Ch 9 (change 7) Flashcards
1
Q
FLIGHT CONTROL/MAIN ROTOR SYSTEM MALFUNCTIONS
A
-
LAND AS SOON AS POSSIBLE.
② EMER ENG(S) SHUTDOWN after landing.
2
Q
Pedal Bind/Restriction or Drive With No Accompanying Caution
A
- 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.
- Collective - Adjust to determine controllability
for landing.
- LAND AS SOON AS PRACTICABLE.
3
Q
Ditching - Power Off
A
- AUTOROTATE.
- Cockpit doors jettison and cabin doors open
prior to entering water. - Apply full collective to decay rotor RPM as
helicopter settles. - Position cyclic in direction of roll.
- Exit when main rotor has stopped.
4
Q
Collective Boost Servo Hardover/Power Piston Failure
A
① BOOST switch - Off.
- LAND AS SOON AS PRACTICABLE.
Hardover failure of the collective boost servo will increase control forces (as much as 150 pounds) in the collective.
5
Q
1 and #2 HYD PUMP Cautions Appear
A
LAND AS SOON AS POSSIBLE. Restrict control movement to moderate rates.
6
Q
APU OIL TEMP HI Caution Appears
A
APU CONTR switch - OFF. Do not attempt
restart until oil level has been checked.
7
Q
CHIP INPUT MDL LH or RH Caution Appears
A
- Establish single engine airspeed
② ENG POWER CONT lever (affected engine) IDLE.
- LAND AS SOON AS POSSIBLE.
8
Q
Loss of Control at Low Airspeed/Hover or
TAIL ROTOR QUADRANT Caution Appears (Left
Rotation).
A
① ENG POWER CONT lever(s) - Retard to decrease %RPM R below 100% and begin a
partial power descent.
- Collective - Adjust to preserve %RPM R.
③ ENG POWER CONT levers - OFF (5 to 10 feet above touchdown).
- Collective - Adjust for landing.
9
Q
1 and 2 FUEL FLTR BYPASS Cautions Appear
A
LAND AS SOON AS POSSIBLE
10
Q
Electrical Fire In Flight.
A
① BATT and GENERATORS switches - OFF.
- LAND AS SOON AS POSSIBLE.
11
Q
% RPM INCREASING/DECREASING (OSCILLATION)
A
1. Establish single engine airspeed.
② Slowly retard the ENG POWER CONT lever
on the suspected engine.
If the oscillation stops:
③ Place that engine in LOCKOUT and manually
control the power.
- LAND AS SOON AS PRACTICABLE.
If the oscillation continues:
⑤ Place the ENG POWER CONT lever back to
FLY and retard the ENG POWER CONT
lever of the other engine.
⑥ Place the engine in LOCKOUT, manually
control the power.
- LAND AS SOON AS PRACTICABLE.
12
Q
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.
A
① TAIL SERVO switch - BACKUP.
- BACKUP HYD PUMP switch - ON.
- LAND AS SOON AS PRACTICABLE.
13
Q
1or2 GEN Caution Appears
A
① Affected GENERATORS switch - RESET;
then ON.
If caution still appears:
② Affected GENERATORS switch - OFF.
14
Q
1 HYD PUMP Caution Appears
A
① TAIL SERVO switch - BACKUP; then NORMAL.
- LAND AS SOON AS PRACTICABLE.
15
Q
2 RSVR LOW and #2 HYD PUMP Cautions Appear With BACK-UP PUMP ON Advisory Appearing
A
① POWER ON RESET s w i t c h e s Simultaneously press then release.
- LAND AS SOON AS PRACTICABLE.
If BACK-UP RSVR LOW caution also appears:
③ SVO OFF switch - 2ND STG.
- LAND AS SOON AS POSSIBLE.
If #1 PRI SERVO PRESS caution appears, establish landing attitude, minimize control inputs, and begin a descent.
- LAND AS SOON AS POSSIBLE.
16
Q
MAIN XMSN OIL PRESS or MAIN XMSN OIL
TEMP Caution Appears / XMSN OIL PRESS LOW /
XMSN OIL TEMP HIGH
A
-
LAND AS SOON AS POSSIBLE.
If time permits: - Slow to 80 KIAS.
③ EMER APU START.
④ GENERATORS NO. 1 and NO. 2 switches - OFF.
17
Q
Loss of Tail Rotor Thrust in Cruise Flight
A
- Airspeed - Adjust to 80 KIAS or above.
- AUTOROTATE - Maintain airspeed at or above 80 KIAS.
③ ENG POWER CONT levers - OFF (during deceleration when intended point of landing is assured).
18
Q
ENG 1 or 2 Chip, Oil Press or Temp Caution appears
A
- Establish single engine airspeed.
② ENG POWER CONT lever – 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 emergency
procedure.
19
Q
Engine Fire In Flight
A
- Establish single engine airspeed.
② ENG POWER CONT lever (affected engine) OFF.
③ ENG EMER OFF handle - Pull.
④ FIRE EXTGH switch - MAIN/RESERVE as Required.
- LAND AS SOON AS POSSIBLE.
20
Q
SAS OFF Caution Appears
A
① SAS 1 and SAS 2 switches - Off.
② FPS switch - Off.
3. LAND AS SOON AS PRACTICABLE
21
Q
Lockout
(definition, warning, caution, procedure)
A
The term LOCKOUT is defined as manual control of engine RPM while bypassing ECU, or DEC functions (700ECU)(701C/D/CC EDECU)
- 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.
- CAUTION: when 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 1 and 2 in operating range.
Procedure: ENG POWER CONT lever - Pull down and advance full forward while maintaining downward pressure, then adjust to set %RPM R as required.
22
Q
APU Compartment Fire
A
① APU fire T-handle - Pull.
② FIRE EXTGH switch - MAIN/RESERVE as required.
23
Q
Increasing RPM R
A
INCREASING RPM R
① ENG POWER CONT lever (high % TRQ/TGT TEMP engine) - Retard. Maintain % TRQ appx 10% below other eng.
- LAND AS SOON AS PRACTICABLE
If the effected engine does not respond to ENG POWER CONT lever movement in the range between FLY and IDLE, the HMU may be malfunctioning internally. If thus occurs:
3: Establish single engine airspeed.
④ Perform EMER ENG SHUTDOWN (affected engine).
⑤ Refer to single-eng failure ep.
“ELEPR”
24
Q
2 RSVR LOW Caution Appears.
Procedure and Note
A
Pilot assist servos will be isolated; if they remain
isolated, proceed as follows:
① BOOST - Off.
② FPS - Off.
- LAND AS SOON AS PRACTICABLE
NOTE: Because the logic module will close the valve supplying pressure to the pilot-assist servos, BOOST SERVO OFF, SAS OFF, and TRIM FAIL cautions will appear.
25
Ditching - Power On
1. Approach to a hover.
2. Cockpit doors jettison and cabin doors open
prior to entering water.
3. Pilot shoulder harness - Lock.
4. Survival gear - Deploy.
5. Personnel, except pilot, exit helicopter.
6. Fly helicopter downwind a safe distance and hover.
7. **ENG POWER CONT** levers **- OFF**.
8. Perform hovering autorotation, apply full collective to decay rotor RPM as helicopter settles.
9. Position cyclic in direction of roll.
10. Exit when main rotor has stopped.
26
1or2 HYD PUMP Caut. Appears & Back-up ON Advisory does not appear
1. _Airspeed - Adjust_ to a comfortable airspeed.
② **_BACKUP HYD PUMP_** _switch - **ON**._
If **BACK-UP PUMP ON** advisory still does not appear:
③ _**FPS** and **BOOST** switches - Off (for #2_ **_HYD PUMP caution_).**
4. _LAND AS SOON AS POSSIBLE_.
27
ATTITUDE HEADING REFERENCE SYSTEM
(AHRS) HEADING DEVIATIONS.
①Set the AHRU Control Unit to DG mode.
②Manually update the HSI heading using the standby compass.
3. LAND AS SOON AS PRACTICABLE.
28
Emergency Landing In Wooded Areas - Power Off.
1. _AUTOROTATE_. Decelerate helicopter to stop all forward speed at treetop level.
2. _Collective adjust_ to maximum before main rotor contacts tree branches.
29
LIGHTNING STRIKE
EP and Warning
① _ENG POWER CONT levers - Adjust as required to control % RPM_.
2. _LAND AS SOON AS POSSIBLE_
Lightning strikes may result in loss of automatic flight control functions, engine controls, and/or electric power
30
#1 or #2 FUEL PRESS Caution Appears (critical)
① _**ENG FUEL SYS** selector on affected engine **XFD**._
② _**FUEL BOOST PUMP CONTROL** switches - **NO. 1 PUMP** or **NO. 2 PUMP - ON** (As applicable)._
3. _LAND AS SOON AS POSSIBLE_.
④ _EMER ENG SHUTDOWN after landing_.
b. Non-critical situations are those where single engine flight is possible.
① ENG FUEL SYS selector on affected engine XFD.
① FUEL BOOST PUMP CONTROL switches NO. 1 PUMP or NO. 2 PUMP - OFF (As applicable).
3. LAND AS SOON AS PRACTICABLE.
31
SAS 2 Failure Advisory Light On
POWER ON RESET s w i t c h e s - Simultaneously press and then release
32
Trim Actuator Jammed
LAND AS SOON AS PRACTICABLE
33
EMERGENCY RELEASE OF RESCUE HOIST LOAD
If the rescue hoist becomes jammed, inoperative, or the
cable is entangled and emergency release is required:
To cut cable from cockpit:
_CABLE SHEAR switch - FIRE._
To cut cable from hoist operator’s position:
_CABLE CUT switch - FIRE_
34
#1 or 2 PRI SERVO PRESS Caution Appears
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. _LAND AS SOON AS POSSIBLE_.
35
DUAL ENGINE FAILURE
(WARNING, PROCEDURE AND RECOMMENDED AIRSPEED AND RPM R)
_AUTOROTATE._
WARNING: Do not respond to ENG OUT warnings and audio until checking TGT TEMP and % RPM R.
Recommended airspeed 80kias. 100%RPM R (110% high drag) will result in achieving maximum glide distance.
36
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
_LAND AS SOON AS POSSIBLE_
37
1 RSVR LOW & 1 HYD PUMP Cautions appear with BACK-UP PUMP ON Advisory Appearring
Procedure & Warning:
1. LAND AS SOON AS PRACTICABLE.
If the BACK-UP RSVR LOW caution also appears:
② _SVO OFF switch - 1ST STG_.
If #2 PRI SERVO PRESS caution appears, establish landing attitude, minimize control inputs, and begin a descent.
3. _LAND AS SOON AS POSSIBLE._
38
UNCOMMANDED NOSE DOWN/UP PITCH
ATTITUDE CHANGE
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 below 40 KIAS.
5. 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 below 40 KIAS.
4. LAND AS SOON AS PRACTICABLE.
39
TAIL ROTOR QUADRANT Caution Appears in Cruise Flight.
1. _Collective - Adjust to determine controllability (Fixed Right or Left)._
2. LAND AS SOON AS PRACTICABLE.
40
ENGINE HIGH-SPEED SHAFT FAILURE
1. _Collective - Adjust_.
2. _Establish single engine airspeed._
③ _EMER ENG SHUTDOWN_ (affected engine).
Do not attempt to restart.
④ Refer to single-engine failure emergency
procedure.
41
Pitch, Roll, or Yaw/Trim Hardover
1. **POWER ON RESET** switches - Simultaneously press and then release.
If failure returns, control affected axis manually.
2. LAND AS SOON AS PRACTICABLE.
42
SMOKE AND FUME ELIMINATION
1. Airspeed - 80 KIAS or less.
2. Cabin doors and gunner’s windows - Open.
3. Place helicopter out of trim.
4. LAND AS SOON AS PRACTICABLE.
43
Compressor Stall
1. _Collective - Reduce._
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 condition recurs:
4. _Establish single engine airspeed._
⑤ _EMER ENG SHUTDOWN_ (affected engine).
⑥ Refer to single-engine failure emergency procedure.
44
BATTERY FAULT Caution Appears
① **BATT** switch - **OFF**; then **ON**. If **BATTERY FAULT** caution appears, cycle **BATT** switch no more than two times.
If caution still appears:
② **BATT** switch - **OFF**.
45
DECREASING RPM R
(PROCEDURE, WARNING, CAUTION, NOTE)
1. _Collective - Adjust to control % **RPM R**._
2. _Establish single-engine airspeed._
③ _**ENG POWER CONT** lever (low % **TRQ/TGT TEMP** engine) - **LOCKOUT**_. Maintain **% TRQ** appx 10% below other eng.
4. LAND AS SOON AS PRACTICABLE
WARNING: GOING TO ECU/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.
"CEEL"
CAUTION: When eng is controlled with ENG POWER CONT lever in LOCKOUT, engine response is much faster and the TGT limiting system is inop. Care must be taken not to exceed TGT limits and keeping % RPM R and % RPM 1 and 2 in operating range.
NOTE: (abbreviated) If %RPM R reduces from 100% to 95-96% in steady flight and %TRQ 1/2 are equal below max Q avail, attempt to use ENG RPM trim sw.
46
#1 OIL FLTR BYPASS OR #2 OIL FLTR BYPASS CAUTION APPEARS.
1. _Establish single engine airspeed._
② **ENG POWER CONT** lever - Retard.
3. LAND AS SOON AS PRACTICABLE.
47
1 and 2 FUEL PRESS Cautions Appear
1. _LAND AS SOON AS POSSIBLE_.
② _EMER ENG SHUTDOWN after landing._
48
SAS Failure With No Failure Advisory Indication
① **SAS 1** switch - Off.
If condition persists:
② **SAS 1** switch - **ON**.
③ SAS 2 switch - Off.
If malfunction still persists:
④ **SAS 1** and **FPS** switches - Off.
49
EMER ENG SHUTDOWN
(DEFINITION AND PROCEDURE)
1. _**ENG POWER CONT** lever(s) - **OFF**_
2. _**ENG FUEL SYS** selector(s) - **OFF**_
3. _**FUEL BOOST PUMP CONTROL** switch(es) - **OFF**_
If TGT is over 538\*C after shutdown
4. _**AIR SOURCE HEAT/START** switch - As requred_
5. _**ENGINE IGNITION** switch - **OFF**_
6. _Starter button - Press_ to motor engine for 30 seconds or until **TGT TEMP** decreases below 538\*C.
50
L/R PITOT HEAT and MASTER Cautions
1. LAND AS SOON AS PRACTICABLE.
If **LFT** or **RT PITOT HEAT** and **MASTER** cautions appear steady:
① Turn off applicable **PITOT HEAT** switch.
If caution disappears, then 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. _LAND AS SOON AS POSSIBLE._
51
Loss of Tail Rotor Thrust or TAIL ROTOR QUADRANT Caution Appears with Loss of Control at Low Airspeed/Hover (Right Rotation)
1. _Collective - Reduce._
② _**ENG POWER CONT** levers - **OFF** (5 to 10 feet above touchdown)._
52
BOOST SERVO OFF Caution Appears
Appearance of the BOOST SERVO OFF caution with no
other cautions appearing indicates a pilot valve jam in
either the collective or yaw boost servo. Control forces in
the affected axis will be similar to flight with boost off.
① **BOOST** switch - Off.
2. LAND AS SOON AS PRACTICABLE
53
Autorotate (definition)
The term AUTOROTATE is defined as adjusting the flight controls as necessary to establish an autorotational descent and landing.
54
Main Transmission Failure
1. _Collective - Adjust only enough to begin a descent with power remaining applied to the main transmission throughout the descent and landing_.
2. _LAND AS SOON AS POSSIBLE_.
55
1 and 2 Generator Failure (1/2 CONV and AC ESS BUS OFF Cautions Appear)
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. LAND AS SOON AS PRACTICABLE.
56
EMERGENCY JETTISONING.
_CARGO REL or HOOK EMER REL switch - Press._
57
STABILATOR MALFUNCTION - AUTO MODE FAILURE
1. _Cyclic mounted stabilator slew-up switch - Adjust if necessary_ 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° for flight above 40 KIAS or full down when airspeed is below 40 KIAS. The preferred method of manually slewing the stabilator up is to use the cyclic mounted stabilator slew-up switch.
6. LAND AS SOON AS PRACTICABLE
58
MR DE-ICE FAULT, MR DE-ICE FAIL, or TR
DE-ICE FAIL Caution Appears
1. Icing conditions - Exit.
② **BLADE DE-ICE POWER** switch - **OFF**, when out of icing conditions.
If vibrations increase:
3. _LAND AS SOON AS POSSIBLE_
59
EMER APU start (definition, procedure, caution)
The term EMER APU START is defined as APU start to accomplish an emergency procedure.
1. _**FUEL PUMP** switch - **APU BOOST**_
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.
2. **_APU CONTR_** _switch_ **_- ON_**
60
Engine/Fuselage Fire On Ground
① _**ENG POWER CONT** levers - **OFF**._
② _**ENG EMER OFF** handle - Pull if applicable._
③ _**FIRE EXTGH switch** - **MAIN/RESERVE** as required._
④ _EMER ENG SHUTDOWN - Perform (other engine)._
61
ENGINE MALFUNCTION - PARTIAL OR COMPLETE POWER LOSS-
(WARNING)
WARNING: Single engine capability must be considered prior to movement of the engine power control lever. Prior to movement of either PCL, it is imparative that the malfunctioning eng and the corresponding PCL be identified. If the decision is made to shut down an engine, take at least 5 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.
Significant rotor drop 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 antiice valves and will result in a max Q available of 18%.
62
FLT PATH STAB Caution Appears
① **(EH) SYSTEMS SELECT - DG/VG.**
② **POWER ON RESET** s w i t c h e s - Simultaneously press and then release.
If failure returns, control affected axis manually.
3. Manually slew stabilator - Adjust to 0° if above 40 KIAS. The preferred method of
manually slewing the stabilator up is to use the cyclic mounted stabilator slew-up switch.
4. LAND AS SOON AS PRACTICABLE.
WARNING
If the airspeed fault advisory light is illuminated, 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.
63
BATT LOW CHARGE Caution Appear
If caution appears after ac power is applied:
① **BATT** switch - **OFF**; then ON. About 30 minutes may be required to recharge battery.
If caution appears in flight:
② **BATT** switch - **OFF**, to conserve remaining battery charge.
64
#2 HYD PUMP Caution Appears
① **POWER ON RESET** switches - Simultaneously press, then release.
2. LAND AS SOON AS PRACTICABLE.
65
Pitch Boost Servo Hardover
① **SAS** (**1** and **2**) and **FPS** switches - Off.
2. LAND AS SOON AS PRACTICABLE.
Hardover failure of the pitch boost servo will increase the longitudinal cyclic control forces (approximately 20
pounds). The increased control forces can be immediately
eliminated by shutting off SAS.
66
PWR MAIN RTR and/or PWR TAIL RTR
Monitor Light On.
checklist item
67
LOAD DEMAND SYSTEM MALFUNCTION.
On ground :
ENG POWER CONT
in IDLE
Ng 3% to 4% higher than
normal.
ENG POWER CONT
in FLY
Torque split (single engine
malfunction).
In flight :
Initial takeoff (during
collective increase).
Increased torque split (single
engine malfunction).
Low power descent
(lowering collective to
minimum)
Rapid rise in engine %RPM
and%RPMR
On ground:
Shut down and consult maintenance.
In flight:
1. LAND AS SOON AS PRACTICABLE.
2. Perform a normal approach, avoiding low power autorotative descents.
68
#1 and #2 CONV cautions appear
procedure, warning,
note: NOTE: when only battery pwr is available, NI-CAD battery life is about __ day and __ night for a battery \_\_% charged. SLAB battery life is about \_\_min day and \_\_min night for a batttery \_\_% charged.
WARNING: Following the loss of DC PRI 1 and 2 bus pwr, both engine anti-ice valves will open, resulting in a loss of max q available of 18% (60L)
①Unnecessary dc electrical equipment - off
NOTE: when only battery pwr is available, NI-CAD battery life is about 22min day and 14min night for a battery 80% charged. SLAB battery life is about 38min day and 24min night for a batttery 80% charged.
2. LAND AS SOON AS PRACTICABLE
69
#1 or #2 FUEL FLTR BYPASS Caution Appears
① **ENG FUEL SYS** selector on affected engine - **XFD**.
2. LAND AS SOON AS PRACTICABLE.
70
LAND AS SOON AS POSSIBLE
And
LAND AS SOON AS PRACTICABLE
a. The term _LAND AS SOON AS POSSIBLE_ is defined as landing at the nearest suitable landing area (e.g., open field) without delay. (The primary consideration is to ensure the survival of occupants.)
b. The term LAND AS SOON AS PRACTICABLE is defined as landing at a suitable landing area. (The primary consideration is the urgency of the emergency.)
71
Single engine failure (warn,warn)
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 should be turned off as necessary to ensure maximum power is available on the remaining engine.
WARNING: Do not repsond to ENG OUT warning and audio until checking TGT TEMP, Ng SPEED, and % RPM 1 and 2.
1. _Collective - Adjust to maintain % **RPM R**._
②. _External cargo/stores - Jettison (if required)._
3. _Establish single-engine airspeed._
_If continued flight is not possible:_
4. _LAND AS SOON AS POSSIBLE_
If continued flight is possible:
5. LAND AS SOON AS PRACTIABLE.
72
TRQ SPLIT BETWEEN ENGINES 1 AND 2
It is possible for a malfunction to occur that can cause a
% TRQ split between engines without a significant
change in % RPM R. The % TRQ split can be corrected
by manual control of the ENG POWER CONT lever on
the affected engine
checklist item
