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UH-1N > AFDW MQF > Flashcards

AFDW MQF Flashcards

1
Q

Operating procedures, techniques, etc., which, will result in personal injury or loss of life if not carefully followed.
Ref: TO 1H-1(U)N-1 Pg: xv

A

Warning

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2
Q

Operating procedures, techniques, etc., which will result in damage to equipment if not carefully followed.
Ref: TO 1H-1(U)N-1 Pg: xv

A

Caution

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3
Q

An operating procedure, technique, etc., which is considered essential to emphasize.
Ref: TO 1H-1(U)N-1 Pg: xv

A

Note

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4
Q

Used only when application of a procedure is mandatory.

Ref: TO 1H-1(U)N-1 Pg: xvi

A

Shall or Will

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5
Q

Used only when application of a procedure is recommended.

Ref: TO 1H-1(U)N-1 Pg: xvi

A

Should

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6
Q

Used to indicate an acceptable or suggested means of accomplishment.
Ref: TO 1H-1(U)N-1 Pg: xvi

A

May

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7
Q

The ground handling wheels will be removed prior to engine start.
Ref: TO 1H-1(U)N-1 Pg: 1-1

A

True

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8
Q

(Engine Fuel Control Units) When operating in AUTO, it is possible to exceed maximum _____.

A

Ng, Nf, Q, and ITT

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9
Q

(Engine Fuel Control Units) When operating in MANUAL, it is possible to overspeed the Ng turbine, Nf turbine, and to exceed maximum ITT or Q.
Ref: TO 1H-1(U)N-1 Pg: 1-13

A

True

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10
Q

(Droop Compensator) When the rivet is sheared, the droop compensator is inoperative. The Nf governors will still control Nf RPM, but transient droop/overspeed and recovery time will decrease. Collective adjustments should be slow to prevent rotor decay or overspeeds.
Ref: TO 1H-1(U)N-1 Pg: 1-13

A

False

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11
Q

(Governor Switch) It is possible to have a GOV MANUAL light and still be in the automatic mode if a malfunction exists in the fuel control valve, solenoid, or wiring.
Ref: TO 1H-1(U)N-1 Pg: 1-21

A

True

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12
Q

(Pilot Override Switch) With the pilot override switch in the ON position, it is possible to engage both starters simultaneously. This should not be attempted as an extreme voltage drain will occur possibly causing destruction of the aircraft battery.
Ref: TO 1H-1(U)N-1 Pg: 1-21

A

False

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13
Q

(Rotor System) The ROTOR BRAKE caution light is actuated by the hydraulic pressure switch (located on the cylinder) at _____ psi. When the pressure drops to _____ psi, the light will extinguish.
Ref: TO 1H-1(U)N-1 Pg: 1-43

A

10, 5

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14
Q

(Rotor System) If _____ TEMP-PLATES are defective then a potential over-temp condition needs to be investigated. Do not fly and make an entry in the AFTO 781A.
Ref: TO 1H-1(U)N-1 Pg: 1-44

A

both

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15
Q

(Collective Pitch Control Lever) The collective has a built in friction which requires a force to move the stick up from the neutral (center of travel) position of _____ to _____ pounds with boost ON.
Ref: TO 1H-1(U)N-1 Pg: 1-45

A

8, 10

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16
Q

(Fuel System Caution Panel) Do not press and hold the ZERO CAL switch.
Ref: TO 1H-1(U)N-1 Pg: 1-50

A

True

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17
Q

(Auxiliary Fuel Transfer) JP-8/JP-8 +100 or JET A/JET A +100 aux fuel transfer rates are: transfer @ 1130 ± 50; shutoff @ 1290 ± 50.
Ref: TO 1H-1(U)N-1 Pg: 1-53

A

True

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18
Q

(Fuel Quantity Data) When using fuels without anti-icing additives avoid flying at altitudes where indicated OAT is below 0°C to preclude fuel system icing.
Ref: TO 1H-1(U)N-1 Pg: 1-55

A

True

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19
Q

(Standby Compass) When only one generator is ON, the standby compass will be in error as much as 30 degrees. Any substantial changes to electrical power usage (i.e., landing light, windshield wipers) will also cause some error.
Ref: TO 1H-1(U)N-1 Pg: 1-81

A

True

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20
Q

(RPM Warning System) The RPM warning light on the instrument panel illuminates whenever Nr drops below _____% ±2 or exceeds _____% ±2. Also, when either engine Ng speed drops below _____% ±2.
Ref: TO 1H-1(U)N-1 Pg: 1-83

A

92, 103, 52

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21
Q

(RPM Warning System) Whenever a low RPM condition exists with the main rotor, a low RPM audio warning (Nr drops below _____% ±2) tone is heard in the pilot’s and copilot’s helmets.
Ref: TO 1H-1(U)N-1 Pg: 1-83

A

92

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22
Q

(Wire Strike Protection System) During takeoff and at any time the helicopter skids are close to the ground (nose low at _____° or more) can result in ground contact of the WSPS lower cutter tip.
Ref: TO 1H-1(U)N-1 Pg: 1-85

A

10

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23
Q

(Heating System Operation) The bleed air heater should be in the ON position during flight conditions requiring maximum engine power available. Use bleed air during ENGINE RESTART INFLIGHT.
Ref: TO 1H-1(U)N-1 Pg: 1-88

A

False

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24
Q

(Mute HTAWS Active Caution) The Mute Active Caution selection is available when a HTWAS Caution occurs. Selecting this will mute HTAWS active Warning and Caution.
Ref: TO 1H-1(U)N-1 Pg: 1-320

A

False

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25
Q

(Normal Procedures) If action is in upper case, state checklist response. During accomplishment of any checklist, AS REQUIRED will not be used as a response; instead actual position or setting of the unit and/or item will be stated. Items of the checklist not applicable to
the model, series, or configuration being operated may be omitted.
Ref: TO 1H-1(U)N-1 Pg: 2-3

A

True

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26
Q

(Exterior Inspection) You may stand on the swashplate, cyclic pitch horns and/or collective levers during inspection. Dirt, trash, etc. on the bottom of foot wear can’t cause cuts, nicks and scratches in corrosion protective coating.
Ref: TO 1H-1(U)N-1 Pg: 2-4

A

False

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27
Q

(Exterior Inspection) Accumulation of __________ will be removed prior to flight.
Ref: TO 1H-1(U)N-1 Pg: 2-4

A

snow and ice

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28
Q

(Exterior Inspection) The rotor blade skin will be inspected for __________. All suspected damage will be inspected by maintenance personnel to determine the extent of damage.
Ref: TO 1H-1(U)N-1 Pg: 2-4.1

A

dents, creases, skin delamination, and corrosion

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29
Q

(Exterior Inspection) Visually check the idle stop lever is fully lowered to ensure throttles are set below the idle stop plunger and in the ON position.
Ref: TO 1H-1(U)N-1 Pg: 2-5

A

False

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30
Q

(Interior Inspection and Before Start) Confirm proper operation of the main rotor and tail rotor prior to engine start.
Ref: TO 1H-1(U)N-1 Pg: 2-8

A

True

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31
Q

(Interior Inspection and Before Start) When moving the collective without hydraulic assist, grip the collective __________ to avoid stress in the area between the throttles.
Ref: TO 1H-1(U)N-1 Pg: 2-8

A

at the throttles

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32
Q

(Interior Inspection and Before Start) Battery starts with static voltage below _____ volts may result in a hot start. Battery starts should not be attempted with voltage below _____ volts.
Ref: TO 1H-1(U)N-1 Pg: 2-10

A

23.5, 20

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33
Q

(Interior Inspection and Before Start) If external power voltage exceeds _____ volts turn off external power immediately, adjust the APU to provide lower voltage. Damage to the aircraft electrical system could occur at voltages above _____ volts.
Ref: TO 1H-1(U)N-1 Pg: 2-10

A

29.5, 29.5

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34
Q

(Starting Engines) To preclude ________, ensure all personnel within 30 feet of the aircraft wear ______ protection.
Ref: TO 1H-1(U)N-1 Pg: 2-11

A

possible hearing loss, hearing

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35
Q

(Starting Engines) If ITT exceeds _____° C, move the throttle to OFF.
Ref: TO 1H-1(U)N-1 Pg: 2-12

A

1090

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36
Q

(Starting Engines) ITT above _____° C shall be monitored during start and if time exceeds limits shown in Figure 5-1 (Engine Overtemperature - Starting), a hot start has occurred.
Ref: TO 1H-1(U)N-1 Pg: 2-12

A

870

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37
Q

(Starting Engines) For a hot start or impending overtemp, continue to motor the engine until ITT decreases to within normal operating limits. If any limits are exceeded, annotate in the AFTO _____.
Ref: TO 1H-1(U)N-1 Pg: 2-12.1

A

781A

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38
Q

(Starting Engines) During cold weather start it is permissible for oil pressure to reach _____ PSI maximum transient during throttle sequence for _____ seconds.
Ref: TO 1H-1(U)N-1 Pg: 2-13

A

150, 10

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39
Q

(Starting Engines) If the Generator Switch is ON while utilizing external power, there may be damage to the voltage regulator, or part of the electrical system.
Ref: TO 1H-1(U)N-1 Pg: 2-13

A

True

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40
Q

(Starting Engines) The start must be terminated if ITT fails to rise within _____ seconds after opening the throttle.
Ref: TO 1H-1(U)N-1 Pg: 2-12, 2-13

A

15

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41
Q

(Starting Engines) Ensure that the second engine has engaged. A non-engaged engine is indicated by near zero torque, low Nf, and much warmer ITT compared to the engaged engine.
Ref: TO 1H-1(U)N-1 Pg: 2-14

A

False

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42
Q

(Before Taxi) Pull pedestal cooling control knob out when temperature is at or above _____°C. If the OAT is more than _____ ° C, the vent blower should also be turned on. At least one of the two intake control valves must be open in order for cool air to reach the center pedestal.
Ref: TO 1H-1(U)N-1 Pg: 2-17, 2-18

A

19, 29

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43
Q

(Taxi) Cockpit readings that do not agree with the computed torque readings (from Appendix
A), but do not exceed plus _____% of computed values, may be considered acceptable. If cockpit torque readings differ from computed values by more than plus _____%for a five foot hover, check cockpit versus computed power for OGE hover. If the two agree within plus _____%, the aircraft may be flown provided OGE power is used for mission planning.
Ref: TO 1H-1(U)N-1 Pg: 2-19

A

4

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44
Q

(Takeoff) The airspeed, vertical velocity and altimeter are unreliable below _____ because of the rotor downwash on the pitot static system. During takeoff, do not rely on these instruments until at least _____.
Ref: TO 1H-1(U)N-1 Pg: 2-20

A

30 KIAS

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45
Q

(Takeoff) If the aircraft cannot be stabilized at _________ hover without RPM bleed off, it is
overloaded for the current conditions. Cargo and/or passengers should be off loaded until RPM remains normal. If the wind is at or above ETL, the operational value of the slide takeoff has been practically eliminated.
Ref: TO 1H-1(U)N-1 Pg: 2-21

A

a two foot

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46
Q

(After Landing) Maintain flight idle _____ minute prior to closing throttles to stabilize engine temperatures.
Ref: TO 1H-1(U)N-1 Pg: 2-24.1

A

one

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47
Q

(Before Leaving Aircraft) The flight crew will make entries in the AFTO 781A to indicate when any limits have been exceeded including the maximum limit reached and the duration of the limit.
Ref: TO 1H-1(U)N-1 Pg: 2-26

A

True

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48
Q

(Emergency Procedures) The nature and environment of the emergency dictate that a landing be made without delay to assure survival of the occupants.
Ref: TO 1H-1(U)N-1 Pg: 3-3

A

Land Immediately

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49
Q

(Emergency Procedures) The nature and environment of the emergency dictate that a landing be made at the first available area which will assure minimum injury to crew or minimum damage to the aircraft.
Ref: TO 1H-1(U)N-1 Pg: 3-3

A

Land As Soon As Possible

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50
Q

(Emergency Procedures) The nature and environment of the emergency dictate that a landing be made at the first available area or landing site which will assure no injury to the crew or damage to the aircraft and provides acceptable access for corrective action.
Ref: TO 1H-1(U)N-1 Pg: 3-3

A

Land As Soon As Practical

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51
Q

(Emergency Shutdown Procedures) Applying the rotor brake above _____% Nr will increase the tendency for the aircraft to spin on smooth surfaces.
Ref: TO 1H-1(U)N-1 Pg: 3-5

A

40

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52
Q

(Engine Fire on the Ground) If a fire pull handle was previously pulled, reset the handle prior to actuating the __________ switch.

A

FIRE EXT

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53
Q

(Engine Fire on the Ground) Activation of the engine fire extinguisher with engine cowling open will cause the extinguishing agent to be effective and is not hazardous to ground crew personnel.
Ref: TO 1H-1(U)N-1 Pg: 3-6

A

False

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54
Q

(Lightning Strikes) When lightning is encountered at night, the interior and instrument lights should be turned to _____ intensity to preclude temporary blindness.
Ref: TO 1H-1(U)N-1 Pg: 3-6

A

full

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55
Q

(Lightning Strikes) Flight in or near thunderstorms, especially in areas of observed or anticipated lightning discharges is permissible.
Ref: TO 1H-1(U)N-1 Pg: 3-6

A

False

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56
Q

(Main Rotor Malfunctions) The severity of the malfunction and the risk associated with continued flight may require the pilot to __________.
Ref: TO 1H-1(U)N-1 Pg: 3-7

A

land immediately

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57
Q

(Loss of Pitch Control to One Blade) If loss of pitch control to one blade occurs: __________.
Ref: TO 1H-1(U)N-1 Pg: 3-7

A

land immediately

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58
Q

(Complete Loss of Tail Rotor Thrust) Tail rotor failure can put the aircraft in such an attitude with respect to the rotor disk and the natural horizon, that the pilot naturally tends toward _____ cyclic to correct the attitude. These cyclic inputs combined with aircraft attitude can exceed the 11° flapping angle and induce mast bumping.
Ref: TO 1H-1(U)N-1 Pg: 3-8

A

right rear

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59
Q

(Complete Loss of Tail Rotor Thrust (Uncontrollable)) At airspeeds below _____ knots, controllability is doubtful and entering autorotation is the only means to recover the aircraft. In a hover, immediately retard throttles to flight idle, maintain level attitude and make an
autorotational landing.
Ref: TO 1H-1(U)N-1 Pg: 3-8, 3-9

A

60

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60
Q

(Complete Loss of Tail Rotor Thrust (Uncontrollable)) The inadvertent application of power at touchdown could have catastrophic results. PRIOR TO THE _____, ROTATE THROTTLES OFF. This will eliminate the possibility of inadvertent throttle input prior to touchdown.
Ref: TO 1H-1(U)N-1 Pg: 3-9

A

FLARE

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61
Q

(Complete Loss of Tail Rotor Thrust (Uncontrollable)) Failure to maintain 60 knots until touchdown may result in an ________ and unrecoverable spin to the ____.
Ref: TO 1H-1(U)N-1 Pg: 3-10

A

uncontrollable, right

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62
Q

(Right Pedal Locked Forward or Neutral) Attempted go around, loss of ETL, or excessive collective increase could result in severe right yaw and uncontrolled flight.
Ref: TO 1H-1(U)N-1 Pg: 3-10

A

True

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63
Q

(Left Pedal Locked Forward or Neutral) In many cases, the nose will yaw right (past centerline) with the increase in power to stop the descent. Throttle reduction may be necessary to control the yaw.
Ref: TO 1H-1(U)N-1 Pg: 3-11

A

True

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64
Q

(Engine Failure) During cruise, the _______________ could fail without recognition unless either a higher power setting is used or a single engine failure should occur.
Ref: TO 1H-1(U)N-1 Pg: 3-12

A

automatic fuel control

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65
Q

(Single Engine Failure) When one engine fails, the remaining engine will automatically decrease to the power required for continued flight, if sufficient power is available, or go to maximum power available.
Ref: TO 1H-1(U)N-1 Pg: 3-12

A

False

66
Q

(Single Engine Failure Inflight) Prior to beginning the approach ensure power available is sufficient for the desired approach and possible _____.
Ref: TO 1H-1(U)N-1 Pg: 3-13

A

go-around

67
Q

(Engine Failure) Monitor the affected engine instruments and upon any indication of impending engine failure, refer to ____________________.
Ref: TO 1H-1(U)N-1 Pg: 3-14

A

ENGINE SHUTDOWN INFLIGHT

68
Q

(Engine Shutdown Inflight) Ensure that the __________ caution light illuminates during shutdown. Failure of the particle separator door to close could prevent normal engine cool down and fuel/fume elimination. It may be necessary to position the particle separator switch to OFF to ensure door closure.
Ref: TO 1H-1(U)N-1 Pg: 3-15

A

PART SEP OFF

69
Q

(Engine Restart Inflight) A failed engine should not be started inflight unless it can be determined that it is reasonably safe to do so. Before restarting engine inflight allow _____ seconds of gas generator coast down with throttle in the OFF position to purge the engine of fumes and fuel.
Ref: TO 1H-1(U)N-1 Pg: 3-15

A

30

70
Q

(Engine Restart Inflight (Manual Start)) When operating on manual fuel, ITT, Ng, Nf and torque limits can be exceeded. Throttle and collective movement should be relatively slow and smooth to avoid inducing compressor stalls and/ or exceeding operating limitations.
Ref: TO 1H-1(U)N-1 Pg: 3-15

A

True

71
Q

(Engine Restart Inflight (Automatic/Manual Start)) A relight should be obtained within 15 seconds and will be evidenced by a rise in _____ and _____.
Ref: TO 1H-1(U)N-1 Pg: 3-16

A

Ng, ITT

72
Q

(Dual Engine Failure) The main rotor RPM decay rate (Figure 3-3) during an autorotation is essentially a function of transmission torque applied at the time of failure. Flight regimes that require high torque settings will produce high main rotor decay rates.
Ref: TO 1H-1(U)N-1 Pg: 3-16

A

True

73
Q

(Dual Engine Failure) Nr can only be regained by lowering the collective and reducing the drag effect of the main rotor. Should the lowering of the collective be delayed and Nr decays below _____%, the main rotor blades will stall and Nr can never be regained.
Ref: TO 1H-1(U)N-1 Pg: 3-16

A

78

74
Q

(Dual Engine Failure) Abrupt lowering of the collective and simultaneous forward movement of the cyclic during flight at high power can result in
___________________. Ref:
TO 1H-1(U)N-1 Pg: 3-16

A

a zero or negative “G” maneuver, mast bumping, and loss of aircraft control

75
Q

(Dual Engine Failure) One of the most common errors is that of landing in a _____ attitude. This often results in such rapid “nose down” pitching that the main rotor strikes the tail boom. To avoid tail boom strikes by the main rotor, aft cyclic should not be applied after ground contact is made. Regardless of the force with which the helicopter strikes the ground, damage will be much
less if it strikes level.
Ref: TO 1H-1(U)N-1 Pg: 3-18

A

“tail low”

76
Q

(Dual Engine Failure) Nr may stabilize near minimum transient limits during high gross weight, high density altitude autorotations. This may result in less rotor energy during the flare.
Ref: TO 1H-1(U)N-1 Pg: 3-18

A

False

77
Q

(Dual Engine Failure Inflight) If time and altitude permit, engine restarts may be attempted after dual engine failure. It is usually better to concentrate on making a restart than to use valuable time attempting a safe landing.
Ref: TO 1H-1(U)N-1 Pg: 3-19

A

False

78
Q

(Engine Fire Inflight) Do not pull the fire handle with the fire extinguisher switch in any position but _____.
Ref: TO 1H-1(U)N-1 Pg: 3-23

A

OFF

79
Q

(Engine Fire Inflight) When a fire handle is pulled, both engine fuel valve, particle separator door, and bleed air valves will close.
Ref: TO 1H-1(U)N-1 Pg: 3-23

A

False

80
Q

(Smoke and Fume Elimination) All unidentifiable odors shall be considered toxic. If airborne, ______________. Do not resume flight until source of odor is identified.
Ref: TO 1H-1(U)N-1 Pg: 3-24

A

land as soon as practical

81
Q

(Fuel Low Light Illumination) Extending flight beyond 5 minutes may result in engine flameout.
Ref: TO 1H-1(U)N-1 Pg: 3-24

A

True

82
Q

(Fuel Boost Pump Failure) If the fuel boost pump circuit breaker (No. 1 or No. 2 FUEL BOOST) is found popped, reset to correct the problem. Resetting a boost pump circuit breaker will not result in an electrical fire in the fuel section.
Ref: TO 1H-1(U)N-1 Pg: 3-25

A

False

83
Q

(Fuel Control System Actuation) Moving the governor switch with the throttles at flight idle may result in an overspeed and/or engine failure.
Ref: TO 1H-1(U)N-1 Pg: 3-27

A

False

84
Q

(Fuel Control System Actuation) Confirm shift of fuel control by observing changes or fluctuations in __________.
Ref: TO 1H-1(U)N-1 Pg: 3-27

A

Ng, ITT, and Fuel Flow

85
Q

(Fuel Control System Actuation) During an engine compressor stall, the possibility exists that extreme temperatures caused by a rapidly rising _____ may cause engine turbine blade damage resulting in engine failure. Additionally during compressor stalls, manually increasing fuel flow to correct for a low power condition may compound the _____ over temp condition.
Ref: TO 1H-1(U)N-1 Pg: 3-27

A

ITT

86
Q

(Main Driveshaft Failure) Rotor control is critical during MAIN DRIVE SHAFT FAILURE. _____ will immediately and rapidly decay, jeopardizing your ability to autorotate. It is imperative to react instantly and lower the collective to maintain _____. You must also be
conscious of possibly inducing negative Gs/mast bumping with rapid collective reduction. (Refer
to Main Rotor RPM Decay Rate, Figure 3-3).
Ref: TO 1H-1(U)N-1 Pg: 3-27

A

Nr

87
Q

(Main Driveshaft Failure) Due to the violent nature of this failure you can expect multiple emergencies to occur. Uncontrolled overspeeding _____ may result in explosive engine failures. Collateral damage to other components, including flight controls, can occur. No set procedure can be developed for compounding emergencies but in all cases, rotor control is critical.
Ref: TO 1H-1(U)N-1 Pg: 3-27

A

Nfs

88
Q

(CGB Low Oil Pressure/High Temperature) During the landing approach be prepared to enter autorotation at any moment. As the CGB starts to fail Nr will normally start to decrease with the engines accelerating. If failure occurs, accomplish procedures for DUAL ENGINE FAILURE.
Ref: TO 1H-1(U)N-1 Pg: 3-28

A

True

89
Q

(Transmission Low Oil Pressure/High Temperature) During this indication a pilot should Autorotate. Engine power must be maintained throughout the approach and landing to prevent the seizure of gears in the transmission.
Ref: TO 1H-1(U)N-1 Pg: 3-29

A

False

90
Q

(Electrical Power System Malfunction) _____ use a circuit breaker as a switch. Circuit breakers are to be pulled only when necessary to isolate a system during an emergency or for maintenance.
Ref: TO 1H-1(U)N-1 Pg: 3-29

A

Never

91
Q

(DC Generator Failure) If equipment powered by the __________ Bus is required, the Non-Essential Bus switch must be in the MANUAL position.
Ref: TO 1H-1(U)N-1 Pg: 3-29

A

NON ESS

92
Q

(Battery Failure) In the event of an overheated battery, open the battery compartment and attempt to disconnect or remove the battery. Battery fluid will cause chemical burns and the overheated battery will cause thermal burns and may explode.
Ref: TO 1H-1(U)N-1 Pg: 3-30

A

False

93
Q

(Hydraulic System Failure) There is a possibility that a partial or total loss of hydraulic power could be the result of an electrical short circuit to the solenoid operated shut-off valve. Pulling the _________ circuit breaker out may restore hydraulic power. If this procedure does not restore power, then the circuit breaker must be reset to restore the function of the Hydraulic Control Master Switch.
Ref: TO 1H-1(U)N-1 Pg: 3-31

A

HYD CONT

94
Q

(Emergency Descent) Extremely high rates of descent will be attained at very low forward speeds, steep bank angles and minimum collective pitch.
Ref: TO 1H-1(U)N-1 Pg: 3-31

A

True

95
Q

(Chip Detector Caution Panel) For a transmission chip detector illumination over land or water, AUTOROTATE. Engine power does not need to be maintained to prevent the seizure of gears in the transmission.
Ref: TO 1H-1(U)N-1 Pg: 3-34

A

False

96
Q

(Cargo Loading (Restraint Criteria)) The following are the units of force of gravity required to restrain cargo in the four directions. For the cargo to be safely carried, the restraint applied must be equal to or greater than the following amounts: Forward ____ G’s; Aft _____ G’s; Side _____ G’s; Vertical (Upward) _____ G’s.
Ref: TO 1H-1(U)N-1 Pg: 4-13

A

8, 8, 8, 4

97
Q

(Cargo Loading (Outsized Cargo)) Cargo which meets the weight limits but length prevents transportation in the cargo area (such as main rotor blades) may be “through loaded” provided weight and balance computations are made, lateral CG is maintained, and cargo security meets restraint criteria.
Ref: TO 1H-1(U)N-1 Pg: 4-20

A

True

98
Q

(4 Crewmember Aft Facing Seat Installation) When installed facing aft, the headrests may be installed.
Ref: TO 1H-1(U)N-1 Pg: 4-30

A

False

99
Q

(Instrument Markings) The flight crew will make entries in AFTO 781A to indicate when any limits have been exceeded including the maximum limit reached and duration of the limit.
Ref: TO 1H-1(U)N-1 Pg: 5-1

A

True

100
Q

(Instrument Markings) _____ markings indicate the limit above or below which continued operation will cause damage or shorten component life.
Ref: TO 1H-1(U)N-1 Pg: 5-1

A

Red

101
Q

(Instrument Markings) _____ markings indicate a safe or normal range of operation.
Ref: TO 1H-1(U)N-1 Pg: 5-1

A

Green

102
Q

(Instrument Markings) _____ markings indicate a range when special attention/considerations will be given to the system covered by the instrument.
Ref: TO 1H-1(U)N-1 Pg: 5-1

A

Yellow

103
Q

(Instrument Markings) Flight with indications in the yellow range is __________.
Ref: TO 1H-1(U)N-1 Pg: 5-1

A

not recommended

104
Q

(Engine Limits) Duration of single engine operation above _____% Q must be entered in AFTO 781A.
Ref: TO 1H-1(U)N-1 Pg: 5-2

A

78

105
Q

(ITT Fluctuation Limitations) Allowable ITT fluctuation is ±_____°C, provided fluctuations are not rapid or erratic.
Ref: TO 1H-1(U)N-1 Pg: 5-2

A

5

106
Q

(Transmission Limitations) Operation equal to or greater than _____% torque is limited to 5 minutes.
Ref: TO 1H-1(U)N-1 Pg: 5-2

A

88

107
Q

(Transmission Limitations) Transient fluctuations up to ±_____ PSI within the normal operating range are permissible provided the oil temperature remains normal.
Ref: TO 1H-1(U)N-1 Pg: 5-2

A

7

108
Q

(ITT Fluctuation Limitations) ITT Transient fluctuations can be expected during turbulence or while hovering in crosswinds.
Ref: TO 1H-1(U)N-1 Pg: 5-2

A

True

109
Q

(Torque Splits) The maximum allowable steady state torque split between the number one and number two engine is _____%. Transient torque splits during power changes are not abnormal as long as torque needles remarry within 20 seconds.
Ref: TO 1H-1(U)N-1 Pg: 5-2

A

4

110
Q

(CGB Oil Pressure Fluctuation Limitations) Allowable combining gear box oil pressure fluctuations are ±_____ PSI within the normal operating range of __________ PSI. This fluctuation is acceptable if it occurs at mean indications of 60 or 85 PSI such that readings of 55
to 65 or 80 to 90 PSI are experienced.
Ref: TO 1H-1(U)N-1 Pg: 5-2

A

5, 60 to 85

111
Q

(Engine Oil Pressure Fluctuation Limitations) Allowable oil pressure fluctuation is ±_____ PSI, within the normal operating range of __________ PSI.
Ref: TO 1H-1(U)N-1 Pg: 5-2

A

5, 80 to 112

112
Q

(Airspeed Limitations) The maximum permissible airspeed is _____ KIAS. The maximum airspeed with an extended load on the rescue hoist is _____ KIAS.
Ref: TO 1H-1(U)N-1 Pg: 5-2

A

130, 30

113
Q

(Engine Oil Temperature and Pressure) At _____% engine torque or greater and with 100% Nr, minimum engine oil pressure is ____ PSI.
Ref: TO 1H-1(U)N-1 Pg: 5-5

A

15, 80

114
Q

(Sideward and Rearward Airspeeds) Sideward airspeed is limited to a maximum of _____ knots, including wind factor. Sideward is the 90°quadrant on either side of the aircraft, from 45° off the nose to 45° off the tail.
Ref: TO 1H-1(U)N-1 Pg: 5-8

A

35

115
Q

(Sideward and Rearward Airspeeds) Rearward airspeed is limited to a maximum of _____ knots including wind factor. Rearward is the 90° quadrant 45° on either side of the tail.
Ref: TO 1H-1(U)N-1 Pg: 5-8

A

30

116
Q

(Cargo Door Airspeed Limits) The maximum airspeed with the cargo doors partially open (unsecured) or to open and close doors inflight is _____ KIAS.
Ref: TO 1H-1(U)N-1 Pg: 5-8

A

80

117
Q

(Cargo Door Airspeed Limits) Maximum airspeed with cargo doors fully opened and secured is _____ KIAS.
Ref: TO 1H-1(U)N-1 Pg: 5-8

A

120

118
Q

(Autorotations) Under all circumstances, autorotational landings should be attempted into the wind. The maximum steady state autorotation airspeed is _____ KIAS.
Ref: TO 1H-1(U)N-1 Pg: 5-8

A

110

119
Q

(Center of Gravity Limitations) The lateral center of gravity limits are _____ inches left or right of the longitudinal axis.
Ref: TO 1H-1(U)N-1 Pg: 5-8

A

6

120
Q

(Gross Weight Limits) The maximum takeoff gross weight of the helicopter is _____ pounds. The maximum ramp gross weight of the helicopter is _____ pounds. Aircraft are restricted from any ground handling, taxi, or takeoff operations above _____ pounds.
Ref: TO 1H-1(U)N-1 Pg: 5-8

A

10500, 11000, 10500

121
Q

(Gross Weight Limits) National Emergency/Nuclear Weapons Security Contingency operations may require flight operations in excess of 10,500 pounds. In this event, gross weights up to 11,000 pounds are authorized, subject to the following warning(s):
Ref: TO 1H-1(U)N-1 Pg: 5-8

A

Single Engine Capability may be marginal or non-existent at higher density altitudes; Safe autorotation capability may not be available, especially at higher density altitudes; Aircraft performance and handling qualities may be significantly degraded.

122
Q

(Gross Weight Limits) Safe autorotation capability will be available, especially at higher density altitudes.
Ref: TO 1H-1(U)N-1 Pg: 5-8

A

False

123
Q

(Flight Restrictions) All operations above 10,500 pounds are increased risk missions and must be kept to an absolute minimum. No flight above 10,500 pounds should ever be construed as a routine or normal operation. The following restriction(s) apply to flights above 10,500 pounds:
Ref: TO 1H-1(U)N-1 Pg: 5-8

A

CG limits are 134-139; Rotor speed should be maintained at 100 percent; Takeoff, landing and In-Ground-Effect (IGE) maneuvering is limited to current flight
manual parameters

124
Q

(Sideslip Limitation) Excessive sideslip angles can induce mast bumping.
Ref: TO 1H-1(U)N-1 Pg: 5-10

A

True

125
Q

(Wind Limitations) Starting and stopping rotors with surface winds above _____ knots is prohibited.
Ref: TO 1H-1(U)N-1 Pg: 5-11

A

45

126
Q

(Extreme Temperature Operation) Operation in ambient temperatures above _____° C and below _____° C is prohibited.
Ref: TO 1H-1(U)N-1 Pg: 5-11

A

52, -54

127
Q

(Maximum Altitude Operation) The maximum operational altitude is 15,000 feet pressure and/or density altitudes. For gross weights above 10,000 pounds, the maximum operational altitude is _____ feet pressure and/ or density altitude.
Ref: TO 1H-1(U)N-1 Pg: 5-11

A

10000

128
Q

(Flight Characteristics) Abrupt flight control movements, coupled with the high bank angles and nose tuck associated with loss of tail rotor effectiveness, may result in mast bumping and main rotor separation.
Ref: TO 1H-1(U)N-1 Pg: 6-3

A

True

129
Q

(Vortex Ring State) Increasing collective has no effect on recovery and will aggravate vortex ring state. During approaches at less than _____ knots, do not exceed _____ feet per minute descent rate.
Ref: TO 1H-1(U)N-1 Pg: 6-6, 6-7

A

40, 800

130
Q

(Settling With Power) Avoid rates of descent in excess of _____ feet per minute with airspeed below _____ knots.
Ref: TO 1H-1(U)N-1 Pg: 6-7

A

800, 40

131
Q

(Settling With Power) When landing level, the aircraft skids are designed to absorb a majority of the impact. Landing level will increase aircrew survivability and decrease overall damage to the aircraft.
Ref: TO 1H-1(U)N-1 Pg: 6-7

A

True

132
Q

(Instrument Flight) __________ required for planned IMC operations.
Ref: TO 1H-1(U)N-1 Pg: 7-1

A

Two pilots are

133
Q

(Instrument Flight Procedures) Do not attempt instrument flying without two operative attitude indicators. In the event of AC power failure, the inverter switch must be placed to the STBY position to regain operation of the attitude indicator. In the event of a generator failure with Standby inverter on, the Non-Essential Bus Switch must be positioned to MANUAL to
retain operation of the attitude indicator.
Ref: TO 1H-1(U)N-1 Pg: 7-1

A

True

134
Q

(Instrument Climb) Climbs with vertical velocities over _____ fpm are not recommended.
Ref: TO 1H-1(U)N-1 Pg: 7-2

A

1500

135
Q

(Instrument Descent) Rates of descent over _____ fpm are not recommended.
Ref: TO 1H-1(U)N-1 Pg: 7-2

A

1000

136
Q

(Rain) If the windshield wipers do not start in LOW or MED position, turn the control switch to _____. After the wiper starts, return the control switch to the desired position.
Ref: TO 1H-1(U)N-1 Pg: 7-2

A

HIGH

137
Q

(Flight in Icing Conditions) Intentional flight through known icing conditions with OAT colder than _____° C is prohibited.
Ref: TO 1H-1(U)N-1 Pg: 7-2

A

-5

138
Q

(Flight in Icing Conditions) The particle separator should be in AUTO when visible moisture is evident at temperatures below _____° C.
Ref: TO 1H-1(U)N-1 Pg: 7-3

A

5

139
Q

(Flight in Icing Conditions) Before entering possible icing conditions, (visible moisture with temperature below _____° C), the pilot should actuate the pitot heat.
Ref: TO 1H-1(U)N-1 Pg: 7-3

A

10

140
Q

(Turbulence and Thunderstorm) Aircraft are restricted from flight in areas where turbulence is known to exceed _____.
Ref: TO 1H-1(U)N-1 Pg: 7-3

A

moderate

141
Q

(Night Operations) When operating in the clouds at night, turn navigation lights to steady and anticollision lights off, to reduce distracting reflections from the clouds. These reflections can result in spatial disorientation. Turning the navigation lights to dim will aid in reducing the reflections in the cockpit.
Ref: TO 1H-1(U)N-1 Pg: 7-10

A

True

142
Q

(Wind Direction and Velocity) Depending on wind velocity, the apparent airspeed/ground speed relationship changes when turning downwind. After the turn, less airspeed is required to maintain ground speed. Reducing airspeed may result in loss of ETL which increases the power required to maintain altitude. When operating close to the surface, especially during downwind maneuvers, _____ and _____ required must be monitored closely.
Ref: TO 1H-1(U)N-1 Pg: 7-7

A

airspeed, power

143
Q

(Cold Weather Operations) When the outside air temperature is below minus _____° C, do not advance throttles beyond _____% Ng until engine, combining gearbox, and transmission oil pressures are stabilized within desired operating range.
Ref: TO 1H-1(U)N-1 Pg: 7-11

A

18, 71

144
Q

(Cold Weather Operations) Hover taxiing over loose or powdery snow is not recommended in a congested area.
Ref: TO 1H-1(U)N-1 Pg: 7-12

A

True

145
Q

(Hot Weather Operations) During hot weather, oil temperatures will probably be on the low side of the operating range.
Ref: TO 1H-1(U)N-1 Pg: 7-13

A

False

146
Q

(Performance Data) All charts are presented for _____% Nf and Nr. It is strongly recommended that _____% RPM be used at 40 knots and below.
Ref: TO 1H-1(U)N-1 Pg: A-1

A

100

147
Q

(Density Altitude) Humidity affects density altitude. The higher the humidity, the higher the density altitude. This in fact could have an effect on power required. Throughout this manual add _____ feet density altitude for each _____ percent increase in humidity above 40 percent.
Ref: TO 1H-1(U)N-1 Pg: A-8

A

100, 10

148
Q

(Fuel Flow) Increase fuel flow _____% for heater on.

Ref: TO 1H-1(U)N-1 Pg: A-11

A

2

149
Q

(Tail Rotor Effectiveness) To ensure adequate tail rotor and cyclic control margins, avoid winds in excess of _____ knots from approximately the __________ o’clock position. Avoiding winds from these critical azimuths can help preclude loss of tail rotor effectiveness.
Ref: TO 1H-1(U)N-1 Pg: A-43

A

20, 2 to 4

150
Q

(Autorotation) Successful cyclic flares and landing maneuvers during autorotation require high rotor speeds.
Ref: TO 1H-1(U)N-1 Pg: A-76

A

True

151
Q

For Block 1 aircraft, Start Switch (ENG 1 or ENG 2) held in START position will disable __________ until Start Switch is returned to OFF position.
Ref: TO 1H-1(U)N-1 Pg: 1-22

A

Anti-collision lights (Upper and Lower)

152
Q

(T/F) The ITT inverter is not applicable to Block 1 Aircraft.
Ref: TO 1H-1(U)N-1 Pg: 1-25

A

True

153
Q

Rotor Brake. An internal pressure relief valve in the master cylinder limits system pressure to a maximum of ____ psi.
Ref: TO 1H-1(U)N-1 Pg: 1-43

A

260

154
Q

The FUEL LOW light is set for a _______ flight attitude.

Ref: TO 1H-1(U)N-1 Pg: 1-66

A

Level

155
Q

(T/F) In the event of a dual CDNU screen failure, communications may still be possible using the No.3 radio aft control head.
Ref: TO 1H-1(U)N-1 Pg: 1-217

A

True

156
Q

What is the minimum DC voltage with the starter engaged on a Block 1 aircraft?
Ref: TO 1H-1(U)N-1 Pg: 5-7

A

15 volts

157
Q

(T/F) The Instructor Control Panel and ITT inverter are not applicable to Block 1 aircraft.
Ref: TO 1H-1(U)N-1 Pg: 1-15, 1-17

A

True

158
Q

In the hydraulic system, an electrically operated clogged filter indicator located in the nose compartment will change from _________ if any of the four filters is clogged.
Ref: TO 1H-1(U)N-1 Pg: 1-46

A

Green light to red light – Block 1 Aircraft

159
Q

(T/F) Auxiliary Fuel Transfer System Operation. In the event the float switch(es) fail to cycle off, fuel venting overboard is imminent.
Ref: TO 1H-1(U)N-1 Pg: 1-62

A

True

160
Q

Where is the Standby Compass located on Block 1 aircraft?

Ref: TO 1H-1(U)N-1 Pg 1-81

A

Above the air vents on each side of the instrument panel

UH-1N (6 decks)

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