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

° 

or 

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. 

(c) Under the emergency landing con-

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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