PIPER COMANCHE SERVICE MANUAL
04/01/09 V - SURFACE CONTROLS
1G17
NOTE: When determining the deflection angle of the flap use a bubble protractor. The angle
between the aircraft leveling lugs and the flaps when they are fully retracted should be 13°,
when the flaps are fully extended to 32° the angle should be 45°. Tolerances are ± 2°.
Measurement of flap angle is taken parallel with and next to the rib rivets 23 inches from
the inboard end of the flap.
NO
TE: Occasionally flaps are adjusted to compensate for wing heaviness with an adjustment
screw located between the center roller brackets of the flap. One flap may be adjusted with
the trailing edge below the neutral position to correct wing heaviness. The maximum
distance allowed below the neutral position is three turns on the adjustment screw. The
screw should be readjusted after rigging is completed.
5-20. Flap Controls. (PA-24-400.)
5-21. Removal Of Flap Control. (PA-24-400.) (Refer to Figure 5-9.)
A. Access for removal of the flap actuating mechanism and flap control cables within the fuselage may
be reached by removing rear seat and baggage compartment floor panel. Access to controls in the
wing may be reached by removing wheel well splash pan and access plate to the flap bellcrank.
B. Remove the flap transmission assembly by disconnecting the motor electrical leads, extracting pin
(16) at the transmission housing and removing bolt (23) at the forward section of the actuating
screw.
C. The actuating arms (15) are removed by disconnecting the flap push-pull control cables clevis, the
step lock release cable on the right arm, and the flap position sender rod. Remove the pivot bolt at
the top spar support tube and the flap guide bracket.
D. To remove the flap push-pull control cable (5) remove the clevis end and locknut from actuator end
of the cable. Disconnect the support clamps and draw the cable from its support tube. Within the
wing, disconnect and remove the clevis end at the flap bellcrank. Enter through the wheel well and
remove the support tube locknut. Draw the cable from the wing into the fuselage.
E. Disconnect the flap control rod and remove the bolt securing the bellcrank.
F. Removal of the step lock mechanism (44) and support cable (27), disconnect the return spring (43)
at the inboard side of the wheel well. Remove the aft wing fairing, the access plate located at the
inboard, under side of the flap and back the adjusting nut (45) off the cable end. Unbolt the
mechanism from the inboard and aft sides of the wing and remove with step lock and support cable.
5-22. Installation Of Flap Control. (PA-24-400.) (Refer to Figure 5-9.)
A. To install the flap actuating mechanism assembly, connect the control arms (14 and 15) to the upper
spar support tube and insert the pivot bolt. Tighten the bolt to a snug fit with no binding of the arms.
Install the flap guide bracket and connect the flap position sender rod (12) to the control arms.
B. The actuating motor and transmission may be installed as a unit. Place the transmission end
between the two brackets leading from the spar support, insert locking pin and safety. Connect the
actuating screw (22) to the lower portion of the actuating arms, insert bolt (23) and secure. Connect
the electrical leads to the motor, referring to the electrical diagram in Section IX. Operate the motor
to assure proper electrical hookup.
C. The flap bellcrank (6) may be installed by placing into position, installing the pivot bolt securing
the bellcrank and tighten to a snug fit. Install the flap control rod (33).
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