OFFER#

IL76TD PS90

TYPE:	Aircraft
DESCRIPTION:	Ilyushin IL76TD with PS90 Engines
PRICE:	Upon Request
PACKING:	As is, Where is

ILYUSHIN IL76TD WITH PS90 ENGINES

STAGE III

The Il-76TD-90 is a further development of the Il-76TD replacing the D-30KP engines by fuel efficient PS-90A-76.

The resulting aircraft has longer range and increased payload capacity.

Compared with the Il-76TD, the Il-76TD-90 only requires a five-man crew instead of a six-man crew.

The Il-76TD-90 is available as a new production aircraft or as upgrade to existing Il-76TDs.

PS-90A-76 Aircraft Engine

PS-90A-76 engine (PS - Pavel Soloviev) is a modification of PS-90A turbofan bypass engine. It extends service life of the large fleet of the IL-76 transport airplanes and raises their efficiency by installation of the PS-90A-76 engine instead of the D-30KP. It allowed to build a new modification of the IL-76 airplane - the IL-76MF military cargo aircraft which meets modern requirements.

Turbofan, bypass, two-shaft, mixed flow, with a thrust reverser in a fan duct and noise absorbing system.

It is intended for various versions of the IL-76 long-range cargo aircraft and the IL-76MF aircraft.

The engine was certified in 2003.

Performance

Thrust, kg take-off: TH< +30°C , PH > 730 mm Hg, H=0 cruise: Н=11 km, М=0.8	14500 3500
Specific fuel consumption (with real nozzle), kg/kgf hour	0.595
Flight altitude, m	up to 13100
Air temperature at sea level (for start and operation), ° С	-47...+45
Airfield height (versus sea level) , m	up to 3500
Wind speed for ground operation, no more, m/s cross wind tail wind	15 5
Engine length, mm	4964
Fan tip diameter, mm	1900
Dry weight, kg	2950
Thrust reverser weight, kg	450
Delivery weight, kg	4160

Advantages of the PS-90A-76 engine compared to D-30KP

Conformity of ecological parameters on emission and noise to ICAO regulations
Increase of reliability and life
Improvement of efficiency
Availability of thrust augmentation up to 16000 kg
Parameter stability of running
Improvement of fire safety in connection with replacement of some fuel accessory units by pneumatic
Feasibility of the fan impeller replacement when running

Dimensions:

Cargo Compartment Height 3.4 m, Cargo Compartment Length 31.1 m, Cargo Compartment Width 3.5 m, Fuel Tank Capacity 109,500 l (28,816 gl), Fuselage Diameter 4.8 m, Height 14.3 m, Length 53.2 m, Payload Capacity 400 metric ton, Wing Area 300 square meter, Wingspan 50.5 m

Weights:

Max Weight 210 t, Payload 60 t

Engine/s Performance:

Thrust 141,000 lb (63,958 kg)

Performance:

Ceiling 12,000 m (39,370 ft), Cruise Speed 850 kph (528 mph), Landing Run Distance 990 m (3,248 ft), Max Range 6,300 km (3,402 nm) carrying a 40t payload or 4,000km carrying a 60t payload, Service Life 30 yr, Take Off Run Distance 1,800 m (5,906 ft)

Other:

Number of Engines 4, Service Life (Flight Hours) 30,000, Service Life (Flights) 10,000

NB: Aircraft offered for sale subject to contract, prior sale, withdrawal from the market and information regarding any aircraft or helicopter and provided verbally or in written documentation and/or contained within this email or associated paper-work should be taken as a guide only in determining the suitability, including that aircraft or helicopters specification and/or performance. We highly recommend that any buyer or lessee perform their own inspections and due diligence to verify any and all technical, performance and specification information contained therein including OEM claims.

PLEASE NOTE: AIRCRAFT SPECIFICATIONS SUBJECT TO VERIFICATION UPON INSPECTION. WE DO NOT ACCEPT ANY LIABILITY FOR AIRCRAFT DEFECTS, HISTORY OR TECHNICAL RECORD ERRORS. IT IS THE BUYERS RESPONSIBILITY TO INDEPENDENTLY VERIFY THE AIRCRAFT AND COMPONENT HISTORY.

GENERAL EQUIPMENT INC.