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555 

Federal Aviation Administration, DOT 

§ 27.1401 

Dihedral angle (light in-

cluded) 

Angle from right or left 

of longitudinal axis, 

measured from dead 

ahead 

Intensity 

(candles) 

and (forward red 

and green).

10

° 

to 10

°

...................

10

° 

to 20

°

...................

20

° 

to 110

°

.................

40 
30 

(rear white) ..............

110

° 

to 180

°

...............

20 

§ 27.1393

Minimum intensities in any 

vertical plane of forward and rear 
position lights. 

Each position light intensity must 

equal or exceed the applicable values in 
the following table: 

Angle above or below the horizontal plane 

Intensity, 

0

°

.........................................................................

1.00 

0

° 

to 5

°

................................................................

0.90 

5

° 

to 10

°

..............................................................

0.80 

10

° 

to 15

°

............................................................

0.70 

15

° 

to 20

°

............................................................

0.50 

20

° 

to 30

°

............................................................

0.30 

30

° 

to 40

°

............................................................

0.10 

40

° 

to 90

°

............................................................

0.05 

§ 27.1395

Maximum intensities in over-

lapping beams of forward and rear 
position lights. 

No position light intensity may ex-

ceed the applicable values in the fol-
lowing table, except as provided in 
§ 27.1389(b)(3). 

Overlaps 

Maximum Intensity 

Area A 

(candles) 

Area B 

(candles) 

Green in dihedral angle .............

10 1 

Red in dihedral angle ................

10 1 

Green in dihedral angle .............

5 1 

Red in dihedral angle ................

5 1 

Rear white in dihedral angle ......

5 1 

Rear white in dihedral angle .....

5 1 

Where— 

(a) Area A includes all directions in 

the adjacent dihedral angle that pass 
through the light source and intersect 
the common boundary plane at more 
than 10 degrees but less than 20 de-
grees, and 

(b) Area B includes all directions in 

the adjacent dihedral angle that pass 
through the light source and intersect 
the common boundary plane at more 
than 20 degrees. 

§ 27.1397

Color specifications. 

Each position light color must have 

the applicable International Commis-
sion on Illumination chromaticity co-
ordinates as follows: 

(a) 

Aviation red— 

is not greater than 0.335; and 
is not greater than 0.002. 

(b) 

Aviation green— 

is not greater than 0.440

¥

0.320

y

is not greater than y

¥

0.170; and 

is not less than 0.390

¥

0.170

x. 

(c) 

Aviation white— 

is not less than 0.300 and not greater than 

0.540; 

y  is not less than x

¥

0.040’’ or 

y

c

¥

0.010, 

whichever is the smaller; and 

y  is not greater than x  + 0.020 nor 

0.636

¥

0.400

x

Where 

y

c

is the 

coordinate of the Planck-

ian radiator for the value of 

considered. 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–6, 36 FR 12972, July 10, 
1971] 

§ 27.1399

Riding light. 

(a) Each riding light required for 

water operation must be installed so 
that it can— 

(1) Show a white light for at least 

two nautical miles at night under clear 
atmospheric conditions; and 

(2) Show a maximum practicable un-

broken light with the rotorcraft on the 
water. 

(b) Externally hung lights may be 

used. 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–2, 33 FR 964, Jan. 26, 
1968] 

§ 27.1401

Anticollision light system. 

(a) 

General.  If certification for night 

operation is requested, the rotorcraft 
must have an anticollision light sys-
tem that— 

(1) Consists of one or more approved 

anticollision lights located so that 
their emitted light will not impair the 
crew’s vision or detract from the con-
spicuity of the position lights; and 

(2) Meets the requirements of para-

graphs (b) through (f) of this section. 

(b) 

Field of coverage. The system must 

consist of enough lights to illuminate 
the vital areas around the rotorcraft, 
considering the physical configuration 
and flight characteristics of the rotor-
craft. The field of coverage must ex-
tend in each direction within at least 
30 degrees below the horizontal plane of 
the rotorcraft, except that there may 

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556 

14 CFR Ch. I (1–1–24 Edition) 

§ 27.1411 

be solid angles of obstructed visibility 
totaling not more than 0.5 steradians. 

(c) 

Flashing characteristics. The ar-

rangement of the system, that is, the 
number of light sources, beam width, 
speed of rotation, and other character-
istics, must give an effective flash fre-
quency of not less than 40, nor more 
than 100, cycles per minute. The effec-
tive flash frequency is the frequency at 
which the rotorcraft’s complete anti-
collision light system is observed from 
a distance, and applies to each sector 
of light including any overlaps that 
exist when the system consists of more 
than one light source. In overlaps, 
flash frequencies may exceed 100, but 
not 180, cycles per minute. 

(d) 

Color.  Each anticollision light 

must be aviation red and must meet 
the applicable requirements of § 27.1397. 

(e) 

Light intensity. The minimum 

light intensities in any vertical plane, 
measured with the red filter (if used) 
and expressed in terms of ‘‘effective’’ 
intensities, must meet the require-
ments of paragraph (f) of this section. 
The following relation must be as-
sumed: 

I

I t dt

t

t

e

t

t

=

+

(

)

( )

.

1

2

0 2

2

1

where: 

I

e

= effective intensity (candles). 

I(t)  = instantaneous intensity as a function 

of time. 

t

2

¥

t

1

= flash time interval (seconds). 

Normally, the maximum value of effective 
intensity is obtained when 

t

2

and 

t

1

are cho-

sen so that the effective intensity is equal to 
the instantaneous intensity at 

t

2

and 

t

1

(f) 

Minimum effective intensities for 

anticollision light. Each anticollision 
light effective intensity must equal or 
exceed the applicable values in the fol-
lowing table: 

Angle above or below the horizontal plane 

Effective 

intensity 

(candles) 

0

° 

to 5

°

................................................................

150 

5

° 

to 10

°

..............................................................

90 

10

° 

to 20

°

............................................................

30 

20

° 

to 30

°

............................................................

15 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–6, 36 FR 12972, July 10, 
1971; Amdt. 27–10, 41 FR 5290, Feb. 5, 1976] 

S

AFETY

E

QUIPMENT

 

§ 27.1411

General. 

(a) Required safety equipment to be 

used by the crew in an emergency, such 
as flares and automatic liferaft re-
leases, must be readily accessible. 

(b) Stowage provisions for required 

safety equipment must be furnished 
and must— 

(1) Be arranged so that the equip-

ment is directly accessible and its loca-
tion is obvious; and 

(2) Protect the safety equipment 

from damage caused by being subjected 
to the inertia loads specified in § 27.561. 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–11, 41 FR 55470, Dec. 20, 
1976] 

§ 27.1413

Safety belts. 

Each safety belt must be equipped 

with a metal to metal latching device. 

(Secs. 313, 314, and 601 through 610 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354, 1355, 
and 1421 through 1430) and sec. 6(c), Dept. of 
Transportation Act (49 U.S.C. 1655(c))) 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–15, 43 FR 46233, Oct. 5, 
1978; Amdt. 27–21, 49 FR 44435, Nov. 6, 1984] 

§ 27.1415

Ditching equipment. 

(a) Emergency flotation and sig-

naling equipment required by any oper-
ating rule in this chapter must meet 
the requirements of this section. 

(b) Each raft and each life preserver 

must be approved and must be installed 
so that it is readily available to the 
crew and passengers. The storage pro-
visions for life preservers must accom-
modate one life preserver for each oc-
cupant for which certification for 
ditching is requested. 

(c) Each raft released automatically 

or by the pilot must be attached to the 
rotorcraft by a line to keep it alongside 
the rotorcraft. This line must be weak 
enough to break before submerging the 
empty raft to which it is attached. 

(d) Each signaling device must be 

free from hazard in its operation and 
must be installed in an accessible loca-
tion. 

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as 
amended by Amdt. 27–11, 41 FR 55470, Dec. 20, 
1976] 

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