116 

14 CFR Ch. I (1–1–24 Edition) 

§ 121.306 

means for preventing malfunctioning 
due to icing. 

(b) A sensitive altimeter. 
(c) A sweep-second hand clock (or ap-

proved equivalent). 

(d) A free-air temperature indicator. 
(e) A gyroscopic bank and pitch indi-

cator (artificial horizon). 

(f) A gyroscopic rate-of-turn indi-

cator combined with an integral slip- 
skid indicator (turn-and-bank indi-
cator) except that only a slip-skid indi-
cator is required when a third attitude 
instrument system usable through 
flight attitudes of 360

° 

of pitch and roll 

is installed in accordance with para-
graph (k) of this section. 

(g) A gyroscopic direction indicator 

(directional gyro or equivalent). 

(h) A magnetic compass. 
(i) A vertical speed indicator (rate-of- 

climb indicator). 

(j) On the airplane described in this 

paragraph, in addition to two gyro-
scopic bank and pitch indicators (arti-
ficial horizons) for use at the pilot sta-
tions, a third such instrument is in-
stalled in accordance with paragraph 
(k) of this section: 

(1) On each turbojet powered air-

plane. 

(2) On each turbopropeller powered 

airplane having a passenger-seat con-
figuration of more than 30 seats, ex-
cluding each crewmember seat, or a 
payload capacity of more than 7,500 
pounds. 

(3) On each turbopropeller powered 

airplane having a passenger-seat con-
figuration of 30 seats or fewer, exclud-
ing each crewmember seat, and a pay-
load capacity of 7,500 pounds or less 
that is manufactured on or after March 
20, 1997. 

(4) After December 20, 2010, on each 

turbopropeller powered airplane having 
a passenger seat configuration of 10–30 
seats and a payload capacity of 7,500 
pounds or less that was manufactured 
before March 20, 1997. 

(k) When required by paragraph (j) of 

this section, a third gyroscopic bank- 
and-pitch indicator (artificial horizon) 
that: 

(1) Is powered from a source inde-

pendent of the electrical generating 
system; 

(2) Continues reliable operation for a 

minimum of 30 minutes after total fail-
ure of the electrical generating system; 

(3) Operates independently of any 

other attitude indicating system; 

(4) Is operative without selection 

after total failure of the electrical gen-
erating system; 

(5) Is located on the instrument panel 

in a position acceptable to the Admin-
istrator that will make it plainly visi-
ble to and usable by each pilot at his or 
her station; and 

(6) Is appropriately lighted during all 

phases of operation. 

[Doc. No. 6258, 29 FR 19205, Dec. 31, 1964, as 
amended by Amdt. 121–57, 35 FR 304, Jan. 8, 
1970; Amdt. 121–60, 35 FR 7108, May 6, 1970; 
Amdt. 121–81, 36 FR 23050, Dec. 3, 1971; Amdt. 
121–130, 41 FR 47229, Oct. 28, 1976; Amdt. 121– 
230, 58 FR 12158, Mar. 3, 1993; Amdt. 121–251, 60 
FR 65929, Dec. 20, 1995; Amdt. 121–262, 62 FR 
13256, Mar. 19, 1997] 

§ 121.306 Portable electronic devices. 

(a) Except as provided in paragraph 

(b) of this section, no person may oper-
ate, nor may any operator or pilot in 
command of an aircraft allow the oper-
ation of, any portable electronic device 
on any U.S.-registered civil aircraft op-
erating under this part. 

(b) Paragraph (a) of this section does 

not apply to— 

(1) Portable voice recorders; 
(2) Hearing aids; 
(3) Heart pacemakers; 
(4) Electric shavers; 
(5) Portable oxygen concentrators 

that comply with the requirements in 
§ 121.574; or 

(6) Any other portable electronic de-

vice that the part 119 certificate holder 
has determined will not cause inter-
ference with the navigation or commu-
nication system of the aircraft on 
which it is to be used. 

(c) The determination required by 

paragraph (b)(6) of this section shall be 
made by that part 119 certificate holder 
operating the particular device to be 
used. 

[Doc. No. FAA–1998–4954, 64 FR 1080, Jan. 7, 
1999, as amended by Docket FAA–2014–0554, 
Amdt. 121–374, 81 FR 33118, May 24, 2016] 

§ 121.307 Engine instruments. 

Unless the Administrator allows or 

requires different instrumentation for