(3)
[Flotation devices, whether stowedor deployed, may not interfere with or obs-truct the exits.]

(e)
Ramp exits. One type I exit only, or one Type II exit only, that is required in the side of thefuselage underparagraph(b) of this section, maybeinstalledinstead in the ramp of .oor ramp rotorcraft if–

(1)
Its installation in the side of the fuselage is impractical; and

(2)
Its installation in the ramp meets Sec. 29.813.

(f)
Tests. The proper functioning of each emergency exit must be shown by test. Amdt. 29-30, E.. 4/5/90

FAR 29.809 : Emergency exit arrangement.

(a)
Each emergency exit must consist of a movable door or hatch in the external walls of the fuselage and must provide an unobstructed opening to the outside.

(b)
Each emergency exit must be openable from the inside and from the outside.

(c)
The means of opening each emergency exit must be simple and obvious and may not require exceptional e.ort.

(d)
Theremustbemeansforlocking each emergency exit andforpreventing openingin .ight inadvertently or as a result of mechanical failure.

(e)
There mustbe meansto minimizetheprobability of thejamming of any emergency exitin a minor crashlanding as a result offuselagedeformation under the ultimate inertial forces in Sec. 29.783(d).

(f)
[Except as provided in paragraph (h) of this section, each land-based rotorcraft emergency exit must have an approved slide as stated in paragraph (g) of this section, or its equivalent, to assist occupants in descending to the ground from each .oor level exit and an approved rope, or its equivalent, for all other exits, if the exit threshold is more than 6 feet above the ground–

(1)
Withthe rotorcraft ontheground and with thelandinggear extended;

(2)
With one or more legs or part of the landing gear collapsed, broken, or not extended; and

(3)
With the rotorcraft resting on its side, if required by Sec. 29.803(d).

(g)
The slidefor eachpassenger emergency exit mustbe a self-supporting slide or equi-valent, and must be designed to meet the following requirements :

(1)
It must be automatically deployed, and deployment must begin during the interval between the time the exit opening means is actuated from inside the rotorcraft and the time the exit is fully opened. However, each passenger emergency exitwhichis alsoapassengerentrancedooror aservicedoormust be provided with means to prevent deployment of the slide when the exit is opened from either the inside or the outside under nonemergency conditions for normal use.

(2)
It must be automatically erected within 10 seconds after deployment is begun.

(3)
It must be of such length after full deployment that the lower end is self-supporting on the ground and provides safe evacuation of occupants to the ground after collapse of one or more legs or part of the landing gear.

(4)
It must have the capability, in 25-knot winds directed from the most critical angle,todeploy and, with the assistanceof only oneperson,to remain usable after full deployment to evacuate occupants safely to the ground.

(5)
Each slide installation must be quali.ed by .ve consecutive deployment and in.ation tests conducted (per exit) without failure, and at least three tests of each such .ve-test series must be conducted using a single representative sample of thedevice.The sampledevices mustbedeployed andin.atedby the system’s primary means after being subjected to the inertia forces speci.ed inSec.29.561(b).If anypart of the systemfails ordoes notfunctionproperly during the required tests, the cause of the failure or malfunction must be corrected by positive means and after that, the full series of .ve consecutive deployment and in.ation tests must be conducted without failure.