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are applicable to engines of all types, used as primary propulsion
units, as required in Parts IIIB, IVB and V.
Note.- The following Standards do not include quantitative
specifications comparable to those found in national
airworthiness codes. In accordance with 1.2.1 of Part IZ, these
Standards are to be supplemented by requirements established,
adopted or accepted by Contracting States.
A. 1.2 The level of airworthiness defined by the appropriate
parts of the comprehensive and detailed national code for
the engines designated in A.l.l shall be at least substantially
equivalent to the overall level intended by the broad Standards
of this part.
A.2 Engine installation
and interfaces
A.2.1 All necessary information for the safe and correct
interfaces between the engine and the aircraft shall be made
available.
A.2.2 The installation instructions shall specify those
assumptions concerning the conditions that may be imposed
on the engine when it is eventually installed in an aircraft.
A.3 Declared ratings, conditions
and limitations
A.3.2 Within the stated limits of A.3.1, the engine shall
produce the thrust or power demanded of it at all required
flight conditions, taking into account environmental effects
and conditions.
A.4 Continuing airworthiness -
maintenance information
A.4.1 General
Information for use in developing procedures for maintaining
the engine in an airworthy condition shall be made available.
The information shall include that described in A.4.2, A.4.3
and A.4.4.
A.4.2 Maintenance information
Maintenance information shall include a description of the
engine and recommended methods for the accomplishment of
maintenance tasks. Such information shall include guidance on
defect diagnosis.
A.4.3 Maintenance programme information
Maintenance programme information shall include the maintenance
tasks and the recommended intervals at which these
tasks are to be performed.
A.4.4 Mandatory maintenance requirements
resulting from the type design approval
A.3.1 The thrust or power ratings and the conditions of Mandatory maintenance requirements that have been specified
the atmosphere upon which they are based and all operating by the State of Design as part of the approval of the type
conditions and limitations which are intended to govern the design shall be identified as such and included in the mainoperation
of the engine shall be declared. tenance information of A.4.3.
ANNEX 8
SUB-PART B. DESIGN AND CONSTRUCTION
B.l Functioning B.3 Materials and manufacturing methods
The engine shall be designed and constructed so as to function The selection of materials and the manufacturing methods and
reliably within its operating limitations under its anticipated processes shall account for the operational environment of the
operating conditions when installed in accordance with engine expected in service. The materials and manufacturing
Parts IIIB, IVB or V of this Annex and, if applicable, fitted methods and processes used in the construction of the engine
with a propeller approved for the installation. shall result in known and reproducible structural behaviour.
B.2 Failure analysis
B.4 Integrity
For turbine engines, a safety assessment of the engine shall be
conducted to ensure that it functions safely throughout the full
range of operating conditions. A summary shall be made of all
foreseeable failures and combinations of failures that result in
hazardous engine effects. If the primary failure of single
elements (for example, disks) is likely to result in hazardous
engine effects, reliance shall be placed on meeting prescribed
integrity requirements.
The integrity of the engine shall be demonstrated throughout
its operating envelope and be maintained for its operational
life. The effects of cyclic loading, environmental and operational
degradation and likely subsequent part failures shall
not reduce the integrity of the engine below acceptable levels.
All necessary instructions for ensuring continued airworthiness
in this regard shall be promulgated.
ANNEX 8
SUB-PART C. TESTS
The engine 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
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附件8--航空器适航性 Airworthiness of Aircraft(73)
