title-14-part-27-sec27-801

522

14 CFR Ch. I (1–1–24 Edition)

§ 27.787

harness may not be less than that cor-
responding to the inertial forces speci-
fied in § 27.561(b), considering the occu-
pant weight of at least 170 pounds, con-
sidering the dimensional characteris-
tics of the restraint system installa-
tion, 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 head-

rest and its supporting structure must
be designed to resist the inertia forces
specified in § 27.561, with a 1.33 fitting
factor and a head weight of at least 13
pounds.

(i) Each seating device system in-

cludes the device such as the seat, the
cushions, the occupant restraint sys-
tem, 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 emer-
gency landing dynamic conditions of
§ 27.562; otherwise, the system must re-
main 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, pri-
marily 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 § 27.561(b).
A berth or litter installed within 15

less of the longitudinal axis of the
rotorcraft must be provided with a pad-
ded end-board, cloth diaphram, or
equivalent means that can withstand
the forward load reaction. A berth or
litter oriented greater than 15

with

the longitudinal axis of the rotorcraft
must be equipped with appropriate re-
straints, such as straps or safety belts,
to withstand the forward load reaction.
In addition—

(1) The berth or litter must have a re-

straint system and must not have cor-
ners or other protuberances likely to
cause serious injury to a person occu-

pying it during emergency landing con-
ditions; and

(2) The berth or litter attachment

and the occupant restraint system at-
tachments to the structure must be de-
signed to withstand the critical loads
resulting from flight and ground load
conditions and from the conditions pre-
scribed in § 27.561(b). The fitting factor
required by § 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]

§ 27.787

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
§ 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.

ditions of § 27.561, 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 § 27.561
including the means of restraint, and
their attachments, required by para-
graph (b) of this section. Sufficient
strength must be provided for the max-
imum 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. 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]

§ 27.801

Ditching.

(a) If certification with ditching pro-

visions is requested, the rotorcraft

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§ 27.807

must meet the requirements of this
section and §§ 27.807(d), 27.1411 and
27.1415.

(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.

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 factor likely
to affect the hydrodynamic character-
istics of the rotorcraft must be consid-
ered.

(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 life rafts
required by § 27.1415. If compliance with
this provision is shown by buoyancy
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
buoyancy 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. 27–11, 41 FR 55469, Dec. 20, 1976]

§ 27.805

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.

must not be obstructed by water or flo-
tation devices after an emergency
landing on water. This must be shown
by test, demonstration, or analysis.

[Doc. No. 29247, 64 FR 45094, Aug. 18, 1999]

§ 27.807

Emergency exits.

(a)

Number and location. (1) There

must be at least one emergency exit on
each side of the cabin readily acces-
sible to each passenger. One of these
exits must be usable in any probable
attitude that may result from a crash;

(2) Doors intended for normal use

may also serve as emergency exits, pro-
vided that they meet the requirements
of this section; and

(3) If emergency flotation devices are

installed, there must be an emergency
exit accessible to each passenger on
each side of the cabin that is shown by
test, demonstration, or analysis to;

(i) Be above the waterline; and
(ii) Open without interference from

flotation devices, whether stowed or
deployed.

(b)

Type and operation. Each emer-

gency exit prescribed by paragraph (a)
of this section must—

(1) Consist of a movable window or

panel, or additional external door, pro-
viding an unobstructed opening that
will admit a 19-by 26-inch ellipse;

(2) Have simple and obvious methods

of opening, from the inside and from
the outside, which do not require ex-
ceptional effort;

(3) Be arranged and marked so as to

be readily located and opened even in
darkness; and

(4) Be reasonably protected from

jamming by fuselage deformation.

(c)

Tests. The proper functioning of

each emergency exit must be shown by
test.

(d)

Ditching emergency exits for pas-

sengers. If certification with ditching
provisions is requested, the markings
required by paragraph (b)(3) of this sec-
tion must be designed to remain visible
if the rotorcraft is capsized and the
cabin is submerged.