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Hydraulic Servicing..............................................................................................................13-01-08
Description.................................................................................................................13-01-08
Hydraulic Servicing Panel..........................................................................................13-01-09
Auxiliary Accumulator Servicing.................................................................................13-01-10
Auxiliary Hydraulic System Schematic....................................................................... 13-01-11
Controls and Indications......................................................................................................13-01-12
Description.................................................................................................................13-01-12
Hydraulic Control Panel.............................................................................................13-01-12
Hydraulic Synoptic Page............................................................................................13-01-13
EICAS Messages................................................................................................................13-01-14
Feb 22/2006 Flight Crew Operating Manual Volume 2 REV 5 CSP 100-6
13-00-01
INTRODUCTION
The Challenger 300 has a left and right hydraulic system that are independent from each other, and an auxiliary system that is tied to the right hydraulic system. The left, right, and auxiliary systems are controlled from the HYDRAULICS panel, located immediately to the right of the throttle quadrant on the center pedestal. The hydraulic systems normally operates at 3000 psi and uses Fire Resistant Phosphate Ester based MIL-H-5440 Type II fluid. The left and right hydraulic systems are both powered by Engine-Driven Pumps (EDPs) which are backed up by a DC Motor-driven Pumps (DCMPs). The left and right hydraulic systems DCMPs are powered by the electrical DC bus supplied by the generator on the engine opposite the engine which drives the EDP. Thus, hydraulic power is provided for the left and right systems after any single engine fail-ure. After the loss of the left and right hydraulic systems, the lower rudder PCU will be powered by the AUX hydraulic system.
The L DCMP is powered by the R MAIN DC bus. There is no battery backup for the R MAIN DC bus. If the right DC generator fails, the R MAIN DC bus can be powered by the L DC generator or the APU.
The R DCMP is powered by the L ESS bus. The bus can be powered by the right dc generator or the APU if the left DC generator fails. If no generators are operational, the R DCMP will only automatically start if the pilot selects the flaps to a non-zero position. If only one generator is operational on the airplane, then only one of the L or R DCMPs is operational, (one DCMP is load shed from the good hydraulic system with the R DCMP taking priority over the left DCMP if both EDPs are failed). AUX DCMP is not load shed for single generator operation.
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本文链接地址：庞巴迪挑战者300公务机机组操作手册 Bombardier Challenger-液压(2)
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