spaschal on DSK3GDR082PROD with CFR

Section 29.729

14 CFR Ch. I (1-1-19 Edition)

(c) The landing gear must withstand
this test without collapsing. Collapse
of the landing gear occurs when a
member of the nose, tail, or main gear
will not support the rotorcraft in the
proper attitude or allows the rotorcraft
structure, other than landing gear and
external accessories, to impact the
landing surface.

device must be provided that functions
continuously when the rotorcraft is in
a normal landing mode and the landing
gear is not fully extended and locked.
A manual shutoff capability must be
provided for the warning device and the
warning system must automatically
reset when the rotorcraft is no longer
in the landing mode.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 27-26, 55 FR 8003, Mar. 6,
1990]

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29-24, 49 FR 44437, Nov. 6,
1984]

Section 29.729 Retracting mechanism.
For rotorcraft with retractable landing gear, the following apply:
(a) Loads. The landing gear, retracting mechanism, wheel well doors, and
supporting structure must be designed
for - 
(1) The loads occurring in any maneuvering condition with the gear retracted;
(2) The combined friction, inertia,
and air loads occurring during retraction and extension at any airspeed up
to the design maximum landing gear
operating speed; and
(3) The flight loads, including those
in yawed flight, occurring with the
gear extended at any airspeed up to the
design maximum landing gear extended
speed.
(b) Landing gear lock. A positive
means must be provided to keep the
gear extended.
(c) Emergency operation. When other
than manual power is used to operate
the gear, emergency means must be
provided for extending the gear in the
event of - 
(1) Any reasonably probable failure in
the normal retraction system; or
(2) The failure of any single source of
hydraulic, electric, or equivalent energy.
(d) Operation tests. The proper functioning of the retracting mechanism
must be shown by operation tests.
(e) Position indicator. There must be
means to indicate to the pilot when the
gear is secured in the extreme positions.
(f) Control. The location and operation of the retraction control must
meet the requirements of SectionSection 29.777 and
29.779.
(g) Landing gear warning. An aural or
equally effective landing gear warning

Section 29.731 Wheels.
(a) Each landing gear wheel must be
approved.
(b) The maximum static load rating
of each wheel may not be less than the
corresponding static ground reaction
with - 
(1) Maximum weight; and
(2) Critical center of gravity.
(c) The maximum limit load rating of
each wheel must equal or exceed the
maximum radial limit load determined
under the applicable ground load requirements of this part.
Section 29.733 Tires.
Each landing gear wheel must have a
tire - 
(a) That is a proper fit on the rim of
the wheel; and
(b) Of a rating that is not exceeded
under - 
(1) The design maximum weight;
(2) A load on each main wheel tire
equal to the static ground reaction corresponding to the critical center of
gravity; and
(3) A load on nose wheel tires (to be
compared with the dynamic rating established for those tires) equal to the
reaction obtained at the nose wheel,
assuming that the mass of the rotorcraft acts as the most critical center of
gravity and exerts a force of 1.0 g downward and 0.25 g forward, the reactions
being distributed to the nose and main
wheels according to the principles of
statics with the drag reaction at the
ground applied only at wheels with
brakes.
(c) Each tire installed on a retractable landing gear system must, at the
maximum size of the tire type expected
in service, have a clearance to surrounding structure and systems that is
adequate to prevent contact between

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