scope:

GENERAL - INSTALLATIONS AND TESTING UNDER GROUND AND FLIGHT CONDITIONS

The requirements of this part of the section, clauses 5.1.1 to 5.1.102, are applicable to the design and construction of all turbine engine propulsion system installations including all the equipment and sub-systems necessary for the satisfactory operation of the engine.

The Aeroplane designer shall be responsible for the propulsion system installation and shall be responsible for carrying out liaison with the engine and equipment manufacturers to ensure compatibility of the operating characteristics and limitations of all equipment included in the propulsion system.

For each propulsion system installation an analysis shall be completed in accordance with the requirements of MAP RA 1200 series and Def Stan 00- 56 Part 3 Requirements (Air Sector) to ensure that no failures will jeopardise the safe operation of the aeroplane. Structural element failures need not be considered if it can be shown that such failures are extremely unlikely.

Components in the propulsion system not approved as part of the engine shall be designed in accordance with Part 1, Section 3, Clause 3.1 and graded as defined in Clauses Part 1, Section 4, Clauses 4.1.2 to 4.1.7

Each Auxiliary Power Unit (APU) must meet the applicable provisions of this Section.

The composition of an Engine Change Unit (ECU) shall be as detailed in the engine specification.

Where the requirements of this section impose severe and unavoidable penalties or constraints on the aeroplane design, their applicability shall be decided by the Project Team Leader who will carry out the necessary consultations.