LEVEL II - ATA 27 Flight Controls

A380 TECHNICAL TRAINING MANUAL MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls

This document must be used for training purposes only

Under no circumstances should this document be used as a reference

It will not be updated.

All rights reserved No part of this manual may be reproduced in any form, by photostat, microfilm, retrieval system, or any other means, without the prior written permission of AIRBUS S.A.S.

A380 TECHNICAL TRAINING MANUAL

LEVEL II - ATA 27 FLIGHT CONTROLS

L1W06161 - L0KT0T0

Flight Controls System Description (2) . . . . . . . . . . . . . . . . . . . . . . . . 2 THS Actuator Bay Lights & Power Outlets Desc. (2) . . . . . . . . . . . . 16 Flight Control System OPS, CTL & IND (2) . . . . . . . . . . . . . . . . . . . 20 Component Location (2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls

TABLE OF CONTENTS

Apr 21, 2006 Page 1


FLIGHT CONTROLS SYSTEM DESCRIPTION (2) Primary Flight Controls System Architecture

L1W06161 - L0KT0T0 - LM27DVLEVEL0201

The primary flight control system has four blocks: - the CONTROL block with the pilot inputs (side sticks, rudder pedals...), - the COMPUTATION block with different computers as the PRIMary systems, the SEcondary Computers, the electrical backup system, and the Flight Control Data Concentrator (FCDC), - the ACTUATION block with the flight control surfaces, - and the INDICATING block with the monitoring displays (PFDs, SD, and EWD). Flight control computer reset P/BSWs are installed on the LH and RH side flight control panels 1211VM and 1212VM installed on the cockpit overhead panel. These reset P/BSWs are used for the software reset of the computers.


FLIGHT CONTROLS SYSTEM DESCRIPTION (2)

Apr 18, 2006 Page 2



PRIMARY FLIGHT CONTROLS SYSTEM - ARCHITECTURE MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 3


FLIGHT CONTROLS SYSTEM DESCRIPTION (2) Primary Flight Controls System (continued) Computer Power Supply


The PRIM1 and SEC1 are supplied by 28VDC (DC ESS BUS). The PRIM2 and SEC2 are supplied by 28 VDC (DC EHA) The PRIM3 and SEC3 are supplied by the 28VDC (DC BUS 1). The electrical backup system is powered by the green and yellow hydraulic system.



Apr 18, 2006 Page 4



PRIMARY FLIGHT CONTROLS SYSTEM - COMPUTER POWER SUPPLY MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 5


FLIGHT CONTROLS SYSTEM DESCRIPTION (2) Primary Flight Controls System (continued) Servo-Control Power Supply


The power supplies used by the servo-controls and the Trimmable Horizontal Stabilizer (THS) actuator are the two hydraulic circuits and three different electrical power sources: - AC ESS BUS (E1), - AC EHA (E2), - AC BUS 1 (E3).



Apr 18, 2006 Page 6



PRIMARY FLIGHT CONTROLS SYSTEM - SERVO-CONTROL POWER SUPPLY MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 7


FLIGHT CONTROLS SYSTEM DESCRIPTION (2) Primary Flight Controls System (continued) Cockpit Safety Devices


To prevent primary surfaces from moving, a lock pin is used to lock the side stick.



Apr 18, 2006 Page 8



PRIMARY FLIGHT CONTROLS SYSTEM - COCKPIT SAFETY DEVICES MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 9


FLIGHT CONTROLS SYSTEM DESCRIPTION (2) Secondary Flight Controls System Architecture The secondary flight control system has four blocks: - the CONTROL with pilot layout (slat flap lever + RESET C/B), - the COMPUTATION with two Slat Flap Control Computers (SFCCs), - the ACTUATION with the transmissions and surfaces, - the INDICATING with the Primary Flight Display (PFD). RESET C/Bs are installed on the 1231VM and 1222VM installed on the cockpit overhead panel. These RESET C/Bs are used for the software reset of the computers.

Computer Power Supply


The SFCC 1 is powered by 28VDC (DC ESS BUS). The SFCC 2 is powered by 28VDC (DC BUS 2).



Apr 18, 2006 Page 10



SECONDARY FLIGHT CONTROLS SYSTEM - ARCHITECTURE & COMPUTER POWER SUPPLY MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 11


FLIGHT CONTROLS SYSTEM DESCRIPTION (2) Secondary Flight Controls System (continued) Power Control Unit Supply


The flap Power Control Unit (PCU) hydraulic motors are powered by the green and yellow hydraulic circuits. The slat PCU hydraulic motor is powered by the green hydraulic circuit, and the electrical motor is powered by 115 VAC ESSential network.



Apr 18, 2006 Page 12



SECONDARY FLIGHT CONTROLS SYSTEM - POWER CONTROL UNIT SUPPLY MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 13


FLIGHT CONTROLS SYSTEM DESCRIPTION (2) Secondary Flight Controls System (continued) Cockpit Safety Devices


To prevent secondary surface from moving, a locking tool is used to lock the slat/flap control lever.



Apr 18, 2006 Page 14



SECONDARY FLIGHT CONTROLS SYSTEM - COCKPIT SAFETY DEVICES MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 15


THS ACTUATOR BAY LIGHTS & POWER OUTLETS DESC. (2) System Overview The Trimmable Horizontal Stabilizer (THS) bay has six Light Emitting Diode (LED) type lights installed in the bay floor and bay ceiling. The system also includes two 28 VDC power outlets to facilitate performance of the maintenance tasks in this area. The lights are controlled from a single toggle switch installed on the fuselage floor, on the LH of the bay access door (311AB). The service lights and the power outlets are energized from the 28 VDC GND SVCE BUS. Human factor point:

L1W06161 - L0KT0T0 - LM27DULEVEL0201

WARNING: BE CAREFUL WITH MOVING SURFACES, MOVEMENT OF SURFACES CAN KILL OR CAUSE INJURY TO PERSONS.


THS ACTUATOR BAY LIGHTS & POWER OUTLETS DESC. (2)

Apr 18, 2006 Page 16



SYSTEM OVERVIEW MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 17



SYSTEM OVERVIEW MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 18



This Page Intentionally Left Blank



Apr 18, 2006 Page 19


FLIGHT CONTROL SYSTEM OPS, CTL & IND (2)

L1W06161 - L0KT0T0 - LM27OVLEVEL0201

Primary Flight Controls



Apr 18, 2006 Page 20



PRIMARY FLIGHT CONTROLS MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 21


FLIGHT CONTROL SYSTEM OPS, CTL & IND (2) Primary Flight Controls (continued) General Operation, Control & Indication NOTE: Note: No more control wheel.


WARNING: Flight control surface movement



Apr 18, 2006 Page 22



PRIMARY FLIGHT CONTROLS - GENERAL OPERATION, CONTROL & INDICATION MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 23


FLIGHT CONTROL SYSTEM OPS, CTL & IND (2) Primary Flight Controls (continued) Flight Control Computer Status and Reset


WARNING: BCM activated if all computers OFF + one hydraulic circuit pressurized.



Apr 18, 2006 Page 24



PRIMARY FLIGHT CONTROLS - FLIGHT CONTROL COMPUTER STATUS AND RESET MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 25


FLIGHT CONTROL SYSTEM OPS, CTL & IND (2) Secondary Flight Controls General Operation, Control & Indication


WARNING: Flight control surface movement, risk of interference between slat or droop nose and engine cowling.



Apr 18, 2006 Page 26



SECONDARY FLIGHT CONTROLS - GENERAL OPERATION, CONTROL & INDICATION MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 27


FLIGHT CONTROL SYSTEM OPS, CTL & IND (2) Secondary Flight Controls (continued)


Slat/Flap Control Computer Status And Reset



Apr 18, 2006 Page 28



SECONDARY FLIGHT CONTROLS - SLAT/FLAP CONTROL COMPUTER STATUS AND RESET MAINTENANCE COURSE - T1 & T2 (RR / Metric) LEVEL II - ATA 27 Flight Controls


Apr 18, 2006 Page 29


COMPONENT LOCATION (2) Primary Flight Controls

L1W06161 - L0KT0T0 - LM27CVLEVEL0201

Secondary Flight Controls


COMPONENT LOCATION (2)

Apr 18, 2006 Page 30


L1W06161 - L0KT0T0 - LM27CVLEVEL0201

This Page Intentionally Left Blank


COMPONENT LOCATION (2)

Apr 18, 2006 Page 31

AIRBUS S.A.S. 31707 BLAGNAC cedex, FRANCE STM REFERENCE L1W06161 APRIL 2006 PRINTED IN FRANCE AIRBUS S.A.S. 2006 ALL RIGHTS RESERVED AN EADS JOINT COMPANY WITH BAE SYSTEMS

LEVEL II - ATA 27 Flight Controls

Recommend Documents