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NATOPS EVALUATION
Question | Answer |
---|---|
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. |