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e.   Yaw axis test
14.  LH  Fuel  System  CHECK

TM-1-1520-240-MTF Army Model CH-47D Heilcopter (EIC:RCD) Manual
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TM 1-1520-240-MTF 2-69 B HOVER (CONT.) (2)   Trim     to     a     stable     hover.     Without operating  the  magnetic  brake  switch, apply a 5_- 7_ bank angle to produce a sideward  velocity.  Return  longitudinal stick to the trim detent. The helicopter shall  maintain  the  commanded  bank angle and hold its original heading (3_) during sideward flight. (3)   Repeat step (2), flying sidewards in the opposite direction. g.   Hover check (NO.1 AFCS). With the aircraft trimmed   in   pitch,   roll,   and   yaw,   AFCS SYSTEM SEL — NO.1 and repeat the tests on step b. thru f. Then set AFCS SYSTEM SEL switch to both. h.   Hover check (NO.2 AFCS). With the aircraft trimmed   in   pitch,   roll,   and   yaw,   AFCS SYSTEM SEL — NO.2 and repeat the tests on step b. thru f. Then set AFCS SYSTEM SEL switch to both. CAUTION Barometric altitude hold shall not be used in a   hover.   Rotor   downwash   and   turbulence changes the reference pressure to the altitude hold transducer. i.   Radar altitude hold. RAD ALT — ENGAGED. Check segment lighted. Check radar altitude hold response while hovering at a known true altitude of at least 25 feet. Altitude shall be held within 5 feet.







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