Module 13

The stall margin mode is controlled by. EPR limits. Speed bug cursors. A O A and flap position sensors.

The versine signal is used in the. pitch channel only. roll channel. pitch and roll channel.

Lift in a helicopter is a result of. Angle of attack X velocity squared and forward speed. Angle of attack X velocity squared. Pitch X square root of speed.

With AGC inop, sensitivity will be effected to signals with. low signal strength. High signal strength. Both.

ADF, quadrature error are eliminated by placing attenuators. Across loop aerial. Across sense aerial. Across goniometer.

Altitude hold mode, what signal is washed out?. Altitude. Pitch angle. Rate of climb.

Voice/Range switch selected to range. allows NAV/ADF and DME through cancelling out voice spectrum. allows NAV/ADF and cancels out voice spectrum. allows noise spectrum through.

GPS L 1 and L 2 signals are. Bi phase 50 bit/ sec. 10.2 KHZ send rate. 1KHz send rate.

ILS indicator is. parallel to filters. series with filters. across filters.

Transmission line losses have what effect on VSWR. Increase. Decrease. Do not affect.

ARINC 629 operates at which speed ?. 1300 Kb/s. 1000 Kb/s. 2000 Kb/s.

A Loran C transmission consists of. 6 pulses each 270 microseconds long. 8 pulses each 270 microseconds long. 6 pulses with a total pulse train length of 8.27 ms.

Water contamination in a capacitance fuel system will. cause contents to overead. cause contents to under read. short out capacitance probe and trip CB.

Using the fast erection switch on a standby horizon prior to the flag clearing may cause. the instrument to erect false datum. application of a large torque to the control phase windings causing failure. You must use the Fast erection switch to clear the flag.

A rate gyro has. one degree of freedom along the lateral axis. a calibrated spring to restrain movement about longitudinal axis. a calibrated spring bet.

An aircraft landing on QFE the altimeter will. read zero on touchdown. read airfield height on landing. read local area pressure.

ARINC 429 operates at which speed?. 13 kb/s or 100 kb/s. 2 Mb/s. 1.3 Mb/s.

On a Cat 3 B landing the localizer signal is used at which phase?. Rollout. Flare. Touchdown.

The glideslope signal integrator. maintains glideslope signal. increases glideslope signal. decreases glideslope signal.

What is the maximum value of installation tester that may be used on a fuel contents system?. 300 Volt. 250 Volt. You cannot use one on the fuel contents system.

A blade of a Helicopter Main Rotor is. highly cambered. symmetrically camber. reverse camber.

A Mode S equipped aircraft has its RA area breached by a Mode A only equipped aircraft. What warning does the Mode S aircraft get?. TA visual and Traffic Traffic aural warning. RA visual and climb or descend aural warning. ATA visual warning only.

The capacitance fuel contents system works on the principle of. capacitive reactance. resistance. capacitance.

Rad Alt failure effects which system?. Mode S transponder. GPWS. nav management systems.

Man made noise causes interference. mainly above 12 Mhz. only in the LF band. mainly below 12 Mhz.

The frequency spectrum of noise is. infinitely wide. restricted to the audio band. restricted to the HF band.

The noise factor of a receiveis 15:1 and O/P signal to. 0.8. 1.25. 2.5.

A receiver with a high IF will successfully reject. the adjacent/image frequency. the 2nd channel/image frequency. the 2nd channel/adjacent frequency.

A receiver in which selected converted to a single frequen. Wideband TRF. Multi-channel receive. superhet rece.

A radar pulse takes 308 microseconds to return, what is the target distance. 12.5 Nautical miles. 25 Nautical miles. 30 Nautical miles.

Delayed Automatic Gain Control is inoperative, the sensitivity of the receiver will. decrease for low signal. increase for low signal. increase for high signal.

Single Side Band filters are. 3 Khz. 1 Khz. 6 Khz.

The loop aerial polar diagram is a. c ardioid. figure 8. c ircle.

The relationship between LORAN master and slave transmitters. Master frequency. higher than slave. lower than slave. same as slave.

What is needed for RHO-RHO navigation?. 2 DME signals. 1 VOR and. 1 VOR /DME signal.

With an ATC code of 0600 selected, the pulses transmitted are. B 2 and B 4. B 1 and B 5. B 0 and B 6.

Tail rotor effects the helicopter in. Vertical. Horizontal. Pitch and Roll.

RNAV accuracy is. +/- 5nm. +/- 5nm 95%. +/- 1nm 85%.

In colour WXR AGC is set. in workshop. automatically on receiver noise level. by operator on manually adjusted gain control.

What is Track angle?. The angle, measured clockwise, between true north and the aircraft ground track. The angle, measured clockwise, between true north and the aircraft longitudinal axis. The angle between true heading (HGD) and ground track.

What is an Ideal VSWR on a Radio Transmission line?. 1:1. 2:1. 1.5:1.

On an FMCS CDU, you can select. N 1 Thrust. VNAV. VOR.

To check side lobe suppression. select ATC on ASP. use a ramp test set. carry out a self test.

A valid interrogation will. disable the RX, enable the encoder and disable the DME. enable the RX, disable the encoder and disable the DME. disable the R.

When calibrating an electronic fuel capacitance indicating system, what piece of test equipment would you use?. a bridge. a decade. a potentiometer.

API Trim pointers are fed by. a synchro. an RVDT. an LVDT.

VHF transmitter output impedance to match with antenna for maximum power transfer is. 50 ohms. 25 to 75 ohms. 129 ohms.

Radio waves are said to have line-of-sight propagation. above about 100 MHz. not below 1000 MHz. from about 10 MHz upwards.

Glide slope gain programming is based on. pressure altitude. altitude above MSL and radio altitude. radio altitude.

The Glide-slope signal integrator. maintains the glide- slope signal. increases the glide-slope signal. decreases the glide-slope signal.

If the static pressure is varied at too great a rate, the instrument that s most affected is the. rate of change indicator. altimeter. airspeed indicator.

The speech clipping modulating circuit. increases the average depth of modulation. clips high amplitude signals. cuts out high tone sounds.

The ATC aerial has a polar diagram which is. directional. omni-dirrectional. limacon shaped.

A padder capacitor has most efficiency at. the lowest frequency of the L O. the middle frequency of the L O. the highest frequancy of the L O.

Voice clipping. increases the depth of modulation. decreases the depth of modulation of high amplitude voice signals. maintains an average depth of modulation.

Flight Director bars controls move up in slow increments, what controls their rate/speed?. Rate feedback. Position feedback. Instrument amplifier gain.

What aircraft system supplies horizon?. Generator bus. Normal power, then switches to emergency supply in an emergency. Battery Bus.

Three RF amplifiers of is the output?. 30 dB and 10 KHz. 10 dB and 1000 KHz. 30 dB and 1000 KHz.

A single side b. High level modulation. Low level modulation. One half of the high le.

If a fault is detected during an autoland approach, the system will totally disconnect if it is a. triplex system. duplex system. dual/dual system.

An autoland is carrid out in which sequence. GS capture, LOC capture, attitude hold, flare. LOC capture, GS capture, Attitude hold, Flare. LOC capture, GS capture, Flare, Attitude hold.

Signals used during the flare are. GS and rad alt. GS and integrated pitch. Rad alt and integrated pitch.

With a Vertical Gyro simulatescanner in left hand position. tilt up. tilt down. tilt right.

Man made noise. mainly above 12mhz. only in the LF band. mainly below 12 mhz.

A receiver having an IF of which of the following signals coulharmonics to produce a receivused. 3995 Khz . 2230 Khz . 465 Khz.

An I F amplifier unit consist of four amplifiers. The amplifiers are normally coupled by. resistor/capacitor coupling. pure resistor coupling. transformer coupling.

A receiver with a high I F will successfully reject. the adjacent/image frequency. the 2nd channel/image frequency. the 2nd channel/adjacent frequency.

Vortex ring start requires. retreating blade stall. advancing blade stall. power on descent.

The integrity of an auotpilot must be increased when the aircraft is flying at. higher speeds. lower speeds. approach and landing phases.

An integrated autoland system has been selected to Go-around during the autoland phase, the aircraft will. increase speed. increase speed and rotate nose up. rotate nose up.

Go-around mode can be initiated. after glideslope capture. at any time. below 2000 ft.

Rollout guidance by the rudder is effective to about. 80 knots. 110 knots. 30 knots.

Delayed Automatic Gain Control is inoperative, the sensitivity of the receive. decrease for low signal. increase for low signal. increase for high signal.

Air density compensation requires. OAT. altitude. altitude and OAT.

A quartz crystal has the characteristics of a. resistive bridge network. high `Q` resonant circuit. pair of tuned circuits.

Which of the following has the best frequency stability?. Hartley. Colpitts. Tuned collector tuned base.

Tx output stages are normally run in class C. because the efficiency is high. so that the output is rich in harmonics. as higher gains can be obtained.

When can the FMS be engaged with the autothrottle?. Before takeoff. After takeoff. Only with the autopilot engaged.

In a dual FMS, a failure of one computer will result in. COMPLETELY blank display on one CDU. down-grade of the landing category. no effect on the CDU.

The aircraft is programmed to leave the glideslope at. 300 ft. the decrab phase. the start of flare.

At its resonant frequency, a parallel tuned circuit. offers minimum impedance. has minimum voltage developed across it. has maximum circulating currents.

The RF resistance of an inductor. decreases as frequency is increased. increases as frequency is increased. is independent of frequency.

Crystals operate reliably at fundamental frequencies up to. 1000 MHz. 100 MHz. 30 MHz.

At its resonant frequency, a parallel tuned circuit has. maximum impedance. minimum impedance. the same impedance as at any other frequency.

An aircraft increases in altitude, the ASI indication remains constant, what will happen to the True airspeed value?. Increase. Decrease. Remain the same.

A Mach meter. compensates for square law. does not compensate for square law. uses a spring and bar.

Where is zone 320 on an aircraft according to the ATA 100 system?. Fin. Horizontal Stabilizer. Fuselage.

The distance over which VHF communication may be achieved is limited. by local weather conditions in the troposphere. to radio line of sight. to conditions in the ionosphere.

When terminating an aluminium cable, what preparations would be carried out before crimping?. Just terminate. Apply a mixture of 50% petroleum jelly and zinc oxide. Degrease spripped cable.

How can ambiguity be avoided during the test of a microwave landing system?. Reverse the phases. TO/FRO. Note scan cycle start time.

What does a current limiter fuse do?. Limit current to a predetermined level to prevent circuit damage. Allow high current to flow for 5 seconds. React when the circuit gets warm.

The stability of an RF oscillator can be improved by. direct coupling to an RF amplifier. a buffer amplifier. tight coupling to an RF amplifier.

A typical ratiometer indicating system would use. 3-phase AC. single phase AC for indicator and transmitter. single phase AC for indicator and dc for transmitter.

The AFCS remains in control: until 2 seconds after touchdown. until reverse thrust is selected. until disengaged by flight crew.

The plane of polarisation is defined as the plane in which the. E field lies. H field lies. E and H fields are parallel.

What type of signal is used for trigger height trip signals?. Switchable d.c. Switchable a.c. variable d.c.

How does the crew select decision height?. selected on the main altimeter. Selected on the radio al. selecting a switch on the control panel.

The decision height on the Radio Altimeter system is adjusted by. moving a bug on the Radio Altitude indication. selecting a switch on the control panel. moving a bug on the Barometric altimeter.

DME squitter comes from. DME station. interrogator. test set.

The frequency range 300KHz-3 MHz is called the. LF band. MF band. VHF band.

On the ASP how many Rx and Tx can be selected at any one time?. multiple Rx and only one Tx. multiple Rx and multiple Tx. only one Rx and only one Tx.

a receiver having an IF of 465 KHz .is tuned to 1300 Khz, which of the following signals could interact with the L O second harmonics to produce a receiver output if no RF amplifier was used. 3995 Khz. 2230 Khz. 465 khz.

ICAO Standard atmosphere is. taken from data measured at the equator. taken from data measured at 45 degrees North. relevant to set parameters.

In a triplex system, if an ILS receiver fails before localizer capture. No auto land. Reverts to cat II. Continues to auto land.

Compass error Q corrections correct. A error. B error. C error.

Slats, when stowed, make up part of the wing. trailing edge. leading edge lower surface. leading edge upper surface.

A plain flap. When stowed makes up part of the wing trailing edge lower surface. When stowed makes up part of the wing trailing edge upper surface. when deployed increases the camber of the wing.

ADF quadrantal error will be at. 0 Degrees. 45 Degrees. 90 Degrees.

Cat 2 RVR if the alert height is 100 feet will be. 300 m. 400 m. 800 m.

A typical Ratiometer indicating system would use. 3 phase AC. Single phase AC for the indicator and transmitter. Single phase AC for the indicator and DC for the transmitter.

An anti-servo tab. assists the pilot to move the controls back to neutral. moves in the same direction as the control surface to assist the pilot. moves in the opposite direction to the control surface to assist the pilot.

An ASI compressibility error correction will be. Positive. Negative. Both.

A GNS satellite system transmis. vertically polarise. horizontally polarise. right hand circular.

When servicing an RVSM aircraft. all pitot/static instruments must be serviceable. the alt alert must be serviceable. the alt hold must be serviceable.

Airspeed hold is a. pitch mode. lateral mode. heading mode.

The auto gain voltage of weather radar is set. in the workshop. by the manufacturer. by adjusting the gain control until optimum picture quality is obtained.

When carrying out an autoland approach, VNAV is de-selected. The aircraft will enter MCP SPD mode when. APP switch is pressed. the aircraft captures the glideslope. the aircraft receives the first ILS signal.

A split flap. forms part of the leading edge`s lower surface when retracted. forms part of the trailing edge`s upper surface when retracted. forms part of the trailing edge`s lower surface when retracted.

TCAS will issue a traffic advisory if. aircraft are within 6 nautical miles laterally and 1200 feet vertically of each other. a collision is within 25 -35 seconds of occurring. a collision is within 35 -40 seconds of occurring.

Non-essential loads such as galleys and cabin lighting operate from. Ground services bus. Ground handling bus. Transfer bus.

Mach trim counters. longitudinal instability. lateral instability. vertical instability.

Aircraft generators are connected in. series to the busbar, parallel to the load and the loads parallel to each other. series to the busbar, series to the load and the loads parallel to each other. parallel to the busbar, series to the load and the loads parallel to each other.

Parallel distribution systems can typically found on all. twin-engined aircraft. aircraft with 3 or more engines. aircraft with 4 or more engines.

The power factor of an AC generator identifies the proportion of. reactive power from the generator that does work. apparent power from the generator that does work. real power from the generator that does work.

Paralleling in AC constant frequency is affected by. contactors. Generator Control Unit (GCU). But Tie Bar (BTB).

If voltage and frequency of the generator drop to zero in flight, it would be an indication that the. Phase sequence detection circuit has operated. CSD drive shaft has sheared. bus tie interlock is inoperative.

A RAT provides AC power of around. 7.5 kva. 63 kva. 28 VAC.

What manoeuvre does TCAS II adv. TA. RA. either RA or.

What are the shapes of traffic shown on a TCAS display ?. White diamonds, red squa s and amber circles. White squares, red diam . White circles, red diamonds and amber squares.

During a system overload, load sharing will first affect. galley servic. IFE. first officers transfer bus.

GPS. uses 24 satellites equally spaced around 6 orbits. uses 18 satellites equally spaced around 6 orbits. uses 21 satellites equally spaced around 7 orbits.

A flux valve becomes permanently magnetized. What will be the effect?. More deviation. More variation. Remote compass will indicate in one direction only.

Bandwidth of HF transmission is. 1 khz. 1.5 khz. 3 khz.

When a compass is in the slave mode. the azimuth gyro will wander uncompensated. azimuth gyro will be corrected by long term monitoring of the flux valve. the azimuth gyro is slaved to the annunciator or synchroniser circuit.

Dome lights on the flight deck are powered by the. battery bus bar. battery bus bar or ground services. ground services.

An accelerometer has. low inertia, free suspension. high inertia, restrained. high inertia, free suspension.

An accelerometer in an INS must be able to detect accelerations down to. 10-3 g. 10-2 g. 10-6 g.

What is the millivolt deflection per dot on ILS/VOR?. 25/75. 25/5. 75/75.

The middle marker is keyed with. dots. dashes. alternate dots and dashes.

The vocal repetition for Mode 6 warnings are repeated. once only. twice only. three times only.

DFDR [digital flight data recorder] ARINC 573 data bus has how many sub-frames?. 4. 6. 8.

Which modes of the GPWS may be inhibited. modes 1, 3, 4 a, 6. modes 2, 4, 5. modes 4b ,5.

A laser dither mechanism ensures that. optical backscatter does not cause the contra rotating beams to lock together. the contra rotating beams are synchronised together. that the two contra rotating beams are each at different frequencies.

The most common type of gyro used in an INS is. a single rate integrating gyro wih viscosity damping. a single rate gyro with a spring restrained gimbal and eddy current damping. a displacement gyro to sense displacement and a rate gyro to sense rate of displacement.

A DME receives a ground transponder reply after 2472 microseconds, the slant range to the transponder is approximately. 196 nm. 200 nm. 200 statute miles.

In a CVR system hot mics. are as selected by the boom/mic switches. is a term applied to all the aircrafts mics. get their power supply from the selected Tx via the r/t switch.

When the ILS marker hi/lo switch is set to lo. receiver sensitivity is reduced by 10 to 12 db. increased by 10 to 12 db. marker lamps are illuminated by a lower signal level.

When using the GPS. database card must be replaced every 28 days. once the database card has expired the system will continue to operate with a warning message. once the database expires the system will not operate.

The mode S squitter pulse will. trigger the TCAS mode S all call interrogation. contain the aircraft identity. contain the aircraft range and altitude information.

When an ADF antenna is repositioned from the bottom of the fuselage to the top, the wiring of the bearing indicator must be. reverse R 1+ R 2 connections only. reverse R 1+ R 2 and S 1 + S2 connections. reverse R 1+ S 2 connection.

The VSWR of a VHF system with a forward power of 100W and a reflected power of 4W will be. 1.5:1. 2:1. 2.5:1.

An isotropic radiator. is an end fed p/ 2 unipole. has a perfectly spherical radiation pattern. has a cardiod shaped polar diagram.

The short circuit stub that is used for broadbanding a VHF whip must have a length of about. 29 cm. 59 cm. 70 cm.

Localizer modulation depth is. 2%. 20%. 50%.

The aerial element of a VHF comms transmitter/receiver should have a midband length of. p /4. p /2. p.

If the 90 Hz tone predominates in a localizer receiver ,the deviation indicator will show. the flag. fly right. fly left.

The components of an ILS are: A localizer and a glide slope. A localizer, a glide slope and the marker beacons. A localizer and the marker beacons.

In ILS, the glide slope provides. lateral steering. vertical steering. distance checks.

A secondary surveillance radar (SSR) interrogation operates on. a frequency of 1030 MHz and pulse spacing of 20.3 microseconds. a frequency of 1030 MHz and pulse spacing depending on mode of interrogation. a frequency of 1090 MHz and pulse spacing 20.3 microseconds.

The DVOR is preferred in comparison to CVOR because. DVOR is relatively insensitive to SITE errors. DVOR ground installation is relatively simpler. DVOR is compatible for digital processing.

In CVOR,9960 c/ s AM subcarrier is used in. VAR phase. REF phase. station identification Morse code.

In an aircraft VOR receiver. 108 MHz reference signal is compared with 9960 Hz variable phase signal. 30 Hz modulated reference signal is compared with 30 Hz variable phase signal. 30 Hz reference signal is compared with 9960 Hz variable phase signal.

Directional property is exhibited by. the sense antenna. the loop antenna. both the sense and loop ant.nna.

In ADF system, Goniometer. combines the signals from fixed loop antenna and sense antenna. effectively simulates a rotating loop antenna. alternately selects signals from loop antenna and sense antenna.

If voltage and frequency of the generator drop to zero in flight, it would be an indication that the. CSD drives shaft had sheared. phase sequence detection circuit has operated. bus tie interlock is inoperative.

Assuming all systems are operating normally, as aircraft electrical load increases, generator output voltage will. decrease and amperage output increases. increases and amperage output increases. remain constant and amperage output increases.

One of the main purposes of a CSD is to. enable generators to be paralleled. prevent engine overload. maintain constant load on the generator.

in a undervolt condition in an AC generator system, the most likely consequence is. activation of the time delay circuit. de-activation of the field regulatory TRs. energise the bus tie relay.

When resetting the CSD on the ground, the engine should be. stationary. rotating at idle. rotating at Nsync.

Differential protection in an AC system protects against. A reverse current flowing from the battery. short circuits. line-line, line-line-line, line-earth faults.

The power factor of an AC generator identifies the proportion of. apparent power from the generator that does work. reactive power from the generator that does work. real power from the generator that does work.

The control of hydraulically powered emergency electrical generator frequency is by. angle of swash plate. IDG. restriction valve.

Inductive reactive load causes. no effect on torque but produces extra heat dissipated. increase in torque and increase in heat dissipated. increase in torque only.

Increasing the real load primarily. decreases frequency. decreases output voltage. increases output voltage and increases frequency.

Paralleled relay for DC system is energised and connected by. voltage coil. current coil. voltage and current coil.

In a transistor voltage regulator the voltage output is controlled by. transformers and transistors. diodes and transformers. zeners and transistors.

The output of a carbon pile regulator with no variation of loading is. stationary. fluctuating. pulse width modulating.

In a carbon pile regulator the resistive element is. in series with the field and changes resistance with changing length. in series with the field and changes resistance with surface area contact. in parallel with the field and changes resistance with changing length.

Battery charging procedures can be found in ATA. Chapter 24 Section 21. Chapter 24 Section 31. Chapter 31 Section 21.

If an aircraft has no battery charger the battery is charged by. constant voltage. constant current. constant current until a predetermined limit when it automatically switches to constant voltage.

Maximum battery temperature on charging before protection circuit starts is. 115 degrees F. 144 Degrees F. 144 Degrees C.

What is the small pin on the DC ground power connector?. Ground or earth. Positive to battery relay. Positive to external power relay.

When installing multiple batteries on aircraft they are connected in. parallel. series. either parallel or series and switched between as an option.

Battery trays are. metal for earthing purposes. metal with PVC coating and anti corrosive paint. absorbent to soak up electrolyte.

A shunt wound generator fitted on an aircraft,a preset potentiometer is fitted. in series with the field winding. in parallel with the field winding. in series with the generator output.

on a VSI fitted on an aircraft, for climb and descent indication. a set screw is provided for zero adjustment. it does not have any adjustment. a set screw is provided for climb/descent increments.

The manufacturer of a pitot head gave a specification indicating 2 inches dia. This is the. opening dia. of pitot head. internal dia of pitot head where air stagnates. external dia of pitot head.

A transformer has a power input of 115V AC. What is the output voltage?. 115V. 345V. 460V.

Radar beamwidth improves. range resolution. range accuracy. bearing resolution.

When an hydraulic system is un pressurized, the position of flight control surfaces are. down. neutral. droop.

Oscillation and hunting of flight control surface are prevented by. Tachogenerator. Feedback from control surface. Feedback from servo motor.

The pitot head is fitted on the aircraft. The alignment of pitot head is carried out with. an inclinometer. micrometer. spirit level.

A D.R. compass fitted on an aircraft. The safe distance for electrical cables carrying electrical current is. 20 inches. 24 inches. 28 inches.

Stick shaker activates at a speed which is above the stalling speed by. 4%. 7%. 10.321%.

Versine signal is governed by. roll. pitch. yaw.

Compass error remaining after all corrections are made is called. apparent error. residual error. index error.

Instruments used on an aircraft are in some instances fitted with cover glasses whose surfaces are bloomed to reduce. Parallax error. Surface reflection. Static to avoid dust attraction.

Compass error remaining after all the corrections, which is used for entry on the deviation card should not exceed. 2 degrees. 3 degrees. 5 degrees.

When more than one D.R. compass is fitted on an aircraft or where a D.R. compass serves as a standby to a remote reading compass. only the master compass readings and adjustments carried out and remaining compasses are adjusted with master compass. all readings and adjustments for each compass should be made simultaneously on each heading. all readings and adjustments for each compass should be made at any one heading only.

Standing waves in a Co-Axial feeder cable are proportional to. length of the cable. transmitter power output. degree of mismatch between transmitter and antenna.

A radar antenna is facing left. On ground test, if you move the vertical gyro to simulate a right bank, the antenna. will not move. will move down. will move up.

Dutch Roll affects. yaw and roll simultaneously. pitch and yaw simultaneously. pitch and roll simultaneously.

When checking the altitude reporting of the transponder. set the rad alt to 0 feet. set the barometric altimeter to 1013.25 mb. set the barometric altimeter to local pressure.

Wing can spoilers be used?. To assist the elevators. As ground spoilers on landing. To assist the respective down going aileron in a turn.

On a modern aircraft about to stall. the flaps retract automatically. engine power increases automatically. the outboard slats extend automatically.

Direction of normal flight is changed by the pilot by applying pressure. to the rudder pedals. to the control column. to the control wheel.

A Doppler VOR station`s transmissions. can be received but not processed with a conventional VOR receiver. can not be received and processed with a conventional VOR receiver. can be received and processed with a conventional VOR receiver.

on an Autoland coupled approach, a GPWS warning. visual warning only. audio and Visual warning. would initiate a Go Around.

An FM signal would have it`s sideband signals. No sidebands present. below the carrier signal. above the carrier signal.

What frequency range does ACARS operate in?. 4-5 GHz. 118-136 MHz. 2-30 MHz.

If the VOR track error is 2 dots, how many degrees off track is the aircraft?. 5. 2.5. 10.

An aircraft receives a response from a DME station, 1236 microseconds after transmitting the interrogation. What is the slant range to the station?. 104 nautical miles. 100 nautical miles. 96 nautical miles.

in an auto trim horizontal stabiliser, `low` speed mode is when. flaps extended. landing gear up and locked. flaps are retracted.

Aircraft is north of VOR beacon, course is set to 90 degrees, RMI indicates. 0. 180. 90.

MLS azimuth range is. +/- 62. +/- 42. +/- 30.

with no.1 h.f. system transmitting the interlock circuit. does not allow no.2 to transmit or receive. allows no.2 h.f. to transmit and receive. allows no.2 h.f. to receive only.

Control loop gain with an autopilot is usually. chosen as a compromise. 100%. dependent on aircraft altitude.

With power applied to the autopilot but not engaged, the trim indicator will indicate. the trim system is out of datum. that the gyro is out of the null and needs aligning. a standby electrical signal in the servo loop.

at take off, if the flaps are lowered there is a. large increase in lift and small increase in drag. small increase in lift and drag. large increase in lift and drag.

In a large transport aircraft to check VSWR of a HF system with a long aerial feeder the VSWR meter has to be connected. between the transmitter and the ATU (ATU end). between the aerial and ATU. between the transmitter and the ATU (transmitter end).

When the flaps are lowered. there is no effect on the lift vector. the lift vector moves rearward. the lift vector moves forward.

A HUMS in a helicopter is. a system which indicates a crack in the blade. a system which monitors time period of components in service and warns of a premature failure. a vibration analysis system.

Transformer coupling between ADI and Flight director is to protect. both of the above. ADI. Flight director computer.

Co-axial transmission line of impedance 80 ohms is connected dipole of 120 ohms. While checking with ohm meter the reading will be. more than 20 mega ohms. 80 ohms. 200 ohms.

DME - how does receiver find the received pulse pairs are valid?. Integrator. Blocking oscillator. Decoder.

In audio clipping. there is no change in relative strength of vowels. vowels are attenuated relative to the remaining signal. vowels are strengthened relative to the remaining signal.

Anti cross-talk network for unwanted signals uses. no attenuation but amplification. amplification first then attenuation. attenuation first then amplification.

Transformer coupling between an ADI and a flight director computer is. to protect the FD computer in case of an HSI failure. to protect the FD computer in case of an ADI failure. to protect the ADI in event of a FD computer failure.

When an AM carrier is modulated, its bandwidth. remains the same. decreases. increases.

A helicopter needs to re-trim. indication is shown on the command bars of the attitude indicator. indication is shown on the command bars of the EHSI. indication is shown on the API.

If the inductance in a parallel tuned circuit is increased in value, the resonant frequency. increases. decreases. remains the same.

Flight director on G/S capture, the pitch integration is. to maintain GS signal. to increase GS signal. to decrease GS signal.

Flight director on VOR, course error wash out signal is lost, following the FD commands. Aircraft will. follow the course with scalloping or bracketing. stay parallel to course. stay on centre of course.

WX radar display the time base is. rectangular wave form. trapezoidal wave form. saw tooth wave form.

Speed control on an emergency hydraulic driven generator is via the. swash plate. CSD. IDG.

If the localiser signal is only applied to the A/P roll channel. aircraft flies in circles. aircraft flies along the runway centre line. aircraft flies parallel to the runway centre line.

Aircraft normally fitted with 2 central maintenance computers and you only have one to dispatch the aircraft. LH or RH side (i.e. doesn`t matter). RH side. LH side.

The term `circling current` refers to. DC generators. AC and DC Generators. AC generators.

A DGPS system installed on an aircraft requires. 1 ground station and 6 satellites. 2 ground stations and 4 satellites. 1 ground station and 4 satellite.

An uncorrected ADI is affected by. descent. roll. climb.

Which would you use to test an aircraft transponder altitude reporting system?. Check the altitude code with the correct alt/code table. Transfer the code displayed by the ATC-600 into binary. Read the altitude directly from ATC-600 panel.

Mode C response is. 8 microseconds. 12 microseconds. 21microseconds.

FMC mode that can be selected through the CDU is. CRZ. LNAV. DME Freq.

Cat IIIB landing, up to what phase is LOC signal used?. Touchdown. Flare. Roll out.

ADF operates within which frequencies?. 32 KHz - 64 KHz. 118 MHz - 132 MHz. 200 KHz - 1000 KHz.

A `q` feel system supplies. control movement effort relief. the pilot with ever increasing awareness of speed. aerodynamic damping.

If the torque were increased on a vertical gyro, what would happen to the precession?. Decrease. Increase. Remain unaffected.

The result of the equation (Dev E - Dev W)/2 is known as. Coefficient C. Coefficient A. Coefficient B.

Which is used for compass damping fluid compensation?. Piston and oil. No damping due to alcohol low temperature co-efficient. Bellows or diaphragm.

On a Ground Power unit which pins are allocated for interlock circuit?. E and F. B and C. A and B.

What does a vibration type sensor measure?. Direction of flexing. Frequency of deflections. Maximum deflection.

Which signal would be integrated to get onto Localiser centreline?. Radio deviation. Course error. Heading error.

What effect does lowering flaps for takeoff have?. Reduces landing speeds only. Reduces takeoff speeds only. Reduces takeoff and landing speeds.

What effect does lowering the flaps for takeoff have?. Increase lift only. Increases lift and drag. Increases lift & reduces drag.

If a roll was commenced, what command would the versine generator give?. Down elevator. Left rudder. Up Elevator.

How does a delta wing aircraft move about the pitch and roll axis?. Ailerons. Elevons. Elevator s.

A Master Warning is issued when. engine fire & trip occurs. cargo smoke and low oil quantity occurs. overspeed and low cabin attitude occurs.

If increasing altitude at constant IAS, TAS will. remain the same. increase. decrease.

What instrument uses ram air pressure and atmospheric pressure?. VSI. Machmeter. ASI.

After a roll to the left of a statically stable helicopter , the helicopter would. come back to level flight. increases roll. continue to roll.

LOC signal modulation is. 20 %. 10 %. 50 %.

If an aircraft moves in roll it is moving about the. longitudinal axis. lateral axis. normal axis.

Rising gust in front of the leading edge with flaps lowered, AoA will. remain. decrease. increase.

Spring tabs. cannot be adjusted. can be adjusted in the flight deck. cannot be adjusted in flight.

If an elevator is fitted with a fixed tab in the down position, the control surface will. move down. remain at the same place. move up.

In a boost gauge system the sensing element contains. 3 capsules. 2 capsules. 1 capsule.

Where is the placement of a mercury switch?. Instrument case. Gyro case. Outer gimbal.

DC power into the GCU comes from. ground service. main battery bus and ground service. main battery bus.

What happens when a control stick is pulled back and to the left?. Elevator down, right aileron down. Elevator up, right aileron down. Elevator up left aileron down.

What should be taken into account when measuring the SG of a battery?. Charge state of the batter. Electrolyte temperature. The outside temperature.

In an amplitude modulated wave, the intelligence is contained in the. sidebands and carrier equally. carrier only. sidebands only.

What is lapse rate?. Density changes with altitude. Temperature changes with altitude. Pressure changes with altitude.

Radio signals chance of penetration of ionosphere. is not affected by frequency. decrease with frequency. increase with the frequency.

Aircraft condition monitoring monitors. and compares the faults on the aircraft with the CMC. with a fault detector and tells master warning computer. certain parameters.

FMC changes movement via. straight to the actuator. flight control computer. A/P actuator.

RMI in ADF mode, the pointer is moved by a. Chinaman. loop voltage. servomotor.

Relative airflow over a helicopter blade. increases at the root. is unaffected by blade position. increases at the tip.

TCAS II is. 100 aircraft per 5 miles square. 24 aircraft per square 5 miles. 10 aircraft per square mile.

What is the difference between transmit and receive pulse frequency?. 63. 1000. 60.

When installing an aerial, added support is needed for the structure. This is achieved by. inner plate. outer plate. webs.

How is temperature compensation achieved in the fluid of a compass?. Press relief valve. Alcohol is used as it does not get effect by temperature. Bellows and diaphragm.

A thermocouple. can be shortened. cannot be shortened. capacitance and inductance cannot be added.

Earths atmosphere is. 3/5 oxygen, 2/5 nitrogen. 4/5 oxygen, 1/5 nitrogen. 1/5 oxygen, 4/5 nitrogen.

With a helicopter with a twin blade same gimbal it is. fully articulating. rigid. semi rigid.

What happens to a helicopter in autorotative flight?. The rotor goes the opposite direction to the normal direction of rotation. The rotor goes in the normal direction of rotation. The cabin goes in the direction of rotation.

How is the output of a constant speed drive fed AC generator controlled?. By a swashplate. No control as the generator is fed via a constant speed drive. Hydraulic feedback to a governor.

capacitance fuel quantity indication test set is connected. in series with capacitance probes. in parallel with capacitance probes. by replacing capacitance probes.

What is aileron droop?. The drop of ailerons with no hydraulics on. One aileron lowered. The leading edge of both ailerons presented to the airflow.

If a QFE is set at an airfield and flown to another airfield at the same level above sea level then. it will probably not need resetting and will read zero. it will display the airfield height above sea level. it will not need resetting and will read zero.

The difference between transient droop and static droop is. a hole in one. overswing. underswing.

What is audio clipping used for in voice communication?. To enable numbers to be heard better. To enable consonants to be heard better. To enable vowels to be heard better.

How is a spoiler interconnected to other flight control systems?. Spoiler to elevator. Spoiler to flap. Spoiler to aileron.

after a roll to the left of a statically unstable helicopter, the helicopter would. remain at the position that it had rolled to. continue to roll further. roll back to the horizontal.

What is the calibration law of a Ratiometer?. Material of the indicator needle. Material of the sensing element. Material of the coil.

What is the minimum candela of an anti-collision beacon?. 20. 50. 100.

What is jitter used for in a DME transmission?. To make an aircraft recognise a DME in a quiet area. To make sure only strong signals are replied to in a dense area. To make an installation recognise it`s own transmission.

A high lift device is used for. landing only. take off only. take off and landing.

What is the major vertical component of an airframe that is a load bearing part of the structure that can be used as walls or partial walls?. Stringer. Bulkhead. Frame.

What would happen to an aircraft at low speed at high angle of attack had an aileron going down?. Have no effect on the stall speed. Increase stall speed. Decrease stall speed.

What is the Speed of an ARINC 429 system. 100 KHz. 2 - 6 GHz. 2.3 - 23 Mhz.

Angle of Attack is the angle between cord line and. horizontal axis. tip path plane. relative air flow.

If cyclic is moved to the right. the rotor blades on the left flap down. the rotor blades on the right flap down. POM shortens on one side and lengthens on another.

ADF is. Theta. Rho-Theta. Rho.

A Boost Gauge reads. above or below ISA atmospheric pressure. absolute pressure. above or below ambient atmospheric pressure.

What is a slot used for?. Increase the speed of the airflow. Increased angle of attack during approach. To reinforce the boundary layer.

What is the aural warning of an aircraft overspeed?. Horn sound. Clacking sound. Bell sound.

Upwash on a helicopter would result in. decrease in speed. decrease in lift. increase in lift without an increase in power.

What would indicate the state of charge of a lead acid battery?. Fluctuations in the terminal voltage. Fluctuations in the SG of the electrolyte. Fluctuations in the level of the electrolyte.

What is the glide slope frequency range?. 329 - 335 Mhz. 108 - 112 Ghz. 108 - 112 Mhz.

Instantaneous Vertical Speed Indicator has instant values of Vertical Speed by. blocking off pitot pressure and by using an accelerometer. using a plunger to correct any lagging of the indicator. blocking off static and by using an accelerometer.

What should be carried out prior to working on or near control surfaces?. Wear ear protection. Pull & tag circuit breakers. Ensure Hydraulics are selected off.

with a control surface tab in the neutral position, what happens when the control surface is moved?. It moves in the opposite direction as the control surface. It moves in the same direction as the control surface. It remains in the neutral position.

What does a piezo electric type vibration sensor detect?. Pressure changes. Velocity. Disturbances.

When using a bonding tester you. use either leads for the testing. use the 60ft lead for testing different points. use the 6ft lead for testing different points.

What is the swash plate on a helicopter used for?. Control of the flap of the rotor blades. Control of the speed of the rotor blades. Control of the pitch of the rotor blades.

What is the entry angle of an MLS installation +/-?. 20. 42. 62.

What is the purpose of the autopilot trim indication?. Control surface position. Trim tab position. The voltage activity in the servo amp.

On an aircraft fitted with a CMC how do you get to the system pages?. Through the Present Leg faults function. Through the Existing faults function. Through the ground test function.

If a series actuator is fitted in the cyclic control circuit of a helicopter what effect will an autopilot input have?. The flight director bars only will move. The cyclic lever will not move. The cyclic lever will move in proportion to the autopilot input.

What does an INS calculate on power up?. Last Known Longitude & Latitude. Last Known Latitude. Last Known Longitude.

What is the output of a localiser NAV receiver?. Either. Polarity sensitive DC. Polarity sensitive AC.

In a series actuator fitted to a helicopter how much authority does it have?. 50%. 100%. 10% approximately.

What is the advancing blade on a helicopter doing?. Increasing in drag. Going to the highest point. Increasing in lift.

What is the diagonal part of the landing gear called?. Shock Absorber. Drag Wire. Drag Strut.

What is the bonding value between secondary structure?. Between 1Megohm and 500,000. 1 ohm. 0.5.

What is the minimum size cable, which is not likely to carry all the current from a primary structure?. No smaller than 18AWG. 0.25inch wide by 26AWG cable. 0.5inch wide by 26AWG cable.

If a bonding lead is found to be broken and a spare is unavailable you must. splice the broken lead. defer the defect until correct spares are available. replace with a self manufactured cable of the same type but larger.

What is the typical aircraft hydraulic system pressure?. 300 psi. 1000 psi. 3000 psi.

If the aircraft is to be rolled to the right where does the pilot feed in this command?. Rudder Pedals. Control Column. Control Wheel.

What are ground spoilers used for?. To slow the aircraft. To assist the aircraft coming to a stop. To dump lift.

On a full time Fly-by-wire system a nose up command causes. the two Ailerons on each wing to move up. all the elevators on each wing to move up. the two elevator surfaces on each side of the stabiliser to move up.

The neutral shift system augments control of the. spoilers. elevator. stabiliser.

If an aircraft moves in yaw what axis is it moving about?. Longitudinal. Lateral. Normal.

What happens to the F/D command bars if the roll gyro fails in a turn?. They Disappear out of view. They return back to neutral when the turn is complete. They stay in the same place as nothing is there to null the input signal.

In what type of Doppler System do altitude holes appear?. FM and Pulse. Pulse. FM.

If an autopilot is fed with radio deviation. it will fly on the heading the aircraft was on. it will fly in circles. it will stand off the centre line by a fixed amount.

What colour are the autoland indication lights next to the pilots instruments with excess deviation?. White. Red. Amber.

On a coupled approach what happens to the aircraft if it looses the localiser signal?. It will fly on the heading the aircraft was on. It will fly in circles. It will fly straight down the original course but will drift.

Flap asymmetry causes the aircraft to. nose down. go one wing down. nose up.

If a stall is approaching, what indication does the pilot get?. EICAS warning. Stick Nudger. Stick Shaker.

At which two points on a gas turbine engine is EPR measured?. Jet pipe and combustion chamber. Combustion chamber and jet pipe. Compressor inlet and jet pipe.

If a control surface that is fitted with a balance tab is moved, what will happen to the tab?. It is moved automatically in the opposite direction as the surface. It is moved automatically in the same direction as the surface. It is moved manually in the opposite direction to the surface.

If an aircraft is entering a turn to the left, what input would the aileron to rudder crossfeed be?. No Rudder. Left Rudder. Right Rudder.

When does the pressure in the standard atmosphere halve?. 5,000ft. 18,000ft. 12,000ft.

An aircraft flying on a heading of 030 receives an ADF signal 030 relative to the aircraft, what is the ADF pointer indicating?. 090. 030. 060.

an RMI in VOR mode, it`s pointer is showing a course of 000. If the course knob is adjusted to 010 what happens to the pointer?. Moves left then hard right. Move right. Move left.

Which is the most important part of preventative maintenance on HIRF installations?. CMC fault indications. Insulation testing. Visual inspections.

A Master Warning is issued when. engine fire & generator trip occurs. cargo smoke & low oil quantity occurs. overspeed & low cabin altitude occurs.

Versine is used in which channel?. Yaw. Roll. Pitch.

for a Vertical Gyro which is moved in pitch, which gimble would be moved to correct the pitch movement?. Normal. Longitudinal. Lateral.

If a fly-by-wire system fails, the rudder. remains in the previous position. controls the aircraft in trim. remains at the neutral position.

Alert Height is when. an alert of the position of the aircraft is made. an alert of the altitude of the aircraft is made. a decision of whether to land is made.

The VHF aerial resistance and transmission line resistance is. 20 ohms and 50 ohms respectively. 20 ohms. 50 ohms.

With a spring balance control system you can. not move the control surface on the ground. move the control surface only by moving the tab. move the control surface on the ground.

A radar response takes 329 micro seconds. How far away is the target?. 40 miles. 25 miles. 12 miles.

What does the Radar contour button do?. Alter the video amplifier. Alter the transmitter power. Alter the beam shape.

How long is the time between the start of the P1 pulse and the P3 pulse ignoring the P2 pulse length?. 17 micro seconds. 8 micro seconds. 21 micro seconds.

What is the primary purpose of a helicopter tail arm?. Provide directional control. Acts to help balance the centre of gravity of the helicopter. Provide a structure for mounting the stabiliser and anti torque rotor.

Forces on a helicopter in a power-on descent are. weight, drag, lift. lift, drag, thrust. lift, drag thrust, weight.

If a helicopter rotor disc is rotating anticlockwise, view from above where would a pitch input be fed into the disc to move the helicopter backwards, 90 degrees to what?. Left of the longitudinal axis. Right of the longitudinal axis. In front of the lateral axis.

Once the G/S has been captured what other pitch modes are available?. All are continuously available. Only when the aircraft is above the glideslope beam. No other pitch modes are available.

When can other autopilot modes can be select once Go-Around has been selected?. Disengage and reengage the AFCS system. When reached a desired altitude. When aircraft has reached 5000ft.

What of the following modes does a autopilot go through in correct sequence?. Rollout, attitude, flare. Attitude, flare, rollout. Flare, attitude, rollout.

On an ILS approach what will cause the aircraft to fly onto the beam?. Course deviation. Radio deviation. Height Deviation.

A helicopter autopilot uses. barometric altitude for both height and altitude hold. barometric altitude for height hold and radio altitude for altitude hold. radio altitude for height hold and barometric altitude for altitude hold.

When will a mode C interrogation be ignored?. If P2 is before P1. When the P2 pulse is antiphase to P1. When the P2 pulse is higher amplitude to P1.

What will happen with a flux valve in a turn?. Stay fixed on magnetic north. Move as the aircraft moves. It will move once the aircraft is established on a new heading.

Magnetic heading errors will be. negative if northerly. negative if easterly. positive if easterly.

To know the valid database on FMS. call up relevant current status. call up relevant page on CDU. perform bite check.

To carry out FMS database update on FMS. insert new data on CDU. insert new EPROM. use database loader.

If one FMS fails in a duel system. FMS display transfers automatically from serviceable computer. FMS CDU on fail side goes blank. system operation will not be affected.

An increase in mach number will cause the. Cof P to move forwards giving less downwash on the tail plane. Cof P to move rearwards giving more downwash on the tail plane. Cof P to move rearwards giving less downwash on the tail plane.

The aileron/rudder signal is demodulated in the rudder channel amplifier. This means it is. DC output whose polarity is related to the phase of AC input. DC. AC.

in parallel rudder system,. The rudder pedals are disconnected. The rudder pedals move in response to rudder movement. the pilot can input on rudder pedals.

If a pointer is not centralised on a trim indicators, it means that. the system is trimmed. the control system is out of trim. the indicator is not serviceable.

Basic monitoring is function of. signal summing. signal comparison. voting.

In series rudder system. yaw damping is only possible signal input. the pilot can input to the system. the pilot cannot input to the system.

High and low signal to voter are. removed. added. average.

Roll out mode occurs. at alert height. before flare. after flare.

During the flair mode the A/T throttle will. select reverse thrust. disconnect autothrottle. retard throttle to idle.

In triplex autoland system failure of one channel will. disconnect the failure channel and continue with a manual approach. disconnect the failure channel and continue autoland approach. disconnect all channels.

During autoland failure of one channel is detected. all channels will disconnect in dual-dual system. all channels will disconnect in dulpex system. all channels will disconnect in triplex system.

Rollout guidance after touch down is by. visual indication and rudder control. visual indication and nosewheel steering. automatic rudder control and nosewheel steering.

Cat-1 autoland DH limits are. below 200 ft but not less than 100 ft. not less than 200 ft. not less than 100 ft.

When GA is initiated?. Auto throttle remains engaged giving correct G/A thrust. Auto throttle remains engaged allowing pilot to control the throttles. Auto throttle disengages at 2000 ft/min rate and wings will level.

The controlling signal in pitch channel in the Flare mode are. integrated pitch and G/S deviation. G/S deviation and radio altitude. integrated pitch and radio altitude.

Cat-2 autoland DH limits are. below 300 feet and not less than 200 ft. below 500 feet but not less than 400 ft. below 200 feet but not less than 100 ft.

The flight director is on a localizer when the radio deviation signal is lost the aircraft would. drift of from the localizer on the same heading. fly parallel to the localizer. continue on flying on the localizer.

The aircraft is due north of a VOR station on a heading of 90o What is a RMI display?. 180o. 90o. 0o.

The rotor disc is. the ground cushion. the rotor head hub. the distance between tip to tip.

A DME is in auto stand by when. the TCAS is transmitting. the DME receives 200 - 300 pulses a second. the ATC transponder is transmitting.

Emergency Electronic equipment is approved by. BCAR A4-8. JAR (OPS) M. Aircraft Maintenance Manual.

GPS Telemetry consists of. 8 bits of preamble and position information. satellite position information. week number and time label.

After a change in pitch of a rotor blade the blade will be at maximum flap at. 0o. 180o. 90o.

The amount of travel of a series actuator is. full control movement. 10% of control movement. 50% of control movement.

After a change in collective pitch the Rotor rpm will rise and fall. This is called. under swing. static droop. transient droop.

Loran C Uses. 100 Khz. 16 KHz. 20 Mhz.

The versine signal is used in the. pitch and roll channel. roll channel only. pitch channel only.

An RMI requires the following inputs: Radio deviation only. Course and radio deviation. Heading and radio deviation.

An O ring in a wave guide is used to. stop moisture entering the wave guide. stop arcing between the wave guide. correct the VSWR.

Mach trim threshold are set by the. manufacture. engineer using aircraft maintenance manual. pilot.

A GPS aerial is polarised. right hand circular. horizontally. vertically.

On a HF radio set the clarifier control is used. an Americanisum for volume. make the audio signal clearer. to adjust the reinserted carrier due to instability in the RX.

The normal axis on a helicopter is. at 90o to the rotor head. at 90o to the C of G. straight down the rotor head.

On aircraft an auto land during auto flare the auto throttle will. reverse thrust. control throttle for a IAS. retard the throttle.

If an FM signal modulated by an audio signal the frequency of the audio would relate to the. rate of frequency change. frequency. amplitude.

In a doppler VOR the 30Hz reference signal is. modulated with a 9960Hz. AM Modulated. FM Modulated.

DSR TK (desired track) means. distance left or right from desired track. a great circle path on surface of earth connecting two way points. the bearing to capture the track.

In helicopter Alt Hold uses a signal from. a rad alt or capsule output depend on height. a rad alt output. the barometric alt capsule.

An auto land system displays Land 2 another failure will make the system. simplex. passive. operational.

The stabiliser is set to high setting when. the flap are moving up or down. the flap are moving up. the flaps are moving down.

Fuel quantity test set consists of. inductance decade. capacitance bridge. resistance decade.

EICAS provides the following. engine warnings and engine parameters. engine parameters and system warnings. engine parameters.

In a flight director system the radio signal outputs from the navigation receiver are. AC. pulsed DC. DC.

The loss of the vertical gyro signal to a flight director system would cause. aircraft to remain in level flight. aircraft to overbank. aircraft to underbank.

The glideslope equipment operates in the. VHF band. UHF band. HF band.

A gyroscope with a vertical spin axis has the roll torque motor located about the gyroscope`s. vertical axis. lateral axis. longitudinal axis.

with a constant torque applied to a gyroscope, the rate of precession will. decrease with a lower rotor speed. decrease with a higher rotor speed. increase with a higher rotor speed.

The instantaneous VSI is designed to. improve the VSI output during acceleration greater than 1g. use an accelerometer to give a rate of climb/descent. overcome the inherent lag by utilising an accelerometer.

An open circuit in the temperature bulb as used in the DC ratiometer would cause. the pointer to read full scale. the pointer to read mid scale. the pointer to read zero.

Stand off errors on localiser approach are washed out by. integrating course error signals. integrating deviation signals. differentiating deviation signals.

Aileron to rudder crossfeed is applied in autopilot systems to. prevents aircraft yawing in the opposite direction to the turn. prevents slip and skid in yaw. assist the aircraft back to datum after disturbance in yaw.

The neutral shift sensor ensures that. after an auto trim, the stabiliser is moved to align with the elevator. after a mach trim, the stabiliser is moved to align with the elevator. after an auto trim, the elevator is moved to align with the stabiliser.

When paralleling two AC generators. they do not need to be in phase. it is important that they are in phase, and can be brought on in either ABC or CBA. it is important that they are in phase, and should be brought on in sequence ABC.

On AC ground power the interlock system is operated by pins. c and d. e and f. a and b.

Wing steady light must be visible through. 180 degrees. 110 degrees. 70 degrees.

When removing the load from a current transformer. leave the terminals open. place a resistor across each terminal. short the terminals.

Distilled or demineralised water would be added to an alkaline battery. when the battery is fully charged. in the charging room only. in the aircraft.

A differential relay in a twin generator system will cause. the generator voltages are nearly equal before they are paralleled. one generator always comes on line before the other. only one generator can supply a bus bar at a time.

The purpose of a force trim release system in an helicopter is to permit the. appropriate cyclic actuator to be over powered. pilot to move the collective to obtain a power change. pilot to move the cyclic stick to obtain desired new attitude without having to maintain the opposing forces of the artificial feel system forces.

How are spoilers normally operated?. Electrical motors. Air pistons. Hydraulic actuator.

With on-board maintenance (OBM) systems, the purpose of central maintenance function (CMF) is to. provides details of defect action. transmits to the CMC. log relevant maintenance data.

Stall warning will be given. at stall. after stall. before stall.

A series actuator in a helicopter autopilot system has. 10% authority. 50% authority. full authority.

A triplex system loses one channel. pilot must make a full manual approach and land. pilot can use auto approach. pilot can continue with autoland.

Glideslope deviation signals are. DC positive going only. AC phase sensitive. DC polarity sensitive.

A yaw damper will apply rudder proportional to. rate of yaw. attitude of aircraft. amount of aircraft disturbance.

In a turn, wing spoilers may be deployed. to assist the up going aileron. in unison with both the up going and down going ailerons. to act as an airbrake, interacting with the ailerons.

When the aircraft nose yaws to the left, the yaw damper will apply corrective rudder to. the left with some aileron assistance. the left. the right.

`Q` feel for the stabiliser requires. pitot and static. static only. pitot only.

On localiser approach the radio deviation signal is lost. aircraft flies heading with increasing drift angle. aircraft flies off centre line on pre-set heading. the aircraft flies in a circle.

The respective band widths for a radar IF amplifier and video amplifier should be for good pulse shape are. wide and wide. narrow and wide. wide and narrow.

The pseudo-random code used by all civilian GPS users is. the c/a code. the p code. the y code.

in MLS, the 12 bit preamble consists of. 7 bits function and 5 bits time reference and carrier. 5 bits time function and carrier and 7 bits function. carrier and 5 bits time reference and 7 bits information.

Fibre glass parts are protected from lightning strikes and dangerous voltages by. earth primary conductors. conductive paint. non conductive paint.

The bearing of a NDB measured by ADF is 060 degrees relative to aircraft heading of 030 degrees. The RMI pointer indicates. 60 degrees. 90 degrees. 30 degrees.

The maximum azimuth coverage by a MLS facility is. +/-60 degrees. +/-40 degrees. +/- 35 degrees.

A CVR is found to be unserviceable. flights must not continue after 72 hours. flights must not continue after four days. flight can continue with serviceable FDR provided they are not combined.

450) Microwave landing systems are modulated with. Manchester code. phase drift keying. FM.

Emergency electronic equipment for the cabin is referred to in. maintenance manual. JAR OPS subpart M. BCARs.

Carbon microphones require. no supply. AC supply. DC supply.

Deviation from the HSI lubber line is known as. true A. real A. apparent A.

Electronic stab trim switches are found on the. behind thrust levers. flight control panel. control column.

on power up, the IRS obtains position. latitude and longitude from previous position. longitude from previous position. latitude from previous position.

Krueger flaps make up part of the. wing lower surface leading edge. wing lower surface trailing edge. wing upper surface leading edge.

Mode 4 of GPWS derives warnings from. approach along localiser with reference to runway threshold. rad alt decrease. rad alt to barometric.

Medium vibration of 4 to 6 times per revolution is experienced on a helicopter. The primary control method is. inspect main rotor head and main drive shaft. design of engine and gearbox supports. inspect loose fixtures and fittings.

GPS sends L1 and L2. What is on L1?. P code only. c/a code and P code. c/a code only.

What is VHF comm range at 9000 feet?. 130 nm. 120 nm. 110 nm.

DME reply pulses are 63MHZ. higher or lower. lower. higher.

Flight director incompatible modes are. VOR and altitude hold. heading and altitude hold. VOR and glideslope.

With a bonding meter. it does not matter which lead goes where. the short lead to the aircraft airframe and long lead to the item. the long lead is attached to the aircraft air frame and short lead to item.

Back beam is captured. by manually selecting the L NAV mode. this automatically trips the L NAV mode. by manually selecting the back beam mode.

in air speed hold mode, a down displacement of the flight director pitch command bar signifies. height decrease. speed decrease. speed increase.

The advancing blade of a helicopter is the one moving. one moving forward into relative airflow. highest blade. one moving in direction of relative air flow.

Fluorescent tubes for the cabin lighting are powered from. high voltage produced by transformer ballast units. 200 volts from ac bus. 115 volts from ac bus.

in a superhet receiver, the advantage of an RF amplifier is. it couples noise factors. it improves signal to noise ratio. it amplifies output stages.

on GPWS, with aircraft below 1700ft. all traffic produces aural alert. systems is disabled. no traffic will be shown.

Mode S pulses. Which are used?. s1,s2,p1,p2. s1,p1,p3,p4. F1,F2,F4,F5.

Radio switches are normally. latched on R/T, latched on I/C. latched on R/T, sprung on I/C. sprung on R/T, latched on I/C.

GPS frequency is. 1525 MHz. 1575 MHz. 1575 GHz.

GPS has. 27 satellites, 3 orbits of 9. 24 satellites, 4 orbits of 6. 24 satellites, 6 orbits of 4.

Audio select panel voice switch. disables DME voice ident. cuts "beeps" from DME signal. allows voice ident of DME.

The crew select DH on. the rad alt display. the DH annunciator panel. the altimeter.

When substituting the radio altimeter antenna cables, you should consider. the diameter of cables. the speed of propagation of rad alt signal. power requirements.

The audio select panel allows the crew to. receive on one channel, transmit on multiple others. transmit on one channel, listen on multiple others. transmit on one channel, listen on one.

The ground run monitor presents information. angle of crosstrack on ground. duration of ground run. of distance to go and ground speed.

A mode C transponder. can be used for TCAS on ILS approach only. cannot be used for TCAS. can be used for TCAS.

Artificial feel is gained by using a. `feel` generator. spring bias unit. hydraulic damper.

Tracking is carried out to_____________the MRB tip path. align. restore. balance.

The rotor cone is formed by. centrifugal force only. centrifugal force and lift. blade alignment.

Mode S transponders transmits a binary code of. 24bits. 64bits. 12bits.

The RAD alt electrical length for an helicopter is. 28ft. 12ft. 16ft.

The best design of a MRB is where the C of P. is insignificant. moves freely along the length of the blade. does not move.

DME transponder transmits on receipt. of a pair of pulses separated by 12 microseconds. of pilot input command request. of any interrogation.

What controls are used in response to PVD display?. Control wheel. PVD control unit. Nose wheel steering or rudder pedals.

on a helicopter, what is vortex ring state?. Tip vortex build-up during hover. Ground vortex interference when hovering close to the ground. Tip vortex interference at high forward speed.

A radar response takes 329 micro seconds how far away is the target?. 40 miles. 25 miles. 12 miles.

If a VOR RMI indicates 000 degrees and the course selected is 000 degrees what will the TO/FROM indicator indicate?. Neither. TO. FROM.

If you carry out a VSWR check of a SSB HF system what should you do with the control switch? Select it to. either USB or LSB. AM. OFF.

What is a versine signal attenuated with?. Decrease in altitude. Increase in altitude. Increase in airspeed.

Why is a wire HF antenna covered in polythene?. To provide lightning protection. To prevent precipitation static. To prevent corrosion.

A spring balance control system you. cannot move the control surface on the ground. can move the control surface only by moving the tab. can move the control surface on the ground.

If a helicopter rotor disc is rotating anticlockwise, viewed from above where would a pitch input be fed into the disc to move the helicopter backwards, 90 degrees to what?. Left of the longitudinal axis. Right of the longitudinal axis. In front of the lateral axis.

When can other autopilot modes be select once Go Around has been selected?. Disengage and reengage the AFCS system. When reached a desired altitude. When aircraft has reached 5000ft.

Which of the following modes does a autopilot go through in correct sequence?. Rollout, attitude, flare. Attitude, flare, rollout. Flare, attitude, rollout.

On an ILS approach what will cause the aircraft to fly onto the beam?. Course deviation. Glideslope deviation. Radio deviation.

An aircraft with autoland is fitted with a CMC. all memory is erased when aircraft lands. records all faults in non-volatile memory. records all faults in volatile memory.

What will happen with a flux valve in a turn?. It stays fixed on magnetic north. It move as the aircraft moves. It moves once the aircraft is established on a new heading.

Helicopter cyclic stick is turned to the right. rotating aerofoil tilts to the right. pitch operating arms lengthen in one direction and shorten in another. rotating aerofoil tilts to the right.

EICAS indicates. engine performance and aircraft status. engine performance only. engine performance and aircraft system malfunctions.

When secondary stops are utilized in control surfaces, they come in contact. at the same time as the primary stops. after the primary stops. before the primary stops.

During testing of ATC altitude function the pressure altimeter is set. prevailing pressure. sea level pressure. 1013.25 mb.

Omega ground stations. series of CW. carrier modulated by three audio tones. transmit pulses of CW.

Back beam scanning in an MLS is at a rate of. 15 degrees per second. 30 degrees per second. 20 degrees per second.

Spring Tabs. provide artificial feel. move in such a way as to help move the control surface. enable the pilot to bring the control surface back to neutral.

Servo tabs. provide artificial feel. move in such a way as to help move the control surface. enable the pilot to bring the control surface back to neutral.

When the bank angle limit is applied to the autopilot , it means. maximum rudder deflection. the max roll angle that can be demanded by the autopilot. the max aileron angle that can be commanded.

Doppler flag comes on when it receives. excess signals. no signal. excessive ground clutter.

Use of a diplexer in a receiver is. to impedance match the aerial and receivers. to amplify the RF signal. to enable signals to be distributed to different receivers.

If the `Q` feel in a powered control system fails. the pilot feels air loads lower than normal. the pilot feels air loads higher than normal. the failed system stops and it remains in this position.

A two bladed helicopter rotor on a central gimbal is called. fully articulated rotor. semi rigid rotor. rigid rotor.

Helicopter derives its lift from. air is pushed downward. rotor acts as a airscrew. the blade of the helicopter creates a low pressure above it.

Index error is. misalignment of compass lubber line. Coefficient P. coefficient B.

In a horizontal gyro the random precession of the inner ring is corrected by. flux valve slaving. mercury switches on the outer ring. mercury switches on the inner ring.

DH is based on. RVR transmitted by ATC. experience of the crew. aircraft characteristics.

in an FDS, the attitude gyro is coupled with the FD computer by means of transformer coupling. The purpose of this arrangement is. to minimise power losses. to protect FD computer in case of attitude gyro failure. to protect the attitude gyro in case of failure of FD computer.

Purpose of the bellcrank is to. adjust friction. reverse direction and transmit motion. transmit motion.

An autopilot computer. is the same sensitivity for VOR and ILS. is more sensitive to VOR than to ILS. is more sensitive to ILS than to VOR.

The cyclic stick in an helicopter is. in the centre. to the right. to the left.

GPS antenna is. circular polarized. horizontally polarized. vertically polarized.

Helicopter blades are. Symmetrical. reverse cambered. highly cambered.

in helicopter autopilots, while operating the actuator, the movement of the cockpit control is prevented by. a lock on the cockpit control. a compressed spring attached to the cockpit control. synchros attached to the control.

What is the authority of series actuator on an helicopters autopilot?. 100%. 50%. 10%.

If two aircraft decide to issue the same RA for a potential conflict, which aircraft changes the decision?. Neither changes the decision. The one with the smaller address. The one with the higher address.

during compass swing, using a datum compass, the error permitted in aligning the aircraft is. 10 degree. 5 degree. 1 degree.

Radiated interference of current carrying cables can be minimized by. Putting the affected cable in a single conduit. Separating the affected and affecting cables. Having filters in power supply lines.

The correction for a positive error for coefficient A in a compass. It may be rotated either direction. is to rotate anticlockwise. is to rotate clockwise.

In a combined pitot-static probe, while carrying out a leak check, which instrument is most likely to be effected by over pressure?. Altimeter. VSI. ASI.

While carrying out a leak check of the altimeter, if the static is leaking, the VSI would. not be affected. indicate decent. indicate climb.

in a dual FMC installation, if one FMC is defective. not be affected as automatic transfer takes place. both CDU blanks. one CDU blanks.

If the static line is disconnected in the cabin, the Mach meter reading would be. not effected. lower mach number. higher mach number.

Main electric trim is controlled by. a wheel on the center pedastal. a switch installed on centre pedestal panel. a switch on control wheel.

In case the airplane is wired for dual installation of the Central Maintenance Computers and only one computer is to be installed. it may be installed either on LH or RH side. it must be installed on RH side. it must be installed on LH side.

Mach trim in some aircraft assists. vertical stability. lateral stability. longitudinal stability.

What is the minimum resistance between all isolated electrostatic conducting parts which may be subjected to appreciable charge and main earth system. 0.5 Megohm or 100,000 ohm/sq.ft. surface area which ever is less. 1 ohm. 0.5 ohm.

for bonding, the two ends of a rubber pipe are joined by. a wire attached by terminal legs at both ends. a corrugated bonding jumper. a thick metallic bonding strip.

If you momentarily short the two spikes of bonding tester. tester would be zero centred. tester reads full scale. tester reads zero.

In a radio altimeter system if you decide to increase the TX cable and RX cable each by 3 inch the total correction factor is. 9 inch. 6 inch. 3 inch.

RVSM, Vertical minimum separation error allowed is. 500 ft. 300 ft. 80 ft.

Mode S has. 36 address bits. 24 address bits. 12 address bits.

If an aircraft is on east of VOR beacon, the reference and variable phases are. Phase quadrature. Opposite phase. In phase.

During take off if an input to auto throttle is fails. Fail light illuminates. Throttle hold is annunciated. Auto throttle disengages.

Flight director command bars indicate. Direction in which the beacon is. Direction in which aircraft is flying. Direction in which aircraft is to be manoeuvred.

When the trailing edge flap is extended. CP move rearward. The CP moves forward but the CG does not change. The CP moves forward and the pitching moment changes to nose up.

in weather radar, short range targets are missed by. Larger frequency. Larger beam width. Larger pulse width.

Range resolution is obtained by. Shorter beam width. Shorter pulse width. High PRF.

As you approach supersonic. thrust is reduced. lift is reduced. total drag is increased.

in modern aircraft, power distribution of Generators are controlled by. SPCU. BPCU. PCDU (power control distribution unit).

What is the error signal used for in a fixed angle approach in LOC coupling?entrifugal force. Heading ,Course error and Deviation. Course error and Deviation. Heading and Deviation.

The compensator in a fuel tank measures. fuel quantity. K value of fuel. specific gravity of fuel.

to transmit position feedback for actuators of roll and pitch control surfaces, in a fly by wire system. Synchros are used. LVDT and RVDT are used for pitch and roll. LVDT is used hence ensuring interchangeability.

During decent with power on in a helicopter. lift, weight and thrust are acting on the helicopter. lift, drag, thrust and weight are acting on the helicopter. lift, drag and thrust are acting on the helicopter.

Align light flashes during alignment. It is indicating progress of alignment. It is attracting operators attention. A fault has occurred and system needs to be turned off fore.

During a left turn. ball is to be maintained in centre turn and slip indicator. right rudder to be used. left rudder to be used.

Drooping of helicopter blades is compensated by. centrifugal force. dragging. flapping.

Zone 500 indicates as per ATA 100. Right wing. Door. Left wing.

Shock stall. occurs at low speeds. occurs at high speeds. is a flap down stall.

The normal axis of a helicopter passes through. a line parallel to rotor axis. through the centre of intersection of longitudinal and lateral axis. the centre of rotor disc.

Acceleration error produces. a false indication of climb. a false indication of right bank. a false indication of left bank.

What is the maximum limit of the artificial horizon?. 85 degrees pitch and 110 degrees in roll. 360 degrees in pitch and roll. 85 degrees in pitch and 360 degrees in roll.

in an Autoland, autothrottle is disengaged. manually after landing. after affixed period of the time after landing. after reverse thrust is applied.

Equivalent airspeed is. calibrated airspeed corrected for compressibility. rectified airspeed corrected for compressibility. indicated airspeed corrected for IE and PE.

When moving the control column. sensor in the AFCS computer produces a signal. sensor located along the control run produces a signal. sensors located under the control column produces a signal.

In the reversed camber horizontal stabilizer as shown. there is an increased tailplane down-force. there is an increases tail plane up-force. the elevator causes tail down movement i.e. increases tail plane down force.

The over-station sensor is activated by. deviation and course error. rate of radio deviation signal. radio deviation signal.

If on an ILS approach, LOC signal is lost. aircraft moves in a circle. aircraft descends in a parallel path to runway. aircraft continues to descent with an accumulating drift.

IDG output voltage. voltage is regulated by IDG. voltage is regulated by GCU. does not require voltage regulation as RPM is constant.

A manual trim wheel, when fully moved in the direction of tail. the down movement authority is effected. the up movement authority is effected. the authority of elevators not effected.

in ACRS, if an upcoming message is received. a chime sounds in the cockpit. a selcall light along with chine comes on. a designated light comes on.

GPS has. 7 satellites in 3 orbits. 4 satellites in 6 orbits. 6 satellites in 4 orbits.

When the captain calls attendant. a high chine and pink light comes on. a low chine and blue light comes on. a high low chine and pink light comes on.

Suppressor line is required for. all L band equipments including TCAS. ATC and DME only. TCAs only.

Differential GPS requires. 4 satellites and 1 ground based transmitters. 4 satellites and 2 ground based transmitters. 3 satellites and two ground based transmitters.

The specific gravity readings of a lead-acid cell taken twice after charging shows substantially lower value. You replace the cell. You top up the cell with distilled water. Cell is defective.

To ensure the compass is serviceable before installation you would carry out. damping and alignment checks. damping and pivot friction check. damping and periodicity checks.

With engine stopped, EPR indicator read slightly above 1. You would adjust the Tx. You would change the Tx as the datum is shifted. This is normal.

Low electrolyte in a nicad battery is caused by. low charge current. high charge current. excessive electrical loading.

Float fuel gauge system is. cannot be adjusted. adjusted when tanks are empty. adjusted when tanks are full.

A vertical structural member forming part or full walls are. frame. longerons. bulkheads.

in a capacitive fuel gauging system an increase in fuel level would. decrease capacitance. increase capacitance. increase capacitive reactance.

When all three leads of a bonding tester are connected together the output reading is. centre scale. full scale deflection. zero.

What is the power supply to cabin flow tubes?. High voltage stepped up. 200v ac. 115v ac.

In a fully fly by wire system if the rudder becomes disconnected. it is centralized by the airflow. its control is maintained by electric trim. it is centralized by a spring.

As the rotor head is tilted to travel forward what happens to the reward travelling blades pitch angle?. No change. Increases. Decreases.

A CSD is monitored for. high temp and high oil pressure. high temp and low oil pressure. low temp and high oil pressure.

During flare mode autothrottle will. select reverse thrust. retard throttles to idle. disconnect autothrottle.

The doppler VOR beacon reference signal. frequency modulates the sub carrier frequency. amplitude modulates the sub carrier frequency. amplitude modulates the carrier frequency.

The loss of the vertical gyro signal to the flight director system would cause. aircraft to remain in level flight. aircraft to overbank. aircraft to underbank.

Temperature compensation is required on an altimeter because of. non linear pressure/height relationship. capsule shape. capsule elasticity.

The applied pressure to an ASI varies with the. cube root of the speed. square root of the speed. square of the speed.

How many bits make up the mode "S" address. 12. 24. 36.

GPWS mode 1 is excessive. rate of ascent. rate of descent. terrain closure.

Magnetic variation is the difference in angle between. the compass north and magnetic north. magnetic heading and aircraft heading. true north and magnetic north.

A fuel flow system can be adjusted for. minimum flow rate. cannot be adjusted. maximum flow rate.

A unit with two springs and a mass pick off is. a tachogenerator. a gyroscope. an accelerometer.

The units of vibration are measured in. relative amplitude. phons. decibels.

When the VOR ref and Vari phase are in phase quadrature, the aircraft is at the. 275 degree radial. 090 degree radial. 180 degree radial.

When an aircraft is at a height of 9500ft and the QNH is 500 ft what is the distance that VHF Com cover?. 140 nm. 120 nm. 100 nm.

Emergency electronic equipment requirement will be found in. JAR OPS. CAAIPs. Maintenance Manual.

When working on a hydraulic operated flight control it is sensible to. remove/disconnect electrical power. pull the appropriate CB. remove/disconnect hydraulic power.

The electrical A/H has a movement of. 360 in roll and 85 in pitch. 360 in roll and 110 in pitch. 85 degree in pitch and roll.

In a modern aircraft a BITE is carried out. only in the air. continuously when the systems are working. on the ground only.

The international emergency frequency used in VHF Comms is. 118.00. 121.5. 131.55.

A rain fall of 5mm/hr is indicated in the WXR by a. red colour. yellow colour. green colour.

An autopilot interlock circuit is to. both a & b. disconnect the system if a fault appears. prevent the system engagement if a fault exists.

Loss of an electrolyte in a battery is due to. excessive charging voltage. excessive charging current. insufficient charging current.

FADEC system gets its power supply from. emergency Batt bus. channel A and B from separate windings of a dedicated Generator. channel A and B from the same windings of a dedicated Generator.

An aircraft will capture the auto land system at. 3500 ft. 1500 ft. 2500 ft.

Stall warning will be given at speeds. at the actual stall speed. that are lower than stall speed. that are higher than stall speed.

when a helicopter lands how does the pilot signal to the ground staff that it is safe to approach the aircraft?. Flashing the landing light. Turning off the anti-collision lights. Turning on and off the NAV lights.

Runway turn of lights have a beam width of. 50 degree. 110 degree. 10 degree.

Circulating currents is caused by an unbalanced. AC & DC generators. AC generators. DC generators.

A device used do dump lift from an aircraft is the. leading edge flaps. trailing edge flaps. spoiler.

The quadrantal error in ADF is maximum at a heading of. 090. 045. 000.

When an aircraft is aligned for a compass swing check to be carried out it will be aligned with an error of plus or minus. 5 degree. 3 degree. 1 degree.

TCAS transmits and receives on a frequency of. 1090 MHz. 1090mhz and 1030mhz respectively. 1030 MHz and 1090mhz respectively.

If a drain trap in a pitot static system is removed but nothing was found. a leak test is never required. a leak test must be carried out even if nothing found. no leak test is required unless the drain trap contains water.

When downgrading an Autoland system what needs to be done?. Crew retraining. An entry in the log book and cockpit placarding. Placards in the cockpit.

Alert Height is when. an alert of the ground proximity is made. an alert of the altitude of the aircraft is made. a decision of whether to land is made.

The Ground Proximity Warning Computer in mode 4 would use which inputs to issue a warning?. A low range altimeter and GPS. A low range altimeter and configuration of aircraft. A low range altimeter and rate of change of low range altimeter.

A poor oscillator in a receiver would cause. poor volume output. poor audio output. poor channel selectivity.

With a trailing edge flap being lowered, due to rising gusts what will happen to the angle of attack?. Stay the same. Tend to decrease. Tend to increase.

TAS uses which inputs. Mach and Temp. Pitot and Static, Mach and Temperature. Pitot and Static.

Other than spoilers, where are speed brakes located?. Either side of the Fuselage. Under the Fuselage. On the wing.

The VHF aerial resistance and transmission line resistance is. 20 and 50 ohms respectively. 20 ohms. 50 ohms.

A Glass Reinforced Plastic surface on an aircraft, to reduce the risk of high potential differences would be. bonded to the primary structure. painted in a non-conductive paint. painted in a conductive paint.

If a fault is detected during an autoland approach the system will totally disconnect if it is a. Simplex system. Duplex system. Triplex system.

an RMI in VOR mode, it`s Pointer is showing a course of 000, if the course knob is adjusted to 010 what happens to the pointer?. Moves left then hard right. Move right. Move left.

What should be done to a transformer secondary connections which are open circuit?. Leave the terminals open circuit. Put a set resistance across the terminals. Short the terminals together.

Sparking in a generator would be caused by. brushes on the Magnetic Neutral Axis. bedding of brushes. low spring tension.

In the ATA zoning where is section 100 in on an aircraft. at the rear of the fuselage behind the bulkhead. at the lower section of the cabin up to the pressure bulkhead. in the undercarriage bay including the doors.

The total static resistance along the length of an aircraft is. 1M - 100,000 ohms. 1 ohms. 50 milliohms.

A Master Warning is issued when. engine fire and generator trip occurs. cargo smoke and a low oil quantity occurs. overspeed and low cabin altitude occurs.

With airspeed hold engaged whilst flying with Flight Director engaged, a down command means your speed has. is the same. decreased. increased.

for a vertical Gyro which is moved in pitch, which gimble would be moved to correct the pitch movement?. Normal. Lateral. Longitudinal.

What controls are used in response to the PVD displays?. Nosewheel steering or rudder pedals. Throttles. Ailerons.

The ground run monitor (GRM) presents. take off speed and distance to go. ground speed and distance to go. distance to go.

What is added to the flare computation at touchdown?. No signal. Nose up bias. Nose down bias.

CAT-3b allows. approach land and runway guidance with taxing visibility in the order of 50 meters. approach land and RVR in the order of 50 meters. approach land and runway guidance with zero DH and RVR.

The definition of fail operational is the ability of a system to. disconnect but leave the aircraft out of trim. continue to control after any first fault. disconnect and leave the aircraft in trim.

What is the controlling factor in the automatic flare mode?. Glideslope signal. Radio altimeter. Decision height.

The two parameters used for category classification are. decision height and runway visual range. localiser and glideslope. radio height/runway visual range.

A triplex system loses one channel, the system becomes a. dual-dual system. duplex system. simplex system.

A fail passive system in the event of failure will. ensure the aircraft can still land automatically. produce no significant out of trim condition. produce a significant out of trim condition.

The flare manoeuvre may be controlled by signals from. the localiser receiver. the glide slope receiver. radio altimeter.

A triplex system looses one channel, the system is now,. fail redundant. fail operational. fail passive.

Automatic steering of the aircraft after touch down is affected by. the airfield marker beacon. the runway localiser. the area navigation system.

An autopilot with two separate power supplies is. fail redundant. fail operational. fail passive.

on touchdown, auto pilot. disconnects after a short time. drives the throttles forward. remains engaged ready for G/A.

When will the decision height aural warning sound. at D.H. before D.H. after D.H.

During an automatic landing , the aircraft descent rate is sensed by. vertical accelerometers. radio altimeters. pitch rate gyros.

The effective gain of the glide path receiver. is decreased as the aircraft descends. remains constant as the aircraft descends. is increased as the aircraft descends.

Purpose of an autoland decrabbing manoeuvre is to. point the aircraft down the runway at touch down. assist with glide slope tracking. assist with localiser tracking.

An autoland failure monitoring system must ensure that. the aircraft will continue its automatic landing in the event of signal failure. the automatic pilot will automatically cause the aircraft to overshoot if any failure is detected. the automatic pilot will automatically disengage whenever any failure is detected.

The order of autoland approach is. GS, LOC, ATT HOLD, FLARE. LOC, GS, FLARE, ATT HOLD. LOC, GS, ATT HOLD, FLARE.

V NAV can be selected. only if A/T selected. only if A/P and F/D selected. alone.

If during autoland the LOC signal is lost at 400 ft in final approach. go-around is initiated. autoland is continued. system degrade to CAT II.

The following modes may be retained when overshoot has been initiated after the selection of autoland. IAS and steering or heading. IAS and glide slope. ILS localiser an IAS.

If go-around has been initiated after autoland has been selected, the aeroplane will. increase speed and rotate nose up. rotate nose up. increase speed.

Overshoot or go-around mode can be initiated. at any time. at any time after autoland has been engaged. only when the autopilot is engaged.

The overshoot or go around mode is initiated. by pushing the throttles forward to maximum. by a selector on the throttle control panel. automatically.

The aeroplanes autopilot is programmed to leave the glide slope at. start of flare phase. the decrab phase. 300 ft.

For an aeroplane to be certified for automatic landing an autothrottle system is. dependent upon the operation of the aeroplane at slow speed. mandatory. a matter of choice for the operator.

Before an aeroplane is able to make an automatic landing the. ILS system must be working. ground radio aids must be at CAT III. ground radio aids must be at least CAT II.

The average risk of autoland should not contribute a rate of fatal accidents per landing greater than. 1 x 10-8. 1 x 10-6. 1 x 10-7.

The facility performance ILS intersect height is the point. where the aeroplanes first receives both the localiser and glide path signals. the localiser and glide path signals cross each other. where the aeroplane receives the first glide path signal.

A category 11 facility performance ILS has an intercept height of. 0 m. 60 m. 15 m.

The ICAO weather category 3A is. operation down to and along the surface of the runway with RVR of 200m. operation down to 60 m and 800 m. operation down to and along the surface of the runway without external reference.

The wheel height at which the approach path has been visually assessed as satisfactory to continue the approach to a landing is know as the. alert height. intercept height. decision height.

Which is the correct sequence for an autoland?. Localiser capture, glideslope capture, flare and attitude hold. Localiser capture, glideslope capture, attitude hold and flare. Glideslope capture, altitude hold and flare.

A FADEC system does not have the following system?. Automatic control of engine fire extinguishers. Control of thrust reverser operation. An automatic starting capability.

A full authority Digital Engine Control System (FADEC) consists of. electronic engine control unit and throttle position transmitter. electronic engine control unit and all its sensors. electronic engine control unit only.

When can the FMS be engaged with the autothrottle. only after take off. With either the Flight Director or the Digital Control System (DFCS) engaged. only with the Flight Director selected.

The stall margin is controlled by. speed bug cursor. angle of attack and flap position. EPR limits.

An aircraft in climb maintains the same IAS. What is it`s true airspeed?. The same as its IAS. Lower than its IAS. Higher than its IAS.

What type of memory do CMCs have?. Hard. Non-volatile. Volatile.

What is the purpose of the tail cone in helicopters?. To provide vibration damping to the tail rotor. To hold the stabilizers and tail rotor. To provide a balance for CofG.

in a CMC aircraft, flight deck indications and warnings are managed and provided by. the engine indicatig and crew alert system (EICAS). the electronic interface units (EIU). the central warning computer (CWC).

in a fly by wire system, pitch and roll control positions are known by using. RVDTs for roll and pitch control surfaces. LVDTs for roll and pitch control surfaces. LVDTs for roll control surfaces and RVDTs for pitch control surfaces.

The electrolyte in a nicad battery can be checked by checking. any single cell as all the others will be the same. only the end cell as all the others will be the same. one cell at a time until all cells are completed.

In a RVSM system what is the tolerance level of separation i.e.. + or - feet. 80ft. 160ft. 400ft.

An elevator tab moves down. to counteract for the aircraft flying tail heavy. to make the nose go down. to counteract for the aircraft flying nose heavy.

Weather radar domes are protected from lightning strikes by. special conducting or non-conducting grease. bonding strips. the use of special conductive paint.

The polythene coating on a HF antenna wire is provided. to prevent the wire from chafing. to prevent the wire from corroding. to prevent precipitation static build up.

What must be taken into account when measuring the SG or relative density of a lead acid battery?. The ambient humidity. The ambient pressure. The temperature.

When changing the brushes on a DC generator the brushes must be bedded first, this can be done. at the manufacturers only. the generator taken off the aircraft and bedding done on the bench. with the generator fitted to the aircraft.

The tail nav light. What angle of divergence should it have?. 140 degrees. 120 degrees. 180 degrees.

If a section of the emergency floor proximity lights are inoperative. the aircraft is allowed to fly back to base where the defect can be fixed. the aircraft can fly but the section with the problem is not used/ shut off. the aircraft cannot fly i.e. grounded until the defect is fixed.

Where does it state what emergency equipment and what levels of emergency equipment should be carried on an aircraft. JAR OPS (M). Maintenance Manual. BCAR section A4-8 or A8-4.

In a vibrator type voltage regulator. in series with the voltage coil. parallel with the field. the resistor is in series with the field.

To improve the image or picture when using the WRX (weather radar receiver). use longer bursts. use shorter bursts. scan at a lower rate.

What is the impedance of VOR or HF aerial cables?. 50 ohms. 25 ohms. 75 ohms and 25 ohms.

A GCR will trip if what is detected?. Over current and over frequency. Over frequency and under current. Under frequency and over frequency.

A yaw damper system operates on. low range frequencies. all yaw frequencies. only mid range frequencies.

Co-ordinated autopilot turns are achieved by. aileron to elevator crossfeed. aileron to rudder crossfeed. yaw rate gyro signals.

On selection of the Turbulence Mode. the gain is reduced to prevent stresses to the airframe. the gain remains the same but signals are phase advanced. the gain is doubled to reduce oscillation.

To know the valid data base on the FMS. call up the relevant page on the CDU. call up the relevant current status. perform a BITE check.

The GA mode is usually initiated by. pressing a button on thrust levers. making a selection on the mode control panel. pressing a button on the control wheel.

In the FMS vertical navigation (V NAV) climb mode the throttles are used for. correction minor speed deviations. controlling to a maximum thrust. maintaining a computed EPR.

Synchronisation circuits in autopilots ensure. that the aircraft will always be returned to straight and level flight when the autopilot is engaged. that the autopilot control circuits are at zero demand conditions engagement. that the trim indicators will read zero prior to engagement.

Automatic trim is used to. allow full authority to be regained by the aileron. maintain level flight. prevents standing loads on the elevator.

An over station sensor (OSS) is triggered by. rate of change of radio deviation. rate of change of course. measured radio deviation.

VOR capture can be determined by. a predetermined level of the VOR deviation signal away from the selected radial. is computed from the vectorial summation of the course error and radio deviation signals. a predetermined level of the course error signal away from the selected radial.

Versine is generated by. synchros resolvers. control synchro transformers. torque receiver synchros.

The Airworthiness requirements for the autopilot / autoland system are laid down in. CAIPs. BCARs. JAR AWO.

On the approach the autopilot loses the LOC signal; the aircraft would. fly parallel to the beam. increase its drift angle. fly a circle.

To carry out an autopilot check first. switch on NAV receivers. switch off all power. ensure all control surfaces are unobstructed.

Which modes are incompatible. HDG + V/S HOLD. G/S + ALTITUDE HOLD. VOR + ALTITUDE HOLD.

With autothrottle selected in the SPEED MODE compatible autopilot modes are. V/S and ALT ARM. IAS HOLD and ALT ARM. VOR ARM and HDG HOLD.

Stand off errors on localiser approach are washed out by. integrating deviation signal. integrating course error. differentiating deviation signal.

in a triplex system, the detection of a failure of one simplex system will disconnect. the failed system and continue with a manual approach. all channels. the failed system and carry on with an autoland.

The purpose of a yaw damper is to. produce a co-ordinated turn. block the Dutch roll frequency. assist the aerodynamic response.

A category 3B aircraft using fail operational automatic landing equipment which fail operational control and roll out guidance will have. a decision height depending upon the RVR. no decision height. a decision height of about 50 feet.

Runway visual range in (RVR) is obtained by. one set of instruments the threshold of the runway. three sets of instruments at the side of the runway. information obtained the local Meteorological Office.

The International Civil Aviation Organisation weather category 3A is. operation down to and along the surface of the runway with RVR of 200 meters. operation down to sixty meters and RVR of 800 meters. operation down to and along the surface of the runway without external reference.

The wheel height at which the approach path has been visually assessed as satisfactory to continue the approach to a landing is known as the. alert height. intercept height. decision height.

Overshoot or go-around mode can be initiated. at any time. after glideslope capture. only when autopilot is engaged.

An automatic throttle, engaged in the EPR mode, will control. the engine throttles to maintain a constant engine power setting. the engine throttles to maintain a constant acceleration rate. the aircraft altitude to maintain constant engine input pressure.

the aircraft decrabbing signal, used during autoland, originates from. heading errors. localiser deviation errors. roll errors.

during an automatic landing, the aircraft descent rate is sensed by. vertical accelerometers. radio altimeters. pitch rate gyros.

What is the `Q` code for runway heading?. QDR. QDM. QDH.

A full operational autopilot system will ensure that. the aircraft will continue its automatic landing in the event of a single failure. the automatic pilot will automatically cause the aircraft to overshoot if any failure is detected. the automatic pilot will automatically disengage whenever any failure is detected.

in MLS, what is the beam angle away from runway. 10 degrees. 15 degrees. 20 degrees.

What happens when battery master is switched off in flight?. Electrical systems shut down. No effect. Battery disconnected from charge circuit.

If on a lead-acid battery, several cell checks of SG read consistently low. Battery needs. recharging. replacing. topping up with distilled water.

How many satellites required for GNS?. 6 90o apart. 8. 4.

When OAT increases what happens to an helicopter operating ceiling?. No effect. Decrease. Increase.

Relative velocity of rotor. is equal for all blades. increases at retreating blade. increases at fwd travelling blade.

What design factors govern RPM of a helicopter rotor?. Fineness ratio. Engine and gearbox. Weight of blade.

What damps vibrations on a helicopter?. Scissor levers. Swashplate. Pfifer damper.

What effect does the ground have on a helicopter?. Increases thrust. No effect. Increases lift.

Which side of the pilot is the collective?. In-between legs. Right. Left.

Maximum power on a wave guide is governed by the. number of joints and bends. narrowest width. widest width.

Adding 6 foot of cable to TX RX aerials on rad alt would give you. 12 foot error. 6ft error. 3 ft error.

If radar pulse is reduced there is. no effect. reduced relative range. increased relative range.

If an 80 ohm coaxial cable is connected to an 80 ohm dipole aerial, resistance would be. 0 ohm. 160 ohm. 80 ohm.

What frequency increases radar relative range. Radar relative range cannot be increased by frequency change. low. high.

What is power at pulse?. Average power. Pulsed power. Peak power.

Aircraft is North of VOR beacon on a course of 090 RMI pointer points to. 180. 090. 0.

Buffer amp on transmitter is between. local oscillator and demodulator. local oscillator and modulator. modulator and power amp.

Galley and cabin lighting operate on. GND services. AC bus. DC bus.

Satellite transmits updates on every. 2nd orbit. 9th orbit. 13th orbit.

How does a balance tab move?. In the opposite direction proportional to the control surface it is attached to. In the same direction a small amount. In the same direction proportional to the control surface it is attached to.

What does a trim tab do?. Provides finer control movements by the pilot. Allows the C of G to be outside the normal limit. Eases control loading for pilot.

If you add an aerial, to strengthen the airframe you add. an intercostals. external doubler. an internal doubler.

What controls pitch and roll on a delta wing aircraft?. Elevons. Ailerons. Elevators.

On a helicopter what is dragging?. Contact of the blade tips on the ground. Movement of each blade horizontally about their vertical hinge. Movement of each blade vertically about their lateral hinges.

What do ruddervators do?. Control yaw and roll. Control pitch and roll. Control pitch and yaw.

What preventative maintenance can be carried out in case of HIRF?. Shielding of all sensitive equipment. Bonding and insulation tests. Check of aircraft structure.

Pushing the left rudder pedal. yaws the aircraft left but has no effect on the wing. yaws the aircraft left and possibly the left wing will rise. yaws the aircraft left and possibly the right wing will rise.

Lowering of the flaps. increases lift. increases drag. increases drag and lift.

Flaps at landing position. decrease landing speed. decrease take off speed. decrease take off and landing speed.

In a dual FMS, a failure of one computer will result in. a blank display on one CDU. a down grade of the landing category. no effect on the CDU di.

Compass error remaining after all the corrections, which is used for entry on the deviation. 2 degrees. 3 degrees. 5 degrees.

Anti cross-talk network for unwanted signals uses. attenuation first then amplification. amplification first the. no attenuation but amplification.

In audio clipping. vowels are strengthened relative to the remaining signal. vowels are attenuated relative to the remaining signal. there is no change in relative strength of vowels.

For a Vertical Gyro which is moved in pitch, which gimble would be moved to correct the pitch movement?. Lateral. Longitudinal. Normal.

If one FMS fails in a dual system. system operation will not be affected. FMS CDU on fail side goes blank. FMS display transfers automatically from serviceable computer.

After a change in pitch of a rotor blade the blade will be at maximum flap at. 90 o. 180 o. 0 o.

When approaching the speed of s. pressure above the wing the wing in places. pressure above the wing equals the pressure below the wing. pressure above the wing can never exceed the pressure below the wing.

A Mode S transponder makes a Mode A/C only call, what is the length of the P 2 pulse?. 0.8 s. 1.6 s. 2 s.

ATCRBS reply pulses are. 0.8 s wide. 0.45 s wide. 1.45 s wide.

What is the time between the F2 framing pulse and the SPI?. 4.35 ms. 2 ms. 1.45 ms.

Range resolution in a radars. shorter Pulse. longer Pulse. narrower Beam.

What is the time between the ATCRBS reply. 21 s. 20.3 s. 21.7 s.

Rear navigation lights have. steady white light with a viewing angle of 60 degrees. flashing white light with a viweing angle of 60 degrees. steady white light with a viewing angle of 140 degrees.

Runway turn off lights have a viewing angle of. 50 degrees. 110 degrees. 160 degrees.

Using the following: FS 345, RWS 45, where is this located?. 345" back from the nose, 45" from the longitudinal centre line of the right wing. 345" back from the datum line, 45" from the longitudinal centre line of the right wing. 345" back from the nose and 45" along the right wing.

When carrying out an insulation resistance test of a pitot probe you would expect. 1 Megohm when cold. 3 Megohm when hot and when cooled down. 5 Megohm.

Slewing of the INS gimballed platform simulates in-flight attitude changes up to. 360 deg in roll and 85 deg in pitch. 71 deg in pitch and 180 deg in azimuth. 110 deg in pitch and 360 deg in azimuth.

Cyclic shift of the stator connections in a torque synchro results in. output datum advanced 180 deg. data to coincide. output datum advanced 240 deg.

Gimbal lock in a displacement gyro occurs when. spin axis becomes coincident with any of the axis of freedom. gimbal rings are mutually not at right angles to each other. bearing friction causes gimbal system to unbalance.

In a turn co-ordinator the output axis of the rate gyro is. parallel to the longitudinal axis of the aircraft. set at 30 deg to the longitudinal axis. parallel to the lateral axis to make the gyro sensitive to rolling and banking as well as turning.

All fly to information in an EFIS System is displayed in. White. Magenta. Green.

In an EICAS display all scales, normal operating range of pointers and digital readouts a. White. green. Magenta.

The scratch pad in an FMS CDU occupies. 24 character spaces of the bottom line. the last 12 character spaces of the bottom line. first 12 character spaces of the bottom line.

The term oblate spheroid refers to. tilting of the earth about the axis. flattening at the Polar Regions. the network of meridians imagined to cover the earth.

The horizontal angle contained between the true and the magnetic meridian at any place is. inclination. declination. angle of dip.

Thermocouple combination mostly used for exhaust gas temperature indications are. Copper-Constantan. Iron-Constantan. Chromel-Alumel.

Wing loading of an aircraft. varies with dynamic loading due to air currents. is independent of altitude. decreases with density.

Glide slope frequency is. 108.10-119.95. 328.6-335.4. 108.00-118.

ADF operation range is at. MF band. HF band. VHF band.

ADF system sense aerial is. null. null Cardioid. rotating figure of 8.

Outer marker frequency is. 3000 hz. 1300 hz. 400 hz.

Tripping the GCR will. trip the GCB. de-excite the generator. both (a) and (b).

In a synchronous motor the rotor is. excited by DC. excited by AC. self excited.

the difference between synchronous speed and rotor speed is called. differential speed. loss. slip.

A squirrel cage rotor will be found in. an induction motor. a synchronous motor. a hysteresis motor.

Airspeeds above the speed of sound, but not exceeding 4 times the speed of sound are. hypersonic. supersonic. hyposonic.

What is a fairlead?. A guide for control cables running through bulkheads etc. A guard to prevent control cables coming off pulleys. An extension to a control cable.

FMC provides data envelope for. ATC. TCAS. GPWS.

In a capacitive fuel contents system changes in temperature are compensated by. placing a capacitor in parallel with the tank unit capacitance. adjustment of a potentiometer. placing a resistor in series with the tank unit capacitance.

In an EICAS system, operation of the cancel switch. removes all messages from the display. removes caution and advisory messages. removes advisory messages.

The true airspeed output from a CADC will be determined by information fed from. The Pitot and Static sensors. The Mach unit. The Mach unit and Temperature Sensor.

The alignment position of an IR Mode Selector unit enables. the accelerometers to correct the axes. sets the start co- ordinates. Gyro run up, levelling, azimuth determination.

Pin Programming is allowed. under CAA Rules. to provide reference to FMS computer as to which side of datum it is fitted to. to enter aircraft performance data base.

The Janus beam is for. working out acceleration. levelling the aerial. to compensate for attitude changes.

Absolute pressure of 25 psi is. 39.7 PSI. 14 PSI. 10.3 PSI.

JAR OPS states that the time an FDR recording must be kept after accident or incident. 30 days after incident 60 days after accident. 60 days. 30 Days.

Coefficient A correction is carried out. before C after B. after B and after C. before B and after C.

A combined ASI indicates Mach. above 0.15. above 10000 feet. all the time airspeed present.

Compass compensator units have greatest effect when the magnets are. Parallel. 45 degrees. 90 degrees.

Sonar Locator Beacons are a. ICAO Requirement. ANO Requirement. Company Requi.

INS power is provided by. DC normal and DC emerge. AC normal and DC emergency. AC normal and AC emergen y.

Aircraft is 9000 ft. When is it out of VHF range. 100 nm. 120 nm. 140 nm.

CVR is unserviceable. The aircraft cannot fly unless required data is recorded by FDR. The aircraft can fly for 72 hours since unserviceablity. The aircraft can fly for 4 days since unserviceablity.

A semi monocoque structure is one which has. an external load bearing skin with no internal load bearing structure. an external load bearing skin with internal load bearing structure. a tubular internal structure fabric covered.

Which of the following is correct?. feedback = error - demand. error = demand - feedback. demand = feedback - error.

A member designed to take mainly compressive load is called a. tie. beam. strut.

Longitudinal members in a semi-monocoque fuselage supporting the skin between longerons are called. ribs. stringers. frames.

A modern large transport aircraft fuselage would be normally be constructed from. warren truss structure. semi monocoque structure. geodetic structure.

If the common portion of the winding of a autotransformer used to supply a 26 vac light bulb from a 115 vac busbar goes open circuit the light bulb will. flicker. go dim. blow.

MCDUs. are used to transmit dat to ground. enable dialog with cent. store fault data.

The uploading function on a on -board maintenance system enables. data to be taken from on-board maintenance system. the on-board data base to be updated. the on-board maintenance system to be interrogated by the engineer.

If the output of the generator starts to fall, a pulse width modulated field supply will. increase the mark-to -space ratio. decrease the mark-to- space ratio. double the mark-to-space ratio.

In a starter generator which coil is used for starting?. Shunt, series and compensating windings. series compensating windings. Shunt compensating windings.

A gate valve is installed in a vacuum system is to prevent. back pressure due to engine surge. oil entering gyro when shut down. reverse flow due to engine backfire.

Normal vertical minimum separation allowed is. 800 ft. 1000 ft. 2000 ft.

The venturi tubes in a vacuum instrument are measured in. Millibars. Inches of Mercury. PSI.

Before processing an AM USB signal what needs to be done?. Carrier added. Carrier removed. Carrier integrated.

On power up, IRS. obtains latitude from previous position. compares longitude from previous position. obtains both from previous position.

The instrument supplied with pitot and is affected by altitude is a. ASI. VSI. Mach Meter.

Speed mode stall margins are governed by. AOA and flap position. Pitch angle and speed. AOA and speed.

When performing an ADF bearing check, commercial stations. can be used. can be used in addition to ADF nav stations. can not be used as they are the wrong frequency.

A fuel system that corrects fuel SG is calibrated in. Pounds or KGs. Litres. Gallons.

DME interrogation is carried out. 63 kHz above transmitted frequency. 63 kHz below transmitted frequency. 63 kHz above or below transmitted frequency.

In ground mode the FMS uses which of the following for velocity calculations?. IRS. RHO-RHO. RHO-THETA.

Component P relates to. coefficient A. coefficient B. coefficient C.

During take off with autothrottle engaged, the autothrottle sensor fails, THR CLP is annuciated on the mode annunciator panel when. aircraft leaves ground. a pre-determined rad alt setting. V 2, as determined by the autothrottle computer.

Confirmation of the correct operation of an ATC transponder ident function, is verified by. use of a ramp test set. observation of the ATC transponder control head ident light. telephone contact with the receiving ATC cell.

IRS serviceability for in-service drift is ascertained by. 3+3t. CDU fault code interrogation. apparent drift divided by flight time.

In a IRS system the accelerometer is double interrogated for. distance. acceleration. velocity.

In flight mode, the FMS preference of data source is. IRS, RHO-RHO, RHO-THETA. RHO-RHO, IRS, RHO-THETA. RHO-THETA, RHO-RHO, IRS.

In aileron control. the up going aileron moves further than down going aileron. the down going aileron moves further than up going aileron. it is assisted by the rudder.

Janus in doppler radar. Adjusts signal for overwater flight. allows adjustment for antenna pitch. adjusts for lateral and vertical steering.

ATC altitude readout is. series Tx with binary encoding. series Tx with octal encoding. parallel Tx with binary encoding.

If radio deviation is fed only to the autopilot roll channel what will happen?. Aircraft will fly in circles. Aircraft will drift from centreline. Aircraft will fly parallel to centreline.

Attenuation in a co-axial cable. increases with frequency increase. decreases with frequency decrease. is not affected by frequency.

Stab trim goes into high speed mode when. Flaps are extended. Flaps are retracted. cruise altitude is reached.

A standby artificial horizon is a. space gyro. earth gyro. free gyro.

Pitot static lines in helicopters. are made of stainless steel, and must withstand twice normal working pressure. must provide an accurate indication of the flight regime below 20 knots. must provide accurate information over the helicopter certified flight envolope.

What is the main operating principle of MLS?. phase shift between Tx and Rx. time difference between TO and FRO pulse. signal strength (mV) difference between left and right beam.

How does a Rx know whether an ILS or a VOR frequency has been selected?. Manually selected by operator. Logic control circuit in control unit. A different receiver is used.

What is the purpose of the current transformer on a Neutral phase of an AC generator?. Negative phase sequencing. Open phase. Differential protection.

An aircraft is on course on an ILS Localiser. What is the depth of modulation?. zero. 20%. 50%.

What is the term used for the amount of water in the atmosphere?. Relative humidity. Absolute humidity. Dew point.

How is the flight deck informed of an ACARS transmission?. SELCAL. ONSIDE VHF T/R. A double chime.

In a FBW system, a complete failure of the electronic flight control system in pitch. is not possible because of the built-in redundancy for all elements. would require the aircraft to be manually controlled in pitch using pitch trim wheel. would cause the captain`s sidestick controller to take over pitch functions.

Capture of a localiser beam is normally dependent on a change of bank angle command based on. airspeed, deviation and altitude. attitude, distance from transmitter and runway heading. ground speed, intercept angle and distance form beam.

The flight data recorder underwater locator beacon operates at a frequency of thirty seven kilohertz. with an operational time of at least thirty days. and has a maximum detection range of two thousand to four thousand feet. and is able to withstand immersion to twenty thousand metres.

The flight recorder accelerometer used in the DFDR system measures vertical acceleration as one of its parameters to values between. plus four ​ g ​ and minus two ​ g​ with a null output of one point six to plus or minus twenty eight millivolts dc. plus six ​ g ​ and minus three ​ g​ with a null output of one point eight volts plus or minus twenty five millivolts dc. plus eight g ​ to minus four ​ g​ with a null output of two volts plus or minus twenty millivolts.

Panels that are attached to the aircraft by answered questionfasteners are: tertiary structure. secondary structure. primary structure.

During a change to a lower altitude the piston unit in an IVSI (instantaneous vertical speed indicator) will create, for an instant more. more pressure to the capsule only. pressure to both case and capsule. more suction to the capsule only.

Movement of the collective control will. increase the pitch of the tail rotor. tilt the disc and increase engine power. increase the pitch of the main rotor blades.

Gust Load Alleviation Function in a FBW system. may be controlled by the elevators. uses the high speed computer responses to compensate for sudden gusts. is achieved by the weight saving from elimination of cables, feel units and other conventional items.

Active load control on a large transport aircraft`s aileron system is fitted to. increase roll control authority of the autopilot. improve trim control due to lateral centre of gravity changes. improve fatigue life, due to aero elasticity and high lift loads.

When attaching more than one jumper or ground lead terminal to structure with a single fastener. place the smallest terminal nearest the structure, covered by a spacer, with the others, to a maximum of six, stacked in increasing size. install the largest terminal nearest the structure, with the others, to a maximum of four, stacked and fanned in decreasing size. connect the largest terminal nearest the structure with the others, to a total of three, stacked symmetrically in any order.

If earthing jumper leads terminate to a connector strain clamp, the expected resistance value when carrying out a check should be. 0.5 milliohms. 1.5 milliohms. 2.5 milliohms.

An extruded or rolled aluminium sheet channel section that runs normally the length of the fuselage is known as. intercostal. stringer. cleat.

A panel at STN + 88 /WL -12 is located 88 units. rearward of the aircraft datum and 12 units above the water line datum. forward of the aircraft vertical centre and 12 units below the water line datum. rearward of the datum and 12 units below the waterline.

Cantilever construction is structure supported at. each end and in the centre. one end only. each end.

A fuselage construction where the skin carries all of the loads is known as: semi-monocoque. semi-stressed. monocoque.

When the rotor of an ac tacho-generator is stationary, the rotor has. no circulating currents. circulating currents. no magnetic field.

An AC tacho-generator stator has. two windings 180 apart. three windings 120 apart. two windings 90 apart.

A leak in the static line in a pressurised part of an aircraft can cause the mach indication to. rise. decrease. no change.

A control surface which forms a slot when deployed is called. slat. slot. flap.

During helicopter forward flight the retreating blade will tend to. flap up. no change. flap down.

Asymmetric flaps will cause. the aircraft to ascend. one wing to rise. the aircraft to descend.

How many satellites comprise the space segment for GPS?. 4 satellites in six orbits. 6 satellites in four orbits. 8 satellites in three orbits.

ACARS message is transmitted in which word format?. Binary. Hex. Decimal.

What type of system is an ADF?. rho. theta. rho-theta.

Small pins on an AC GPU receptacle. prevent arcing when inserting or removing the connector. use AC as part of an interlock circuit. are used to prevent incorrect orientation.

Mach meter is. not square law compensated. is automatically compensated. is compensated with square law screws and an arm.

Mach meter reads the correct value. above 10,000 feet only. at sea level only. at any altitude.

Battery charging on an aircraft. may produce excessive charging initially, especially if the battery charge is low. will be reasonably stable due to constant voltage charging. will be reasonably stable due to constant current charging.

A vibrating contact voltage regulator. has a resistor in parallel with the two contacts. has a resistor in series with the two contacts. has a resistor in series with the voltage coil.

A fuel system that measures SG will be displayed in. Lbs or kgs. Ltrs or gals. Ltrs or kgs.

When a helicopter rotor disc is tilted forward, what happens to the pitch of the retreating blade?. Increases. Decreases. Remains constant.

Data communication between the aircraft and the operational control centre is possible through. selcal system. ACARS system. satcom system.

Which is not displayed on an attitude director indicator (ADI). glide slope deviation. localizer deviation. VOR lateral deviation.

In an interrogator Mode S addressing format when does the first sync phase reversal occur?. 0.8 seconds after P2. 1.25 seconds after P2. 2.75 seconds after P2.

If a ground station interrogating an aircraft transmits P1, P2 and P6 through the rotating beam antenna and P5 is radiated by omni -directional antenna, which mode is it addressing. Mode A and C only. Mode S only. Mode A&C and S.

Which of the following navigation system is not a hyperbolic navigation system. Loran C. VLF omega. Doppler.

The length of a resonant antenna dipole is. lambda. lambda/2. lambda/4.

A typical emergency locator transmitter (ELT). receives 2 frequencies. transmit 3 frequencies. transmits 2 frequencies.

The pulse repetition frequency (PRF). high for long ranges. low for long ranges. low for short ranges.

Radio altimeter (radar) normally indicates the altitude of. plus-minus 2500feet. to 2500feet pressure altitude. 0 to 2500 feet above the ground level.

GPS consists of 24 orbiting satellites located. in a 10900 miles high orbit. in a 5000 miles high orbit. in a 8800 miles high orbit.

The path of a point which moves such that the difference in distance from two fixed points is called. parabola. circle. hyperbola.

A selcal signal transmits. a pair of tones continuously. four tones continuously. two pair of tones-one pair after the other.

The frequency of 111.1 MHz is used by. ILS localiser. VOR. ILS glideslope.

In VOR the manual phase shift resolver is a. 30 Hz signal. 9960 Hz signal. 1020 Hz signal.

The impedance of an HF aerial is. 50 ohms. 75 ohms. dependent on frequency.

The VHF aeronautical emergency frequency is. 125.5 MHz. 121.5 MHz. 121.0 MHz.

On an RMI the input to the ADF pointer is fed via. a differential synchro. a synchro. a matching unit.

Full scale deflection on a VOR system is. 2 degrees. 5 degrees. 10 degrees.

A VHF comm blade aerial has a length of. a quarter wavelength. a half wavelength. a full wavelength.

Doppler VOR, when received by a conventional VOR receiver. has normal reception but no ident signal. has normal reception with an ident signal. can not be received on CVOR equipment.

At resonance in a series tuned circuit the impedance is. low. high. reactive.

A mode `S` transponder utilises a. linear amplifier. logarithmic amplifier. Darlington pair.

What is the time taken for one radar statute mile?. 10.75 seconds. 12.36 seconds. 11.03 seconds.

What is the main cause of standing waves in waveguide?. Mismatch of impedances. The frequency transmitted is too high. The velocity of propagation is too high.

The code in an altitude reporting system uses. all C pulses together. at least one C pulse. C1 and C4 pulses together.

In a secondary radar system at what frequency does the interrogator transmit on?. 1090MHz. 1030MHz. 1090KHz.

In the OBS the printing report system is activated: Manually. Automatically. Both of the above.

In the downlink 11 format a 0.5 per sec pulse in the first half of the slot represents a logic. a logic one. a logic zero. the start of the preamble.

The uplink 11 format utilises. Differential Phase Shift Keying. Pulse Position Monitoring. Mono-pulse Dual Interrogation.

In a universal all-call transponder interrogation P2 is radiated by the. Omni-directional aerial. Directional aerial. Horizontal dipole.

Group countdown in a transponder receiver changes the. Selectivity. Sensitivity. Fidelity.

T.C.A.S transmits squitter pulses on a frequency of. 1060 MHz. 1030 MHz. 1090MHz.

T.C.A.S considers another aircraft to be on the ground at a difference height between the barometric altimeter and rad/alt of. 200ft. 160ft. 180ft.

In a radio altimeter installation the aerial spacing between aerials must be. 12 feet. 8 feet. 10 feet.

ACARS is used to transmit. in Flight. on the ground. both of the above.

A Class 3 fault reporting failure. may have an operational consequence. does not have an operational consequence but may do if a second failure occurs. has no consequences on aircraft safety.

Audio frequency range is. 20 to 2000 Hz. 20 to 20,000 Hz. 20 to 200,000 Hz.

An engine vibration indicator system uses. AC/DC in the indicator. 2 filters in the indicator. AC/DC in the transmitter.

GCU power derives its power supply from. AC/DC power supplies. generator`s own supply. initially a trickle voltage from the permanent magnet.

Bedding of brushes of a generator in the air. cannot be done. can be done if limits of brush wear are not exceeding 80% depth 50% width. can be done once bedded in on the ground.

GCU is reset. manually. by engine shut down restart. automatically.

turn and slip needle/pointer moves to the left what is the aircraft doing. turning left. rolling left. turning right.

Alpha floor protection to the autothrottle will. withdraw flaps. increase speed. increase angle of attack.

Throttle hold will occur. with weight on wheels. at the beginning of the take-off run. at a predetermined take-off speed.

An autopilot transfer valve. converts hydraulic power to electrical power. converts electrical power to hydraulic power. converts hydraulic power to electrical power and converts electrical power to hydraulic powe.

The autothrottle controls the aircraft. vertically. laterally. both later ally and vertically.

Speed information to the autothrottle is derived from. the CADC. the IRS. the DME.

On replacement of an actuator that incorporates an autopilot actuator, the autopilot must be checked for. correct sense of movement. correct sense and range of movement. correct sense and range of movement and autopilot breakout checks.

On replacement of an autopilot servo motor. position feedback must be checked. elevator and aileron must be checked. torque limiting settings must be checked.

The autopilot prevents adverse yaw by. aileron to rudder cross feed. rudder to aileron cross feed. rudder to pitch cross feed.

The frequency of dutch roll oscillations are. high. medium. low.

A series yaw damper. moves the rudder only. moves ailerons and rudder. moves the rudder and the rudder pedals.

The purpose of a yaw damper is to prevent. loss of height in a turn. adverse yaw. dutch roll.

Mach trim usually operates between. 6.0 mach 7.0 mach. 9.0 mach and 9.99 mach. 7.0 and 8.0 mach.

An automatic disengagement of an autopilot will cause. a red warning light to illuminate. a red warning light to illuminate and an aural warning. an aural warning only.

Mach trimming is initiated by an input signal from. CADC. IRS. Vertical gyro.

Mach trim prevents. the nose dropping in a low speed turn. the nose lifting at high speed. the nose dropping at high speed.

Auto trimming trims the aircraft by. moving the leading edge of the stabiliser. movement of the elevator. movement of either the elevator or the stabiliser.

Automatic trimming starts on the detection of. loss of position feedback. standing load on the elevator. loss of servo input.

An autopilot runaway is prevented by. position feedback. a fuse. torque limiting devise.

An autopilot hardover runaway is caused by. loss of position feedback. loss of servo power supply. loss of clutch supply.

Inner loop servo control of an autopilot will provide. stability and navigation commands. navigation commands only. stability only.

A signal at 120 MHz freq will normally propagate by means of. ground waves. sky waves. space waves.

The length of a resonant antenna dipole is. lambda. lambda/2. lambda/4.

In a vertically polarized electromagnetic wave. the electric field vectors are vertical. the magnetic field vectors are vertical. both electric and magnetic are vertical.

In yagi-array antenna, the signal is fed through a cable to. dipole. parasitic elements. both.