60L chapter 9 Flashcards
The urgency of certain emergencies requires immediate and instinctive action by the pilot e.g., Dual-Engine Failure, Engine Fire in Flight, Loss of Tail Rotor Thrust. The most important single consideration is ______________ ______________. All procedures are subordinate to this requirement. The _____________ _____________ should be reset after each malfunction to allow systems to respond to subsequent malfunctions. If time permits during a critical emergency, transmit ____________ call, set transponder to ________________, ________________ external stores if required, turn off _____________ _____________, and lock _________________ ______________.
helicopter control
MASTER CAUTION
MAYDAY
emergency
jettison
boost pumps
shoulder harnesses
Define LAND AS SOON AS POSSIBLE:
landing at the nearest suitable landing area (e.g., open field) without delay. (The primary consideration is to ensure the survival of occupants.)
Define LAND AS SOON AS PRACTICABLE:
landing at a suitable landing area. (The primary consideration is the urgency of the emergency.)
Define AUTOROTATE:
adjusting the flight controls as necessary to establish an auto-rotational descent and landing.
In autorotation, as airspeed increases above ____- ____ KIAS, the rate of descent and glide distance ______________ significantly. As airspeed decreases below _____ KIAS, the rate of descent will ___________ and glide distance will _____________.
70 - 80
increase
64
increase
decrease
The recommended airspeed for autorotation is _____ KIAS. Autorotation below _____knots is not recommended because the deceleration does not effectively arrest the __________________________.
80
80
rate of descent
Define ESTABLISH SINGLE-ENGINE AIRSPEED:
maneuvering the aircraft to an appropriate airspeed that will allow for continued flight under partial power conditions to a suitable recovery area.
ESTABLISH SINGLE-ENGINE AIRSPEED procedure:
(1) _____________________________________________________________________________
(2) _____________________________________________________________________________
(3) _____________________________________________________________________________
- Cyclic — Adjust as required.
- Collective—Adjustasrequiredtomaintain % RPM R within normal operating range.
- Establish appropriate airspeed.
Define EMER ENG SHUTDOWN:
engine shutdown without delay.
Engine shutdown in flight is usually not an immediate-action item unless a ________ exists. Before attempting an engine shutdown, identify the affected engine by checking _____________ warnings, % ________, % _______, ENG OIL __________, _________ TEMP, and_________SPEED.
fire
ENG OUT
RPM
TRQ
PRESS
TGT
Ng
EMER ENG SHUTDOWN procedure:
(1) _____________________________________________________________________________
(2) _____________________________________________________________________________
(3) _____________________________________________________________________________
ENG POWER CONT lever(s) — OFF.
ENG FUEL SYS selector(s) — OFF.
FUEL BOOST PUMP switch(es) — OFF.
CAUTION: If TGT is above 538°C after shutdown: place ___________________________________ switch as required, turn ENGINE IGNITION switch _______, and press starter to motor engine for _____ seconds or until TGT TEMP decreases below _______°C.
AIR SOURCE HEAT/START
OFF
30
500
Define LOCKOUT:
manual control of engine RPM while bypassing DEC/EDECU functions.
LOCKOUT procedure: ____________________________________________________________________________________________________________________________________________________________________________
The most reliable indication of engine power will be ______________.
ENG POWER CONT lever — Pull down and advance full forward while maintaining downward pressure, then adjust to set % RPM R as required.
TGT TEMP
WARNING: Going to ECU/DEC/EDECU LOCKOUT to obtain additional power does not remove _____________ _________ ___________or _______ ______. %RPM R will decrease below normal operating range if the above are exceeded.
Maximum Fuel Flow
Ng limits
CAUTION: When engine is controlled with ENG POWER CONT lever in LOCKOUT, engine response is much ___________ and _____ ____________ system is inoperative. Care must be taken not to exceed _______ limits and keeping % __________ and % _____ ___ and ___ in operating range.
faster
TGT limiting
TGT
% RPM R
% RPM 1 and 2
Define EMER APU START:
APU start to accomplish an emergency procedure.
EMER APU START procedure:
(1) _____________________________________________________________________________
(2) _____________________________________________________________________________
FUEL PUMP switch — APU BOOST.
APU CONTR switch — ON.
CAUTION: Ensure that the mask blowers are disconnected and position the BCA MCU control knobs to ____ prior to switching from main power to APU power.
OFF
After a malfunction of equipment has occurred, appropriate emergency actions have been taken and the helicopter is on the ground, an entry shall be made in the Remarks Section of DA Form 2408-___-___ describing the malfunction. Ground and flight operations shall be ________________ until corrective action has been taken.
13 - 1
discontinued
WARNING: For helicopters with a non-operational roll-trim actuator, the cyclic shall be held at all times with the rotor turning. In cases where emergency exit is required prior to rotor coasting to a stop, make sure that the cyclic stick is centered until the last crewmember can depart the cockpit. Since the main rotor shaft has a 3° forward tilt, an exit to the _______ _______or _________ ________will provide the greatest rotor clearance safety.
right rear
left rear
To release the cockpit door (emergency release of the door), the jettison handle is pulled ________________; the door may then be jettisoned by kicking the ___________________________ of the door. If the door fails to jettison, egress ______ through the cabin or through the ___________ ______________ door.
to the rear
lower forward
aft
opposite cockpit
Cabin door window jettison. To provide emergency exit from the cabin, two jettisonable windows are installed in each cabin door. To release the windows, a handle (under a jettison lever guard) marked EMERGENCY EXIT PULL AFT, (left side; right side, PULL FWD) on the inside of the cabin door, is moved in the direction of the __________, releasing the windows. The windows can then be _________________.
arrow
pushed out
Emergency equipment consists of two hand held ______________________, one _______________, and three __________________________.
fire extinguishers
crash ax
first aid kits
WARNING: Prior to movement of either power control lever, it is imperative that the _________________ and the corresponding ______________ ______________ be identified. If the decision is made to shut down an engine, take at least _______ full seconds while retarding the ENG POWER CONT lever from FLY to IDLE, monitoring % TRQ, Ng SPEED, TGT TEMP, % RPM, and ENG OUT warning appearance.
malfunctioning engine
ENG POWER CONT lever
five
WARNING: Significant rotor droop that results in the generators dropping off line or a dual generator or converter failure will result in a partial power loss. This power loss will be due to the opening of engine anti-ice valves and will result in a loss of maximum torque available of _____%.
18
WARNING: When the power available during single engine operation is marginal or less, consideration should be given to ____________________________________. The _______________________ and _____________________________should be turned off as necessary to ensure maximum power is available on the remaining engine.
jettisoning the external stores
engine anti-ice
cockpit heater switches
WARNING: Do not respond to ______________________ and _____________ until checking TGT TEMP, Ng SPEED, and % RPM 1 and 2.
ENG OUT warning
audio
SINGLE ENGINE FAILURE
1. _____________________________________________________________________________
(2) _____________________________________________________________________________
If continued flight is not possible:
3. _____________________________________________________________________________
If continued flight is possible:
4. LAND AS SOON AS PRACTICABLE.
- ESTABLISH SINGLE-ENGINE AIRSPEED.
- External cargo/stores — Jettison (if required). If continued flight is not possible:
- LAND AS SOON AS POSSIBLE.
Use of a crossbleed start could result in a power loss of up to ______% TRQ on the operational engine.
18
DUAL ENGINE FAILURE
_____________________________________________________________________________
AUTOROTATE
WARNING: Do not respond to ENG OUT warnings and audio until checking ________ and _________.
TGT TEMP
% RPM R.
ECU/DEC/EDECU LOW SIDE FAILURE
1. _________________________________________________________.
(2) ________________________________________________________. Maintain % TRQ approximately
10% below other engine.
3. LAND AS SOON AS PRACTICABLE
- ESTABLISHSINGLE-ENGINEAIRSPEED.
2. ENG POWER CONT lever (low % TRQ/ TGT TEMP engine) — LOCKOUT.
NOTE: If %RPM R reduces from 100% to 95-96% during steady flight, check %TRQ 1 and 2. If %TRQ 1 and 2 are equal and below _______________________________, attempt to increase %RPM R with __________________________________________.
Maximum Torque Available
ENG RPM trim switch
ECU/DEC/EDECU HIGH SIDE FAILURE
1. _________________________________________________________.
(2) _________________________________________________________. Maintain % TRQ approximately 10% below other engine.
3. LAND AS SOON AS PRACTICABLE
If the affected engine does not respond to ENG POWER CONT lever movement in the range between FLY and IDLE, the HMU may be malfunctioning internally. If this occurs:
(4) Perform___________________________________________.
(5) Refer to single-engine failure emergency procedure.
ESTABLISH SINGLE-ENGINE AIRSPEED.
ENG POWER CONT lever (high % TRQ/TGT TEMP engine) — Retard
EMER ENG SHUTDOWN (affected engine)
Increasing the collective (during a high side failure) will probably ____________ the malfunctioning engine’s TGT TEMP above ______°C.
increase
900
% RPM INCREASING/DECREASING (OSCILLATION)
(Step 1)____________________________________________.
ESTABLISH SINGLE-ENGINE AIRSPEED
% TRQ SPLIT BETWEEN ENGINES 1 AND 2
(Step 1)__________________________________________.
ESTABLISH SINGLE-ENGINE AIRSPEED
LOAD DEMAND SYSTEM MALFUNCTION
Refer to checklist
ENGINE COMPRESSOR STALL
- _____________________________________________________________________________
If condition persists:
(2) ____________________________________________(TGT TEMP should decrease)
(3) ENG POWER CONT lever (affected engine) - FLY
If stall condition recurs:
(4) _______________________________ (affected engine).
(5) Refer to single engine failure emergency procedure.
ESTABLISH SINGLE-ENGINE AIRSPEED
ENG POWER CONT lever (affected engine) — Retard
EMER ENG SHUTDOWN
1 OIL FLTR BYPASS OR #2 OIL FLTR BYPASS CAUTION APPEARS
(Step 1) _____________________________________________________
- ESTABLISH SINGLE-ENGINE AIRSPEED.
CHIP #1 ENGINE OR CHIP #2 ENGINE, #1 ENGINE OIL PRESS OR #2 ENGINE OIL PRESS, #1 ENGINE OIL TEMP OR #2 ENGINE OIL TEMP CAUTION APPEARS
- _____________________________________________________________________________
(2) _______________________________________________________________ (to reduce torque).
If oil pressure is below minimum limits or if oil temperature remains above maximum limits:
(3) ______________________________________________ (affected engine).
(4) Refer to single-engine failure emergency procedure.
ESTABLISH SINGLE-ENGINE AIRSPEED.
ENG POWER CONT lever (affected engine) — Retard
EMER ENG SHUTDOWN
ENGINE HIGH-SPEED SHAFT FAILURE
- _____________________________________________________________________________
(2) ________________________________ (affected engine). Do not attempt to restart.
(3) Refer to single-engine failure emergency procedure.
ESTABLISH SINGLE-ENGINE AIRSPEED.
EMER ENG SHUTDOWN
LIGHTNING STRIKE
- _____________________________________________________________________________
(2) _____________________________________________________________________________ - _____________________________________________________________________________
WARNING: Lightning strikes may result in loss of automatic flight control functions, engine controls, and/or electric power.
ESTABLISH SINGLE-ENGINE AIRSPEED
ENG POWER CONT levers — Adjust as required to control % RPM.
LAND AS SOON AS POSSIBLE.
After a lightning strike, if practical, the pilot should reduce speed to _____ KIAS. This will reduce the criticality of having exactly the correct rotor speed 100%.
80
LOSS OF TAIL ROTOR THRUST IN CRUISE FLIGHT
- _____________________________________________________________________________
(2) _____________________________________________________________________________
AUTOROTATE — Maintain airspeed at or above 80 KIAS.
ENG POWER CONT levers — OFF (during deceleration when intended point of landing is assured).
LOSS OF TAIL ROTOR THRUST OR TAIL ROTOR QUADRANT CAUTION APPEARS WITH LOSS OF CONTROL AT LOW AIRSPEED/HOVER (RIGHT ROTATION)
- _____________________________________________________________________________
(2) _____________________________________________________________________________
Collective — Reduce.
ENG POWER CONT levers — OFF (5 to 10 feet above touchdown).
TAIL ROTOR QUADRANT CAUTION APPEARS IN CRUISE FLIGHT
- _____________________________________________________________________________
- LAND AS SOON AS PRACTICABLE
- Collective — Adjust to determine controllability (Fixed Right or Left).
WARNING: If the helicopter is shut down and/or hydraulic power is removed with one tail rotor cable failure, disconnection of the other tail rotor cable will occur when force from the boost servo cannot react against control cable quadrant spring tension. The quadrant spring will ___________ the cable and boost servo piston enough to _____________ the quadrant cable.
displace
unlatch
Loss of one tail rotor cable will be indicated by appearance of the _________________________ caution. No change in handling characteristics should occur if only one cable fails.
TAIL ROTOR QUADRANT
If both tail rotor control cables fail, a centering spring will position the tail rotor servo linkage to provide _____ degrees of pitch. This will allow trimmed flight at about _____ KIAS and _____ KIAS (these speeds will vary with gross weight). At airspeeds below _____ KIAS and above_____ KIAS, right yaw can be controlled by ___________the collective. Between _____ KIAS and _____ KIAS, left yaw can be controlled by ____________ collective.
10½
25
up to 145
25
145
reducing
25
145
increasing
LOSS OF CONTROL AT LOW AIRSPEED/HOVER OR TAIL ROTOR QUADRANT CAUTION APPEARS (LEFT ROTATION)
- ENG POWER CONT lever(s) — Retard to decrease % RPM R below 100% and begin a partial power descent.
- Collective—Adjusttopreserve % RPM R.
- ENG POWER CONT levers — OFF (5 to 10 feet above touchdown).
- Collective — Adjust for landing.
WARNING: Reducing collective in a left rotation will __________ rate of turn with the ENG
POWER CONT lever(s) ___ ______ depending on the rate at which the ENG POWER CONT lever(s) are retarded. It is critical that the pilot on the controls maintain a ______ __________, preserve RPM R, and apply cushion for the landing.
increase
at fly
level attitude
PEDAL BIND/RESTRICTION OR DRIVE WITH NO ACCOMPANYING CAUTION
(Step 1) ___________________________________________________________________________
- Apply pedal force to oppose the drive.
A malfunction within the yaw boost servo or tail rotor servo can produce much higher force at the pedals and the affected servo must be turned off. A hard over failure of the yaw boost servo will ___________ control forces as much as ______ pounds on the pedals.
increase
250
1 TAIL RTR SERVO CAUTION APPEARS AND BACK-UP PUMP ON ADVISORY DOES NOT APPEAR OR #2 TAIL RTR SERVO ON ADVISORY DOES NOT APPEAR
(1) _____________________________________________________________________________
(2) BACKUP HYD PUMP switch – ON
3. LAND AS SOON AS PRACTICABLE
TAIL SERVO switch — BACKUP.
During # 1 TAIL RTR SERVO CAUTION APPEARS AND BACK-UP PUMP ON ADVISORY DOES NOT APPEAR OR #2 TAIL RTR SERVO ON ADVISORY DOES NOT APPEAR, ____________ _________________ did not take place. Loss of both the No. 1 hydraulic pump and backup pump results in both stages of the tail-rotor servo being unpressurized. The yaw boost servo is still pressurized and the mechanical control system is still intact allowing limited tail-rotor control. Because of the limited yaw control range available, a roll-on landing at approximately _____ KIAS is required.
Automatic switch over
40 KIAS or above
MAIN XMSN OIL PRESS OR MAIN XMSN OIL TEMP CAUTION APPEARS, XMSN OIL PRESS LOW, XMSN OIL TEMP HIGH.
- _____________________________________________________________________________
If time permits:
- Slow to 80 KIAS.
(3) _____________________________________________________________________________
(4) GENERATORS NO. 1 and NO. 2 switches – OFF
LAND AS SOON AS POSSIBLE
EMER APU START