Piper Comanche PA-24 Service Manual page 278

D. The flap push-pull control cable may be installed by drawing the cable from the fuselage into the
wing. Place the cable end through the support tube, locknut and to the flap bellcrank. Install the
cable end and connect to the bellcrank. Secure and safety the locknut at the support tube. Within the
fuselage, insert the cable through the support tube and locknut, secure and safety.
E. To install the step lock mechanism (44) and return cable (27) in the right wing, enter through the
wheel well and install the lock mechanism with the return cable wrapped around the pulley and
secured. Insert the cable end to the flap, through the trailing edge of the wing and into the flap. Start
the adjusting nut (45) a few threads onto the cable end. Draw the tension spring in place at the
inboard side of the wheel well Attach the step lock release cable to the lock release and to the
control arms within the fuselage. Install cable pulley and secure.
F. Rig and adjust per Paragraph 5-23 and reinstall access panels, wheel well splash pan, rear seat, etc.
5-23. Rigging And Adjustment Of Flap Control. (PA-24-400.) (Refer to Figure 5-9.)
A. Adjust the flap control rod (33) to a length of 5-5/16 inch from center hole in rod end bearing to
center hole in fork.
B. With flap push-pull cables disconnected, adjust the up limit switch (11) (rear switch) to obtain a
dimension of .375 inch ± .062 inch between forward face of transmission housing and rear edge of
the transmission sleeve assembly (22). Move the flap selector switch in the down position, moving
the control arms (14 and 15) away from the up limit switch (11) until the adjustment screw is clear
of the up limit switch. Move the selector switch to the up position and let the system deactivate
itself, check the .375 inch dimension.
NOTE: When determining the deflection angle of the flap use a bubble protractor. The angle between
the aircraft when level and flaps when they are fully retracted should be 13°, when the flaps
are fully extended to 38° the angle should be 51°
parallel with and next to the rib rivets 23 inches from the inboard end of the flap.
NOTE: Occasionally flaps are adjusted to compensate for wing heaviness with an adjustment
screw located between the center roller bracket 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.
C. Place the flaps in full up position and adjust the clevis fitting on the control arms (14 and 15) so that
the clevis bolt may be inserted through the clevis and the slot in the control arms (14 and 15). The
bolt should fit snug against the forward radius of the slot in the control arms (14 and 15). Ascertain
that a wire cannot be inserted through the minimum thread hole of the clevis ends both in the
cockpit and wings. Secure in position with the jam nuts.
D. With the flaps fully retracted, adjust the step lock release cable within the fuselage so there is no
slack in the cable and the step lock cable adjusting nut (45) at the flap to .125 inch travel in the flap.
E. To make the flap down adjustment, run the flaps to a measured 38° down position. The down limit
switch (9) adjustment screw is then turned out until the down limit switch is activated and then
screwed out an additional 1/2 turn. Secure adjustment screw with jam nut. Retract flaps to clear
adjustment screw from switch, then extend the flaps allowing the system to deactivate itself and
check flap travel.
F. Position the flaps in the 15° extended location. Then adjust rod (12) so the hand on the flap position
indicator on the instrument panel is positioned at the bottom of the white arc. Operate the flap
system and check for proper operation. Check turnbuckles and push-pull rods for safeties.
V - SURFACE CONTROLS
PIPER COMANCHE SERVICE MANUAL
1°. Measurement of flap angle is taken
±
1G18
04/01/09