Section 121.306

14 CFR Ch. I (1-1-19 Edition)

means for preventing malfunctioning
due to icing.
(b) A sensitive altimeter.
(c) A sweep-second hand clock (or approved equivalent).
(d) A free-air temperature indicator.
(e) A gyroscopic bank and pitch indicator (artificial horizon).
(f) A gyroscopic rate-of-turn indicator combined with an integral slipskid indicator (turn-and-bank indicator) except that only a slip-skid indicator is required when a third attitude
instrument system usable through
flight attitudes of 360Section of pitch and roll
is installed in accordance with paragraph (k) of this section.
(g) A gyroscopic direction indicator
(directional gyro or equivalent).
(h) A magnetic compass.
(i) A vertical speed indicator (rate-ofclimb indicator).
(j) On the airplane described in this
paragraph, in addition to two gyroscopic bank and pitch indicators (artificial horizons) for use at the pilot stations, a third such instrument is installed in accordance with paragraph
(k) of this section:
(1) On each turbojet powered airplane.
(2) On each turbopropeller powered
airplane having a passenger-seat configuration of more than 30 seats, excluding each crewmember seat, or a
payload capacity of more than 7,500
pounds.
(3) On each turbopropeller powered
airplane having a passenger-seat configuration of 30 seats or fewer, excluding each crewmember seat, and a payload 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 bankand-pitch indicator (artificial horizon)
that:
(1) Is powered from a source independent of the electrical generating
system;

(2) Continues reliable operation for a
minimum of 30 minutes after total failure 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 generating system;
(5) Is located on the instrument panel
in a position acceptable to the Administrator that will make it plainly visible 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]

Section 121.306 Portable electronic devices.
(a) Except as provided in paragraph
(b) of this section, no person may operate, nor may any operator or pilot in
command of an aircraft allow the operation of, any portable electronic device
on any U.S.-registered civil aircraft operating 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
Section 121.574; or
(6) Any other portable electronic device that the part 119 certificate holder
has determined will not cause interference with the navigation or communication 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]

Section 121.307 Engine instruments.
Unless the Administrator allows or
requires different instrumentation for

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