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PANEL
CB
LOCATION
NOTES
Windshield Wipers
WIPER PILOT DC BUS 1 1 G5
Wiper System WIPER C/PLT DC BUS 2 2 G5
Vol. 1 16--00--1
LANDING GEAR
Table of Contents REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
CHAPTER 16 --- LANDING GEAR
Page
TABLE OF CONTENTS 16--00--1
Table of Contents 16--00--1
INTRODUCTION 16--10--1
Introduction 16--10--1
NOSE AND MAIN LANDING GEAR 16--20--1
Nose and Main Landing Gear 16--20--1
Landing Gear Retraction 16--20--5
Landing Gear Extension 16--20--5
Alternate Landing Gear Extension 16--20--8
Wheels and Tires 16--20--8
Landing Gear Doors 16--20--8
PROXIMITY SENSING SYSTEM 16--30--1
Proximity Sensing System 16--30--1
System Circuit Breakers 16--30--5
BRAKE SYSTEM 16--40--1
Brake System 16--40--1
Parking Brake 16--40--4
Brake Temperature Monitoring System 16--40--6
Anti-Skid System 16--40--8
System Circuit Breakers 16--40--11
NOSE WHEEL STEERING SYSTEM 16--50--1
Nose Wheel Steering System 16--50--1
System Circuit Breakers 16--50--4
LIST OF ILLUSTRATIONS
INTRODUCTION
Figure 16--10--1 Landing Gear Assemblies 16--10--1
MAIN AND NOSE LANDING GEAR
Figure 16--20--1 Main Landing Gear 16--20--2
Figure 16--20--2 Nose Landing Gear 16--20--3
Figure 16--20--3 Landing Gear Retraction and Extension -- Schematic 16--20--4
Figure 16--20--4 Landing Gear Controls 16--20--6
Figure 16--20--5 Landing Gear EICAS Indications 16--20--7
Vol. 1 16--00--2
LANDING GEAR
Table of Contents REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
PROXIMITY SENSING SYSTEM
Figure 16--30--1 Proximity Sensing System -- Schematic 16--30--2
Figure 16--30--2 Landing Gear Position Indicator 16--30--3
Figure 16--30--3 Proximity Sensing System EICAS Indications 16--30--4
BRAKE SYSTEM
Figure 16--40--1 Brake System -- Schematic 16--40--2
Figure 16--40--2 Brake System EICAS Indications 16--40--3
Figure 16--40--3 Parking Brake Controls 16--40--4
Figure 16--40--4 Parking Brake EICAS Indications 16--40--5
Figure 16--40--5 BTMS Controls 16--40--6
Figure 16--40--6 BTMS EICAS Indications 16--40--7
Figure 16--40--7 Anti--Skid System Controls 16--40--9
Figure 16--40--8 Anti--Skid System EICAS Indications 16--40--10
NOSE WHEEL STEERING SYSTEM
Figure 16--50--1 Nose Wheel Steering System -- Schematic 16--50--2
Figure 16--50--2 Nose Wheel Steering EICAS Indications 16--50--3
Vol. 1 16--10--1
LANDING GEAR
Introduction REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. INTRODUCTION
The landing gear is a retractable tricycle type consisting of two wing root mounted main
landing gear assemblies and a forward fuselage mounted steerable nose landing gear
assembly. Each gear assembly has two wheels. The main landing gear assemblies retract
inboard and the nose landing gear assembly retracts forward. Each landing gear has a
shock strut to absorb and dissipate the shock loads encountered when the aircraft lands.
The main landing gear are fitted with steel multi-disc brakes.
Landing gear extension and retraction is electrically activated by the landing gear selector
lever and controlled by the proximity sensing electronic unit (PSEU). Sensors for the PSEU
are mounted on the landing gear and landing gear doors. The PSEU also provides landing
gear position indication on the EICAS display. The landing gear is hydraulically actuated by
hydraulic system 3, in normal operation. An alternate independent means of extending the
landing gear is available should the normal extension system fail.
A tail bumper protects the aircraft tail structure from tail strikes caused by over-rotation of the
aircraft on take-off. The tail bumper consists of a shock absorber, a skid assembly and a
strike indicator.
Landing Gear Assemblies
Figure 16---10---1
MAIN
LANDING
GEAR
TAIL BUMPER
NOSE
LANDING
GEAR
FORWARD
DOORS
GEAR
BAYS
MAIN
GEAR
DOOR
MAIN
GEAR
DOOR
AFT
DOOR
Vol. 1 16--10--2
LANDING GEAR
Introduction Sep 09/02
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 16--20--1
LANDING GEAR
Nose and Main Landing Gear REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. NOSE AND MAIN LANDING GEAR
Normal extension or retraction of the landing gear is initiated by landing gear control handle
selection. The retraction or extension signal is sent to the proximity sensing electronic unit
　
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