Piper SB 1301: No revision named

Date: January 6, 2017 (M)

SERVICE

BULLETIN NO. 1301

PIPER CONSIDERS

COMPLIANCE MANDATORY Piper Aircraft, Inc.

2926 Piper Drive Vero Beach, FL, U.S.A. 32960 (OVER) ATA/JASC: 2497 Subject: Wiring inSpection ModelS Affected: SeriAl nuMberS Affected:

PA-31T Cheyenne/Cheyenne II 31T -7400002 through 31T -8120104 PA-31T1 Cheyenne I/IA 31T -7804001 through 31T -8304003;

31T -1104004 through 31T -1104017 PA-31T2 Cheyenne IIXL 31T -8166001 through 31T -8166076;

31T -1166001 through 31T -1166008 PA-31T3 T -1040 31T -8275001 through 31T -8475001, 31T -5575001 PA-31P-350 Mojave 31P-8414001 through 31P-8414050 coMpliAnce tiMe: Initial compliance is to coincide with the next regularly scheduled maintenance event. Thereafter, compliance is to be accomplished on a recurring basis, at an interval not to exceed 2,000 operating hours or seven (7) calendar years time-inservice, whichever occurs first.

purpoSe: The affected aircraft have a circuit breaker panel installed in the cockpit floor which includes wires that carry a high electric current. Any deterioration of the insulation on these wires could result in an electrical short, which poses a fire hazard. This service bulletin mandates a recurring inspection of this wiring to detect and repair any deterioration or damage.

SAfety intent: The safety intent of this service bulletin is to identify and correct any wiring conditions that could lead to arcing, shorting, or other damage to the floor mounted circuit breaker panel and associated wiring, which is located directly below this circuit breaker panel.

SerVice bulletin no. 1301 pAge 2 of 5 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 SB, if the RC steps can be done and the airplane can be put back in a serviceable condition.

NOTE: Temporary removal of floor panels and/or access plates and panels will be required to accomplish the inspections described in this service bulletin. Removal of the circuit breaker panel itself is not recommended as part of this inspection, as this would disturb the “as installed” routing of the wiring.

NOTE: Perform the inspections described in this service bulletin using a 10X magnifier, a mirror, and a suitable light source or other equipment capable of providing equal or better resolution.

NOTE: The cockpit floor is part of the pressure vessel structure and is therefore subject to elastic deflection due to changes in cabin pressure. Wires with only a small clearance from adjacent components while the aircraft is on the ground may touch these components while in flight. Inspect the condition of wires at these locations, as described below.

NOTE: For additional guidance, consult one or more of the following aviation industry publications:

• FAA Advisory Circular (AC) 43.13-1B “Acceptable Methods, Techniques and Practices,” Chapter 11

• AC65-15A “Airframe & Powerplant Mechanics Airframe Handbook,” Chapter 11

• Military Specification MIL-W-5088 Rev. L “Wiring, Aerospace Vehicle”

• SAE Aerospace Standard AS50881 Rev. D “Wiring Aerospace Vehicle”

1. RC – Locate the main circuit breaker panel, which is installed on the cockpit floor between the pilot and copilot seats. Gain access to the area immediately below this circuit breaker panel.

This circuit breaker panel will resemble one of the illustrations shown in Figure 2, but may vary depending on modifications made to the aircraft.

2. RC – Inspect the routing of all wiring. Reroute or rework as necessary to minimize the likelihood of chafing contact between adjacent components such as fluid carrying lines, airframe structure, and other wiring.

3. RC – Inspect the condition of all wiring. Repair or replace any wires with chafing, burning, breaks in insulation, corrosion or any other apparent damage. Inspect for loose, corroded or broken terminals and repair or replace on condition.

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

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

SERVICE BULLETIN NO. 1301 PAGE 3 of 5

MAIN CIRCUIT BREAKER

PANEL LOCATION - SEE FIGURE 2 T FWD

•ESSENTIAL BUS BATTERY

LEFT GEN RIGHT GEN

BUS TIE BUS TIE Figure 1 Figure 2, Sheet 1 of 2 Plan View of Aircraft Interior Main Circuit Breaker Panel Configurations

SerVice bulletin no. 1301 pAge 4 of 5 figure 2, Sheet 2 of 2 Main Circuit Breaker Panel Configurations NON

ESSENTIAL LEFT ICE LEFT

GENERATOR LEFT W’SHLD HEAT RIGHT W’SHLD HEAT RIGHT

GENERATOR

BATTERY

RIGHT ICE LEFT MAIN RIGHT MAIN NO.1

AVIONICS

LEFT GEN FEED LEFT MAIN RIGHT MAIN NO. 2

AVIONICS

RIGHT GEN FEED LEFT ALT

ICE BATTERY

RIGHT ALT NON ESS LEFT MAIN L ALT FIELD RIGHT MAIN NO. 1

AVIONICS

LEFT ALT FEED R ALT FIELD LEFT MAIN RIGHT MAIN NO. 2

AVIONICS

RIGHT ALT FEED NON

ESSENTIAL LEFT ICE LEFT

GENERATOR RIGHT

GENERATOR

BATTERY

RIGHT ICE LEFT MAIN RIGHT MAIN NO.1

AVIONICS

LEFT GEN FEED LEFT MAIN RIGHT MAIN NO. 2

AVIONICS

RIGHT GEN FEED

SerVice bulletin no. 1301 pAge 5 of 5 MAteriAl reQuired: N/A AVAilAbility of pArtS: Y our Factory Authorized Piper Service Facility effectiVity dAte: This service bulletin is effective upon receipt.

SuMMAry: Please contact your Factory Authorized Piper Service Facility 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.

Attn: Customer Service 2926 Piper Drive Vero Beach, FL 32960