(b)
In the absence of more rational data, the inertial loads may be assumed to be equal to KW, where–
(1)
K =24 vertical surfaces;
(2)
K =12 for horizontal surfaces; and
(3)
W = weight of the movable surfaces.]
Amdt. 23-48, E.. 03/11/96
FAR23.395 :Control system[loads.]
(a)
Each .ight control system and its supporting structure must be designed for loads corresponding to at least 125 percent of the computed hinge moments of the mo-vable control surface in the conditions prescribed in Secs. 23.391 through 23.459. In addition, the following apply :
(1)
The system limit loads need not exceed the higher of the loads that can be produced by thepilot and automatic devices operating the controls.However, autopilot forces need not be added to pilot forces. The system must be de-signed for the maximum e.ort of the pilot or autopilot, whichever is higher. In addition, if the pilot and the autopilot act in opposition, the part of the system between them may be designed for the maximum e.ort of the one thatimposesthelesserload.[Pilotforcesusedfordesign need not exceed the maximum forcesprescribed in Sec. 23.397(b).]
(2)
The design must,in any case,provide a rugged systemfor service use, conside-ringjamming,groundgusts, taxiingdownwind, controlinertia, andfriction. [Compliance with this subparagraphmay be shown by designing for loads re-sulting from application of the minimum forces prescribed in Sec. 23.397(b).]
(b)
A125percentfactor on computedhinge moments mustbe used todesign elevator, aileron, and rudder systems. However, a factor as low as 1.0 may be used if hinge moments are based on accurate .ight test data, the exact reduction depending upon the accuracy and reliability of the data.
(c)
[Pilot forces used for design are assumed to act at the appropriate control grips or pads as they would in .ight, and to react at the attachments of the control system to the control surface horns.]
Amdt. 23-7, E.. 09/14/69
FAR 23.397 : Limit control forces and torques.
(a)
In the control surface .ight loading condition, the airloads on movable surfaces and thecorrespondingde.ectionsneed not exceed thosethat would resultin .ightfrom the applicationofanypilotforce withinthe rangesspeci.edinparagraph(b) of this section.In applyingthis criterion, the e.ects of control systemboost and servo-mechanisms,and the e.ects of tabs mustbe considered.The automaticpilot e.ort must be used for design if it alone can produce higher control surface loads than the human pilot.
(b)
The limit pilot forces and torques are as follows :
′
Elodie Roux. Septembre 2003
Subpart C : Structure
Control Maximum forces to torques for design weight, W equal to or less than 5,000 pounds1 Minimum forces or torques2
Aileron :
Stick 67 lbs 40 lbs
Wheel3 50 D in. lbs.4 40 D in.-lbs.4
Elevator :
Stick 167 lbs 100 lbs.
Wheel (symmetrical) 200 lbs. 100 lbs
Wheel (unsymmetrical)5 - 100 lbs
Rudder 200 lbs. [150 lbs.]
1 Fordesign weight(W)more than 5,000 pounds, the speci.ed maximum values must be increased linearly with weight to 1.18 times the speci.ed values at a design weight of12,500pounds, andfor commuter category airplanes, the spe-ci.ed valuesmustbeincreasedlinearly with weightto1.35 timesthe speci.ed values at adesign weight of19,000pounds.
2 If the design of any individual set of control systems or surfaces makes these speci.ed minimum forces or torques inapplicable, values corresponding to the present hinge moments obtained under Sec. 23.415, but not less than 0.6 of the speci.ed minimum forces or torques, may be used.
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本文鏈接地址：FAA規(guī)章 美國聯(lián)邦航空規(guī)章 Federal Aviation Regulations 2(4)
