SERVICE BULLETIN NO. 1123B

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 SERVICE BULLETIN NO. 1123B PAGE 3 of 12 Figure 1 Trunnion Inspection (See Table 1, Item 3) Table 1 (Continued) Scheduled Maintenance 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 SERVICE BULLETIN NO. 1123B PAGE 4 OF 12 AFT TUNNEL STA. 49.5 BULKHEAD Figure 1A Actuator Mounting Bracket Rivets Inspect for loose mounting rivets that attach the actuator mounting bracket to tunnel aft of Sta. 49.5 bulkhead by placing aircraft on jacks, extend and retract landing gear and note any relative motion between the subject bracket and the tunnel. It will be necessary to pull carpet away from the side of tunnel to inspect noted rivets. Inspect These (4 Rivets) for Attachment of Tunnel Bracket 95554-000. Inspect These 11 Rivets Inspect for Cracks in Flange Radius 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. NOTE: Aircraft serial numbers 3449262, 3449313 and up have had these parts factory installed during production. a. Drag link-to-nose gear strut bolt, P/N 400-274 (AN7-35). The Nose Gear Installation has been revised to change this AN7-35 bolt to P/N 693-215, (NAS6207-50D) bolt that is stronger. This bolt change is approved for all PA-34 Series aircraft, and is an Alternate Method of Compliance as a substitute for the P/N 400-274 (AN7-35) bolt per AD 93-24-14. b. Steering Channel Assembly 95394-000. 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. c. Actuator Mount Bracket P/N 95724 and Bushing P/N 95061-89. 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. SERVICE BULLETIN NO. 1123B PAGE 5 OF 12 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 & Up 767-358 PA-34-200T 34-7570001 & Up 95724-005 Replaces 95724-002 767-359 PA-34-220T III 34-8133001 & Up 3433001 & Up 3448001 thru 3448037 767-359 PA-34-220T IV 3447001 & Up 3448038 & Up 767-359 PA-34-220T V 3449001 through 3449261; 3449263 through 3449312 95724-006 Replaces 95724-004 Table 2 Actuator Mount Bracket Kits d. Turn-stop boss failure on the strut upper tube assembly P/N 95720. 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.) SERVICE BULLETIN NO. 1123B PAGE 6 OF 12 Figure 2 Service Wear Limit Locations INSTRUCTIONS: (Continued) 3. Service Wear Limits 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. Table 3 Service Wear Limits SEE DETAIL VIEW A DETAIL VIEW A 9 4 3 2 1 8 7 6 5 SERVICE BULLETIN NO. 1123B PAGE 7 OF 12 Figure 3 Drag Link Over-Center Measurement Nose Gear Installation SERVICE BULLETIN NO. 1123B PAGE 8 OF 12 Figure 3A Nose Gear Installation NOTE: Upstop NOT installed on PA-34-200 aircraft S/N 34-7250001 through 34-7350135 unless Kit 760-699 has been complied with. INSTRUCTIONS: (Continued) 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 a. For Senecas serial numbers 34-7250001 through 34-7450220: Rigging of the nose gear installation (Item 13, Table 1) shall be accomplished per this Service Bulletin. The ‘over center’ measurement for the Seneca, as for all Senecas, shall be 0.250 or greater as measured from the center (See Figure 3). The Service Manual will be revised to delete reference to Service Bulletin 413. All required measurements are in this service bulletin and will be incorporated into the Service Manual. b. For Senecas II through V: Rigging of the nose gear installation (Item 13, Table 1) shall be accomplished per the appropriate Service Manual with the following exception for the Seneca II. The ‘over center’ measurement for the Seneca II, as for all Senecas, shall be 0.250 or greater as measured from the center (See Figure 3). The 0.250 dimension supersedes the 0.300 dimension which was incorrectly stated in the Seneca II Maintenance Manual. Refer to the Maintenance Manual for the procedure to make the over center measurement. This Service Bulletin supersedes Service Bulletin No. 413, Nose gear Drag Link Dimension Check. 4.2 Steering Arm Channel Clearance 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 clearance of 0.03 of an inch. Tighten the upper mounting bolts. SERVICE BULLETIN NO. 1123B PAGE 9 OF 12 Figure 4 Steering Arm Channel Clearance SERVICE BULLETIN NO. 1123B PAGE 10 OF 12 INSTRUCTIONS: (Continued) 4.3 Installation and Rigging of Nose Gear (Refer to Figures 3 and 3A) NOTE:. Installation and rigging instructions for the Seneca II aircraft will be revised to match the rigging instructions for the later Seneca models as follows. 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 strut 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 housing attachment assembly (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. 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. 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: After any up stop adjustment, the gear must be cycled to ensure the strut engages the stop under pressure. SERVICE BULLETIN NO. 1123B PAGE 11 OF 12 INSTRUCTIONS: (Continued) 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: 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. 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. 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. 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. SERVICE BULLETIN NO. 1123B PAGE 12 OF 12 MATERIAL REQUIRED: One (1) each, Nose Gear Hydraulic Jack Mount Assembly Kit, Piper part number 767-357; 767-358 or 767-359 (See Table 1 for correlation between the aircraft serial number effectivity and the correct Kit number required), Turn Limit Kit, Piper part number 767-368, NAS6207-50D bolt, Piper part number 693- 215, Steering Channel, New Piper part number 95394-005, if required, per aircraft. AVAILABILITY OF PARTS: Your Piper Field Service Facility. EFFECTIVITY DATE: This Service Bulletin is effective upon receipt. SUMMARY: Warranty is not available for this Service Bulletin. The kits available through this Service Bulletin are considered ‘product improvements’. 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: If you are no longer in possession of this aircraft, please forward this information to the present owner/operator and notify the factory of address/ownership corrections. Changes should include aircraft model, serial number, current owner's name and address. Corrections/changes should be directed to: THE NEW PIPER AIRCRAFT, INC. Attn: Customer Service 2926 Piper Drive Vero Beach, FL 32960