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14 CFR Ch. I (1–1–24 Edition)
§ 29.812
(1) There must be a 2-inch colored
band outlining each passenger emer-
gency exit, except small rotorcraft
with a maximum weight of 12,500
pounds or less may have a 2-inch col-
ored band outlining each exit release
lever or device of passenger emergency
exits which are normally used doors.
(2) Each outside marking, including
the band, must have color contrast to
be readily distinguishable from the sur-
rounding fuselage surface. The contrast
must be such that, if the reflectance of
the darker color is 15 percent or less,
the reflectance of the lighter color
must be at least 45 percent. ‘‘Reflec-
tance’’ is the ratio of the luminous flux
reflected by a body to the luminous
flux it receives. When the reflectance
of the darker color is greater than 15
percent, at least a 30 percent difference
between its reflectance and the reflec-
tance of the lighter color must be pro-
vided.
(g) Exits marked as such, though in
excess of the required number of exits,
must meet the requirements for emer-
gency exits of the particular type.
Emergency exits need only be marked
with the word ‘‘Exit.’’
[Amdt. 29–3, 33 FR 968, Jan. 26, 1968, as
amended by Amdt. 29–24, 49 FR 44438, Nov. 6,
1984; Amdt. 27–26, 55 FR 8004, Mar. 6, 1990;
Amdt. 29–31, 55 FR 38967, Sept. 21, 1990]
§ 29.812
Emergency lighting.
For transport Category A rotorcraft,
the following apply:
(a) A source of light with its power
supply independent of the main light-
ing system must be installed to—
(1) Illuminate each passenger emer-
gency exit marking and locating sign;
and
(2) Provide enough general lighting
in the passenger cabin so that the aver-
age illumination, when measured at 40-
inch intervals at seat armrest height
on the center line of the main pas-
senger aisle, is at least 0.05 foot-candle.
(b) Exterior emergency lighting must
be provided at each emergency exit.
The illumination may not be less than
0.05 foot-candle (measured normal to
the direction of incident light) for min-
imum width on the ground surface,
with landing gear extended, equal to
the width of the emergency exit where
an evacuee is likely to make first con-
tact with the ground outside the cabin.
The exterior emergency lighting may
be provided by either interior or exte-
rior sources with light intensity meas-
urements made with the emergency
exits open.
(c) Each light required by paragraph
(a) or (b) of this section must be oper-
able manually from the cockpit station
and from a point in the passenger com-
partment that is readily accessible.
The cockpit control device must have
an ‘‘on,’’ ‘‘off,’’ and ‘‘armed’’ position
so that when turned on at the cockpit
or passenger compartment station or
when armed at the cockpit station, the
emergency lights will either illuminate
or remain illuminated upon interrup-
tion of the rotorcraft’s normal electric
power.
(d) Any means required to assist the
occupants in descending to the ground
must be illuminated so that the erect-
ed assist means is visible from the
rotorcraft.
(1) The assist means must be pro-
vided with an illumination of not less
than 0.03 foot-candle (measured normal
to the direction of the incident light)
at the ground end of the erected assist
means where an evacuee using the es-
tablished escape route would normally
make first contact with the ground,
with the rotorcraft in each of the atti-
tudes corresponding to the collapse of
one or more legs of the landing gear.
(2) If the emergency lighting sub-
system illuminating the assist means
is independent of the rotorcraft’s main
emergency lighting system, it—
(i) Must automatically be activated
when the assist means is erected;
(ii) Must provide the illumination re-
quired by paragraph (d)(1); and
(iii) May not be adversely affected by
stowage.
(e) The energy supply to each emer-
gency lighting unit must provide the
required level of illumination for at
least 10 minutes at the critical ambient
conditions after an emergency landing.
(f) If storage batteries are used as the
energy supply for the emergency light-
ing system, they may be recharged
from the rotorcraft’s main electrical
power system provided the charging
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