(OLD!!)UH-60A/L CH9

Question 1

Define: Land as soon as possible

Answer 1

Landing at the nearest suitable area without delay(i.e. open field). (The primary consideration is to ensure the survival of occupants.)

Question 2

Define: Land as soon as practicable

Answer 2

Landing at a suitable landing area. (The primary consideration is the urgency of the emergency.)

Question 3

Define: Autorotate

Answer 3

Adjusting the flight controls as necessary to establish an autorotational decent and landing.

Question 4

Define: Establish single-engine airspeed

Answer 4

Maneuvering the AC to an appropriate airspeed that will allow for continued flight under partial power conditions to a suitable recovery area.

Question 5

Establish single-engine airspeed

Answer 5

(1. ) (Cyclic - Adjust as required.)
(2. ) (Collective - Adjust as required to maintain %RPM R within normal operating range.)
(3. ) (Establish appropriate airspeed.)

Question 6

Define: EMER ENG SHUTDOWN

Answer 6

The term EMER ENG SHUTDOWN is defined as engine shutdown without delay. Engine shutdown in flight is usually not an immediate-action item unless a fire exists. Before attempting an engine shutdown, identify the affected engine by checking ENG OUT warnings, %RPM, %TRQ, ENG OIL PRESS, TGT TEMP, and Ng SPEED.

Question 7

EMER ENG SHUTDOWN

Answer 7

(1. ) (ENG POWER CONT lever(s) - OFF.)
(2. ) (ENG FUEL SYS selector(s) - OFF.)
(3. ) (FUEL BOOST PUMP CONTROL switch(es) - OFF.)

CAUTION
If TGT rises above 538C after shutdown, place AIR SOURCE HEAT/START switch as required, turn ENGINE IGNITION switch OFF, and press starter to motor engine for 30 seconds or until TGT decreases below 538C.

Question 8

Define: LOCKOUT

Answer 8

The term LOCKOUT is defined as manual control of engine RPM while bypassing ECU, or DEC/EDECU functions. Bypass of the engine control will be required when %RPM 1 or 2 decreases below normal demand speed due to a malfunction of the ECU/DEC/EDECU.

CAUTION
When the engine is controlled with ENG POWER CONT lever in LOCKOUT, engine response is much faster and TGT limiting system is inoperative. Care must be taken not to exceed TGT limits and keeping %RPM R and %RPM 1 and 2 in operating range.

WARNING
Going to ECU/DEC/EDECU LOCKOUT to obtain additional power does not remove Maximum Fuel Flow or NG limits. %RPM R will decrease below normal operating range if Maximum Fuel Flow or Ng limits are exceeded.

Question 9

LOCKOUT

Answer 9

(ENG POWER CONT lever - Pull down and advance full forward while maintaining downward pressure, then adjust to set %RPM R as required.)

Question 10

Define: EMER APU START

Answer 10

The term EMER APU START is defined as APU start to accomplish an emergency procedure.

Question 11

EMER APU START

Answer 11

(1. ) (FUEL PUMP switch - APU BOOST.)
(2. ) (APU CONTR switch - ON.)

CAUTION
Ensure that the mask blowers are disconnected and position the BCA MCU control knobs to OFF prior to switching from main power to APU power.

Question 12

SINGLE-ENGINE FAILURE

Answer 12

1. (ESTABLISH SINGLE-ENGINE AIRSPEED.)
   (2. ) (External cargo/stores - Jettison (if required))

If continued flight is not possible:
3. (LASAP)

If continued flight is possible:
4. LASAPRAC

WARNING
When the power available during single engine operation is marginal or less, consideration should be given to jettisoning the external stores. The engine anti-ice and cockpit heater switches should be turned off as necessary to ensure maximum power is available on the remaining engine.

WARNING
Do not respond to ENG OUT warning and audio until checking TGT TEMP, Ng SPEED, and %RPM 1 and 2.

Question 13

DUAL-ENGINE FAILURE

Answer 13

(AUTOROTATE.)

WARNING
Do not respond to ENG OUT warning lights and audio until checking TGT TEMP, and %RPM R.

Question 14

ECU/DEC/EDECU LOW SIDE FAILURE

Answer 14

1. (ESTABLISH SINGLE-ENGINE AIRSPEED.)

If partial powered flight cannot be maintained:
(2.) (ENG POWER CONT lever (low %TRQ/TGT TEMP engine) - LOCKOUT.) Maintain %TRQ approximately 10% below other engine.

3. LASAPRAC

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 Maximum Torque Available, attempt to increase %RPM R with ENG RPM trim switch.

CAUTION
When the engine is controlled with ENG POWER CONT lever in LOCKOUT, engine response is much faster and TGT limiting system is inoperative. Care must be taken not to exceed TGT limits and keeping %RPM R and %RPM 1 and 2 in operating range.

WARNING
Going to ECU/DEC/EDECU LOCKOUT to obtain additional power does not remove Maximum Fuel Flow or NG limits. %RPM R will decrease below normal operating range if Maximum Fuel Flow or Ng limits are exceeded.

Question 15

ECU/DEC/EDECU HIGH SIDE FAILURE

Answer 15

1. (ESTABLISH SINGLE ENGINE AIRSPEED.)
   (2. ) (ENG POWER CONT lever (high %TRQ/TGT TEMP engine) - Retard.) Maintain %TRQ approximately 10% below the other engine.
2. LASAPRAC

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 (EMER ENG SHUTDOWN (affected engine).)
(5. ) Refer to single-engine failure EP.

Question 16

ENGINE COMPRESSOR STALL

Answer 16

1. (ESTABLISH SINGLE-ENGINE AIRSPEED)

If condition persists:

(2. ) (ENG POWER CONT lever (affected engine) - Retard) (TGT TEMP should decrease).
(3. ) ENG POWER CONT lever (affected engine) - FLY.

If stall conditions recurs:

(4. ) (EMER ENG SHUTDOWN) (affected engine).
(5. ) Refer to single-engine failure EP.

Question 17

CHIP #1 ENGINE OR CHIP #2 ENGINE, #1 ENGINE OIL PRESS OR #2 ENGINE OIL PRESS, #1 ENG OIL TEMP OR #2 ENG OIL TEMP CAUTION APPEARS

Answer 17

1. (ESTABLISH SINGLE ENGINE AIRSPEED.)
   (2. ) (ENG POWER CONT lever (affected engine) - Retard) (to reduce torque).

If oil pressure is below minimum limits or if oil temperature remains above maximum limits:

(3. ) (EMER ENG SHUTDOWN) (affected engine).
(4. ) Refer to single-engine failure EP.

Question 18

ENGINE HIGH-SPEED SHAFT FAILURE

Answer 18

1. (ESTABLISH SINGLE-ENGINE AIRSPEED.)
   (2. ) (EMER ENG SHUTDOWN) (affected engine). Do not attempt to restart.
   (3. ) Refer to single-engine failure EP.

Question 19

LIGHTNING STRIKE

Answer 19

1. (ESTABLISH SINGLE-ENGINE AIRSPEED.)
   (2. ) (ENG POWER CONT levers - Adjust as required to control %RPM.)
2. (LASAP.)

WARNING
Lighting strikes may result in loss of automatic flight control functions, engine controls, and/or electric power.

Question 20

Loss of Tail Rotor Thrust in Cruise Flight

Answer 20

1. (AUTOROTATE - Maintain airspeed at or above 80 KIAS.)

2. ) (ENG POWER CONT levers - OFF (during deceleration when the intended point of landing is assured).

Question 21

Loss of Tail Rotor Thrust or TAIL ROTOR QUADRANT Caution Appears with Loss of Control at Low Airspeed/Hover (Right Rotation)

Answer 21

1. (Collective - Reduce.)

2. ) (ENG POWER CONT levers - OFF ( 5 to 10 feet above touchdown).

Question 22

TAIL ROTOR QUADRANT Caution Appears in Cruise Flight

Answer 22

1. (Collective - Adjust to determine controllability (Fixed Right or Left).)
2. LASAPRAC.

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 displace the cable and boost servo piston enough to unlatch the quadrant cable.

Question 23

Loss of Control at Low Airspeed/Hover or TAIL ROTOR QUADRANT Caution Appears (Left Rotation)

Answer 23

(1. ) (ENG POWER CONT lever(s) - Retard to decrease %RPM R below 100% and begin a partial power decent.)
2. (Collective - Adjust to preserve %RPM R.)
(3. ) (ENG POWER CONT levers - OFF ( 5 to 10 feet above touchdown).)
4. (Collective - Adjust for landing.)

WARNING
Reducing collective in a left rotation will increase rate of turn with the ENG POWER CONT lever(s) at fly 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 level attitude, preserve RPM R, and apply cushion for the landing.

Question 24

Pedal Bind/Restriction or Drive With No Accompanying Caution

Answer 24

1. (Apply pedal force to oppose the drive.)
   (2. ) Check other pedals for proper operation.
   (3. ) TAIL SERVO switch - BACKUP.

If normal control authority is not restored:

(4. ) TAIL SERVO switch - NORMAL.
(5. ) BOOST switch - OFF.

If normal control forces are not restored:

(6. ) BOOST switch - ON
7. Collective - Adjust to determine controllability for landing.
8. LASAPRAC.

Question 25

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

Answer 25

(1. ) (TAIL SERVO switch - BACKUP.)
(2. ) BACKUP HYD PUMP switch - ON.
3. LASAPRAC.

Question 26

MAIN XMSN OIL PRESS or MAIN XMSN OIL TEMP Caution Appears/XMSN OIL PRESS LOW/XMSN OIL TEMP HIGH

Answer 26

1. (LASAP.)

If time permits:

2. Slow to 80 KIAS
   (3. ) (EMER APU START.)
   (4. ) GENERATORS NO.1 and NO.2 switches - OFF.

Question 27

CHIP INPUT MDL LH or RH Caution Appears.

Answer 27

1. (ESTABLISH SINGLE-ENGINE AIRSPEED.)
   (2. ) (ENG POWER CONT lever (affected engine) - IDLE.)
2. (LASAP.)

Question 28

CHIP MAIN MDL SUMP, CHIP ACCESS MDL LH or RH, CHIP TAIL XMSN or CHIP INT XMSN/TAIL XMSN OIL TEMP or INT XMSN OIL TEMP Caution Appears

Answer 28

(LASAP.)

Question 29

Main Transmission Failure

Answer 29

1. (Collective - Adjust only enough to begin a decent with power remaining applied to the main transmission throughout the decent and landing.)
2. (LASAP.)

NOTE
Decreasing %RPM R may be accompanied by a drop in transmission oil pressure of 10 psi or more, and possible unusual helicopter vibrations.

WARNING
If %RPM R decreases from 100% to below 96% with an increase in torque during steady flight with no engine malfunction, the main transmission planetary carrier may have failed. During a main transmission planetary carrier failure, it may be impossible to maintain %RPM R at 100%.

Question 30

Engine/Fuselage Fire On Ground

Answer 30

(1. ) (ENG POWER CONT lever(s) - OFF.)
(2. ) (ENG EMER OFF handle(s) - Pull if applicable.)
(3. ) (FIRE EXTGH switch - MAIN/RESERVE as required.)

WARNING
If No.2 DC primary bus electrical power is not available, only the reserve fire bottle can be discharged and fire extinguishing capability for the #2 engine will be lost.

Question 31

APU Compartment Fire

Answer 31

(1. ) (APU fire T-handle - Pull.)

2. ) (FIRE EXTGH switch - MAIN/RESERVE as required.

Question 32

Engine Fire in Flight

Answer 32

1. (ESTABLISH SINGLE ENG AS)
   (2. ) (ENG POWER CONT lever - OFF (affected engine).)
   (3. ) (ENG EMER OFF handle - Pull.)
   (4. ) (FIRE EXTGH switch - MAIN/RESERVE as required.)
2. (LASAP.)

WARNING
Attempt to visually confirm fire before engine shutdown or discharging extinguishing agent.

Question 33

Electrical Fire In Flight

Answer 33

(1. ) (BATT and GENERATORS switches - OFF.)

2. (LASAP.)

Question 34

1 and #2 FUEL FLTR BYPASS Cautions Appear

Answer 34

(LASAP)

Question 35

1 or #2 FUEL PRESS Caution Appears

Answer 35

(1. ) (ENG FUEL SYS selector on affected engine - XFD.)
(2. ) (FUEL BOOST PUMP CONTROL switch on side being used - ON.)
3. (LASAP.)
(4. ) (EMER ENG SHUTDOWN after landing.)

WARNING
Consideration must be given to any suspected fuel system compromise. If a compromise is suspected, the pilot must make every attempt to avoid or reduce the possibility of an ignition source. A fuel leak occurring in the oil cooler access area may result in fuel and/or fumes accumulating in or around the APU/engine.

Question 36

1 and #2 FUEL PRESS Cautions Appear

Answer 36

1. (LASAP.)
   (2. ) (EMER ENG SHUTDOWN after landing.)

WARNING
If both the #1 and #2 FUEL PRESS cautions appear, flame out is possible. Do not make rapid collective movements. Landing the aircraft as soon as possible is crucial. The possibility of a fuel leak may result in a fire; therefore, both engines should be shutdown immediately after landing.

Question 37

1 and #2 Generator Failure (#1 and #2 CONV and AC ESS BUS OFF Cautions Appear)

Answer 37

(1. ) SAS 1 switch - Press off.
2. Airspeed - Adjust (80 KIAS or less).
(3. ) GENERATORS NO.1 and NO.2 switches - RESET; then ON.

If cautions still appear:

(4. ) GENERATORS NO.1 and NO.2 switches - OFF.
5. If MCUs are in use: BCA MCU control knobs (pilot, copilot, and crewmembers) - OFF.
(6. ) (EMER APU START.)
(7. ) SAS 1 switch - ON.
8. LASAPRAC.

WARNING
Following the loss of DC PRI 1 and 2 bus power, both engine anti-ice valves will open, resulting in a loss of maximum torque available by 700 16% or 701C/701D/CC 18%.

Question 38

LFT or RT PITOT HEAT and MASTER Cautions Appear or Are Flashing

Answer 38

If LFT or RT PITOT HEAT and MASTER cautions are flashing:

1. LASAPRAC

If LFT or RT PITOT HEAT and MASTER cautions appear steady:

(1.) Turn off applicable PITOT HEAT switch.

If caution disappears, the applicable pitot heat has failed:

2. Exit icing conditions.

If LFT or RT PITOT HEAT and MASTER cautions still appear:

(3. ) Set PITOT HEAT switch as needed.
4. (LASAP)

CAUTION
LFT or RT PITOT HEAT and MASTER cautions appearing, with the PITOT HEAT switch in the OFF position, indicates complete failure of 5 Vdc power in the corresponding left or right relay panel. Do not fly the helicopter.

CAUTION
Flashing LFT or RT PITOT HEAT and MASTER cautions indicates a failure of a 5 Vdc power supply in the corresponding solid state left or right relay panel. Do not fly the helicopter.

Question 39

1 HYD PUMP CAUTION APPEARS

Answer 39

1. TAIL SERVO switch - BACKUP; then NORMAL

2. LASAPRAC

Question 40

2 HYD PUMP CAUTION APPEARS

Answer 40

1. POWER ON RESET switches - Simultaneously press, then release.
2. LASAPRAC

Question 41

1 and #2 HYD PUMP Cautions Appear

Answer 41

(LASAP.) Restrict control movement to moderate rates.

Question 42

1 or #2 HYD PUMP Caution Appears and BACK-UP PUMP ON Advisory Does Not Appear

Answer 42

1. (Airspeed - Adjust) to a comfortable airspeed.
   (2. ) (BACKUP HYD PUMP switch - ON.)

If BACK-UP PUMP ON advisory appears:

(3.) Refer to #1 HYD PUMP or #2 HYD PUMP caution appears EP.

If BACK-UP PUMP ON advisory still does not appear:

(4. ) (FPS and BOOST switches - OFF (for #2 HYD PUMP caution).)
5. (LASAP.)

Question 43

1 or #2 PRI SERVO PRESS Caution Appears

Answer 43

1. (SVO OFF switches - Check both are centered.)
2. (If the caution appears with the SVO OFF switch centered, move the SVO OFF switch to turn off the malfunctioning servo.)
3. (LASAP.)

Question 44

1 RSVR LOW and #1 HYD PUMP Cautions Appear With BACK-UP PUMP ON Advisory Appearing

Answer 44

1. LASAPRAC.

If the BACK-UP RSVR LOW caution also appears:

(2. ) (SVO OFF switch - 1ST STG.)
3. (LASAP.)

WARNING
If #2 PRI SERVO PRESS caution appears, establish landing attitude, minimize control inputs, and begin a descent.

Question 45

2 RSVR LOW and #2 HYD PUMP Cautions Appear With BACK-UP PUMP ON Advisory Appearing

Answer 45

(1. ) POWER ON RESET switches - Simultaneously press then release.
2. LASAPRAC.

If the BACK-UP RSVR LOW caution also appears:

(3. ) (SVO OFF switch - 2ND STG.)
4. (LASAP.)

WARNING
If #1 PRI SERVO PRESS caution appears, establish landing attitude, minimize control inputs, and begin a decent.

Question 46

Collective Boost Servo Hardover/Power Piston Failure

Answer 46

(1. ) (BOOST switch - Off.)

2. LASAPRAC.

Question 47

Emergency Landing in Wooded Areas - Power Off

Answer 47

1. (AUTOROTATE.) Decelerate helicopter to stop all forward speed at treetop level.
2. (Collective adjust) to maximum before main rotor contacts tree branches.

Question 48

Ditching - Power Off

Answer 48

1. (AUTOROTATE.)
2. Cockpit doors jettison and cabin doors open prior to entering water.
3. Apply full collective to decay rotor RPM as helicopter settles.
4. Position cyclic in direction of roll.
5. Exit when main rotor has stopped.

Question 49

FLIGHT CONTROL/MAIN-ROTOR SYSTEM MALFUNCTIONS

Answer 49

ON GROUND:

(1.) (EMER ENG(S) SHUTDOWN)

IN FLIGHT:

1. (LASAP.)
   (2. ) (EMER ENG(S) SHUTDOWN after landing.)

NOTE
Blade cuff failure is typically a chord wise crack of the cuff through the blade attachment bolt holes on the upper or lower ligament.

WARNING
Danger exists that the main rotor system could collapse or separate from the aircraft after landing. Exit when main rotor has stopped.

Question 50

STABILATOR MALFUNCTION - AUTO MODE FAILURE

Answer 50

1. (Cyclic mounted stabilator slew-up switch - Adjust as required) to arrest or prevent nose down pitch rate.
   (2. ) (AUTO CONTROL switch - Press ON once after establishing a comfortable airspeed.)

If automatic control is not regained:

3. Manually slew stabilator - Adjust to 0 degrees for flight above 40 KIAS or full down when airspeed is 40 KIAS or less. The preferred method of manually slewing the stabilator up is to use the cyclic mounted stabilator slew-up switch.
4. LASAPRAC.

If manual control is not possible:

5. STAB POS indicator - Check and fly at or below KIAS LIMITS shown on placard.
6. LASAPRAC.

NOTE
Use of cyclic mounted stabilator slew-up switch should be announced to the crew to minimize cockpit confusion.

Question 51

Uncommanded Nose Down/Up Pitch Attitude Change

Answer 51

If an uncommanded nose down pitch attitude occurs:

1. (Cyclic — Adjust as required.)
2. (Collective — Maintain or increase.)
3. (Cyclic mounted stabilator slew-up switch — Adjust as required) to arrest nose down pitch rate.
   (4. ) MAN SLEW switch — Adjust to 0° at airspeeds above 40 KIAS and full down at airspeeds 40 KIAS or less.
4. LAND AS SOON AS PRACTICABLE.

If an uncommanded nose up pitch attitude occurs:

1. (Cyclic — Adjust as required.)
2. (Collective — Reduce as required.)
   (3. ) MAN SLEW switch — Adjust to 0° at airspeeds above 40 KIAS and full down at airspeeds 40 KIAS or less.
3. LAND AS SOON AS PRACTICABLE.

Question 52

Emergency Jettisoning

Answer 52

(CARGO REL or HOOK EMER REL switch — Press.)

Question 53

Emergency Release of Rescue Hoist Load

Answer 53

If the external rescue hoist becomes jammed, inoperative, or the cable is entangled and emergency release is required.

1. (If possible, relieve tension on cable.)
2. (On either pilots or crew panel CABLE CUT button — Press.)

WARNING
Safety of hoist rider is primary consideration. When possible hoist rider shall be lowered to safety prior to performing an emergency release.

NOTE
Crews hoist control panel ARM - TEST switch must be in ARM to cut cable from either position.

Question 54

Hoist Runaway or Motor Brake Failure

Answer 54

1. (Hoist operator’s pendant UP/OFF/DN thumbwheel — UP or DN, as required to control cable and load.)

If control is not possible:

(2.) (Pilot’s hoist control panel PILOT OVER-RIDE switch — UP or DN as required to control cable and load.)

If control is possible (indicates Motor Brake Failure):

3. (LASAP.)

If control is not possible (indicates Hoist Runaway):

(4. ) (Pilot’s hoist control panel HOIST POWER switch — OFF.)
5. (LAND AS SOON AS POSSIBLE.)

WARNING
When a motor brake failure occurs do not remove hoist power. If removed will result in operator losing manual control of the load

Peel out is the likely result of a motor brake failure and may be accompanied by a burning smell. Hoist operators pendant or pilots hoist control panel shall be used to manually compensate for a failed motor brake.