TD15 Flashcards
The 701D engine on the UH-60M has the DECs or EDECUs that replace the ECUs found in the UH-60A. The DECs or EDECUs provides significant droop improvement how?
Explain how and when the DEC limits TGT.
The transient compensation system provides significant droop improvement during some maneuvers by monitoring engine torque, collective rate of change, and NR rate of change.
The temperature limiting system limits fuel flow when the TGT reaches the dual engine 10 minute limiting value of approximately 879°C. The automatic contingency power limiting will switch to a higher single-engine 21⁄2 minute temperature limiting value of approximately 903°C when the opposite Q is less than 50%. Fuel flow is regulated to hold a constant TGT.
List the three times the EDECU will bypass the 10 minute limiter.
On engines with the EDECU installed, the TGT will bypass the 10 minute limiter and limit at the 2.5 minute contingency power setting when any of the following conditions are met:
NP drops below 96%;
greater than 3% droop between reference NP and actual NP;
greater than 5% per second NP droop rate exists and NP less than or equal to NP reference speed.
Discuss the heading hold functions in FPS above and below 50 knots.
In the yaw axis, the FPS provides heading hold at airspeeds below 50 knots and heading hold or turn coordination above 50 knots.
Below 50 knots, the helicopter maintains the last trimmed heading when the pilot removes their feet from the pedals. To change heading, the pilot can use pedals to adjust and retrim to a new heading and the four-way collective trim beeper to slew to a new heading.
Above 50 knots, the system also provides turn coordination in addition to heading hold.
In the event of an electrical failure, the ENG A/I start/bleed valves are going to revert to the __________ mode.
What advisory activates?
How much Q will be lost from
MAX TQ available?
anti-icing
ENG 1 ANTI-ICE ON or ENG 2 ANTI-ICE ON advisory.
10% Q.
Operating an engine against the __________ is prohibited on rotor brake equipped helicopters. When using the rotor brake before starting engines, the minimum pressure will be ______ psi. If inadvertent rotor blade movement should occur due to rotor brake slippage, immediately _________ engine(s) or _____________.
During engine run-up, for rotor brake operations, ensure that approximately 45% NR for single engine operations and 57% NR for dual engine is reached prior to advancing PCLs to fly.
gustlock
450
shutdown
release rotor break
Discuss the safety devices, limitations, and emergency procedures for the rotor brake. (6 bullets)
EP: Rotor Brake ON Advisory appears in flight:
If secondary indications present:
If no secondary indications present:
a. Operating an engine against the gust lock is prohibited.
b. Rotor brake shall not be applied with engine(s) operating and rotor turning except during an emergency stop. Maximum rotor speed for emergency rotor brake applications is 76% NR.
c. Routine stops will be with engine(s) off, NR below 40% and with 150-180 psi applied to stop the rotor in not less than 12 seconds.
d. Minimum rotor brake pressure for engine start is 450 psi. Maximum rotor brake pressure for engine start is 690 psi.
e. Use of the rotor brake with engine(s) operating is restricted to single and dual engine starts and operations at IDLE only.
f. Single and dual engine starts and operation at IDLE with rotor brake on are not time limited.
EP:
- Rotor Brake Handle — Check in detent and gauge pressure at zero
- Check for secondary indications of brake pad dragging (smoke, smell, noise, etc.)
LAND AS SOON AS POSSIBLE
LAND AS SOON AS PRACTICABLE
Where are the cold start capsule lights located? What indications do they provide?
Upper console, status indicators and caution lights for the emergency cargo release, battery, APU and APU oil temperature, and accumulator.
How long must a CAUTION be displayed before the pilot is able to acknowledge the caution?
Pressing the MASTER CAUTION PRESS TO RESET caution on the instrument panel causes new cautions that have been displayed for at least two seconds to transition to an acknowledged status.
What are the three annunciators on the top of the FMS and what do they indicate?
STS Indicates change in system status. Go to the system status screen and acknowledge recognition of the fault to clear the annunciator.
FMS Indicates a BIT failure within the FMS. Go to the system status screen to clear the annunciator.
MSG Active, reserved for future use. Illuminates during test, not currently used for any other function.
