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Flight Instruments Pt 3 > Limitation UH60 > Flashcards

Limitation UH60 Flashcards

1
Q

Rotor Brake/Gust Lock
Emergency Max Rotor Speed

A

76%

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2
Q

Rotor Brake/Gust Lock
Below NR%

A

40%

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3
Q

Rotor Brake/Gust Lock
Engine OFF <12 SEC.

A

150-180 PSI

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4
Q

Rotor Brake/Gust Lock
MIN/MAX Rotor Brake

A

450/690 PSI

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5
Q

Rotor Brake/Gust Lock Operating against the gust lock is ____________

A

prohibited

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6
Q

Slope Limitations
NOSE UP/RIGHT/LEFT

A

15 DEG

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7
Q

Slope Limitations
NOSE DOWN

A

6 DEG

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8
Q

Slope Limitations
Max Tail Wind

A

15 KTS

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9
Q

Landing Gear Limitations
Gross Weight Up to 16,825 LBS: Level

A

540 FPM

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10
Q

Landing Gear Limitations
Gross Weight Up to 16,825 LBS: Slope

A

360 FPM

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11
Q

Landing Gear Limitations
Gross Weight Above 16, 825 LBS: Level

A

300 FPM

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12
Q

Landing Gear Limitations
Gross Weight Above 16,825 LBS: Slope

A

180 FPM

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13
Q

APU Operations
43*C Engine/Rotor ON

A

30 minutes

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14
Q

APU operations
51*C Engine/Rotor OFF

A

Continuous

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15
Q

APU Operations
APU Oil Hot Caution

A

30 Minutes

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16
Q

Max Airspeed/Wind Limits
VNE

A

193 KTS

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17
Q

Max Airspeed/Wind Limits
Landing Light Extended Prior To:

A

130 KTS

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18
Q

Max Airspeed/Wind Limits: Landing Light Max Speed Extended

A

180 KTS

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19
Q

Max Airspeed/Wind Limits
Search Light Extended Prior To

A

100 KTS

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20
Q

Max Airspeed/Wind Limits
Search Light Max Speed Extended

A

180 KTS

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21
Q

Max Airspeed/Wind Limits
1 Hydraulic Pump/1 SAS INOP

A

170 KTS

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22
Q

Max Airspeed/Wind Limits
2 Hydraulic Pump/2 SAS INOP

A

150 KTS

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23
Q

Max Airspeed/Wind Limits
2 Hydraulic Pump/2 SAS INO (IMC)

A

140 KTS

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24
Q

Max Airspeed/Wind Limits
Cabin Doors Open

A

145 KTS

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25
Q

Max Airspeed/Wind Limits
Stabilator INOP Autorotation Airspeed Limit

A

120 KTS

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26
Q

Max Airspeed/Wind Limits
Stabilator Full Down at Speeds Below

A

40 KTS

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27
Q

Max Airspeed/Wind Limits
Stabilator Set at 0* Above

A

40 KTS

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28
Q

Max Airspeed/Wind Limits
Max Autorotation Airspeed Below 16,825

A

150 KTS

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29
Q

Max Airspeed/Wind Limits
Max Autorotation Airspeed Above 16,825 LBS

A

130 KTS

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30
Q

Max Airspeed/Wind Limits
Max Airpseed OEI

A

130 KTS

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31
Q

Max Airspeed/Wind Limits
Max Forward Touchdown Speed Limit

A

60

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32
Q

Max Airspeed/Wind Limits
Rotor Start & Stop Winds

A

45 KTS

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33
Q

Max Airspeed/Wind Limits
Side/Rearward Hover Winds

A

45 KTS

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34
Q

Prohibited Manuevers
Hovering Turns

A

30*/sec

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35
Q

Prohibited Maneuvers
Max Pitch

A

30*

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36
Q

Prohibited Maneuvers
Max Roll

A

60*

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37
Q

Prohibited Maneuvers
Simultaneous moving of both ________ levers to ______ or ______ (Throttle Chop) in flight is prohibited

A

EPC
IDLE
OFF

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38
Q

Prohibited Maneuvers
Rearward Ground Taxi is __________

A

prohibited

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39
Q

Cargo Hook Limits
Max Load

A

9000 LBS

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40
Q

Cargo Hook Limits
Max Bank Angle

A

30*

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41
Q

Cargo Hook Limits
Rearward Flight

A

35 KTS

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42
Q

High Speed Yaw Maneuvers
Avoid abrupt full pedal inputs above:

A

80 KTS

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43
Q

Flight in Icing Conditions
Equipment Installed, Operational, & Turned On Permitted to Fly into Trace or Light Icing (List all 5)

A
  1. Windshield Anti-Ice
  2. Pitot Heat
  3. Engine Anti-ice
  4. Engine Inlet Anti-ice Modulating Valve
  5. Insulated Ambient Air Sensing Tube
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44
Q
A
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45
Q
A
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46
Q
A
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47
Q
A
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48
Q
A
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49
Q

Flight in Icing Conditions
Flight into heavy or severe icing is __________________

A

Prohibited

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50
Q

Turbulence & Thunderstorm Operation
Intentional flight into severe turbulence is ______________

A

Prohibited

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51
Q

Turbulence & Thunderstorm Operation
Intentional flight into severe thunderstorms is ______________

A

Prohibited

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52
Q

Turbulence & Thunderstorm Operation
Intentional flight into turbulence with a sling load and an INOP collective trim is ___________

A

Prohibited

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53
Q

Blue Force Tracker Temperature Limits
Normal Operating Temperature *F

A

-6

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54
Q

Blue Force Tracker Temperature Limits
Normal Operating Temperature *C

A

-26-71*c

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55
Q

NP1/NP2
12 Second Transient

A

105-107%

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56
Q

NP1/NP2
High Transient

A

101-105%

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57
Q

NP1/NP2
Continuous

A

95-101%

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58
Q

NP1/NP2
Low Transient

A

91-95%

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59
Q

NP1/NP2
Avoid Operations High

A

60-90%

60
Q

NP1/NP2
Avoid Operations Low

A

20-40%

61
Q

NR Power ON
High Transient

A

101-107%

62
Q

NR Power ON Continuous

A

95-101%

63
Q

NR Power ON
Low Transient

A

91-95%

64
Q

NR Power OFF
Maximum

A

110%

65
Q

NR Power OFF
Transient

A

105-110%

66
Q

NR Power OFF
Normal

A

90-105%

67
Q

NG
12 Second Transient

A

105-106%

68
Q

NG
Continuous

A

0-105%

69
Q

10 Second Transient-Dual Engine
Above 80 KIAS

A

100-144%

70
Q

10 Second Transient-Dual Engine
80 KIAS or Below

A

120-144%

71
Q

10 Second Transient-Single Engine
10 Second Transient

A

135-144%

72
Q

Continuous - Single Engine
Continuous

A

0-135%

73
Q

Continuous-Dual Engine
Above 80 KIAS

A

0-100%

74
Q

Continuous-Dual Engine
80 KIAS or Below

A

0-120%

75
Q

TGT
12 Second Transient

A

903-949*C

76
Q

TGT
2.5 Minute Transient (Continuous Power)

A

879-903*C

77
Q

TGT
Start Abort

A

851*C

78
Q

TGT
10 Minute Limit

A

846-879*C

79
Q

TGT
30 Minute Limit

A

793-846*C

80
Q

TGT
Normal

A

0-793*C

81
Q

Engine Oil Pressure
5 Minute Limit

A

100-120 PSI

82
Q

Engine Oil Pressure
Continuous

A

26-100 PSI

83
Q

Engine Oil Pressure
IDLE

A

22-26 PSI

84
Q

Engine Oil Temperature
30 Minute Limit

A

135-150*C

85
Q

Engine Oil Temperature
Continuous

A

-20-135*C

86
Q

Transmission Oil Pressure
Precautionary

A

65-130 PSI

87
Q

Transmission Oil Pressure
Continuous

A

30-65 PSI

88
Q

Transmission Oil Pressure
IDLE & Transient

A

20-30 PSI

89
Q

Transmission Oil Pressure
>10 Nose UP

A

30-35 PSI

90
Q

Transmission Oil Pressure
>15 Nose UP

A

10-15 PSI

91
Q

Transmission Oil Temperature
Precautionary

A

105-140

92
Q

Transmission Oil Temperature
Continuous

A

-20-105

93
Q

Back Up Pump Operations
Temperature (1 of 3)

A

-54-32*C

94
Q

Back Up Pump Operations
Temperature (2 of 3)

A

33-38*C

95
Q

Back Up Pump Operations
Temperature (3 of 3)

A

39-52*C

96
Q

Back Up Pump Operations
Operation/Cooldown (1 of 3)

A

Unlimited/ n/a

97
Q

Back Up Pump Operations
Operation/Cooldown (2 of 3)

A

24/72 minutes

98
Q

Back Up Pump Operations
Operations/Cooldown (3 of 3)

A

16/48 minutes

99
Q

Engine Starter Limit
<15*C

A

2 Starts/3 Minute Rest/2 Starts/30 Minute Rest

100
Q

Engine Starter Limit
15-52*C

A

2 Starts/30 Minute Rest

101
Q

Engine Starter Limit
Required Before Additional Starts

A

30 Minutes

102
Q

Windshield Anti-Ice Limitations
Anti-Ice Check Max Temperature *C

A

27*C

103
Q

Windshield Anti-ice Limitations
Anti-ice Check Max Temperature *F

A

80*F

104
Q

DUAL-ENGINE FAILURE

Indications:
_________________—–__________________—–___________
*
*
Immediate Actions
1. _________________________________________

A

1 ENG OUT + #2 ENG OUT + Steady Tone

*Change in NP, TGT, NG, Q, P, NR, ENG OUT warnings and audio
*Change in engine noise

  1. Autorotate
105
Q

SINGLE ENGINE FAILURE
Indications
_____________—–________________—–________________
*___________________________
*___________________________

Additional Indications
__________—–__________
__________—–__________

Immediate Actions
1. _______________________________(if possible)
2. ___________________________-________________________

A

1 ENG OUT - or - #2E NG OUT -or - Steady Tone

*Changes in NP, TGT, NG, Q, P, NR, ENG OUT warnings and audio
*Change in engine noise

ENG 1 OIL PRESS - or - ENG 2 OIL PRESS
FUEL 1 PRESS LOW - or - FUEL 2 PRESS LOW

  1. Achieve safe single engine airspeed (if possible)
  2. External cargo/stores - Jettison (if required)
106
Q

FIRES
Indications
_____________
*________________________________________
*________________________________________
*________________________________________

If ENG EMER OFF Handle/APU fire T-handle illuminates in flight:
1. ____________________-_______________________________________________
2. _____________________________-______________________________
3. ______________________________________-_____________(as appropriate)
4. ____________________-_______________________________________________

If an electrical fire is present:
1. _________________________________-________________

Urgency to land
____________________

A

FIRE
*ENG EMER OFF HANDLE-illuminated
*Smoke trail/visible flames/visible arcing or flame, sharp smell

  1. Establish - airspeed of 80 KIAS or less
  2. ENG POWER CONT lever - OFF
  3. ENG EMER OFF handle/APU fire Thandle - Pull (as appropriate)
  4. FIRE EXTGH switch - MAIN/RESERVE as required
  5. BATT and GENERATORS switches - OFF

LAND AS SOON AS POSSIBLE

107
Q

ENGINE CONTROL MALFUNCTION - (DEC/EDECU) LOW SIDE FAILURE
Indications
_______________—______________
*Decreasing NR
*Low Q/TGT malfunctioning engine and high Q/TGT on other engine.

Immediate Actions
If an engine control unit fails to the low side and the other engine is unable to provide sufficient torque, NR will decrease
If NR continues to decrease and single engine flight is not possible:
1. ______________________________-__________________________(Maintain Q approximately 10% below other engine)

A

LOW ROTOR R.P.M. + “Steady Tone”

  1. Engine Power Control lever (low Q/TGT engine) - LOCKOUT (Maintain Q approximately 10% below other engine)
108
Q

The Term Lockout is defined as: __________________________

A

Manual control of engine RPM while bypassing DEC/EDECU functions.

109
Q

STABILATOR MALFUNCTION-AUTO MODE FAILURE
1. _____________________-______________ (as required to arrest nose down pitch rate.)

A
  1. Cyclic mounted stabilator slew-up switch - Adjust (as required to arrest nose down pitch rate)
110
Q

FLIGHT CONTROL/ROTOR SYSTEM VIBRATIONS OR MALFUNCTIONS ON GROUND
Indications
*Feedback
*Main rotor/Tail rotor vibration/Severe main rotor flapping
*Binding
*Resistance
*Sloppiness

Immedeate Actions
1. ___________________-______________
2. ___________________-______________
3. ___________________-______________

Urgency to Land
1. ___________________________________________

A
  1. ENG POWER CONT levers - OFF
  2. ENG FUEL SYS selectors - OFF
  3. FUEL BOOST PUMP switche(s) - Off
  4. LAND AS SOON AS POSSIBLE
111
Q

LIGHTNING STRIKE
Indications
*Immediate maximum power
*System instruments may be inoperative
*Loss of automatic flight control functions
*Loss of electric power
Immediate Actions
1. ______________________________-_________(as required to control NP and NR)
Urgency to Land
_____________________________________________

A
  1. ENG POWER CONT levers - Adjust (as required to control NP and NR)

LAND AS SOON AS POSSIBLE

112
Q

MAIN TRANSMISSION FAILURE
Indications
*NR decrease from 100% to 96% with an increase in Q during steady state flight
*No engine malfunctions
*Unusual helicopter vibrations
Urgency to Land
1. __________________________: (__________________________)

A
  1. LAND AS SOON AS POSSIBLE: (Keep power applied to the main transmission during descent and landing)
113
Q

LOSS OF TAIL ROTOR CONTROL
Indications
*Nose of the helicopter will yaw left/right regardless of airspeed
*At higher airspeed, a right yaw may develop more slowly but may continue to increase
*At high power setting, a left yaw may develop more slowly, but can become more significant if power is decreased
*If tail rotor components are lost, the nose will pitch down. Continued level flight may not be possible following this type of failure.

Immediate Actions
If during cruise flight a right yaw becomes uncontrollable:
1. _______________-_____________________
2. _______________-_____________________(during deceleration when intended point of landing is assured)

If at low airspeed or hover a right yaw becomes uncontrollable:
3. _______________-_____________________
4. _______________-_____________________(5-10 feet above touchdown)

If an uncontrolled left yaw develops during low aispeed or hover:
5. _______________-_____________________
6. _______________-_____________________(NR will decrease)
7. _______________-_____________________(5-10 feet above touchdown)
8. _______________-_____________________ for landing

A
  1. AUTOROTATE - Maintain airspeed at or above 80 KIAS
  2. ENG POWER CONT LEVERS - OFF (during deceleration when intended point of landing is assured)
  3. Collective - Reduce
  4. ENG POWER CONT levers - OFF (5-10 feet above touchdown)
  5. ENG POWER CONT levers - Retard
  6. Collective - Increase (NR will decrease)
  7. ENG POWER CONT levers - OFF 5-10 feet above touchdown)
  8. Collective - Adjust for landing
114
Q

FUEL 1 BYPASS AND FUEL 2 BYPASS
Indications
__________—__________
Urgency to Land
1. ________________________________________

A
  1. LAND AS SOON AS POSSIBLE
115
Q

FUEL 1 PRESS LOW AND FUEL 2 PRESS LOW
Indications
__________—__________
Urgency to Land
1. ________________________________________

A
  1. LAND AS SOON AS POSSIBLE
116
Q

HYD PUMP 1 FAIL AND HYD PUMP 2 FAIL
Indications
__________—__________
Additional indications
__________—__________—__________—__________—__________
Urgency to Land
1. ________________________________(Restrict control movements to moderate rate)

A

HYD PUMP 1 FAIL + HYD PUMP 2 FAIL

TRIM FAIL + FPS FAIL + T/R SERVO 1 FAIL + T/R SERVO 2 ON + BACK-UP PUMP ON

  1. LAND AS SOON AS POSSIBLE
117
Q

HYD PUMP 1 FAIL WITH NO BACK-UP PUMP ON ADVISORY
Indications
__________—__________—__________
Immediate Actions
1. ______________________-_____________

A

HYD PUMP 1 FAIL + T/R SERVO 1 FAIL + PRI SERVO 1 FAIL

  1. BACK-UP HYD PUMP switch - ON
118
Q

T/R SERVO 1 FAIL WITH NO BACK-UP PUMP ON ADVISORY OR T/R SERVO 2 ON ADVISORY DOES NOT APPEAR
Indications
__________

Immediate Actions
1. ___________________________-______

Urgency to Land
LAND AS SOON AS PRACTICABLE

A

T/R SERVO 1 FAIL

  1. TAIL SERVO switch - BACK-UP
119
Q

STABILATOR UNCOMMANDED NOSE DOWN PITCH ATTITUDE CHANGE
Indications: Uncommanded nose down pitch attitude occurs
Immediate Actions:
1. _____________________________-__________(as required to arrest nose down pitch rate)

Urgency to Land
LAND AS SOON AS PRACTICABLE

A
  1. Cyclic mounted stabilator slew-up switch - adjust (as required to arrest nose down pitch rate)
120
Q

COUPLED FLIGHT DIRECTOR MALFUNCTION
Indications: Any uncommanded changes in pitch, roll, or yaw other than those observed in normal flight conditions when coupled to the flight director.

Immediate Actions:
1. _______________-_____________________
If coupled FD does not disengage:
2. _______________-_____________________
If coupled FD does not disengage:
3. _______________-_____________________
After FD is uncoupled:
4. _______________-_____________________

A
  1. RMT SBY swithc - Press to disengage FD modes
  2. CPLD switch - Press to uncouple FD
  3. FPS and TRIM switches - OFF
  4. FPS and TRIM switches - ON
121
Q

AFCS
1. ____________
2. ____________
3. ____________
4. ____________
5. ____________

A
  1. SAS
  2. Trim
  3. FPS
  4. Stabilator
  5. Coupled Flight Director
122
Q

FPS
Basic autopilot-Enhances ______________ through ______________ in pitch, roll, and yaw. It is the “Brain”. When coupled with Trim, FPS has ______ control auth at ______ per sec

A

Static stability
Long term rate dampening
100%
10%

123
Q

FPS
Below 50 KTS: Above 50 KTS:
1. 1.
2. 2.
3. 3.

A
  1. Att. hold PITCH 1. Att. Hold
  2. Att. hold ROLL 2. Att. Hold
  3. Hdg Hold YAW 3. Head Hold/Tn coor
124
Q

FPS
These systems must be ______ and _________ for FPS to func. at 100%
1. ____________
2. ____________
3. ____________
4. ____________

A

on
operational
1. SAS 1 and/or SAS 2
2. SAS/Boost
3. Trim
4. Stabilator (helps, but not required)

125
Q

TRIM
Provies a __________ and ____________ holding force for _____, ______, _____, and _____. Consists of 3 electromechanical actuators (__________, __________, __________), and 1 electrohydromechanical actuator (_________).
_________/_________ required for operation.
Slip clutch req. _____lbs max in yaw, _____ lbs max in roll, _____ lbs max collective during actuator jam. FCC monitors ____________, will turn off ____________________.

A

gradient
detent
pitch, roll, collective, yaw
roll, yaw, collective
pitch
SAS/Boost
80
22
13
continuously
driving trim actuator

126
Q

AVCS
Reduces __________ and ______________ vibrations by mechanically generating additional vibrations that are ______________________ with the main rotor (_________________). (1 FG - _____________lbs, 2 FG ______________ lbs)
Uses ____ Force Generators, ___ MU’s each

A

cabin
cockpit
out-of-phase
90-105 NR
1,000
450
3
2

127
Q

SAS 1&2
Provides _______________________ in pitch, roll, and yaw axes. Enhances turn coord >___kts. Hover augment <_____kts _____% cont. auth. Ea. controlled by respective _____ computers.
Input:
1. _________, ________, and _________ signals from resp. ________(Nose)
2. __________, air data computer
3. Malf indicated by ______________, reset CPTR 1/2, or turn off that SAS

A

short term rate dampening
50
50
5
FCC
1. pitch, roll, yaw, EGIs
2. Airspeed
3. erratic movement

128
Q

STABILATOR
Variable __________________ airfoil that ________ the handling qualities in the pitch axis in __________ flight.
SCALP
1. ____________ w/rotor downwash at low speed (below _____kts) to minimize nose up attitude from downwash. (_____,_____)
2. ___________________ to minimize ________ attitude excursions due to ______________.
3. ________________________ decreases above _____kts to improve ____________________. (_____,_____)
4. ________________________ to _______________ to reduce susceptibility to _____. Stab ___ for right pedal, stab ___ for left pedal. (_______________)
5. ________________________ to improve dynamic stability. Dampen __________________ due to turbulence of “G” forces. (_____,_____)

A

angle of incidence
enhances

  1. Streamlines, 30 kts, (ADC, FCC)
  2. Collective Coupling, pitch, collective inputs
  3. Angle of Incidence, 30 kts, static stability (ADC,FCC)
  4. Lateral Sideslip, pitch coupling, gusts, up, down, (Lat. accelerometers)
  5. Pitch Rate Feedback, pitch excursions, (EGI,FCC)
129
Q

ODV
HOPS
1. ____________ shuts fuel flow at _____*C, NG ,____%, Np<____%
2. ____________ (NP) from ______ at _______+-1%
3. ____________ main fuel manifold and allows ____________ of ___________ for purging.
4. ____________ fuel through _________ to ____________ for starting & engine operation.

A
  1. Hot start prevention, 900*C, 60%, 50%
  2. Over-speed protection, DEC, 120 +- 1%
  3. Purges, back-flow, high-pressure air
  4. Sends, manifold, injectors
130
Q

HMU
Basic ___________; incl. __________ fuel pump & ________________ servo-actuator.
PM CAN VDTO
1. ____________ fuel at __________

  1. ____________ fuel to ______ in response to ______, _____, ___ motor from DEC, & _________ variables.
  2. ____________ through the _____. When the collective is moved, ____ is reset for immediate _____ response.
  3. ____________ flow limiting preventing _____________, __________, or ___________.
  4. ____________-Limits ______________ under low temp conditions.
  5. ____________ of the ___________________________ for optimum performance.
  6. ________________________________________________. Allows pilot to mechanically bypass _________________.
  7. ____________ To fine tune ______________. Can be overridden in _____________.
  8. ____________for manual _____ priming, to remove air from _____.
A

fuel control, high press., variable geometry
1. pumps, high pressure

  1. Meters, ODV, PAS, LDS, Q, engine
  2. Collective Pitch Compensation, LDS, Ng, Np
  3. Accel/Decel, compressor stalls, engine damage, flame out
  4. Ng limiting, max torque available
  5. Variable Geometry Positioning, inlet guide vanes
  6. DEC lockout PAS Override & Control with DEC Inoperative, torque motor inputs
  7. Torque Motor to Trim NG Output, engine output, DEC lockout
  8. Opens Vapor Vent, HMU, HMU
131
Q

DEC
Controls ____________ of engines and transmits operation info to ____________.

TINT SHHOT F

  1. ____________: Limits fuel flow when reaching appx. _____ Dual Eng., _____(___min) when opp Q is <50%
  2. ____________ DEC will maintain _____ reference
  3. ____________ from the cockpit, (INCR/DECR from _____-_____%)
  4. ____________ Increase Q of ______ side to match up to ___% NP above reference.
  5. ____________: Sends signals to the cockpit for___, ___, and ___
  6. ____________ Sends signals to _________________
  7. ____________ Tells ___ to shut off fuel when _____*C is reached, Ng<___%, Np<___%.
  8. ____________Triggered when Np reaches ______+-1%
  9. ____________ 4 to 1 improvement to compensate for _________________. Uses collective position xducer signal.
  10. ____________DEC code sent to _________ indicators and _________ status page.
A

electronic functions, cockpit

  1. TGT Limiting, 879, 903(2.5 min)
  2. Isochronous NP Governing, NP
  3. NP Reference, 96-100%
  4. Torque Matching/Load Sharing, low, 3%
  5. Signals to Cockpit, Np, Q, TGT
  6. History counter, history counter
  7. Hot Start Preventer, ODV, 900*C, 60%, 50%
  8. Overspeed Protection, 120 +- 1%
  9. Transient Droop Compensation, transient rotor droop
  10. Fault Monitor, ENG Q, FMS DEC
132
Q

Power Pod
1. Displays ___, ___, ___, ___, and ___
2. NG displays only above _____% NG or NG1/NG2 difference >= ___% or _____ engine out.
3. TGT displays only above _____C or TGT difference >=___C or _____ out

A
  1. NR, NP, Q, NG, TGT
  2. 100%, 5%, DCU
  3. 793C, 75C, DCU
133
Q

Stormscope WX-500
1. Detects withing ____NM x or +
2. Stores up to ________ individual _____ or _____ positions for ___ minutes.
3. Maximum of _____ most recent strikes and cells are displayed at any one time.

A
  1. 200
  2. 3600, strike, cell
  3. 128
134
Q

Weight-On Wheels Switch

CHAFF AIM TUBE

  1. ____________: IBIT, erase on gnd
  2. ____________ leak test disabled in flight
  3. ____________ for low NR disabled on the ground.
  4. ____________enabled in-flight
  5. ____________acft, EGI GC or GPC alignment IBIT on ground/EGI air alignment in flight
  6. ____________ Pitch, Roll Att hold/ Hdg hold/ Maneuvering Stab/ Rad Alt hold/ Airspeed hold - Enabled in-flight
  7. ____________Auto Zeroize enabled in flight.
  8. ____________status page activation on grnd
  9. ____________protection for B/U pump enabled on the ground
  10. ____________protection disabled in flight (right switch)
  11. ____________regardless of switch position enabled in flight. Disabled ond gnd unless Acc. Low
  12. ____________jettison disabled on ground. (right switch)
A
  1. CVR/FDR
  2. Hydraulic
  3. Audio
  4. Flight Dir. Modes
  5. FMS-Model
  6. AFCS
  7. IFF Mode 4
  8. MFD
  9. Thermal
  10. Underfreq.
  11. B/U Pump Auto OPN
  12. ESS
135
Q

Engine Alternator NID
Three windings for three functions:
1. ___ signal to cockpit _______ (_____)
2. __________ power to the _________ during start. (_____)
3. _______ power (_____)
Loss of alternator does not result in __________ because of _____________ to DEC.

A
  1. NG, tachometer, green
  2. Ignition, exciters, yellow
  3. DEC yellow
136
Q

Collective Capture:
1. ____________
2. ____________
3. ____________
4. ____________
5. ____________
6. ____________

A
  1. ALT
  2. ALTP
  3. GS
  4. RALT
  5. GA
  6. VS
137
Q

Pitch Capture:
1. ____________
2. ____________
3. ____________
4. ____________

A
  1. DCL
  2. IAS
  3. POSN (Hover)
  4. VHLD (Hover)
138
Q

Roll Armed
1. ____________
2. ____________

Roll Capture:
1. ____________
2. ____________
3. ____________
4. ____________
5. ____________

A

Roll Armed
1. LOC
2. NAV (VOR)

Roll Capture
1. BC
2. HDG
3. LNAV
4. LOC
5. NAV (VOR)

139
Q

Fuel Flow in the Engine

  1. ____________
  2. ____________
  3. ____________
  4. ____________
  5. ____________
A
  1. Pump (engine driven)
  2. Fuel filter
  3. HMU
  4. Liquid to liquid cooler
  5. ODV
140
Q

Mechanical Mixing

Collective to Pitch

A

compensates for rotor downwash on the stabilator

141
Q

Mechanical Mixing

Collective to Roll

A

Translating Tendency

142
Q

Mechanical Mixing

Collective to Yaw

A

Torque Effect

143
Q

Mechanical Mixing

Yaw to Pitch

A

Lift component of Tail Rotor

144
Q

Electronic Coupling

Collective to Airspeed to Yaw- Compensates for ___________ in addition to ____________ to _________ mixing based on ___________________ and ______________. FCC#___ commands yaw trim actuator _____% below ___kts, decreases until ____kts, none above _____kts.

A

torque effect
collective
yaw
collective position
airspeed
2
100%
40kts
100kts
100kts

145
Q
A

Flight Instruments Pt 3 (10 decks)

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