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or multi-engine helicopter which does not meet Category A
standards. Category B helicopters have no guaranteed capability
to continue safe flight in the event of an engine
failure, and a forced landing is assumed.
Configuration (as applied to the aeroplane). A particular
combination of the positions of the moveable elements,
such as wing flaps and landing gear, etc., that affect the
aerodynamic characteristics of the aeroplane.
Critical power-unit(s). The power-unit(s) failure of which
gives the most adverse effect on the aircraft characteristics
relative to the case under consideration.
Note.- On some aircraj there may be more than one
equally critical power-unit. In this case, the expression "the
critical power-unit " means one of those critical power-units.
Design landing mass. The maximum mass of the aircraft at
which, for structural design purposes, it is assumed that it
will be planned to land.
Design take-vff mass. The maximum mass at which the
aircraft, for structural design purposes, is assumed to be
planned to be at the start of the take-off run.
Design taxiing mass. The maximum mass of the aircraft at
which structural provision is made for load liable to occur
during use of the aircraft on the ground prior to the start of
take-off.
Discrete source damage. Structural damage of the aeroplane
that is likely to result from: impact with a bird, uncontained
fan blade failure, uncontained engine failure, uncontained
high-energy rotating machinery failure or similar causes.
Engine. A unit used or intended to be used for aircraft propulsion.
It consists of at least those components and equipment
necessary for functioning and control, but excludes the
propeller (if applicable).
Factor of safety. A design factor used to provide for the
possibility of loads greater than those assumed, and for
uncertainties in design and fabrication.
ANNEX 8 1-1 13/12/07
Part I
Final approach and take-off area (FATO). A defined area
over which the final phase of the approach manoeuvre to
hover or landing is completed and from which the take-off
manoeuvre is commenced. Where the FAT0 is to be used
by performance Class 1 helicopters, the defined area
includes the rejected take-off area available.
Fireproof; The capability to withstand the application of heat
by a flame for a period of 15 minutes.
Note.- The characteristics of an acceptable flame can be
found in IS0 2685.
Fire resistant. The capability to withstand the application of
heat by a flame for a period of 5 minutes.
Note.- The characteristics of an acceptable flame can be
found in IS0 2685.
Helicopter. A heavier-than-air aircraft supported in flight
chiefly by the reactions of the air on one or more powerdriven
rotors on substantially vertical axes.
Human Factors principles. Principles which apply to aeronautical
design, certification, training, operations and maintenance
and which seek safe interface between the human
and other system components by proper consideration to
human performance.
Human performance. Human capabilities and limitations
which have an impact on the safety and efficiency of aeronautical
operations.
Landing surface. That part of the surface of an aerodrome
which the aerodrome authority has declared available for
the normal ground or water run of aircraft landing in a
particular direction.
Limit loads. The maximum loads assumed to occur in the
anticipated operating conditions.
Load factor. The ratio of a specified load to the weight of the
aircraft, the former being expressed in terms of aerodynamic
forces, inertia forces, or ground reactions.
Maintenance. The performance of tasks required to ensure the
continuing airworthiness of an aircraft, including any one
or combination of overhaul, inspection, replacement, defect
rectification, and the embodiment of a modification or
repair.
Performance Class I helicopter. A helicopter with performance
such that, in case of engine failure, it is able to land
on the rejected take-off area or safely continue the flight to
an appropriate landing area.
Performance Class 2 helicopter. A helicopter with performance
such that, in case of engine failure, it is able to safely
continue the flight, except when the failure occurs prior to
a defined point after take-off or after a defined point before
landing, in which cases a forced landing may be required.
Performance Class 3 helicopter. A helicopter with performance
such that, in case of engine failure at any point in the
flight profile, a forced landing must be performed.
　
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本文鏈接地址：附件8--航空器適航性 Airworthiness of Aircraft(13)