Source: https://www.law.cornell.edu/cfr/text/14/23.729
Timestamp: 2016-07-27 02:05:06
Document Index: 286806063

Matched Legal Cases: ['art 23', '§ 23', '§ 23', '§ 23', '§ 106', '§ 40113', '§ 44701', '§ 44702', '§ 44704']

14 CFR 23.729 - Landing gear extension and retraction system. | US Law | LII / Legal Information Institute
CFR › Title 14 › Chapter I › Subchapter C › Part 23 › Subpart D › Section 23.729 14 CFR 23.729 - Landing gear extension and retraction system.
§ 23.729 Landing gear extension and retraction system.
General. For airplanes with retractable landing gear, the following apply: (1) Each landing gear retracting mechanism and its supporting structure must be designed for maximum flight load factors with the gear retracted and must be designed for the combination of friction, inertia, brake torque, and air loads, occurring during retraction at any airspeed up to 1.6 V
1 with flaps retracted, and for any load factor up to those specified in § 23.345 for the flaps-extended condition. (2) The landing gear and retracting mechanism, including the wheel well doors, must withstand flight loads, including loads resulting from all yawing conditions specified in § 23.351, with the landing gear extended at any speed up to at least 1.6 V
1 with the flaps retracted. (b)
Landing gear lock. There must be positive means (other than the use of hydraulic pressure) to keep the landing gear extended. (c)
Emergency operation. For a landplane having retractable landing gear that cannot be extended manually, there must be means to extend the landing gear in the event of either - (1) Any reasonably probable failure in the normal landing gear operation system; or (2) Any reasonably probable failure in a power source that would prevent the operation of the normal landing gear operation system.
Operation test. The proper functioning of the retracting mechanism must be shown by operation tests. (e)
Position indicator. If a retractable landing gear is used, there must be a landing gear position indicator (as well as necessary switches to actuate the indicator) or other means to inform the pilot that each gear is secured in the extended (or retracted) position. If switches are used, they must be located and coupled to the landing gear mechanical system in a manner that prevents an erroneous indication of either “down and locked” if each gear is not in the fully extended position, or “up and locked” if each landing gear is not in the fully retracted position.
Landing gear warning. For landplanes, the following aural or equally effective landing gear warning devices must be provided:
Equipment located in the landing gear bay. If the landing gear bay is used as the location for equipment other than the landing gear, that equipment must be designed and installed to minimize damage from items such as a tire burst, or rocks, water, and slush that may enter the landing gear bay.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 FR 13091, Aug. 13, 1969; Amdt. 23-21, 43 FR 2318, Jan. 16, 1978; Amdt. 23-26, 45 FR 60171, Sept. 11, 1980; Amdt. 23-45, 58 FR 42164, Aug. 6, 1993; Amdt. 23-49, 61 FR 5166, Feb. 9, 1996] This is a list of United States Code sections, Statutes at Large, Public Laws, and Presidential Documents, which provide rulemaking authority for this CFR Part.This list is taken from the Parallel Table of Authorities and Rules provided by GPO [Government Printing Office].It is not guaranteed to be accurate or up-to-date, though we do refresh the database weekly. More limitations on accuracy are described at the GPO site.United States CodeU.S. Code: Title 49 - TRANSPORTATION§ 106 - Federal Aviation Administration§ 40113 - Administrative§ 44701 - General requirements§ 44702 - Issuance of certificates§ 44704 - Type certificates, production certificates, airworthiness certificates,,11 So in original. and design and production organization certificates