Page 404 - (KU)01-75GAJ-1.5 - Change 1

INTRO

EP'S (KU)01-75GAJ-1.5 FIGURES

1.12.1.9 Rudder, Aileron or Elevator Autopilot Servo
Clutch Failure ACAWS

The autopilot servos are powered anytime there is electrical power
applied to the airplane. Therefore, while the autopilot is disengaged, a GROUND
failure of the autopilot servo clutch to de-clutch in the rudder, aileron,
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the controls against the force generated by the affected autopilot servo. TAKEOFF
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landing or go-around will be possible.
FIRE/SMK
NORM A. Autopilot....................................................................Disengage (PF)

B. CP AUTOPILOT SERVO ECB (827).................................PULL (PM) PRES/OXY
NOT FOR FLIGHT
C. P AUTOPILOT SERVO ECB (427)..................................PULL (PM)
ENG/PROP
(End of Procedure)

1.12.2 FLAPS SYSTEM FAILURE FUEL

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failure. The utility hydraulic system supplies hydraulic pressure for AAR
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electrical control system fails. Also, a system comprising a handcrank, HYD
input shaft, and manual shift handle is provided for mechanical operation
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Figure 1-5 for a diagram of Flap Emergency Controls. FLT CTRL

WARNING
GEAR

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PERF resulting in a change in trim about the roll axis and
aileron binding. If the aircraft is controllable, do not
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SHUFHQW WRZDUG WKH SRVLWLRQ RI WKH XQFRQWUROODEOH ÀDS
'XULQJ ÀDS PRYHPHQW FKHFN DLOHURQ FRQWURO FRQVWDQWO\ LANDING
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DITCHING
NOTE

Any suspected or known structural failure that may cause BAILOUT
aircraft control problems will require a Controllability
Check prior to landing.
OPER FAULT LG

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