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from the minimum wind velocity which would make the runway in (a)
above unusable due to cross wind limitations;
provided that if the weight derived from (b) above is greater than the weight
derived from (a), the weight derived from (a) shall be the limiting weight. In
determining these weights, account shall be taken of the aerodrome pressure
altitude and forecast temperature for the time of landing.
4 TAKE-OFF OBSTACLE CLEARANCE LIMITATIONS
4.1 No aeroplane shall take off at a weight which exceeds any weight limitation in
the aeroplane flight manual with respect to take-off climb with all engines
operating. In determining this weight, account shall be taken of the aerodrome
pressure altitude and the ambient temperature.
4.1.1 Additionally, no aeroplane having a maximum take-off weight exceeding
3 500 kg shall take off at a weight such that the take-off climb gradient with
the critical engine inoperative is less than the obstacle-free gradient specified
for the take-off distance available. Where the obstacle-free gradient specified
for the take-off distance available is less than 1.9%, the take-off weight shall
be determined on the basis of a 1.9% gradient. The gradient shall be
established for a distance of 3 000 metres from the end of the take-off distance
available. In determining this weight, account shall be taken of the aerodrome
pressure altitude and ambient temperature.
5 EN-ROUTE LIMITATIONS
5.1 No aeroplane shall take off at a weight in excess of that which, in accordance
with approved one engine inoperative en-route performance data permits the
aeroplane to comply with the requirements of paragraphs 5.2 or 5.3 under the
prevailing meteorological conditions.
5.2 An aeroplane shall be capable of climbing to, and maintaining, a flight altitude
which provides at least 1 000 feet vertical clearance from all terrain and
obstructions along the route within:
(a) 5 nautical miles on either side of track, for V.F.R. procedures flights; and
(b) such greater distances as required by the accuracy of the navigation aids
used for I.F.R. procedures flights.
Note: Lowest Safe Altitudes (LSALT) published in the Aeronautical Information Publication
satisfy the terrain and obstacle clearance requirements for I.F.R. procedure flights.
Issue 4: 8 December 2004
Amdt No. 211
-3- SECTION 20.7.2
Issue 4
5.3 If compliance with paragraph 5.2 is not possible a “drift down” procedure may
be planned such that with one engine inoperative:
(a) a return to the aerodrome of departure is possible clear of all terrain and
obstructions if one engine fails before the aeroplane reaches the planned
cruising altitude; and
(b) after reaching the planned cruising altitude, the resultant flight path will be
such as to permit the aeroplane to continue flight to an aerodrome where a
landing can be made and will provide at least 2000 feet vertical clearance
from all terrain and obstructions within the distance specified in paragraph
5.2.
5.4 Conditions
In determining take-off weight required by paragraph 5.1 of this section:
(a) engine failure shall be assumed to occur at the most critical point along the
route; and
(b) forecast atmospheric pressures and temperatures shall be used; and
(c) the effect of forecast wind velocities shall be applied to the flight path; and
(d) in meteorological conditions where the use of aeroplane icing protection
systems is likely to be required, the effect of their use on the flight path
shall be taken into account; and
(e) fuel jettisoning shall be permitted in accordance with the aeroplane flight
manual procedures, to the extent consistent with reaching the intended
aerodrome of landing with the required fuel reserves; and
(f) the aerodrome where the aeroplane is assumed to land after engine failure
shall be specified in the flight plan and shall meet the requirements for an
alternate aerodrome; and
(g) consumption of fuel after engine failure shall be calculated to meet the
consumptions required in following the planned flight path.
6 LANDING LIMITATIONS
Except in an emergency, an aeroplane shall not land at an aerodrome unless the
landing distance available on the runway of intended landing is equal to, or
greater than, the landing distance required in the aeroplane flight manual for
the landing weight of the aeroplane. In deriving the landing distance required,
account shall be taken of the aerodrome pressure altitude and ambient
temperature, the runway slope and surface, and the wind velocity existing at
the time of landing.
7 UNSERVICEABLE EQUIPMENT
7.1 When any item of equipment, which will invalidate any performance
　
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