Sec. 25.809 - Emergency exit arrangement.
(a) Each emergency exit, including a
flight crew emergency exit, must be a movable door or hatch in the
external walls of the fuselage, allowing unobstructed opening to the
(b) Each emergency exit must be openable
from the inside and the outside except that sliding window emergency exits
in the flight crew area need not be openable from the outside if other
approved exits are convenient and readily accessible to the flight crew
area. Each emergency exit must be capable of being opened, when there is
no fuselage deformation --
(1) With the airplane in the normal
ground attitude and in each of the attitudes corresponding to collapse of
one or more legs of the landing gear; and
(2) Within 10 seconds measured from the
time when the opening means is actuated to the time when the exit is fully
(c) The means of opening emergency exits
must be simple and obvious and may not require exceptional effort.
Internal exit-opening means involving sequence operations (such as
operation of two handles or latches or the release of safety catches) may
be used for flight crew emergency exits if it can be reasonably
established that these means are simple and obvious to crewmembers trained
in their use.
(d) If a single power-boost or single
power-operated system is the primary system for operating more than one
exit in an emergency, each exit must be capable of meeting the
requirements of paragraph (b) of this section in the event of failure of
the primary system. Manual operation of the exit (after failure of the
primary system) is acceptable.
(e) Each emergency exit must be shown by
tests, or by a combination of analysis and tests, to meet the requirements
of paragraphs (b) and (c) of this section.
(f) There must be a means to lock each
emergency exit and to safeguard against its opening in flight, either
inadvertently by persons or as a result of mechanical failure. In
addition, there must be a means for direct visual inspection of the
locking mechanism by crewmembers to determine that each emergency exit,
for which the initial opening movement is outward, is fully locked.
(g) There must be provisions to minimize
the probability of jamming of the emergency exits resulting from fuselage
deformation in a minor crash landing.
(h) When required by the operating rules
for any large passenger-carrying turbojet-powered airplane, each ventral
exit and tailcone exit must be --
(1) Designed and constructed so that it
cannot be opened during flight; and
(2) Marked with a placard readable from
a distance of 30 inches and installed at a conspicuous location near the
means of opening the exit, stating that the exit has been designed and
constructed so that it cannot be opened during flight.
[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25-15, 32 FR 13264, Sept. 20, 1967; Amdt. 25-32, 37 FR
3970, Feb. 24, 1972; Amdt. 25-34, 37 FR 25355, Nov. 30, 1972; Amdt. 25-46,
43 FR 50597, Oct. 30, 1978; Amdt. 25-47, 44 FR 61325, Oct. 25, 1979; Amdt.
25-72, 55 FR 29782, July 20, 1990]