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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 engine.
E.3.5.2 Propeller vibration. The propeller vibration
stresses shall be determined and shall not exceed values that
have been found safe for operation within the operating limitations
established for the aeroplane.
E.3.5.3 Cooling. The cooling system shall be capable of
maintaining the temperature of powerplant components and
fluids within the established limits (see E.3.1) at ambient air
temperatures up to the maximum air temperature appropriate
to the intended operation of the aeroplane.
E.3.5.4 Associated systems. The fuel, oil, air induction,
and other systems associated with the power-unit shall be
capable of supplying each engine in accordance with its established
requirements, under all conditions affecting the functioning
of the systems (e.g. engine power or thrust, aeroplane
attitudes and accelerations, atmospheric conditions, fluid
temperatures) within the anticipated operating conditions.
E.3.5.5 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 f).
a) Isolation. Such regions shall be isolated by fireproof
material from other regions of the aeroplane where the
presence of fire would jeopardize continued flight,
taking into account the probable points of origin and
paths of propagation of fire.
b) Flammable fluids. Flammable fluid system components
located in such regions shall be fire resistant. Drainage of
each region shall be provided to minimize hazards
ANNEX 8 V-E-1 13/12/07
Annex 8 - Airworthiness of Aircraft
resulting from the failure of any component containing
flammable fluids. Means shall be provided for the crew
to shut off the flow of flammable fluids into such regions
if a fire occurs. Where sources of flammable fluid exist
in such regions, the whole of the related system within
the region, including supporting structure, shall be fire
proof or shielded from the effects of the fire.
C) Fire detection. A sufficient number of fire detectors
shall be provided and located to ensure rapid detection
of any fire that might occur in such regions of the
following aeroplane types: aeroplanes with more than
one power-unit powered by turbine or turbo-charged
engines, or aeroplanes where the engine(s) are not
readily visible from the cockpit.
SUB-PART F. SYSTEMS AND EQUIPMENT
F.1 General F.3 Safety and survival equipment
F.l.l The aeroplane shall be provided with approved
instruments, equipment and systems, including guidance and
flight management systems necessary for the safe operation of
the aeroplane in the anticipated operating conditions. These
shall include the instruments and equipment necessary to
enable the crew to operate the aeroplane within its operating
limitations. Instruments and equipment design shall consider
Human Factors principles.
Note 1.- Instruments and equipment additional to the
minimum necessary for the issuance of a Certificate of Airworthiness
are prescribed in Annex 6, Parts I and 11, for
particular circumstances or on particular kinds of routes.
Note 2.- For systems software assessment, see Sub-part H.
Note 3.- Guidance material on Human Factors principles
can be found in the Human Factors Training Manual
(Doc 9683) and in the Human Factors Guidelines for Air
Traffic Management (ATM) Systems (Doc 9758).
F.1.2 The design of the instruments, equipment and systems
required by F.l.l and their installation shall be such that:
a) an inverse relationship exists between the probability of
a failure condition and the severity of its effect on the
aircraft and its occupants, as determined by a system
safety assessment process;
b) they perform their function under all anticipated operating
conditions; and
C) electromagnetic interference between them is minimized.
F.1.3 Means shall be provided to warn the crew of unsafe
system operating conditions and to enable them to take corrective
action.
F.1.4 The design of the electrical power supply system
shall be such as to enable it to supply power loads during
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附件8--航空器适航性 Airworthiness of Aircraft(69)
