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.
