Flight Path Deviation Indicator

Technical Information

Catalogue No: C1314
Category: Navigation/Inertial
Object Type: Indicator/Instrument
Object Name: Flight Path Deviation Indicator
Part No: 7233-3A14D2
Serial No: 104111
Manufacturer: Bendix
Division: Eclipse-Pioneer [of Bendix]
Platform(s):
Year of Manufacture: circa 1965
Dimensions:
Width (mm):
102 
Height (mm):
102 
Depth (mm):
248 
Weight (g):
2,620 
Location: Archive Object Store
Inscription(s):

Indicator, Flight Path Deviation
TSO-C52 SAE-AS420
TSO-C6c SAE-AS3999A
Wt. 5.5LBS
Type No. 7233-3A14D2
Serial No. 104111
Bendix
The Bendix Corporation
Eclipse-Pioneer Division
Teterboro, New Jersey
Made in USA
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Modification Record
-2, -3, --4, -6, -8, -9, 10, -11, -12, -13, -14, -15, FG2327, FA66557
The Bendix Corporation
Navigation & Control Division
Teterboro, New Jersey
────────────────
[maintenance mark]
EBLO 10.80

Notes:

The course deviation indicator has a rotating compass card behind a fixed aircraft silhouette and lubber line. A marker and digital counter may be used to set desired course against the compass card and a heading marker is provided. Linked with the course marker and occupying the centre of the dial is a left/right needle which provides simple VOR/ILS deviation information. It rotates with the course marker to give a semi-pictorial indication of the relationship of the aircraft to a VOR or ILS beam. A normal glide-slope deviation needle remains horizontally aligned. The pilot thus has a "straight" plan-position indicator and a computing director instrument.

The flight director computes and displays the proper pitch and bank angles required for the aircraft to follow a selected flight path. The flight director instrument system on the VC10 is considered as an alternative to the autopilot for all modes except automatic flare-out and for this reason is integrated with the automatics to only a limited extent. It derives its attitude and compass signals respectively from the main vertical gyros and Polar Path compasses and takes radio information from either group of radio receivers.

These signals are electrically separated from the autopilot as far as is practicable. The system is of necessity duplicated in that each pilot has his own course deviation indicator and horizon director indicator but only a single flight steering computer is provided. The attitude displays have independent absolute monitors consisting of circuits which check the vertically of the gyro and the continuity and operation of the transmission system. Failure warning is by a flag in the horizon indicator. Additionally there are comparator units between the horizon displays and between the compass systems which illuminate warning lights in the event of a difference between the two sides. Comparison is effected mechanically through torque synchros so that electrical isolation between the systems is maintained.

The system, supplied by Elliott Brothers (London) Ltd, is based largely on components of the well-proved Bendix PB-20 autopilot, made under licence by Elliott, and interchangeable with American built components as installed in Boeing 707s.

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