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Should conflict exist between the NATOPS flight manual and other publications, the NATOPS flight manual shall govern.
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Anyone can recommend a change to NATOPS in accordance with OPNAVIST 3710.7
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NATOPS EVALUATION

QuestionAnswer
Should conflict exist between the NATOPS flight manual and other publications, the NATOPS flight manual shall govern. False Will govern Pg 1
Anyone can recommend a change to NATOPS in accordance with OPNAVIST 3710.7 True Pg. 56
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
Each General Electric T700-GE-401C engine is rated(uninstalled) at______ shp. 1,800 Pg 1-2
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
Each MFD has ____ lighted hard bezel keys across the bottom that are functionally grouped for ease of identification and access. Nine Pg 2-1
Default displays on power up are ____page on the ______MFDs and _____page on the MFDs. MAP, Inboard, FLT Pg 2-3
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
The bottom two rows of the keyboard contain five special purpose dedicated keys as follows: ____, ____, _____, _____, and _____. Frequency FRQ, TCN, SQK, IDNT, MRK
The T700-GE-401C engines are _____ ______, ______ ______ of modular construction. Front drive, turboshaft engines Pg 2-10
Each engine is comprised of a combination ______/______ ____-_____ ______, an _____ _____ _____ _____ _____ _____, and a ____-_____ ________ ________ Axial/centrifugal six-stage compressor, annular combustor with fuel injectors, two-stage power turbine
A coaxial driveshaft extends from the power turbine rearward through the gas generator turbine and compressor. False Forward Pg 2-10
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
The _____ automatically controls engine functionally throughout entire Np range. DECU Pg 2-13
The power turbine (Np) is protected from destructive over speed by an _____ _____ _____. Over speed protection system Pg 2-13
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
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
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
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
Release the rotor brake prior to _____% Nr to avoid _____ _____. 0, sudden stoppage Pg 2-34
Loss of MRGB oil pressure will render the helicopter unflyable within _____ minutes. 15 Pg 2-37
The oil COOLER PBA selects and controls the oil cooler fan _____ _____. Hydraulic motors Pg 2-38
The combining gearbox drives two D.C. generators that _____ _____ _____ to the helicopter. Supply electrical power Pg 2-38
The combining gearbox incorporates _____ _____ chip detectors to monitor the oil in the system. Three magnetic Pg 2-38
Total internal fuel capacity is _____ U.S. gallons of which _____ U.S. gallons are unusable. 386, 383 Pg 2-43
The _____ _____/_____ pump supplies fuel to the _____ automatically when the _____ is started or operating. Left prime/boost, APU, APU Pg 2-44
The OBIGGS provides nitrogen-enritched air (NEA) for the ullage of aircraft fuel cells. True Pg 2-47
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
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
Each generator has a _____ and a line control relay. GCU Pg 2-59
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
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
Both hydraulic systems provide dual power for the main rotor controls through _____ _______. Three MRAs Pg 2-73
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
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
The SCAS PBA is used to engage _____ _____ and the _____ _____. SCAS channels, active elevator Pg 2-86
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
_____ _____ _____ 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
Engaging any _____ _____ _____ _____ with torque greater than _____% may result in overtorque, attitude oscillations, and aircraft unusual attitudes. Outer loop hold function, 85 Pg 2-96
Landing gear structural damage will occur when the sink rate is in excess of ____ feet per minute. 240 Pg 2-109
With regard to the fire extinguisher system, illumination of _____ is not dependent upon any condition other than low bottle pressure. DISCH Pg 2-110
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
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
Pitot heat is turned ON using the _____ bezel key on the SYS page. T3 Pg 2-117
The windshield wipers should not be utilized on a _____ windshield. Dry Pg 2-117
The inertia reel will automatically lock when the helicopter encounters an impact force in excess of a _____ deceleration. 2g Pg 2-118
Each relief tube horn assembly on a quick-release relief horn bracket is located _____ _____ _____ _____. Under each pilot seat Pg 2-119
Wire strike protection consists of _____ and _____ _____ installed on upper and lower portions of the forward fuselage. Deflectors and two cutters Pg 2-120
Only personnel designated by _____ _____ are authorized to conduct engine motoring wash procedures. Commanding officers 3-1
The minimum oil temperature for starting with lubricating oil MILF-PRF-23699 is ______. -40°C or -40°F Pg 3-11
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
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
Engine starter limits between 61° and 126° F are first cycle on, _____ off, second cycle on, _____ off. 60 sec, 30 min Pg 4-2
For a rotor brake start, release within _____ seconds after _____% and is attained. 25, 67+- 3%ng Pg 4-3
Main Rotor Limits- Power OFF (less than 30% combined torque): 84% Minimum Operation (at 1g) 91-110.9% Continuos Operation 110.9% Maximum
Power Turbine Speed (Np) Limits: 99-101.7% Continuos 101.8-116.9% Transient Operation (12sec) 55-70% Avoid Range
Main Rotor Gearbox Torque Limits: 0-104.9% Continuos Operation 105-110.9% Transient Operation (10sec)
_____ _____ 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
Maximum engine torque is _____ percent. 65.7 Pg 4-4
Transient Operation MGT is _____ °C for _____ seconds. 917-964, 12 Pg 4-5
Normal Operation Hydraulic pressure is ______ to _____psi. 2700-3150 Pg 4-7
The maximum airspeed for safety state autorotation is _____KIAS. 120 Pg 4-9
The maximum MRGB torque in a dive at air speeds above Vh is _____%. 50 Pg 4-11
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
Flight below _____g is prohibited. -.5 Pg 4-18
Full autorotation landings as a practice maneuver are _____. Prohibited Pg 4-10
Only APU fire PBA should be illuminated if the battery is powering only the _____ bus. Battery Pg 7-50
After start with the throttle at the low side of idle, the Ng should be at _____%. 67+- 3% Pg 7-14
A non-engaged engine is indicated by a higher _____ rpm than the engaged engine along with _____ torque. Np, 0 Pg 7-26
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
During steep approaches at less than _____, avoid descent rates exceeding _____ fpm. 40 knots, 800 Pg 7-41
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
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
The two basic types of formations are _____ and _____. Parade and tactical Pg 9-2
The four basic types of parade formations are _____, _____, _____, and _____. Echelon, fingertip, diamond, and column Pg 9-2
The two types of basic rendezvous are the _____ rendezvous and the _____-_____ rendezvous. Running and the carrier-type Pg 9-6
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
A marked increase in airframe vibration is an indication of impending _____ _____ _____. Rotor blade stall
During left rolling maneuvers of high-power dives, _____, _____, _____ will increase while _____ and _____ decrease momentarily. Torque, Ng, MGT. Np and Nr Pg 11-2
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
The _____ _____ system minimizes main rotor yoke loads for each trimmed flight condition. Active elevator Pg 11-9
_____ _____ is a characteristic that tends to prolong the effectiveness of collective control in the autorotation landing. Rotor inertia Pg 11-13
List the five factors that affect power-off rotor rpm. Airspeed, Gross weight, Density Altitude, Cyclic Flare, Pilot Techniques Pg 11-3
Loss of trail rotor effectiveness occurs when _____ _____ input is _____ to provide directional control. Full pedal, insufficient Pg 11-15
The note for _____ _____ _____ says that extended flight can lead to a _____ _____. VF slip ring fail, contaminated MRGB Pg 12-10
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
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
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
When transient droop exceeds normal limits, maneuvers requiring large power changes, (i.e., _____, _____, _____ _____) should be avoided. Quick stops, NOE, practice autorotations Pg 15-20
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
When reset, it will take approximately ____ minutes and _____ seconds for the MCs to come back on line. 2min, 30sec Pg 15-27
The fire bottle contains only enough retardant to extinguish _____ _____ _____ fire or _____ _____ fire. One engine bay, APU bay fire Pg 15-30
If an engine-driven suction fuel pump fails, the engine flames out in less than _____ seconds because of fuel starvation. 15 Pg 15-33
Because of the wet bulb temperature system, _____ _____ may not be accompanied by a _____ _____ indication. Oral starvation, rising temperature Pg 15-37
Under instrument condition, turns should not be executed prior to reaching a _____-foot altitude. 200 Pg 17-3
The following items are required for night and instrument flight:
The _____ is responsible for briefing the crew. Pilot Pg 6-5
A proper _____ conducted under tactical or training conditions can, in many instances, be the most important part of a flight. Debriefing Pg 6-10
_____ bus and _____ bus status is displayed on the BUS sub-page. The _____ warfare bus status is not reported on the BUS sub-page.
Created by: BarBar1775
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