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Chapter 9 (change 8) > Chapter 9 (change 8) > Flashcards

Chapter 9 (change 8) Flashcards

1
Q

LAND AS SOON AS POSSIBLE

LAND AS SOON AS PRACTICABLE

A

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.)

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2
Q

AUTOROTATE (definition)

A

The term AUTOROTATE is defined as adjusting the flight controls as necessary to establish an autorotational descent and landing.

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3
Q

EMER ENG SHUTDOWN(DEFINITION AND PROCEDURE)

A
  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 538ºC after shutdown

  1. AIR SOURCE HEAT/START switch - As requred
  2. ENGINE IGNITION switch - OFF
  3. Starter button - Press to motor engine for 30 seconds or until TGT TEMP decreases below 538ºC.
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4
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.

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5
Q

EMER APU START (definition, procedure, caution)

A

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.

  1. APU CONTR switch - ON
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6
Q

ENGINE MALFUNCTION - PARTIAL OR COMPLETE POWER LOSS-(WARNING)(WARNING)

A

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, %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 further reduction of max Q available by18% for the 701D Engine
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7
Q

SINGLE ENGINE FAILURE (WARNING)(WARNING)

A
  1. Collective - Adjust to maintain % RPM R.

②. External cargo/stores - Jettison (if required).

  1. Establish single-engine airspeed.

If continued flight is not possible:

  1. LAND AS SOON AS POSSIBLE

If continued flight is possible:

  1. LAND AS SOON AS PRACTIABLE.

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, Ng, and % RPM 1 and 2.

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8
Q

DUAL ENGINE FAILURE

(PROCEDURE, WARNING AND STEADY STATE FACTORS)

A

AUTOROTATE.

WARNING

Do not respond to ENG OUT warnings and audio until checking TGT TEMP and % RPM R.

STEADY STATE FACTORS

  • ROTOR within limits
  • AIRSPEED above 80 KIAS
  • TORQUE
  • TRIM
  • SAFE, Aircraft in a position to land at desired touchdown point.
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9
Q

DECREASING % RPM R

(PROCEDURE, WARNING, CAUTION, NOTE)

A

“CEEL”

  1. Collective - Adjust to control % RPM R.
  2. Establish single-engine airspeed.

③ ENG POWER CONT lever (low % TRQ/TGT engine) - LOCKOUT. Maintain % TRQ appx 10% below other eng.

  1. 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.

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.

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10
Q

Increasing % RPM R

A

“ELEPR”

① ENG POWER CONT lever (high % TRQ/TGT engine) - Retard. Maintain % TRQ appx 10% below other eng.

  1. 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:

  1. Establish single engine airspeed.

④ Perform EMER ENG SHUTDOWN (affected engine).

⑤ Refer to single-engINE failure EP.

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11
Q

% RPM INCREASING/DECREASING (OSCILLATION)

A
  1. Establish single engine airspeed.② Slowly retard the ENG POWER CONT leveron the suspected engine. If the oscillation stops:③ Place that engine in LOCKOUT and manuallycontrol the power.4. LAND AS SOON AS PRACTICABLE. If the oscillation continues:⑤ Place the ENG POWER CONT lever back toFLY and retard the ENG POWER CONTlever of the other engine.⑥ Place the engine in LOCKOUT, manuallycontrol the power.7. LAND AS SOON AS PRACTICABLE.
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12
Q

TRQ SPLIT BETWEEN ENGINES 1 AND 2It is possible for a malfunction to occur that can cause a% TRQ split between engines without a significantchange in % RPM R. The % TRQ split can be correctedby manual control of the ENG POWER CONT lever onthe affected engine

A

checklist item

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13
Q

LOAD DEMAND SYSTEM MALFUNCTION.On ground :ENG POWER CONTin IDLENg 3% to 4% higher thannormal.ENG POWER CONTin FLYTorque split (single enginemalfunction).In flight :Initial takeoff (duringcollective increase).Increased torque split (singleengine malfunction).Low power descent(lowering collective tominimum)Rapid rise in engine %RPMand%RPMR

A

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.

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14
Q

Engine Compressor Stall

A
  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.
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15
Q

1 OIL FLTR BYPASS OR #2 OIL FLTR BYPASS CAUTION APPEARS.

A
  1. Establish single engine airspeed.② ENG POWER CONT lever - Retard.3. LAND AS SOON AS PRACTICABLE.
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16
Q

ENG 1 or 2 Chip, Oil Press or Temp Caution appears

A
  1. 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 emergencyprocedure.
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17
Q

ENGINE HIGH-SPEED SHAFT FAILURE

A
  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 emergencyprocedure.
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18
Q

LIGHTNING STRIKE EP and Warning

A

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

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19
Q

Loss of Tail Rotor Thrust in Cruise Flight

A
  1. Airspeed - Adjust to 80 KIAS or above.2. AUTOROTATE - Maintain airspeed at or above 80 KIAS.③ ENG POWER CONT levers - OFF (during deceleration when intended point of landing is assured).
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20
Q

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

A
  1. Collective - Reduce.② ENG POWER CONT levers - OFF (5 to 10 feet above touchdown).
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21
Q

TAIL ROTOR QUADRANT Caution Appears in Cruise Flight.

A
  1. Collective - Adjust to determine controllability (Fixed Right or Left).2. LAND AS SOON AS PRACTICABLE.
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22
Q

Loss of Control at Low Airspeed/Hover orTAIL ROTOR QUADRANT Caution Appears (LeftRotation).

A

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

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23
Q

Pedal Bind/Restriction or Drive With No Accompanying Caution

A
  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 controllabilityfor landing.8. LAND AS SOON AS PRACTICABLE.
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24
Q

1 TAIL RTR SERVO Caution Appears andBACK-UP PUMP ON Advisory Does Not Appear or#2 TAIL RTR SERVO ON Advisory Does Not Appear.

A

① TAIL SERVO switch - BACKUP.2. BACKUP HYD PUMP switch - ON.3. LAND AS SOON AS PRACTICABLE.

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25
Q

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

A
  1. LAND AS SOON AS POSSIBLE.If time permits:2. Slow to 80 KIAS.③ EMER APU START.④ GENERATORS NO. 1 and NO. 2 switches - OFF.
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26
Q

CHIP INPUT MDL LH or RH Caution Appears

A
  1. Establish single engine airspeed② ENG POWER CONT lever (affected engine) IDLE.3. LAND AS SOON AS POSSIBLE.
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27
Q

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

A

LAND AS SOON AS POSSIBLE

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28
Q

Main Transmission Failure

A
  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.
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29
Q

Engine/Fuselage Fire On Ground

A

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).

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30
Q

APU Compartment Fire

A

① APU fire T-handle - Pull.② FIRE EXTGH switch - MAIN/RESERVE as required.

31
Q

APU OIL TEMP HI Caution Appears

A

APU CONTR switch - OFF. Do not attemptrestart until oil level has been checked.

32
Q

Engine Fire In Flight

A
  1. 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.5. LAND AS SOON AS POSSIBLE.
33
Q

Electrical Fire In Flight.

A

① BATT and GENERATORS switches - OFF.2. LAND AS SOON AS POSSIBLE.

34
Q

SMOKE AND FUME ELIMINATION

A
  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.
35
Q

1 or #2 FUEL FLTR BYPASS Caution Appears.

A

① ENG FUEL SYS selector on affected engine - XFD.2. LAND AS SOON AS PRACTICABLE.

36
Q

1 and 2 FUEL FLTR BYPASS Cautions Appear

A

LAND AS SOON AS POSSIBLE

37
Q

1 and #2 FUEL LOW Cautions Appear.

A

LAND AS SOON AS PRACTICABLE

38
Q

1 or #2 FUEL PRESS Caution Appears (critical)

A

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).

  1. 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.

② FUEL BOOST PUMP CONTROL switches NO. 1 PUMP or NO. 2 PUMP - OFF (As applicable).

  1. LAND AS SOON AS PRACTICABLE.
39
Q

1 and #2 FUEL PRESS Cautions Appear.

A
  1. LAND AS SOON AS POSSIBLE.

② EMER ENG SHUTDOWN after landing.

40
Q

1 AND #2 Generator Failure (#1 and #2 CONV and AC ESS BUS OFF Caution Appear).

A

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.

41
Q

1 or #2 GEN Caution Appears.

A

① Affected GENERATORS switch - RESET;then ON.

If caution still appears:

② Affected GENERATORS switch - OFF.

42
Q

1 and #2 CONV cautions appear

A
43
Q

BATTERY FAULT Caution Appears

A

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.

44
Q

BATT LOW CHARGE Caution Appear

A

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.

45
Q

L/R PITOT HEAT and MASTER Cautions

A
  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.
46
Q

1 HYD PUMP Caution Appears

A

① TAIL SERVO switch - BACKUP; then NORMAL.2. LAND AS SOON AS PRACTICABLE.

47
Q

2 HYD PUMP Caution Appears

A

① POWER ON RESET switches - Simultaneously press, then release.2. LAND AS SOON AS PRACTICABLE.

48
Q

1 and #2 HYD PUMP Cautions Appear

A

LAND AS SOON AS POSSIBLE. Restrict control movement to moderate rates.

49
Q

1 or #2 HYD PUMP Caut. Appears and BACK-UP PUMP ON Advisory does not appear.

A
  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 emergency procedure.

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

③ FPS and BOOST switches - Off (for #2 HYD PUMP caution).

  1. LAND AS SOON AS POSSIBLE.
50
Q

1 or #2 PRI SERVO PRESS Caution Appears

A
  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.
51
Q

1 RSVR LOW and #1 HYD PUMP Cautions appear with BACK-UP PUMP ON Advisory Appearring.

Procedure & Warning:

A
  1. LAND AS SOON AS PRACTICABLE.

If the BACK-UP RSVR LOW caution also appears:

② SVO OFF switch - 1ST STG.

WARNING

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

  1. LAND AS SOON AS POSSIBLE.
52
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.

  1. LAND AS SOON AS PRACTICABLE.

If BACK-UP RSVR LOW caution also appears:

③ SVO OFF switch - 2ND STG.

WARNING

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

  1. LAND AS SOON AS POSSIBLE.
53
Q

2 RSVR LOW Caution Appears.Procedure and Note

A

Pilot assist servos will be isolated; if they remainisolated, proceed as follows:① BOOST - Off.② FPS - Off.3. 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.

54
Q

Collective Boost Servo Hardover/Power Piston Failure

A

① BOOST switch - Off.2. LAND AS SOON AS PRACTICABLE. Hardover failure of the collective boost servo will increase control forces (as much as 150 pounds) in the collective.

55
Q

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.

A

① BOOST switch - Off.2. LAND AS SOON AS PRACTICABLE

56
Q

Pitch Boost Servo Hardover

A

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 20pounds). The increased control forces can be immediatelyeliminated by shutting off SAS.

57
Q

Emergency Landing In Wooded Areas - Power Off.

A
  1. AUTOROTATE. Decelerate helicopter to stop all forward speed at treetop level.2. Collective adjust to maximum before main rotor contacts tree branches.
58
Q

Ditching - Power On

A
  1. Approach to a hover.2. Cockpit doors jettison and cabin doors openprior 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.
59
Q

Ditching - Power Off

A
  1. AUTOROTATE.2. Cockpit doors jettison and cabin doors openprior to entering water.3. Apply full collective to decay rotor RPM ashelicopter settles.4. Position cyclic in direction of roll.5. Exit when main rotor has stopped.
60
Q

FLIGHT CONTROL/MAIN ROTOR SYSTEM MALFUNCTIONS

A
  1. LAND AS SOON AS POSSIBLE.

② EMER ENG(S) SHUTDOWN after landing.

61
Q

SAS Failure With No Failure Advisory Indication

A

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.

62
Q

SAS 2 Failure Advisory Light On

A

POWER ON RESET s w i t c h e s - Simultaneously press and then release

63
Q

SAS OFF Caution Appears

A

① SAS 1 and SAS 2 switches - Off.② FPS switch - Off.3. LAND AS SOON AS PRACTICABLE

64
Q

FLT PATH STAB Caution Appears

A

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 ofmanually slewing the stabilator up is to use the cyclic mounted stabilator slew-up switch.4. LAND AS SOON AS PRACTICABLE. WARNINGIf the airspeed fault advisory light is illuminated, continued flight above 70 KIASwith the stabilator in the AUTO MODE is unsafe since a loss of the airspeedsignal from the remaining airspeed sensor would result in the stabilatorslewing full-down.

65
Q

Pitch, Roll, or Yaw/Trim Hardover

A
  1. POWER ON RESET switches - Simultaneously press and then release. If failure returns, control affected axis manually.2. LAND AS SOON AS PRACTICABLE.
66
Q

Trim Actuator Jammed.

A

LAND AS SOON AS PRACTICABLE

67
Q

STABILATOR MALFUNCTION - AUTO MODE FAILURE

A
  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
68
Q

UNCOMMANDED NOSE DOWN ATTITUDE CHANGE

A
  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 atairspeeds below 40 KIAS.

  1. LAND AS SOON AS PRACTICABLE.
69
Q

UNCOMMANDED NOSE UP ATTITUDE CHANGE

A
  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 atairspeeds below 40 KIAS.

  1. LAND AS SOON AS PRACTICABLE.
70
Q

ATTITUDE HEADING REFERENCE SYSTEM(AHRS) HEADING DEVIATIONS.

A

①Set the AHRU Control Unit to DG mode.②Manually update the HSI heading using the standby compass.3. LAND AS SOON AS PRACTICABLE.

71
Q

EMERGENCY JETTISONING.

A

CARGO REL or HOOK EMER REL switch - Press.

72
Q

EMERGENCY RELEASE OF RESCUE HOIST LOAD

A

If the rescue hoist becomes jammed, inoperative, or thecable 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

73
Q

MR DE-ICE FAULT, MR DE-ICE FAIL, or TRDE-ICE FAIL Caution Appears

A
  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
74
Q

PWR MAIN RTR and/or PWR TAIL RTRMonitor Light On.

A

checklist item

Chapter 9 (change 8) (2 decks)

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