8. Check all travels with specifications given in Figure 27-14.
9. Determine the free play of the rudder tab with the rudder securely held against either stop. Total free
travel measured at the tab trailing edge must not exceed 0.15 inch. If this tolerance is exceeded, check
the travel control arm assembly for wear at the center bolt and bolt attaching the rudder trim rod to the
control arm. Replace the arm assembly and associated hardware if there is any noticeable wear or
elongation of the holes. Check the rudder trim barrel end play in the mounting bracket.
RUDDER PEDAL ASSEMBLY.
REMOVAL OF RUDDER PEDAL ASSEMBLY. (Refer to Figure 27-17.)
1. Remove the access panel to the aft section of the fuselage.
2 . Relieve rudder and stabilator cable tension by loosening one of the rudder and stabilator cable
t u r nb u c kles in the aft section of the fuselage.
3. Remove the fuel selector knobs and cover panels by removing the attachment screws.
4. Remove the tunnel plate just aft of the tee bar by laying back enough tunnel carpet to remove the plate
attachment screws.
5. Disconnect the stabilator control cable from the lower end of the tee bar assembly.
6. Remove the tee bar attachment bolts with their washers and nuts which are through each side of the
floor tunnel. Pull the lower end of the tee bar aft.
7 . Disconnect the control cable ends from the arms on the torque tube by removing the cotter pins, washers,
nuts and bolts.
8. Disconnect the rudder trim from the torque assembly by removing the cotter pin, washers and bolt that
connects the arm to the trim.
9. Disconnect the close-out rods at the rudder pedals by removing nuts and bolts.
10. Disconnect the brake cylinders at the lower end of each cylinder rod by removing the cotter pins,
washers, nuts and bolts.
11 . Disconnect the vee braces (two braces are used with right hand brakes) from the torque tube by
r e m o ving nuts, washers and bolts that secure the strap bracket to the vee brace.
12. If an AutoPilot amplifier is installed over the torque tube at the right side of the fuselage, disconnect
the electrical plug and release the two fasteners that secure it to its mounting bracket.
13. Disconnect the torque tube support bracket where it attaches to the floor tunnel by removing its attach-
ment bolts.
14. Remove the two bolts that extend through the torque tube and are located at the center of the tube
assembly over the floor tunnel. Compress the tubes.
15. Disconnect the torque tube support blocks from their support brackets on each side of the fuselage by
removing the attachment nuts, washers and bolts.
16. Remove the trim side panels, if desired.
17. Remove the assembly from the airplane. Note the spacer washer on each end and between the support
blocks.
INSTALLATION OF RUDDER PEDAL ASSEMBLY. ( Refer to Figure 27-17.)
1. Assemble the torque tube assembly as shown in Figure 27-17. Do not install the two bolts through the
center of the tube assembly at this time.
2. Place the upper support blocks on the ends of the torque tube assembly. Note that a washer is required
on each end of the tube.
3. Position the support blocks on their mounting brackets at each side of the fuselage and secure with
bolts, washers and nuts. Note that a bushing is required in the bolt holes of the upper support block,
and a plate on top of the upper block, between the upper and lower blocks and under the block
m o u n ting bracket.
PIPER AIRCRAFT
PA - 4 4 - 1 8 0 / 1 8 0 T
AIRPLANE MAINTENANCE MANUAL
27-20-05
Page 27-28
Revised: June 20, 1995
1L6
Summary of Contents for SEMINOLE PA-44-180
Page 38: ...CHAPTER DIMENSIONS AND AREAS 1B14...
Page 49: ...CHAPTER LIFTING AND SHORING 1C1...
Page 53: ...CHAPTER LEVELING AND WEIGHING 1C5...
Page 58: ...CHAPTER TOWING AND TAXIING 1C10...
Page 62: ...CHAPTER PARKING AND MOORING 1C14...
Page 65: ...CHAPTER REQUIRED PLACARDS 1C17...
Page 70: ...CHAPTER SERVICING 1C22...
Page 98: ...CHAPTER STANDARD PRACTICES AIRFRAME 1E2...
Page 108: ...CHAPTER ENVIRONMENTAL SYSTEM 1E12...
Page 189: ...CHAPTER AUTOFLIGHT 1H21...
Page 192: ...CHAPTER COMMUNICATIONS 1H24...
Page 202: ...CHAPTER ELECTRICAL POWER 1I10...
Page 228: ...CHAPTER EQUIPMENT FURNISHINGS 1J12...
Page 233: ...CHAPTER FIRE PROTECTION 1J17...
Page 238: ...CHAPTER FLIGHT CONTROLS 1J24...
Page 304: ...2A18 CHAPTER FUEL...
Page 325: ...2B17 CHAPTER HYDRAULIC POWER...
Page 357: ...2D1 CHAPTER ICE AND RAIN PROTECTION...
Page 414: ...CHAPTER LANDING GEAR 2F13...
Page 479: ...2I6 CHAPTER LIGHTS...
Page 488: ...2I16 CHAPTER NAVIGATION AND PITOT STATIC...
Page 503: ...2J7 CHAPTER OXYGEN...
Page 524: ...2K6 CHAPTER VACUUM...
Page 535: ...2K19 CHAPTER ELECTRICAL ELECTRONIC PANELS AND MULTIPURPOSE PARTS...
Page 546: ...INTENTIONALLY LEFT BLANK PA 44 180 180T AIRPLANE MAINTENANCE MANUAL 2L6 PIPER AIRCRAFT...
Page 547: ...2L7 CHAPTER STRUCTURES...
Page 582: ...CHAPTER DOORS 3A18...
Page 593: ...CHAPTER STABILIZERS 3B8...
Page 604: ...CHAPTER WINDOWS 3B22...
Page 611: ...CHAPTER WINGS 3C10...
Page 624: ...CHAPTER PROPELLER 3D1...
Page 643: ...CHAPTER POWER PLANT 3D21...
Page 667: ...CHAPTER ENGINE FUEL SYSTEM 3F1...
Page 681: ...CHAPTER IGNITION 3F16...
Page 712: ...CHAPTER ENGINE INDICATING 3H1...
Page 730: ...CHAPTER EXHAUST 3H19...
Page 734: ...CHAPTER OIL 3I1...
Page 743: ...CHAPTER STARTING 3I11...
Page 755: ...CHAPTER TURBINES 3J1...