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Hydraulics > EPs > Flashcards

EPs Flashcards

1
Q

Indication:
No communication with MP + loss of symbology and imagery, loss of MPDs, non- operational UFD

A

EP: dual MP failure - exit NOE environment
- Land as soon as possible
Additional effects: no voice warning or master warning/caution lights
Do not fire weapons, system inhibits are not available
MAN stab, no symbology
Radios and IDM cannot be zeroized

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2
Q

Indications:
PLT FORMAT or CPG format will flash for 3 seconds and remain displayed in HMD

A

EP: single MP failure - NVS select switch- select alternate sensor
Crewmember not on the controls- assume controls
Subsequent effects: video page may not match hmd display
MPD stale condition, on left or right mpd

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3
Q

Ditching power off

A

Autorotate
Canopy- jettison prior to entering water
Cyclic- position in direction of roll
Exit when rotor has stopped

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4
Q

Canopy jettison

A

Helmet visor- down
Area around helicopter- clear of personnel
Canopy jet handle- operate

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5
Q

Indications:
Loss of FLIR image
Possible NVS fail message in HAD
Possible loss of PNVS elevation control

A

EP: NVS failure - exit the NOE environment
- p* NVS select switch- select alternate sensor
Subsequent effects: may take up to 3 seconds for new sensor to slew to your LOS

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6
Q

Indications:
Erratic or no TQ on effected engine
Np exceeds Nr
Np does not drop below Nr with power levers at idle
Possible Engine Overspeed

A

EP: main xmsn input drive clutch failure - achieve safe single engine flight conditions or land
Subsequent effects: most likely on power lever manipulation

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7
Q

Indications: uncommanded flight control input
Resistance or increased force required to move controls
Sluggish flight control response

A

EP: flight control malfunction - FMC release button- press
Subsequent effects: force trim will remain on (unless failed or partial fail)

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8
Q

Indications: loss of yaw control
Possible tail rotor hyd warning

A

EP: tail rotor fixed pitch forward flight - collective- adjust to minimize yaw rate
Cyclic - oppose yaw
If pedals are jammed - break into bucs
Subsequent effects: avoid right turns
Collective application may result in uncontrollable right yaw

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9
Q

Indications: Loss of yaw control
Possible tail rotor hyd failure
(Low airspeed of hover)

A

EP: tail rotor fixed pitch - collective- adjust to minimize yaw rate
Cyclic- minimize drift
If pedals are jammed- break into bucs
Subsequent effects: lowering collective in touch down may result in aircraft rolling

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10
Q

Indications: right yaw with loss of yaw control
Possible GRBX VIBRATION caution

A

EP: loss tail rotor thrust continued flight possible
Airspeed- 100kts minimum (until 10-20ft above touch down)
Subsequent effects: if airspeed goes below 100kts may result in loss of helicopter control

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11
Q

Indications: right yaw with loss of yaw control
Possible GRBX VIBRATION caution

A

EP: loss tail rotor thrust continued flight possible
Airspeed- 100kts minimum (until 10-20ft above touch down)
Subsequent effects: if airspeed goes below 100kts may result in loss of helicopter control

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12
Q

Nr

A

110: max (>110 red)
106-110: transient high 12sec (yellow)
106: high rotor annunciated
95 - 105: normal (green)
0 - 94: transient low (red)

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13
Q

Eng 1 or Eng 2 oil pressure (psi)

A

120: max (>120 red with box)
23 - 120: normal (green)
23: minimum (<23 red)

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14
Q

Hydraulic Pressure limits (psi)

A

> 3410: transient 5 sec (yellow) (> 5 sec red with box)
3310 - 3400: transient 5 min (yellow) (>5min red with box)
2700 - 3300: Normal (green)
1260: minimum (< 1260 red with box)

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15
Q

Engine starter limitations

A

~ must have 60sec between the completion of one cycle and the beginning of the next
~ ambient temp below 61F(16C): 2 consecutive start attempts, 3 min rest, 2 additional attempts, 30 min rest
~ ambient temp above 61F(16C): 2 consecutive start attempts, 30 min rest before additional starts
~ dual engine starts prohibited due to insufficient ipas air

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16
Q

TGT Limits (*C)

A

949: max (red)
904 - 949: transient 12sec (yellow)
880 - 903: Contingency 2.5min (yellow)
847 - 879: Max rated power 10min (yellow)
794 - 846: intermediate rated power 30min (yellow)
793: maximum continuous power
0 - 793: normal (green)

851: max during start
TGT Limiter dual engine: 879 +/- 12
TGT Limiter single engine: 903 +/- 12

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17
Q

np

A

121: max (>121 red with box)
106 - 121: transient 12 sec (yellow)
0 - 105: normal (green)

115: engine over speed annunciated

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18
Q

Ng

A

106: max ( >106 red)
105.1 - 106: transient 12 sec (yellow)
63.1 - 105: normal (green)
63: minimum (<63 red w/box)

19
Q

Torque limits (restricted Nr)

A

Nr < 50
30: maximum (>30 red)
0 - 30: normal (green)

Nr < 90
70: maximum (>70 red)
0 - 70: normal (green)

20
Q

Torque limits - DE

A

115: max (>115 red)
101 - 115: transient 6 sec (yellow)
0-100: normal (green)

21
Q

Torque limits - SE

A

125: max (>125 red)
123 - 125: transient 6 sec (yellow)
111 - 122: single engine contingency 2.5 min (yellow)
110: single engine max continuous power
0 - 110: normal (green)

22
Q

APU operating CAUTION

A

Prolonged operation at 94% - 96% Nr with APU running, APU clutch with oscillate from engaged to disengaged. Creates high loads on the clutch

23
Q

APU starting limits

A

use prohibited in normal flight
after aborted start, wait 30sec before another attempt, after 2 consecutive starts wait 20 min before a third attempt
No more than 3 attempt in an hour

24
Q

APU extended operations

A

If prolonged ground operations longer than 30 min, observe xmsn 1 & 2 temp. If temp exceeds 130*, shut down and let cool for 30min

25
Q

max gross weight

A

max gross weight 20,260 lbs
non-tactical ferry flights 23,000 lbs

26
Q

airspeed limit for autorotation

A

145 ktas

27
Q

Airspeed limit for one engine inop

A

67% Vne

28
Q

Max airspeeds during manual stab

A

depends on the position of the stabilator, can be found on the FLT, FLT SET, SYS pages
can select manual at airspeeds less than 80 kcas

29
Q

Maximum rearward and sideward airspeed

A

45 KTAS

30
Q

Max airspeed for searchlight extension

A

90 KTAS
lighthead can be left in any extended position at speeds up to VNE.

31
Q

Max airspeed for symmetrical external fuel tanks

A

130 KTAS

32
Q

Max airspeed for stores jettison

A

130 KTAS
Hover to 45 KTAS: minimize side slip angle
45 - 130 KTAS: ball centered

33
Q

External tanks jettison

A

Not allowed unless in case of emergency
Must be from airspeeds less than 90 KTAS, level flight if possible

34
Q

pitch and roll limits

A

Pitch: +/- 60
Roll: +/- 120

35
Q

excessive tail rotor scissor loads

A

Avoid aggressive directional and lateral control inputs larger than 1in per sec

36
Q

Excessive tail rotor loads

A

Avoid large pedal step inputs greater than 60*/second

37
Q

Flight with canopy open

A

Prohibited except for smoke or fume elimination

38
Q

Slope landings

A

-asymmetrical configurations, attempts to land >5* should be avoided
- data not available above 17,500 lbs gross weight
- 7* nose up, 12* nose down, 10* roll

39
Q

Flight into turbulence

A

Flight into known or forecast extreme turbulence or into known severe tur-bulence is prohibited.

40
Q

Flight into icing conditions

A

Flight into known or forecast moderate icing is prohibited. Flight in light or trace icing is authorized only as a transient condition. If icing is encountered, attempt to exit the condition as soon as practicable.

41
Q

Flight in IMC conditions

A

The aircraft is not qualified for IMC flight. Backup instruments must be installed and operational for all flights

42
Q

Rotor start/stop limitations

A

Max wind velocity for rotor start/stop is 45kts to prevent droopstop damage

43
Q

Use of force trim

A

Force trim will not be selected off unless in a failed or partial failed mode

Hydraulics (15 decks)

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