Source: https://www.law.cornell.edu/cfr/text/14/25.121
Timestamp: 2017-05-23 11:17:39
Document Index: 609344226

Matched Legal Cases: ['art 25', '§ 25', '§ 25', '§ 25', '§ 25', '§ 25', '§ 25', '§ 25', '§ 25', '§ 25', 'art 25']

14 CFR 25.121 - Climb: One-engine-inoperative. | US Law | LII / Legal Information Institute
CFR › Title 14 › Chapter I › Subchapter C › Part 25 › Subpart B › Section 25.121 14 CFR 25.121 - Climb: One-engine-inoperative.
§ 25.121 Climb: One-engine-inoperative.
(a)Takeoff; landing gear extended. In the critical takeoff configuration existing along the flight path (between the points at which the airplane reaches VLOF and at which the landing gear is fully retracted) and in the configuration used in § 25.111 but without ground effect, the steady gradient of climb must be positive for two-engine airplanes, and not less than 0.3 percent for three-engine airplanes or 0.5 percent for four-engine airplanes, at VLOF and with - (1) The critical engine inoperative and the remaining engines at the power or thrust available when retraction of the landing gear is begun in accordance with § 25.111 unless there is a more critical power operating condition existing later along the flight path but before the point at which the landing gear is fully retracted; and (2) The weight equal to the weight existing when retraction of the landing gear is begun, determined under § 25.111. (b)Takeoff; landing gear retracted. In the takeoff configuration existing at the point of the flight path at which the landing gear is fully retracted, and in the configuration used in § 25.111 but without ground effect:
(2) The requirements of paragraph (b)(1) of this section must be met:
(i) In non-icing conditions; and
(A) The stall speed at maximum takeoff weight exceeds that in non-icing conditions by more than the greater of 3 knots CAS or 3 percent of VSR; or
(B) The degradation of the gradient of climb determined in accordance with § 25.121(b) is greater than one-half of the applicable actual-to-net takeoff flight path gradient reduction defined in § 25.115(b).
(c)Final takeoff. In the en route configuration at the end of the takeoff path determined in accordance with § 25.111:
(1) The steady gradient of climb may not be less than 1.2 percent for two-engine airplanes, 1.5 percent for three-engine airplanes, and 1.7 percent for four-engine airplanes, at VFTO with - (i) The critical engine inoperative and the remaining engines at the available maximum continuous power or thrust; and
(ii) The weight equal to the weight existing at the end of the takeoff path, determined under § 25.111.
(2) The requirements of paragraph (c)(1) of this section must be met:
(d)Approach. In a configuration corresponding to the normal all-engines-operating procedure in which VSR for this configuration does not exceed 110 percent of the VSR for the related all-engines-operating landing configuration:
(1) The steady gradient of climb may not be less than 2.1 percent for two-engine airplanes, 2.4 percent for three-engine airplanes, and 2.7 percent for four-engine airplanes, with - (i) The critical engine inoperative, the remaining engines at the go-around power or thrust setting;
(2) The requirements of paragraph (d)(1) of this section must be met:
[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-84, 60 FR 30749, June 9, 1995; Amdt. 25-108, 67 FR 70826, Nov. 26, 2002; Amdt. 25-121, 72 FR 44666; Aug. 8, 2007; Amdt. 25-140, 79 FR 65525, Nov. 4, 2014]
Title 14 published on 03-May-2017 03:58The following are ALL rules, proposed rules, and notices (chronologically) published in the Federal Register relating to 14 CFR Part 25 after this date.2017-05-12; vol. 82 # 91 - Friday, May 12, 201782 FR 22065 - Special Conditions: Bombardier Aerospace, Model BD-700-2A12 and BD-700-2A13 Airplanes; Limit Engine Torque Loads
14 CFR 91.611 — Authorization for Ferry Flight With One Engine Inoperative.
14 CFR 25.121 — Climb: One-Engine-Inoperative.
14 CFR 25.107 — Takeoff Speeds.
14 CFR 25.143 — General.
14 CFR 25.149 — Minimum Control Speed.
14 CFR 25.21 — Proof of Compliance.
14 CFR 25.1045 — Cooling Test Procedures.
14 CFR 25.1533 — Additional Operating Limitations.
14 CFR 25.105 — Takeoff.