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the aeroplane essential for its safe operation. The protection
that any limitations and instructions for such operations might
provide may be taken into account.
5.1 Scope
CHAPTER 5. ENGINES
5.4 Tests
The Standards of Chapter 5 shall apply to engines of all types
that are used on the aeroplane as primary propulsion units.
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 aeroplane in accordance with
Chapter 7 and, if applicable, fitted with a suitable propeller.
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.
An engine of the type shall complete satisfactorily such tests
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:
a) Power calibration. Tests shall be conducted to establish
the power or thrust 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, thrust, 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
CHAPTER 6. PROPELLERS
6.1 Scope
The Standards of Chapter 6 shall apply to propellers of all
types.
6.2 Design, construction and functioning
The propeller 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
aeroplane in accordance with Chapter 7.
6.3 Declared ratings, conditions and limitations
The power ratings and all operating conditions and limitations
which are intended to govern the operation of the propeller
shall be declared.
6.4 Tests
A propeller of the type shall complete satisfactorily such tests
as are necessary to ensure that it will operate 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 vibration and overspeeding characteristics are
satisfactory and to demonstrate proper and reliable
functioning of pitch changing and control mechanisms.
b) Endurance. Tests of sufficient duration shall be
conducted at such powers, speeds and other operating
conditions as are necessary to demonstrate reliability
and durability of the propeller.
ANNEX 8
CHAPTER 7. POWERPLANT INSTALLATION
7.1 General
7.1.1 Applicable Standards
7.2.2 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.
The powerplant installation shall comply with the Standards of
Chapter 4 and with the Standards of this chapter.
7.2.3 Cooling
7.1.2 Compliance with engine and
propeller limitations
The powerplant installation shall be so designed that the
engines and propellers (if applicable) are capable of being
used in the anticipated operating conditions. In conditions
established in the aeroplane flight manual, the aeroplane shall
be capable of being operated without exceeding the limitations
established for the engines and propellers in accordance with
Chapters 5, 6 and 7.
7.1.3 Control of engine rotation
In those installations 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
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附件8--航空器适航性 Airworthiness of Aircraft(26)
