(ii)
So that the center line of the exit handle is within ± one inch of the projectedpoint of the arrow whenthehandlehas reachedfull travel and has released the locking mechanism; and

′
Elodie Roux. Septembre 2003
Subpart D : Design and Construction
(iii) With the word ”open” in red letters, one inch high, placed horizontally near the head of the arrow; and
(7) In addition to the requirements ofparagraph(a) ofthis section, the external marking of each emergency exit must–
(i)
Include a 2-inch colorband outlining the exit; and

(ii)
Have a color contrast thatis readilydistinguishablefrom the surrounding fuselage surface. The contrast must be such that if the re.ectance of the darkercoloris15percent orless,the re.ectance of thelighter color must be at least 45 percent. ”Re.ectance” is the ratio of the luminous .ux re-.ected by a body to the luminous .ux it receives. When the re.ectance of the darker color is greater than 15 percent, at least a 30 percent di.e-rence between its re.ectance and the re.ectance of the lighter color must be provided.]

Amdt. 23-46, E.. 06/16/94
FAR23.812 :[Emergencylighting.]
[When certi.cation to the emergencyexitprovisions ofSec.23.807(d)(4)is requested, the following apply :
(a)
An emergency lighting system, independent of the main cabin lighting system, must beinstalled.However,the source ofgeneral cabinillumination may be commonto boththe emergencyand mainlighting systemsifthepower supplyto the emergency lighting system is independent of the power supply to the main lighting system.

(b)
There must be a crew warning light that illuminates in the cockpit when power is on in the airplane and the emergency lighting control device is not armed.

(c)
Theemergencylightsmustbeoperablemanuallyfromthe .ightcrewstationandbe provided with automatic activation. The cockpit control device must have ”on”, ”o.,” and ”armed” positions so that, when armed in the cockpit, the lights will operate by automatic activation.

(d)
There must be a means to safeguard against inadvertent operation of the cockpit control device from the ”armed” or ”on” positions.

(e)
The cockpit control device must have provisions to allow the emergency lighting system to be armed or activated at any time that it may be needed.

(f)
When armed, the emergencylightingsystem must activate and remainlighted when–

(1)
The normal electricalpower of the airplaneislost; or

(2)
The airplane is subjected to an impact that results in a deceleration in excess of 2g and a velocity change in excess of 3.5 feet-per-second, acting along the longitudinal axis of the airplane; or

(3)
Any other emergency condition exists where automatic activation of the emer-gency lighting is necessary to aid with occupant evacuation.

(g)
Theemergencylighting system mustbe capableofbeing turned o. and resetby the .ightcrew after automatic activation.

(h)
The emergency lighting system must provide internal lighting, including–

(1) Illuminated emergency exit marking and locating signs, including those requi-red in Sec. 23.811(b);
(2)
Sources ofgeneralilluminationinthe cabinthatprovide an averageillumina-tion of not less than 0.05 foot-candle and an illumination at any point of not less than 0.01 foot-candle when measured along the center line of the main passenger aisle(s) and at the seat armrest height; and

(3)
Floorproximity emergency escapepath marking thatprovides emergency eva-cuation guidance for the airplane occupants when all sources of illumination more than 4 feet above the cabin aisle .oor are totally obscured.

(i)
The energy supply to each emergency lighting unit must provide the required le-vel of illumination for at least 10 minutes at the critical ambient conditions after activation of the emergency lighting system.
　
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本文鏈接地址：FAA規(guī)章 美國(guó)聯(lián)邦航空規(guī)章 Federal Aviation Regulations 2(43)