Autopilot and Flight Director Computer

Technical Information

Catalogue No: C0610
Category: Flight Control
Object Type: Signal/Data Processor
Object Name: Autopilot and Flight Director Computer
Part No: 41-0001-01
Serial No: 04
Manufacturer: Elliott/SFENA Consortium
Division: Unknown
Platform(s): Concorde 
Year of Manufacture: circa 1967
Dimensions:
Width (mm):
123 
Height (mm):
206 
Depth (mm):
554 
Weight (g):
10,080 
Location: Archive Object Store
Inscription(s):

Elliott SFENA
Consortium Design
Elliot Bros (London) Ltd
Rochester Kent England
Unit: A/P&F/D.Pitch Computer.
Type:
Serial:
Code 66-266-236-00

Notes:

Computing circuits and power packs which constitute the Concorde automatic flight control system were packed into eight basic computers ( 2 off each), namely:
● Autopilot and Flight Director Pitch Computer;
● Autopilot and Flight Director Azimuth Computer;
● Autostabiliser Computer;
● Autothrottle Computer;
● Electric Pitch Trim Computer;
● Warning and Landing Display Computer;
● Safety Flight Control Computer;
● Item Computer.

The computing circuits were split into modules which are arranged in stacks either side of the chassis assembly. These stacks were located together by plugs which also provide a means of inter-connecting the individual modules and connecting the modules to a mother-board mounted on the chassis. These mother-boards were connected to the cableforms which run to the rear aircraft connectors and front test connectors.

The box was physically segregated in to command and monitor computing areas to preclude common failures. The solid state logic switching circuitry was incorporated in the centre segregation spline.
The electronic implementation was based on standardised micro-electronic linear computing elements with external components to set gain and transfer functions. Electromechanical integrators were eliminated and digital integration was used when long term storage of datums was required. All switching was solid state except where total electrical isolation or filament drivers were involved.

The computers included built-in test circuitry which was aimed at satisfying airworthiness requirements prior to take-off and fulfilling the first line maintenance objectives. Additional test points are provided on the front of the computer to facilitate fault location to module level at the intermediate servicing stage.

The barely legible, hand-written paper label seems to read: Concorde; FCSD ELS

The visible module's part numbers are:
7622-00010 (Manometric)
7622-00011 (Common Services)
7622-00014 (Altitude Command)
7622-00014/15 (Altitude Command/Monitor)
7726-00001 (Digital Integrator Computing Assembly)

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