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60's > 60L chapter 5 > Flashcards

60L chapter 5 Flashcards

1
Q

Any time an operational limit is exceeded, the helicopter shall not be flown until _____________ _______________is taken.

A

corrective action

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2
Q

The minimum crew required to fly the helicopter is ______________________.

A

two pilots

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3
Q

RED markings indicate the limit above or below which continued operation is likely to cause _________ or _________ component life.

A

damage

shorten

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4
Q

YELLOW markings indicate the range when _________ __________ should be given to the operation covered by the instrument.

A

special attention

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5
Q

GREEN markings indicate the ________ or _________ range of operation.

A

safe

normal

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6
Q

It is not abnormal to observe a % RPM 1 and 2 speed ______ during auto-rotational descent when the engines are fully decoupled from the main rotor. A speed increase of one engine from ____% reference to ____% maximum can be expected. During power recovery, it is normal for the engine operating above 100% RPM to _____ the other engine.

A

split

100

103

lead

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7
Q

Rotor start/stop max wind velocity____kts from any direction.

A

45

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8
Q

Power off (autorotation) rotor speeds up to ______% RPM are authorized for use by maintenance test flight pilots during autorotational RPM checks.

A

120

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9
Q

Transmission oil pressure should remain _______during steady state forward flight or in level hover. Momentary fluctuations in oil pressure may occur during transient maneuvers (i.e. hovering in gusty wind conditions), or when flying with pitch attitudes above ____°. These types of oil pressure fluctuations are __________, even when oil pressure drops into the yellow range (below ____ psi). Oil pressure should remain steady and should be in the ____ to ____ psi range for the UH-60L, to ensure that when fluctuations occur they remain in the acceptable range as defined above. If oil pressure is not steady during steady state forward flight or in a level hover, or if oil pressure is steady but under ____ psi, make an entry on Form 2408-13-1. Sudden pressure drop (more than ____ PSI) without fluctuation requires an entry on Form 2408-13-1.

A

steady

+6

acceptable

30

45

60

45

10

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10
Q

A demand for maximum power from engines with different engine torque factors (ETF) will cause a ________ ________ when the low ETF engine reaches TGT limiting. This is normal. Under these circumstances, the high power engine may or may not (circle one) exceed the dual engine limit.

A

torque split

may

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11
Q

With transmission oil temperature operation in the precautionary range, an entry should be made on DA Form 2408-13-1 except when __________________________________________________________.

A

hovering in adverse conditions

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12
Q

Main Rotor Overspeed _____%,_____%,_____%

A

127

137

142

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13
Q 
Engine % RPM 1-2 (NP)
​12 sec transient \_\_\_\_\_%-\_\_\_\_\_%
​Transient           \_\_\_\_\_%-\_\_\_\_\_%
​Continuous       \_\_\_\_\_%-\_\_\_\_\_%
​Transient           \_\_\_\_\_%-\_\_\_\_\_%
​Avoid operations in \_\_\_%-\_\_\_% and \_\_\_%-\_\_\_% except during start and shutdown.
A

105 -107

101 - 105

95 - 101

91 -95

20 - 40

60 - 90

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14
Q 
Main Rotor % RPM R (NR)
​Power On
​Transient           \_\_\_\_\_%-\_\_\_\_\_%
​Continuous       \_\_\_\_\_%-\_\_\_\_\_%
​Transient         \_\_\_\_\_%-\_\_\_\_\_%
A

101 - 107

95 - 101

91 - 95

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15
Q

Power-off (autorotation)
​Maximum _____%
​Transient _____%-_____%
​Normal _____%-_____%

A

110

105 - 110

90 - 105

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16
Q

Fuel Quantity
​Normal _____lbs-_____lbs​
​Precautionary _____lbs-_____lbs

A

200 - 1500

0 - 200

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17
Q

Airspeed

​Maximum _____knots

A

193

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18
Q 
Stabilator Limit
​0 degrees \_\_\_\_ KIAS
​10 degrees ​\_\_\_\_ KIAS
​20 degrees ​\_\_\_\_ KIAS
​30 degrees \_\_\_\_ KIAS
​40 degrees ​\_\_\_\_ KIAS
A

150

100

80

60

45

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19
Q

Engine Ng
​12 sec transient​ _____%-_____%
​30 Minute Limit _____%-_____%
​Continuous ​ _____%-_____%

A

102 - 105

99 - 102

0 - 99

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20
Q

Engine Oil Temp
​30 Minute Limit ____°C-____°C
​Continuous​ ____°C-____°C

A

135 - 150

-50 - 135

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21
Q

Engine Oil Pressure
​5 Minute Limit ​_____ PSI-_____ PSI​​
​Normal Operation ​_____ PSI-_____ PSI
​Idle _____ PSI-_____ PSI

A

100 - 120

26 - 100

22 - 26

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22
Q 
Engine % TQ​​​​
​10-Second Transient​​​​
​​Dual (above 80 KIAS)     \_\_\_\_\_%-\_\_\_\_\_%​
Dual (80 KIAS or below) \_\_\_\_\_%-\_\_\_\_\_% ​
​Single​​           \_\_\_\_\_%-\_\_\_\_\_%
A

100 - 144

120 - 144

135 - 144

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23
Q 
Engine % TQ​​​​
Continuous​​​​​
Dual (above 80 KIAS)     \_\_\_\_\_%-\_\_\_\_\_%
Dual (80 KIAS or below) \_\_\_\_\_%-\_\_\_\_\_%
Single​​            \_\_\_\_\_%-\_\_\_\_\_%
A

0 - 100

0 - 120

0 - 135

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24
Q

Turbine Gas Temp
12-Second Transient ​​_____°C-_____°C
2.5 Mins Transient (cont pwr)​_____°C-_____°C TGT LIMITING Approx ____°C
Start Abort Limit ​​_____°C
10-Minute Limit​​​_____°C-_____°C TGT LIMITING Approx ____°C
30-Minute Limit​​​_____°C-_____°C
Normal​​​​_____°C-_____°C

A

903 - 949

878 - 903 (891)

851

851 - 878 (866)

810 - 851

0 - 810

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25
Q

Main Transmission Oil Temp
Precautionary​_____°C-_____°C
Continuous​_____°C-_____°C

A

105 - 140

-50 - 105

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26
Q

Main Transmission Oil Pressure
Precautionary​​_____PSI-_____PSI
Continuous​​_____PSI-_____PSI
Idle and Transient​_____PSI-_____PSI

A

65 - 130

30 - 65

20 - 30

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27
Q

Transient % RPM 1 or 2 operation in yellow range (_____% to _____%) is not recommended __ ________ _______________ ______________. However, ___ ________________ to either engine or drive train __ _______________ by operation within this range.

A

101 - 105

as good operating practice

no damage

is incurred

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28
Q

Momentary transients above_____% RPM 1 or 2 are authorized for use by maintenance test pilots during autorotational rpm checks.

A

107

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29
Q

A starting cycle is the interval from______ __________ and____________ of the ____________ from _______ RPM, to ____________ ____________.

A

start initiation

acceleration

compressor

zero

starter dropout

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30
Q

At Ambient Temp of ______°C and below______ consecutive start cycles may be made followed by a ______min rest period, followed by ______additional consecutive start cycles. A _____min rest period is then required before any additional starts.

A

15

two

3

two

30

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31
Q

At Ambient Temp of ____°C up to ____°C, _____ consecutive start cycles may be made, a
____minute rest period is then required before any additional start cycles.

A

15

52

two

30

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32
Q

A ____second delay is required between start cycles unless required for an emergency.

A

60

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33
Q

The minimum ground air source (pneumatic) required to start the helicopter engines is
____psig and _____ppm at _____°C. The maximum ground air source to be applied to the helicopter is ____psig at _____°C measured at the __________ ____ _______________on the fuselage.

A

40

30

149

50

249

external air connector

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34
Q

CAUTION: Engine start attempts at or above ____________ft could result in a Hot Start.

A

18,000

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35
Q

Cross bleed starts shall not be attempted unless_______________ or ________________ advisory does not appear and operating engine must be a _____% Ng or above and rotor speed at ______% RPMR.

A

1 ENG ANTI-ICE ON

90

100

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36
Q

When attempting single-engine starts at pressure altitudes above ________ feet, press the start switch with the ENG POWER CONT lever OFF, until the maximum motoring speed (about ____%) is reached, before going to IDLE.

A

14,000

24

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37
Q

T-F Engine overspeed checks may be performed in flight.

A

False

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38
Q

Fuel boost pumps shall be off, except as required by Emergency Procedures and the following limitations: Boost pumps shall be on when operating with ________ or equivalent (as specified in
Operators’ Manual) at __________ft PA and above; when operating in ____________________ with ________ at any altitude.

A

JP-4

5000

crossfeed

JP-4

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39
Q

CAUTION: Due to fuel volatility, when converting from JP-4 to JP-5/JP-8, ________ aircraft refueling operations must be completed before performing operations with boost pumps off.

A

three

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40
Q

When a helicopter operating with JP-4 is restarted within ____ hours of engine shutdown and the air temperature is above ____°C, a minimum _____ minutes of dual engine ground operation at 100% RPMR is required prior to takeoff to purge possible hot fuel from engine nacelle area.

A

2

21

2

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41
Q

Maximum Weight __________lbs.

A

22,000

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42
Q

Maximum Weight External lift missions __________lbs.

A

23,500

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43
Q

External lift missions above _________lbs can only be flown with cargo hook loads above
_________lbs and up to __________lbs.

A

22,000

8,000

9,000

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44
Q

Maximum weight limited by cargo floor max capacity______lbs/ft2.

A

300

45
Q

Max capacity for each stowage compartment is ______lbs.

A

125

46
Q

The four cabin ceiling tie-down fittings have limited load capacity of _________lbs.

A

4,000

47
Q

Max Cargo hook weight is __________lbs.

A

9,000

48
Q

The airspeed operating limits charts define velocity never exceed (Vne) as a function of ___________, ______________, and _________ __________.

A

altitude, temperature

gross weight

49
Q

Max A/S with external cargo hook loads > than 8000 lbs and corresponding gross weight > than 22000lbs shall not exceed _______KIAS.

A

120

50
Q

Max A/S one engine inop _______KIAS.

A

130

51
Q

Max A/S Autorotation gwt<=16825 _______ KIAS.

A

150

52
Q

Max A/S Autorotation gwt>16825 _______KIAS.

A

130

53
Q

Hovering in winds greater than ___ knots from the sides or rear is _________________.

A

45

prohibited

54
Q

Side/rearward flight shall not exceed _______ KIAS (when combined with windspeed).

A

45

55
Q

SAS inop airspeed limits

a. One SAS inop ​_______KIAS
b. Two SAS inop ​_______KIAS
c. Two SAS inop in IMC​_______KIAS

A

170

150

140

56
Q

Hydraulic system inop airspeed limits

a. One hydraulic system inop ​​_______KIAS
b. Two hydraulic systems inop ​​_______KIAS
c. Two hydraulic systems inop in IMC ​_______KIAS

A

170

150

140

57
Q

Landing light airspeed limits

a. Landing light must be extended prior to reaching a max fwd airspeed of ______KIAS.
b. Landing light is extended A/S limit _______KIAS.

A

130

180

58
Q

Search light airspeed limits
​a. Search light must be extended prior to reaching a max fwd airspeed of ______KIAS.
a. Search light is extended A/S limit _______KIAS.

A

100

180

59
Q

Cabin doors may be fully open up to _______ KIAS with soundproofing installed aft of station 379.

A

100

60
Q

Cabin doors may be fully open up to _______ KIAS with soundproofing removed aft of station 379 or with soundproofing secured properly.

A

145

61
Q

The cabin doors will not be _____________ moved from fully open or closed position in flight (except during hover flight).

A

intentionally

62
Q

Gunner’s window(s) may be fully open up to _____ KIAS.

A

170

63
Q

Cockpit doors sliding windows will not be ___________ or _____________during flight except during hover.

A

opened

closed

64
Q

Flight with cockpit doors(s) removed is __________________.

A

prohibited

65
Q

If automatic stabilator control fails in flight and operation cannot be restored:

a. The stabilator shall be set ______ ________ at speeds ______ KIAS and below.
b. The stabilator shall be set at ____° at speeds above______ KIAS.
c. Autorotation airspeed shall be limited to _______KIAS at all gross weights.

A

full down

40

0

40

120

66
Q

If manual control is not available the _________ airspeed limits shall be observed as a ______-____-____________speed (powered flight and autorotation), except in no case shall the autorotation limit exceed _______KIAS.

A

placard

not to exceed

120

67
Q

What are the prohibited maneuvers?

a. Hovering turns greater than ____° / sec.
b. ____________________maneuvers beyond attitudes of +/-______° pitch or over_____° in roll.
c. ________________ moving of both ENG POWER CONT lever to _______or ______in flight.
d. ________________ ground taxi.

A

30

intentional

30

60

Simultaneous

idle

off

rearward

68
Q

Manual operation of the stabilator is prohibited except as required by _____________________ ______________________ and ______________________________ or ____________________ ______________________in case the AUTO mode malfunctions.

A

formal training

maintenance test flight requirements

as alternate stabilator control

69
Q

Prolonged _____________ flight or _________________ hovering are to be avoided to prevent accumulation of exhaust fumes in the helicopter and heat damage to windows on open cargo doors.

A

rearward

downward

70
Q

NOTE: Maneuvers entered from a low power setting may result in transient droop of ____% RPM R or greater.

A

5

71
Q

The blade stall chart while not a helicopter limitation, provides the level flight angle of bank at which blade stall will begin to occur as a function of ______________, ________________, ____________________, and ____________________.

A

airspeed, gross weight, pressure altitude, and temperature

72
Q

Recovery from blade stall is always accomplished by ___________________________________ that is by___________________, _____________________, and/or ____________________________.

A

reducing the severity of the maneuver

reducing collective

reducing airspeed

reducing the angle of bank

73
Q

Maneuvering flight which results in severe blade stall and significant increase in a 4-per-rev vibration is ________________.

A

prohibited

74
Q

Above ______KIAS avoid abrupt full pedal inputs to prevent excess _________________________.

A

80

tail rotor system loading

75
Q

Maneuvering limitation with a sling load is limited to a maximum of _____° angle of bank in forward flight. Sideward flight is limited by_____ _________and is decreased as _____________increases.

A

30

bank angle

airspeed

76
Q

Rearward flight with a sling load is limited to ______ knots.

A

35

77
Q

Bank angles shall be limited to _______° when a PRI SERVO PRESS caution appears.

A

30

78
Q

Do not exceed a touchdown sink rate of ________ft/min on level terrain and ______ft/min on slopes with gross weights of up to ___________lbs.

A

540

360

16,825

79
Q

Do not exceed a touchdown sink rate of ________ft/min on level terrain and ______ft/min on slopes with gross weights over ___________lbs.

A

300

180

16,825

80
Q

Maximum forward touchdown speed is _______knots ground speed on level terrain.

A

60

81
Q

NOTE: Because of the flat profile of the main transmission and forward location of both transmission oil pump, transmission oil pressure will drop during nose-up slope operations. At slope angle of _____° an indicated oil pressure of ____PSI to ____PSI is normal and at a _____° slope angle a pressure in the range of ____PSI to ____PSI is normal due to pitching of the helicopter.

A

10

30 to 35

15

10 to 15

82
Q

Slope Limitations:
a. ______° nose up right wheel up or left wheel upslope.
​b. The slope limitations shall be further reduced by _____° for every _____knots of wind.
​c. _______° nose downslope.

A

15

2

5

6

83
Q

NOTE: The low fuel pressure indicator light(s) may intermittently light when the helicopter returns to a neutral or positive attitude after extended operation at nose down attitudes with fuel boost pumps off. This may also occur during a climb to high altitude followed by a pitch-up maneuver. If the light extinguishes immediately, _____ _______________ is required by the pilot.

A

no action

84
Q

Landing in downslope conditions with tail winds greater than _____knots shall not be conducted. A ______________________________________ may occur when landing nose-down on a slope with the cyclic near the aft stop.

A

15

low-frequency oscillation

85
Q

The main gearbox may be operated up to ______ minutes at a time with pressure fluctuations when the helicopter is known to be at a nose up attitude.

A

30

86
Q

NOTE: The ice detecting system is calibrated for ________ KIAS. When flying at airspeeds above ______ KIAS, the ice rate meter will indicate __________ LWC than the actual conditions.

A

100

100

higher

87
Q

When the ambient air temperature is ____°C or below and visible liquid moisture is present, icing may occur. Icing severity is defined by the liquid water content (LWC) of the outside air and measured in grams per cubic meter (g/m3).

a. Trace :​LWC _____ to _____ g/m3
​b. Light :​LWC _____ to _____ g/m3
​c. Moderate :​LWC _____ to _____ g/m3
​d. Heavy :​LWC greater than _____ g/m3

A

4

0 to 0.25

  1. 25 to 0.5
  2. 5 to 1.0
  3. 0
88
Q

T or F. NOTE: Helicopters with blades coated with Advanced Erosion Protection Coating (HONTEK) are authorized for flight into icing conditions.

A

True

89
Q

Helicopters with the following equipment installed an operation are permitted to fly into trace or light icing conditions:

a. ______________________________________
b. ______________________________________
c. ______________________________________
d. ______________________________________
e. ______________________________________

A

Windshield Anti-ice.

Pitot Heat.

Engine Anti-ice.

Engine Inlet Anti-ice Modulating Valve.

Insulated Ambient Air Sensing Tube.

90
Q

Flight into light icing is not recommended without the __________ __________ _____.

A

blade deice kit

91
Q

For flight into moderate icing conditions the previous equipment is mandatory plus __________ __________ _____ must be installed, operational, and turned on.

A

blade deice kit

92
Q

Flight into heavy or severe icing is ____________________.

A

prohibited

93
Q

Helicopters equipped with ___________ ____________ __________ _______ are prohibited from flight into icing conditions.

A

blade erosion kit tape

94
Q

At engine power levels of ______%TRQ and below full anti-ice capability cannot be provided.

A

10

95
Q

Avoid high rates of descent _________ fpm or greater or ground operations below ________ % RPMR during icing conditions.

A

1900

100

96
Q

The cabin heating system should be turned _____ before initiating a high rate of descent.

A

off

97
Q

During prolonged ground operation with the backup pump with the rotor system static–limited to the following temperature/time/cool-down limits because of hydraulic fluid overheating:

FAT​​ Operating time ​​Cool down time (pump off)
-54° to 32°C​ ____________min​ ___________min
33° to 38°C ​____________min ​___________min
39° to 52°C ​____________min ​___________min

A

Unlimited - -

24 72

16 48

98
Q

To prevent APU over heating, APU operation at ambient temperature of ______°C and above with engine and rotor operating is limited to _____min.

A

43

30

99
Q

With the engine and rotor not operating the APU may be run ___________________ up to an ambient temperature of ________°C.

A

continuously

51

100
Q

Windshield anti-ice check shall not be done when FAT is over _______°C.

A

27

101
Q

Intentional flight into severe turbulence and thunderstorms is _________________.

A

prohibited

102
Q

Intentional flight into turbulence with a sling load attached and an inoperative collective pitch control friction is _______________.

A

prohibited

103
Q

If performing an overwater mission with the Air Warrior Overwater Gear Carrier, remove the seat back cushion to allow space for the raft. The pan cushion must ___________ in the seat. Failure to remove the seat back cushion may result in _____ _________ restriction.

A

remain

aft cyclic

104
Q

While wearing the chemical protective mask, the mask hose should be secured to the vest to eliminate potential _______________ of the flight controls without restricting head movement and without _______________ the hose.

A

snagging

crimping

105
Q

WARNING: Before engine operation can be performed with the gust lock engaged ________ __________ __________ ________________ shall be removed.

A

all main rotor tiedowns

106
Q

Dual engine operation with the gust lock engaged is ____________________.

A

prohibited

107
Q

Single engine operation with the gust lock engaged will be performed by____________ __________ at ____________ only.

A

authorized pilot(s)

IDLE

108
Q

Gust lock shall not be disengaged with _____________ _____________.

A

engine running

109
Q

Maintenance operational checks (MOC) will be accomplished in accordance with
TM 1 - 1500 - ____ - ____.

A

328

23

60's (12 decks)

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