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GF1510_006
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005

LANDING GEAR
 
LANDING GEAR ELECTRONIC CONTROL UNIT (LGECU)
The Landing Gear Electronic Control Unit (LGECU) consists of two sub-systems which perform:
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All landing gear control and indication, including WOW.

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Landing gear and landing gear door operations.

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Control, indication and fuselage door status functions (refer to AIRPLANE GENERAL Chapter 1 for fuselage door indications).

LGECU SYSTEM SCHEMATIC

Rev 2A, Apr 11, 2005 Flight Crew Operating Manual  Volume 2

LANDING GEAR
 
LGECU CONTROL
The LGECU receives gear position commands (current or new) from the landing gear control handle in the flight compartment. The handle is compared with actual gear position and WOW for each landing gear assembly. The landing gear system includes proximity sensors for gear and door positioning and locked position monitoring.
The EICAS monitors the information received from the LGECU and generates status and warning messages when certain conditions are met.
The landing gear door, control and indications system provides three basic functions:
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Landing gear sequencing control . The system performs logic on handle position, landing gear and door positions, WOW and gear lock inputs. It provides the signals that command the landing gear, landing gear door and lock actuators that change the position of the landing gear based on this input logic.

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Landing gear, door and fuselage door position indication . The system monitors door position inputs, landing gear door inputs, landing gear position inputs and provides indication of the position status of airplane doors and landing gear.

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Weight-On-Wheels indication . The system monitors landing gear strut compression (sensor input) and provides indication of the air or ground status of the airplane. Weight-On-Wheel sensors on each landing gear assembly report to the LGECU and are divided into two classifications, WOW 1 and WOW 2 inputs. In addition, the system monitors its own circuitry and provides fault information to the central airplane information maintenance system or CAIMS and/or EICAS system.

The LGECU is divided into two sub-systems which provide control and indication to the landing gear system.
Sub-system A functions include:
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WOW #1 (WOW sensor input logic).

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Landing gear control and secondary position indication.

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Landing gear door control.

Sub-system B functions include:
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WOW #2 (WOW sensor input logic).

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Landing gear primary position indication.

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Landing gear door indication.
　
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