Выполненное тестовое задание вместе с заполненной Анкетой отправляйте, пожалуйста, по адресу: *****@***ru

Тематика: Авиация

Языковая пара: английский - русский

Оригинал

Перевод

Technical Information of Aircraft

Information Required

Vendor to specify

Useful Load - Maximum Take Off Weight (MTOW) in kilograms - at various altitudes (sea level to max take off)

Provide tech info

Endurance excluding reserve fuel for 45 min + fuel for 100 Nm diversion

Instrument Meteorological Conditions capability as per DGCA requirements. Please indicate Yes/No

Type and make of Avionics - In detail including avionics ground testing facility

Type of de-icing/anti-icing system

Available power for Special Mission Equipment(s) including electrical power/load analysis and heat load analysis for air conditioning system

Capable of interfacing the instrument(s) data with the avionics suite - please describe the avionics systems to be interfaced.

Power output available/details of alternator and its capacity

Possibility of having necessary cut-outs in the aircraft for installing various instruments/sensor systems for non-interfering simultaneous use (EMI/EMC compatibility)

Auxiliary Jacking Points - Safety Stay

When the aircraft is on jacks, it is recommended that a safety stay be placed under the fuselage, between FR73 and FR74 to prevent tail tipping caused by accidental displacement of the center of gravity. The safety stay is not used to lift the aircraft.

A male spherical ball pad with a 19 mm (0.75 in) radius forming part of the airplane structure is provided for using the safety stay. Jack design In fully retracted position (jack stroke at minimum) the height is such that the jack may be placed beneath the airplane under the most adverse conditions, namely, tires deflated and shock absorbers depressurized.

In addition, a clearance of 50 mm (1.97 in) approximately must be provided between the airplane jacking point and the jack upper end. The lifting jack stroke enables the aircraft to be jacked up so that the fuselage longitudinal datum line (aircraft center line) parallel to the ground, with a 100 mm (3.94 in) clearance between the main landing gear wheels and the ground. In particular, this enables the landing gear extension/retraction tests to be performed.