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materials used in its manufacture, including cabin
interior furnishing materials replaced during major
refurbishing, shall be such as to minimize the possibility
of in-flight and ground fires and also to minimize the
production of smoke and toxic gases in the event of a
fire. Means shall be provided to contain or to detect and
extinguish, wherever possible, all accessible fires as
might occur in such a way that no additional danger to
the helicopter is caused.
0 Incapacitation of occupants. Design precautions shall be
taken to protect against possible instances of cabin
depressurization and against the presence of smoke or
other toxic gases that could incapacitate the occupants of
the helicopter.
4.1.7 Ernergenc y landing provisions
Provisions shall be made in the design of the helicopter
to protect the occupants from fire and effects of deceleration
in the event of an emergency landing. Facilities shall be
provided for the rapid evacuation of the helicopter in
conditions likely to occur following an emergency landing.
Such facilities shall be related to the passenger and crew
capacity of the helicopter. On helicopters certificated for
ditching conditions, provisions shall also be made in the
design to give maximum practicable assurance that safe
evacuation from the helicopter of passengers and crew can be
executed in case of ditching.
4.1.8 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 helicopter essential for its safe operation. The protection
that any limitations and instructions for such operations might
provide may be taken into account.
CHAPTER 5. ENGINES
5.1 Scope 5.4 Tests
The Standards of Chapter 5 shall apply to engines of all types An engine of the type shall complete satisfactorily such tests
that are used on the helicopter as primary propulsion units. as are necessary to verify the validity of the declared ratings,
conditions and limitations and to ensure that it will operate
satisfactorily and reliably. The tests shall include at least the
following:
5.2 Design, construction
and functioning
The engine complete with accessories shall be designed and
constructed so as to function reliably within its operating
limitations under the anticipated operating conditions when
properly installed in the helicopter in accordance with
Chapter 6 and with the suitable rotor and power transmission
installed.
53 Declared ratings, conditions
and limitations
The power ratings and the conditions of the atmosphere upon
which they are based and all operating conditions and limitations
which are intended to govern the operation of the
engine shall be declared.
a) Power calibration. Tests shall be conducted to establish
the power characteristics of the engine when new and
also after the tests in b) and c). There shall be no
excessive decrease in power at the conclusion of all the
tests specified.
b) Operation. Tests shall be conducted to ensure that
starting, idling, acceleration, vibration, overspeeding and
other characteristics are satisfactory and to demonstrate
adequate margins of freedom from detonation, surge or
other detrimental conditions as may be appropriate to the
particular type engine.
C) 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 engine. They shall
also include operation under conditions in excess of the
declared limits to the extent that such limitations might
be exceeded in actual service.
ANNEX 8 IVA -5-1
CHAPTER 6. ROTOR AND POWER TRANSMISSION SYSTEMS
AND POWERPLANT INSTALLATION
6.1 General
The powerplant installation, including rotor and power transmission
system, shall comply with the Standards of Chapter 4
and with the Standards of this chapter.
6.2 Design, construction
and functioning
The rotor and power transmission systems assembly complete
with accessories shall be designed and constructed so as to
function reliably within its operating limitations under the
anticipated operating conditions when properly fitted to the
engine and installed in the helicopter in accordance with this
chapter.
63 Declared ratings, conditions
and Limitations
The power ratings and all operating conditions and limitations
which are intended to govern the operation of the rotor and
power transmission systems shall be declared.
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附件8--航空器适航性 Airworthiness of Aircraft(48)
