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. 

(c) Each tire installed on a retract-

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 

(c) Adequate to— 
(1) Counteract any normal unbal-

anced torque when starting or stopping 
the rotor; and 

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