TM 1-1520-240-MTF
2-72
B HOVER (CONT.)
b.
714A Torque Differential Check.
(1) While stable on the ground, flat pitch,
100% RRPM and FADEC in PRI move
No. 2 ECL to the Ground detent. Ensure
RRPM is 100%. Increase thrust until
aircraft is stabilized at 5 to 20 foot aft
wheel height while ensuring RRPM is
100%. Record TQ and N1 values on No.
1 engine when stabilized.
(2) Maintaining a constant thrust position
slowly bring the No. 2 ECL to the FLT
position while monitoring the RRPM at
100%. Reduce No. 1 ECL smoothly to
the ground position while monitoring
RRPM at 100%. When No. 1 ECL is at
GND position record TQ and N1 values
on the No. 2 engine.
(3) Smoothly decrease thrust to ground
detent. Smoothly advance No. 1 ECL to
flight position. Ensure RRPM 100%.
(4) Difference will be no greater than 6%
between No. 1 and No. 2 ENG TQ
values.
17. Droop Eliminator.
a. Establish 100 percent rotor rpm in the
ground detent.
b. AFCS SYSTEM SEL — BOTH.
c. Lift off to stabilized hover, 15 to 20 feet aft
wheel height.
d. Check 100% rotor rpm (+0 -1.0%),
maximum stabilized droop. Maximum
stabilized torque split 712 6%, 714A 4%.
