国内精品♨️_精品国产乱码久久久久久1区2区-亚洲_.手.动.输.入.网.址.联.系.客.服.人.员.lanan_shell
Pilot’s Manual PM-132A III-1 TABLE OF CONTENTS Hydraulic System ..................................................................................... 3-1 Firewall Shutoff Valves ......................................................................... 3-2 Source Selector Valve............................................................................. 3-2 AUX HYD Pump Control ..................................................................... 3-2 Main/Auxiliary System Pressure........................................................ 3-3 Brake Accumulator Pressure........................................................... 3-4 Hydraulic Ground Service.................................................................... 3-4 Hydraulic System Page......................................................................... 3-5 HYD System Page (Figure 3-1) ............................................................ 3-5 Hydraulic System Schematic (Figure 3-2) ..........................................3-7 Landing Gear System................................................................................ 3-9 Landing Gear Control Switch .............................................................. 3-9 Landing Gear Extension/Retraction Schematic (Figure 3-3) ........ 3-11 Landing Gear Position Lights ............................................................ 3-12 Landing Gear Warning System.......................................................... 3-13 Landing Gear Free Fall................................................................... 3-14 Nose Wheel Steering System.............................................................. 3-15 Nose Steer Switch ........................................................................... 3-16 Wheel Brake Control /Anti-Skid System............................................. 3-17 Touchdown Protection ........................................................................ 3-17 Emergency/Parking Brake................................................................. 3-18 Anti-Skid Switch .................................................................................. 3-19 Wheel Brake Control/Anti-Skid System Schematic (Figure 3-4)....................................................................................... 3-21 SECTION III HYDRAULICS & LANDING GEAR Pilot’s Manual PM-132A 3-1 SECTION III HYDRAULICS & LANDING GEAR HYDRAULIC SYSTEM The aircraft hydraulic system supplies hydraulic pressure for operation of the aircraft landing gear, brake, flap, spoiler/spoileron and thrust reverser systems. Hydraulic fluid flows from the main hydraulic reservoir through two firewall shutoff valves to the main engine-driven hydraulic pumps for distribution to the required systems upon demand. The hydraulic system has both a main and auxiliary source of hydraulic power. These sources are totally separate up to the source selector valve. An auxiliary dc motor-driven hydraulic pump is installed to provide auxiliary hydraulic pressure to the brake system through the brake source shuttle valve and to the landing gear and flap system through the source selector valve in the event of a malfunction. The auxiliary hydraulic system only provides pressure for the brake system while the aircraft is on the ground. A 260 cu. in. (4261 cc) reservoir supplies hydraulic fluid to the main and auxiliary hydraulic systems. The reservoir is designed with a separation wall (partition) to contain fluid for either the main or auxiliary system. Reservoir pressure is maintained at approximately 20 psi (138 kPa) by bleed air supplied through a pressure regulator. A bleed-air pressure relief valve releases pressure in excess of 20 psi (138 kPa), and a vacuum relief valve prevents negative pressure in the reservoir. A thermal shutoff valve prevents high energy bleed air (>390° F [199° C]) from entering the reservoir in the event of a hydraulic line failure. The main and auxiliary hydraulic pumps will each maintain a nominal pressure of 3000 psi (20,685 kPa) for their applicable systems. A precharged (1500 psi [10,343 kPa]) hydraulic accumulator is installed to dampen and absorb pressure surges within the main hydraulic system. A separate brake accumulator, fed by the auxiliary system, maintains pressure for the emergency/parking brakes. Two high-pressure filters and two return filters prevent hydraulic fluid contamination within the main and auxiliary systems. These filters incorporate bypass valves which will open in the event they become clogged. A hydraulic pressure relief valve, installed between the high-pressure and return lines www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：BOMBARDIER_Learjet_0-Hydraulics_and_Landing_Gear
