(2)
There must be means to keep the blade from hitting the droop stops during any operation other than starting and stopping the rotor.
Amdt. 29-17, E.. 12/1/78
FAR 29.679 : Control system locks.
If there is a device to lock the control system with the rotorcraft on the ground or water, there must be means to–
(a)
Automatically disengage the lock when the pilot operates the controls in a normal manner,orlimittheoperationof the rotorcraft soastogiveunmistakable warning to the pilot before takeo.; and
(b)
Prevent the lock from engaging in .ight.
FAR 29.681 : Limit load static tests.
(a)
Compliance with thelimitload requirements of thispart mustbe shownby testsin which–
(1)
Thedirection of thetestloadsproducesthe most severeloadinginthe control system; and
(2)
Each .tting, pulley, and bracket used in attaching the system to the main structure is included;
(b)
Compliancemustbeshown(by analysesorindividualloadtests) withthe special factor requirementsfor control systemjoints subjectto angular motion.
′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction
FAR 29.683 : Operation tests.
It must be shown by operation tests that, when the controls are operated from the pilot compartment with the control system loaded to correspond with loads speci.ed for the system, the system is free from–
(a)
Jamming;
(b)
Excessive friction; and
(c)
Excessive de.ection.
FAR 29.685 : Control system details.
(a)
[Eachdetailof each control system mustbedesigned topreventjamming, cha.ng, andinterferencefrom cargo,passengers,loose objects, orthefreezing of moisture.]
(b)
There must be means in the cockpit to prevent the entry of foreign objects into places wherethey wouldjamthe system.
(c)
There mustbe meanstopreventthe slapping of cables ortubes againstotherparts.
(d)
Cable systems must be designed as follows :
(1)
Cables,cable .ttings,turnbuckles,splices,andpulleysmustbeofanacceptable kind.
(2)
The design of cable systems must prevent any hazardous change in cable ten-sion throughout the range of travel under any operating conditions and tem-perature variations.
(3)
No cable smaller than one-eighth inch diameter may be used in any primary control system.
(4)
Pulleykinds and sizes must correspond to the cables with which they are used. The pulley-cable combinations and strength values speci.ed in MIL-HDBK-5 must be used unless they are inapplicable.
(5)
Pulleysmusthaveclose .ttingguardstopreventthecablesfrombeing displa-ced or fouled.
(6)
Pulleys mustlie close enough to theplanepassing through the cable toprevent the cable from rubbing against the pulley .ange.
(7)
No fairlead may cause a change in cable direction of more than 3'.
(8)
No clevis pin subject to load or motion and retained only by cotter pins may be used in the control system.
(9)
Turnbuckles attached to parts having angular motion must be installed to prevent binding throughout the range of ravel.
(10)
There must be means for visual inspection at each fairlead, pulley, terminal, and turnbuckle.
(e)
Control systemjoints subjecttoangularmotion mustincorporatethefollowing spe-cial factors with respect to the ultimate bearing strength of the softest material used as a bearing :
(1)
3.33 for push-pull systems other than ball and roller bearing systems.
(2)
2.0 for cable systems.
(f)
Forcontrol systemjoints,the manufacturer’sstatic,non-Brinellrating ofballand roller bearings may not be exceeded.
Amdt. 29-12, E.. 2/1/77
FAR 29.687 : Spring devices.
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 5(39)
