SERVICE BULLETIN No. 1123C

12. Lubricate the nose landing gear per the lubrication chart located in the applicable aircraft Maintenance Manual. 0 0 0 0 13. Verify proper adjustment of the nose gear down lock link by performing the rigging procedure per the "Installation and Rigging of the Nose Gear' section of the applicable Maintenance Manual, as modified by section 4, Rigging Instructions, of this service bulletin. 0 0 0 14. Inspect the Tunnel Bracket 95554-000 installation for loose attachment rivets to the tunnel and nose gear mount fitting 95555-000 and visually inspect for cracks in the bracket attachment flange adjacent to the fitting. This inspection can be accomplished through an access opening located in the bottom skin at B.L. 00.00, just aft of Sta. 49.5 bulkhead. Inspect for loose rivets by observing the area during the landing gear cycle test performed per Inspection No. 9. (Ref Figure 1A) and looking for any relative motion between riveted components. 0 0 0 PAGE 3 of 12 Figure 1 Trunnion Inspection (See Table 1, Item 3) PAGE 4 of 12 Figure 1A Actuator Mounting Bracket Rivets PAGE 5 of 12 INSTRUCTIONS: (Continued) 2. Modified Components The following parts have been modified to increase their service life. This Service Bulletin does not require the immediate replacement of the currently installed part, but are recommended as replacements. a. Nose gear upper drag link attach bolt AN7-35, Piper P/N 400-274. b. Steering Channel Assembly 95394-000. c. Actuator Mount Bracket P/N 95724 and Bushing P/N 95061-89. NOTE: Aircraft serial numbers 3449262, 3449313 and up have had the modified parts factory installed during production. While they are already installed, they still need to be inspected. The Nose Gear Installation has been revised to replace the AN7-35 bolt with NAS6207-50D, Piper P/N 693-215, a stronger bolt. The Steering Channel has been revised to increase the material thickness by 25% and the height increased to prevent "ball-out-of- track" failures. The part number for the redesigned Steering Channel is 95394-005. The 95394-005 Steering Channel is Approved for all PA-34 Series aircraft. The Actuator Mount Bracket has gone through two major design changes, from aluminum to steel, and a recent change of adding reinforcements to increase the bearing surfaces for the P/N 95061-089 bushing. For all PA-34-200 and PA-34-200T serial numbers 34-7250001 through 34-7570050 (with aluminum bracket), visually inspect the aluminum mount bracket for wear, cracks, loose rivets and other damage, within the next 50 hours and at 50 hour intervals thereafter (Ref. Table 1, item 9). For PA-34-200T aircraft, serial number 34-7570051 and up, for all PA-34-220T aircraft through serial number 3449193, visually inspect the steel mount bracket for wear, cracks, loose rivets and elongation of the attachment hole for the P/N 95061-089 bushing, within the next 50 hours and at 100 hour intervals thereafter. The following kits are required if the aluminum or steel Actuator Mount Brackets are discrepant and must be replaced for the noted aircraft and serial numbers. The kit includes the latest design mount bracket and new required hardware for the attachment of the Nose Gear retraction Link Assembly P/N 95712-00/-04. d. Turn-stop boss failure on the strut upper tube assembly P/N 95720. Table 2 Actuator Mount Bracket Kits KIT NUMBER MODEL EFFECTIVITY MOUNT ASSEMBLY 767-357 PA-34-200 34-7250001 thru 34-7350135 95724-007 Replaces 95724-000 767-358 PA-34-200 34-7350136 thru 34-7450220 95724-005 Replaces 95724-002 767-358 PA-34-200T II 34-7570001 thru 34-8170092 767-359 PA-34-220T III 34-8133001 thru 34-8633031; 3433001 thru 3433172; 3448001 thru 3448037 95724-006 Replaces 95724-004 767-359 PA-34-220T IV 3447001 thru 3447029; 3448038 thru 3448079 767-359 PA-34-220T V 3449001 through 3449261; 3449263 through 3449312 Service Kit 767-368 has been established to add a Turn Limit Indicator on PA-34 Series aircraft prior to serial number 3449060. (PA- 34-220T Seneca V aircraft serial numbers 3449060 & up have a factory installed turn limit placard.) PAGE 6 of 12 INSTRUCTIONS: (Continued) Figure 2 Service Wear Limit Locations 3. Service Wear Limits Table 3 Service Wear Limits Part Description ID Wear Limits Min. Max. 1. Drag Link Upper Bushing 0.562 0.564 2. Drag Link Center Bushing 0.375 0.377 3. Drag Link Lower Bushing 0.438 0.442 4. Trunnion Pivot Bushings 0.500 0.503 5. Steering Arm Center Pivot Bushings 0.375 0.377 Part Description ID Wear Limits Min. Max. 6. Steering Arm Center Pivot Sleeve 0.250 0.253 7. Down Lock Link Bushing 0.251 0.253 8. Actuator Mount Bracket 0.250 0.252 9. Down Lock Link Rod End 0.190 0.192 These Wear Limits are in effect until the contents of this service bulletin are incorporated into the appropriate Maintenance Manuals. Table 3 is a "Wear Limits Chart" that can be used to determine the acceptable / or replacement condition for the listed parts that were inspected per Instructions Step 1. in this Service Bulletin. Visually inspect all bolts/pins for wear, damage, or corrosion. Replace as required. PAGE 7 of 12 Figure 3 Drag Link Over-Center Measurement Nose Gear Installation PAGE 8 of 12 Figure 3A Nose Gear Installation PAGE 9 of 12 INSTRUCTIONS: (Continued) Figure 4 Steering Arm Channel Clearance 4. Rigging Instructions These Rigging Instructions are in effect until the contents of this service bulletin are incorporated into the appropriate Maintenance Manuals. All other rigging instructions as called out in the "Installation and Rigging of the Nose Gear" section of the appropriate Aircraft Maintenance Manual are still valid and must be complied with in addition to these corrections/clarifications. 4.1 Nose Gear Drag Link Inspection and Adjustment 4.2 Steering Arm Channel Clearance a. For Seneca serial numbers 34-7250001 through 34-7450220: Rigging of the nose gear installation (Item 13, Table 1) shall be accomplished per this service bulletin. b. For Seneca II through V: Rigging of the nose gear installation (Item 13, Table 1) shall be accomplished per the appropriate service manual. Refer to the maintenance manual for the procedure to make the over center measurement. a. Turn the nose gear full travel and make sure the clearance between the steering arm assembly and the tiller track is a minimum 0.03 of an inch at both the left and right stops. (see Figure 4). If insufficient clearance is obtained, loosen the upper mounting bolts for the tiller track and move the track upwards in the slotted holes where the track is attached to the gear mount assembly. Adjust to obtain a minimum of 0.03 inch clearance. Tighten the upper mounting bolts. PAGE 10 of 12 INSTRUCTIONS: (4) (Continued) 4.3 Installation and Rigging of Nose Gear (Refer to Figures 3 and 3A) NOTE: With reference to Chapter 12 for proper lubricants, ensure affected parts of the landing gear such as bearings, bushings, etc, are lubricated prior to and following assembly. a. Position the gear assembly between the mounting points, making certain the tiller roller is properly inserted in the steering arm channel. b. Align the mounting points of the trunnion assembly with those on the mount and install the appropriate hardware. The bolt heads should be inboard, with the nuts outboard and just loose enough to allow the gear to swing freely. c. If necessary, assemble the drag links. Installed or removed, use the appropriate instructions in this section to check their rigging. d. The drag links are installed with their through center stops facing up, the upper link connection aligned with the right side of the gear's upper ring block and the lower link connection positioned in its bracket on the bottom rear of the nose gear mount (refer to Figure 3). With the links in position, install the connecting hardware and move the gear to assure free movement. e. At the actuator downlock mount (See Sketch B, Figure 3A), disconnect the retention spring from the retraction link fitting. f. Position the gear in its down locked position and check that the drag links have fully extended to their through center position with the stop surfaces in contact. g. With the actuating piston rod extended, adjust the piston rod end such that 0.25 of an inch of rod travel remains in the actuator before full extension. Connect the rod end to its mount on the gear assembly. The retraction link to which the actuator is attached should be near its stop. h. Reconnect the retention spring to the retraction link fitting. i. Install the down lock link (see Figure 3) with the rod end connected to the retraction link and the other end to the bottom drag link. j. Adjust the down lock link as necessary until the guide pin is completely bottomed out at the top of its slot and the retraction link is moved against its stop. k. Retract and free fall the landing gear at least three times. Remove the down lock link, shorten it by 1/2 turn and reinstall. l. The down and locked limit switch should be adjusted to have it actuated when the retraction link is back against its stop. m. Using a tow bar to reach full travel against stops, rig the nose gear steering rod ends as necessary to allow full deflection. n. Refer to Figure 3A, Sketch D and set the up stop to the dimension shown. Retract the gear and ensure the nose gear housing engages the stop under retraction pressure. Adjust as necessary. NOTE: If the down lock link is adjusted properly, the retraction link will be moved completely to its stop by the down lock link therefore taking up some of the extra actuator piston rod travel and activating the down and locked limit switch. NOTE: After any up stop adjustment, the gear must be cycled to ensure the strut engages the stop under pressure. PAGE 11 of 12 INSTRUCTIONS: (4.3) (Continued) 5. Documentation of Compliance o. Retract the gear and check that the up switch is just activated when the gear contacts the stop. Following this, adjust the switch upward another 0.02 to 0.04 of an inch. p. Support the gear in its up locked position and adjust the rod end of the actuator piston rod to allow a minimum of 0.06 of an inch actuator travel remaining with the gear up and locked. q. Cycle the gear a few times and check down lock, and up stop action, and switch activation. Include short pickup cycles which simulate gear sag pickup in flight. Leave gear up. r. Check up switch bracket override action to ensure proper activation. s. Extend the gear and check that the actuator piston travel remaining till full extension is not less than .15 of an inch. t. Retract and free fall the gear to ensure the retraction link retention spring moves to the assemblies aft causing the down lock link to fully compress and the drag links to lock in their over center position. u. Turn the nose gear full travel and make sure the clearance between the steering arm assembly and the tiller track is between 0.06 and 0.03 of an inch at both the left and right stops. v. Verify free and correct movement of the tiller roller between the steering arm channel and the tiller track and up and down the tiller track. w. Refer to the appropriate paragraph in this section for rigging of the nose gear doors. x. Lube the system as specified in Chapter 12. y. Ascertain the gear is down and locked and check alignment of landing gear. Refer to the appropriate section of this chapter. z. Remove airplane from jacks. All adjustments of the limit switches should be made with the airplane on jacks. Do not bend actuator springs mounted on the limit switches. Adjustment of the nose gear up limit switch: The gear up limit switch is mounted on a bracket attached to the lower inner left tubular member of the nose gear mount, adjacent to the gear roller track assembly. To facilitate adjustment of the limit switch, disconnect gear doors. Turn master switch ON, move gear selector switch to the gear up position and raise the landing gear. Turn the master switch OFF. Block the nose gear in the up position and slowly pull the free fall knob away from the instrument panel. This will relieve hydraulic pressure and permit the main gear to drop. Loosen the attachment screws of the switch and rotate the switch toward the actuator tang until the switch is heard to actuate. Retighten the switch attachment screws. Remove the block from under the gear and allow it to extend slowly. Turn master switch on, raise gear and determine that the gear lights function properly. NOTE: For PA-34-200 aircraft (S/N 34-7250001 through 34-7350135) which do not have "Upstop" kit 760-699 installed, rig the up limit switch as noted: CAUTION: THE TILLER, TILLER ROLLER, AND STEERING ARM CHANNEL CAN BE DAMAGED IF NOSE WHEEL TURN LIMITS ARE EXCEEDED WHEN TOWING THE AIRPLANE WITH POWER EQUIPMENT. INSPECT, ADJUST, REPAIR OR REPLACE AS REQUIRED. Make a logbook entry indicating compliance with this service bulletin. PAGE 12 of 12 MATERIAL REQUIRED: AVAILABILITY OF PARTS: Your Piper service facility. EFFECTIVITY DATE: This service bulletin is effective upon receipt. SUMMARY: One (1) each, Nose Gear Hydraulic Jack Mount Assembly Kit, Piper P/N 767-357, 767-358 or 767-359 (See Table 2 for correlation between the aircraft serial number effectivity and the correct kit number required), Turn Limit Kit, Piper P/N 767-368, AN7-35 bolt, Piper P/N 400-274 or NAS6207-50D bolt, Piper P/N 693-215, AN960-716L washer, Piper P/N 407-591, AN960-716 washer, Piper P/N 407-568, AN320-7 nut, Piper P/N 404-396, MS24665-302 cotter pin, Piper P/N 424-085, Steering Channel, Piper P/N 95394-005, if required, per aircraft. Please contact your Piper approved 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, current owner's name and address. Corrections and/or changes should be directed to: THE NEW PIPER AIRCRAFT, INC. Attn: Customer Service 2926 Piper Drive Vero Beach, FL 32960 ATTACHMENT, Page 1 of 2 COPY JUN 21 2013 Eric Wright, ODA administrator Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, Florida 32960 Dear Mr. Wright: The Federal Aviation Administration (FAA) received your letter dated June 4, 2013, proposing an alternative method of compliance (AMOC) to paragraphs (e) and (g) of Airworthiness Directive (AD) 2005-13-16 for all Piper Model PA-34 aircraft. This AD requires owners/operators of affected aircraft to detect, correct, and prevent failure in certain components of the nose landing gear (NLG), lack of cleanliness of the NLG due to inadequate maintenance, or lack of lubricant in the NLG or NW components. This failure of the NLG could lead to loss of control of the airplane during take-off, landing, or taxiing operations. The AD requires the actions to be done following Piper Service Bulletin (SB) 1123A dated November 30, 2004. Your letter proposed SB 1123C dated May 30, 2013, as an AMOC in its entirety as a replacement (supersedure) of SB 1123A called out in the AD. The data showing the proposal as an acceptable level of safety is provided in your letter. The Atlanta Aircraft Certification Office (ACO) has reviewed your request and approves your proposal of SB 1123C dated May 30, 2013, in its entirety as an AMOC to paragraph (e) and (g) of AD 2005-13-16 for all models listed therein (paragraph (c)). All provisions of AD 2005-13-16 that are not specifically referenced above remain fully applicable and must be complied with accordingly. This FAA AMOC is transferable with the aircraft. Please include a copy of this AMOC when distributing SB 1123C. Before using this AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. When complying with or verifying compliance with AD 2005-13-16 using this AMOC, a copy of this letter shall be inserted into the maintenance records of the airplane. U.S. Department Small Airplane Directorate of Transportation Atlanta Aircraft Certification Office Federal Aviation 1701 Columbia Ave. Administration College Park, Georgia 30337 ATTACHMENT, Page 2 of 2 If you have any questions or need additional information, please contact Gregory K. (Keith) Noles by phone at (404) 474-5551, fax at (404) 474- 5606, or electronic mail at gregory.noles@faa.gov. Sincerely, /s/ Melvin D. Taylor, Manager, Atlanta Aircraft Certification Office cc: ACE-100 ACE-113 (Showers/Wessley) ACE-MKC-AEG-11 (Alquist)