Document ID: chunk:federal_register_of_legislation:F2014C01352:body:0:p8
Version: federal_register_of_legislation:F2014C01352
Segment Type: other
Provision Reference: 
Character Range: 18850–21654

the gross climb gradients established in accordance with paragraph 8.2 must be reduced by 0.3% for three-engined aeroplanes and 0.5% for four-engined aeroplanes.

9 Approach climb performance
       9.1For paragraph 5.1 (b), the approach climb requirements are met if, in the approach configuration with the critical engine inoperative at a speed not more than 1.5 VS, an aeroplane has a gross gradient of climb of at least:
(a) for a twin-engined aeroplane — 2.1%; or
(b) for a 3 engined aeroplane — 2.3% or
(c) for a 4 engined aeroplane — 2.4%.

10 Landing climb performance
       10.1For the purposes of subparagraph 5.1 (c), the landing climb requirements are met if, in the landing configuration an aeroplane has a gross gradient of climb of not less than 3.2% at a climbing speed not in excess of 1.3 VS with all engines operating.

11 Landing distance required
       11.1When determining the maximum weight for take-off of a jet-engined aeroplane of maximum take-off weight greater than 5 700 kg for the purpose of subparagraph 4.1 (d), the landing distance required is:
(a) for an aeroplane engaged in regular public transport operations when the appropriate weather reports and forecasts, or a combination, indicate that the runways will be dry at the estimated time of arrival, or in charter operations — 1.67 times the distance required to bring the aeroplane to a stop on a dry runway; or
(b) for an aeroplane engaged in regular public transport operations when the appropriate weather reports and forecasts, or a combination, indicate that the runways may be wet at the estimated time of arrival:
           (i) 1.92 times the distance required to bring the aeroplane to a stop on a dry runway; or
           (ii) the distance set out in the flight manual or operations manual for operations conducted on wet runways.
       11.2When determining the maximum weight for landing of a jet-engined aeroplane of maximum take-off weight greater than 5 700 kg for the purpose of subparagraph 5.1 (a), the landing distance required is 1.67 times the distance required to bring the aeroplane to a stop on a dry runway or, if actual landing distance data is supplied by the aircraft's type certificate holder, 1.15 times the actual landing distance.
Note   Subparagraph 4.1 (d) refers to determining the permissible landing weight before take‑off and subparagraph 5.1 (a) refers to re-assessing the permissible landing weight after take-off.
       11.3For subparagraphs 4.1 (d) and 5.1 (a), when determining the maximum weight for take-off and landing, respectively, of a jet-engined aeroplane of maximum take-off weight not greater than 5 700 kg engaged in regular public transport operations, the landing distance required is 1.43 times the distance required to bring the aeroplane to a stop on a