SERVICE LETTER No.997

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Piper Aircraft Corporation SERVICE No.997 LETTER Vero Beach, Florida, U.S.A. Date: May 14, 1987 S SUBJECT: Wing Removal and Reinstallation: Reference Airworthiness Directive 87-08-08 MODELS AFFECTED: SERIAL NUMBERSAFFECTED: PA-28-140 Cherokee PA-28-150/160/180 Cherokee PA-28-151 Warrior PA-28-161 Warrior Ii PA-28-181 Archer ii PA-28R-180 Arrow PA-28R-200 Arrow/Arrow ii PA-28R-201 Arrow iii PA-28R-201T Turbo Arrow iii PA-28RT-201 Arrow IV PA-28RT-201T Turbo Arrow IV PA-28-235 Cherokee PA-32-260 Cherokee Six PA-32-300 Cherokee Six 300 28-20000 through 28-7725290 28-l through 28-7505259 and 28-E13 28-7415001 through 28-7715314 28-7716001 through 28-8616057, 2816001 and up 28-7690001 through 28-8690056, 28-8690061, 28-8690062, 2890001 and 28R-30001 through 28R-7130013 28R-35001 through 28R-7635545 28R-7737001 through 28R-7837319 28R-7703001 through 28R-7803374 28R-7918001 through 28R-8218026 28R-7931001 through 28R-8631005, 2831001 and up 28-10001 through 28-7710089 and 28-E11 32-l through 32-7800008 32-40001 through 32-7840202 COMPLIANCE TIME: in accordance with Airworthiness Directive 87-08-08 PURPOSE: This Service Letter is intended to supplement Airworthiness Directive 87-08-08 by providing instructions for removal and reinstallation of wings on Piper PA-28 and PA-32 Model aircraft. APPROVAL: The technical contents of this Service Letter have been F.A.A. approved. INSTRUCTIONS: NOTE: FOR DETAILED INSTRUCTIONS REGARDING CABLE TENSIONS, CONTROL SURFACE TRAVELS, TORQUE VALUES, HYDRAULIC AND FUEL SYSTEM SERVICING PROCEDURES, REFER TO THE APPROPRIATE SERVICE/MAINTENANCE MANUAL. (over) ATA: 5711 SERVICE LETTER NO. 997 PAGE 2 OF 4 INSTRUCTIONS: (Cont’d) Wing Removal : 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. 11. 12. 13. 14. 15. 16. 17. 18. 19. 20. 21 . Disconnect aileron balance and control cables at turnbuckles within fuselage aft of spar or at bellcranks in wing as applicable. Remove cotter pins and/or cable guards from pulley bracket assemblies to brackets. allow cable ends to pass between pulleys and Disconnect flaps from the torque tube by ful the bolt and bushing from the bearing at the Disconnect fuel lines at fittings located at ly lowering flaps and removing aft end of the control rod. or near the wing butt Iine. CAUTION: TO PREVENT DAMAGEAND CONTAMINAT AND OTHER LINES, CAP OR PLUG ALL SEPARATED DURING WING REMOVAL. ION OF FUEL, HYDRAULIC LINE ENDS WHICH ARE Disconnect battery. Completely drain fuel system. Completely drain brake lines and reservoir. On PA-28R, drain hydraulic lines by separating lines at the main landing gear actuators. Remove access plates and wing to fuselage seals at wing butt rib. Remove seats forward and aft of spar carrythrough. Remove seatboard (if appIicabIe), spar carrythrough carpet and left and right interior side panels aft and forward of the spar carrythrough. Place aircraft on jacks. NOTE: TO FACILITATE REINSTALLATION OF CONTROL CABLES, FUEL AND HYDRAULIC LINES, MARK CABLE AND LINE ENDS AND/OR ATTACH A LINE WHEREAPPLICABLE TO CABLES BEFORE DRAWING THEM THROUGHFUSELAGE OR WING. Remove clamps and/or ties as required to release the electrical harness assembIy. Disconnect applicable electrical leads from the terminal strip assembly, (located on the aft spar frame, left side within the fuselage), by removing cover and appropriate nuts and washers. Access brake line fittings by removing lower forward air vent assemblies, if applicable. Disconnect brake lines at fittings located within the cockpit at the leading edge of the wing on the left and right sides; On PA-28R, disconnect hy draulic lines within the cockpit aft of the spar carrythrough. On the left side it wil I the cockpit at the wing Arrange a suitable fuse I Remove wing jacks. be necessary to disconnect the pitot tubes within butt Iine. age cradle and supports for both wings. Remove the front and rear spar to fuselage attach nuts, washers and bolts, discard nuts. (Note number and position of washers at each attach point for reinstalIation.) Remove eighteen (per wing) main spar to spar carry-through attach nuts, washers and bolts, discard nuts. (Note position of shims at top spar cap for reinstallation.) PAGE 3 OF 4 SERVICE LETTER NO. 997 INSTRUCTIONS: (Cont’d) WARNING: USE EXTREMECARE IN REMOVING BOLTS TO PRECLUDE DAMAGE TO THE BOLT HOLES IN MAIN SPAR AND SPAR CARRYTHROUGH. NUMBEREACH BOLT AND BOLT HOLE UPON REMOVAL OF BOLT TO ASSURE REINSTALLATION OF BOLTS IN ORIGINAL LOCATIONS. 22. Slowly and very carefully extract wing from fuselage being certain all electrical leads, cables and I i nes are disconnected and that no undue upward or downward pressure Is exerted upon the inboard spar within the spar carrythrough. NOTE: INSPECT WING SPAR N ACCORDANCEWITH AIRWORTHINESS DIRECTIVE 87-08-08 . Wing lnstallation : 1. 2. 3. 4. 5. 6. 7. 8. 9. 10. WARNING: IF REPLACEMENTOF BOLTS IS REQUIRED, ENSURE PROPER GRIP LENGTH IS MAINTAINED. INSTALL NEW NUTS ON MAIN SPAR AND FORWARDAND AFT SPAR ATTACH BOLTS, SEE APPROPRIATE PARTS CATALOG FOR PROPER HARDWARE . Ascertain that the fuselage is solidly positioned on the support cradle. Place wing in position for Installation a few inches away from the fuselage. Prepare the various lines , cables and electrical leads for inserting into the wing or fuselage when the wing is slid into place. Insure that the front wing fitting bushing is installed. Slide the wing into position In the fuselage, assuring that the lines, cables and electrical leads are fed into place. Install the eighteen (per wing) main spar to spar carrythrough attach bolts. (Note: Top spar cap shims must be in position prior to installing bolts.) IF REINSTALLING ORIGINAL BOLTS MARKED PER REMOVAL NOTE: INSTRUCTIONS, REINSTALL IN CORRESPONDINGHOLES. IF NEW BOLTS ARE USED, INSTALL IN ACCORDANCEWITH THE BOLT LEGEND IN THE APPLICABLE SERVICE/MAINTENANCE MANUAL. Install front and rear spar to fuselage attach bolts. Refer to applicable Service/Maintenance Manual for correct installation of washers.