GM1 21L.A.273(c) Production control system

TESTS

If relevant, the natural or legal person that produces under Subpart R should perform functional, ground and flight tests of the manufactured products.

The production ground and flight tests for a new aircraft are specified by the declarant of the declaration of design compliance. These tests typically include:

— a check on the handling qualities;

— a check on flight performance (using normal aircraft instrumentation);

— a check on the proper functioning of all aircraft equipment and systems;

— a determination that all instruments are properly marked, and that all placards and required flight manuals are installed before the flight test;

— a check of the operational characteristics of the aircraft on the ground; and

— a check on any other items peculiar to the aircraft being tested.

For production flight-test activities, the natural or legal person that produces under Subpart R may consider establishing a flight test operations manual (FTOM) (refer to AMC1 21L.A.127(b) and to point 21L.A.177(b)).

If the design compliance of the engine is covered by the declaration of the aircraft design compliance, then the declarant of the aircraft design compliance should also provide the specifications for the functional test required for a new engine. These will normally include at least the following:

— break-in runs that include the determination of fuel and oil consumption and the determination of power characteristics at rated maximum continuous power and, if applicable, at rated take-off power;

— a period of operation at rated maximum continuous power; for engines that have a rated take-off power, part of that period should be at rated take-off power.

The test equipment used for the test run should be capable of an output determination of accuracy sufficient to assure that the engine output delivered complies with the specified rating and operational limitations.

If the design compliance of the propeller is covered by the declaration of the aircraft design compliance, then the declarant of the aircraft design compliance should also provide the specifications for the functional test required for a new propeller. These will normally include several complete cycles of control throughout the propeller pitch and rotational speed ranges. In addition, for feathering and/or reversing propellers, several cycles of feathering operation and reversing operation from the lowest normal pitch to the maximum reverse pitch should normally be required.

After functional testing, each engine or propeller will need to be inspected to determine that the engine or propeller is in condition for safe operation. Such inspections are specified by the declarant of the aircraft design compliance and are normally including internal inspection and examination.
The degree of internal inspections should normally be determined on the basis of the positive results of previous inspections conducted on the first-produced engine or propeller, and on the basis of in-service experience.