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KCAA Flight Engineer practice questions

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Question 1Aircraft systems, powerplants and airworthiness

On a turbojet engine, what is the primary function of the diffuser section of the compressor inlet?

  1. To cool the compressor bleed air used for cabin pressurization
  2. To convert high-velocity inlet air into a lower-velocity, higher-pressure flow Correct answer.
  3. To increase the velocity of the air entering the first compressor stage
  4. To mix fuel with incoming air before compression

Explanation

The diffuser slows the incoming airstream and converts kinetic energy into static pressure before the air reaches the first compressor stage. This improves compressor efficiency and reduces shock losses at the face of the first stage. Fuel mixing occurs in the combustion chamber, not at the inlet diffuser.

Question 2Aircraft systems, powerplants and airworthiness

In a gas turbine engine, the combustion chamber must accomplish which of the following?

  1. Add heat energy to the air with minimal pressure loss Correct answer.
  2. Raise gas pressure while lowering temperature
  3. Separate the compressor from the turbine mechanically
  4. Reduce the mass flow before the turbine

Explanation

The combustion chamber adds heat energy to the compressed air while keeping pressure losses as low as practical, so the turbine can extract useful work. Pressure does drop slightly across the burner, but the essential purpose is heat addition. The mass flow continues essentially unchanged into the turbine.

Question 3Aircraft systems, powerplants and airworthiness

Which statement correctly describes the function of the turbine section in a turbojet engine?

  1. It regulates fuel flow to the combustion chamber
  2. It converts exhaust velocity directly into thrust at the nozzle
  3. It compresses air before combustion
  4. It extracts energy from the hot gases to drive the compressor and accessories Correct answer.

Explanation

The turbine expands the hot high-pressure gases and extracts energy to drive the compressor and engine accessories. The remaining energy is left in the exhaust for thrust production at the nozzle. Compression and fuel metering are functions of the compressor and fuel control unit respectively.

Question 4Aircraft systems, powerplants and airworthiness

What is the purpose of the igniter plugs in a turbine engine combustion section?

  1. To initiate combustion during start and, on some installations, during adverse weather Correct answer.
  2. To provide continuous ignition throughout the flight
  3. To distribute fuel evenly around the burner
  4. To measure combustion chamber temperature

Explanation

Igniters start combustion during engine start and, in some installations, provide relight capability in heavy rain or icing conditions. Once combustion is self-sustaining, ignition is normally switched off. They do not meter fuel or sense temperature.

Question 5Aircraft systems, powerplants and airworthiness

An aircraft hydraulic system is described as having a 'closed-center' selector valve. What does this mean when the valve is in neutral?

  1. Both the pressure and return ports are blocked, trapping fluid in the actuator lines Correct answer.
  2. The pressure and return ports are connected directly to each other
  3. The pressure port is blocked and the return port is open to the actuator
  4. The actuator is free to move under external load

Explanation

In a closed-center system the pressure and return ports are blocked at neutral, so hydraulic fluid is trapped in the actuator lines and the actuator holds its position. Pressure is maintained in the supply line and relieved by the pump's pressure regulator. This differs from an open-center system where flow is bypassed to return.

Question 6Aircraft systems, powerplants and airworthiness

Why is a hydraulic system reservoir often pressurized?

  1. To reduce the pressure required to actuate the landing gear
  2. To cool the hydraulic fluid during heavy demand
  3. To increase the viscosity of the fluid
  4. To prevent pump cavitation at high altitude and to keep fluid in the lines Correct answer.

Explanation

Pressurizing the reservoir raises the fluid's pressure above the low ambient pressure encountered at altitude, which suppresses pump cavitation and helps prevent fluid from draining out of the lines. It does not change viscosity appreciably or cool the fluid. System operating pressure is set by the pump and relief valves.

Question 7Aircraft systems, powerplants and airworthiness

In a pneumatic (bleed air) system, what is the purpose of the pressure regulator valve?

  1. To shut off bleed air only when the engine fails
  2. To limit bleed-air pressure delivered to the manifold to a safe, usable value Correct answer.
  3. To convert bleed air into hydraulic pressure
  4. To cool the bleed air before it reaches the pack

Explanation

The pressure regulator valve modulates the engine bleed down to a controlled manifold pressure so downstream components and the airframe are protected from excessive temperature and pressure. It does not perform cooling or hydraulic conversion. Shutoff is handled by a separate bleed valve.

Question 8Aircraft systems, powerplants and airworthiness

What is the primary function of a constant-speed drive (CSD) on an engine-driven AC generator?

  1. To convert AC to DC for the aircraft bus
  2. To provide emergency power during engine failure
  3. To maintain a constant generator speed despite varying engine RPM Correct answer.
  4. To regulate generator voltage

Explanation

A CSD uses a hydraulic or mechanical transmission to keep the generator turning at constant speed so the AC frequency remains constant as engine RPM varies. Voltage regulation is a separate function of the generator control unit. Emergency power comes from batteries, APUs, or air-driven generators.

Question 9Aircraft systems, powerplants and airworthiness

Which of the following best describes the function of the air data computer (ADC) in an aircraft?

  1. It controls the fuel flow to each engine
  2. It manages the electrical load on the generator bus
  3. It computes altitude, airspeed, and other air data from pitot and static inputs for display and systems use Correct answer.
  4. It commands the landing gear to retract

Explanation

The ADC derives altitude, airspeed, Mach number, and vertical speed from pitot and static pressure inputs and supplies these to displays and other systems. Fuel control and electrical load management are separate subsystems. Landing gear operation is controlled by the gear control system.

Question 10Aircraft systems, powerplants and airworthiness

During a preflight inspection, you notice a small amount of oil seeping from the drain mast under the engine cowling. What is the most appropriate action?

  1. Increase the oil level to compensate for the loss
  2. Record it, check the oil quantity and the applicable maintenance manual limits, and refer if beyond limits Correct answer.
  3. Immediately shut down and replace the engine
  4. Ignore it because minor seepage is always normal

Explanation

Minor seepage may be acceptable within limits, but the engineer must consult the maintenance manual for allowable leakage and verify oil quantity. Overfilling to compensate can cause foaming or seal damage. Engine removal is not justified without evidence of a defect beyond limits.

Question 11Aircraft systems, powerplants and airworthiness

What does an EGT indication that rises above the start limit during engine start most likely indicate?

  1. An indication that the igniters are not firing
  2. A faulty fuel flow indicator only
  3. A hot start or hung start requiring immediate corrective action Correct answer.
  4. A normal hot start that will self-correct

Explanation

An EGT exceeding the start limit signals a hot start or hung start, which can damage the turbine if not addressed. The correct response is to shut off fuel and continue motoring to clear the combustion section. A hot start does not self-correct and must be managed promptly.

Question 12Aircraft systems, powerplants and airworthiness

A turbine engine experiences a compressor stall. Which of the following is a typical indication?

  1. A constant fuel flow with no change in engine parameters
  2. Loud bangs, fluctuating RPM, and possible flame from the tailpipe Correct answer.
  3. A gradual rise in oil pressure only
  4. A steady decrease in EGT and smooth operation

Explanation

Compressor stall typically produces loud bangs, RPM fluctuations, high EGT, and sometimes flame from the exhaust as airflow separates from the blades. The pilot or engineer must reduce power and restore smooth airflow. Steady or unchanged parameters are not characteristic of a stall.

Question 13Aircraft systems, powerplants and airworthiness

What is the purpose of the fan reverser on a high-bypass turbofan engine?

  1. To redirect fan bypass airflow forward to produce reverse thrust on the ground Correct answer.
  2. To increase forward thrust during takeoff
  3. To cool the engine core after shutdown
  4. To reverse the direction of fan rotation for braking

Explanation

The reverser deploys cascade or blocker doors to turn the fan bypass air forward, producing a rearward-acting force that assists braking on the ground. It does not reverse fan rotation or increase forward thrust. Core cooling is unrelated to reverser operation.

Question 14Aircraft systems, powerplants and airworthiness

An aircraft is certified under a continuing airworthiness program. What is the primary purpose of an airworthiness directive (AD)?

  1. To describe routine servicing intervals only
  2. To mandate corrective action for an unsafe condition found in a type design Correct answer.
  3. To recommend optional improvements to aircraft comfort
  4. To set the purchase price of spare parts

Explanation

An airworthiness directive is a mandatory requirement issued to correct an unsafe condition in a type design, and compliance is required for continued airworthiness. It is not optional and is not limited to routine servicing. Pricing of parts is unrelated to airworthiness regulation.

Question 15Aircraft systems, powerplants and airworthiness

What does a 'minimum equipment list' (MEL) allow an operator to do?

  1. Operate with certain inoperative equipment under specified conditions until repairs are made Correct answer.
  2. Operate without any airworthiness certificate
  3. Defer all maintenance indefinitely
  4. Reduce the aircraft's maximum takeoff weight permanently

Explanation

The MEL, derived from the master minimum equipment list, permits dispatch with specific items inoperative provided defined conditions and repair intervals are met. It does not allow indefinite deferral or removal of the airworthiness certificate. Weight limitations are set by the flight manual, not the MEL.

Question 16Aircraft systems, powerplants and airworthiness

On a multi-engine aircraft, what is the purpose of the firewall shutoff valve in the fuel system?

  1. To stop fuel flow to the engine in the event of a fire Correct answer.
  2. To increase fuel pressure at high altitude
  3. To balance fuel between tanks
  4. To drain water from the fuel tanks

Explanation

The firewall shutoff valve isolates the engine fuel supply so that a fire can be starved of fuel and contained. It is operated by the fire handle or fire switch. Fuel balancing and water drainage are separate functions of the fuel management system.

Question 17Aircraft systems, powerplants and airworthiness

Why must jet fuel be checked for the presence of water and sediment before flight?

  1. To increase the fuel's energy content
  2. To prevent fuel control malfunction and engine flameout from contaminated fuel Correct answer.
  3. To improve the fuel's octane rating
  4. To reduce the freezing point of the fuel

Explanation

Water and sediment can cause fuel control unit malfunction, icing at altitude, or flameout if they reach the engine. Sump drains are used to remove contaminants before flight. Checking for water does not change octane, energy content, or freezing point.

Question 18Aircraft systems, powerplants and airworthiness

What is the purpose of the anti-icing system on a turbine engine inlet?

  1. To prevent ice formation on the inlet lip and guide vanes that could disrupt airflow Correct answer.
  2. To increase the compressor pressure ratio
  3. To cool the inlet air for better density
  4. To reduce engine noise on takeoff

Explanation

Inlet anti-icing uses hot bleed air or electrical heating to keep the inlet lip and front frame free of ice, which could otherwise break loose and damage the engine or distort airflow. It does not cool the air or change the pressure ratio. Noise reduction is a separate design feature.

Question 19Aircraft systems, powerplants and airworthiness

During an engine run, the oil pressure gauge reads zero while the engine is running. What is the most appropriate immediate action?

  1. Ignore the indication if oil temperature is normal
  2. Increase power to raise oil pressure
  3. Shut down the engine and investigate the cause Correct answer.
  4. Continue running to see if pressure recovers

Explanation

Zero oil pressure with the engine running indicates a loss of lubrication that can destroy bearings and the engine within seconds. The engine must be shut down promptly and the cause investigated. Increasing power would worsen the damage.

Question 20Aircraft systems, powerplants and airworthiness

What is the function of the accessory gearbox on a turbine engine?

  1. To compress the air entering the combustion chamber
  2. To provide thrust during takeoff
  3. To drive engine and aircraft accessories such as pumps and generators from the engine shaft Correct answer.
  4. To cool the turbine blades

Explanation

The accessory gearbox takes power from the engine shaft to drive fuel pumps, oil pumps, hydraulic pumps, generators, and starter components. It does not compress air, produce thrust, or cool turbine blades. Its role is to distribute mechanical power to accessories.

Question 21Aircraft systems, powerplants and airworthiness

A pilot reports that the cabin altitude is climbing while the aircraft is at a constant flight level. Which system should the engineer suspect first?

  1. The pressurization system, including outflow valve and controller Correct answer.
  2. The hydraulic system pressure regulator
  3. The fuel crossfeed valve
  4. The landing gear retraction system

Explanation

A climbing cabin altitude at constant flight level points to a pressurization fault, such as an outflow valve stuck open or a controller malfunction. The hydraulic, fuel, and landing gear systems do not control cabin pressure. The engineer should check the outflow valve position and pressurization controller.

Question 22Aircraft systems, powerplants and airworthiness

What is the purpose of the compressor bleed valves (variable stator vanes or bleed bands) on a multi-stage axial compressor?

  1. To cool the turbine section during cruise
  2. To prevent compressor stall at low engine speeds by relieving excess pressure in rear stages Correct answer.
  3. To increase fuel flow to the combustor
  4. To reduce the compressor's rotational speed

Explanation

At low RPM the rear compressor stages may deliver more pressure than the front stages can accept, leading to stall. Bleed valves or variable stator vanes relieve this mismatch and maintain stable airflow. They do not meter fuel or cool the turbine.

Question 23Aircraft systems, powerplants and airworthiness

An aircraft has a 28-volt DC system with a battery and a generator. What is the function of the reverse-current relay?

  1. To increase generator output at high altitude
  2. To reverse the polarity of the generator for starting
  3. To disconnect the battery during engine start only
  4. To prevent the battery from discharging through the generator when generator voltage falls below battery voltage Correct answer.

Explanation

The reverse-current relay opens the generator-to-bus circuit when current flows from the battery back into the generator, which would otherwise discharge the battery and damage the generator. It does not reverse polarity or boost output. Its purpose is to protect the system when generator voltage drops below battery voltage.

Question 24Aircraft systems, powerplants and airworthiness

During a borescope inspection, a turbine blade shows a small nick on the leading edge within the maintenance manual limits. What is the correct disposition?

  1. Blend the blade without reference to the manual
  2. Remove the engine from service immediately
  3. Ignore the finding because it is small
  4. Record the finding and return the engine to service per the manual limits Correct answer.

Explanation

Findings within published limits may be accepted, but must be documented and dispositioned according to the maintenance manual. Blending without reference to approved procedures is not permitted. Immediate removal is not required for damage within limits.

Question 25Aircraft systems, powerplants and airworthiness

What is the effect of operating a turbine engine with a partially clogged fuel nozzle?

  1. Uneven combustion, possible hot spots, and high EGT on affected can Correct answer.
  2. Uniform combustion with lower fuel consumption
  3. Reduced oil consumption
  4. Increased compressor efficiency

Explanation

A clogged nozzle delivers less fuel to its combustion can, causing uneven combustion, localized hot spots, and high EGT that can damage the liner and turbine. It does not improve efficiency or reduce oil use. The nozzle must be cleaned or replaced per maintenance instructions.

Question 26Aircraft systems, powerplants and airworthiness

In a gas turbine engine, what is the primary function of the diffuser section that follows the compressor outlet?

  1. To convert air velocity into static pressure and slow the flow for stable combustion Correct answer.
  2. To increase air velocity before combustion
  3. To drive the accessory gearbox through a radial shaft
  4. To cool the combustion gases before they reach the turbine

Explanation

The diffuser reduces the airflow velocity leaving the compressor and converts that dynamic energy into static pressure, creating the low-speed, high-pressure air needed for stable combustion. Without this deceleration, flame stability in the combustor would be poor and pressure losses would rise.

Question 27Aircraft systems, powerplants and airworthiness

Which statement correctly describes the purpose of the thrust reverser on a turbofan engine during landing rollout?

  1. It deploys spoilers on the wing to dump lift
  2. It reverses the direction of fan rotation to produce negative thrust
  3. It redirects fan or exhaust flow forward to produce a decelerating force Correct answer.
  4. It increases engine idle RPM to shorten the landing distance

Explanation

A reverser physically redirects the bypass or exhaust stream forward, producing a rearward-acting force that decelerates the aircraft. The engine continues to rotate in the same direction; only the direction of the gas path is changed.

Question 28Aircraft systems, powerplants and airworthiness

On a turbine engine, what does a high oil consumption rate combined with blue-grey exhaust smoke most likely indicate?

  1. A clogged oil filter bypass valve
  2. An overfilled hydraulic reservoir
  3. Oil leaking past a seal into the turbine or exhaust path Correct answer.
  4. A failed fuel-oil heat exchanger core leak into the fuel line

Explanation

Oil entering the hot section burns and appears as blue-grey smoke, and the loss shows up as increased oil consumption. Typical causes are worn bearing seals or a pressurization seal failure allowing oil into the gas path.

Question 29Aircraft systems, powerplants and airworthiness

What is the primary purpose of the igniter plugs in a turbine engine combustion section?

  1. To maintain continuous combustion throughout the flight
  2. To measure combustion temperature for the EGT gauge
  3. To provide the initial ignition of the fuel-air mixture during start and for relight capability Correct answer.
  4. To atomize fuel before it enters the combustor

Explanation

Igniters supply the spark that starts combustion and, on many engines, allow automatic relight after a flameout. Once combustion is established, the flame is self-sustaining and the igniters are normally switched off.

Question 30Aircraft systems, powerplants and airworthiness

What is the function of the fire detection loop installed in an engine nacelle?

  1. To discharge extinguishing agent automatically
  2. To sense a fire or overheat and trigger a warning in the cockpit Correct answer.
  3. To shut down the engine without crew action
  4. To cool the nacelle by circulating air

Explanation

The detection loop senses a temperature rise or fire condition and provides a warning to the flight crew, who then decide on the response. Detection and extinguishing are separate functions handled by different components.

Question 31Aircraft systems, powerplants and airworthiness

What does the term 'wet-sump' mean in relation to a reciprocating engine lubrication system?

  1. Oil is mixed with fuel before entering the cylinders
  2. Oil is stored in a sump integral to the engine crankcase Correct answer.
  3. Oil is stored in a separate tank outside the engine
  4. Oil is cooled by fuel before returning to the sump

Explanation

In a wet-sump system the oil supply sits in a sump built into the engine crankcase and is drawn from there by the oil pump. A dry-sump system instead keeps the supply in a separate tank.

Question 32Aircraft systems, powerplants and airworthiness

In an aircraft DC electrical system, what is the purpose of the bus tie breaker?

  1. To convert AC to DC for battery charging
  2. To connect or isolate the main DC buses so a failed source does not de-energize the whole system Correct answer.
  3. To protect individual avionics circuits from overcurrent
  4. To disconnect the battery during engine start

Explanation

Bus tie breakers allow power sources and buses to be paralleled or separated, preserving supply to essential loads if one generator or bus fails. They are system-level devices, not individual circuit protection.

Question 33Aircraft systems, powerplants and airworthiness

What is the purpose of the airworthiness certificate issued for an aircraft?

  1. It records the aircraft's maintenance schedule
  2. It certifies that the operator is financially fit to run the aircraft
  3. It confirms the aircraft conforms to its approved type design and is safe to operate Correct answer.
  4. It authorizes the pilot to fly in controlled airspace

Explanation

An airworthiness certificate attests that the aircraft meets its type design and is in a condition for safe operation. It remains valid only while the aircraft is maintained in accordance with the applicable requirements.

Question 34Aircraft systems, powerplants and airworthiness

A turbine engine's fuel control unit receives a signal that compressor discharge pressure has fallen while fuel flow remains constant. What is the most likely immediate effect on engine operation?

  1. The oil pressure will drop to zero
  2. The engine will overspeed immediately
  3. The fuel-air ratio becomes richer and EGT may rise Correct answer.
  4. The starter will remain engaged

Explanation

If airflow falls while fuel flow stays the same, the fuel-air ratio shifts richer, which typically raises exhaust gas temperature and can cause a hot start or surge. The fuel control normally schedules fuel against airflow to prevent this.

Question 35Aircraft systems, powerplants and airworthiness

During cruise, the captain reports that the left generator has tripped offline and the battery is discharging. What is the most appropriate immediate action for the flight engineer?

  1. Increase the battery discharge rate to stabilize the bus
  2. Deploy the ram air turbine immediately
  3. Shut down all non-essential avionics and continue without further action
  4. Reset the generator field and attempt to bring the generator back online per the checklist Correct answer.

Explanation

The correct response is to follow the approved checklist, which typically involves attempting to reset and reconnect the failed generator before shedding loads. Load shedding is a subsequent step if the source cannot be restored.

Question 36Aircraft systems, powerplants and airworthiness

An engine experiences a bird strike that dents several fan blades beyond the maintenance manual limits. What is the appropriate airworthiness action?

  1. Continue operation and monitor for vibration
  2. Blend the damage per approved data or replace the blades, then document the action Correct answer.
  3. Reduce engine thrust limits and defer repair indefinitely
  4. Return the aircraft to service after a visual inspection only

Explanation

Damage beyond manual limits requires repair or replacement in accordance with approved maintenance data, and the work must be recorded. Operating with out-of-limit damage compromises structural integrity and is not permitted.

Question 37Aircraft systems, powerplants and airworthiness

What is the function of the variable inlet guide vanes (VIGV) on an axial compressor?

  1. To cool the turbine blades with bypass air
  2. To drive the accessory gearbox
  3. To regulate airflow angle into the first stage and improve stall margin at low speed Correct answer.
  4. To increase fuel pressure at the burner nozzles

Explanation

VIGVs change the angle of the incoming air to the first compressor stage so the early stages are not over-angled at low corrected speed, which improves surge margin. They modulate with engine speed and are a key anti-stall feature.

Question 38Aircraft systems, powerplants and airworthiness

Why is the fuel-oil heat exchanger often placed in the engine oil system?

  1. To cool the fuel and warm the oil to keep oil viscosity within limits Correct answer.
  2. To prevent fuel from freezing in the tank
  3. To filter contaminants from the oil
  4. To increase fuel pressure for the fuel control unit

Explanation

The fuel-oil heat exchanger uses cold fuel to cool hot engine oil while warming the fuel, which helps maintain oil viscosity and improves fuel flow characteristics. This dual benefit is why it is common on turbine engines.

Question 39Aircraft systems, powerplants and airworthiness

What is the primary purpose of the engine mount isolators on a turbofan installation?

  1. To carry all engine thrust loads directly to the wing spar
  2. To provide a fireproof barrier between nacelle zones
  3. To measure engine torque for the cockpit indicator
  4. To damp vibration and accommodate thermal expansion between engine and airframe Correct answer.

Explanation

Engine mount isolators are elastomeric or hydraulic elements that damp vibration and allow for thermal growth while still transmitting thrust and inertia loads to the airframe. They are not primary load paths on their own.

Question 40Aircraft systems, powerplants and airworthiness

A pressurization controller is set to maintain a cabin pressure altitude of 8,000 ft, but the outflow valve remains fully open at cruise. What is the most likely cause?

  1. The cabin altitude warning horn is inoperative
  2. The cabin pressure controller is commanding maximum differential pressure
  3. The outflow valve is stuck open or its actuator has failed Correct answer.
  4. The air conditioning packs are producing too much bleed air

Explanation

If the outflow valve stays fully open, cabin pressure cannot build and the cabin altitude rises despite the controller setting. A stuck valve or failed actuator is the most direct explanation.

Question 41Aircraft systems, powerplants and airworthiness

What does the term 'on-condition maintenance' mean in an approved aircraft maintenance program?

  1. All components are overhauled at every C-check
  2. Components are inspected and replaced only when wear or degradation is found Correct answer.
  3. Maintenance is deferred until a failure occurs in service
  4. Components are replaced at fixed calendar intervals regardless of condition

Explanation

On-condition maintenance uses inspections and measurements to determine whether a component can remain in service, replacing it only when it approaches a defined limit. It differs from hard-time replacement and from run-to-failure.

Question 42Aircraft systems, powerplants and airworthiness

In a turbine engine, what is the purpose of the active clearance control system on the high-pressure turbine?

  1. To modulate cooling air to the turbine case to control tip clearance and improve efficiency Correct answer.
  2. To vary the exhaust nozzle area
  3. To control compressor bleed valve position
  4. To adjust the fuel schedule during acceleration

Explanation

Active clearance control directs cooling air onto the turbine case to shrink it and reduce blade tip clearance at cruise, improving specific fuel consumption. The system is scheduled with engine power and altitude.

Question 43Aircraft systems, powerplants and airworthiness

A flight engineer notices that the fuel quantity gauge reads lower than the calculated fuel on board after refueling. Which action is most appropriate before dispatch?

  1. Defer the discrepancy without recording it
  2. Dispatch based on the calculated figure and ignore the gauge
  3. Verify quantity with drip sticks or a calibrated measuring method and resolve the discrepancy Correct answer.
  4. Add fuel until the gauge reads full

Explanation

An unexplained fuel quantity discrepancy must be resolved before flight because fuel indication affects range and legality. Cross-checking with drip sticks or another calibrated method is the standard way to verify actual quantity.

Question 44Aircraft systems, powerplants and airworthiness

What is the function of the anti-skid system on an aircraft braking system?

  1. To increase brake pressure during landing
  2. To apply the parking brake automatically
  3. To retract the landing gear after touchdown
  4. To modulate brake pressure to prevent wheel lockup and maintain directional control Correct answer.

Explanation

Anti-skid systems sense wheel deceleration and release brake pressure to prevent skidding, preserving friction and steering control on the runway. They modulate, rather than increase, applied brake pressure.

Question 45Aircraft systems, powerplants and airworthiness

During a climb, the engine bleed valves fail in the open position. What is the most likely consequence?

  1. Loss of oil pressure
  2. Reduced compressor efficiency and possible turbine overtemperature Correct answer.
  3. Immediate flameout of the engine
  4. Increased surge margin and higher thrust

Explanation

Bleed valves stuck open waste compressor air, reducing efficiency and altering the fuel-air schedule, which can lead to higher turbine temperatures and reduced thrust. Surge margin is generally reduced, not improved.

Question 46Aircraft systems, powerplants and airworthiness

What does a 'hard landing' inspection typically require after a reported hard landing?

  1. No action if the aircraft subsequently flies normally
  2. A structural and landing gear inspection per the maintenance manual criteria Correct answer.
  3. Only a visual walk-around of the tires
  4. An engine borescope inspection only

Explanation

A hard landing can overstress the landing gear and airframe, so the maintenance manual specifies inspection criteria such as load limits, gear components, and structural attachments. A simple walk-around is not sufficient.

Question 47Aircraft systems, powerplants and airworthiness

A turbine engine is being operated with a partially clogged fuel nozzle. Which set of indications is most consistent with this condition?

  1. Uniform EGT across all cylinders with normal fuel flow
  2. Localized hot section distress, uneven EGT spread, and possible combustion instability Correct answer.
  3. Low oil pressure with high oil temperature
  4. High starter current during start

Explanation

A partially clogged nozzle restricts fuel to one combustor can, producing uneven temperature distribution, localized hot spots, and possible rough combustion. The EGT spread between cans becomes abnormal.

Question 48Aircraft systems, powerplants and airworthiness

An engine's compressor is operating near its surge line at high altitude. Which combination of changes would most improve surge margin?

  1. Opening bleed valves and modulating variable stator vanes toward a less angled position Correct answer.
  2. Increasing turbine inlet temperature and reducing bleed
  3. Increasing fuel flow and closing bleed valves
  4. Closing the variable inlet guide vanes fully

Explanation

Opening bleed valves reduces back-pressure in the compressor and modulating variable vanes reduces the angle of attack on the early stages, both of which increase surge margin. Fuel flow and temperature changes do not directly improve surge margin.

Question 49Aircraft systems, powerplants and airworthiness

An aircraft's airworthiness directive requires repetitive inspections of a structural fitting. The operator has complied with the initial inspection but has not scheduled the repetitive inspections. What is the airworthiness status?

  1. The directive is automatically cancelled after the first inspection
  2. Compliance can be deferred indefinitely if no cracks were found initially
  3. The aircraft is not in compliance and must not be operated until the repetitive inspections are accomplished Correct answer.
  4. The aircraft remains airworthy because the initial inspection was done

Explanation

An airworthiness directive is mandatory in full, including any repetitive inspection requirements, and the aircraft is not airworthy if those are not met. The initial inspection alone does not satisfy the directive.

Question 50Aircraft systems, powerplants and airworthiness

During an engine ground run, the fuel control unit is found to be scheduling fuel based on an incorrect compressor inlet temperature signal. What is the most likely operational consequence?

  1. The oil system will overheat immediately
  2. The ignition system will fail to fire
  3. The fuel schedule will be biased, causing possible overtemperature or reduced acceleration margin Correct answer.
  4. The engine will exceed its maximum allowable thrust at all times

Explanation

Compressor inlet temperature is used to correct fuel scheduling for air density, so a false signal biases the schedule and can lead to hot starts, overtemperature, or sluggish acceleration. The effect depends on the direction of the error.