(b) of this section. Su.cient strength must be provided for the maximum authorized weight of cargo and baggage at the critical loading distribution.]

(d)
If cargo compartment lamps are installed, each lamp must be installed so as to prevent contact between lamp bulb and cargo.

Amdt. 29-31, E.. 10/22/90
FAR29.801 :[Ditching.]
(a) [If certi.cation with ditching provisions is requested, the rotorcraft must meet the requirements of this section and Secs. 29.807(d), 29.1411 and 29.1415.
′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction
(b)
Eachpracticabledesign measure, compatible withthegeneral characteristics of the rotorcraft, must be taken to minimize the probability that in an emergency lan-ding on water, the behavior of the rotorcraft would cause immediate injury to the occupants or would make it impossible for them to escape.

(c)
The probable behavior of the rotorcraft in a water landing must be investigated by model tests or by comparison with rotorcraft of similar con.guration for which the ditching characteristics are known. Scoops, .aps, projections, and any other factors likely to a.ect the hydrodynamic characteristics of the rotorcraft must be considered.

(d)
It must be shown that, under reasonably probable water conditions, the .otation time and trim of the rotorcraft will allow the occupants to leave the rotorcraft and enter the liferafts required by Sec. 29.1415. If compliance with this provision is shown by buoyancy and trim computations, appropriate allowances must be made for probable structural damage and leakage. If the rotorcraft has fuel tanks (with fuel jettisoning provisions) that can reasonably be expected to withstand a ditching without leakage, the jettisonable volume of fuel may be considered as buoyancy volume.

(e)
Unless the e.ects of the collapse of external doors and windows are accounted for in the investigation of the probable behavior of the rotorcraft in a water landing (asprescribedinparagraphs(c) and(d) ofthis section),the externaldoorsand windows must be designed to withstand the probable maximum local pressures.]

Amdt. 29-12, E.. 2/1/77
FAR 29.803 : Emergency evacuation.
(a)
Each crew and passenger area must have means for rapid evacuation in a crash landing, with the landing gear (1) extended and (2) retracted, considering the possibility of .re.

(b)
Passenger entrance, crew, and service doors may be considered as emergency exits if they meet the requirements of this section and of Secs. 29.805 through 29.815.

(c)
[[Reserved.]

(d)
Except asprovidedinparagraph(e) of this section, thefollowing categories of ro-torcraft must be tested in accordance with the requirements of Appendix D of this part to demonstrate that the maximum seating capacity, including the crewmem-bers required by the operating rules, can be evacuated from the rotorcraft to the ground within 90 seconds.

(1)
Rotorcraft with a seating capacity of more than 44 passengers.

(2)
Rotorcraft with all of the following :

(i)
Ten or morepassengersperpassenger exitasdetermined underSec.29.807(b).

(ii)
No main aisle, asdescribedinSec.29.815,for eachrow ofpassenger seats.

(iii) Access to each passenger exit for each passenger by virtue of design features of seats, such as folding or break-over seat backs or folding seats.

(e)
A combination of analysis and tests may be used to show that the rotorcraft is capable of being evacuated within 90 seconds under the conditions speci.ed in Sec. 29.803(d)if theAdministrator .ndsthatthecombinationof analysisand testswill providedata, withrespect to the emergency evacuation capability of the rotorcraft, equivalent to that which would be obtained by actual demonstration.]

Amdt. 29-30, E.. 4/5/90
FAR 29.805 : Flight crew emergency exits.
　
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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(46)