AMC E 210 Failure Analysis

(1)The Failure analysis would normally include investigation of those Engine components that could affect the functioning and integrity of the major rotating assemblies, and for the control system, all manual and automatic controls such as refrigerant injection system, Engine and fuel system speed governors, Engine over-speed limiters, Propeller control systems, Propeller thrust reversal systems, etc., as applicable.

(2)Unless the effects can be shown to be adequately mitigated in the assumed installation, and appropriate assumptions are detailed in the Engine instructions for installation (as required under CS-E 30), the Failure effects considered to lead to unsafe Engine conditions beyond the normal control of the flight crew should include, but not necessarily be limited to, the following ones: — non-containment of high-energy debris, — uncontrolled fire, — Failure of the Engine mount system leading to inadvertent Engine separation, — release of the Propeller by the Engine, — significant thrust in the opposite direction to that commanded by the pilot (e.g. unintended movement of the Propeller blades below the established minimum in-flight low-pitch position), — complete inability to shut the Engine down.

(3)The analysis should take into account the effects of Failures of components that are part of the Engine type design on components that are not part of the Engine type design, and vice versa.

(4)The Failure of individual components of the Engine and its installation need not be included in the analysis if the Agency accepts that the possibility of such Failure is sufficiently remote.

[Amdt. No.: E/1]