LANDING GEAR
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 15-01-01
INTRODUCTION
The landing gear system for the Challenger 300 is arranged in a retractable tricycle configuration consisting of two main
landing gear assemblies and a steerable nose landing gear assembly. Each landing gear assembly has twin wheels and tires.
Normal extension and retraction of the landing gear is powered by the aircraft’s left hydraulic system. The Manual Release
System (MRS) is used to deploy the landing gear, if normal extension of the landing gear is inoperative. Landing gear position
monitoring is a provided by the Proximity Sensor System (PSS) and displayed through a combination of EICAS messages
and aural alerts.
Each of the main landing gear is equipped with self-adjusting multidisc carbon brakes. The left hydraulic system powers
the brakes of the inboard wheels, the right hydraulic system powers the brakes of the outboard wheels. Anti-skid control
and locked-wheel protection is provided. The PARK/EMER BRAKE operates both the inboard and outboard brakes, however,
anti-skid is not available when utilizing emergency brakes.
Associated subsystems include:
- Main Landing Gear and Doors
- Nose Landing Gear and Doors
- Gear Extension and Retraction System
- Manual Release System
- Steering Control System
- Proximity Sensing System
- EICAS Messages and Audio Alerts
- Brake System
CFO1501002_026
MAIN
LANDING
GEAR
NOSE
LANDING
GEAR
LANDING GEAR
Volume 2 Flight Crew Operating Manual Sep 13/2004
15-01-02 CSP 100-6 REV 1
PROXIMITY SENSING SYSTEM
DESCRIPTION
The Proximity Sensing System (PSS) consists of the Proximity Sensing Electronic Unit (PSEU) and proximity sensors.
The PSS sequences the landing gear operation. It also monitors the aircraft doors, thrust levers, and spoiler position.
COMPONENTS AND OPERATION
The PSEU receives data from the LANDING GEAR selector handle and various proximity sensors.The PSEU processes
the information to sequence the landing gear and program other aircraft configurations for flight and ground operations.
The PSEU also monitors the position of the landing gear, uplocks, and downlocks. It also electrically controls the hydraulic
selector valves during normal landing gear extension and retraction. After takeoff, the PSEU disables the normal brakes
and nose wheel steering systems. At touchdown, it re-arms the systems for use during the landing roll and taxi.
The sensors measure the physical relationship between two aircraft components. If the components are close, the sensors
provide a “near” signal. If the components are separated, a “far” signal is generated. The PSEU processes this information
to command landing gear and other aircraft systems operation.
NOTE: Dual proximity sensors, installed on each of the landing gear, supply the PSEU with weight-on-wheels (WOW)
information. The dual main landing gear WOW sensors and dual nose landing gear WOW sensors provide redundancy
if a failure of any one WOW proximity sensor fails.
LANDING GEAR POSITION AND WARNING SYSTEM
The status of the landing gear is determined by the PSEU using inputs from various proximity sensors. The resulting output
is sent to the EICAS which monitors the condition and position display of each item.
A GEAR DISAGREE caution message is posted if any of the following conditions occur:
- Any one gear remains in-transit for more than 28 seconds
- The position of at least one gear does not agree with landing gear control lever except during normal transit
- The landing gear control handle is left in the up position during manual extension
The gear down, in-transit, and disagree conditions are displayed as long as the condition exists. The gear and flaps display
is removed from the primary page 30 seconds after the flaps are retracted and the gear is up.
The AURAL — GEAR is non-mutable if the following conditions are met:
" Any of the gear not down and locked AND
" Radio Altimeter valid and Radio Altimeter < 500 feet AND
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