We use cookies on our site to analyze traffic, enhance your experience, and provide you with tailored content.

For more information visit our privacy policy.

Common use of Power Plant Clause in Contracts

Power Plant. Two Rolls-Royce Deutschland BR710A2-20 turbofan engines power the Aircraft. The engines produce 14,750 lb. of thrust up to 35°C (ISA+20°C) at sea level. The engine is assembled from seven sub-assemblies: fan rotor, intermediate fan casing, HP compressor, combustor/HP turbine, LP turbine, exhaust case and accessory gearbox. It has a single stage low-pressure fan driven by a two stage shrouded low-pressure turbine. A two-stage high-pressure turbine drives a ten-stage high-pressure compressor. The first four stages of the compressor are equipped with variable-pitch stators controlled by the engine’s Full Authority Digital Engine Control (FADEC). The combustor is an annular conventional flow type designed for low emissions and smoke control. A forced mixer exhaust is integrated with a two-door full flow type thrust reverser. The hydraulically operated thrust reverser system, with weight on wheels or wheel spin-up available, will deploy when the thrust reverser levers on the throttle quadrant are operated. For maintenance, the thrust reverser can be locked open. The engine has been designed for “on condition” type maintenance which requires periodic inspection of specific major components. Only those parts that show distress are replaced or overhauled. The periodic maintenance checks are established utilizing the MSG-3 process. The complete power plant assembly is detachable from the pylon as a unit.

Appears in 2 contracts

Samples: Aircraft Purchase Agreement, Aircraft Purchase Agreement (Microstrategy Inc)

AutoNDA by SimpleDocs

Power Plant. Two Rolls-Royce Deutschland BR710A2-20 20/01 bypass turbofan engines power the Aircraft. The engines produce 14,750 lb. of thrust up to 35°C (ISA+20°C) at sea level. The engine is assembled from seven sub-assemblies: fan rotor, intermediate fan casing, HP compressor, combustor/HP turbine, LP turbine, exhaust case and accessory gearbox. It has a single stage low-pressure fan driven by a two stage shrouded low-pressure turbine. A ten-stage high-pressure compressor is driven by a two-stage high-pressure turbine drives a ten-stage high-pressure compressorturbine. The first four stages of the compressor are equipped with variable-pitch stators controlled by the engine’s Full Authority Digital Engine Control (FADEC). The combustor is an annular conventional flow type designed for low emissions and smoke control. A forced mixer exhaust is integrated with a two-door full flow type thrust reverser. The hydraulically operated thrust reverser system, with weight on wheels or wheel spin-up available, will deploy when the thrust reverser levers on the throttle quadrant are operated. For maintenance, the thrust reverser can be locked open. The engine has been designed for “on condition” type maintenance which requires periodic inspection of specific major components. Only those parts that show distress are replaced or overhauled. The periodic maintenance checks are established utilizing the MSG-3 process. The complete power plant assembly is detachable from the pylon as a unit.

Appears in 1 contract

Samples: Aircraft Purchase Agreement (Williams Sonoma Inc)

AutoNDA by SimpleDocs

Power Plant. Two Rolls-Royce Deutschland BR710A2-20 20/01 bypass turbofan engines power the Aircraft. The engines produce 14,750 lb. of thrust up to 35°C (ISA+20°C) at sea level. The engine is assembled from seven sub-assemblies: fan rotor, intermediate fan casing, HP compressor, combustor/HP turbine, LP turbine, exhaust case and accessory gearbox. It has a single stage low-pressure fan driven by a two stage shrouded low-pressure turbine. A ten-stage high-pressure compressor is driven by a two-stage high-pressure turbine drives a ten-stage high-pressure compressorturbine. The first four stages of the compressor are equipped with variable-pitch stators controlled by the engine’s Full Authority Digital Engine Control (FADEC). The combustor is an annular conventional flow type designed for low emissions and smoke control. A forced mixer exhaust is integrated with a two-door full flow type thrust reverser. The hydraulically operated thrust reverser system, with weight on wheels or wheel spin-up available, will deploy when the thrust reverser levers on the throttle quadrant are operated. For maintenance, the thrust reverser can be locked open. The engine has been designed for “on condition” type maintenance which requires periodic inspection of specific major components. Only those parts that show distress are replaced or overhauled. The periodic maintenance checks are established utilizing the MSG-3 process. The complete power plant assembly is detachable from the pylon as a unit. A Honeywell RE220 gas turbine APU is installed in the Aircraft tail cone to provide bleed air and electrical power on the ground and in flight. Control of APU speed and temperature is automatic. APU starting is initiated by a single switch located in the cockpit. The APU supplies bleed air for cabin cooling and heating, as well as engine starting. The APU also drives a 40/45 kVA generator, which provides electrical power on the ground and as back-up to the main engine driven generators in-flight.

Appears in 1 contract

Samples: Aircraft Purchase Agreement (Williams Sonoma Inc)

Draft better contracts in just 5 minutes Get the weekly Law Insider newsletter packed with expert videos, webinars, ebooks, and more!