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This material was contained in substance in Attachment A
to the now superseded edition of Annex 6 which became
effective on 1 May 1953. It is based on the type of requirements
developed by the Standing Committee on Performance*
with such detailed changes as are necessary to make it reflect
as closely as possible a performance code that has been used
nationally.
A substantial number of civil transport aeroplanes have
been manufactured and are being operated in accordance with
these codes. Those aeroplanes are powered with reciprocating
engines, turbo-propellers and turbo-jets. They embrace twinengined
and four-engined aeroplanes over a mass range from
approximately 5 500 kg to 70 000 kg over a stalling speed
range, Vso, from approximately 110 to 170 k d h (60 to 90 kt)
and over a wing loading range from approximately 120 to
350 kg/m2. Cruising speeds range up to 740 k d h (400 kt).
Those aeroplanes have been used in a very wide range of
altitude, air temperature and humidity conditions.
Although only past experience can warrant the fact that this
example illustrates the level of performance intended by the
Standards and Recommended Practices of Chapter 5, it is
considered to be applicable, except for some variations in
detail as necessary to fit particular cases, over a much wider
range of aeroplane characteristics. Reservation should,
however, be made concerning one point. The landing distance
specification of this example, not being derived from the same
method as other specifications, is valid only for the range of
conditions stated for Example 1 in this Attachment.
This example is not intended for application to aeroplanes
having short take-off and landing (STOL) or vertical take-off
and landing (VTOL) capabilities.
No detailed study has been made of the applicability of this
example to operations in all-weather conditions. The validity
of this example has not therefore been established for
operations which may involve low decision heights and be
associated with low weather minima operating techniques and
procedures.
1. Definitions
Declared distances.
a) Take-off run available (TORA). The length of runway
declared available and suitable for the ground run of an
aeroplane taking off.
b) Take-off distance available (TODA). The length of the
take-off run available plus the length of the clearway, if
provided.
* The ICAO Standing Committee on Performance, established as a
result of recommendations of the Airworthiness and Operations
Divisions at their Fourth Sessions, in 195 1, met four times between
1951 and 1953.
ATT C-9 111 1/01
Annex 6 - Operation of Aircraft Part I
C) Accelerate-sty distarzce available (ASDA). The length
of the take-off run available plus the length of the
stopway, if provided.
d) Landing distance available (LDA). The length of
runway which is declared available and suitable for the
ground run of an aeroplane landing.
TAS (True airspeed). The speed of the aeroplane relative to
undisturbed air.
Note.- See Chapter I and Annexes 8 and 14, Vnlrrme I, for
other definitions.
Note.- The calculation of declared distances is described
in Annex 14, Volume I, Attachment A.
2.1 Mass
Declared temperature. A temperature selected in such a way
that when used for performance purposes, over a series of
operations, the average level of safety is not less than
would be obtained by using official forecast temperatures.
Expected. Used in relation to various aspects of performance
(e.g. rate or gradient of climb), this term means the
standard performance for the type, in the relevant
conditions (e.g. mass, altittide and temperature).
Height. The vertical distance of a level, a point, or an object
considered as a point, measured from a specified datum.
Note.- For the purposes of this example, the point referred
to above is the lowest part of the aeroplane and the specified
datum is the take-off or landing surface, whichever is
applicable.
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.
Net gradient. The net gradient of climb throughout these
requirements is the expected gradient of climb diminished
by the manoeuvre performance (i.e. that gradient of climb
necessary to provide power to manoeuvre) and by the
margin (i.e. that gradient of climb necessary to provide for
those variations in performance which are not expected to
be taken explicit account of operationally).
Reference humidity. The relationship between temperature
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ICAO 附件6 Operation of Aircraft(61)
