60L chapter 5 Flashcards
(109 cards)
1
Q
Any time an operational limit is exceeded, the helicopter shall not be flown until _____________ _______________is taken.
A
corrective action
2
Q
The minimum crew required to fly the helicopter is ______________________.
A
two pilots
3
Q
RED markings indicate the limit above or below which continued operation is likely to cause _________ or _________ component life.
A
damage
shorten
4
Q
YELLOW markings indicate the range when _________ __________ should be given to the operation covered by the instrument.
A
special attention
5
Q
GREEN markings indicate the ________ or _________ range of operation.
A
safe
normal
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
7
Q
Rotor start/stop max wind velocity____kts from any direction.
A
45
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
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
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
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
12
Q
Main Rotor Overspeed _____%,_____%,_____%
A
127
137
142
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
14
Q
Main Rotor % RPM R (NR) Power On Transient \_\_\_\_\_%-\_\_\_\_\_% Continuous \_\_\_\_\_%-\_\_\_\_\_% Transient \_\_\_\_\_%-\_\_\_\_\_%
A
101 - 107
95 - 101
91 - 95
15
Q
Power-off (autorotation)
Maximum _____%
Transient _____%-_____%
Normal _____%-_____%
A
110
105 - 110
90 - 105
16
Q
Fuel Quantity
Normal _____lbs-_____lbs
Precautionary _____lbs-_____lbs
A
200 - 1500
0 - 200
17
Q
Airspeed
Maximum _____knots
A
193
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
19
Q
Engine Ng
12 sec transient _____%-_____%
30 Minute Limit _____%-_____%
Continuous _____%-_____%
A
102 - 105
99 - 102
0 - 99
20
Q
Engine Oil Temp
30 Minute Limit ____°C-____°C
Continuous ____°C-____°C
A
135 - 150
-50 - 135
21
Q
Engine Oil Pressure
5 Minute Limit _____ PSI-_____ PSI
Normal Operation _____ PSI-_____ PSI
Idle _____ PSI-_____ PSI
A
100 - 120
26 - 100
22 - 26
22
Q
Engine % TQ 10-Second Transient Dual (above 80 KIAS) \_\_\_\_\_%-\_\_\_\_\_% Dual (80 KIAS or below) \_\_\_\_\_%-\_\_\_\_\_% Single \_\_\_\_\_%-\_\_\_\_\_%
A
100 - 144
120 - 144
135 - 144
23
Q
Engine % TQ Continuous Dual (above 80 KIAS) \_\_\_\_\_%-\_\_\_\_\_% Dual (80 KIAS or below) \_\_\_\_\_%-\_\_\_\_\_% Single \_\_\_\_\_%-\_\_\_\_\_%
A
0 - 100
0 - 120
0 - 135
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
25
Main Transmission Oil Temp
Precautionary_____°C-_____°C
Continuous_____°C-_____°C
105 - 140
-50 - 105
26
Main Transmission Oil Pressure
Precautionary_____PSI-_____PSI
Continuous_____PSI-_____PSI
Idle and Transient_____PSI-_____PSI
65 - 130
30 - 65
20 - 30
27
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.
101 - 105
as good operating practice
no damage
is incurred
28
Momentary transients above_____% RPM 1 or 2 are authorized for use by maintenance test pilots during autorotational rpm checks.
107
29
A starting cycle is the interval from______ __________ and____________ of the ____________ from _______ RPM, to ____________ ____________.
start initiation
acceleration
compressor
zero
starter dropout
30
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.
15
two
3
two
30
31
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.
15
52
two
30
32
A ____second delay is required between start cycles unless required for an emergency.
60
33
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.
40
30
149
50
249
external air connector
34
CAUTION: Engine start attempts at or above ____________ft could result in a Hot Start.
18,000
35
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.
#1 ENG ANTI-ICE ON
#2 ENG ANTI-ICE ON
90
100
36
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.
14,000
24
37
T-F Engine overspeed checks may be performed in flight.
False
38
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.
JP-4
5000
crossfeed
JP-4
39
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.
three
40
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.
2
21
2
41
Maximum Weight __________lbs.
22,000
42
Maximum Weight External lift missions __________lbs.
23,500
43
External lift missions above _________lbs can only be flown with cargo hook loads above
_________lbs and up to __________lbs.
22,000
8,000
9,000
44
Maximum weight limited by cargo floor max capacity______lbs/ft2.
300
45
Max capacity for each stowage compartment is ______lbs.
125
46
The four cabin ceiling tie-down fittings have limited load capacity of _________lbs.
4,000
47
Max Cargo hook weight is __________lbs.
9,000
48
The airspeed operating limits charts define velocity never exceed (Vne) as a function of ___________, ______________, and _________ __________.
altitude, temperature
gross weight
49
Max A/S with external cargo hook loads > than 8000 lbs and corresponding gross weight > than 22000lbs shall not exceed _______KIAS.
120
50
Max A/S one engine inop _______KIAS.
130
51
Max A/S Autorotation gwt<=16825 _______ KIAS.
150
52
Max A/S Autorotation gwt>16825 _______KIAS.
130
53
Hovering in winds greater than ___ knots from the sides or rear is _________________.
45
prohibited
54
Side/rearward flight shall not exceed _______ KIAS (when combined with windspeed).
45
55
SAS inop airspeed limits
a. One SAS inop _______KIAS
b. Two SAS inop _______KIAS
c. Two SAS inop in IMC_______KIAS
170
150
140
56
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
170
150
140
57
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.
130
180
58
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.
100
180
59
Cabin doors may be fully open up to _______ KIAS with soundproofing installed aft of station 379.
100
60
Cabin doors may be fully open up to _______ KIAS with soundproofing removed aft of station 379 or with soundproofing secured properly.
145
61
The cabin doors will not be _____________ moved from fully open or closed position in flight (except during hover flight).
intentionally
62
Gunner’s window(s) may be fully open up to _____ KIAS.
170
63
Cockpit doors sliding windows will not be ___________ or _____________during flight except during hover.
opened
closed
64
Flight with cockpit doors(s) removed is __________________.
prohibited
65
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.
full down
40
0
40
120
66
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.
placard
not to exceed
120
67
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.
30
intentional
30
60
Simultaneous
idle
off
rearward
68
Manual operation of the stabilator is prohibited except as required by _____________________ ______________________ and ______________________________ or ____________________ ______________________in case the AUTO mode malfunctions.
formal training
maintenance test flight requirements
as alternate stabilator control
69
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.
rearward
downward
70
NOTE: Maneuvers entered from a low power setting may result in transient droop of ____% RPM R or greater.
5
71
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 ____________________.
airspeed, gross weight, pressure altitude, and temperature
72
Recovery from blade stall is always accomplished by ___________________________________ that is by___________________, _____________________, and/or ____________________________.
reducing the severity of the maneuver
reducing collective
reducing airspeed
reducing the angle of bank
73
Maneuvering flight which results in severe blade stall and significant increase in a 4-per-rev vibration is ________________.
prohibited
74
Above ______KIAS avoid abrupt full pedal inputs to prevent excess _________________________.
80
tail rotor system loading
75
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.
30
bank angle
airspeed
76
Rearward flight with a sling load is limited to ______ knots.
35
77
Bank angles shall be limited to _______° when a PRI SERVO PRESS caution appears.
30
78
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.
540
360
16,825
79
Do not exceed a touchdown sink rate of ________ft/min on level terrain and ______ft/min on slopes with gross weights over ___________lbs.
300
180
16,825
80
Maximum forward touchdown speed is _______knots ground speed on level terrain.
60
81
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.
10
30 to 35
15
10 to 15
82
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.
15
2
5
6
83
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.
no action
84
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.
15
low-frequency oscillation
85
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.
30
86
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.
100
100
higher
87
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
4
0 to 0.25
0. 25 to 0.5
0. 5 to 1.0
1. 0
88
T or F. NOTE: Helicopters with blades coated with Advanced Erosion Protection Coating (HONTEK) are authorized for flight into icing conditions.
True
89
Helicopters with the following equipment installed an operation are permitted to fly into trace or light icing conditions:
a. ______________________________________
b. ______________________________________
c. ______________________________________
d. ______________________________________
e. ______________________________________
Windshield Anti-ice.
Pitot Heat.
Engine Anti-ice.
Engine Inlet Anti-ice Modulating Valve.
Insulated Ambient Air Sensing Tube.
90
Flight into light icing is not recommended without the __________ __________ _____.
blade deice kit
91
For flight into moderate icing conditions the previous equipment is mandatory plus __________ __________ _____ must be installed, operational, and turned on.
blade deice kit
92
Flight into heavy or severe icing is ____________________.
prohibited
93
Helicopters equipped with ___________ ____________ __________ _______ are prohibited from flight into icing conditions.
blade erosion kit tape
94
At engine power levels of ______%TRQ and below full anti-ice capability cannot be provided.
10
95
Avoid high rates of descent _________ fpm or greater or ground operations below ________ % RPMR during icing conditions.
1900
100
96
The cabin heating system should be turned _____ before initiating a high rate of descent.
off
97
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
Unlimited - -
24 72
16 48
98
To prevent APU over heating, APU operation at ambient temperature of ______°C and above with engine and rotor operating is limited to _____min.
43
30
99
With the engine and rotor not operating the APU may be run ___________________ up to an ambient temperature of ________°C.
continuously
51
100
Windshield anti-ice check shall not be done when FAT is over _______°C.
27
101
Intentional flight into severe turbulence and thunderstorms is _________________.
prohibited
102
Intentional flight into turbulence with a sling load attached and an inoperative collective pitch control friction is _______________.
prohibited
103
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.
remain
aft cyclic
104
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.
snagging
crimping
105
WARNING: Before engine operation can be performed with the gust lock engaged ________ __________ __________ ________________ shall be removed.
all main rotor tiedowns
106
Dual engine operation with the gust lock engaged is ____________________.
prohibited
107
Single engine operation with the gust lock engaged will be performed by____________ __________ at ____________ only.
authorized pilot(s)
IDLE
108
Gust lock shall not be disengaged with _____________ _____________.
engine running
109
Maintenance operational checks (MOC) will be accomplished in accordance with
TM 1 - 1500 - ____ - ____.
328
23
