520 

14 CFR Ch. I (1–1–19 Edition) 

Pt. 135, App. A 

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 qual-

ify as a floor level emergency exit. Each ad-
ditional 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 en-
trance 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 op-
posite 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 sec-
onds. 

(e) Each emergency exit must be marked 

with the word ‘‘Exit’’ by a sign which has 
white letters 1 inch high on a red back-
ground 2 inches high, be self-illuminated or 
independently internally electrically illumi-
nated, 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 ex-
ceed the values in the following table: 

Total seating capacity 

Minimum main passenger 

aisle width 

Less than 25 

inches from 

floor 

25 inches 
and more 
from floor 

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

9 inches .......

15 inches. 

Miscellaneous 

33. 

Lightning strike protection. 

Parts that 

are electrically insulated from the basic air-
frame must be connected to it through light-
ning arrestors unless a lightning strike on 
the insulated part— 

(a) Is improbable because of shielding by 

other parts; or 

(b) Is not hazardous. 

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 es-

tablish, on the basis of the airplane’s oper-
ational needs, the adequacy of the ice protec-
tion system for the various components of 
the airplane. In addition, tests of the ice pro-
tection system must be conducted to dem-
onstrate that the airplane is capable of oper-
ating 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 informa-
tion the applicant considers essential for the 
proper maintenance of the airplane. That in-
formation must include the following: 

(a) Description of systems, including elec-

trical, 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 applica-

ble to the various systems. 

(d) Tolerances and adjustments necessary 

for proper functioning. 

(e) Methods of leveling, raising, and tow-

ing. 

(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 air-
plane. 

(i) Special repair methods applicable to the 

airplane. 

(j) Special inspection techniques, such as 

X-ray, ultrasonic, and magnetic particle in-
spection. 

(k) List of special tools. 

Propulsion 

General 

36. 

Vibration characteristics. 

For turbo-

propeller powered airplanes, the engine in-
stallation must not result in vibration char-
acteristics of the engine exceeding those es-
tablished during the type certification of the 
engine. 

37. 

In flight restarting of engine. 

If the en-

gine 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 con-
sistently accomplished. Restart information 

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