compliance Time Exceed) All Airplanes OPTION 1: Replace all Within 24 months after the Cargo Track Crown Fit- Original Issue date of Retings with new Cargo Track quirements Bulletin 767- Crown Fittings (Ti-6Al-4V 53A0337 RB.
alloy material).
OPTION 2: Do an X-Ray Within 24 months after the Fluorescence (XRF) in- Original Issue date of Respection to identity the quirements Bulletin 767- material composition of the 53A0337 RB.
Cargo Track Crown Fittings.
CONDITION 3: ANY CAR- No further action required. -
GO TRACK CROWN FIT-
TING FOUND THAT HAS
A MATERIAL COMPOSI-
TION CONSISTENT WITH Ti-6AI-4V.
CONDITION 4: ANY CAR- Replace the affected Car- Before further flight.
GO TRACK CROWN FIT- go Track Crown Fitting TING FOUND THAT with a new Cargo Track DOES NOT HAVE A MA- Crown Fitting (Ti-6Al-4V TERIAL COMPOSITION alloy material).
CONSISTENT WITH Ti- 6AI-4V OR MATERIAL
CANNOT BE DETER- MINED.
Original Issue: October 17, 2025 Export Controlled ECCN: 9E991 See page 1 for details 767-53A0337 RB 7 of 65
REQUIREMENTS BULLETIN 767-53A0337
ALERT ALERT
4. APPROVAL This Requirements Bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this document comply with the applicable regulations and are FAA approved, as well as European Union Aviation Safety Agency (EASA) approved for all EASA approved airplanes listed in this Requirements Bulletin effectivity. This document and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other Boeing changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this Requirements Bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this Requirements Bulletin.
Original Issue: October 17, 2025 767-53A0337 RB Export Controlled ECCN: 9E991 See page 1 for details 8 of 65
REQUIREMENTS BULLETIN 767-53A0337
ALERT ALERT
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 locations are marked RC Start and RC End to identify the requirements that are are not required by the AD and are for guidance only. For the related SB, some ested on the fa. for he ate c 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. 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 and fasteners are in Structural Repair Manual (SRM) Chapter 51
- Torque Values:
- Values for structural fasteners are given in 767 Structural Repair Manual, Chapter 51.
- Values for airframe maintenance tasks are included in Chapter 20 of 767 Aircraft Maintenance Manual (AMM).
— Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring Practices Manual (SWPM).
- Non-standard torque values for maintenance tasks are included in the applicable installation step.
Original Issue: October 17, 2025 Export Controlled ECCN: 9E991 767-53A0337 RB See page 1 for details 9 of 65
REQUIREMENTS BULLETIN 767-53A0337
ALERT ALERT
5. 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.
6. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part.
7. 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.
Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51.
9. 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.
10. The instructions in Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools.
11. If the length of any fastener specified in this service bulletin does not meet installation standards given in 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. Refer to SOPM 20-50-01 for ADJUSTMENT OF GRIP LENGTH and USE OF WASHERS as an accepted procedure.
12. Some Boeing parts are supplied in a temporary configuration. Those parts are identified with a 'U, 'W', or 'Y' in place of the '"' (dash) in the part number. It is permitted to install parts identified with a 'U', 'W', or 'Y' as an alternative to the '' (dash) part number. Boeing Drawing 005W0900 contains more data.
13. Use of colors in Figures is based on guidance from the ATA e-Business Program (ATA) iSpec 2200.
B. WORK INSTRUCTIONS Actions Required for Compliance
1. Requirements Original Issue: October 17, 2025 767-53A0337 RB Export Controlled ECCN: 9E991 See page 1 for details 10 of 65
REQUIREMENTS BULLETIN 767-53A0337
ALERT ALERT Table 1: Fuselage - Section 43 - Cargo Track Crown Fittings Inspection and Replacement Condition Action Method of Compliance Refer to the listed procedures in SB 767-53A0337 Original Issue or later approved revisions as an accepted procedure.
All Airplanes OPTION 1: Replace all Do PART 1: OPEN AC- Cargo Track Crown Fit- CESS tings with new Cargo Track Do PART 3: CARGO Crown Fittings (Ti-6Al-4V TRACK CROWN FITTING alloy material). ACCESS FIGURE 1 Do PART 4: CLOSE AC- CESS OPTION 2: Do an X-Ray Do PART 1: OPEN AC- Fluorescence (XRF) in- CESS spection to identity the FIGURE 2 material composition of the Cargo Track Crown Fittings.
CONDITION 1: ANY CAR- No further action required. - Do PART 2: APPLY CAR-
GO TRACK CROWN FIT- GO TRACK CROWN FIT-
TING FOUND THAT HAS TING FINISH
A MATERIAL COMPOSI- Do PART 4: CLOSE AC-
TION CONSISTENT WITH CESS Ti-6AI-4V.
CONDITION 2: ANY CAR- Replace the affected Car- Do PART 3: CARGO GO TRACK CROWN FIT- go Track Crown Fitting TRACK CROWN FITTING TING FOUND THAT with a new Cargo Track ACCESS DOES NOT HAVE A MA- Crown Fitting (Ti-6Al-4V FIGURE 4 TERIAL COMPOSITION alloy material).
CONSISTENT WITH Ti- Do PART 4: CLOSE AC- 6AI-4V OR MATERIAL CESS
CANNOT BE DETER- MINED.
Original Issue: October 17, 2025 Export Controlled ECCN: 9E991 767-53A0337 RB See page 1 for details 11 of 65
REQUIREMENTS BULLETIN 767-53A0337
ALERT ALERT Table 2: Fuselage - Section 46 - Cargo Track Crown Fittings Inspection and Replacement Condition Action Method of Compliance Refer to the listed procedures in SB 767-53A0337 Original Issue or later approved revisions as an accepted procedure.
All Airplanes OPTION 1: Replace all Do PART 1: OPEN AC- Cargo Track Crown Fit- CESS tings with new Cargo Track Do PART 3: CARGO Crown Fittings (Ti-6Al-4V TRACK CROWN FITTING alloy material). ACCESS FIGURE 5 Do PART 4: CLOSE AC- CESS OPTION 2: Do an X-Ray Do PART 1: OPEN AC- Fluorescence (XRF) in- CESS spection to identify the FIGURE 6 material composition of the Cargo Track Crown Fittings.
CONDITION 3: ANY CAR- No further action required - Do PART 2: APPLY CAR-
GO TRACK CROWN FIT- GO TRACK CROWN FIT-
TING FOUND THAT HAS TING FINISH
A MATERIAL COMPOSI- Do PART 4: CLOSE AC-
TION CONSISTENT WITH CESS Ti-6AI-4V.
CONDITION 4:ANY CAR- Replace the affected Car- Do PART 3: CARGO GO TRACK CROWN FIT- go Track Crown Fitting TRACK CROWN FITTING TING FOUND THAT with a new Cargo Track ACCESS DOES NOT HAVE A MA- Crown Fitting (Ti-6Al-4V FIGURE 8 TERIAL COMPOSITION alloy material).
CONSISTENT WITH Ti- Do PART 4: CLOSE AC- 6AI-4V OR MATERIAL CESS
CANNOT BE DETER- MINED.
Original Issue: October 17, 2025 Export Controlled ECCN: 9E991 767-53A0337 RB See page 1 for details 12 of 65