a. The EEC is designed to accept external software loading.
b. The EEC is certified as part of an engine.
c. The support equipment is qualified in accordance with procedures set forth by the engine (and aircraft, if necessary) certifying authority if the EEC cannot detect an integrity violation of the loaded program.
The software to be loaded has been approved by the engine and aircraft certifying authorities.
One or more configurations of EEC hardware has been identified for each version of software which is to be loaded in the EEC.
It is appropriate to use these guidelines in the initial development phase, although the certification issues would not be applicable.
Approval as used herein means approval by the engine (and aircraft, if necessary) certifying authority. There are cases where the engine may commence certification activities and no specific aircraft application has been identified. In these cases, the aircraft certification authority should be notified of the EEC''s external software loading capability when the engine''s application is identified. The appropriate documentation can be delivered to the aircraft certifying authority at that time.