title-14-part-29-sec29-735

609

Federal Aviation Administration, DOT

§ 29.735

(1) The loads occurring in any ma-

neuvering condition with the gear re-
tracted;

(2) The combined friction, inertia,

and air loads occurring during retrac-
tion 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 en-
ergy.

(d)

Operation tests. The proper func-

tioning 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 posi-
tions.

(f)

Control. The location and oper-

ation of the retraction control must
meet the requirements of §§ 29.777 and
29.779.

(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.

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

§ 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 re-
quirements of this part.

§ 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 cor-
responding to the critical center of
gravity; and

(3) A load on nose wheel tires (to be

compared with the dynamic rating es-
tablished for those tires) equal to the
reaction obtained at the nose wheel,
assuming that the mass of the rotor-
craft acts as the most critical center of
gravity and exerts a force of 1.0

g down-

ward 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.

able landing gear system must, at the
maximum size of the tire type expected
in service, have a clearance to sur-
rounding structure and systems that is
adequate to prevent contact between
the tire and any part of the structure
or systems.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–12, 41 FR 55471, Dec. 20,
1976]

§ 29.735

Brakes.

For rotorcraft with wheel-type land-

ing gear, a braking device must be in-
stalled that is—

(a) Controllable by the pilot;
(b) Usable during power-off landings;

and

anced torque when starting or stopping
the rotor; and

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14 CFR Ch. I (1–1–24 Edition)

§ 29.737

(2) Hold the rotorcraft parked on a

10-degree slope on a dry, smooth pave-
ment.

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

§ 29.737

Skis.

(a) The maximum limit load rating of

each ski must equal or exceed the max-
imum limit load determined under the
applicable ground load requirements of
this part.

(b) There must be a stabilizing means

to maintain the ski in an appropriate
position during flight. This means
must have enough strength to with-
stand the maximum aerodynamic and
inertia loads on the ski.

LOATS AND

ULLS

§ 29.751

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 com-
partment flooded, the mainfloats will
provide a margin of positive stability
great enough to minimize the prob-
ability of capsizing.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–3, 33 FR 967, Jan. 26,
1968]

§ 29.753

Main float design.

(a)

Bag floats. Each bag float must be

designed to withstand—

(1) The maximum pressure differen-

tial that might be developed at the
maximum altitude for which certifi-
cation with that float is requested; and

(2) The vertical loads prescribed in

§ 29.521(a), distributed along the length
of the bag over three-quarters of its
projected area.

(b)

Rigid floats. Each rigid float must

be able to withstand the vertical, hori-
zontal, and side loads prescribed in
§ 29.521. An appropriate load distribu-
tion under critical conditions must be
used.

§ 29.755

Hull buoyancy.

Water-based and amphibian rotorcraft.

The hull and auxiliary floats, if used,
must have enough watertight compart-
ments so that, with any single com-
partment of the hull or auxiliary floats
flooded, the buoyancy of the hull and
auxiliary floats, and wheel tires if
used, provides a margin of positive
water stability great enough to mini-
mize the probability of capsizing the
rotorcraft for the worst combination of
wave heights and surface winds for
which approval is desired.

[Amdt. 29–3, 33 FR 967, Jan. 26, 1968, as
amended by Amdt. 27–26, 55 FR 8003, Mar. 6,
1990]

§ 29.757

Hull and auxiliary float

strength.

The hull, and auxiliary floats if used,

must withstand the water loads pre-
scribed by § 29.519 with a rational and
conservative distribution of local and
distributed water pressures over the
hull and float bottom.

[Amdt. 29–3, 33 FR 967, Jan. 26, 1968]

ERSONNEL AND

ARGO

CCOMMODATIONS

§ 29.771

Pilot compartment.

For each pilot compartment—
(a) The compartment and its equip-

ment must allow each pilot to perform
his duties without unreasonable con-
centration or fatigue;

(b) If there is provision for a second

pilot, the rotorcraft must be control-
lable with equal safety from either
pilot position. Flight and powerplant
controls must be designed to prevent
confusion or inadvertent operation
when the rotorcraft is piloted from ei-
ther position;

teristics of cockpit appurtenances may
not interfere with safe operation;

(d) Inflight leakage of rain or snow

that could distract the crew or harm
the structure must be prevented.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–3, 33 FR 967, Jan. 26,
1968; Amdt. 29–24, 49 FR 44437, Nov. 6, 1984]