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h+d
as in Sec. 23.725.]
Amdt. 23-7, E.. 09/14/69
FAR 23.729 : Landing gear extension and retraction system.
(a) General. For airplanes with retractable landing gear, the following apply :
(1)
Eachlandinggearretracting mechanism andits supporting structure mustbe designed for maximum .ight 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 VS1 with .aps retracted, and for any load factor up to those speci.ed in Sec. 23.345 for the .aps-extended condition.

(2)
The landing gear and retracting mechanism, including the wheel well doors, must withstand .ight loads, including loads resulting from all yawing condi-tions speci.edinSec.23.351,with thelandinggearextended at any speed up to at least 1.6VS1 with the .aps retracted.

(b)
Landing gear lock.There mustbepositive means(other than the use ofhydraulic pressure) to keep the landing gear extended.

(c)
Emergency operation. For a landplane having retractable landing gear that cannot be extended manually, there mustbe means to extend the landinggearin the event of either–

(1)
Any reasonablyprobablefailureinthe normallandinggearoperation system; or

(2)
Any reasonably probable failure in a power source that would prevent the operation of the normal landing gear operation system.

 

(d)
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) orothermeanstoinformthepilotthat eachgearis securedinthe extended(or retracted) position. If switches are used, they must be located and coupled to the landinggearmechanical systemin a mannerthatprevents an erroneousindication 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.]

(f)
Landinggear warning.Forlandplanes, thefollowing aural or equally e.ectivelanding gear warning devices must be provided :

(1)
A device that functions continuously when one or more throttles are closed beyond the power settings normally used for landing approach if the landing gear is not fully extended and locked. A throttle stop may not be used in place of an aural device. If there is a manual shuto. for the warning device prescribed in this paragraph, the warning system must be designed so that when the warning has been suspended after one or more throttles are closed, subsequent retardation of any throttle to, or beyond, the position for normal landing approach will activate the warning device.

(2)
Adevicethatfunctionscontinuously whenthewing.apsareextendedbeyond the maximum approach .ap position, using a normal landing procedure, if thelandinggearisnotfully extended andlocked.Theremay notbe amanual shuto.forthiswarningdevice.The .appositionsensing unit maybeinstalled at any suitable location. The system for this device may use any part of the system (including the aural warning device) for the device required in paragraph(f)(1) of this section.

 

′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction
(g) [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 desi-gned and installed to minimize damage from items such as a tire burst, or rocks, water, and slush that may enter the landing gear bay.]
Amdt. 23-49, E.. 03/11/96
FAR 23.731 : Wheels.
(a)
[The maximum static loadrating of each wheel may not be less than the correspon-ding static ground reaction–
　
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