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| Should conflict exist between the NATOPS flight manual and other publications, the NATOPS flight manual shall govern. | False
Will govern Pg 1
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| Anyone can recommend a change to NATOPS in accordance with OPNAVIST 3710.7 | True
Pg. 56
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| A WARNING as defined in NATOPS is an operating procedure or technique that may result in damage to equipment if not carefully observed or followed. | False
Pg. 57
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| Each General Electric T700-GE-401C engine is rated(uninstalled) at______ shp. | 1,800
Pg 1-2
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| The primary mission of the UH-1Y is that of a____ _____ helicopter, capable of _____-_____ flight; ____ _____ _____ support; and _____ _____ support. | Tactical utility, high-speed, multiple weapon fire, troop helicopter
Pg 1-2
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| Each MFD has ____ lighted hard bezel keys across the bottom that are functionally grouped for ease of identification and access. | Nine
Pg 2-1
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| Default displays on power up are ____page on the ______MFDs and _____page on the MFDs. | MAP, Inboard, FLT
Pg 2-3
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| The ____ _____ MFD will not provide any displaced information if only the essential bus if powered because _____ will not be powered to an ON state. For this reason, the pilot must turn the mode selector to ____ to see displayed information. | Pilots inboard, MC No. 2, RPT
Pg. 2-3
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| The bottom two rows of the keyboard contain five special purpose dedicated keys as follows: ____, ____, _____, _____, and _____. | Frequency FRQ, TCN, SQK, IDNT, MRK
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| The T700-GE-401C engines are _____ ______, ______ ______ of modular construction. | Front drive, turboshaft engines
Pg 2-10
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| Each engine is comprised of a combination ______/______ ____-_____ ______, an _____ _____ _____ _____ _____ _____, and a ____-_____ ________ ________ | Axial/centrifugal six-stage compressor, annular combustor with fuel injectors, two-stage power turbine
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| A coaxial driveshaft extends from the power turbine rearward through the gas generator turbine and compressor. | False
Forward
Pg 2-10
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| The fuel system for "the T-700-GE-401C engine, in fuel flow sequence, consists of the engine-driven suction pump, _____ _____, _____ _____ _____, _____, _____, _____, and the twelve fuel injectors. | Fuel filter, fuel pressure switch, hydro mechanical unit(hmu), over speed and drain valve(odv), manifold
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| The _____ automatically controls engine functionally throughout entire Np range. | DECU
Pg 2-13
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| The power turbine (Np) is protected from destructive over speed by an _____ _____ _____. | Over speed protection system
Pg 2-13
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| The _____ _____ _____ feature of the DECU is designed to limit the engines to the set maximum torque level and works on the _____ ______ of the both engines. | Total torque limiting, combined torque
Pg 2-15
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| At MGT limiting, the _____ _____ ____ overrides the Np governing and load sharing systems, and the _____ _____ is limited to hold a constant MGT by actuating the HMU torque motor. | Temperature limiting circuits, fuel flow
Pg 2-16
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| Engine anti-icing is provided three ways: by an __-heated bellmouth installed between each engine and the intake ducts; hot axial compressor discharge __ __ flowing through the swirl and inlet guide vanes; and __ __ __ flowing through internal passages in | Electrically, bleed air, hot scavenge oil
Pg 2-17
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| The air delivery system for the pneumatic start system collects bleed air from four sources: the _____, _____, _____, or an _____ _____. | APU, engine 1, engine 2, external source
Pg 2-18
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| Release the rotor brake prior to _____% Nr to avoid _____ _____. | 0, sudden stoppage
Pg 2-34
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| Loss of MRGB oil pressure will render the helicopter unflyable within _____ minutes. | 15
Pg 2-37
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| The oil COOLER PBA selects and controls the oil cooler fan _____ _____. | Hydraulic motors
Pg 2-38
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| The combining gearbox drives two D.C. generators that _____ _____ _____ to the helicopter. | Supply electrical power
Pg 2-38
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| The combining gearbox incorporates _____ _____ chip detectors to monitor the oil in the system. | Three magnetic
Pg 2-38
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| Total internal fuel capacity is _____ U.S. gallons of which _____ U.S. gallons are unusable. | 386, 383
Pg 2-43
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| The _____ _____/_____ pump supplies fuel to the _____ automatically when the _____ is started or operating. | Left prime/boost, APU, APU
Pg 2-44
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| The OBIGGS provides nitrogen-enritched air (NEA) for the ullage of aircraft fuel cells. | True
Pg 2-47
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| DC power is supplied by the _____, _____ starter generator, _____ _____ generators, or external power source through the _____ _____ _____. | Battery, APU, Two main, external power receptacle
Pg 2-55
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| The battery contains _____ individual _____-_____ cells that are capable of starting the _____ and supplying power to the D.C. system if _____ power is not available or when _____ power is not available. | 19, nickel-cadmium, APU, generator, external
Pg 2-56
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| Each generator has a _____ and a line control relay. | GCU
Pg 2-59
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| When the NON ESS/MAN PBA is in the _____ position (annunciator blank), power is supplied to the 28Vdc non-essential bus when the _____ _____/_____ or one _____ _____ is operating. | Normal, APU starter/generator, main generator
Pg 2-60
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| In the event of dual generator failure, the pilot may reclaim the nonessential 28Vdc bus loads by selecting the _____ position with the _____. | MAN, PBA
Pg 2-60
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| Both hydraulic systems provide dual power for the main rotor controls through _____ _______. | Three MRAs
Pg 2-73
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| Hydraulic system No. 1 powers the following: | Main rotor actuators, tail rotor actuators(primary), oil cooler fan(primary), rotor brake control unit(no backup), pitch SCAS, roll SCAS
Pg 2-73
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| Hydraulic system No. 2 supplies system power for the following: | Main rotor actuators, tail rotor actuators(backup), oil cooler fan motor(backup), roll SCAS
Pg 2-73
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| The SCAS PBA is used to engage _____ _____ and the _____ _____. | SCAS channels, active elevator
Pg 2-86
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| When both the _____ and _____ legends are illuminated on the PITCH, ROLL, YAW OR ELEV PBAs, the axis is ready to be engaged by pressing the SCAS PBA. | R and D
Pg 2-86
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| _____ _____ _____ of P, R, Y, and C are located in the right region to the left of the _____ _____ indication. | Individual status indicators, COL TRIM
Pg 2-91
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| Engaging any _____ _____ _____ _____ with torque greater than _____% may result in overtorque, attitude oscillations, and aircraft unusual attitudes. | Outer loop hold function, 85
Pg 2-96
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| Landing gear structural damage will occur when the sink rate is in excess of ____ feet per minute. | 240
Pg 2-109
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| With regard to the fire extinguisher system, illumination of _____ is not dependent upon any condition other than low bottle pressure. | DISCH
Pg 2-110
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| Pressing the READY/DISCH PBA with two or more ARMED fire PBAs will cause fire retardant to be discharged into all selected compartments providing a sufficient amount of retardant to extinguish a fire in any compartment. | False
2-111
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| Pressing ENG 1, 2 or APU fire PBA will close the appropriate ____ _____ _____, close the _____ _____ _____ circuits, within the fire extinguisher system. | Firewall fuel SOV, heater control valve
Pg 2-111
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| Pitot heat is turned ON using the _____ bezel key on the SYS page. | T3
Pg 2-117
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| The windshield wipers should not be utilized on a _____ windshield. | Dry
Pg 2-117
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| The inertia reel will automatically lock when the helicopter encounters an impact force in excess of a _____ deceleration. | 2g
Pg 2-118
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| Each relief tube horn assembly on a quick-release relief horn bracket is located _____ _____ _____ _____. | Under each pilot seat
Pg 2-119
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| Wire strike protection consists of _____ and _____ _____ installed on upper and lower portions of the forward fuselage. | Deflectors and two cutters
Pg 2-120
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| Only personnel designated by _____ _____ are authorized to conduct engine motoring wash procedures. | Commanding officers
3-1
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| The minimum oil temperature for starting with lubricating oil MILF-PRF-23699 is ______. | -40°C or -40°F
Pg 3-11
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| To prevent damage to the pneumatic starter and over-servicing, do not service through the pneumatic started vent port at the _____ o'clock position. | 12
Pg 3-12
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| With SCS 6.0 some color indications in the NATOPs publications may not match the color indications displayed in the cockpit. | True
Pg 4-2
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| Engine starter limits between 61° and 126° F are first cycle on, _____ off, second cycle on, _____ off. | 60 sec, 30 min
Pg 4-2
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| For a rotor brake start, release within _____ seconds after _____% and is attained. | 25, 67+- 3%ng
Pg 4-3
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| Main Rotor Limits- Power OFF (less than 30% combined torque): | 84% Minimum Operation (at 1g)
91-110.9% Continuos Operation
110.9% Maximum
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| Power Turbine Speed (Np) Limits: | 99-101.7% Continuos
101.8-116.9% Transient Operation (12sec)
55-70% Avoid Range
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| Main Rotor Gearbox Torque Limits: | 0-104.9% Continuos Operation
105-110.9% Transient Operation (10sec)
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| _____ _____ over torque within 105-110.9% or operation within this range for more than _____ seconds requires a maintenance inspection. | Six transient, 10
Pg 4-4
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| Maximum engine torque is _____ percent. | 65.7
Pg 4-4
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| Transient Operation MGT is _____ °C for _____ seconds. | 917-964, 12
Pg 4-5
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| Normal Operation Hydraulic pressure is ______ to _____psi. | 2700-3150
Pg 4-7
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| The maximum airspeed for safety state autorotation is _____KIAS. | 120
Pg 4-9
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| The maximum MRGB torque in a dive at air speeds above Vh is _____%. | 50
Pg 4-11
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| A commercial FSII additive, _____, may be used with commercial jet fuel (JET A/JET A-1/JET B) when premixed with the fuel. | PRIST
Pg 4-14
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| Flight below _____g is prohibited. | -.5
Pg 4-18
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| Full autorotation landings as a practice maneuver are _____. | Prohibited
Pg 4-10
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| Only APU fire PBA should be illuminated if the battery is powering only the _____ bus. | Battery
Pg 7-50
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| After start with the throttle at the low side of idle, the Ng should be at _____%. | 67+- 3%
Pg 7-14
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| A non-engaged engine is indicated by a higher _____ rpm than the engaged engine along with _____ torque. | Np, 0
Pg 7-26
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| TFU clearance can be reduced to less than _____ inches on slopes inside the _____ ______ landing limitation, which may result in damage to the TFU and associated equipment. | 3, six degree
Pg7-31
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| During steep approaches at less than _____, avoid descent rates exceeding _____ fpm. | 40 knots, 800
Pg 7-41
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| During day or night operations in the Charlie pattern, the 180° position is _____ KIAS, _____ feet altitude, and about _____ yards abeam of the ship. | 80, 300, 400
Pg 8-11
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| Lighting at night becomes a critical area. The general rule of limiting _____-______ _____ lights on the flight deck should be observed. | Non- NVG compatible
Pg 8-13
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| The two basic types of formations are _____ and _____. | Parade and tactical
Pg 9-2
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| The four basic types of parade formations are _____, _____, _____, and _____. | Echelon, fingertip, diamond, and column
Pg 9-2
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| The two types of basic rendezvous are the _____ rendezvous and the _____-_____ rendezvous. | Running and the carrier-type
Pg 9-6
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| FCF crews, together with Quality Assurance personnel, shall ensure that at a minimum those _____ affected by maintanence action are _____ _____. | Systems, tested completely
Pg 10-1
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| A marked increase in airframe vibration is an indication of impending _____ _____ _____. | Rotor blade stall
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| During left rolling maneuvers of high-power dives, _____, _____, _____ will increase while _____ and _____ decrease momentarily. | Torque, Ng, MGT. Np and Nr
Pg 11-2
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| The helicopter has a tendency to roll to the _____ when forward cyclic is used to initiate a lower-than-_____ maneuver in forward flight. | Right, 1g
Pg 11-3
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| The _____ _____ system minimizes main rotor yoke loads for each trimmed flight condition. | Active elevator
Pg 11-9
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| _____ _____ is a characteristic that tends to prolong the effectiveness of collective control in the autorotation landing. | Rotor inertia
Pg 11-13
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| List the five factors that affect power-off rotor rpm. | Airspeed, Gross weight, Density Altitude, Cyclic Flare, Pilot Techniques
Pg 11-3
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| Loss of trail rotor effectiveness occurs when _____ _____ input is _____ to provide directional control. | Full pedal, insufficient
Pg 11-15
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| The note for _____ _____ _____ says that extended flight can lead to a _____ _____. | VF slip ring fail, contaminated MRGB
Pg 12-10
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| During a single hydraulic failure, reduce airspeed and transition to a flight condition with airspeeds less than _____ KIAS and angles of bank less than _____ degrees. | 100, 35
Pg 15-1,15-2
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| For most gross weights, it is unlikely that the helicopter can maintain _____ powered flight following the loss of tail rotor thrust. | Stabilized
Pg 15-8
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| There are failure modes (i.e., engine alternator failure) that may result in zero _____, _____, and/or _____ _____ indications in conjunction with an over speed condition. | Ng, Np, engine torque
Pg 15-18
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| When transient droop exceeds normal limits, maneuvers requiring large power changes, (i.e., _____, _____, _____ _____) should be avoided. | Quick stops, NOE, practice autorotations
Pg 15-20
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| In the event both generators fail in flight, emergency power is supplied by the _____ and assuming 100 percent charge, will supply essential bus power for _____ minutes with anti-ice ON and night lighting. | Battery, 9
Pg 15-25
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| When reset, it will take approximately ____ minutes and _____ seconds for the MCs to come back on line. | 2min, 30sec
Pg 15-27
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| The fire bottle contains only enough retardant to extinguish _____ _____ _____ fire or _____ _____ fire. | One engine bay, APU bay fire
Pg 15-30
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| If an engine-driven suction fuel pump fails, the engine flames out in less than _____ seconds because of fuel starvation. | 15
Pg 15-33
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| Because of the wet bulb temperature system, _____ _____ may not be accompanied by a _____ _____ indication. | Oral starvation, rising temperature
Pg 15-37
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| Under instrument condition, turns should not be executed prior to reaching a _____-foot altitude. | 200
Pg 17-3
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| The following items are required for night and instrument flight: |
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| The _____ is responsible for briefing the crew. | Pilot
Pg 6-5
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| A proper _____ conducted under tactical or training conditions can, in many instances, be the most important part of a flight. | Debriefing
Pg 6-10
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| _____ bus and _____ bus status is displayed on the BUS sub-page. The _____ warfare bus status is not reported on the BUS sub-page. |
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