(OVER) 

# SERVICE **BULLETIN**

Date: October 23, 2015 (M) 

## NO. 

# 1213A

Service Bulletin (SB) 1213A supersedes SB 1213 in its entirety. Aircraft that have previously complied with SB 1213 are in compliance with SB 1213A.

**S ub**  **j ect**  : **Em er**  **g enc**  **y Gear**  **Ex tensi**  **o n**  **C able**  **Ro utin**  **g I**  **ns p**  **ecti o**  **n**

**R eas**  **o n**  **fo r**  **R evisi**  **o n**  : SB 1213A changes format from the original document release. It also expands the number of affected airplanes.

**M od**  **els Aff**  **ecte d**  : **S erial**  **N u**  **m bers**  **Aff ecte**  **d** : PA-44-180 Seminole 4496245 through 4496377, 4496379, 4496380, 4496384 through 4496386

**Comp liance**  **T i**  **m e**  **:** Within 30 days of receipt of this service bulletin

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

**Pur po**  **se :**  In some affected aircraft, the emergency gear extension cable may be routed incorrectly. Left uncorrected, this condition could allow the copilot’s left rudder pedal to become entangled with the cable, resulting in a restriction of rudder movement. This service bulletin mandates a one-time examination of the routing and security of the emergency gear extension cable and, if necessary, instructions to reroute the emergency gear extension cable to conform to type design.

**S a**  **f et**  **y I ntent**  : The safety intent of this service bulletin is to prevent the copilot rudder pedals from contacting or being restrained by the emergency gear extension cable.

**C O**  **N F**  **I G**  **URATI O**  **N D**  **ESCRI P**  **TI O**  **N** : Incorporating this service bulletin will ensure that the emergency gear extension cable is correctly installed. Specifically, the instructions in this service bulletin will ensure that the cable is properly clamped to the toe brake brace assembly tube, forward of the rudder pedals, so that the cable does not inhibit rudder control and nose gear steering. 

# P **I P**  **ER C O**  **NSI D**  **ERS C**  **OMP LIANCE**  **M AN**  **D AT**  **O R**  **Y**

ATA: 3230 **Piper Aircraft, Inc.** 2926 Piper Drive Vero Beach, FL, U.S.A. 32960**SERVICE BULLETIN N O**  **. 1213A P**  **A G**  **E 2 of 4**

**I nstructi**  **o ns**  **:** 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 : When checking for positive clearance between the rudder pedal and the emergency gear extension cable, be advised that maximum forward deflection of the left rudder pedal is achieved only by full left rudder input combined with full left brake input with the aircraft on jacks. Refer to Section 7-10-00, Jacking, in the applicable Piper Airplane Maintenance Manual (AMM).
**P art I.**  **Inspection** RC – Examine the routing of the emergency gear extension cable, located forward of the copilot (right seat) left side rudder pedal. Verify that the cable is routed forward of the toe brake brace assembly. Also verify that the cable is secured with the proper clamp to the outboard bolt common to the toe brake brace assembly tubes and the rudder pedal assembly, as shown in Figure 1. NO te : Figure 1 shows two (2) bolts in close proximity. A conforming installation will have the cable clamp installed on the outboard bolt, with the cable clamp oriented 15° above the outboard direction, exactly as shown in Figure 1. Any other configuration is nonconforming, and must be reworked.

• If the emergency gear extension cable is installed in the aircraft as described above, rework is not required. Proceed to Part III.
• If the emergency gear extension cable is NOT installed as described above, rework is required. Proceed to Part II. **P art II.**  **Rework** 1. RC – If the hardware that mounts the emergency gear extension cable to the rudder pedal assembly is incorrectly installed, remove and reinstall to match the configuration shown in Figure 1. 2. If some or all of the hardware shown in Figure 1 is missing, order replacement hardware from Piper. See Table 1 under MATERIAL REQUIRED, below. 3. RC – Place the aircraft on jacks to allow free rotation of the nose gear. (Refer to Section 7-10-00, Jacking, in the applicable AMM.) Operate the rudder pedals and brakes through the full range of motion and verify that the rudder pedals do not contact the emergency gear extension cable. 4. RC – Perform a functional test of the emergency gear extension cable, as specified in Chapter 32 of the applicable AMM. Verify smooth operation of the emergency gear knob and adjust the cable routing as needed to eliminate any possibility of contact with the rudder pedal. Remove the aircraft from jacks. (Refer to Section 7-10-00, Jacking, in the applicable AMM.) 5. Proceed to Part III. **P art III.**  **D ocumentation of Compliance**  Make a logbook entry documenting compliance with this service bulletin.**SERVICE BULLETIN N O**  **. 1213A P**  **A G**  **E 3 of 4**

**F igure 1**  Emergency Gear Extension Cable, Correct Routing TOE BRAKE BRACE ASSEMBLY TUBES

LOOKING FWD AT COPILOT SIDE **OUTBD UP**  

### A **A** EMERGENCY GEAR EXTENSION CABLE

RUDDER PEDAL ASSEMBLY (CO-PILOT SIDE) **CORRECT** CABLE ROUTING

CLAMP ORIENTATION 15° CLAMP (P/N 454-930) HOLDING CABLE IS ATTACHED TO OUTBOARD BOLT RUDDER PEDAL ASSEMBLY AN3-17A BOLT (400-450)

**OUTBD AFT** **FWD**

**VIEW** 

## A

**− A** 
LOOKING UP EMERGENCY GEAR EXTENSION CABLE

FORWARD BULKHEAD ASSEMBLY NAS1149FO363P WASHER (690-612)

NAS43HT3-28 SPACER (687-209) NAS1149FO363P WASHER (690-612)

MS21042-3 NUT (404-526) PS10017-2-6 CLAMP (454-930) **CORRECT** CABLE ROUTING **INCORRECT** CABLE ROUTING**SERVICE BULLETIN N O**  **. 1213A P**  **A G**  **E 4 of 4**

**M ATERIAL REQUIRE**  **D** : On condition only, order parts required per Table 1, per aircraft **T**

**able 1**  **R e**  **p lace**  **m ent**  **M o**  **untin g H**  **ar dw**  **are** 

### Quantity **P iper**  **P art Number**  **Nomenclature D**  **escription** 1 454-930 CLAMP PS10017-2-6 2 690-612 WASHER NAS1149F0363P 1 687-209 SPACER NAS43HT3-28 1 404-526 NUT MS21042-3 1 400-450 BOLT AN3-17A

**AVAILABILIT Y**  **OF P**  **ARTS** : Your Factory Authorized Piper Service Facility

**Eff ectivit**  **y d ate**  : This service bulletin is effective upon receipt.

**S u**  **mm ar**  **y** : 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 Factory Authorized Piper Service Facility to make arrangements for compliance with this service bulletin in accordance with the compliance time indicated.
**No te**  : 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