321 

Federal Aviation Administration, DOT 

§ 23.1501 

(5) Except for recorders powered sole-

ly by the engine-driven electrical gen-
erator system, there is an automatic 
means to simultaneously stop a re-
corder that has a data erasure feature 
and prevent each erasure feature from 
functioning, within 10 minutes after 
crash impact; 

(6) Any single electrical failure exter-

nal to the recorder does not disable 
both the cockpit voice recorder and the 
flight data recorder; and 

(7) It is in a separate container from 

the cockpit voice recorder when both 
are required. If used to comply with 
only the flight data recorder require-
ments, a combination unit may be in-
stalled. If a combination unit is in-
stalled as a cockpit voice recorder to 
comply with § 23.1457(e)(2), a combina-
tion unit must be used to comply with 
this flight data recorder requirement. 

(b) Each nonejectable record con-

tainer must be located and mounted so 
as to minimize the probability of con-
tainer rupture resulting from crash im-
pact and subsequent damage to the 
record from fire. In meeting this re-
quirement the record container must 
be located as far aft as practicable, but 
need not be aft of the pressurized com-
partment, and may not be where aft- 
mounted engines may crush the con-
tainer upon impact. 

(c) A correlation must be established 

between the flight recorder readings of 
airspeed, altitude, and heading and the 
corresponding readings (taking into ac-
count correction factors) of the first pi-
lot’s instruments. The correlation 
must cover the airspeed range over 
which the airplane is to be operated, 
the range of altitude to which the air-
plane is limited, and 360 degrees of 
heading. Correlation may be estab-
lished on the ground as appropriate. 

(d) Each recorder container must: 
(1) Be either bright orange or bright 

yellow; 

(2) Have reflective tape affixed to its 

external surface to facilitate its loca-
tion under water; and 

(3) Have an underwater locating de-

vice, when required by the operating 
rules of this chapter, on or adjacent to 
the container which is secured in such 
a manner that they are not likely to be 
separated during crash impact. 

(e) Any novel or unique design or 

operational characteristics of the air-
craft shall be evaluated to determine if 
any dedicated parameters must be re-
corded on flight recorders in addition 
to or in place of existing requirements. 

[Amdt. 23–35, 53 FR 26143, July 11, 1988, as 
amended by Amdt. 23–58, 73 FR 12562, Mar. 7, 
2008; 74 FR 32800, July 9, 2009] 

§ 23.1461

Equipment containing high 

energy rotors. 

(a) Equipment, such as Auxiliary 

Power Units (APU) and constant speed 
drive units, containing high energy ro-
tors must meet paragraphs (b), (c), or 
(d) of this section. 

(b) High energy rotors contained in 

equipment must be able to withstand 
damage caused by malfunctions, vibra-
tion, abnormal speeds, and abnormal 
temperatures. In addition— 

(1) Auxiliary rotor cases must be able 

to contain damage caused by the fail-
ure of high energy rotor blades; and 

(2) Equipment control devices, sys-

tems, and instrumentation must rea-
sonably ensure that no operating limi-
tations affecting the integrity of high 
energy rotors will be exceeded in serv-
ice. 

(c) It must be shown by test that 

equipment containing high energy ro-
tors can contain any failure of a high 
energy rotor that occurs at the highest 
speed obtainable with the normal speed 
control devices inoperative. 

(d) Equipment containing high en-

ergy rotors must be located where 
rotor failure will neither endanger the 
occupants nor adversely affect contin-
ued safe flight. 

[Amdt. 23–20, 42 FR 36969, July 18, 1977, as 
amended by Amdt. 23–49, 61 FR 5170, Feb. 9, 
1996] 

Subpart G—Operating Limitations 

and Information 

§ 23.1501

General. 

(a) Each operating limitation speci-

fied in §§ 23.1505 through 23.1527 and 
other limitations and information nec-
essary for safe operation must be es-
tablished. 

(b) The operating limitations and 

other information necessary for safe 
operation must be made available to 

VerDate Mar<15>2010 

10:12 Mar 18, 2014

Jkt 232046

PO 00000

Frm 00331

Fmt 8010

Sfmt 8010

Y:\SGML\232046.XXX

232046

pmangrum on DSK3VPTVN1PROD with CFR