3272-11 sys (1.13)

Selection of the INS Mode Selector Unit (MSU) to ATT REF is made. to feed information to the Captain and 1st Officers ADI displays. when attitude information is lost. when navigation information is lost.

For the INS, the Battery Unit provides. standby power when airborne, switched by weight-off switches in the undercarriage. both when airborne and on the ground. standby power only when on the ground, to maintain the alignment phase.

Control Display Unit (CDU) selection of TKE displays. distance perpendicular from the selected track. difference in degrees that the aircraft track is to the right or left of the desired track. difference in degrees from True North in a clockwise direction from the desired track.

The Earth Rate Compensation for an INU is computed from. the earth's rotational rate (15°/hour) times the sine of the longitude. the earth's rotational rate (15°/hour) times the cosine of the latitude. the earth's rotational rate (15°/hour) times the sine of the latitude.

INS wind speed is calculated from. the vectorial addition of IAS and TAS. the vectorial addition of TAS and GS. the vectorial addition of IAS and GS.

Centripetal error compensation is achieved by. allowing the platform to oscillate at a fixed rate. an additional signal is added to the N/S accelerometer to cancel the centripetal error. the platform is torqued to align the N/S accelerometer along its insensitive axis.

Transport Rate compensation is achieved by. an additional signal added to the N/S accelerometer output depending on heading. allowing the platform to oscillate at a fixed rate. the platform being torqued by a computed torquing signal.

If the battery fails on the ground (INS System). an amber light appears on the MSU and a horn sounds. a red warning light appears on the MSU and a horn sounds. a red light appears on the CDU and a horn sounds.

An IRS alignment. takes 10 minutes and present position must be entered before alignment. takes 10 minutes and present position can be entered any time during the alignment. takes 10 minutes and the previous flight shut down present position is used for the alignment.

For an IRS system to pass the 'Alignment System Performance Test' the. the No. 1 and No.2 must both have the same latitude and longitude present position entered. entered present latitude and longitude must agree with the latitude and longitude at the last power own. latitude entered must be within given limits of the latitude computed by IRU.

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

The localiser deviation signal for the flight director comes from the. flight director computer. VHF comm system. VHF nav system.

The heading error signal used in the heading select mode. is the difference between the desired heading and the actual heading. is the difference between the desired course and the actual course. comes direct from the compass system.

The crab angle of the aircraft during VOR or LOC modes is displayed by the. difference between the course arrow and aircraft heading. difference between the selected heading and aircraft heading. selected course counter.

VOR left-right deviation signals come from the. DME system. VLF nav system. VHF nav set.

Above the glideslope, the ILS glideslope signal modulation is. 90 Hz. 150 Hz. 90 KHZ.

The localiser modulation signal to the left of the localiser centre line, as seen from the localiser transmitter, is. 90 Hz. 90 KHz. 150 Hz.

The correct sense demand generated for a selected heading 180°, when the aircraft heading is 150° is. turn left. straight ahead. turn right.

When an aircraft is flying along the extended centre line of the runway it is in the. 150 Hz modulation sector. 90 Hz modulation sector. equi-signal sector.

The localiser system offers approach guidance to the runway in terms of. the vertical plane. the horizontal plane. distance to touch down.

The glideslope transmitter is located. at the end opposite to the approach end of the runway. adjacent to the touch-down point of the runway. at the approach end of the runway.

The glideslope and localiser frequencies. are fixed and common to all runways therefore frequency selection is not necessary. have to be selected separately. are paired and one frequency selector suffices for both.

The glideslope system offers approach guidance to runways in terms of. distance to touchdown. the vertical plane. the horizontal plane.

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

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

The aircraft equipment determines the bearing of a ground station by comparing. the amplitude of two 30 Hz modulations. the phase of two 30 Hz modulations. the phase of one 30 Hz modulation with that of a 9960 Hz modulation.

The number of different radials provided by a ground station is. infinite. 180 per quadrant, i.e. 720 in 360°. 360.

Which of the following frequencies is allocated to VOR?. 114.3 MHz. 127.2 MHz. 103.9 MHz.

Aerial masts may be damaged by. water. killfrost anti-icing fluid. Skydrol hydraulic fluids.

Most radio aerial masts are. not bonded. bonded. insulated from the fuselage.

When an aircraft is heading due north (magnetic) towards a VOR station the reference and variable signals will be. 270° out of phase. in phase. 180° out of phase.

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

The modulation of the outer marker is. 3000 Hz. 400 Hz. 1300 Hz.

The approximate distance of the middle marker from the runway threshold is. 7 miles. 3 miles. 3500 ft..

Marker information is usually provided to the pilot. aurally. both visually and aurally. visually.

An over station sensor (OSS) detects. the rapid rate of the VOR signal over the cone of confusion. radio deviation signals proportional to distance from a localiser transmitter. radio deviation signals proportional to distance from a VOR transmitter.

Incompatible Flight Director modes are. altitude hold and ILS. VRU and compass. VOR and glidepath.

The VOR system comprises. reference phase signal. variable and reference phase signals. variable phase signal.

The most sensitive system between ILS and VOR is. they both have the same sensitivity. ILS. VOR.

If an aircraft is flying on a heading of 000 away from a VOR station, the TO/FROM indicator would show. to. From. no indication.

How does the flight director computer differentiate between VOR and ILS frequencies?. Frequency discriminator in receiver. Trigger pulse from ground station. Discriminator on control panel.

The glideslope transmitter operates on. the VHF band. frequencies of 108 to 118 MHZ. the UHF band.

The pilots instinctive autopilot disengage button is on the. left of the control column. right of the control column. side of the controls away from the throttles.

If the autopilot automatically disconnects in the autoland mode, the audible warning. switches off after a time interval. is switched off by the instinctive cut-out button. can only be switched off by re-engaging the autopilot.

A category 3B aircraft using fail operational automatic landing equipment will have. a decision height depending on RVR. a decision height of 50ft. no decision height.

For an aircraft to be certified for automatic landing, an autothrottle system is. mandatory. a matter of choice for the operator. dependent on the operation of the aircraft at slow speeds.

With autothrottle engaged, the application of reverse thrust will. drive the throttles to the minimum thrust position. drive the throttles to the reverse thrust position. disconnect the autothrottle.

During ATC transponder operation, side lobe suppression acts to. mute the DME operation during transmit phase. mute coms transmission during transponder operation. supply altitude readout.

During operation of a twin HF radio system transceiver. #1 HF system operation is inhibited during #2 operation. both systems can be operated simultaneously. #1 HF system can transmit but not receive.

Which L band frequency is not used by DME for transmitting?. 2210 MHz. 1090 MHz. 4133 MHz.

Function of ADF & VOR and DME in navigation system with reference to aircraft and beacon is;. The first provides distance between aircraft and beacon and latter provides bearing line from aircraft to beacon. the first provides bearing line from aircraft to beacon and latter provides distance between aircraft and beacon. None of above.

Which two frequencies are paired?. Which two frequencies are paired?. Glideslope and localizer. Localizer and DME.

Localizer beam width is the angle where the two edges of beam are apart at the runway threshold by. 7 ft. 700 ft. 70 ft.

What happens if frequency decreases without altering the physical length of aerial?. The aerial becomes inductively capacitive. The aerial becomes capacitively reactive. The aerial becomes inductively reactive.

What happens if frequency increases without altering the physical length of aerial?. The aerial becomes inductively reactive. The aerial becomes capacitively reactive. The aerial becomes inductively capacitive.

Aerials provide optimum output at one particular frequency, when its load is purely. resistive. capacitive. inductive.

The torque pre-set in an autopilot system is. to stop the motor overheating. to give control surface feel. to allow it to be overridden at a certain force.

Most aerials are. not bonded. bonded. made from non-conductive material.

The Middle Marker beacon is what colour?. Amber. White. Blue.

Laser gyros have. no rotating parts. moving parts. a spinning rotor.

Laser gyros are aligned to. magnetic north. true north. aircraft structure.

Triplex autopilot is. fail passive. fail soft. fail operational.

Flight management control system (FMCS) utilises. ILS, VOR, ADF. ILS, DME, ADC,. VOR, ADF, DME.

ACARS is. a navigation system. a satellite communication system. a way of reporting defects to maintenance base in flight.

Where is an ATC transponder mode 'A' selected ON?. The airspeed indicator. The ATC control panel. The altimeter.

How many data bases are required in an FMS system?. 2. 1. 3 (one is used for redundancy).

What channel of the autopilot does the glideslope control?. Pitch. Yaw. Roll.

What is secondary radar?. Signal returned from a transponder. A backup radar on an airfield. Reflected radar bounce from an aircraft.

In an autothrottle system, when is EPR or thrust mode used?. Approach. Cruise. Take-off.

What is Mode 1 & 2 of GPWS used for?. Excessive descent rate, unsafe terrain clearance. Excessive descent rate, excessive terrain closure rate. Excessive terrain closure rate, altitude loss after take-off.

For radio communication over a distance of over 250 miles we use. VHF. VLF. HF.

Autopilot, when on approach to landing, how many axis are used?. 3. 2. 1.

A lead-acid battery is considered to be fully charged when the. cells begin to gas freely. SG reaches 1.180. SG and voltage remain constant for specified period.

A diode across a contactor. reduces contact bounce. enables it to be connected to either an AC or DC circuit. reduces contact arcing.

The preferred method of battery charging a Ni-Cad battery is constant. voltage. power. current.

A battery in situ on an aircraft. charges at a fairly constant rate because generator voltage remains constant. may charged at an excessive rate if initial battery voltage is low. may charge slowly if initial battery voltage is low.

To parallel an alternating current generator with one or more other generators, phase A must be. 90 degrees out-of-phase and ABC. in-phase with other generators and CBA only. in-phase with other generators and ABC.

On an unparalleled twin generator alternating current system, the phase of the second generator to be brought on line. must be in-phase prior to paralleling. is unimportant. is important if the first generator fails.

The power supply for aircraft is. 28VDC, 115VAC, 400Hz. 28VDC, 220VAC, 400Hz. 28VDC, 115VAC, 200Hz.

On a Direct Current circuit, Current Limiters. prevent overheating by limiting current to load. limit generator field excitation. limit current to field circuit.

On a direct current circuit, current limiters. allow excessive current to the load circuit. prevent excessive current to the load circuit. prevent excessive current to the field circuit.

When a current transformer is disconnected from its load. a resistor should be placed across the terminals. the terminals should be shorted together. the terminals should be left disconnected.

Ram Air Turbines have variable fan blades to. maintain a constant speed. provide a constant flow rate. produce maximun hydraulic pressure required by the system.

On a direct current twin generator system, the paralleling relay contacts close when the oncoming generators voltage is. below bus voltage. the same as bus voltage. above bus voltage.

Where is a commutator found?. An AC generator. A DC generator. A DC alternator.

Calculate the battery terminal voltage of a NiCad battery with 15 cells. 18 V. 15 V. 30 V.

Reactive electrical loads are adjusted by. adjustment of generator speed. adjustment of the regulator output. varying the frequency circuit.

IDG oil is used for. internal hydraulic functions only. cooling, lubrication and internal hydraulic functions. cooling and lubrication only.

A silver oxide cell has a voltage of. 1.55 V. 1.8 V. 1.2 V.

Lithium cells. are very efficient. have an unlimited re-charge cycle capacity. are not rechargeable.