Table 7-2. Simulated Malfunction Details (cont)

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