615 

Federal Aviation Administration, DOT 

§ 29.807 

appendix D of this part to demonstrate 
that the maximum seating capacity, 
including the crewmembers required by 
the operating rules, can be evacuated 
from the rotorcraft to the ground with-
in 90 seconds: 

(1) Rotorcraft with a seating capacity 

of more than 44 passengers. 

(2) Rotorcraft with all of the fol-

lowing: 

(i) Ten or more passengers per pas-

senger exit as determined under 
§ 29.807(b). 

(ii) No main aisle, as described in 

§ 29.815, for each row of passenger seats. 

(iii) Access to each passenger exit for 

each passenger by virtue of design fea-
tures 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 evacu-
ated within 90 seconds under the condi-
tions specified in § 29.803(d) if the Ad-
ministrator finds that the combination 
of analysis and tests will provide data, 
with respect to the emergency evacu-
ation capability of the rotorcraft, 
equivalent to that which would be ob-
tained by actual demonstration. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–3, 33 FR 967, Jan. 26, 
1968; Amdt. 27–26, 55 FR 8004, Mar. 6, 1990] 

§ 29.805

Flight crew emergency exits. 

(a) For rotorcraft with passenger 

emergency exits that are not conven-
ient to the flight crew, there must be 
flight crew emergency exits, on both 
sides of the rotorcraft or as a top 
hatch, in the flight crew area. 

(b) Each flight crew emergency exit 

must be of sufficient size and must be 
located so as to allow rapid evacuation 
of the flight crew. This must be shown 
by test. 

(c) Each exit must not be obstructed 

by water or flotation devices after a 
ditching. This must be shown by test, 
demonstration, or analysis. 

[Amdt. 29–3, 33 FR 968, Jan. 26, 1968, as 
amended by Amdt. 27–26, 55 FR 8004, Mar. 6, 
1990] 

§ 29.807

Passenger emergency exits. 

(a) 

Type. For the purpose of this part, 

the types of passenger emergency exit 
are as follows: 

(1) 

Type I. This type must have a rec-

tangular opening of not less than 24 
inches wide by 48 inches high, with cor-
ner radii not greater than one-third the 
width of the exit, in the passenger area 
in the side of the fuselage at floor level 
and as far away as practicable from 
areas that might become potential fire 
hazards in a crash. 

(2) 

Type II. This type is the same as 

Type I, except that the opening must 
be at least 20 inches wide by 44 inches 
high. 

(3) 

Type III. This type is the same as 

Type I, except that— 

(i) The opening must be at least 20 

inches wide by 36 inches high; and 

(ii) The exits need not be at floor 

level. 

(4) 

Type IV. This type must have a 

rectangular opening of not less than 19 
inches wide by 26 inches high, with cor-
ner radii not greater than one-third the 
width of the exit, in the side of the fu-
selage with a step-up inside the rotor-
craft of not more than 29 inches. 

Openings with dimensions larger than 
those specified in this section may be 
used, regardless of shape, if the base of 
the opening has a flat surface of not 
less than the specified width. 

(b) 

Passenger emergency exits; side-of- 

fuselage.  Emergency exits must be ac-
cessible to the passengers and, except 
as provided in paragraph (d) of this sec-
tion, must be provided in accordance 
with the following table: 

Passenger seating 

capacity 

Emergency exits for each 

side of the fuselage 

Type I 

Type II  Type III 

Type IV 

1 through 10 ............

............

............

............

1 

11 through 19 ..........

............

............

1 or 

2 

20 through 39 ..........

............

1  ............

1 

40 through 59 ..........

1  ............

............

1 

60 through 79 ..........

1  ............

1 or 

2 

(c) 

Passenger emergency exits; other 

than side-of-fuselage. In addition to the 
requirements of paragraph (b) of this 
section— 

(1) There must be enough openings in 

the top, bottom, or ends of the fuselage 
to allow evacuation with the rotorcraft 
on its side; or 

(2) The probability of the rotorcraft 

coming to rest on its side in a crash 
landing must be extremely remote. 

(d) 

Ditching emergency exits for pas-

sengers.  If certification with ditching 

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616 

14 CFR Ch. I (1–1–24 Edition) 

§ 29.809 

provisions is requested, ditching emer-
gency exits must be provided in accord-
ance with the following requirements 
and must be proven by test, demonstra-
tion, or analysis unless the emergency 
exits required by paragraph (b) of this 
section already meet these require-
ments. 

(1) For rotorcraft that have a pas-

senger seating configuration, excluding 
pilots seats, of nine seats or less, one 
exit above the waterline in each side of 
the rotorcraft, meeting at least the di-
mensions of a Type IV exit. 

(2) For rotorcraft that have a pas-

senger seating configuration, excluding 
pilots seats, of 10 seats or more, one 
exit above the waterline in a side of the 
rotorcraft meeting at least the dimen-
sions of a Type III exit, for each unit 
(or part of a unit) of 35 passenger seats, 
but no less than two such exits in the 
passenger cabin, with one on each side 
of the rotorcraft. However, where it 
has been shown through analysis, 
ditching demonstrations, or any other 
tests found necessary by the Adminis-
trator, that the evacuation capability 
of the rotorcraft during ditching is im-
proved by the use of larger exits, or by 
other means, the passenger seat to exit 
ratio may be increased. 

(3) Flotation devices, whether stowed 

or deployed, may not interfere with or 
obstruct the exits. 

(e) 

Ramp exits. One Type I exit only, 

or one Type II exit only, that is re-
quired in the side of the fuselage under 
paragraph (b) of this section, may be 
installed instead in the ramp of floor 
ramp rotorcraft if— 

(1) Its installation in the side of the 

fuselage is impractical; and 

(2) Its installation in the ramp meets 

§ 29.813. 

(f) 

Tests.  The proper functioning of 

each emergency exit must be shown by 
test. 

[Amdt. 29–3, 33 FR 968, Jan. 26, 1968, as 
amended by Amdt. 29–12, 41 FR 55472, Dec. 20, 
1976; Amdt. 27–26, 55 FR 8004, Mar. 6, 1990] 

§ 29.809

Emergency exit arrangement. 

(a) Each emergency exit must consist 

of a movable door or hatch in the ex-
ternal 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 emer-

gency exit must be simple and obvious 
and may not require exceptional effort. 

(d) There must be means for locking 

each emergency exit and for preventing 
opening in flight inadvertently or as a 
result of mechanical failure. 

(e) There must be means to minimize 

the probability of the jamming of any 
emergency exit in a minor crash land-
ing as a result of fuselage deformation 
under the ultimate inertial forces in 
§ 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 para-
graph (g) of this section, or its equiva-
lent, to assist occupants in descending 
to the ground from each floor level exit 
and an approved rope, or its equivalent, 
for all other exits, if the exit threshold 
is more that 6 feet above the ground— 

(1) With the rotorcraft on the ground 

and with the landing gear 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 § 29.803(d). 

(g) The slide for each passenger emer-

gency exit must be a self-supporting 
slide or equivalent, and must be de-
signed to meet the following require-
ments: 

(1) It must be automatically de-

ployed, 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 exit which is also 
a passenger entrance door or a service 
door must be provided with means to 
prevent deployment of the slide when 
the exit is opened from either the in-
side or the outside under non-
emergency 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 

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