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2. General
2.1 Significant factors
To determine the performance of the helicopter, account is
taken of at least the following factors:
a) mass of the helicopter;
b) elevation or pressure-altitude and temperature;
C) wind: for take-off and landing, accountability for wind
shall be'no more than 50 per cent of any reported steady
head wind component of 5 hots or more. Where
take-off and landing with a tail wind component is
permitted in the flight manual, not less than 150 per cent
of any reported tail wind component shall be allowed.
Where precise wind measuring equipment enables
accurate measurement of wind velocity over the
point of take-off and landing, these values may be
varied: and
d) operating techniques.
2.2 For performance Class 2 or 3 helicopters in any flight
phase where a power-unit failure may cause the helicopter to
force land:
a) a minimum visibility must be defined by the operator,
taking into account the characteristics of the helicopter,
but never less than 1 MX, m for perfomlance Class 2
helicopters and 1500 m for performance Class 3
helicopters;
b) the operator is obliged to verify that the surface below
the intended flight path permits the pilot to execute a
safe forced landing; in addition, in case of a flight over
water, the operator must also verify that the helicopter
has been certificated for ditching.
Take-off distance avaikble (TODAH). The length of the final
approach and take-off area plus the length of helicopter In addition, performance Class 3 operations are not to be
clearway (if provided) declared available and suitable for performed:
helicopters td complete the take-off.
c) out of the sight of the surface; or
Touchdown and lift-off area (TLOF). A load bearing area on
which a helicopter may touch down or lift off. d) at night; or
V, Best rate of climb speed. e) wherthe cloud ceiling is less than 180 m (600 ft).
ANNEX 6 - PART III ATT A-1
Annex 6 - Operation of Aircmfr Part IZI
3. Operating area considerations
3.1 Touchdown and lift-off area
On surface level heliports, the length or width of the
undercarriage, whichever is the greater, does not exceed Z3
the diameter of the circle contained in the touchdown and liftoff
area. On elevated heliports and on helidecks, it is presumed
that the FAT0 and the touchdown and lift-off area will be
coincidental.
The over-all length or width of the helicopter, whichever is the
greater, does not exceed 213 the smallest dimension of the
FAT0 except in case of a water helipoa. In this case, it does
not exceed 1/2 the width of the FATO. If the FAT0 includes
Nater surface, the helicopter is to be specifically approved in
its flight manual for routine water operations including
rejected take-off onto water surfaces. For performance Class 1
helicopters, the dimensions of the FAT0 are not less than
those which are indicated in the flight manual of the
helicopter.
3.3 Helicopter clearway
The over-all length or width of the helicopter, whichever is
greater, does not exceed 2/3 the width of the helicopter
clearway in case of a land heliport or half the width of the
helicopter cleanvay in case of a water heliport.
4. Limitations resulting from performance
4.1 Performance Class 1 helicopters
4.1.1.1 No helicopter is taken off at a mass that exceeds
the maximum take-off mass specified in the flight manual for
the altitude of the heliport and for the ambient temperature
existing at the time of the take-off.
4.1.1.2 Take-off from a surface-level
heliport (Figure A- 1 )
The take-off mass is such that:
a) the rejected take-off distance required does not exceed
the rejected take-off distance available;
b) the take-off distance required does not exceed the takeoff
distance available; or
As an alternative (Figure A-2), the take-off distance
required may be disregarded provided that the helicopter
with the critical power-unit failure at the TDP can, when
continuing the take-off, clear all obstacles between the
end of the take-off distance available and the point at
which it becomes established in a climb at V, by a
vertical margin of 10.7 m (35 ft) or more. An obstacle
is coqsidered to be in the path of the helicopter if its
distance from the nearest point on the surface below the
intended line of flight does not exceed 30 m or 1.5 times
the maximum dimension of the helicopter, whichever is
greater.
4.1.1.3 Take-off from an elevated
heliport or helideck (Figure A-3)
The take-off mass is such that:
a) it is possible to reject the take-off and land on the FAT0
　
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