spaschal on DSK3GDR082PROD with CFR

Federal Aviation Administration, DOT

Section 27.801

harness may not be less than that corresponding to the inertial forces specified in Section 27.561(b), considering the occupant weight of at least 170 pounds, considering the dimensional characteristics of the restraint system installation, and using a distribution of at
least a 60-percent load to the safety
belt and at least a 40-percent load to
the shoulder harness. If the safety belt
is capable of being used without the
shoulder harness, the inertial forces
specified must be met by the safety
belt alone.
(h) When a headrest is used, the headrest and its supporting structure must
be designed to resist the inertia forces
specified in Section 27.561, with a 1.33 fitting
factor and a head weight of at least 13
pounds.
(i) Each seating device system includes the device such as the seat, the
cushions, the occupant restraint system, and attachment devices.
(j) Each seating device system may
use design features such as crushing or
separation of certain parts of the seats
to reduce occupant loads for the emergency landing dynamic conditions of
Section 27.562; otherwise, the system must remain intact and must not interfere
with rapid evacuation of the rotorcraft.
(k) For the purposes of this section, a
litter is defined as a device designed to
carry a nonambulatory person, primarily in a recumbent position, into
and on the rotorcraft. Each berth or
litter must be designed to withstand
the load reaction of an occupant
weight of at least 170 pounds when the
occupant is subjected to the forward
inertial factors specified in Section 27.561(b).
A berth or litter installed within 15Section or
less of the longitudinal axis of the
rotorcraft must be provided with a padded end-board, cloth diaphram, or
equivalent means that can withstand
the forward load reaction. A berth or
litter oriented greater than 15Section with
the longitudinal axis of the rotorcraft
must be equipped with appropriate restraints, such as straps or safety belts,
to withstand the forward load reaction.
In addition - 
(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 occu-

pying 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 27.561(b). The fitting factor
required by Section 27.625(d) shall be applied.
[Amdt. 27-21, 49 FR 44434, Nov. 6, 1984, as
amended by Amdt. 27-25, 54 FR 47319, Nov. 13,
1989; Amdt. 27-35, 63 FR 43285, Aug. 12, 1998]

Section 27.787 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 27.561.
(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 27.561, 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 27.561
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. 5074, 29 FR 15695, Nov. 24, 1964, as
amended by Amdt. 27-11, 41 FR 55469, Dec. 20,
1976; Amdt. 27-27, 55 FR 38966, Sept. 21, 1990]

Section 27.801 Ditching.
(a) If certification with ditching provisions is requested, the rotorcraft

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