Document ID: chunk:federal_register_of_legislation:F2005B00785:body:0:p2
Version: federal_register_of_legislation:F2005B00785
Segment Type: other
Provision Reference: 
Character Range: 2645–5511

an excessive crosswind forecast for the estimated time of landing then;
 (b) on the most suitable available runway, using wind components derived 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.
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