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9-1-70.  Ditching Power OFF
9-1-77.  Vertical Gyro (VGI) Malfunction

TM-1-1520-240-10 Army CH-47D Heilcopter (EIC:RCD) Manual
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TM  1-1520-240-10 9-1-28            Figure 9-1-9.  Ditching Exits 9-1-73.  Flight Controls. 9-1-74.  Longitudinal    Cyclic    Trim    (LCT)    System Failure. Should the system fail during cruise, with the cyclic trim system programmed for maximum forward tilt of the ro- tors, an abnormal nose-up attitude will result with de- creasing airspeed. Should one or both cyclic actuators fail in full retract position, airspeed must be limited ac- cording to Vne for retracted longitudinal cyclic trim. With both LCTs partially or fully retracted, maintain below Vne and if failure occurs extended, maintain airspeed at or above 60 KIAS or until the approach to landing. Should the longitudinal cyclic trim system fail, perform the follow- ing: CYCLIC TRIM circuit breakers — In. If cyclic trim opera- tion is not restored, proceed with the procedures below for AUTO or MANUAL modes of operation. If in AUTO mode: 1.   Airspeed — Adjust. 2.   CYCLIC TRIM switch — MANUAl. 3.   FWD and AFT CYCLIC TRIM switches  — Adjust for airspeed. If LCT operation is not indicated: FWD and AFT CYCLIC TRIM switches — RET for 30 seconds, before landing. If in MANUAL mode: 1.   Airspeed — Adjust. 2.   CYCLIC TRIM switch — AUTO. If normal LCT operation is not indicated: 1.   CYCLIC TRIM switch — MANUAl. 2.   FWD  and  AFT  CYCLIC  TRIM  switches  — RET both LCTS for 30 seconds, before land- ing. If both actuators are retracted, the landing will be normal. If one or both actuators fail in extended position, the pitch atitude of the helicopter will be higher than normal during the approach and will be dependent upon the amount of actuator extension at the time of the failure. Execute a shallow  approach  to  a  hover  or  to  the  ground  with  a normal touchdown, avoiding large cyclic changes. When the aft gear areon the ground, apply brakes and lower the nose. As the forward gear touch the ground, the aircraft will tend to accelerate more than normal.Continue to ap- ply brakes as necessary to prevent forward movement. If the helicopter is taxied with the actuators failed in the extend position, use minimum control applications and adjust the thrust control at ground detent or higher. There is  an  increased  susceptibility  to  droop-stop  pounding with this condition. 9-1-75.  Single AFCS Failure — Both Selected. A malfunction of the AFCS can usually be detected by an abrubt attitude change (hardover) or unusual oscilations in one or more of the flight control axes or by lighting of the NO.1 or NO. 2 AFCS OFF caution. If flight is con- ducted at low altitude such as contour or NOE, a climb to higher altitude must be iniated before the pilot attempts isolation of the defective system. 1.   Airspeed  — Reduce to 100 KIAS or Vne, whichever is slower. 2.   Altitude  — Adjust as required. NOTE A hardover in the opposite direction may oc- cur when the malfunctioning AFCS is turned off and the functioning AFCS reacts on the flight controls. 3.   AFCS   SYSTEM   SEL   switch —   Isolate defective   system.   Turn   NO.   1   ON,   if   not isolated, turn NO. 2 ON. If system is not isolated: AFCS SYSTEM SEL switch — OFF.







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