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D.5.2 The aeroplane shall also be protected against
catastrophic effects of lightning. Due account shall be taken of
the material used in the construction of the aeroplane.
D.6 Emergency landing provisions
D.6.1 Provisions shall be made in the design of the aeroplane
to protect the occupants, in the event of an emergency
landing, from fire and from the direct effects of deceleration
forces as well as from injuries arising from the effect of
deceleration forces on the aeroplane's interior equipment.
D.6.2 Facilities shall be provided for the rapid evacuation
of the aeroplane in conditions likely to occur following an
emergency landing. Such facilities shall be related to the
passenger and crew capacity of the aeroplane and shall be
shown to be suitable for their intended purpose.
D.6.3 The interior layout of the cabin and the position and
number of emergency exits, including the means of locating
and illuminating the escape paths and exits, shall be such as to
facilitate rapid evacuation of the aeroplane in conditions likely
to occur following an emergency landing.
D.6.4 On aeroplanes certificated for ditching conditions,
provisions shall be made in the design to give maximum
practicable assurance that safe evacuation from the aeroplane
of passengers and crew can be executed in case of ditching.
D.7 Ground handling
Adequate provisions shall be made in the design to minimize
the risk that ground-handling operations (e.g. towing, jacking)
may cause damage, which could pass unnoticed, to the parts of
the aeroplane essential for its safe operation. The protection
that any limitations and instructions for such operations might
provide may be taken into account.
SUB-PART E. POWERPLANT
E.l Engines E.3.4 Engine restarting
The Standards of Part VI of this Annex shall apply to each Means shall be provided for restarting an engine in flight at
engine that is used on the aeroplane as a primary propulsion altitudes up to a declared maximum altitude.
unit.
E.2 Propellers E.3.5 Arrangement and functioning
The Standards of Part VII of this Annex shall apply to each
propeller that is used on the aeroplane. E.3.5.1 Independence of power-units
E3 Powerplant installation
E.3.1 Compliance with engine and
propeller limitations
The powerplant shall be arranged and installed so that each
power-unit 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
power-unit.
The powerplant installation shall be so designed that the
engines and propellers (if applicable) are capable of functioning
reliably in the anticipated operating conditions. In condi- E.3.5.2 propeller vibration
tions established in the flight manual, the aeroplane shall be
capable of being operated without exceeding the limitations The propeller vibration stresses shall be determined and shall
established for the engines and propellers in accordance with not exceed values that have been found safe for operation
this sub-part. within the operating limitations established for the aeroplane.
E.3.2 Control of engine rotation
E.3.5.3 Cooling
In those installations where continued rotation of a failed
engine would increase the hazard of fire or of a serious struc- The cooling system shall be capable of maintaining the
tural failure, means shall be provided for the crew to stop the temperature of powerplant and fluids within the
rotation of the engine in flight or to reduce it to a safe level. established limits (see E.3.1) at ambient air temperatures up to
the maximum air temperature appropriate to the intended oper-
E.3.3 Turbine engine
For a turbine engine installation:
a) the design shall minimize the hazards to the aeroplane in
the event of failure of engine rotating parts, or an engine
fire which burns through the engine case; and
b) the power-unit together with the associated engine
control devices, systems and instrumentation shall be
designed to give reasonable assurance that those engine
operating limitations that adversely affect the structural
integrity of rotating parts shall not be exceeded in
service.
- - -
ation of the aeroplane. The maximum and, if necessary,
minimum ambient air temperature for which the powerplant
has been established as being suitable shall be scheduled in the
flight manual.
E.3.5.4 Associated systems
The fuel, oil, air induction, and other systems associated with
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附件8--航空器适航性 Airworthiness of Aircraft(37)
