Date: February 15, 2019 (M)

SERVICE BULLETIN

NO. 1337

PIPER CONSIDERSCOMPLIANCE MANDATORY

Piper Aircraft, Inc.2926 Piper DriveVero Beach, FL, U.S.A. 32960

(OVER)

ATA/JASC: 2460, 2497

SUBJECT: EMERGENCY POWER SUPPLY MODIFICATION

MODELS AFFECTED: SERIAL NUMBERS AFFECTED:

PA-34-220T Seneca V 3449459, 3449467 through 3449508

COMPLIANCE TIME: To coincide with the next regularly scheduled maintenance event, but not to exceed the next 100 hours time in service

APPROVAL: The engineering aspects of this service document have been shown to comply with the applicable Federal Aviation Regulations and are FAA approved.

PURPOSE: This service bulletin provides instructions for the modification of the emergency power supply assembly.

SAFETY INTENT: The safety intent of this service bulletin is to prevent electrical arcing between a wire bundle and the rudder control cables, which, if not corrected, could cause failure of the rudder control system.

CONFIGURATIONDESCRIPTION: Incorporating this service bulletin results in a portion of the emergency power

wiring being rerouted to improve clearance from the rudder control cables.

INSTRUCTIONS:

NOTE: Some steps in these instructions are identified as “required for compliance” (RC). If this service bulletin is mandated by an airworthiness directive (AD), the steps identified as RC must be done to comply with the AD. Steps not identified as RC are recommended and may be deviated from, done as a part of other actions, or done with accepted methods different from those given in this service bulletin, if the RC steps can be done and the airplane can be put back in a serviceable condition.

NOTE: The temporary removal of interior components, fairings and/or access panels may be required in order to accomplish the following instructions.

1. Disconnect electrical power from the affected systems:

• Pull the breakers marked “Emer Batt Position 340” (on the circuit breaker panel) and “ESS Bus 1 & 2” (on the instrument panel).

• Alternatively, disconnect both the primary and emergency batteries. The batteries are in the same area as the emergency power supply assembly (see Figure 1).

SERVICE BULLETIN NO. 1337 PAGE 2 of 7

2. RC – Identify the Emergency Power Supply (EPS) Assembly, Piper part number (P/N) 107279-002, mounted under the floor of the aft baggage compartment (located behind the last row of seats). See Figure 1. Remove the assembly, P/N 107279-002, from the aircraft.

3. RC – Inspect the rudder flight control cables and the EPS wiring for chafing and other damage.

• To inspect the rudder control cables for damage, refer to Piper PA-34-220T Seneca IV/V Airplane Mainte-nance Manual, P/N 761-888, Sections 27-00-00 and 27-20-00. For replacement, if required, refer to Section 27-20-00.

• If any damage to wiring is evident, repair or replace per FAA Advisory Circular (AC) 43.13-1B, Chapter 11.

4. RC – In order to prevent chafing of the relocated wire harness, install a Grommet, MS21266-1N, as follows:

a. Prepare mounting surface by cleaning with isopropyl alcohol.

b. Cut a section of MS21266-1N grommet to a length to fit the edge, identified in Figure 2, View C–C, of Bracket, P/N 107384-001. Bond the grommet in place using 3M Adhesive EC-1300L or 1300L (or equivalent). Alternatively, bond the grommet in place using epoxy resin.

5. RC – Install two (2) new Panduit ABMM-A Cable Tie Mounts (Piper P/N 279-044), or an equivalent, as follows:

a. Prepare the mounting surface by cleaning it with isopropyl alcohol.

b. Peel the backing paper off of each cable tie mount. Position the adhesive mount on the surface, in locations approximate to those shown in View D–D. Press the mounts firmly onto the surface.

6. RC – Remove the Cover, P/N 95213-002. Retain the cover and hardware for reuse.

7. RC – Remove the two (2) cable tie straps that hold the wire harness to the ABMM-A cable tie mounts. Discard the cable tie straps.

8. RC – Relocate the wiring harness as follows:

a. Remove the Bridge Rectifier, P/N 584-465, from the Bracket, P/N 107384-001.

NOTE: Do not remove the two wires that are soldered onto the bridge rectifier. It is not necessary to remove them to accomplish this modification.

b. Reroute the wiring connected to the Terminal Board, MS27212-1-6, to the opposite side of Bracket, P/N 107384-001, as shown in View B–B and other figure illustrations. The terminal stack-up is shown in View E–E.

c. Torque the terminal nuts to 22 in-lb.

d. Rotate the rectifier 180 degrees and reinstall it, as shown in Detail K.

9. RC – Secure the wiring harness to the cable tie mounts, which were installed in Step 5, with two (2) cable tie straps MS3367-4-9, as shown in View D–D. Alternatively, use any MS3367 series cable tie straps that will fit through the slots of the cable tie mounts.

10. RC – Reinstall the Cover, P/N 95213-002, with the opening facing to the right (that is, rotated 180 degrees from its original configuration), to provide clearance for the new routing path for the wiring.

11. RC – Locate the clamp securing the power cable P10A4, shown in Figure 3. In order to prevent possible chafing of the relocated wiring harness, rearrange the mounting hardware with the screw heads on inboard side of the Zee Assembly, P/N 68632, as shown in View F–F. Accordingly, install the washer, nut and clamp on the outboard side.

12. RC – Reinstall the Emergency Power Supply Assembly, P/N 107279-002, into the aircraft. Confirm that there is a minimum of 1.50 inches of separation between all flight control cables and wires P38B12 and P38C12 (with the wires connected to the bridge rectifier D302).

13. Reconnect the electrical power that was disconnected in Step 1.

14. RC – Perform a functional test on any electrical systems that were disturbed during this modification.

15. RC – Make a logbook entry documenting compliance with this service bulletin.

SERVICE BULLETIN NO. 1337 PAGE 3 of 7

Figure 1Emergency Power Supply Location

SEE DETAIL J

LOOKING DOWN AT THE FUSELAGE

FWD

FS168.78REF

DETAIL JEMERGENCY POWER SUPPLY ASSEMBLY,

MAIN AND EMERGENCY BATTERY

EPS ASSEMBLYP/N 107279-002 A A

B B

C

C

MAIN BATTERY

EMERGENCYBATTERY

FF

SERVICE BULLETIN NO. 1337 PAGE 4 of 7

Figure 2, Sheet 1 of 3Emergency Power Supply Assembly Modification

F802 F801 F800

F803F804F805

F808 F807 F806

F809F810

K408 K409

P615

J356

PIR 107279 A 03

VIEW B−BAFTER MODIFICATION

LOOKING UP, AS INSTALLED, ATEMERGENCY POWER SUPPLY ASSEMBLY

SEE DETAIL L

SEE DETAIL K

WIRING HARNESSMOVED TO LEFT HAND

SIDE (AS INSTALLED)

BRIDGE RECTIFIERROTATED 180 DEGREES

BRACKETP/N 107384-001

D

D

PIR 107279 NEW 03

VIEW A−ABEFORE MODIFICATION

LOOKING UP, AS INSTALLED, ATEMERGENCY POWER SUPPLY ASSEMBLY

REMOVE COVERP/N 95213-002

(TWO SCREWS)

REMOVE THE 2 CABLE TIES THAT ATTACH

HARNESS TO CABLE TIE MOUNTS

BRIDGE RECTIFIERP/N 584-465

FWD

SERVICE BULLETIN NO. 1337 PAGE 5 of 7

Figure 2, Sheet 2 of 3Emergency Power Supply Assembly Modification

DETAIL KLOOKING UP

MODIFIED INSTALLATION OF BRIDGE RECTIFIER (D302)

BRIDGE RECTIFIERP/N 584-465

BEVELED CORNER(REF)

FWD

VIEW C−CLOOKING FORWARD

MODIFIED INSTALLATION OF EPS BRACKET

UP

GROMMETMS21266-1NP/N 189-625

GROMMET MS2166-1N(ALREADY INSTALLED)

BRIDGE RECTIFIER WIRING(CONFIGURATION

AFTER MODIFICATION)

BRIDGE RECTIFIER (REF)(AFTER MODIFICATION)

BRACKETP/N 107834-001

VIEW D−DMODIFIED INSTALLATION OF EPS ASSEMBLY

FWD

UP

ATTACH HARNESS TO MOUNT:CABLE TIES MS3367-4-9

(OR EQUIVALENT)(2 REQ.)

PANDUIT ABMM-A CABLE TIE MOUNT PIPER P/N 279-044 (OR EQUIVALENT)

(2 REQ.)

SERVICE BULLETIN NO. 1337 PAGE 6 of 7

Figure 2, Sheet 3 of 3Emergency Power Supply Assembly Modification

(MS27212-1-6 TERMINAL BOARD)

PIR 107279 A 03

DETAIL LEMERGENCY POWER SUPPLY

MODIFIED WIRING TERMINATION (LOOKING UP)

BRACKETP/N 107384-001

TERMINAL BOARDMS27212-1-6

SCREWMS51861-34

(2 REQ.)

E E

FWD

VIEW E−EEMERGENCY POWER SUPPLY

TERMINAL INSTALLATION STACK-UP

DOWN

COVERP/N 95213-002

TERMINAL STRIP BUSP/N 35207-004

COVERP/N 95213-000

NUT NAS679A06WASHER NAS1149FN616P(6 PLACES)

SCREW MS35206-217WASHER NAS1149FN416PNUT MS21042-04(2 PLACES)

TERMINAL BOARDMS27212-1-6

WIRE WITH RING TERMINAL(6 PLACES)

SERVICE BULLETIN NO. 1337 PAGE 7 of 7

Figure 3Battery Power Cable Installation Modification

VIEW F−FAFTER MODIFICATION

LOOKING INBOARD AT ZEE ASSEMBLY MAIN BATTERY CABLE CLAMPS

REINSTALL THIS CLAMP HARDWAREWITH SCREW HEAD INBOARD, WASHER AND NUT OUTBOARD(REVERSE OF ORIGINAL)

ZEE ASSEMBLY

POWER CABLE P10A4

FWD

UP

MATERIAL REQUIRED: Per aircraft:

• Two (2) each, Cable Tie Mounts, Panduit ABMM-A (Piper P/N 279-044), or equivalent

• Two (2) each, Cable Tie Straps, MS3367-4-9 (Piper P/N 488-722), or other suitable MS3367 series straps

• Sufficient length, Grommet MS21266-1N (Piper P/N 189-625)

AVAILABILITY OF PARTS: Your Piper Approved Service Center, or procure locally

EFFECTIVITY DATE: This service bulletin is effective upon receipt.

SUMMARY: Applicable factory participation is limited to new aircraft in warranty at the time of compliance. Factory participation will remain in effect for a period of time not to exceed 180 days from the date of this service bulletin.

Please contact your Piper Approved Service Center to make arrangements for compliance with this service bulletin in accordance with the compliance time indicated.

NOTE: Please notify the factory of any address/ownership corrections. Changes should include aircraft model, serial number, and current owner’s name and address.

Corrections and/or changes should be directed to:

PIPER AIRCRAFT, INC. Att’n: Customer Service 2926 Piper Drive Vero Beach, FL 32960or: CustomerService@piper.comPlease include in subject line: “Aircraft ownership update”