614 

14 CFR Ch. I (1–1–24 Edition) 

§ 29.787 

conditions and from the conditions pre-
scribed in § 29.561(b). The fitting factor 
required by § 29.625(d) shall be applied. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–24, 49 FR 44437, Nov. 6, 
1984; Amdt. 29–29, 54 FR 47320, Nov. 13, 1989; 
Amdt. 29–42, 63 FR 43285, Aug. 12, 1998] 

§ 29.787

Cargo and baggage compart-

ments. 

(a) Each cargo and baggage compart-

ment must be designed for its plac-
arded maximum weight of contents and 
for the critical load distributions at 
the appropriate maximum load factors 
corresponding to the specified flight 
and ground load conditions, except the 
emergency landing conditions of 
§ 29.561. 

(b) There must be means to prevent 

the contents of any compartment from 
becoming a hazard by shifting under 
the loads specified in paragraph (a) of 
this section. 

(c) Under the emergency landing con-

ditions of § 29.561, cargo and baggage 
compartments must— 

(1) Be positioned so that if the con-

tents break loose they are unlikely to 
cause injury to the occupants or re-
strict any of the escape facilities pro-
vided for use after an emergency land-
ing; or 

(2) Have sufficient strength to with-

stand the conditions specified in 
§ 29.561, including the means of re-
straint and their attachments required 
by paragraph (b) of this section. Suffi-
cient strength must be provided for the 
maximum authorized weight of cargo 
and baggage at the critical loading dis-
tribution. 

(d) If cargo compartment lamps are 

installed, each lamp must be installed 
so as to prevent contact between lamp 
bulb and cargo. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–12, 41 FR 55472, Dec. 20, 
1976; Amdt. 29–31, 55 FR 38966, Sept. 21, 1990] 

§ 29.801

Ditching. 

(a) If certification with ditching pro-

visions is requested, the rotorcraft 
must meet the requirements of this 
section and §§ 29.807(d), 29.1411 and 
29.1415. 

(b) Each practicable design measure, 

compatible with the general character-
istics of the rotorcraft, must be taken 

to minimize the probability that in an 
emergency landing on water, the be-
havior 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 com-
parison with rotorcraft of similar con-
figuration for which the ditching char-
acteristics are known. Scoops, flaps, 
projections, and any other factors like-
ly to affect the hydrodynamic charac-
teristics of the rotorcraft must be con-
sidered. 

(d) It must be shown that, under rea-

sonably probable water conditions, the 
flotation time and trim of the rotor-
craft will allow the occupants to leave 
the rotorcraft and enter the liferafts 
required by § 29.1415. If compliance with 
this provision is shown by bouyancy 
and trim computations, appropriate al-
lowances must be made for probable 
structural damage and leakage. If the 
rotorcraft has fuel tanks (with fuel jet-
tisoning provisions) that can reason-
ably be expected to withstand a ditch-
ing without leakage, the jettisonable 
volume of fuel may be considered as 
bouyancy volume. 

(e) Unless the effects of the collapse 

of external doors and windows are ac-
counted for in the investigation of the 
probable behavior of the rotorcraft in a 
water landing (as prescribed in para-
graphs (c) and (d) of this section), the 
external doors and windows must be 
designed to withstand the probable 
maximum local pressures. 

[Amdt. 29–12, 41 FR 55472, Dec. 20, 1976] 

§ 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, con-
sidering the possibility of fire. 

(b) Passenger entrance, crew, and 

service doors may be considered as 
emergency exits if they meet the re-
quirements of this section and of 
§§ 29.805 through 29.815. 

(c) [Reserved] 
(d) Except as provided in paragraph 

(e) of this section, the following cat-
egories of rotorcraft must be tested in 
accordance with the requirements of 

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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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