ED
Decision 2020/001/R
(See AMC 25.933)
(a) For turbojet reversing systems:
(1) Each system intended for ground operation
only must be designed so that either:
(i) The aeroplane can be shown to be capable
of continued safe flight and landing during and after any thrust reversal in
flight; or
(ii) It can be demonstrated that any in-flight thrust reversal
complies with CS 25.1309(b).
(See AMC 25.933(a)(1))
(2) Each system intended for inflight use must
be designed so that no unsafe condition will result during normal operation of
the system, or from any failure (or reasonably likely combination of failures)
of the reversing system, under any anticipated condition of operation of the
aeroplane including ground operation. Failure of structural elements need not
be considered if the probability of this kind of failure is extremely remote.
(3) Each system must have means to prevent the
engine from producing more than idle thrust when the reversing system
malfunctions, except that it may produce any greater forward thrust that is
shown to allow directional control to be maintained, with aerodynamic means
alone, under the most critical reversing condition expected in operation.
(b) For propeller reversing systems:
(1) Each system intended for ground operation
only must be designed so that no single failure (or reasonably likely
combination of failures) or malfunction of the system will result in unwanted
reverse thrust under any expected operating condition. Failure of structural
elements need not be considered if this kind of failure is extremely remote.
(2) Compliance with this paragraph may be
shown by failure analysis or testing, or both, for propeller systems that
allow propeller blades to move from the flight low-pitch position to a
position that is substantially less than that at the normal flight low-pitch
position. The analysis may include or be supported by the analysis made to
show compliance with the requirements of CS-P 70 for the propeller and
associated installation components.
[Amdt
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