(b)
A side load condition in which–
(1)
A verticalload of0.75 timesthetotal verticalload speci.edinparagraph(a) (1)of this section is divided equally among the .oats; and
(2)
Foreach .oat,theload sharedetermined undersubparagraph(1) ofthispa-ragraph, combined with a total side load of 0.25 times the total vertical load speci.edinsubparagraph(1) of thisparagraph,isappliedtothat .oatonly.
Amdt. 29-3, E.. 2/25/68
′
Elodie Roux. Septembre 2003
Subpart C : Strength Requirements
73.6 Main Component Requirements
FAR29.547 :[Main and tail rotor structure.]
(a)
[Arotoris an assembly of rotating components, whichincludes the rotorhub,blades, blade dampers, the pitch control mechanisms, and all other parts that rotate with the assembly.
(b)
Eachrotor assembly mustbedesigned asprescribedin this section and mustfunction safely for the critical .ight load and operating conditions. A design assessment mustbeperformed,including adetailedfailure analysistoidentify allfailuresthat will prevent continued safe .ight or safe landing, and must identify the means to minimize the likelihood of their occurrence.
(c)
The rotorstructure mustbedesigned to withstand thefollowingloadsprescribedin Secs. 29.337 through 29.341 and 29.351 :]
(1)
Critical .ight loads.
(2)
Limit loads occurring under normal conditions of autorotation.
(d)
[The rotor structure must be designed to withstand loads simulating–]
(1)
For the rotor blades, hubs, and .apping hinges, the impact force of each blade against its stop during ground operation; and
(2)
Any other critical condition expected in normal operation.
(e)
[The rotor structure mustbedesignedto withstandthelimit torque at any rotational speed, including zero. In addition :]
(1) The limit torque need not be greater than the torque de.ned by a torque limiting device(whereprovided), and may notbelessthanthegreater of–
(i)
The maximum torque likely to be transmitted to the rotor structure, in either direction, by the rotor drive or by sudden application of the rotor brake; and
(ii)
[For the main rotor, the limit engine torque speci.ed in Sec. 29.361.]
(2)
Thelimit torque mustbe equallyand rationallydistributedto the rotorblades. Amdt. 29-40, E.. 8/8/96
FAR 29.549 : Fuselage and rotor pylon structures.
(a)
Eachfuselage and rotorpylon structure mustbedesigned to withstand–
(1)
The criticalloadsprescribedinSecs.29.337 through29.341, and29.351;
(2)
The applicablegroundloadsprescribedinSecs.29.235,29.471through29.485, 29.493, 29.497, 29.505, and 29.521; and
(3)
TheloadsprescribedinSec.29.547(d)(1) and(e)(1)(i).
(b)
Auxiliary rotor thrust, the torque reaction of each rotor drive system, and the ba-lancing air and inertia loads occurring under accelerated .ight conditions, must be considered.
(c)
Each engine mount and adjacent fuselage structure must be designed to withstand theloads occurringunder accelerated.ight andlanding conditions,including engine torque.
(d) [Deleted.]
(e) [Ifapprovalfor the use of2
-minute OEIpoweris requested, each engine mount and
12
adjacent structure must be designed to withstand the loads resulting from a limit torque equal to 1.25 times the mean torque for 2站-minute power OEI combined with 1g .ight loads.]
Amdt. 29-26, E.. 10/3/88
FAR 29.551 : Auxiliary lifting surfaces.
Each auxiliary lifting surface must be designed to withstand–
(a) The critical .ight loads in Secs. 29.337 through 29.341, and 29.351;
(b) The applicablegroundloadsinSecs.29.235,29.471 through29.485,29.493,29.505, and 29.521; and 中國航空網 m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 5(29)
