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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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