DQ-142

Question 1

Q1. In cruise flight an AC power failure causes a Stabilator Auto mode failure. Explain the actions required to regain control? If ac power is not restored how can the stabilator be controlled?

Answer 1

Helicopter shall be slowed to 80 KIAS before power is restored. AUTO CONTROL RESET may be pressed to reengage the AUTO MODE.

If AC power is not restored, auto mode is not avail. Press master caution reset to turn off beeping tone, and manually slew the stabilator with the cyclic mounted stab. Slew up switch, or the Man slew up switch on the stabilator control panel.

Question 2

Q2. During shutdown, when turning GENERATORS NO. 1 and NO. 2 switches – OFF, the Stabilator Auto mode fails. Is this a system malfunction?

Answer 2

No. Either the APU is not running, or the APU generator is OFF, and therefore the #2 DC primary bus is not energized, causing the stabilator auto mode to fail.

OR

The battery is causing it to fail?

(Im a bit unsure about this one)

Question 3

Q3. During takeoff and acceleration if the stabilator auto mode fails which of the following will cause a loss of longitudinal control.

Descending left turn

Hardover signal to one of the actuators

Collective is decreased ✔

Continued flight above 70 KIAS

Answer 3

Collective is decreased ✔

“WARNING

If acceleration is continued or collective is decreased with the stabilator in a trailing edge down position, longitudinal control will be lost …”

Question 4

Q4. When the APU generator is turned on during run-up there is a knocking in the rotor system, it is noted SAS 1 is ON. What caused the knocking and how is it stopped?

Answer 4

Malfunction of the SAS 1. (Erratic movement of the helicopter can be felt, with no accompanying failure advisory) If this occurs, SAS 1 shall be turned off.

Question 5

Q5. The FLT PATH STAB caution and airspeed fault advisory light illuminate and will not reset, list the system(s) that will/may be affected and any pilot action?

Answer 5

The stabilator. Continued flight above 70 KIAS with the stabilator in the AUTO mode is unsafe since a loss of the airspeed signal from the remaining airspeed sensor would result in the stabilator slewing full down.

Pilot action:

Manually slew stabilator to 0 degrees if above 40 KIAS.

Land as soon as practicable.

Question 6

Q6. Explain what Critical torque is and what would occur If an engine malfunctions when operating above CT?

Answer 6

Dual engine torque value, which when exceeded, may not allow the aircraft to maintain % RPM R within normal limits under single-engine operations in the same flight conditions.

Essentially, in conditions that require DE TQ greater than CT, pilot is operating outside aircraft low ETF single-engine capability. If single engine failure occurs, pilot must immediately adjust TQ, airspeed and/or GW to achieve SE capability.