Carroceria

The airplane is powered by two engines. CFM56-7, 26.000 pounds of thrust. CFM56-3, 26.000 pounds of thrust. CFM56-7, 22.000 pounds of thrust. CFM55-7, 26.000 pounds of thrust.

Primary engine indications. N1, EGT. N2, EGT. N1. EGT.

Bleed air is connected to. N1. N2. Low turbine. High turbine.

N1 roto consists of. Low perssure compressor, low pressure turbine. High pressure comrpessor, High pressure turbine. Low pressure compressor, High pressure turbine. high pressure compressor, low pressure turbine.

N2 roto consists of. High pressure compressor, high pressure turbine. Low pressure compressor, high pressure turbine. Low pressure compressor, Low pressure turbine. High pressure compressor, Low pressure turbine.

Each engine is controlled by: EEC. FMC. ECU. FCC.

Secondary engine indications. N2, fuel flow, Vibrations, oil pressure, oil temp, oil qty. N1, fuel flow, oil pressure, oil temp, oil qty. N2, fuel flow, oil pressure, oil qty.

When EEC not powered: N1, N2, oil qty and eng vibrations are displayed directly from engine sensors. N1, N2 from engine sensors, the rest from ECU. none of the above.

When is ENG FAIL displayed in amber on the EGT indicator. below 50% N2, Engine start lever in idle. Below 50% N1, High EGT temp. High EGT temp, low N2 pressure.

In normal mode the EEC uses which conditions to calculate N1 thrust ratings. Flight conditions and bleed air demand. Fligh condition and EGT limits. N1 limits and EGT limits. N1, N2 and flight conditions.

When does is the EEC powered. 15% N2. 30% N2. 15% N1. 30% N1.

Soft mode and hard mode mean soft uses last valid flight conditions, hard can exceed limits. True. False.

Approach idle is selected automatically below. 15.000ft. 19.000ft. 22.000ft. 14.000ft.

N1 & N2 % RPM is higher in approach idle than flight minimum idle. True. False.

When is the FILTER BYPASS light illuminated. When Filter is clogged and fuel bypasses. When filter is operating slowly. When fuel becomes too saturared because of height.

Fuel flow is measured where?. Engine shutoff valves. Spar valves. Main tank valves.

Engines in idle Fuel flow accuracy is reduced?. True. False.

How many stages in fuel system. 2. 3. 4.

What happens on first stage of fuel?. Heat exchanger and filter. HMU. Heat exchanger. Filter.

What happens on the second stage of fuel system?. HMU, EEC. Heat exchanger. Filter and heat exchanger.

The oil system is pressurized by. Engine driven oil pump. Engine filter bypass. Scavenge pumps. Oil tank.

Starter operation requires ¿. Pressurized air and electrical power. Electrical power. EEC. Ac and DC current.

Porcentage of N2 fuel valves open. 25%. 15%. 56%. 50%.

Starter cutout speed. 56% N2. 15% N1. 22% N2. 50% N1.

Does EEC monitor hot starts, engine stalls on air start?. True. False.

Ways of inflight starting. Xbleed and windmill. Xbleed. APU start. Battery start.

When is an auto relight provided. Flameout protection. Overheat protection. Low pressure N1 detection. low oil pressure.

At low N2 values the oil scavenge pump may not provide. Enough pressure to return oil to the tank. Low oil qty indication. All of the above.

Thrust reverser engine No. 1 works mainly with. Hydraulic system A. Hydraulic system B. Standby system.

When reversers working with standby system assymetry is possible and speed of operation is slower. True. False.

When can thrust reversers be deployed. 10 ft radio altimeter or less. Idle thrust levers. Ground sensors. All of the above.

APU supplies bleed ONLY for engine starting?. True. False.

Fuel for APU with AC fuel pumps comes from. Left main tank. Center tank. Right main Tank. Left side of the fuel manifold.

Fuel for APU without AC fuel pumps comes from. Left main tank. Center tank. Right main Tank. Left side of the fuel manifold.

Start cycle of the APU may take as long as. 120 sec. 60 sec. 180 sec. none of the above.

Do not use APU as source of bleed air before. 2 min. 3 min. 1.5 min.

Is it necessary to monitor EGT temperature. True. False.