EPs Flashcards
Indication:
No communication with MP + loss of symbology and imagery, loss of MPDs, non- operational UFD
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
Indications:
PLT FORMAT or CPG format will flash for 3 seconds and remain displayed in HMD
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
Ditching power off
Autorotate
Canopy- jettison prior to entering water
Cyclic- position in direction of roll
Exit when rotor has stopped
Canopy jettison
Helmet visor- down
Area around helicopter- clear of personnel
Canopy jet handle- operate
Indications:
Loss of FLIR image
Possible NVS fail message in HAD
Possible loss of PNVS elevation control
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
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
EP: main xmsn input drive clutch failure - achieve safe single engine flight conditions or land
Subsequent effects: most likely on power lever manipulation
Indications: uncommanded flight control input
Resistance or increased force required to move controls
Sluggish flight control response
EP: flight control malfunction - FMC release button- press
Subsequent effects: force trim will remain on (unless failed or partial fail)
Indications: loss of yaw control
Possible tail rotor hyd warning
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
Indications: Loss of yaw control
Possible tail rotor hyd failure
(Low airspeed of hover)
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
Indications: right yaw with loss of yaw control
Possible GRBX VIBRATION caution
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
Indications: right yaw with loss of yaw control
Possible GRBX VIBRATION caution
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
Nr
110: max (>110 red)
106-110: transient high 12sec (yellow)
106: high rotor annunciated
95 - 105: normal (green)
0 - 94: transient low (red)
Eng 1 or Eng 2 oil pressure (psi)
120: max (>120 red with box)
23 - 120: normal (green)
23: minimum (<23 red)
Hydraulic Pressure limits (psi)
> 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)
Engine starter limitations
~ 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
TGT Limits (*C)
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
np
121: max (>121 red with box)
106 - 121: transient 12 sec (yellow)
0 - 105: normal (green)
115: engine over speed annunciated
Ng
106: max ( >106 red)
105.1 - 106: transient 12 sec (yellow)
63.1 - 105: normal (green)
63: minimum (<63 red w/box)
Torque limits (restricted Nr)
Nr < 50
30: maximum (>30 red)
0 - 30: normal (green)
Nr < 90
70: maximum (>70 red)
0 - 70: normal (green)
Torque limits - DE
115: max (>115 red)
101 - 115: transient 6 sec (yellow)
0-100: normal (green)
Torque limits - SE
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)
APU operating CAUTION
Prolonged operation at 94% - 96% Nr with APU running, APU clutch with oscillate from engaged to disengaged. Creates high loads on the clutch
APU starting limits
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
APU extended operations
If prolonged ground operations longer than 30 min, observe xmsn 1 & 2 temp. If temp exceeds 130*, shut down and let cool for 30min
max gross weight
max gross weight 20,260 lbs
non-tactical ferry flights 23,000 lbs
airspeed limit for autorotation
145 ktas
Airspeed limit for one engine inop
67% Vne
Max airspeeds during manual stab
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
Maximum rearward and sideward airspeed
45 KTAS
Max airspeed for searchlight extension
90 KTAS
lighthead can be left in any extended position at speeds up to VNE.
Max airspeed for symmetrical external fuel tanks
130 KTAS
Max airspeed for stores jettison
130 KTAS
Hover to 45 KTAS: minimize side slip angle
45 - 130 KTAS: ball centered
External tanks jettison
Not allowed unless in case of emergency
Must be from airspeeds less than 90 KTAS, level flight if possible
pitch and roll limits
Pitch: +/- 60
Roll: +/- 120
excessive tail rotor scissor loads
Avoid aggressive directional and lateral control inputs larger than 1in per sec
Excessive tail rotor loads
Avoid large pedal step inputs greater than 60*/second
Flight with canopy open
Prohibited except for smoke or fume elimination
Slope landings
-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
Flight into turbulence
Flight into known or forecast extreme turbulence or into known severe tur-bulence is prohibited.
Flight into icing conditions
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.
Flight in IMC conditions
The aircraft is not qualified for IMC flight. Backup instruments must be installed and operational for all flights
Rotor start/stop limitations
Max wind velocity for rotor start/stop is 45kts to prevent droopstop damage
Use of force trim
Force trim will not be selected off unless in a failed or partial failed mode
