Chapter 5 Flashcards by Amy Norman

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__.

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

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Minimum Crew Requirements

The minimum crew required to fly the helicopter is two pilots.

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Additional crewmembers, as required, will be added __1__, in accordance with pertinent __2__.

at the discretion of the commander
Department of the Army regulations

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EICAS: Red and yellow striped tapes and red readouts indicate _____.

the limit above or below which continued operation is likely to cause damage or shorten component life

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EICAS: Yellow tapes and readouts indicate _____.

the range when special attention should be given to the parameter the instrument represents

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EICAS: Green tapes and readouts indicate _____.

the normal operating range of the parameter the instrument represents

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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.

engines are fully decoupled from the main rotor
107%
engine operating above 100% NP

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Maximum wind velocity for rotor start or stop is _____ from any direction.

45 knots

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Power off (autorotation) rotor speeds up to __1__ are authorized for use by __2__ during __3__.

120% NR
maintenance test flight pilots
autorotational RPM checks

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Operating an engine against the _____ is prohibited.

gust lock

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Rotor brake shall not be applied with engine(s) operating and rotor turning except during an _____.

emergency stop

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Maximum rotor speed for emergency rotor brake applications is _____.

76% NR

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Routine stops will be with __1__, __2__, and with __3__ applied to stop the rotor in not less than __4__.

engine(s) off
NR below 40%
150-180 psi
12 seconds

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Minimum rotor brake pressure for engine start is __1__. Maximum rotor brake pressure for engine start is __2__.

450 psi
690 psi

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Use of the rotor brake with engine(s) operating is restricted to single and dual engine starts and operations at _____.

IDLE only

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Single and dual engine starts and operation at __1__ with rotor brake on are __2__.

IDLE
not time limited

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Transmission oil pressure should remain steady during __1__ or __2__.

steady state forward flight
in a level hover

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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).

transient maneuvers (i.e. hovering in gusty wind conditions
+6%

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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.

45 psi
60 psi

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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.

45 psi

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Sudden transmission pressure drop (more than _____) without fluctuation requires and entry on the appropriate maintenance form.

10 psi

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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__.

engine torque factors (ETF)
low ETF engine
TGT limiting
high power engine
dual engine limit

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With transmission oil temperature operation in the __1__, an entry should be made on the appropriate maintenance form except when __2__.

precautionary range
hovering in adverse conditions (desert and hot weather)

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Power Turbine Speed (NP) Limitaions

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%)

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Rotor Speed (NR) Power-On Limitations

1. Transient (91-95%) 2. Continuous (95-101%) 3.

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.

Gas Generator Speed (NG) Limitations

1. Continuous (0-105%) 2. 12-Second Transient (105-106%)

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%)

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)

Turbine Gas Temperature (TGT) Limitations

Engine Oil Temperatue Limitations

1. Continuous (-20-135°C) 2. 30 Minute Limit (135-150°C)

Engline Oil Pressure Limitations

1. IDLE (22-26 psi) 2. Normal (26-100 psi) 3. 5 Minute Limit (100-120 psi)

Transmission Oil Temperature Limitations

1. Continuous (-20-105°C) 2. Precautionary (105-140°C)

Transmission Oil Pressure Limitations

1. IDLE & Transient (20-30 psi) 2. Continuous (30-65 psi) 3. Precautionary (65-130 psi)

Fuel Limitations

1. Normal (\>200 lb - each tank) 2. Precautionary (0-200 - each tank)

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

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

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

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

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

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

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

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

CAUTION: Engine start attempts at or above a pressure altitude of _____ could result in a hot start.

18,000 feet

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

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%)

Engine overspeed check in flight is \_\_1\_\_. Engine overspeed checks, on the ground, are authorized by \_\_2\_\_.

1. prohibited 2. designated maintenance personnel only

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

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

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

Maximum Weight

22,000 lb 23,500 lb (external lift)

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

Maximum weight is further limited by cargo floor maxium capacity of _____ per square foot.

300 lb

Maximum capacity for each storage compartment is \_\_\_\_\_.

125 lb

The \_\_1\_\_ cabin ceiling tiedown fittings have a limited load capacity of \_\_2\_\_.

1. four 2. 4,000 lb

The \_\_1\_\_ tiedown fittings installed on the cargo floor can restrain a \_\_2\_\_ load in any direction.

1. 17 2. 5,000 lb

The \_\_1\_\_ net restraint rings in the cargo compartment are rated at \_\_2\_\_ capacity in any direction.

1. eight 2. 3,500 lb

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

The maxium weight that may be suspended from the rescue hoist is \_\_\_\_\_.

600 lb

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

Maximum airspeed: external cargo hook loads up to 8,000 lb

140 KIAS

Maximum airspeed: external cargo hook loads greater than 8,000 lb shall not exceed

120 KIAS

Maximum airspeed: one engine inoperative

130 KIAS

Maximum airspeed: autorotation at a gross weight of 16,825 lb or less

150 KIAS

Maximum airspeed: autorotation at a gross wight of 16,825 or more

130 KIAS

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

Airspeed limits: one SAS inoperative two SAS inoperative two SAS inoperative in IMC

170 KIAS 150 KIAS 140 KIAS

Airspeed limits: one hydraulic system inoperative two hydraulic systems inoperative two hydraulic systems inoperative in IMC

170 KIAS 150 KIAS 140 KIAS

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

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

Cabin door(s) may be fully open up to \_\_\_\_\_.

145 KIAS

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

Flight with cockpit door(s) removed is \_\_\_\_\_.

prohibited

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

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

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°

Simultaneous moving of both \_\_1\_\_ to \_\_2\_\_ or \_\_3\_\_ in flight is prohibited.

1. ENG POWER CONT levers 2. IDLE 3. OFF

\_\_\_\_\_ ground taxi is prohibited.

Rearward

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.

Restricted Maneuvers

1. Manual operation of the stabilator 2. Downwind hovering

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

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

NOTE: Maneuvers entered from a \_\_1\_\_ may result in transient droop of \_\_2\_\_ or greater.

1. low power setting 2. 5% NR

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

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

Fully developed stall wil be accompanied by \_\_1\_\_, increasing \_\_2\_\_, and loss of \_\_3\_\_.

1. heavy vibrations 2. torque 3. altitude

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

Above \_\_1\_\_ avoid \_\_2\_\_ to prevent excess tail rotor system loading.

1. 80 KIAS 2. abrupt, full pedal inputs

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

Bank angles shall be limited to _____ when a PRI SERVO FAIL caution appears.

30°

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

Maximum forward touchdown speed is limited to _____ ground speed on level terrain.

60 knots

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

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

Slope limitations: 6° downslope Landing in downslope conditions with tail wind greater than _____ shall not be conducted.

15 knots

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

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

When the ambient air temperature is ____ and visible liquid moisture is present, icing may occur.

4° C or below

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

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.

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

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

During prolonged ground operation of the backup pump with the rotor system \_\_\_\_\_, the backup pump is limited because of hydraulic fluid overheating.

static

Backup Hydraulic Pump Hot WX Limitations: -54° - 32° 33° - 38° 39° - 52°

Operating/ Cooldown Time (in minutes) unlimited 24/72 16/48

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

Windshield anti-ice check shall not be done when FAT is over \_\_\_\_\_.

27° C

Intentional flight into _____ turbulence is prohibited.

severe

Intentional flight into _____ is prohibited.

thunderstorms

CAUTION: Operating the BFT system outside this range may cause failure or erratic operation.

-26°C to 71°C

Chapter 5 Flashcards

(109 cards)