BS G 248:1993

National foreword
Committees responsible
Specification
1. Scope
2. Normative references
3. Definitions
4. General characteristics
5. Design characteristics
6. Operating characteristics
7. Environmental conditions and test procedures
8. Qualification tests
Tables
1. Strength of threaded terminals (static value of
     pull and torque)
2. Strength of threaded mounting studs (static value
     of pull and torque)
3. Controller rating and associated wire size for
     testing
4. Endurance tests for controllers
5. Endurance tests for circuit breakers
6. Contact voltage drop
7. Trip characteristics
8. Prospective short-circuit calibration currents
9. Environmental conditions and test procedures
10. Qualification tests
Figures
1. Diagrammatic illustration of a type A hybrid remote
     power controller
2. Diagrammatic illustration of a type B hybrid remote
     power controller
3. Timing sequence diagram

Specifies the general design and performance requirements of hybrid remote power controllers for aircraft. Includes definitions, tables and diagrams.

This International Standard specifies the general design and performance requirements of hybrid remote power controllers for aircraft. They consist of an electromagnetic device or a combined electromagnetic/solid-state device, for load switching, and a solid-state control circuit for control of the load-switching devices.

On aircraft, remote power controllers are used to close and open the electrical circuit and to protect wiring and equipment in the event of overload or short-circuit conditions.

The load-switching device and solid-state control circuit may be mounted in a common enclosure or may be discrete inter-connected units.

NOTE 1 This International Standard recognizes the need to have hybrid units which are, as far as practical, interface-compatible with fully solid-state power controllers.