304
14 CFR Ch. I (1–1–14 Edition)
§ 23.1326
(f) [Reserved]
(g) For airplanes prohibited from
flight in instrument meteorological or
icing conditions, in accordance with
§ 23.1559(b) of this part, paragraph (b)(3)
of this section does not apply.
[Amdt. 23–1, 30 FR 8261, June 29, 1965, as
amended by Amdt. 23–6, 32 FR 7586, May 24,
1967; 32 FR 13505, Sept. 27, 1967; 32 FR 13714,
Sept. 30, 1967; Amdt. 23–20, 42 FR 36968, July
18, 1977; Amdt. 23–34, 52 FR 1834, Jan. 15, 1987;
Amdt. 23–42, 56 FR 354, Jan. 3, 1991; Amdt. 23–
49, 61 FR 5169, Feb. 9, 1996; Amdt. 23–50, 61 FR
5192, Feb. 9, 1996]
§ 23.1326
Pitot heat indication systems.
If a flight instrument pitot heating
system is installed to meet the require-
ments specified in § 23.1323(d), an indi-
cation system must be provided to in-
dicate to the flight crew when that
pitot heating system is not operating.
The indication system must comply
with the following requirements:
(a) The indication provided must in-
corporate an amber light that is in
clear view of a flightcrew member.
(b) The indication provided must be
designed to alert the flight crew if ei-
ther of the following conditions exist:
(1) The pitot heating system is
switched ‘‘off.’’
(2) The pitot heating system is
switched ‘‘on’’ and any pitot tube heat-
ing element is inoperative.
[Doc. No. 27806, 61 FR 5169, Feb. 9, 1996]
§ 23.1327
Magnetic direction indicator.
(a) Except as provided in paragraph
(b) of this section—
(1) Each magnetic direction indicator
must be installed so that its accuracy
is not excessively affected by the air-
plane’s vibration or magnetic fields;
and
(2) The compensated installation may
not have a deviation in level flight,
greater than ten degrees on any head-
ing.
(b) A magnetic nonstabilized direc-
tion indicator may deviate more than
ten degrees due to the operation of
electrically powered systems such as
electrically heated windshields if ei-
ther a magnetic stabilized direction in-
dicator, which does not have a devi-
ation in level flight greater than ten
degrees on any heading, or a gyroscopic
direction indicator, is installed. Devi-
ations of a magnetic nonstabilized di-
rection indicator of more than 10 de-
grees must be placarded in accordance
with § 23.1547(e).
[Amdt. 23–20, 42 FR 36969, July 18, 1977]
§ 23.1329
Automatic pilot system.
If an automatic pilot system is in-
stalled, it must meet the following:
(a) Each system must be designed so
that the automatic pilot can—
(1) Be quickly and positively dis-
engaged by the pilots to prevent it
from interfering with their control of
the airplane; or
(2) Be sufficiently overpowered by
one pilot to let him control the air-
plane.
(b) If the provisions of paragraph
(a)(1) of this section are applied, the
quick release (emergency) control
must be located on the control wheel
(both control wheels if the airplane can
be operated from either pilot seat) on
the side opposite the throttles, or on
the stick control, (both stick controls,
if the airplane can be operated from ei-
ther pilot seat) such that it can be op-
erated without moving the hand from
its normal position on the control.
(c) Unless there is automatic syn-
chronization, each system must have a
means to readily indicate to the pilot
the alignment of the actuating device
in relation to the control system it op-
erates.
(d) Each manually operated control
for the system operation must be read-
ily accessible to the pilot. Each control
must operate in the same plane and
sense of motion as specified in § 23.779
for cockpit controls. The direction of
motion must be plainly indicated on or
near each control.
(e) Each system must be designed and
adjusted so that, within the range of
adjustment available to the pilot, it
cannot produce hazardous loads on the
airplane or create hazardous deviations
in the flight path, under any flight con-
dition appropriate to its use, either
during normal operation or in the
event of a malfunction, assuming that
corrective action begins within a rea-
sonable period of time.
(f) Each system must be designed so
that a single malfunction will not
produce a hardover signal in more than
one control axis. If the automatic pilot
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