Section 27.731

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

(d) Operation tests. The proper functioning of the retracting mechanism
must be shown by operation tests.
(e) Position indicator. There must be a
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 27.777 and
27.779.
(g) Landing gear warning. An aural or
equally effective landing gear warning
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.
[Amdt. 27-21, 49 FR 44434, Nov. 6, 1984]

Section 27.731

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.

spaschal on DSK3GDR082PROD with CFR

Section 27.733

Tires.

(a) Each landing gear wheel must
have a tire - 
(1) That is a proper fit on the rim of
the wheel; and
(2) Of the proper rating.
(b) The maximum static load rating
of each tire must equal or exceed the
static ground reaction obtained at its
wheel, assuming - 
(1) The design maximum weight; and
(2) The most unfavorable center of
gravity.
(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

the tire and any part of the structure
or systems.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27-11, 41 FR 55469, Dec. 20,
1976]

Section 27.735

Brakes.

For rotorcraft with wheel-type landing gear, a braking device must be installed that is - 
(a) Controllable by the pilot;
(b) Usable during power-off landings;
and
(c) Adequate to - 
(1) Counteract any normal unbalanced torque when starting or stopping
the rotor; and
(2) Hold the rotorcraft parked on a
10-degree slope on a dry, smooth pavement.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27-21, 49 FR 44434, Nov. 6,
1984]

Section 27.737 Skis.
The maximum limit load rating of
each ski must equal or exceed the maximum limit load determined under the
applicable ground load requirements of
this part.
FLOATS AND HULLS
Section 27.751 Main float buoyancy.
(a) For main floats, the buoyancy
necessary to support the maximum
weight of the rotorcraft in fresh water
must be exceeded by - 
(1) 50 percent, for single floats; and
(2) 60 percent, for multiple floats.
(b) Each main float must have
enough water-tight compartments so
that, with any single main float compartment flooded, the main floats will
provide a margin of positive stability
great enough to minimize the probability of capsizing.
[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27-2, 33 FR 963, Jan. 26,
1968]

Section 27.753 Main float design.
(a) Bag floats. Each bag float must be
designed to withstand - 
(1) The maximum pressure differential that might be developed at the
maximum altitude for which certification with that float is requested; and

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