Piper Aircraft Corporation Malibu Mirage PA-46-350P, Airplane Maintenance Manual

Page: 546 / 1956

PAGE 8
Feb 28/07
3D2
27-10-00
PIPER AIRCRAFT, INC.
PA-46-350P, MALIBU MIRAGE
MAINTENANCE MANUAL
6 Remove the bolt, washers, and nut securing the control column tube to the quadrant
shaft and separate the tube from the shaft. Make a note of washer buildup for
reinstallation.
NOTE: The control column stop assy is fitted over the tube, secured by the same
bolt, and will be removed with the tube.
7 The control column can now be removed by lifting the forward end and sliding the
assembly forward until the tube clears the instrument panel.
(2) Installation
(a) Forward column assembly:
NOTE: Check bearing on instrument panel for security. If it is loose, use LOC-498-50 or
LOC-495-50 Super Bond adhesive to bond bearing onto instrument panel.
1 Place the control column assembly under and behind the instrument panel, keeping
the forward end raised until the aft end of the tube can be inserted into the bearing in
the instrument panel. Slide the assembly aft and lower the forward end to its installed
position.
2 Ensuring the control column stop assembly is in place over the forward end of the
control column tube, slide the tube over the quadrant shaft. Secure the control
column tube and control column stop assembly to the quadrant shaft with bolt,
washers, and nut.
3 Attach the arms on the control column to the arm on the elevator torque tube. (The
bolt beads should point outboard.)
4 Reconnect the control wheel switches electrical harness (if installed.)
5 Attach the primary and control wheel balance cables to the aileron quadrant at the
forward end of the control column assembly and secure each cable end retainer (i.e.
- lockplate) with a screw (see note below). Safety the cable end retainer screws with
MS20995-C32 safety wire.
NOTE: As of early 2006, the original MS35265-42 fillister head screw has been
replaced by a higher strength MS24674-8 (P/N 520-036) socket head screw.
In earlier airplanes, anytime the cable end retainer screws are removed, if
the original fillister head screws are still installed, they must be replaced with
the socket head screws upon reassembly. Additionally, when using the
MS24674-8 (P/N 520-036) socket head screws, torque to 12 to 15 in.-lbs.
6 Remove the aileron primary cable blocks from the pulleys at F.S. 100.00.
(b) Control wheel:
Install control wheel as described for the appropriate serial number range under Control
Wheel, above.
(c) Rig the aileron control system in accordance with instructions given in this chapter.
Ensure that turnbuckles are safetied with locking clips and that protective tube is installed
over turnbuckle on the control wheel balance cable.
(d) Check the system for proper operation and freedom from binding.
3. Aileron Control Cables (See Figure 4.)
A. Removal
(1) For removal of any control cables in the fuselage or wings, first determine which cables are to
be removed and then proceed with the appropriate set of instructions which follow.
(2) To remove either right or left primary control cables that are located in the fuselage, the
following procedures may be used.