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satisfactorily and reliably within the declared ratings,
conditions and limitations. The tests shall include at least the
following:
a) Operation. Tests shall be conducted to ensure that
strength and vibration characteristics are satisfactory
and to demonstrate proper and reliable functioning of
pitch changing and control mechanisms and free wheel
mechanisms. Overspeed characteristics shall be demonstrated
to be satisfactory for helicopters of maximum
certificated take-off mass greater than 3 175 kg; and
b) Endurance. Tests of sufficient duration shall be conducted
at such powers, engine and rotor speeds, and other
operating conditions as are necessary to demonstrate
reliability and durability of the rotors and rotor drive
systems.
E.2.5 Compliance with engine, rotor and rotor
drive system limitations
The powerplant installation shall be so designed that the
engines, rotors and rotor drive systems are capable of functioning
reliably in the anticipated operating conditions. In conditions
established in the flight manual, the helicopter shall be capable
of being operated without exceeding the limitations established
for the engines, rotors and rotor drive systems in accordance
with this sub-part and Part VI.
E.2.6 Control of engine rotation
For helicopters of a maximum certificated take-off mass
greater than 3 175 kg and for helicopters which are certificated
ANNEX 8 IVB-E-1 13/12/07
Annex 8 - Airworthiness of Aircraft Part IVB
to Category A Standard, where continued rotation of a failed
engine would increase the hazard of fire or of a serious structural
failure, means shall be provided for the crew to stop the
rotation of the failed engine in flight or to reduce it to a safe
level.
E.2.7 Engine restarting
For helicopters of a maximum certificated take-off mass
greater than 3 175 kg and for helicopters which are certificated
to Category A Standard, a means shall be provided for restarting
an engine in flight at altitudes up to a declared maximum
altitude.
E.2.8 Arrangement and functioning
E.2.8.1 Independence of engines. For Category A helicopters,
the powerplant shall be arranged and installed so that
each engine together with its associated systems is capable of
being controlled and operated independently from the others
and so that there is at least one arrangement of the powerplant
and systems in which any failure, unless the probability of its
occurrence is extremely remote, cannot result in a loss of more
power than that resulting from complete failure of the critical
engine.
E.2.8.2 Rotors and rotor drive systems vibration. The
vibration stresses for the rotors and rotor drive systems shall
be determined and shall not exceed values that have been
found safe for operation within the operating limitations
established for the helicopter.
E.2.8.3 Cooling. The cooling system shall be capable of
maintaining powerplant temperatures within the established
limits (see E.2.5) at all ambient temperatures approved for
operation of the helicopter. The maximum and minimum
ambient air temperatures for which the powerplant has been
established as being suitable shall be scheduled in the flight
manual.
E.2.8.4 Associated systems. The fuel, oil, air induction,
and other systems associated with each engine, rotor drive
system and rotor, shall be capable of supplying the appropriate
unit in accordance with its established requirements, under all
conditions affecting the functioning of the systems (e.g. engine
power setting, helicopter attitudes and accelerations, atmospheric
conditions, fluid temperatures) within the anticipated
operating conditions.
E.2.8.5 Fire protection. For regions of the powerplant
where the potential fire hazards are particularly serious
because of the proximity of ignition sources to combustible
materials, the following shall apply in addition to the general
Standard of D.2 e).
a) Isolation. Such regions shall be isolated by fire resistant
material from other regions of the helicopter where the
presence of fire would jeopardize continued flight and
landing (helicopters of a maximum certificated take-off
mass greater than 3 175 kg or Category A) or would
jeopardize safe landing (other helicopters), taking into
account the probable points of origin and paths of propagation
of fire.
b) Flammable jluids. Flammable fluid system components
located in such regions shall be fire resistant. Drainage
of each region shall be provided to minimize hazards
resulting from the failure of any component containing
flammable fluids. Means shall be provided for the crew
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附件8--航空器适航性 Airworthiness of Aircraft(58)
