(2)
Thecompensatedinstallationmay nothaveadeviation,inlevel .ight,greater than 10 degrees on any heading.

(b) A magnetic nonstabilized direction indicator may deviate more than 10 degrees due to the operation of electrically powered systems such as electrically heated wind-shields if either a magnetic stabilized direction indicator, which does not have a deviation in level .ight greater than 10 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. 27.1547(e).]
Amdt. 27-13, E.. 9/1/77
FAR 27.1329 : Automatic pilot system
(a)
Each automatic pilot system must be designed so that the automatic pilot can–

(1)
Besu.ciently overpoweredby onepilottoallowcontrol of the rotorcraft; and

(2)
Be readilyandpositivelydisengagedby eachpilot topreventitfrominterfering with control of the rotorcraft.

(b)
Unless thereis automatic synchronization, eachsystem musthave a means to readily indicatetothepilotthealignmentof theactuatingdeviceinrelationtothe control system it operates.

(c)
Eachmanually operated controlfor the system’s operation mustbe readily accessible to the pilots.

(d)
The system must be designed and adjusted so that, within the range of adjustment available to thepilot,it cannotproducehazardousloads on the rotorcraft 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.

(e)
If the automatic pilot integrates signals from auxiliary controls or furnishes signals for operationof other equipment,there mustbepositiveinterlocks and sequencing of engagement to prevent improper operation.

(f)
[If the automatic pilot system can be coupled to airborne navigation equipment, means must be provided to indicate to the pilots the current mode of operation. Selector switch position is not acceptable as a means of indication.]

Amdt. 27-35, E.. 9/8/98
FAR27.1335 :[Flightdirector systems.]
[If a .ight director system is installed, means must be provided to indicate to the .ight crew its current mode of operation. Selector switch position is not acceptable as a means of indication.] Amdt. 27-13, E.. 9/1/77
FAR 27.1337 : Powerplant instruments
(a) Instruments and instrument lines.
(1)
Each powerplant instrument line must meet the requirements of Secs. 27.961 and 27.993.

(2)
Each line carrying .ammable .uids under pressure must–

(i) Have restricting ori.ces or other safety devices at the source of pressure to prevent the escape of excessive .uid if the line fails; and
′
Elodie Roux. Septembre 2003
Subpart F–Equipment
(ii) Be installed and located so that the escape of .uids would not create a hazard.
(3) Each powerplant instrument that utilizes .ammable .uids must be installed and located so that the escape of .uid would not create a hazard.
(b)
Fuel quantity indicator. Each fuel quantity indicator must be installed to clearly indicate to the .ight crew the quantity of fuel in each tank in .ight. In addition–

(1)
Each fuel quantity indicator must be calibrated to read ”zero” during level .ight whenthequantity offuel remaininginthetankis equal tothe unusable fuel supply determined under Sec. 27.959;

(2)
When two or more tanks are closely interconnected by a gravity feed system and vented, and when it is impossible to feed from each tank separately, at least onefuelquantity indicator mustbeinstalled; and

(3)
Each exposed sight gauge used as a fuel quantity indicator must be protected against damage.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(123)