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UH60A/L - 5 and 9 test > uh-60_a_l_vikan_ch_5_20160313214647 (1) > Flashcards

uh-60_a_l_vikan_ch_5_20160313214647 (1) Flashcards

1
Q
  • Maximum wind velocity for rotor start and stop is __KTS from any direction.
A

Maximum wind velocity for rotor start and stop is 45 KTS from any direction.

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2
Q
  • If oil pressure is not steady during steady state forward flight or in a level hover or if oil pressure is steady but under __psi, make an entry on DA Form 2408-13-1. Sudden pressure drops (more than __psi) without fluctuations require an entry on DA Form 2408-13-1.
A

If oil pressure is not steady during steady state forward flight or in a level hover or if oil pressure is steady but under 45psi, make an entry on DA Form 2408-13-1. Sudden pressure drops (more than10psi) without fluctuations require an entry on DA Form 2408-13-1.

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3
Q

ENGINE % RPM 1 - 2 (Np)__Sec. Transient __Transient ___Continuous ___Transient ___Avoid Operations in the __- __and __- __range except during start and shutdown

A

ENGINE % RPM 1 - 2 (Np)12 Sec. Transient 105-107%Transient101-105 %Continuous95-101 %Transient91-95 %Avoid Operations in20 - 40 and 60 - 90 range except during start and shutdown

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4
Q

ENGINE Ng__Sec. Transient _______Min Limit ____Continuous ____

A

ENGINE Ng12 Sec. Transient 102-105 %30 Min Limit99-102 %Continuous0-99 %

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5
Q

ENGINE OIL TEMPERATURE__Min Limit ___Continuous ___

A

ENGINE OIL TEMPERATURE30 Min Limit 135-150ºCContinuous-50 - 135ºC

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6
Q

GAS TURBINE TEMPERATURE__Sec. Transient ________ Min. Transient (Contingency Power) ____Start abort limit ________ Min Limit ________ Min Limit ____Normal ____

A

GAS TURBINE TEMPERATURE12Sec. Transient903-949ºC2.5MinTransient (Contingency Power)878-903ºCStart abort limit851ºC10Min Limit851-878ºC30Min Limit810-851ºCNormal0-810ºC

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7
Q

MAIN TRANSMISSION OIL TEMPERATUREPrecautionary _____Continuous _____

A

MAIN TRANSMISSION OIL TEMPERATUREPrecautionary 105-140ºCContinuous-50 -105ºC

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8
Q

MAIN ROTOR % RPM RPower onTransient ____Continuous ____Transient ____Power off (Autorotation)Maximum ____Transient ____Normal ____

A

MAIN ROTOR % RPM RPower onTransient101-107%Continuous95-101 %Transient 91-95 %Power off (Autorotation)Maximum110 %Transient105-110 %Normal90-105 %

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9
Q

FUEL QUANTITYNormal ____Precautionary ____

A

FUEL QUANTITYNormal 200-1500 LbsPrecautionary0-200 Lbs

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10
Q

ENGINE OIL PRESSURE__Min Limit _____Normal Operation _____ PSIIdle _____ PSI* _____ PSI minimum @ 90% Ng and above

A

ENGINE OIL PRESSURE5Min Limit100-120 PSINormal Operation26- 100 PSIIdle22-26 PSI* 35PSI minimum @ 90% Ng and above

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11
Q 
ENGINE % TRQ\_\_-Second Transient	Dual-Engine			
* Above \_\_KIAS \_\_\_\_		
* \_\_KIAS or Below \_\_\_\_			
* Single-Engine \_\_\_\_
Continuous	
* Single-Engine \_\_\_\_	Dual-Engine			
* Above \_\_KIAS \_\_\_\_		
* \_\_KIAS or Below \_\_\_\_
A

ENGINE % TRQ10-Second Transient Dual-Engine Above 80 KIAS 100-144 %
80 KIAS or Below120-144 % Single-Engine135-144 %
Continuous Single-Engine0-135 % Dual-Engine Above 80KIAS0-100 %
80KIAS or Below0-120 %

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12
Q

MAIN TRANSMISSION OIL PRESSUREPrecautionary ____Continuous ____Idle and Transient ____

A

MAIN TRANSMISSION OIL PRESSUREPrecautionary65-130 PSIContinuous30-65 PSIIdle and Transient20-30 PSI

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13
Q

ENGINE STARTER LIMITSAt ambient temperatures of ______ °C and below, ______ consecutive start cycles may be made, followed by a _______ minute rest period, followed by _____ additional start cycles. A _____ minute rest period is then required.At ambient temperatures above _____°C up to ______° C, ______ consecutive start cycles may be made. A ______ minute rest period is then required before any additional start cycles.

A

ENGINE STARTER LIMITSAt ambient temperatures of 15°C and below, 2consecutive start cycles may be made, followed by a 3minute rest period, followed by 2additional start cycles. A 30minute rest period is then required.At ambient temperatures above 15°C up to52° C, 2consecutive start cycles may be made. A 30minute rest period is then required before any additional start cycles.

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14
Q

PNEUMATIC SOURCE INLET LIMITSThe minimum air source required to start the helicopter is ____ psig and ____ ppm at ____° C.The maximum is _____ psig at _____° C.

A

PNEUMATIC SOURCE INLET LIMITSThe minimum air source required to start the helicopter is 40psig and 30ppm at 149° C.The maximum is 50psig at 249° C.

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15
Q

ENGINE OVERSPEED CHECK LIMITIATIONSEngine overspeed check in flight is _________. Engine overspeed checks, on the ground, are authorized by ____________________only.

A

ENGINE OVERSPEED CHECK LIMITIATIONSEngine overspeed check in flight is PROHIBITED. Engine overspeed checks, on the ground, are authorized by DESIGNATED MAINTENANCE PERSONNELonly.

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16
Q

ENGINE START LIMITSCross bleed start shall not be attempted unless the __________________advisory does not appear, and the operating engine must be at ___% NG speed or above and rotor speed at ___% RPM R.

A

ENGINE START LIMITSCross bleed start shall not be attempted unless the #1 ENG ANTI-ICE ON OR #2 ENG ANTI-ICE ONadvisory does not appear, and the operating engine must be at 90% NG speed or above and rotor speed at 100% RPM R.

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17
Q

LOADING LIMITS

  • Maximum capacity for each storage compartment is ___pounds .
  • Maximum cargo hook capacity (UH-60L) ____ pounds.
  • Max weight is further limited by cargo floor maximum capacity of ____ lbs per square foot.
  • Max weight UH60 with seven lugs wheels _____ pounds.
A

LOADING LIMITS Maximum capacity for each storage compartment is 125pounds . Maximum cargo hook capacity (UH-60L) 9000pounds. Max weight is further limited by cargo floor maximum capacity of 300lbs per square foot. Max weight UH60 with seven lugs wheels20,500pounds.

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18
Q

AIRSPEED LIMITS

  • Max airspeed for one engine inoperative ___KIAS.
  • Max autorotational airspeed gross weight at 16,825 lbs or less ___KIAS.
  • Max autorotational airspeed gross weight more than 16,825 lbs ___KIAS.
  • Sideward/rearward flight into the wind, when combined with wind speed, shall not exceed ___KTS.
A

AIRSPEED LIMITS Max airspeed for one engine inoperative 130KIAS. Max autorotational airspeed gross weight at 16,825 lbs or less 150KIAS. Max autorotational airspeed gross weight more than 16,825 lbs 130KIAS. Sideward/rearward flight into the wind, when combined with wind speed, shall not exceed 45KTS.

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19
Q

SAS Inoperative Limits KIASOne SAS ____Two SAS ____Two SAS & IMC ____

A

SAS Inoperative Limits KIASOne SAS170 KIASTwo SAS150KIASTwo SAS & IMC140KIAS

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20
Q

Hydraulic System Inoperative Limits KIASOne hydraulic system ____Two hydraulic systems ____Two hydraulic systems & IMC ____

A

Hydraulic System Inoperative Limits KIASOne hydraulic system170KIASTwo hydraulic systems150KIASTwo hydraulic systems & IMC140KIAS

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21
Q

Maximum airspeed for:

A
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22
Q

FLIGHT WITH CABIN DOOR(S) / WINDOWS(S) OPEN:

  • Cabin doors may be fully open up to ____ KIAS with soundproofing installed aft of station 379.
  • Cabin doors may be fully open up to ____ KIAS with soundproofing removed aft of station 379 or with sound proofing secured properly.
  • Gunner’s window(s) may be fully open up to____ KIAS
  • Cockpit doors sliding window will not be ____ or ____ during flight except during ____.
  • Flight with cockpit door(s) removed is ____.
A

FLIGHT WITH CABIN DOOR(S) / WINDOWS(S) OPEN: Cabin doors may be fully open up to 100KIAS with soundproofing installed aft of station 379. Cabin doors may be fully open up to 145KIAS with soundproofing removed aft of station 379 or with sound proofing secured properly. Gunner’s window(s) may be fully open up to170KIAS Cockpit doors sliding window will not beOPEN or CLOSEDduring flight except during HOVER. Flight with cockpit door(s) removed is PROHIBITED.

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23
Q

AIRSPEED LIMITSFollowing failure of the Automatic Stabilator Control System.Manual control is available:
* Stabilator shall be full down at speeds below ____KIAS
* Stabilator shall be set at zero degrees for speeds above ____KIAS
* Autorotation airspeed shall be limited to ____KIAS at all gross weights.
Manual control not available:
* Placard airspeed limits shall be observed as not-to-exceed speed (powered flight and autorotation), except in no case shall the autorotation limit exceed ____KIAS.

A

AIRSPEED LIMITSFollowing failure of the Automatic Stabilator Control System.Manual control is available: Stabilator shall be full down at speeds below 40KIAS Stabilator shall be set at 0 degrees for speeds above 40KIAS Autorotation airspeed shall be limited to 120KIAS at all gross weights.
Manual control not available: Placard airspeed limits shall be observed as not-to-exceed speed (powered flight and autorotation), except in no case shall the autorotation limit exceed 120KIAS.

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24
Q

PROHIBITED MANEUVERS

  • Hovering turns greater than ___° per second are prohibited. Intentional maneuvers beyond attitudes of ___ ° in pitch or over ___° in roll are prohibited.
  • Simultaneous moving of ___ to___ or ___ in flight is prohibited.
  • ___ ground taxi is prohibited.
A

PROHIBITED MANEUVERS Hovering turns greater than30° per second are prohibited. Intentional maneuvers beyond attitudes of +/- 30° in pitch or over 60° in roll are prohibited. Simultaneous moving of BOTH EPCLtoIDLEor OFFin flight is prohibited.
REARWARDground taxi is prohibited.

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25
Q

RESTRICTED MANEUVERS

  • Manual operation of the stabilator in flight is _____, except as required by formal training and _____ requirements or as alternate stabilator control in case of AUTO mode malfunctions.
  • Prolonged rearward flight and downwind hovering are to be avoided to prevent accumulation of _____ in the helicopter and _____ to windows on _____.
A

RESTRICTED MANEUVERS Manual operation of the stabilator in flight is PROHIBITED,except as required by formal training and MAINTENANCE TEST FLIGHTrequirements or as alternate stabilator control in case of AUTO mode malfunctions. Prolonged rearward flight and downwind hovering are to be avoided to prevent accumulation of EXHAUST FUMESin the helicopter and HEAT DAMAGEto windows on OPEN CARGO DOORS.

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26
Q

MANEUVERING LIMITATIONSNOTE: Maneuvers entered from a low power setting may result in _____ of _____ % RPM R orgreater.

A

MANEUVERING LIMITATIONSNOTE: Maneuvers entered from a low power setting may result in TRANSIENT DROOPof 5% RPM R orgreater.

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27
Q

High Speed yaw maneuver limitationsAbove ___KIAS avoid _____________ to prevent excess tail rotor system loading.

A

High Speed yaw maneuver limitationsAbove 80KIAS avoidABRUBT, FULL PEDAL INPUTSto prevent excess tail rotor system loading.

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28
Q

Sling Loads

  • Maneuvering limitations with a sling load is limited to a maximum of __° angle of bank in forward flight.
  • Side flight is limited by ________and is decreased as _______
  • Rearward flight with a sling load is limited to __knots.
A

Sling Loads Maneuvering limitations with a sling load is limited to a maximum of 30° angle of bank in forward flight. Side flight is limited by BANK ANGLEand is decreased as AIRSPEEDINCREASES Rearward flight with a sling load is limited to 35knots.

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29
Q

Bank Angle LimitationBank angle shall be limited to __° when either PRI SERVO PRESS caution light appears.

A

Bank Angle LimitationBank angle shall be limited to 30° when either PRI SERVO PRESS caution light appears.

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30
Q

LANDING GEAR LIMITATION

A
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31
Q

LANDING SPEED LIMITATIONSMaximum forward touchdown speed is limited to ___knots ground speed on level terrain.

A

LANDING SPEED LIMITATIONSMaximum forward touchdown speed is limited to 60 knots ground speed on level terrain.

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32
Q

SLOPE LANDING LIMITATIONS

  • __° nose-up, right wheel up or left wheel upslope, reduced by __for each __KTS of wind.
  • __° nose downslope. Landing in nose downslope conditions with tail winds greater than ___KTS shall not be conducted.
  • The main gearbox may be operated up to __minutes at a time with pressure fluctuations when the helicopter is known to be at a ________________.
A

SLOPE LANDING LIMITATIONS
15° nose-up, right wheel up or left wheel upslope, reduced by 2for each 5KTS of wind.
6° nose downslope. Landing in nose downslope conditions with tail winds greater than 15KTS shall not be conducted. The main gearbox may be operated up to 30minutes at a time with pressure fluctuations when the helicopter is known to be at a NOSE-UP ATTITUDE.

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33
Q

ENVIRONMENTAL RESTRICTIONSHelicopters with the following equipment installed, operational, and turned on are permitted to fly into ______ or ______ icing conditions.
* ____________________
* ____________________
* ____________________
* ____________________
* ____________________
Flight into moderate icing conditions _________________ must be installed, operational, and turned on.Flight into heavy or severe icing is ____________

A

ENVIRONMENTAL RESTRICTIONSHelicopters with the following equipment installed, operational, and turned on are permitted to fly into TRACE or LIGHT icing conditions. WINDSHIELD ANTI-ICE PITOT HEAT ENGINE ANTI-ICE ENGINE INLET ANTI-ICE MODULATING VALVE INSULATED AMBIENT AIR SENSING TUBE.
Flight into moderate icing conditions ALL EQUIPMENT AND BLADE DEICE KITmust be installed, operational, and turned on.Flight into heavy or severe icing is PROHIBITED

34
Q

BACKUP HYDRAULIC PUMP HOT WEATHER LIMITS with the rotor system _________.

A

BACKUP HYDRAULIC PUMP HOT WEATHER LIMITS with the rotor system STATIC.

35
Q

APU OPERATING LIMITSTo prevent APU overheating, at ambient temperature of ___°C and above with the engine and rotor operating is limited to ___minutes. With the engine and rotor not operating, the APU can be operated __________ up to a temperature of ___°C.

A

APU OPERATING LIMITSTo prevent APU overheating, at ambient temperature of 43°C and above with the engine and rotor operating is limited to 30minutes. With the engine and rotor not operating, the APU can be operated CONTINUOUSLYup to a temperature of 51°C.

36
Q

WINDSHIELD ANTI-ICE LIMITATIONSWindshield anti-ice check shall not be done when FAT is over __°C.

A

WINDSHIELD ANTI-ICE LIMITATIONSWindshield anti-ice check shall not be done when FAT is over 27°C.

37
Q

TURBULENCE AND THUNDERSTORM OPERATION

  • Intentional flight into thunderstorms is ____________.
  • Intentional flight into ____________ turbulence is prohibited.
  • Intentional flight into turbulence with a sling load attached and an inoperative ____________ is prohibited.
A

TURBULENCE AND THUNDERSTORM OPERATION Intentional flight into thunderstorms is PROHIBITED. Intentional flight into SEVEREturbulence is prohibited. Intentional flight into turbulence with a sling load attached and an inoperative COLLECTIVE PITCH CONTROL FRICTIONis prohibited.

38
Q

GUST LOCK LIMITATIONS

  • Dual-engine operations with the gust lock engaged are _________.
  • Single-engine operations with gust lock engaged will be performed by authorized pilot(s) at _________ only.
  • Gust lock shall not be _________with engine running.
A

GUST LOCK LIMITATIONS Dual-engine operations with the gust lock engaged are PROHIBITED. Single-engine operations with gust lock engaged will be performed by authorized pilot(s) at IDLEonly. Gust lock shall not be DISENGAGEDwith engine running.

39
Q

The term LAND AS SOON AS POSSIBLE is defined as

A

LANDING AT THE NEAREST SUITABLE LANDING AREA (E.GOPEN FIELD) WITHOUT DELAY. (THE PRIMARY CONSIDERATION IS TO ENSURE THE SURVIVAL OF THE OCCUPANTS.)

40
Q

The term LAND AS SOON AS PRACTICABLE is defined as

A

LANDING AT A SUITABLE LANDING AREA.(THE PRIMARYCONSIDERATION IS THE URGENCY OF THEEMERGENCY.)

41
Q

The term AUTOROTATE is defined as

A

ADJUSTING THE FLIGHT CONTROLS AS NECESSARY TO ESTABLISH ANAUTOROTATIONAL DESCENT AND LANDING

42
Q

The term EMER ENG SHUTDOWN is defined as___EP:1. _______________2. _______________3. _______________If TGT is above 538°C after shutdown:4. _______________5. _______________6. _______________

A

The term EMER ENG SHUTDOWN is defined asENGINE SHUTDOWN WITHOUT DELAYEP:1. EPCL (S)- OFF2. ENG FUEL SYS SELECTOR (S)- OFF3. FUEL BOOST PUMP CONTROL SWITCH(ES)- OFFIf TGT is above 538°C after shutdown:4. AIR SOURCE HEAT/START SWITCH - AS REQUIRED5. ENGINE IGNITION SWITCH - OFF6.STARTER BUTTON - PRESS

43
Q

The term LOCKOUT is defined as ________________EP:

* ________________

A

The term LOCKOUT is defined asMANUAL CONTROL OF THE ENGINE RPM WHILE BYPASSING THE DECFUNCTIONSEP: EPCL- PULL DOWN AND ADVANCE FORWARD WHILE MAINTAINING DOWNWARD PRESSURE, THEN ADJUST TO SET% RPM R AS REQUIRED

44
Q

The term EMER APU START is defined as ____________________________EP:

  • ___________________________
  • __________________________
A

The term EMER APU START is defined asAPU START TO ACCOMPLISH AN EMERGENCY PROCEDUREEP: FUEL PUMP SWITCH - APU BOOST APU CONTROL SWITCH - ON

45
Q

SINGLE ENGINE FAILURE1. _____________2. _____________3. _____________If continued flight is not possible:4. _____________If continued flight is possible:5. LAND AS SOON AS PRACTICABLE.

A

SINGLE ENGINE FAILURE1. COLLECTIVE - ADJUST TO MAINTAIN % RPM R2. EXTERNAL CARGO/STORES - JETTISON (IF REQUIRED)3. ESTABLISH SINGLE ENGINEAIRSPEEDIf continued flight is not possible:4.LAND AS SOON AS POSSIBLEIf continued flight is possible:5.LAND AS SOON AS PRACTICABLE.

46
Q

DUAL ENGINE FAILURE____________________

A

DUAL ENGINE FAILUREAUTOROTATE

47
Q

DECREASING % RPM R

  • ____________
  • ____________
  • ____________
  • LAND AS SOON AS PRACTICABLE.
A

DECREASING % RPM R COLLECTIVE - ADJUST TO CONTROL % RPM R ESTABLISH SINGLE-ENG AIRSPEED
EPCL (LOW % TRQ/TGT TEMP ENGINE) - LOCKOUT.
* LAND AS SOON AS PRACTICABLE.

48
Q

INCREASING % RPM R1. _______________________2. 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:3. Establish single engine airspeed.4. Perform ___________5. Refer to single-engine failure emergency procedure.

A

INCREASING % RPM R1. EPCL (HIGH TRQ/TGT TEMP ENGINE) - RETARD.2. 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:3. Establish single engine airspeed.4. PerformEMER ENG SHUTDOWN (AFFECTED ENGINE)5. Refer to single-engine failure emergency procedure.

49
Q

ENGINE COMPRESSOR STALL1. __________________If condition persists:2. __________________3. ENG POWER CONT lever (affected engine) - FLY.If stall condition recurs:4. __________________5. __________________6. Refer to single-engine failure emergency procedure

A

ENGINE COMPRESSOR STALL1. COLLECTIVE - REDUCEIf condition persists:2. EPCL (AFFECTED ENGINE) - RETARD3. ENG POWER CONT lever (affected engine) - FLY.If stall condition recurs:4. ESTABLISH SINGLE-ENG AIRSPEED5. EMERGENCY ENG SHUTDOWN (AFFECTED ENGINE)6. Refer to single-engine failure emergency procedure

50
Q

CHIP #1 ENG OR CHIP #2 ENG, #1 ENG OIL PRESS OR #2 ENG OIL PRESS, #1 ENG OIL TEMP OR #2 ENG OIL TEMP CAUTION APPEARS.1. __________________2. __________________lever (affected engine) – Retard (to reduce torque)If oil pressure is below minimum limits or if oil temp remains above maximum limits:3. ___________________4. Refer to single-engine failure emergency procedure.

A

CHIP #1 ENG OR CHIP #2 ENG, #1 ENG OIL PRESS OR #2 ENG OIL PRESS, #1 ENG OIL TEMP OR #2 ENG OIL TEMP CAUTION APPEARS.1. ESTABLISH SINGLEENGINE AIRSPEED2. ♦​EPCL (AFFECTED ENGINE) - RETARD(to reduce torque)If oil pressure is below minimum limits or if oil temp remains above maximum limits:3. EMER ENG SHUTDOWN (AFFECTED ENGINE)4. Refer to single-engine failure emergency procedure.

51
Q

ENGINE HIGH-SPEED SHAFT FAILURE

  • ___________________
  • ___________________
  • ___________________
  • Refer to single-engine failure emergency procedure.
A

ENGINE HIGH-SPEED SHAFT FAILURE COLLECTIVE - ADJUST ESTABLISH SINGLEENGINE AIRSPEED EMER ENG SHUTDOWN (AFFECTED ENGINE)
* Refer to single-engine failure emergency procedure.

52
Q

LIGHTNING STRIKE

  • ___________________________
  • ___________________________
A

LIGHTNING STRIKE EPCLS - ADJUST AS REQUIRED TO CONTROL % RPM LAND AS SOON AS POSSIBLE

53
Q

LOSS OF TAIL ROTOR THRUST IN CRUISE FLIGHT

  • ________________________
  • ________________________
  • ________________________
A

LOSS OF TAIL ROTOR THRUST IN CRUISE FLIGHT AIRSPEED - ADJUST TO 80 KIAS OR ABOVE AUTOROTATE - MAINTAIN AIRSPEED AT OR ABOVE 80 KIAS EPCLS - OFF (DURING DECELERATION WHEN INTENDED POINT OF LANDING IS ASSURED

54
Q

LOSS OF TAIL ROTOR THRUST OR TAIL ROTOR QUADRANT CAUTION APPEARS WITH LOSS OF CONTROL AT LOW AIRSPEED / HOVER (RIGHT ROTATION)

  • _____________________
  • _____________________
A

LOSS OF TAIL ROTOR THRUST OR TAIL ROTOR QUADRANT CAUTION APPEARS WITH LOSS OF CONTROL AT LOW AIRSPEED / HOVER (RIGHT ROTATION) COLLECTIVE - REDUCE EPCLS - OFF ( 5 - 10 FEET ABOVE TOUCHDOWN)

55
Q

TAIL ROTOR QUADRANT CAUTION APPEARS IN CRUISE FLIGHT

  • _____________________
  • LAND AS SOON AS PRACTICABLE.
A

TAIL ROTOR QUADRANT CAUTION APPEARS IN CRUISE FLIGHT COLLECTIVE ADJUST TO DETERMINE CONTROLLABILITY (FIXED RIGHT OR LEFT)
* LAND AS SOON AS PRACTICABLE.

56
Q

LOSS OF CONTROL AT LOW AIRSPEED/HOVER OR TAIL ROTOR QUADRANT CAUTION APPEARS (LEFT ROTATION)

  • ___________________
  • ___________________
  • ___________________
  • ___________________
A

LOSS OF CONTROL AT LOW AIRSPEED/HOVER OR TAIL ROTOR QUADRANT CAUTION APPEARS (LEFT ROTATION) EPCL(S) - RETARD TO DECREASE% RPM R BELOW 100% & BEGIN A PARTIAL POWER DESCENT COLLECTIVE - ADJUST TO PRESERVE % RPM R ​EPCLS - OFF ( 5 - 10 FEET ABOVE TOUCHDOWN) COLLECTIVE ADJUST FOR LANDING

57
Q

PEDAL BIND / RESTRICTION OR DRIVE WITH NO ACCOMPANYING CAUTION1. ___________________2. Check other pedals for proper operation3. TAIL SERVO switch - BACKUPIf normal control authority is not restored:4. TAIL SERVO switch - NORMAL5.BOOST switch - OFF

A

PEDAL BIND / RESTRICTION OR DRIVE WITH NO ACCOMPANYING CAUTION1. APPLY PEDAL FORCE TO OPPOSE THE DRIVE2. Check other pedals for proper operation3. TAIL SERVO switch - BACKUPIf normal control authority is not restored:4. TAIL SERVO switch - NORMAL5. BOOST switch - OFF

58
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.

  • ___________________
  • BACKUP HYD PUMP switch – ON.
  • LAND AS SOON AS PRACTICABLE.
A

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. TAIL SERVO SWITCH - BACKUP

  • BACKUP HYD PUMP switch – ON.
  • LAND AS SOON AS PRACTICABLE.
59
Q

MAIN XMSN OIL PRESS CAUTION APPEARS / XMSN OIL PRESS LOW / XMSN OIL TEMP HIGH OR XMSN OIL TEMP CAUTION APPEARS1. __________________If time permits:2. Slow to _____ KIAS.3.__________________4. GENERATORS NO.1 and NO. 2 switches - OFF.

A

MAIN XMSN OIL PRESS CAUTION APPEARS / XMSN OIL PRESS LOW / XMSN OIL TEMP HIGH OR XMSN OIL TEMP CAUTION APPEARS1. LAND AS SOON AS POSSIBLEIf time permits:2. Slow to 80KIAS.3. EMERGENCY APU START4. GENERATORS NO.1 and NO. 2 switches - OFF.

60
Q

CHIP INPUT MDL LH OR RH CAUTION APPEARS

  • ____________________________
  • ____________________________
  • ____________________________
A

CHIP INPUT MDL LH OR RH CAUTION APPEARS ESTABLISH SINGLEENGINE AIRSPEED EPCL (AFFECTED ENGINE) - IDLE LAND AS SOON AS POSSIBLE

61
Q

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 ___________________________________

A

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 APPEARSLAND AS SOON AS POSSIBLE

62
Q

MAIN TRANSMISSION FAILURE

  • _______________________________
  • _______________________________
A

MAIN TRANSMISSION FAILURE COLLECTIVE - ADJUST ONLY ENOUGH TO BEGIN A DESCENT WITH POWER REMAINING APPLIED TO THE MAIN TRANSMISSION THROUGHOUT THE DESCENT AND LANDING LAND AS SOON AS POSSIBLE

63
Q

ENGINE/FUSELAGE FIRE ON GROUND

  • _______________________
  • _______________________
  • _______________________
  • _______________________
A

ENGINE/FUSELAGE FIRE ON GROUND EPCLS - OFF ENG EMER OFF HANDLE - PULL IF APPLICABLE FIRE EXTGH SWITCH - MAIN / RESERVE AS REQUIRED EMER ENG SHUTDOWN - PERFORM (OTHER ENG)

64
Q

APU COMPARTMENT FIRE

  • ________________________
  • ________________________
A

APU COMPARTMENT FIRE APU FIRE T - HANDLE - PULL FIRE EXTGHSWITCH - MAIN / RESERVE AS REQUIRED

65
Q 
ENGINE FIRE IN FLIGHT	
* \_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_	
* \_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_	
* \_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_	
* \_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_	
* \_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_\_
A

ENGINE FIRE IN FLIGHT ESTABLISH SINGLE ENGINE AIRSPEED EPCL (AFFECTED ENGINE) - OFF ENG EMER OFF HANDLE - PULL FIRE EXTGH SWITCH - MAIN / RESERVE AS REQUIRED LAND AS SOON AS POSSIBLE

66
Q

ELECTRICAL FIRE IN FLIGHT

  • _______________________
  • _______________________
A

ELECTRICAL FIRE IN FLIGHT BATT AND GENERATORS SWITCHES - OFF LAND AS SOON AS POSSIBLE

67
Q

1 AND #2 FUEL FLTR BYPASS CAUTIONS APPEAR_____________________________

A

1 AND #2 FUEL FLTR BYPASS CAUTIONS APPEARLAND AS SOON AS POSSIBLE

68
Q

1 OR #2 FUEL PRESS CAUTIONS APPEARIf the caution appears and the situation is critical:

  • _______________
  • _______________
  • _______________
  • _______________
A

1 OR #2 FUEL PRESS CAUTIONS APPEARIf the caution appears and the situation is critical: ENG FUEL SYS SELECTOR ON AFFECTED ENGINE- XFD FUEL BOOST PUMP CONTROL SWITCHES - NO. 1 PUMP OR NO. 2 PUMP - ON (AS APPLICABLE) LAND AS SOON AS POSSIBLE EMER ENG SHUTDOWN AFTER LANDING

69
Q

1 AND #2 FUEL PRESS CAUTIONS APPEAR

  • ____________________
  • ____________________
A

1 AND #2 FUEL PRESS CAUTIONS APPEAR LAND AS SOON AS POSSIBLE EMER ENG SHUTDOWN AFTER LANDING

70
Q

1 AND #2 GENERATOR FAILURE (#1 AND #2 CONV AND AC ESS BUS OFF CAUTIONS APPEAR)1. SAS 1 switch - Press off2. Airspeed - Adjust (80 KIAS or less)3. GENERATORS NO. 1 and NO. 2 switches - RESET; then ONIf cautions still appear:4. GENERATORS NO. 1 and NO. 2 switches - OFF5. If MCUs are in use: BCA MCU control knobs (pilot, copilot, and crewmembers) - OFF6. ___________________7. SAS 1 switch – ON8. LAND AS SOON AS PRACTICABLE

A

1 AND #2 GENERATOR FAILURE (#1 AND #2 CONV AND AC ESS BUS OFF CAUTIONS APPEAR)1. SAS 1 switch - Press off2. Airspeed - Adjust (80 KIAS or less)3.GENERATORS NO. 1 and NO. 2 switches - RESET; then ONIf cautions still appear:4. GENERATORS NO. 1 and NO. 2 switches - OFF5. If MCUs are in use: BCA MCU control knobs (pilot, copilot, and crewmembers) - OFF6. EMER APU START7. SAS 1 switch – ON8. LAND AS SOON AS PRACTICABLE

71
Q

1 AND #2 HYD PUMP CAUTIONS APPEAR_____________ Restrict control movement to moderate rates.

A

1 AND #2 HYD PUMP CAUTIONS APPEARLAND AS SOON AS POSSIBLE.Restrict control movement to moderate rates.

72
Q

1 OR #2 HYD PUMP CAUTION APPEARS AND BACK-UP PUMP ON ADVISORY DOES NOT APPEAR1. ___________________2. ___________________If BACK-UP PUMP ON Advisory still does not appear:3. ___________________4. ___________________

A

1 OR #2 HYD PUMP CAUTION APPEARS AND BACK-UP PUMP ON ADVISORY DOES NOT APPEAR1. AIRSPEED - ADJUST2. BACKUP HYD PUMP SWITCH - ONIf 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

73
Q

1 OR #2 PRI SERVO PRESS CAUTIONS APPEAR

  • ______________
  • ______________
  • ______________
A

1 OR #2 PRI SERVO PRESS CAUTIONS APPEAR SVO OFF SWITCHES - CHECK BOTH ARE CENTERED IF THE CAUTION APPEARS WITH THE SVO OFF SWITCH CENTERED, MOVE THE SVO OFF SWITCH TOTURNOFF THE MALFUNCTIONING SERVO LAND AS SOON AS POSSIBLE

74
Q

1 RSVR LOW AND #1 HYD PUMP CAUTIONS APPEAR WITH BACK-UP PUMP ON ADVISORY APPEARING1.LAND AS SOON AS PRACTICABLE.If the BACK-UP RSVR LOW caution also appears:2. _______________3. _______________

A

1 RSVR LOW AND #1 HYD PUMP CAUTIONS APPEAR WITH BACK-UP PUMP ON ADVISORY APPEARING1. LAND AS SOON AS PRACTICABLE.If the BACK-UP RSVR LOW caution also appears:2.SVO OFF SWITCH - 1ST STAGE3. LAND AS SOON AS POSSIBLE

75
Q

2 RSVR LOW AND #2 HYD PUMP CAUTIONS APPEAR WITH BACK-UP PUMP ON ADVISORY APPEARING1. POWER ON RESET switches-Simultaneously press; then release.2. LAND AS SOON AS PRACTICABLE.If the BACK-UP RSVR LOW caution also appears:3. ___________________4. ___________________

A

2 RSVR LOW AND #2 HYD PUMP CAUTIONS APPEAR WITH BACK-UP PUMP ON ADVISORY APPEARING1. POWER ON RESET switches-Simultaneously press; then release.2.LAND AS SOON AS PRACTICABLE.If the BACK-UP RSVR LOW caution also appears:3. SVO OFF SWITCH - 2ND STG4. LAND AS SOON AS POSSIBLE

76
Q

COLLECTIVE BOOST SERVO HARDOVER / POWER PISTON FAILURE

  • ______________________
  • LAND AS SOON AS PRACTICABLE.
A

COLLECTIVE BOOST SERVO HARDOVER / POWER PISTON FAILURE BOOST SWITCH - OFF
* LAND AS SOON AS PRACTICABLE.

77
Q

Emergency Landing In Wooded Areas - Power Off

  • _____________Decelerate helicopter to stop all forward speed at treetop level.
  • _____________to maximum before main rotor contacts tree branches
A

Emergency Landing In Wooded Areas - Power Off
AUTOROTATE.Decelerate helicopter to stop all forward speed at treetop level.
COLLECTIVE - ADJUSTto maximum before main rotor contacts tree branches

78
Q

DITCHING (POWER OFF)

  • _______________________
  • Cockpit doors jettison and cabin doors open prior to entering water.
  • Cyclic-Position in direction of roll.
  • Exit when main rotor has stopped
A

DITCHING (POWER OFF) AUTOROTATE

  • Cockpit doors jettison and cabin doors open prior to entering water.
  • Cyclic-Position in direction of roll.
  • Exit when main rotor has stopped
79
Q

FIGHT CONTROL / MAIN ROTOR SYSTEM MALFUNCTIONSIf the main rotor system malfunctions:

  • ____________________
  • ____________________
A

FIGHT CONTROL / MAIN ROTOR SYSTEM MALFUNCTIONSIf the main rotor system malfunctions: LAND AS SOON AS POSSIBLE EMER ENG(S) SHUTDOWN AFTER LANDING

80
Q

STABILATOR MALFUNCTION – AUTO MODE FAILUREIf an AUTO Mode Failure occurs:1. ___________________2. ___________________If automatic control in 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.4. LAND AS SOON AS PRACTICABLE.If manual control is not possible:5. STAB POS indicator-Check and fly at or below KIAS LIMITS shown on placard.6. LAND AS SOON AS PRACTICABLE.

A

STABILATOR MALFUNCTION – AUTO MODE FAILUREIf an AUTO Mode Failure occurs:1. CYCLIC MOUNTED STABILATOR SLEW-UP SWITCH - ADJUST IF NECESSARY2. AUTO CONTROL SWITCH - PRESS ON ONCE AFTER ESTABLISHING A COMFORTABLE AIRSPEEDIf automatic control in 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.4. LAND AS SOON AS PRACTICABLE.If manual control is not possible:5. STAB POS indicator-Check and fly at or below KIAS LIMITS shown on placard.6. LAND AS SOON AS PRACTICABLE.

81
Q

UNCOMMANDED NOSE DOWN / UP PITCH ATTITUDE CHANGEIf an un-commanded nose down pitch attitude occurs:
* ___________________
* ___________________
* ___________________
* MAN SLEW switch-Adjust to 0° at airspeeds above 40 KIAS and full down at airspeeds below 40 KIAS.
* LAND AS SOON AS PRACTICABLE.
If an un-commanded nose up pitch attitude occurs:
* ___________________
* ___________________
* MAN SLEW switch-Adjust to 0° at airspeeds above 40 KIAS and full down at airspeeds below 40 KIAS.

A

UNCOMMANDED NOSE DOWN / UP PITCH ATTITUDE CHANGEIf an un-commanded nose down pitch attitude occurs: CYCLIC - ADJUST AS REQUIRED COLLECTIVE - MAINTAIN OR INCREASE CYCLIC- MOUNTED STABILATOR SLEW-UP SWITCH - ADJUST AS REQUIRED
* MAN SLEW switch-Adjust to 0° at airspeeds above 40 KIAS and full down at airspeeds below 40 KIAS.
* LAND AS SOON AS PRACTICABLE.
If an un-commanded nose up pitch attitude occurs: CYCLIC - ADJUST AS REQUIRED COLLECTIVE - REDUCE AS REQUIRED
* MAN SLEW switch-Adjust to 0° at airspeeds above 40 KIAS and full down at airspeeds below 40 KIAS.

UH60A/L - 5 and 9 test (2 decks)

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