MODUK - DEF STAN 00-970: V2 P7
Design and Airworthiness Requirements for Service Aircraft Volume 2 - Rotorcraft Book 3 (Parts 7 to 10) Part 7: Installations
|Publication Date:||10 March 1998|
The requirements of this Chapter 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 rotorcraft 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 a failure mode and effects analysis (FMEA) shall be completed to ensure that no single failure or probable combination of failures will jeopardise the safe operation of the rotorcraft. (Failure of structural elements need not be considered if the probability of such failures is extremely remote as defined in Chapter 117 (in preparation - JAC Paper 1169 1).
Components in the propulsion system not approved as part of the engine shall be designed in accordance with Chapter 200 and graded as defined in Chapter 400, para 2.
Each Auxiliary Power Unit (APU) must meet the applicable provisions of this Chapter.
The composition of an Engine Change Unit (ECU) shall be as detailed in the engine specification.
Where the requirements of this Chapter impose severe and unavoidable penalties or constraints on the rotorcraft design, their applicability shall be decided by the Rotorcraft Project Director who will carry out the necessary consultations.