SERVICE BULLETIN NO. 1242A

• If the rudder bar assembly conforms to Figure 2, Detail A, modification is required. Proceed to Step 2, below. NOTE: All new replacement rudder bar assemblies conform to the configuration shown in Detail B. At the operator’s discretion, a new replacement rudder bar assembly may be installed in lieu of the modification described below. 2. Remove the rudder bar assembly from the airplane and disassemble. NOTE: Removing and reinstalling the rudder bar assembly from the aircraft will require disconnecting, reinstalling, and rigging of flight control, braking, and steering systems. Refer to the appropriate sections or chapters of the applicable Piper maintenance manual for specific instructions for each system, as well as the required installation torque for threaded fasteners. Strip the area to be modified using a commercially available chemical paint stripper, such as Cee-Bee E-2012 or E-2060 paint stripper. SERVICE BULLETIN NO. 1242A PAGE 4 of 7 3. Examine the area to be modified for cracks, using the inspection criteria described in Part II. Any cracked components must be replaced prior to proceeding. 4. Order one each of Piper part numbers (P/N) 99938-000 and 99938-001 rudder bar straps. TIG weld in place as shown in Detail B, per Chapter 4 of AC 43.13-1B (or latest revision). After welding, relieve residual stress in the affected area: Heat with a non-carburizing torch flame to 1,000 – 1,100 °F (538 – 593 °C) (a brown red color) then air cool to room temperature. All welding must be performed by a certified welder. NOTE: Installation of the rudder bar straps does not relieve the requirement for the recurring inspection in Part II. NOTE: The following information will assist in the modification: • All materials are 4130 normalized steel. • The rudder bar tubes have a nominal outside diameter of 0.875 inches and nominal wall thickness of 0.058 inches. • P/N 99938-000 and 99938-001 rudder bar straps are made from sheet steel with a nominal thickness of 0.040 inches. 5. Descale, degrease and repaint the bare steel on the rudder bar assembly using epoxy primer (two coats) and a topcoat of matching black color. 6. Reassemble the rudder bar and reinstall into the airplane. 7. Make a logbook entry documenting compliance with Part I of this service bulletin. Figure 1 Rudder Pedal Installation (Typical) STEP 3c: INSPECT 2 BENDS STEPS 3a/3e: REMOVE/REINSTALL 4 BOLTS STEP 2b: INSPECT WELDS COMMON TO TUBE AND RUDDER CONTROL ARM ASSEMBLY, AS APPLICABLE STEP 3b: INSPECT 4 BOLT HOLES PEDAL AND BAR ASSEMBLY DETAIL A DETAIL B(Fig. 2) FWD UP RUDDER BAR SUPPORT ASSEMBLY STEP 3d: INSPECT SUPPORT STRUCTURE INSIDE TUNNEL STEP 2c: REMOVE BOLTS, INSPECT FOR CRACKS, THEN REINSTALL BOLTS STEP 2a: INSPECT WELDED AREAS SERVICE BULLETIN NO. 1242A PAGE 5 of 7 0.10 IN. DETAIL B RUDDER BAR ASSEMBLY RUDDER BAR STRAPS: 99938-000 NEAR SIDE 99938-001 FAR SIDE DETAIL A RUDDER BAR ASSEMBLY INBD UP Figure 2 Rudder Bar Welding (Typical) SERVICE BULLETIN NO. 1242A PAGE 6 of 7 Part II. Inspection NOTE: Temporary removal of interior components may be required in order to accomplish the instructions that follow. NOTE: Refer to the appropriate section or chapter of the applicable Piper maintenance manual for the required installation torque for threaded fasteners that are reinstalled. 1. Gain access to the areas identified in Figure 1. NOTE: The inspections described in this service bulletin shall be accomplished using a 10X magnifier, a mirror and a suitable light source or other equipment capable of providing equal or better resolution. NOTE: Any cracked components must be replaced prior to next flight. 2. Pedal and Bar Assembly Inspection Visually inspect the rudder pedal and bar assembly (locations identified in Figure 1), with specific emphasis on: a. Welds identified in Details A and B (see Figure 2). b. Welds common to the tube and the rudder control arm assembly, as applicable. c. Bolt holes: remove the bolts that fasten the left and right pedal assemblies to each pedal and bar assembly. Using a borescope or other suitable tool, visually inspect the bolt hole in both inner and outer tubes for cracks. Reinstall bolts. NOTE: At the operator’s discretion, or, if a borescope is not readily available, the left and right pedal assemblies may be disassembled, allowing direct visual examination of the inner tube for cracks at the bolt holes. 3. Rudder Bar Support Assembly Inspection NOTE: The inspection described in Step 3 is applicable only to the following airplane models: • PA-28 series, fixed gear models only • PA-32 series, both fixed gear and retractable gear models • PA-44 series The retractable gear PA-28R series and the PA-34 series models use a different type of rudder bar support assembly, which does not have a service history of cracking. a. Remove and retain the four (4) bolts that secure the rudder bar support assembly to the cockpit floor. NOTE: It is not necessary to remove the rudder bar support assembly to accomplish this inspection. b. Visually inspect the four (4) bolt holes for cracks and elongation. See Figure 1. The diameter of the four bolt holes should measure 0.250 +0.005/-0.001 inches. c. Visually inspect the two (2) sheet metal bends common to the base for cracking, the entire length of each bend, both inner and outer surfaces. See Figure 1. d. Visually inspect the support structure for cracks or other damage. The support structure is located under the top surface of the tunnel, directly below the rudder bar support assembly. e. Reinstall the four (4) bolts that secure the rudder bar support assembly to the cockpit floor. 4. Perform a functional check on any system(s) that were disturbed during this inspection. 5. Make a logbook entry documenting compliance with this service bulletin, until the next inspection interval is reached per Compliance Time, above. SERVICE BULLETIN NO. 1242A PAGE 7 of 7 MATERIAL REQUIRED: Per aircraft: • Part I: One each, on condition as determined by inspection, P/N 99938-000 and 99938-001 rudder bar straps • Part II: On condition as determined by inspection, rudder pedal assembly components (see applicable parts catalog) AVAILABILITY OF PARTS: Your Piper Approved Service Center EFFECTIVITY DATE: This service bulletin is effective upon receipt. SUMMARY: 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 32960 or: CustomerService@piper.com Please include in subject line: “Aircraft ownership update”