Piper PA-24 Comanche, Руководство по обслуживанию, Страница: 275 / 846

PIPER COMANCHE SERVICE MANUAL
04/01/09 V - SURFACE CONTROLS
1G15
5-16.
Electrically Operated Flaps.
5-17.
Removal Of Electrically Operated Flap Controls.
(PA-24-250 and PA-24-260.) (Refer to Figure 5-9.)
A. Access for the removal of the flap actuating mechanism and flap control cable within the fuselage
may be reached by removing the rear seat. Access to the controls in the wing may be reached by
removing the 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
(19) at the transmission housing and removing bolt (23) at the forward section of the actuating screw.
C. Actuating arms (14 and 15) are removed by disconnecting control cables (2 and 5) at the arms, the
flap position sender rod and removing the pivot bolt at the top spar support tube.
D. To remove the control cable (2) located in the fuselage, remove the cable pulley(s) and disconnect
turnbuckle (46) located inside the fuselage. On the PA-24-180, PA-24-250, PA-24-260 Serial Nos.
24-4000 to 24-4246, 24-4248 to 24-4299 disconnect tension spring (42) with left turnbuckle.
E. The control cable located in the wing may be removed by entering through the wheel well and
removing the cable pulley. Disconnect the cable at the bellcrank and draw the cable through the
fuselage or wheel well.
F. To remove the bellcrank disconnect the flap control rod (33) and bellcrank return spring (4) at the
bellcrank, remove the bolt securing the bellcrank.
G. To remove the left flap return cable, enter through the wheel well and disconnect the cable spring
(43) at the inboard side of the wheel well. Disconnect the other end at the leading edge of the flap.
H. Removal of the right flap return cable and step lock mechanism is accomplished by disconnecting
the return spring (43) at the inboard side of wheel well. Remove the aft wing fairing, the access
plate located at the inboard, under side of flap, and back the adjusting nut (45) off the cable end.
Unbolt step lock pulley mechanism (44) and withdraw support cable.
5-18.
Installation Of Electrically Operated Flap Contr ol
. (PA-24-250 and PA-24-260.) (Refer to Figure
5-9).
A. To install the flap actuating mechanism assembly, connect the actuating 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
arm. Connect the flap position sender rod (12) to the actuating arm.
B. The actuating motor and transmission may be installed as a unit.
NOTE: Refer to Lubrication Chart Special Instructions for specific lubrication instructions of flap
transmission assembly.
Place the transmission end between the two brackets leading from the spar support insert locking
pin (19) and safety. Connect the transmission 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) and bellcrank return spring (4).
D. The control cable that leads from the fuselage to the wing may be installed by connecting the cable
to the bellcrank and drawing it through the wing into the fuselage. Enter through the wheel well and
install the cable pulley.