Document ID: chunk:federal_register_of_legislation:F2014C01352:body:0:p7
Version: federal_register_of_legislation:F2014C01352
Segment Type: other
Provision Reference: 
Character Range: 16175–19125

existing at the end of the level flight acceleration manoeuvre, an aeroplane must be able to achieve a gross gradient of climb of at least:
(a) for a twin-engined aeroplane — 1.2%; or
(b) for a 3-engined aeroplane — 1.4%; or
(c) for a 4-engined aeroplane — 1.5%.
       7.4.2The gradient of climb must be achievable at final take-off climb speed with the critical engine inoperative and the remaining engines at maximum continuous power or thrust.
       7.5In determining the net flight path of an aeroplane to show compliance with subsection 12, the gross gradients of climb achieved in paragraphs 7.2 and 7.4.1 must be reduced by 0.8% for twin-engined aeroplanes, 0.9% for three‑engined aeroplanes and 1.0% for four-engined aeroplanes. Similarly the horizontal distance to accelerate in compliance with paragraph 7.3.1 must be increased due to the acceleration reduction equivalent to the climb gradient reductions specified in this paragraph.
Note   The net flight path and the gross flight path may be considered identical when the aeroplane is in the take-off configuration described in paragraph 7.1.
       7.6In this section:
commuter type aeroplane means:
(a) a SFAR 41 aeroplane; or
(b) an aeroplane that is certificated as a commuter category aircraft.
SFAR 41 aeroplane means an aeroplane that:
(a) is certificated as a normal category aircraft; and
(b) is such that an applicant under part 4 (c) of SFAR No. 41 would be entitled to a type certificate amendment or a supplemental type certificate that shows compliance with Annex 8 to the Chicago Convention in relation to the aeroplane; and
(c) is operated in accordance with a flight manual that specifies performance standards that are at least equivalent to the standards set out in Annex 8 to the Chicago Convention.
SFAR No. 41 means Special Federal Aviation Regulation No. 41 of the United States of America.

8 En-route climb performance
       8.1The en-route climb performance of an aeroplane with the critical engine inoperative is to be determined taking into account all normal operating altitudes, operating weights, and anticipated temperatures.
       8.2The en-route climb performance of a three- or four-engined aeroplane with the 2 most critical engines inoperative is to be determined taking into account all normal operating altitudes, operating weights, and anticipated temperatures.
       8.3In determining the net flight path of an aeroplane to show compliance with subsection 12, the gross climb gradients established in accordance with paragraph 8.1 must be reduced by 1.1% for twin-engined aeroplanes, 1.3% for three-engined aeroplanes and 1.4% for four-engined aeroplanes. Similarly 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