Honda Aircraft Company
HA-420
SYSTEMS
POM
DESCRIPTION
HJ1-29000-005-001
October 30, 2016
1-117
HYDRAULICS AND LANDING GEAR
HYDRAULIC SYSTEM
The hydraulic power system contains one electrical-motor-driven
hydraulic pump (DCMP), a hydraulic reservoir-and-filter module, three
accumulators, check valves, pressure transducers and pressure and
temperature switches. The Main accumulator supplies the landing gear
and optional speed brake, the Brake accumulator supplies the normal and
anti-skid brakes and the Emergency accumulator supplies the
emergency/parking brake and the nosewheel steering. Each accumulator
is isolated by a check valve.
Control of the hydraulic system is fully automatic and no cockpit
controls are incorporated.
The single hydraulic pump is a fixed displacement, motor pump which
maintains the aircraft hydraulic system at a pressure between 2500-2950
psig except when the aircraft is on the ground on battery power at which
time it is regulated at 1725-1875 psig. Pressure switches installed on the
hydraulic reservoir-and-filter module control the system pressure. An
unloading valve in the system will open to release pressure at 3200 psig.
FOR TRAINING PURPOSES ONLY
