(b)
The indication provided must be designed to alert the .ight crew if either of the following conditions exist :

(1)
The pitot heating system is switched ”o..”

(2)
Thepitotheating systemisswitched ”on” and anypitottubeheating element is inoperative.]

Amdt. 23-49, E.. 03/11/96
FAR 23.1327 : Magnetic direction indicator.
(a)
[Except asprovidedinparagraph(b)of this section–

(1)
Each magneticdirectionindicatormustbeinstalled sothatits accuracyisnot excessively a.ectedby theairplane’svibrationormagnetic .elds; and

(2)
Thecompensatedinstallationmay nothaveadeviation,inlevel .ight,greater than ten degrees on any heading.

(b)
A magnetic nonstabilized direction indicator may deviate more than ten degrees due to the operation of electrically powered systems such as electrically heated windshields if either a magnetic stabilized direction indicator, which does not have a deviation in level .ight greater than ten degrees on any heading, or a gyrosco-pic direction indicator, is installed. Deviations of a magnetic nonstabilized direc-tion indicator of more than 10 degrees must be placarded in accordance with Sec. 23.1547(e).]

Amdt. 23-20 E.. 09/01/77
FAR 23.1329 : Automatic pilot system.
If an automatic pilot system is installed, it must meet the following :
(a)
Each system must be designed so that the automatic pilot can–

(1)
Bequicklyandpositivelydisengagedbythepilots topreventitfrominterfering with their control of the airplane; or

(2)
Be su.ciently overpowered by one pilot to let him control the airplane.

(b)
Iftheprovisionsofparagraph(a)(1) ofthis section are applied,thequick release (emergency) control must be located on the control wheel [(both control wheels if the airplane can be operated from either pilot seat)] on the side opposite the throttles, or onthe stick control,(both stick controls,ifthe airplane canbe operated from eitherpilot seat) such thatit canbe operated without moving thehandfrom its normal position on the control.

(c)
Unless thereis automatic synchronization, eachsystem musthave a means to readily indicate to thepilot the alignment of the actuatingdevice in relation to the control system it operates.

(d)
Each manually operated control for the system operation must be readily accessible to the pilot. Each control must operate in the same plane and sense of motion as speci.edinSec.23.779for cockpit controls.Thedirection of motion mustbeplainly indicated on or near each control.

(e)
Each system must be designed and adjusted so that, within the range of adjustment available to the pilot, it cannot produce hazardous loads on the airplane or create hazardous deviations in the .ight path, under any .ight condition appropriate to its use, either during normal operation or in the event of a malfunction, assuming that corrective actionbegins within a reasonableperiod of time.

(f)
Each system must be designed so that a single malfunction will not produce a har-doversignalin morethan onecontrol axis.If the automaticpilotintegratessignals from auxiliary controls or furnishes signals for operation of other equipment, po-sitive interlocks and sequencing of engagement to prevent improper operation are required.

(g)
There must be protection against adverse interaction of integrated components, re-sulting from a malfunction.

(h)
If the automatic pilot system can be coupled to airborne navigation equipment, meansmustbeprovidedtoindicatetothe .ight crewthecurrent modeof operation. Selector switch position is not acceptable as a means of indication.

Amdt. 23-49, E.. 03/11/96
FAR23.1331 :Instruments using apower[source.]
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 2(86)