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Commercial Airplanes 737 Requirements Bulletin ALERT Number: 737-24A1248 RB Original Issue: May 16, 2022 ATA System: 2400 SUBJECT: ELECTRICAL POWER - General - P6 Panel Bonding Jumper Installation 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 © 2022 Boeing.
Unpublished Work. All Rights Reserved.
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: May 16, 2022 737-24A1248 RB 1 of 17
2.0
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 16, 2022 737-24A1248 RB 2 of 17 REQUIREMENTS BULLETIN 737-24A1248
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Table of Contents
1. EFFECTIVITY5
A. Airplanes5
B. Spares Affected7
2. CONCURRENT REQUIREMENTS7
3. COMPLIANCE7
4. APPROVAL7
5. ACCOMPLISHMENT INSTRUCTIONS9
A. General Information9
B. Work Instructions10
FIGURE 1: FLIGHT COMPARTMENT - P6 PANEL BONDING JUMPERS - INSTALLATION12
Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 16, 2022 737-24A1248 RB 4 of 17 REQUIREMENTS BULLETIN 737-24A1248
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Commercial Airplanes 737 Requirements Bulletin ALERT Number: 737-24A1248 RB Original Issue: May 16, 2022 ATA System: 2400 SUBJECT: ELECTRICAL POWER - General - P6 Panel Bonding Jumper Installation
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 737-8, 737-9 Airplane(s), line number(s) 5602, 5668, 5788, 5852, 5902, 5948, 5992, 6034, 6074, 6114, 6154, 6188, 6222, 6272, 6290, 6308, 6326, 6344, 6360, 6372, 6384, 6396, 6408, 6420, 6430, 6441, 6448, 6456, 6464, 6472, 6481, 6490, 6499, 6508, 6515, 6521, 6528, 6535, 6542, 6548, 6555, 6562, 6569, 6575, 6582, 6589, 6594, 6598, 6603, 6607, 6612, 6616, 6621, 6625, 6630, 6634, 6639, 6643, 6648, 6652, 6657, 6661, 6666, 6672, 6677, 6681, 6686, 6690, 6695, 6699, 6704, 6708, 6713, 6717, 6722, 6726, 6731, 6735, 6740, 6749, 6753, 6758, 6762, 6767, 6771, 6776, 6780, 6783, 6785, 6789, 6792, 6794, 6796, 6803, 6805, 6807, 6810, 6814, 6816, 6819, 6821, 6825, 6828, 6830, 6834, 6837, 6839, 6841, 6843, 6848, 6850, 6852, 6855, 6859, 6861, 6864, 6866, 6868, 6872, 6875, 6877, 6881, 6884, 6886, 6890, 6893, 6895, 6897, 6899, 6904, 6906, 6908, 6911, 6915, 6917, 6920, 6922, 6926, 6929, 6931, 6935, 6938, 6940, 6942, 6944, 6949, 6951, 6953, 6956, 6960, 6963, 6965, 6968, 6970, 6973, 6975-6976, 6978, 6980, 6983, 6985, 6988, 6990-6991, 6993, 6995, 6998, 7000, 7003, 7005-7006, 7008, 7010, 7013, 7015, 7018, 7020, 7023, 7025, 7027-7028, 7030, 7033, 7035, 7038, 7040, 7042-7043, 7045, 7048, 7050, 7053, 7055, 7060, 7062, 7064-7065, 7068, 7070, 7073, 7075, 7077, 7079-7080, 7083, 7085, 7088, 7090, 7093, 7095-7096, 7098, 7100, 7103, 7105, 7108, 7110-7111, 7113, 7115, 7118, 7120, 7123, 7125, 7128, 7130, 7132-7133, 7135, 7138, 7140, 7143, 7145, 7147-7148, 7150, 7153, 7155, 7158, 7160, 7163, 7165-7166, 7168, 7170, 7173, 7175, 7178, 7180-7181, 7183, 7185-7186, 7188, 7190, 7192-7193, 7195-7196, 7198, 7200-7201, 7203, 7205, 7207-7208, 7210-7211, 7213, 7215-7216, 7218, 7220, 7222-7223, 7225-7226, 7228, 7230-7231, 7233, 7236-7238, 7240-7241, 7245-7246, 7248, 7250, 7252-7253, 7255-7256, 7258, 7261, 7265, 7267-7268, 7270-7271, 7275-7276, 7278, 7281-7283, 7286, 7288, 7290-7291, 7293, 7295-7296, 7298, 7300-7301, 7303, 7305-7306, 7308, 7310-7311, 7313, 7315-7316, 7320-7321, 7323, 7328, 7330-7331, 7333, 7335-7336, 7338, 7340-7341, 7343, 7348, 7350, 7353, 7355-7356, 7358, 7360-7361, 7363, 7365-7366, 7368, 7370, 7373, 7375, 7378, 7380-7381, 7383-7386, 7388-7390, 7393-7395, 7398-7401, 7403-7406, 7409-7411, 7413-7414, 7416, 7419, 7421, 7423 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.
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Original Issue: May 16, 2022 737-24A1248 RB 5 of 17
The Variable Numbers and Group Information for the applicable airplanes is given below.
DESCRIPTIONCONFIGURATIONGROUP 737-8, 737-9 Airplanes with a single ground strap installed between the P6 Panel and the primary structure.
-1 Airplane Models:
737-8, 737-9 GroupVariable Number 11A001 - 1A002 11A004 - 1A035 11A201 - 1A209 11A211 11A301 - 1A318 11A401 - 1A413 11A451 - 1A467 11A476 - 1A482 11A501 - 1A502 11A521 - 1A523 11A531 11A541 - 1A545 11A601 - 1A614 11A676 - 1A691 11A726 - 1A730 11A741 - 1A743 11A751 - 1A757 11A801 11A851 - 1A865 11A916 - 1A919 11A926 - 1A929 11A943 11A951 - 1A956 11B001 - 1B012 GroupVariable Number 11B101 - 1B124 11B201 - 1B206 11B251 - 1B266 11B376 - 1B380 11B386 - 1B389 11B396 11B401 11B491 - 1B494 11B511 - 1B512 11B521 - 1B522 11B531 11B540 - 1B541 11B566 - 1B569 11B576 - 1B578 11B601 11B635 - 1B636 11B651 - 1B657 11B701 11B801 - 1B806 11B930 - 1B934 11C001 - 1C002 11C201 - 1C202 11C221 11C301 - 1C303 GroupVariable Number 11C326 - 1C335 11C401 - 1C404 11C451 11C453 11C501 - 1C510 11C690 11C701 - 1C711 11C826 - 1C827 11C946 - 1C947 11D002 - 1D004 11D051 - 1D056 11D101 - 1D113 11D201 11D251 - 1D253 11D401 11D466 11J021 11J041 - 1J042 11J066 - 1J067 11J101 - 1J102 11J301 11J401 - 1J402 11J601 -- B. Spares Affected Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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None.
2. CONCURRENT REQUIREMENTS None.
3. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to Requirements Bulletin 737-24A1248 RB. The Airworthiness Directive will make the compliance tasks and times given in Requirements Bulletin 737-24A1248 RB mandatory.
Accomplish the required action(s), based on the applicable condition(s) in Table 1 in accordance with Accomplishment Instructions.
Table 1: P6 Panel Bonding Jumper Installation Repeat Interval (Not to Exceed) Boeing Recommended Compliance Time ActionCondition -Within 3 years after the Original Issue date of Requirements Bulletin 737- 24A1248 RB.
Install two bonding jumpers from the P6 panel structure to the primary structure.
All Airplanes
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)/Joint Aviation Authorities (JAA) approved for all EASA/JAA 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.
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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. 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. 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 737 Structural Repair Manual, Chapter 51.
— Values for airframe maintenance tasks are included in Chapter 20 of 737 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 737 Aircraft Maintenance Manual (AMM).
— Non-standard torque values for maintenance tasks are included in the applicable installation step.
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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.
8. Use the approved fastener, process and material substitutions in accordance with SRM Chapter 51.
9. Torque Values: Apply torque to self-locking nut to the applicable value. If the self locking nut is not accessible, it is permitted to torque the fastener head to applicable value. If the terminal or jumper rotates when applying torque to the self-locking nut, hold the self-locking nut with a wrench and apply torque to the fastener head.
10. For Bonding Jumper installations: The terminal lug of the bonding jumper may be adjusted by clocking to make sure the bonding jumper does not contact edges or corners of structure, wiring, system elements and equipment, unless otherwise defined.
11. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures.
12. The necessary conditions for selection of clamp type and size are included in SWPM 20-10-12. If any wire bundle support clamp specified in this service bulletin does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select a clamp that fits correctly.
13. 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. 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.
B. WORK INSTRUCTIONS Actions Required for Compliance
1. Requirements:
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Original Issue: May 16, 2022 737-24A1248 RB 10 of 17 REQUIREMENTS BULLETIN 737-24A1248
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Table 1: P6 Panel Bonding Jumper Installation Refer to the listed procedures in SB 737-24A1248 Original Issue or later approved revisions as an accepted procedure.
Method of ComplianceActionCondition PART 1: P6 Panel Open Access.-Install two bonding jumpers from the P6 panel structure to the primary structure.
All Airplanes -FIGURE 1 PART 2: P6 Panel Close Access.- Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details.
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REQUIREMENTS BULLETIN 737-24A1248
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FLIGHT COMPARTMENT (LOOKING AFT) FWD 2982721 FIGURE 1: FLIGHT COMPARTMENT - P6 PANEL BONDING JUMPERS - INSTALLATION (SHEET 1 OF 6) Original Issue: May 16, 2022 737-24A1248 RB Export Controlled ECCN: 9E991 Copyright © Unpublished Work - See page 1 for details. 12 of 17