DESCRIPTION
General 15−10−1
Landing Gear 15−10−1
Description 15−10−1
Components 15−10−2
Operation 15−10−5
Proximity Sensing Electronic Unit (PSEU) 15−10−10
Description 15−10−10
Operation 15−10−10
Main Wheel Bins and Overheat Detection 15−10−11
Description 15−10−11
Components and Operation 15−10−11
Nose Wheel Steering System 15−10−11
Description 15−10−11
Components and Operation 15−10−12
Wheels and Brakes 15−10−14
Description 15−10−14
Components and Operation 15−10−14
Controls and Indicators 15−10−17
EICAS Messages 15−10−19
SUMMARY
Power Supply and Circuit Breaker Summary 15−20−1
LIST OF ILLUSTRATIONS
DESCRIPTION
Figure 15−10−1 Landing Gear 15−10−1
Figure 15−10−2 Main Landing Gear 15−10−3
Figure 15−10−3 Nose Gear 15−10−5
Figure 15−10−4 Normal Gear Extension 15−10−7
Figure 15−10−5 Alternate Gear Extension 15−10−9
Figure 15−10−6 MLG BAY OVHT TEST Switches 15−10−11
Figure 15−10−7 Steering Tiller 15−10−13
LANDING GEAR
Table of Contents
Vol. 2 15−00−1
Oct 05/06
CHAPTER 15 - LANDING GEAR
15−00−1
CL−605 Flight Crew Operating Manual
PSP 605−6
TABLE OF CONTENTS
Page
TABLE OF CONTENTS
LIST OF ILLUSTRATIONS
DESCRIPTION
Figure 15−10−8 Brakes and Lower Main Gear Structure 15−10−15
Figure 15−10−9 HYDRAULIC Synoptic Page (Inboard and Outboard Brake
Pressure) 15−10−15
Figure 15−10−10 PARKING BRAKE Handle 15−10−16
Figure 15−10−11 Landing Gear Panel 15−10−17
Figure 15−10−12 Landing Gear Manual Release 15−10−17
Figure 15−10−13 Landing Gear EICAS Page 15−10−18
LANDING GEAR
Table of Contents
Vol. 2 15−00−2
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
Page
GENERAL
The landing gear for the Challenger 605 is arranged in a standard retractable tricycle configuration.
Associated subsystems include:
• Proximity sensing system;
• Nose gear doors;
• Nosewheel steering;
• Wheel brakes with anti-skid; and
• Main landing gear overheat detection.
Hydraulic system 3 powers landing gear extension and retraction, nosewheel steering, and brakes.
Landing Gear
Figure 15−10−1
LANDING GEAR
Description
The main landing gear consists of two trailing link-type assemblies. The main landing gear retracts
inward towards the centerline of the fuselage. The main landing gear is hydraulically actuated by
hydraulic system 3, and electrically controlled by the proximity sensing electronic unit (PSEU).
The nose gear is a forward retracting assembly. The nose gear and forward nose gear doors are
hydraulically actuated by hydraulic system 3, and electrically controlled by the PSEU.
A manual landing gear extension feature is provided.
LANDING GEAR/BRAKES
Description
Vol. 2 15−10−1
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
LANDING GEAR (CONT'D)
Components
Main Landing Gear (MLG)
Each main gear assembly consists of:
• Main beam;
• Nitrogen-charged/oil-filled shock strut;
• Trailing link;
• MLG actuator;
• Internal downlock mechanism;
• Axle, brake, and wheel assemblies;
• Uplock pins;
• MLG doors; and
• Weight-on-wheels proximity sensors.
Main Wheel Bins
Each main gear assembly retracts inward into wheel bins recessed in the main landing gear
bay. Each wheel contains a single-loop overheat detection wire, to provide an EICAS warning
should a wheel overheat occur.
MLG Uplocks and Downlocks
The MLG is held in the up-and-locked position by mechanical uplocks. With the gear extended,
internal locking mechanisms within the MLG actuators lock the gear in the down position. On
the ground, MLG ground locking pins can be inserted into the MLG actuator.
MLG Doors
MLG doors, mechanically attached to each of the MLG struts, allow for partial enclosure of the
gear when retracted. In the retracted position, brush seals on the door and wheel bins provide
　
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