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produce excessive wear of brakes or tires, and the
operating pressures on the braking system are not in
excess of those approved.
3.3.2 The gradient of the steady approach and the details
of the technique used in determining the landing distance,
together with such variations in the technique as are
recommended for landing with the critical engine inoperative,
and any appreciable variation in landing distance resulting
therefrom, are entered in the flight manual.
Example 3
Purpose and scope
The purpose of the following example is to illustrate the level
of performance intended by the provisions of Chapter 5 as
applicable to turbine-powered subsonic transport type
aeroplanes over 5 700 kg maximum certificated take-off mass
having two or more engines. However, where relevant, it can
be applied to all turbine-powered or piston-engined subsonic
aeroplanes having two, three or four engines. This example is
shown to be compatible with principal national airworthiness
codes in effect in 1969.
No study has been made of the applicability of this material
to turbine-powered subsonic aeroplanes having characteristics
other than those of the transport aeroplanes introduced into
service up to 1969.
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 minima operating techniques and
procedures.
1. General
1.1 The provisions of 1 to 5 are to be complied with,
unless deviations therefrom are specifically authorized by the
State of Registry on the ground that the special circumstances
of a particular case make a literal observance of these
provisions unnecessary for safety.
1.2 Compliance with 1 to 5 is to be established using
performance data in the flight manual and in accordance with
other applicable operating requirements. In no case may the
limitations in the flight manual be exceeded. However,
ATT C-17 1/11/01
Annex 6 - Operation of Aircraft
additional limitations may be applied when operational
conditions not included in the flight manual are encountered.
1.3 The procedures scheduled in the flight manual are to
be followed except where operational circumstances require
the use of modified procedures in order to maintain the
intended level of safety.
Note.- See the Airworthiness Manual (Doc 9760) for the
related airworthiness performance guidance material.
2. Aeroplane take-off
performance limitations
2.1 No aeroplane is taken off at a mass which exceeds the
take-off mass specified in the flight manual for the altitude of
the aerodrome and for the ambient temperature existing at the
time of the take-off.
2.2 No aeroplane is taken off at a mass such that,
allowing for normal consumption of fuel and oil in flight to the
aerodrome of destination and to the destination alternate
aerodromes, the mass on arrival will exceed the landing mass
specified in the flight manual for the altitude of each of the
aerodromes involved and for the ambient temperatures
anticipated at the time of landing.
2.3 No aeroplane is taken off at a mass which exceeds the
mass at which, in accordance with the minimum distances for
take-off scheduled in the flight manual, compliance with 2.3.1
to 2.3.3 inclusive is shown. These distances correspond with
the altitude of the aerodrome, the runway, stopway and clearway
to be used, the runway slope, the stopway slope, the clearway
plane slope, and the ambient temperature and wind
existing at the time of take-off.
3. Take-off obstacle
clearance limitations
3.1 No aeroplane is taken off at a mass in excess of that
shown in the flight manual to correspond with a net take-off
flight path which clears all obstacles either by at least a height
of 10.7 m (35 ft) vertically or at least 90 m plus 0.125D
laterally, where D is the horizontal distance the aeroplane has
travelled from the end of take-off distance available, except as
provided in 3.1.1 to 3.1.3 inclusive. In determining the
allowable deviation of the net take-off flight path in order to
avoid obstacles by at least the distances specified, it is
assumed that the aeroplane is not banked before the clearance
of the net take-off flight path above obstacles is at least
15.2 m (50 ft) and that the bank thereafter does not exceed
　
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