Chapter 5 Flashcards
(109 cards)
1
Q
Any time an operational limit is exceeded, an appropriate entry shall be made on __1__.
Entry shall state what __2__, __3__, __4__, __5__ that would aid maintenance personnel in the maintenance action that may be required.
The helicopter __6__.
A
- DA Form 2408-13-1
- limit(s) were exceeded
- range
- time beyond limits
- and any additional data
- shall not be flown until corrective action is taken
2
Q
Minimum Crew Requirements
A
The minimum crew required to fly the helicopter is two pilots.
3
Q
Additional crewmembers, as required, will be added __1__, in accordance with pertinent __2__.
A
- at the discretion of the commander
- Department of the Army regulations
4
Q
EICAS: Red and yellow striped tapes and red readouts indicate _____.
A
the limit above or below which continued operation is likely to cause damage or shorten component life
5
Q
EICAS: Yellow tapes and readouts indicate _____.
A
the range when special attention should be given to the parameter the instrument represents
6
Q
EICAS: Green tapes and readouts indicate _____.
A
the normal operating range of the parameter the instrument represents
7
Q
Rotor Limitations: It is normal to observe and NP speed split during autorotational descent when the __1__.
A speed increase of one engine from 100% reference to __2__ maximum can be expected.
During power recovery, it is normal for the __3__ to lead the other engine.
A
- engines are fully decoupled from the main rotor
- 107%
- engine operating above 100% NP
8
Q
Maximum wind velocity for rotor start or stop is _____ from any direction.
A
45 knots
9
Q
Power off (autorotation) rotor speeds up to __1__ are authorized for use by __2__ during __3__.
A
- 120% NR
- maintenance test flight pilots
- autorotational RPM checks
10
Q
Operating an engine against the _____ is prohibited.
A
gust lock
11
Q
Rotor brake shall not be applied with engine(s) operating and rotor turning except during an _____.
A
emergency stop
12
Q
Maximum rotor speed for emergency rotor brake applications is _____.
A
76% NR
13
Q
Routine stops will be with __1__, __2__, and with __3__ applied to stop the rotor in not less than __4__.
A
- engine(s) off
- NR below 40%
- 150-180 psi
- 12 seconds
14
Q
Minimum rotor brake pressure for engine start is __1__. Maximum rotor brake pressure for engine start is __2__.
A
- 450 psi
- 690 psi
15
Q
Use of the rotor brake with engine(s) operating is restricted to single and dual engine starts and operations at _____.
A
IDLE only
16
Q
Single and dual engine starts and operation at __1__ with rotor brake on are __2__.
A
- IDLE
- not time limited
17
Q
Transmission oil pressure should remain steady during __1__ or __2__.
A
- steady state forward flight
- in a level hover
18
Q
Momentary fluctuations in transmission oil pressure may occur during __1__, or when flying with pitch attitudes above __2__. These types of oil pressure fluctuations are acceptable, even when pressure drops into the yellow range (blow 30 psi).
A
- transient maneuvers (i.e. hovering in gusty wind conditions
- +6%
19
Q
Transmission oil pressure should remain steady and should be in the __1__ to __2__ range to ensure that when fluctuations occur, they remain in the acceptable range.
A
- 45 psi
- 60 psi
20
Q
If transmission oil pressure is not steady during steady state forward flight or in a level hover, or if oil pressure is steady but under _____, make an entry on the appropriate maintenance form.
A
45 psi
21
Q
Sudden transmission pressure drop (more than _____) without fluctuation requires and entry on the appropriate maintenance form.
A
10 psi
22
Q
A demand for maximum power from engines with different __1__ will cause a torque split when the __2__ reaches __3__.
This torque split is normal.
Under these circumstances, the __4__ may exceed the __5__.
A
- engine torque factors (ETF)
- low ETF engine
- TGT limiting
- high power engine
- dual engine limit
23
Q
With transmission oil temperature operation in the __1__, an entry should be made on the appropriate maintenance form except when __2__.
A
- precautionary range
- hovering in adverse conditions (desert and hot weather)
24
Q
Power Turbine Speed (NP) Limitaions
A
Avoid operations in 20-40% and 60-90% except during start and shutdown.
- Transient (91-95%)
- Continuous (95-101%)
- Transient (101-105%)
12 Second Transient (105-107%)
25
Rotor Speed (NR) Power-On Limitations
1. Transient (91-95%)
2. Continuous (95-101%)
3.
26
Rotor Speed (NR) Power-Off (Autorotation) Limitations
2. Normal (90-105%)
3. Transient (105-11%)
Maximum (110%)
Upper red range begins at 110% to correspond with the power off limit.
27
Gas Generator Speed (NG) Limitations
1. Continuous (0-105%)
2. 12-Second Transient (105-106%)
28
Torque (Q) Limitations
1. Continuous: Dual Engine \>80 KIAS (0-100%)
2. Continuous: Dual Engline \<80 KIAS (0-120%)
3. Continuous - Single Engine (0-135%)
4. 10 Second Transient (100/120/135-144%)
29
Turbine Gas Temperature (TGT) Limitations
1. Normal (0-793°C)
2. 30 Minute Limit (793-846°C)
3. 10 Minute Limit (846-879°C)
4. 2.5 Minute Transient (Contingency Power) (879-903°C)
12 Second Transient (903-949°C)
Start Abort Limit (851°C)
30
Turbine Gas Temperature (TGT) Limitations
1. Normal (0-793°C)
2. 30 Minute Limit (793-846°C)
3. 10 Minute Limit (846-879°C)
4. 2.5 Minute Transient (Contingency Power) (879-903°C)
12 Second Transient (903-949°C)
Start Abort Limit (851°C)
31
Engine Oil Temperatue Limitations
1. Continuous (-20-135°C)
2. 30 Minute Limit (135-150°C)
32
Engline Oil Pressure Limitations
1. IDLE (22-26 psi)
2. Normal (26-100 psi)
3. 5 Minute Limit (100-120 psi)
33
Transmission Oil Temperature Limitations
1. Continuous (-20-105°C)
2. Precautionary (105-140°C)
34
Transmission Oil Pressure Limitations
1. IDLE & Transient (20-30 psi)
2. Continuous (30-65 psi)
3. Precautionary (65-130 psi)
35
Fuel Limitations
1. Normal (\>200 lb - each tank)
2. Precautionary (0-200 - each tank)
36
Transient NP operation in yellow range (101%
to 105%) is \_\_\_\_\_.
However, no damage to either engine or drive train is
incurred by operation within this range.
not recommended as good operating practice
37
The pneumatic starter is capable of making the
number of consecutive start cycles with an
interval of at lease \_\_\_\_\_.
60 seconds between the completion of
one cycle and the beginning of the next cycle
38
A pneumatic starting cycle is the interval from \_\_1\_\_ and \_\_2\_\_, from \_\_3\_\_, to \_\_4\_\_.
1. start iniatiation
2. acceleration of the compressor
3. zero rpm
4. starter dropout
39
The \_\_1\_\_ between start attempts applies when the first attempt is \_\_2\_\_, and it applies regardless of the duration of the first attempt.
If motoring is required for an emergency, the 60 second delay \_\_3\_\_.
1. 60 second delay
2. aborted for any reason
3. does not apply
40
At ambient temperatures of \_\_1\_\_, \_\_2\_\_ consecutive start cycles may be made, followed by a \_\_3\_\_ rest period, followed by \_\_4\_\_ additional consecutive start cycles. A \_\_5\_\_ rest period is then required before any additional starts.
1. 15°C and below
2. two
3. 3 minute
4. two
5. 30 minute
41
At ambient temperatures \_\_1\_\_ up to \_\_2\_\_, \_\_3\_\_ consecutive start cycles may be made. A \_\_4\_\_ rest period is then required before any additional start cycles.
1. above 15°C
2. 52°C
3. 2 minute
4. 30 minute
42
The minimum ground-air source (pneumatic) required to start the helicopter engines is \_\_1\_\_ and \_\_2\_\_ at \_\_3\_\_.
1. 40 psig
2. 30 ppm
3. 149°C
43
The maximum ground-air source (pneumatic) to be applied to the helicopter is \_\_1\_\_ at \_\_2\_\_, measured at the \_\_3\_\_ on the fuselage.
1. 50 psig
2. 249°C
3. external air connector
44
CAUTION:
Engine start attempts at or above a pressure altitude of _____ could result in a hot start.
18,000 feet
45
Crossbleed starts shall not be attempted unless the \_\_1\_\_ does not appear, and operating engine must be at \_\_2\_\_ and rotor speed at \_\_3\_\_.
1. ENG 1/2 ANTI-ICE ON advisory
2. 90% NG or above
3. 100% NR
46
When attempting single-engine starts at pressure altitudes above \_\_1\_\_, press the start switch with the ENG POWER CONT lever OFF, until the \_\_2\_\_ is reached, before going to IDLE.
1. 14,000 feet
2. maximum motoring speedd (about 24%)
47
Engine overspeed check in flight is \_\_1\_\_. Engine overspeed checks, on the ground, are authorized by \_\_2\_\_.
1. prohibited
2. designated maintenance personnel only
48
Fuel boost pumps shall be off except as required by \_\_1\_\_.
Or when operating with \_\_2\_\_: at \_\_3\_\_ or when operating in \_\_4\_\_.
1. emergency procedures
2. JP-4 or equivenlant
3. 5000 feet pressure altitude or above
4. crossfeed at any altitude
49
CAUTION:
Due to fuel volatility, when converting from JP-4 to JP-5/8, \_\_1\_\_ helicopter refueling operations must be completed before performing operations with \_\_2\_\_.
1. three
2. fuel boost pumps off
50
When a helicopter operating with JP-4 is restarted within \_\_1\_\_ of engine shutdown and the air temperature is above \_\_2\_\_, a minimum of \_\_3\_\_ of dual engine group operation at \_\_4\_\_ is required prior to takeoff to purge possible hot fuel from engine nacelle area.
1. 2 hours
2. 21° C
3. 2 minutes
4. 100% NR
51
Maximum Weight
22,000 lb
23,500 lb (external lift)
52
External lift missions above \_\_1\_\_ can only be flown with cargo hood loads above \_\_2\_\_ and up to \_\_3\_\_.
1. 22,000 lb
2. 8,000 lb
3. 9,000 lb
53
Maximum weight is further limited by cargo floor maxium capacity of _____ per square foot.
300 lb
54
Maximum capacity for each storage compartment is \_\_\_\_\_.
125 lb
55
The \_\_1\_\_ cabin ceiling tiedown fittings have a limited load capacity of \_\_2\_\_.
1. four
2. 4,000 lb
56
The \_\_1\_\_ tiedown fittings installed on the cargo floor can restrain a \_\_2\_\_ load in any direction.
1. 17
2. 5,000 lb
57
The \_\_1\_\_ net restraint rings in the cargo compartment are rated at \_\_2\_\_ capacity in any direction.
1. eight
2. 3,500 lb
58
The maximum weight that may be suspended from the cargo hook is \_\_\_\_\_. The external load limit of the airframe will not be exceeded when using the cargo hook.
9,000 lb
59
The maxium weight that may be suspended from the rescue hoist is \_\_\_\_\_.
600 lb
60
The airspeed operating limits charts define velocity never exceed (Vne) as a function of \_\_1\_\_, \_\_2\_\_, and \_\_3\_\_.
The dashed lines represent the Mach limited airspeeds due to \_\_4\_\_ effects.
1. altitude
2. temperature
3. gross weight
4. compressibility
61
Maximum airspeed: external cargo hook loads up to 8,000 lb
140 KIAS
62
Maximum airspeed: external cargo hook loads greater than 8,000 lb shall not exceed
120 KIAS
63
Maximum airspeed: one engine inoperative
130 KIAS
64
Maximum airspeed: autorotation at a gross weight of 16,825 lb or less
150 KIAS
65
Maximum airspeed: autorotation at a gross wight of 16,825 or more
130 KIAS
66
Hovering in winds greater than \_\_1\_\_ from the sides or rear is \_\_2\_\_.
Sideward/rearward flight into the wind, when combined with windspeed, shall not exceed \_\_3\_\_.
1. 45 knots
2. prohibited
3. 45 knots
67
Airspeed limits:
one SAS inoperative
two SAS inoperative
two SAS inoperative in IMC
170 KIAS
150 KIAS
140 KIAS
68
Airspeed limits:
one hydraulic system inoperative
two hydraulic systems inoperative
two hydraulic systems inoperative in IMC
170 KIAS
150 KIAS
140 KIAS
69
Landing light must be extended prior to reaching a maximum forward airspeed of \_\_1\_\_.
With landing light extened, airspeed is limited to \_\_2\_\_.
1. 130 KIAS
2. 180 KIAS
70
Searchlight must be extended prior to reaching a maximum forward airspeed of \_\_1\_\_.
With searchlight extened, airspeed is limited to \_\_2\_\_.
Rescue hoist searchlight airspeed limits are the same as above.
1. 100 KIAS
2. 180 KIAS
71
Cabin door(s) may be fully open up to \_\_\_\_\_.
145 KIAS
72
The door(s) will not be intentionally moved from the \_\_1\_\_ in flight unless specific mission dictates otherwise (rescue hoist operations).
If you are required to open cabin doors in flight, the aircraft must be below \_\_2\_\_ and crew members opening the cabin door must be secured to the aircraft prior to opeing the cabin door.
1. fully open or closed position
2. 80 KIAS
73
Flight with cockpit door(s) removed is \_\_\_\_\_.
prohibited
74
NOTE:
Vne becomes variable to indicate the airspeed limit applicable for the current stabilator position, except in no case shall the autorotation limit exceed \_\_\_\_\_.
120 KIAS
75
If the automatic stablilator control system fails in flight and operation cannot be restored:
stabilator shall be set \_\_1\_\_ at speeds below \_\_2\_\_.
stabilator shall be set at \_\_3\_\_ at speeds above \_\_4\_\_.
1. full down
2. 40 KIAS
3. 0°
4. 40 KIAS
76
Hovering turns greater than \_\_1\_\_ are prohibited.
Intentional maneuvers beyond attitudes of \_\_2\_\_ pitch or over \_\_3\_\_ roll are prohibited.
1. 30° per second
2. 30°
3. 60°
77
Simultaneous moving of both \_\_1\_\_ to \_\_2\_\_ or \_\_3\_\_ in flight is prohibited.
1. ENG POWER CONT levers
2. IDLE
3. OFF
78
\_\_\_\_\_ ground taxi is prohibited.
Rearward
79
Prohibited Maneuvers
1. Hover turns greater than 30° per second are prohibited. Intentional maneuvers beyond attitudes of 30° pitch or over 60° roll.
2. Simultaneous moving of both ENG POWER CONT levers to IDLE or OFF in flight.
3. Rearward ground taxi.
80
Restricted Maneuvers
1. Manual operation of the stabilator
2. Downwind hovering
81
Manual operation of the stabilator in flight is \_\_1\_\_ except as requird by \_\_2\_\_ and \_\_3\_\_ or as alternate stabilator control in case the AUTO mode malfunctions.
1. prohibited
2. formal training
3. maintenance test flight requirements
82
Prolonged rearward flight and downwind hovering are to be avoided to prevent \_\_1\_\_ in the helicopter and \_\_2\_\_ to windows on open cargo doors.
1. accumulation of exhaust fumes
2. heat damage
83
NOTE:
Maneuvers entered from a \_\_1\_\_ may result in transient droop of \_\_2\_\_ or greater.
1. low power setting
2. 5% NR
84
The blade stall chart provides the level flight angle of bank at which blade stall will begin to occur as a function of \_\_1\_\_, \_\_2\_\_, \_\_3\_\_, and \_\_4\_\_.
1. airspeed
2. gross weight
3. pressure altitude
4. temperature
85
When operating near blade stall, any increase in \_\_1\_\_, \_\_2\_\_, \_\_3\_\_, or \_\_4\_\_ will increase the severity of the stall.
1. airspeed
2. load factor (bank angle)
3. turbulence
4. abrupt control inputs
86
Fully developed stall wil be accompanied by \_\_1\_\_, increasing \_\_2\_\_, and loss of \_\_3\_\_.
1. heavy vibrations
2. torque
3. altitude
87
Stall recovery is always accomplished by reducing the severity of the maneuver, that is by reducing \_\_1\_\_, \_\_2\_\_, \_\_3\_\_.
1. collective
2. airspeed
3. angle of bank
88
Above \_\_1\_\_ avoid \_\_2\_\_ to prevent excess tail rotor system loading.
1. 80 KIAS
2. abrupt, full pedal inputs
89
Maneuvering limitations with a sling load or rescue hoist loads are limited to \_\_1\_\_ in forward flight.
Side flight is limited by \_\_2\_\_ and is \_\_3\_\_ as airspeed increases.
Rearward flight is limited to \_\_4\_\_.
Rate of descent is limited to \_\_5\_\_.
1. 30° angle of bank
2. bank angle
3. decreases
4. 35 knots
5. 1,000 feet-by-minute
90
Bank angles shall be limited to _____ when a PRI SERVO FAIL caution appears.
30°
91
Do not exceed a touchdown sink rate of \_\_1\_\_ on level terrain and \_\_2\_\_ on slopes with gross weights of up to 16,825 pounds.
Above 16,825 pounds gross weight do not exceed \_\_3\_\_ on level terrain and \_\_4\_\_ on slopes.
1. 540 feet-per-minute
2. 360 feet-per-minute
3. 300 feet-per-minute
4. 180 feet-per-minute
92
Maximum forward touchdown speed is limited to _____ ground speed on level terrain.
60 knots
93
NOTE:
Because of the flat profile of the main transmission and forward location of both transmission oil pumps, transmission oil pressure will drop during nose-up slope operations.
At slope of 10°, an indicated oil pressure of \_\_1\_\_ to \_\_2\_\_ is normal; at slope of 15°, a pressure in the range of \_\_3\_\_ to \_\_4\_\_ is normal.
1. 30 psi
2. 35 psi
3. 10 psi
4. 15 psi
94
Slope limitations:
\_\_1\_\_ nose-up, and \_\_2\_\_ right wheel up or left wheel up
Further reduced by \_\_3\_\_ for every \_\_4\_\_.
1. 6°
2. 15°
3. 2°
4. 5 knots of wind
95
Slope limitations:
6° downslope
Landing in downslope conditions with tail wind greater than _____ shall not be conducted.
15 knots
96
The main gearbox may be operated up to _____ at a time with pressure fluctuations when the helicopter is known to be at a nose-up attitude.
30 minutes
97
NOTE:
The ice detecting system is calibrated for \_\_\_\_\_. When flying at airspeeds above \_\_\_\_\_, the ice rate meter will indicate higher LWC than the actual conditions.
100 KIAS
98
When the ambient air temperature is ____ and visible liquid moisture is present, icing may occur.
4° C or below
99
Liquid Water Content:
Trace
Light
Moderate
Heavy
0 to 0.25 g/m3
0. 25 to 0.5 g/m3
0. 5 to 1.0 g/m3
greater than 1.0 g/m3
100
Helicopters with the following equipment installed, operational, and turned on are permitted to fly into trace or light icing conditions. Flight into light icing is not recommended without the blade deice.
(1) Windshield Anti-ice.
(2) Pitot Heat.
(3) Engine Anti-ice.
(4) Engine Inlet Anti-ice Modulating Valve.
(5) Insulated Ambient Air Sensing Tube.
101
For flight into moderate icing conditions, all equipment in paragraph 5.30 b. and \_\_1\_\_ must be installed, operational, and turned on. Flight into \_\_2\_\_ icing is prohibited.
1. blade deice
2. heavy or severe
102
At engine power levels of 10% Q per engine and below, full anti ice capability cannot be provided, due to engine bleed limitations.
Avoid operation under conditions of extreme low power requirements such as high rate of descent, or ground bleed air HEATER operation below \_\_2\_\_, during icing conditions. The cabin heating system should be turned off
before initiating a high rate of descent.
1. 10% Q per engine and below
2. 100% NR
103
During prolonged ground operation of the backup pump with the rotor system \_\_\_\_\_, the backup pump is limited because of hydraulic fluid overheating.
static
104
Backup Hydraulic Pump Hot WX Limitations:
-54° - 32°
33° - 38°
39° - 52°
Operating/ Cooldown Time (in minutes)
unlimited
24/72
16/48
105
To prevent APU overheating, APU operation at ambient temperature of \_\_1\_\_ with engine and rotor operating, is limited to \_\_2\_\_. With engine and rotor not operating, the APU may be operated continuously up to an ambient temperature of \_\_3\_\_.
If APU OIL HOT caution appears a \_\_4\_\_ cooling period is required, before checking oil level.
1. 43° C and above
2. 30 minutes
3. 51° C
4. 30 minute
106
Windshield anti-ice check shall not be done when FAT
is over \_\_\_\_\_.
27° C
107
Intentional flight into _____ turbulence is prohibited.
severe
108
Intentional flight into _____ is prohibited.
thunderstorms
109
CAUTION:
Operating the BFT system outside this range may cause failure or erratic operation.
-26°C to 71°C
