# Boeing Alert Requirements Bulletin 737-24A1248 RB: No revision named

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- Title as filed: RB-737-24A1248-00
- Pages: 17
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### Page 1

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Unpublished Work.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
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2.0

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### Page 3

Table of Contents
1. EFFECTIVITY . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5
B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
2. CONCURRENT REQUIREMENTS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
3. COMPLIANCE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
4. APPROVAL . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7
5. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
A. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9
B. Work Instructions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10
FIGURE 1: FLIGHT COMPARTMENT - P6 PANEL BONDING JUMPERS - INSTALLATION . . . . . 12
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Export Controlled ECCN: 9E991
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### Page 5

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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### Page 6

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
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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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Table 1: P6 Panel Bonding Jumper Installation
Refer to the listed procedures in
SB 737-24A1248 Original Issue or
later approved revisions as an ac-
cepted 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.-
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### Page 12 (OCR)

REQUIREMENTS BULLETIN 737-24A1248
ALERT  ALERT
FLIGHT COMPARTMENT
(LOOKING AFT)
FWD
2982721
FIGURE 1: FLIGHT COMPARTMENT - P6 PANEL BONDING JUMPERS - INSTALLATION
(SHEET 1 OF 6)
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### Page 13 (OCR)

REQUIREMENTS BULLETIN 737-24A1248
ALERT  ALERT
EXISTING
GROUND
STUD
INBD
35°
EXISTING  25°
GROUND
STUD  LOOKING DOWN
WASHER  NUT  A-A
LUG
WASHER
LUG
WASHER
EXISTING -  2982789
PANEL  B-B
STRUCTURE
FIGURE 1: FLIGHT COMPARTMENT - P6 PANEL BONDING JUMPERS - INSTALLATION
(SHEET 2 OF 6)
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### Page 14 (OCR)

REQUIREMENTS BULLETIN 737-24A1248
ALERT  ALERT
1.81
1.31
$2.66
2.16
LOOKING INBOARD
C-C
GROUND
EXISTING  STUD
PANEL
STRUCTURE  WASHER
WASHER
→ LUG
WASHER
— NUT
D-D  2982794
FIGURE 1: FLIGHT COMPARTMENT - P6 PANEL BONDING JUMPERS - INSTALLATION
(SHEET 3 OF 6)
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### Page 15

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY
numbers shown below are the number of parts necessary for each airplane.
More DataQtyIdentificationNameTaskStep
THIS STEP IS NOT
SHOWN. BENCH
WORK. (a)
2BACJ40AP30-13
(BACJ40AP30-14 or
BACJ40A30-13 or
BACJ40A30-14 option-
al)
JUMPER ASSYGet1
(a)1280A3172-10101INSULATION SLEEV-
ING
Install (New)
(a)(b)30BACS38W2
(BACS38W1 or
BACS38W3 or
BACS38K1 or
BACS38K10 or
BMS13-54, TYPE III,
CLASS 2, FINISH C
optional)
STRAPInstall (New)
0.279-0.291 inch di-
ameter
1-HOLEDrill2
(c)2-Prepare surfacesClean3
2BACJ40AP30-13
(BACJ40AP30-14 or
BACJ40A30-13 or
BACJ40A30-14 option-
al)
JUMPER ASSYInstall (New)4
(d)1BACS12GU4K12SCREWInstall (New)5
Install under screw
head.
1NAS1149D0416HWASHER, FLATInstall (New)
Install under terminal
lug.
1NAS1149D0416HWASHER, FLATInstall (New)
Install between termi-
nal lugs.
2NAS1149D0463HWASHER, PLAINInstall (New)
Install under nut.1NAS1149D0416HWASHER, FLATInstall (New)
(d)1BACN10YR4CDNUTInstall (New)
FIGURE 1: FLIGHT COMPARTMENT - P6 PANEL BONDING JUMPERS - INSTALLATION
(SHEET 4 OF 6)
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More DataQtyIdentificationNameTaskStep
Install under lower
terminal lug.
1NAS1149D0463HWASHER, PLAINInstall (New)6
Install between termi-
nal lugs.
1NAS1149D0463HWASHER, PLAINInstall (New)
Install under nut.1NAS1149D0416HWASHER, FLATInstall (New)
(e)(f)1BACN10YR4CDNUTInstall (New)
(g)2BACS38K11
(BACS38K12 or
BACS38K5 optional)
STRAPInstall (New)7
(h)2-RESISTANCEMeasure8
(i)1 Oz-TOUCH-UP FINISHApply9
(a) 1. Cut the insulation sleeving to the length necessary to cover each bonding jumper.
For insulated bonding jumper: Make sure that the insulation sleeving makes a minimum overlap of 0.10
inch on the black moisture sleeve on each terminal lug.
For non-insulated bonding jumper: Make sure that the insulation sleeving is not installed more than 0.25
inch from each terminal crimp barrel.
2. Cut the insulation sleeving along the length of the material.
3. Wrap the insulation sleeving around the bonding jumper cable. Make sure that the cut edge of the in-
sulation sleeving makes a minimum overlap of 50 percent of the circumference of the bonding jumper.
4. Install straps or lacing tape on the Teflon Sleeve at 2.0 +/- 0.25 inch intervals to hold the Teflon Sleeve
in place. Make sure that the straps are located at 0.25 - 0.50 inch from each end of the Teflon Sleeve.
5. Contact between sleeved jumpers and structure, wiring, system elements and equipment is permitted.
Refer to SWPM 20-10-11 as an accepted procedure.
Alternate Part: M23053/12-(CD)-C, 6 feet Teflon Sleeve. Use the C=Class and D=Diameter as follows:
Teflon sleeves (TFE-2X), M23053/12-213-C to M23053/12-222-C, Class 2, sleeve inner diameter from
0.191 inch to 0.410 inch is acceptable.
(b) The quantity shown is the maximum quantity of straps needed to install insulation sleeving on the bonding
jumpers. More parts may be supplied than necessary.
(c) Prepare structure surface using Cleaning Procedure 1, 2, or 3. Prepare terminal(s), preinstalled ground
studs and washers using Cleaning Procedure 5 - Removal of Contamination with Cleaning Solvent. Refer
to SWPM 20-20-00 as an accepted procedure.
(d) Nut side torque to between 65 and 70 inch-pounds or screw head side torque to between 63 and 77 inch-
pounds. Refer to SWPM 20-20-10 as an accepted procedure.
FIGURE 1: FLIGHT COMPARTMENT - P6 PANEL BONDING JUMPERS - INSTALLATION
(SHEET 5 OF 6)
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More DataQtyIdentificationNameTaskStep
(e) Bending of the upper terminal lug (between the crimp and the lug head) to make sure contact between
the lug head and the washer is complete, is acceptable. Refer to SWPM 20-20-10 as an accepted proce-
dure.
(f) Apply torque nut to between 65 and 70 inch-pounds. Refer to SWPM 20-20-10 as an accepted procedure.
(g) Tie each bonding jumper separately to the wire bundle using procedure titled Wire Harnesses that Touch
at an Intersection. Refer to SWPM 20-10-11 as an accepted procedure.
(h) Make sure that the resistance does not exceed 1.0 milliohm. Measure from the lug furthest away from
the structure to the adjacent structure. Refer to SWPM 20-20-10 as an accepted procedure.
(i) Where material was removed to measure resistance, manually apply chemical coating Type 2 Class A
(Type 5 Class F optional), Refer to SOPM 20-43-03 as an accepted procedure. Apply one layer of BMS10-
11, Type 1 prime. Refer to SOPM 20-41-02 as an accepted procedure.
FIGURE 1: FLIGHT COMPARTMENT - P6 PANEL BONDING JUMPERS - INSTALLATION
(SHEET 6 OF 6)
Export Controlled ECCN: 9E991
Copyright © Unpublished Work - See page 1 for details.
Original Issue: May 16, 2022
737-24A1248 RB
17 of 17
REQUIREMENTS BULLETIN 737-24A1248
ALERTALERT

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