Table 7-2. Simulated Malfunction Details - Continued
Method of
Indications and effects on
Effects sensed by trainee
introduction
related systems as presented
if corrective action is
Malfunction
by instructor
to the instructor and trainee
not taken
Longitudinal
667 (Forward)
If CYCLIC TRIM function switch
Level fuselage attitude
cyclic trim
668 (Aft)
is in AUTO, pointer(s) on CYCLIC
is not maintained as
669 (Both)
TRIM indicator(s) does not change
airspeed is increased or
when making a speed change.
decreased.
NOTE
Switching to the MANUAL mode for malfunctions 667, 668, and 669 enables the system to be managed in that
mode with no malfunction effects.
Longitudinal
670
If CYCLIC TRIM function switch
Level fuselage attitude
cyclic trim
is in MANUAL, actuators do not
is not selectable by man-
manual
respond to manual EXT or RET
ual longitudinal cyclic
switch inputs.
trim system operation.
Thrust control
671
Operation of THRUST CONT BRAKE
10 to 20 pounds of force
rod brake switch
TRIGGER fails to release mag-
are necessary to move
netic brake on thrust rod.
thrust rod.
Thrust control
672
Same as 671. Corrective action
Same as 671.
rod brake
attempts of pulling THRUST
BRAKE circuit breaker do not
affect system.
Thrust cockpit
673
Loss of altitude hold, creeping
Loss of altitude hold,
control driver
thrust control rod, or rapid
creeping thrust control
actuator (CCDA)
change in altitude or torque.
rod, or rapid change in
altitude or torque.
7-20
