Amdt. 29-12, E.. 2/1/77
FAR 29.1323 : Airspeed indicating system.
For each airspeed indicating system, the following apply :
(a)
Each airspeedinstrument mustbe calibratedtoindicatetrue airspeed(at sealevel with a standard atmosphere) with a minimum practicable instrument calibration error whenthe correspondingpitot and staticpressures are applied.

(b)
Each system must be calibrated to determine system error excluding airspeed ins-trument error. This calibration must be determined–

(1)
Inlevel .ightatspeedsof20knotsandgreater,and overanappropriaterange of speeds for .ight conditions of climb and autorotation; and

(2)
During takeo., with repeatable and readable indications that ensure–

(i)
Consistentrealizationof the .eldlengthsspeci.edintheRotorcraftFlight Manual; and

(ii) Avoidance of the critical areas of the height-velocity envelope as establi-shed under Sec. 29.87.

(c)
For Category A rotorcraft–

(1)
Theindication must allow consistentde.nition of the[takeo.] decisionpoint; and

(2)
The system error, excludingthe airspeedinstrument calibration error, may not exceed–

(i)
Three percent or 5 knots, whichever is greater, in level .ight at speeds above80percent oftakeo. safety speed; and

(ii)
Ten knots in climb at speeds from 10 knots below takeo. safety speed to 10 knots above VY.

(d)
For Category B rotorcraft, the system error, excluding the airspeed instrument ca-libration error, may not exceed 3 percent or 5 knots, whichever is greater, in level .ight at speeds above 80 percent of the climbout speed attained at 50 feet when complying with Sec. 29.63.

(e)
Each system must be arranged, so far as practicable, to prevent malfunction or serious error due to the entry of moisture, dirt, or other substances.

(f)
Each system must have a heated pitot tube or an equivalent means of preventing

malfunction due to icing. Amdt. 29-44, E.. 11/17/99
FAR 29.1325 : Static pressure and pressure altimeter systems.
(a)
Each instrument with static air case connections must be vented to the outside atmospherethrough an appropriatepiping system.

(b)
Each vent must be located where its ori.ces are least a.ected by air.ow variation, moisture, or other foreign matter.

(c)
Each static pressure port must be designed and located in such manner that the correlation between air pressure in the static pressure system and true ambient atmospheric static pressure is not altered when the rotorcraft encounters icing conditions.An anti-icing means or an alternate source of staticpressure maybe used in showing compliance with this requirement. If the reading of the altimeter, when on the alternate static pressure system, di.ers from the reading of the altimeter when on the primary static system by more than 50 feet, a correction card must be provided for the alternate static system.

(d)
Except for the vent into the atmosphere, each system must be airtight.

(e)
Each pressure altimeter must be approved and calibrated to indicate pressure alti-tudein a standard atmospherewith a minimumpracticablecalibrationerrorwhen the corresponding static pressures are applied.

(f)
[Each system must be designed and installed so that an error in indicted pressure altitude, at sealevel, with a standard atmosphere, excludinginstrument calibration error, does not result in an error of more than ±30 feet per 100 knots speed. However, the error need not be less than ±30 feet.]

(g)
Except asprovidedinparagraph(h) ofthis section,ifthe staticpressure system incorporatesboth aprimary and an alternatestaticpressuresource,the meansfor selecting one or the other source must be designed so that–

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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 5(90)