Pt. 135, App. A

14 CFR Ch. I (1-1-19 Edition)

crewmembers to determine whether external
doors and exits, for which the initial opening
movement is outward, are fully locked. In
addition, there must be a visual means to
signal to crewmembers when normally used
external doors are closed and fully locked.
(c) The passenger entrance door must qualify as a floor level emergency exit. Each additional required emergency exit except floor
level exits must be located over the wing or
must be provided with acceptable means to
assist the occupants in descending to the
ground. In addition to the passenger entrance door:
(1) For a total seating capacity of 15 or
less, an emergency exit as defined in FAR
23.807(b) is required on each side of the cabin.
(2) For a total seating capacity of 16
through 23, three emergency exits as defined
in FAR 23.807(b) are required with one on the
same side as the door and two on the side opposite the door.
(d) An evacuation demonstration must be
conducted utilizing the maximum number of
occupants for which certification is desired.
It must be conducted under simulated night
conditions utilizing only the emergency
exits on the most critical side of the aircraft.
The participants must be representative of
average airline passengers with no previous
practice or rehearsal for the demonstration.
Evacuation must be completed within 90 seconds.
(e) Each emergency exit must be marked
with the word  - Exit -  by a sign which has
white letters 1 inch high on a red background 2 inches high, be self-illuminated or
independently internally electrically illuminated, and have a minimum luminescence
(brightness) of at least 160 microlamberts.
The colors may be reversed if the passenger
compartment illumination is essentially the
same.
(f) Access to window type emergency exits
must not be obstructed by seats or seat
backs.
(g) The width of the main passenger aisle
at any point between seats must equal or exceed the values in the following table:
Minimum main passenger
aisle width
Total seating capacity

Less than 25
inches from
floor

10 through 23 .........................

9 inches .......

34. Ice protection. If certification with ice
protection provisions is desired, compliance
with the following must be shown:
(a) The recommended procedures for the
use of the ice protection equipment must be
set forth in the Airplane Flight Manual.
(b) An analysis must be performed to establish, on the basis of the airplane-s operational needs, the adequacy of the ice protection system for the various components of
the airplane. In addition, tests of the ice protection system must be conducted to demonstrate that the airplane is capable of operating safely in continuous maximum and
intermittent maximum icing conditions as
described in appendix C of part 25 of this
chapter.
(c) Compliance with all or portions of this
section may be accomplished by reference,
where applicable because of similarity of the
designs, to analysis and tests performed by
the applicant for a type certificated model.
35. Maintenance information. The applicant
must make available to the owner at the
time of delivery of the airplane the information the applicant considers essential for the
proper maintenance of the airplane. That information must include the following:
(a) Description of systems, including electrical, hydraulic, and fuel controls.
(b) Lubrication instructions setting forth
the frequency and the lubricants and fluids
which are to be used in the various systems.
(c) Pressures and electrical loads applicable to the various systems.
(d) Tolerances and adjustments necessary
for proper functioning.
(e) Methods of leveling, raising, and towing.
(f) Methods of balancing control surfaces.
(g) Identification of primary and secondary
structures.
(h) Frequency and extent of inspections
necessary to the proper operation of the airplane.
(i) Special repair methods applicable to the
airplane.
(j) Special inspection techniques, such as
X-ray, ultrasonic, and magnetic particle inspection.
(k) List of special tools.
Propulsion

25 inches
and more
from floor

General

15 inches.

Miscellaneous
33. Lightning strike protection. Parts that
are electrically insulated from the basic airframe must be connected to it through lightning arrestors unless a lightning strike on
the insulated part - 
(a) Is improbable because of shielding by
other parts; or
(b) Is not hazardous.

36. Vibration characteristics. For turbopropeller powered airplanes, the engine installation must not result in vibration characteristics of the engine exceeding those established during the type certification of the
engine.
37. In flight restarting of engine. If the engine on turbopropeller powered airplanes
cannot be restarted at the maximum cruise
altitude, a determination must be made of
the altitude below which restarts can be consistently accomplished. Restart information

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