Federal Aviation Administration, DOT

Section 29.801

(1) The berth or litter must have a restraint system and must not have corners or other protuberances likely to
cause serious injury to a person occupying it during emergency landing conditions; and
(2) The berth or litter attachment
and the occupant restraint system attachments to the structure must be designed to withstand the critical loads
resulting from flight and ground load
conditions and from the conditions prescribed in Section 29.561(b). The fitting factor
required by Section 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]

spaschal on DSK3GDR082PROD with CFR

Section 29.787 Cargo and baggage compartments.
(a) Each cargo and baggage compartment must be designed for its placarded 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
Section 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 conditions of Section 29.561, cargo and baggage
compartments must - 
(1) Be positioned so that if the contents break loose they are unlikely to
cause injury to the occupants or restrict any of the escape facilities provided for use after an emergency landing; or
(2) Have sufficient strength to withstand the conditions specified in
Section 29.561, including the means of restraint and their attachments required
by paragraph (b) of this section. Sufficient 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.
[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]

Section 29.801

Ditching.

(a) If certification with ditching provisions is requested, the rotorcraft
must meet the requirements of this
section and SectionSection 29.807(d), 29.1411 and
29.1415.
(b) Each practicable design measure,
compatible with the general characteristics of the rotorcraft, must be taken
to minimize the probability that in an
emergency landing 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 configuration for which the ditching characteristics are known. Scoops, flaps,
projections, and any other factors likely to affect the hydrodynamic characteristics of the rotorcraft must be considered.
(d) It must be shown that, under reasonably probable water conditions, the
flotation time and trim of the rotorcraft will allow the occupants to leave
the rotorcraft and enter the liferafts
required by Section 29.1415. If compliance with
this provision is shown by bouyancy
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
bouyancy volume.
(e) Unless the effects 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 (as prescribed in paragraphs (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]

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