For LOMAC Strike Fighters: Project 1 Wings Over Europe 01 Apr 2006
Rob "Bunyap" McCray email@example.com www.bunyap2w1.com
Table of Contents
Section I - Description Section II - Normal Procedures Section III - Operating Limitations /TOLD
This guide draws primarily on information from T.O.1A-10A-1, the A-10A flight manual. Many procedures called out in the guide can be duplicated using the controls available in LOMAC and Strike Fighters. You will find these procedures highlighted in yellow. As a general rule, procedures presented in italics can not be performed or verified within the sim and are presented for informational purposes only.
THE AIRCRAFT The A-10is a single-seat close air support aircraft manufactured by Fairchild Republic Company, Farmingdale, New York. The aircraft is a low wing, low tail configuration with two high bypass turbo fan engines installed in nacelles mounted on pylons extending from the aft fuselage. Twin vertical stabilizers are mounted on the outboard tips of the horizontal tail. The tricycle forward retracting Sandinggear is equipped with an anti-skid system and a steerable nosewheel. The nose gear is installed to the right of the aircraft centerline to permit near centerline gunfire. The nose gear retracts fully into the fuselage while the main gears partially retract into streamlined pods in the wings. A titanium armor installation surrounds the cockpit. The primary flight controls are equipped with artificialfeel devices to simulate aerodynamic feel. The elevator and aileron controls split into redundant separate systems before leaving the armor protection. The controls are powered by two independent hydraulic systems, either of which has the capability of controlling the airplane. If both hydraulic systems fail, the airplane can be flown using a manual reversion system. The ailerons consist of anupper and lower panel that become speed brakes when opened. The windshield front panel is resistant to small arms fire and birds. The windshield side panels are resistant to spall spray caused by penetrations. The fuselage fuel cell sumps are
self-sealing on the lower portion and tear resistant on the upper portion. The cells are filled with a flexible foam to prevent fuel tank explosion.Single-point ground refueling and engine feed lines are self-sealing. The escape system provides a zero/zero capability (zero velocity, and zero pitch and roll attitude) either with the canopy removed or through the canopy. The armament system includes a high fire rate 30mm seven-barrel gun with ammunition stored in a drum. A variety of stores are carried on 11 pylons, 4 on each wing and 3 on thefuselage. ENGINES The aircraft is powered by two General Electric TF34-GE-100/l00A engines. Sea level, standard day, static thrust for an installed engine is approximately 8,900 pounds at maximum thrust. The engine incorporates a single-stage bypass fan and a 14-stage axial flow compressor. Bypass air produces over 85% of engine thrust. Therefore, engine fan speed is the best indication of thrust.Variable inlet guide vanes automatically modulate throughout the engine operating range. An accessory gearbox drives a hydraulic pump, fuel pump and fuel control, oil pump, and an electric generator. An air bleed for aircraft systems is provided. Engine acceleration time from IDLE to MAX thrust will be approximately 10 seconds at sea level.
AUXILIARY POWER UNIT The APU supplies air for enginestarling, drives a generator for electric power, and can drive a hydraulic pump for ground maintenance functions. The unit is located in the aft fuselage between the two engines and is provided with safety devices that shut down the APU when certain operating limitations are exceeded. Fuel for APU starting is supplied by the DC fuel pump. APU controls are powered by the DC essential bus.