B HOVER (CONT.)
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
17. Droop Eliminator.
a. Establish 100 percent rotor rpm in the
b. AFCS SYSTEM SEL BOTH.
c. Lift off to stabilized hover, 15 to 20 feet aft
d. Check 100% rotor rpm (+0 -1.0%),
maximum stabilized droop. Maximum
stabilized torque split 712 6%, 714A 4%.