ABI 180/185 Tail Gear Assembly Installation and ICA Manual

not have bolt through holes (ABI-0742152-2). Ensure that the stopper is fully seated onto the spring. 5.2.3 Bolt the saddle assembly (ABI-0742146-10) onto the spring (ABI-0742152-2) as shown in Figure 1. Use the (2) NAS6205-31 bolts supplied with the assembly along with the (4) NAS1149F0532P washers and (2) MS21042-5 nuts supplies with the assembly. Torque the bolts to 160 in-lbs. ABI 180/185 TAIL GEAR ASSEMBLY INSTALLATION AND ICA MANUAL Doc. No. ABI-12-5 Revision A, 7-10-14 Page 7 of 10 5.2.4 Insert both angled Bushings (ABI-0742112) into the fuselage aft saddle castings so that the bushings are flush with the exterior of the aircraft. 5.2.5 Insert the assembled spring assembly into the spring receptacle in the aft fuselage, ensure that it is seated to the stop. 5.2.6 Insert the (2) thick ABI-0742179-1 washers between the spring saddle and the casting on the aft fuselage (one on each side). 5.2.7 Insert as many ABI-0742100-6 washers as necessary to fill in the gap between the thick ABI-0742179-1 washers and the fuselage saddle castings. Note: it is possible that no washers will be required. 5.2.8 Insert the saddle tube (ABI-0742150-2) through the aft fuselage saddle castings. Note ensure that the clevis holes in the saddle tube align with the clevis holes in the saddle. 5.2.9 Insert the (2) MS20392-1C33 clevis pins through the saddle and saddle tube to ensure that the saddle tube is retained. Capture each clevis pin with a MS24665- 134 cotter pin to retain the clevis pin. 5.2.10 Mount the removed tail wheel assembly onto the new tail gear assembly. CAUTION! LUBRICATE UNPAINTED END OF TAIL SPRING WITH RUST PREVENTATIVE OIL OR GREASE BEFORE INSTALLING TAIL WHEEL ASSEMBLY. THIS WILL HELP PREVENT FUTURE CORROSION AND GALLING OF THE ALUMINUM DURING INSTALLATION. 5.2.11 Re-attach the steering cables onto the tail wheel assembly. Ensure that the tail wheel rotates freely and that the tail gear assembly is secure. 5.2.12 Re-assembly the tail cone assembly to the aft fuselage. 5.2.13 Lower the aft fuselage and remove the padded stand. 5.3 WEIGHT AND BALANCE COMPUTATIONS Weigh the tail gear assembly that was removed. Subtract from new weights to derive weight increase/decrease created by the ABI 180/185 tail gear assembly installation. Mu l tip l y weight increase/decrease by applicable aircraft moment and revise weight and balance information in the aircraft records. 5.3.1 WEIGHT AND BALANCE DATA ABI 180/185 tail gear assembly installed weight: 11.13 LBS ABI 180/185 TAIL GEAR ASSEMBLY INSTALLATION AND ICA MANUAL Doc. No. ABI-12-5 Revision A, 7-10-14 Page 8 of 10 6.0 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS This section is designed to provide aircraft technicians with sufficient information to inspect and repair the ABI 180/185 tail gear assembly 6.1 INSPECTION BEFORE FLIGHT 6.1.1 Prior to each flight, visually inspect the tail gear assembly to ensure that there is no excessive corrosion, cracks or other visible damage. Any indication of these would require the tail gear assembly to be further inspected in accordance with the Inspection and Repair procedures presented below. 6.1.2 At each 100 hour and annual inspection, inspect and service the tail gear assembly in accordance with the Inspection and Repair procedures in Section 6.2. 6.2 TAIL GEAR INSPECTION AND REPAIR 6.2.1 Inspect the spring assembly for corrosion, cracks, nicks or other physical damage. Obvious cracks and severe corrosion are cause for rejection of the part. A further inspection using the dye penetrant method should be performed on any part whose serviceability is questionable. Small nicks, scratches and pits may be blended out and polished with fine (400 grit) sandpaper and then painted for corrosion resistance. 6.2.2 Move the tail of the aircraft side to side and visually inspect for play between the fuselage and the tail gear assembly. If excessive play is observed check the torque of the saddle bolts and the bolts attaching the tail wheel assembly. If after checking the saddle bolts and tail wheel bolts torque, excessive play is sti ll pre sent, remove the tail gear assembly from the fuselage. Remove the saddle assembly and tail wheel assembly from the spring. Check the saddle, tail wheel, and spring bolt holes for wear. If the bolt holes are worn on the spring, replace the saddle and spring assembly. If the bolt holes are worn on the saddle, replace the saddle. If the bolt holes are worn on the tail wheel assembly, replace the tail wheel assembly. Note: The spring is a heat treated and stress relieved component so drilling or reaming oversized holes in the spring is not acceptable. With the tail gear assembly removed from the fuselage check all washers, bushings, and stoppers for wear and overall condition. Replace all worn components with new ABI parts. 6.2.3 Remove and Install according to Section 5.0 “Installation Instructions” of this document. ABI 180/185 TAIL GEAR ASSEMBLY INSTALLATION AND ICA MANUAL Doc. No. ABI-12-5 Revision A, 7-10-14 Page 9 of 10 AIRWORTHINESS LIMITATIONS The airworthiness Limitations section is FAA approved and specifies maintenance required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. There are no limitations associated with this modification 2 COTTER PIN MS24665-134 12 2 CLEVIS PIN MS20392-1C33 11 2 NUT MS21042-5 10 4 WASHER NAS1149F0532P AN960-516L OR 9 2 BOLT ITEM PartNo DESCRIPTION QTY 1 ABI-0742152-2 TAILGEAR SPRING 1 2 ABI-0742146-10 SADDLE ASSEMBLY 1 3 ABI-0742150-2 SADDLE TUBE - LONG 1 4 ABI-0742151-1 SPRING STOPPER 1 5 ABI-0742112 BUSHING 2 6 ABI-0742100-6 WASHER 2 7 ABI-0742179-1 WASHER 2 8 NAS6205-31 REVISIONS REV. DESCRIPTION DATE APPROVED A ADDED -1 TO WASHER PART NO. CORRECTED ASSY DRAWING NO. 8/5/2013 ABI B ADDED NOTE FOR BOLT TORQUE. 8/21/2013 ABI C ADDED ITEM 9 OPTION FOR NAS1149 UPDATED ITEM 8 TO NAS6205-31 7/9/2014 JLP TWO PLACE DECIMAL ALASKAN BUSHWHEEL Inc. IS PROHIBITED. KSE KELLER 2/20/2013 ABI-0742152 ASSEMBLY 5 2 1 2 3 A B C D E F G H H G F E D C B A 6 8 1 4 5 6 7 TAIL GEAR SHEET 1 OF 1 3 C 8 SCALE: 1:2 DWG NO. / PART NO. WEIGHT: C REV SIZE .02 4 7 COMMENTS: PROPRIETARY AND CONFIDENTIAL THREE PLACE DECIMAL .005 DRAWN CHECKED ENG APPR. MFG APPR. Q.A. DATE NAME TITLE: DIMENSIONS ARE IN INCHES TOLERANCES: FRACTIONAL ANGULAR: MACH BEND THE INFORMATION CONTAINED IN THIS DRAWING IS THE SOLE PROPERTY OF ALASKAN BUSHWHEEL Inc. ANY REPRODUCTION IN PART OR AS A WHOLE WITHOUT THE WRITTEN PERMISSION OF ABI LLC 9 4 6 7 1 5 3 6 8 9 7 5 11 2 10 12 NOTES: 1. TORQUE NUTS ON ATTACHMENT BOLTS (#8) PER CESSNA 100 SERIES SERVICE MANUAL.