3272-11 sys (1.6)

To correct for nose heaviness on an aircraft fitted with a variable incidence tailplane, the incidence of the tailplane would be. decreased, which is done by lowering the leading edge. decreased, which is done by lowering the trailing edge. increased, which is done by lowering the leading edge.

Variable incidence tailplanes. move rapidly when trimming the aircraft during climb out and landing approach and slowly during cruise. always move slowly. move rapidly when trimming the aircraft during the landing approach and slowly at all other times.

On an aircraft with a variable incidence trimming tailplane, the tailplane incidence changes. if the control column is moved back or forward. if the trim wheel is turned back or forward. automatically if the elevator moves.

An elevator controls the aircraft motion in. pitch. roll. yaw.

The balance tab is an auxiliary surface fitted to a main control surface. operating automatically to assist the pilot in moving the controls. operated independently at which point in the length of cable the tensiometer is applied. operating automatically to provide 'feel' to the controls.

The outboard ailerons on some large aircraft. are isolated at high speeds. are isolated at low speeds. are isolated to improve sensitivity.

Control surface flutter may be caused by. excessive play in trim tab attachments. high static friction in trim tab control tabs. incorrect angular movement of trim tabs.

A 'frise' aileron is incorporated to. provide aerodynamic balancing so assisting the pilot to move the control. equalize aileron drag in a turn. ensure aileron control is retained at high angles of attack.

The term 'empennage' incorporates: rudder, ailerons, spoilers. elevators, stabiliser, ailerons. elevators, stabiliser, rudder.

The web of an 'I' beam takes mainly which type of load?. Shear. Tension. Bending.

The four main structural items making up a horizontal stabiliser are. spar, rib, stringers, skin panels. spar, rib, longerons, skin panels. spar, rib, bulkheads, skin panels.

The direction of travel of an electrically operated variable incidence tailplane is determined by. direction of rotation of the electric motor. a gearbox. solenoid operated clutches.

An upward elevator deflection on the reverse camber tailplane. will increase tailplane download. will decrease tailplane download. may increase or decrease download depending upon the aircraft C of G position.

Aerodynamic balance. will cause CP to move towards the trailing edge and cause instability. will reduce aerodynamic loading. will cause CP to move forward of hinge and cause overbalance.

A flying control mass balance weight. keeps the control surface C of G as close to the trailing edge as possible. tends to move the control surface C of G close to the hinge line. tends to move the control surface C of G forward of the hinge line.

What is attached to the rear of the vertical stabilizer?. elevator. rudder. aileron.

Aerodynamic balance is used to. prevent flutter of the flying controls. reduce the control load to zero. make the flying controls easier to move.

An excess of aerodynamic balance would move the control surface centre of pressure. rearwards, resulting in loss of assistance. forwards, resulting in an unstable overbalance. rearwards, resulting in too much assistance.

A control surface is mass balanced by. the attachment of weights acting on the hinge line. fitting a balance tab. the attachment of weights acting forward of the hinge line.

A horn balance is. a projection of the outer edge of the control surface forward of the hinge line. a rod projecting forward from the control surface with a weight on the end. a rod projecting upward from the main control surface to which the control cables are attached.

Aerodynamic balancing of flight controls is achieved by. providing a portion of the control surface ahead of the hinge point. placing a weight in the leading edge of the control surface. placing a weight ahead of the hinge point.

The extension to the rudder (shaded portion shown on the diagram), is provided to: prevent control surface flutter. provide aerodynamic assistance for the pilot when moving the rudder. make the pilot aware of the aerodynamic forces encountered when moving the control.

Which of the following are primary control surfaces?. Elevators, ailerons, rudder. Roll spoilers, elevators, tabs. Elevators, roll spoilers, tabs.

Aerodynamic balance of a control surface may be achieved. by a trimming strip at the trailing edge of the surface. by a horn at the extremity of the surface forward of the hinge line. by weights added to the control surface aft of the hinge line.

The purpose of anti-balance tabs is to. relieve stick loads. trim the aircraft. give more feel to the control column.

A flying control mass balance weight. tends to move the control surface C of G close to the hinge line. keeps the control surface C of G as close to the trailing edge as possible. ensures that the C of G always acts to aid the pilot thus relieving control column load.

An elevator provides control about the. longitudinal axis. lateral axis. horizontal stabilizer.

Flutter can be reduced by using. mass balancing. a horn balance. servo tabs.

Construction such as horn balance and inset hinge balance installed on control surface assembly. is meant to trim CG of control surfaces. serves as a 'servo' system of balance. has same effect of the balance tab.

A control surface is provided with aerodynamic balancing to. decrease the drag when the control is deflected. assist the pilot in moving the control. increase stability.

The method employed to mass balance control surfaces is to. attach weights forward of the hinge line. allow the leading edge of the surface to project into the airflow. fit bias strips to the trailing edge of the surfaces.

In most pressurization systems, the amount of compressed air delivered to the cabin is. variable, depending on the amount selected by the cabin rate of change selector. reasonably constant irrespective of altitude. constant at any particular altitude but varies for different altitudes.

Air supplied for pressurization and conditioning is. hottest from an engine compressor bleed. the same for both the above sources. hottest from a compressor driven by an engine gear box.

The function of the mass airflow control valve is to. ensure system operating pressure is not exceeded. ensure that constant airflow out of the cabin is dictated by cabin altitude. maintain a reasonable mass flow of air into the cabin irrespective of aircraft altitude.

Which of the following can be used on the ground?. Turbo fan. Turbo brake. Turbo compressor.

What is the minimum cabin air mass flow?. 1 lbs per minute per person. 10 lbs per minute per person. 0.5 lbs per minute per person.

Jet engines are usually mounted by. welded steel tubing. aluminium castings. forged mounts and bolted to aircraft forged structure.

The mounting bolts are tightened so the engine can move. fore and aft. laterally, longitudinally, vertically. torsionally.

Wing mounted podded engines and integral fuel tanks. reduce tailplane download. provide wing bending relief. provide increased safety if the undercarriage collapses on landing.

ATA chapter for Nacelles/Pylons is. 53. 54. 55.

A pylon structural member supports the. empennage. centre section. engine.

In large air conditioning systems, the main fan is activated to. ensure conditioned air is distributed. ensure conditioned air is distributed and maintain positive duct pressure. ensure positive duct pressure is maintained.

A pack valve controls. air flow. trim air. air temperature.

A spill valve opens. to control the air from the cabin to outside. to control the flow to the cabin. to prevent an excessive pressure difference.

The mass flow delivery from engine driven blowers is controlled by. engine speed variations. automatic control devices. spill valves.

The purpose of a 'Spill' valve in a cabin air supply system is. to relieve the pressure in the air supply ducting to atmosphere. to spill overboard excess air delivered at S.L. and lower altitudes. to give a heating effect.

The purpose of a mass flow controller is to. allow pilot to select the desired cabin altitude. ensure that a constant mass of air is delivered to cabin at all times. ensure the cabin altitude remains constant during cruise at all altitudes.

The function of spill valves is to control. the rate of pressurization. air supply to the cabin. cabin pressure differential.

The function of an air mass flow control valve is to. control the airflow out of the cabin. maintain a reasonably constant air mass flow into the cabin at all altitudes. ensure that system differential pressure is not exceeded.

How much air is required for the Flight Deck?. 10 cubic feet/minute. 10 lbs/minute. Whatever the captain sets.

In a Bleed Air air-conditioning system, the warm air supply is provided by. the compressor of the gas turbine engine. the engine exhaust heat. the gas turbine exhaust.

The velocity of air from the cabin ventilation system should not exceed. 20 feet per minute. 40 feet per minute. 120 feet per minute.

A water separator is located. upstream of the turbine. downstream of turbine. downstream of heat exchanger.

A refrigerant is used in which of the following?. Vapour cycle. Pneumatic pump. Air cycle machine.

The thermostatic valve sensing bulb is located just before. the evaporator. the condenser. the compressor.

The first component that the charged air enters from the IP compressor is. the check valve. the bleed valve. the pre-cooler.

What is the maximum allowable concentration (by volume) of carbon monoxide in occupied aircraft compartment?. 0.005% (50 p.p.m). 0.02 % (200 p.p.m). 0.01 % (100 p.p.m).

An advantage of using air cycle system over the vapour cycle system in aircraft is. both air conditioning and pressurization are obtained. less hazardous than vapour cycle system. weight reduction by avoiding big tanks carrying freon gas.

A large aircraft air conditioning system's cabin temperature control. all zone temperatures are controlled from one master switch. is selectable for each zone individually from the flight station. involves modulating the pack valve.

Cockpit ventilation is required to be. selected by the crew. 10 cu/ft per crew member per minute. 10 litres per crew member per minute.

If a reduction in pack outlet temp is demanded, the temperature of the air at the outlet of the ACM compressor will. rise. fall. remain the same.

In a cabin air recirculation system, recirculated air and fresh air are supplied in the proportions. 50% of fresh air, 50% of recirculated air. 60% of fresh air, 40% of recirculated air. 40% of fresh air, 60% of recirculated air.

In an air conditioning system, before distribution, the air goes through the. TCV. TCV and mixer valve. flow control valve.

When does a 'blower' air conditioning system produce the most air?. It is not affected by altitude. At high altitudes. At low altitudes.

Where is the silencer located in a 'blower' air conditioning system?. At the outlet of the blower. At the inlet of the blower. At the inlet to the cabin.

Where is the water trap located in a bootstrap compressor?. At the outlet of the compressor. At the inlet of the compressor. At the inlet of the turbine.

Air exiting the compressor side of an ACM. will have increased pressure and temperature. no change in temperature or pressure as it is a centrifugal compressor. will have decreased pressure and temperature.

An air cycle machine turbine. drives compressor to increase temperature. drives compressor to pressurise aircraft. drives compressor to decrease temperature.

Air conditioning systems. increase the temperature of air. increase and decrease the temperature of air. decrease the temperature of air.

In an air conditioning system, heat is added to air by. restricting compressor inlet. restricting compressor outlet. restricting duct outlets.

In typical vapour cycle system, the sub-cooler. is a heat exchanger to superheat the vapour. cools the vapour further to prevent slugging. delivers extra cooling effect when the aircraft is on ground.

In a turbo fan cold air system, the heat exchanger cooling air is. ram air from ambient conditions. air bled directly from engine or through blower. bled from cabin air supply duct..

When a 'muff' or air ducting is built around the engine exhaust system and air is directed around inside the muffler, this is an. exhaust heater. combustion heater. thermal heater.

A cold air unit produces a drop in temperature by. directing compressed air into a heat exchanger. air supply to the cabin. expanding hot air across a turbine which is driving a compressor.

A cold air unit allows for cabin temperatures to be. lower than ambient air temperature despite compression heating. a little more than ambient air temperature. same as ambient temperature, despite compression heating.

Heating for pressure cabins is obtained from. driving the units compressor. air supply heated by the pressurising process. only by adding heat electrically to the air supplies.

A cold air unit produces a drop in temperature by. driving the unit's compressor. reducing pressure. reducing pressure and driving the unit's compressor.

If pressurisation air supplies come from an engine compressor, an internal oil leak will. contaminate the air. not contaminate the air. not affect the issue as it is automatically detected and vented overboard.

In pressurized aircraft, temperature conditioning is mainly achieved by. adding heat to the pressurising air. extracting heat from the pressurising air. varying cabin pressure.

Temperature control of cabin air is achieved by. varying the ambient airflow to the heat exchanger. controlling the water vapour in the supply. regulating the amount of air by-passing the cooling system.

An air-to-air heat exchanger is provided to. increase the air supply temperature. provide an emergency ram air supply. reduce the air supply temperature.

Before filling a vapour cycle cooling system. pre-heat the system to 100°F. flush the system with a solvent. apply suction to remove air and moisture.

One of the principles of cooling employed in an air cycle system is. by surface heat exchange in the C.A.U. by compression of ambient air across a turbine. conversion of heat energy to mechanical energy in the C.A.U.

The humidity within a passenger cabin should. not be less than 60%. not be greater than 40%. be between 30% and 70%.

In a 'bootstrap' cooling system the supply of air is first. passed across an expansion turbine, then compressed and passed through a heat exchanger. compressed then passed through a heat exchanger and across an expansion turbine. passes across an expansion turbine, then directly to the heat exchanger.

The temperature within the cabin of the aircraft is normally maintained at. 20oC to 24oC. 18oC to 24oC,. 12oC to 18oC.

In a Boot-Strap Air Conditioning supply system the source of compressed air is from. gas turbine compressor bleed air. gas turbine intake ram air. ram air at the wing leading edge.

The ventilation air in the aircraft cabin must have a minimum humidity of. 60 percent. 30 percent. 20 percent.

When carrying out a ground pressure test, you should use. a G.P.U. and A.P.U. combination. ground trolley and clean air. the aircraft engines because you can test the whole system.

Which of the following sometimes inhibits an air conditioning pack?. Flap position switches. Undercarriage switches. Throttle switches.

Conditioned air is. temperature and pressure adjusted. moisture removed. oxygen added.