349
Federal Aviation Administration, DOT
§ 125.223
the seat in front of the user, or in an-
other approved stowage location so
that it does not block the aisle way or
the entryway to the row. If the device
is to be operated by the user, it must
be operated only at a seat location that
does not restrict any passenger’s access
to, or use of, any required emergency
or regular exit, or the aisle(s) in the
passenger compartment.
[Docket No. 19779, 45 FR 67235, Oct. 9, 1980, as
amended by Docket FAA–2014–0554, Amdt.
125–65, 81 FR 33119, May 24, 2016; Docket
FAA–2018–0119, Amdt. 125–68, 83 FR 9173, Mar.
5, 2018]
§ 125.221 Icing conditions: Operating
limitations.
(a) No pilot may take off an airplane
that has frost, ice, or snow adhering to
any propeller, windshield, stabilizing
or control surface; to a powerplant in-
stallation; or to an airspeed, altimeter,
rate of climb, flight attitude instru-
ment system, or wing, except that
takeoffs may be made with frost under
the wing in the area of the fuel tanks
if authorized by the FAA.
(b) No certificate holder may author-
ize an airplane to take off and no pilot
may take off an airplane any time con-
ditions are such that frost, ice, or snow
may reasonably be expected to adhere
to the airplane unless the pilot has
completed the testing required under
§ 125.287(a)(9) and unless one of the fol-
lowing requirements is met:
(1) A pretakeoff contamination
check, that has been established by the
certificate holder and approved by the
Administrator for the specific airplane
type, has been completed within 5 min-
utes prior to beginning takeoff. A pre-
takeoff contamination check is a check
to make sure the wings and control
surfaces are free of frost, ice, or snow.
(2) The certificate holder has an ap-
proved alternative procedure and under
that procedure the airplane is deter-
mined to be free of frost, ice, or snow.
(3) The certificate holder has an ap-
proved deicing/anti-icing program that
complies with § 121.629(c) of this chap-
ter and the takeoff complies with that
program.
(c) No pilot may fly under IFR into
known or forecast light or moderate
icing conditions, or under VFR into
known light or moderate icing condi-
tions, unless—
(1) The aircraft has functioning deic-
ing or anti-icing equipment protecting
each propeller, windshield, wing, stabi-
lizing or control surface, and each air-
speed, altimeter, rate of climb, or
flight attitude instrument system;
(2) The airplane has ice protection
provisions that meet appendix C of this
part; or
(3) The airplane meets transport cat-
egory airplane type certification provi-
sions, including the requirements for
certification for flight in icing condi-
tions.
(d) Except for an airplane that has
ice protection provisions that meet ap-
pendix C of this part or those for trans-
port category airplane type certifi-
cation, no pilot may fly an airplane
into known or forecast severe icing
conditions.
(e) If current weather reports and
briefing information relied upon by the
pilot in command indicate that the
forecast icing condition that would
otherwise prohibit the flight will not
be encountered during the flight be-
cause of changed weather conditions
since the forecast, the restrictions in
paragraphs (b) and (c) of this section
based on forecast conditions do not
apply.
[45 FR 67235, Oct. 9, 1980, as amended by
Amdt. 125–18, 58 FR 69629, Dec. 30, 1993; Amdt.
125–58, 74 FR 62696, Dec. 1, 2009]
§ 125.223 Airborne weather radar
equipment requirements.
(a) No person may operate an air-
plane governed by this part in pas-
senger-carrying operations unless ap-
proved airborne weather radar equip-
ment is installed in the airplane.
(b) No person may begin a flight
under IFR or night VFR conditions
when current weather reports indicate
that thunderstorms, or other poten-
tially hazardous weather conditions
that can be detected with airborne
weather radar equipment, may reason-
ably be expected along the route to be
flown, unless the airborne weather
radar equipment required by paragraph
(a) of this section is in satisfactory op-
erating condition.
(c) If the airborne weather radar
equipment becomes inoperative en
350
14 CFR Ch. I (1–1–24 Edition)
§ 125.224
route, the airplane must be operated
under the instructions and procedures
specified for that event in the manual
required by § 125.71.
(d) This section does not apply to air-
planes used solely within the State of
Hawaii, within the State of Alaska,
within that part of Canada west of lon-
gitude 130 degrees W, between latitude
70 degrees N, and latitude 53 degrees N,
or during any training, test, or ferry
flight.
(e) Without regard to any other pro-
vision of this part, an alternate elec-
trical power supply is not required for
airborne weather radar equipment.
§ 125.224 Collision avoidance system.
Effective January 1, 2005, any air-
plane you operate under this part 125
must be equipped and operated accord-
ing to the following table:
C
OLLISION
A
VOIDANCE
S
YSTEMS
If you operate any
. . .
Then you must operate that airplane
with:
(a) Turbine-powered
airplane of more
than 33,000
pounds maximum
certificated take-
off weight.
(1) An appropriate class of Mode S
transponder that meets Technical
Standard Order (TSO) C–112, or a
later version, and one of the fol-
lowing approved units:
(i) TCAS II that meets TSO C–119b
(version 7.0), or a later version.
(ii) TCAS II that meets TSO C–119a
(version 6.04A Enhanced) that was
installed in that airplane before May
1, 2003. If that TCAS II version
6.04A Enhanced no longer can be
repaired to TSO C–119a standards,
it must be replaced with a TCAS II
that meets TSO C–119b (version
7.0), or a later version.
(iii) A collision avoidance system equiv-
alent to TSO C–119b (version 7.0),
or a later version, capable of coordi-
nating with units that meet TSO C–
119a (version 6.04A Enhanced), or a
later version.
(b) Piston-powered
airplane of more
than 33,000
pounds maximum
certificated take-
off weight.
(1) TCAS I that meets TSO C–118, or
a later version, or
(2) A collision avoidance system equiv-
alent to TSO C–118, or a later
version, or
(1)(3) A collision avoidance system and
Mode S transponder that meet para-
graph (a)(1) of this section.
[Doc. No. FAA–2001–10910, 68 FR 15903, Apr. 1,
2003]
§ 125.225 Flight data recorders.
(a) Except as provided in paragraph
(d) of this section, after October 11,
1991, no person may operate a large air-
plane type certificated before October
1, 1969, for operations above 25,000 feet
altitude, nor a multiengine, turbine
powered airplane type certificated be-
fore October 1, 1969, unless it is
equipped with one or more approved
flight recorders that utilize a digital
method of recording and storing data
and a method of readily retrieving that
data from the storage medium. The fol-
lowing information must be able to be
determined within the ranges, accura-
cies, resolution, and recording inter-
vals specified in appendix D of this
part:
(1) Time;
(2) Altitude;
(3) Airspeed;
(4) Vertical acceleration;
(5) Heading;
(6) Time of each radio transmission
to or from air traffic control;
(7) Pitch attitude;
(8) Roll attitude;
(9) Longitudinal acceleration;
(10) Control column or pitch control
surface position; and
(11) Thrust of each engine.
(b) Except as provided in paragraph
(d) of this section, after October 11,
1991, no person may operate a large air-
plane type certificated after September
30, 1969, for operations above 25,000 feet
altitude, nor a multiengine, turbine
powered airplane type certificated
after September 30, 1969, unless it is
equipped with one or more approved
flight recorders that utilize a digital
method of recording and storing data
and a method of readily retrieving that
data from the storage medium. The fol-
lowing information must be able to be
determined within the ranges, accura-
cies, resolutions, and recording inter-
vals specified in appendix D of this
part:
(1) Time;
(2) Altitude;
(3) Airspeed;
(4) Vertical acceleration;
(5) Heading;
(6) Time of each radio transmission
either to or from air traffic control;
(7) Pitch attitude;
(8) Roll attitude;
(9) Longitudinal acceleration;
(10) Pitch trim position;
(11) Control column or pitch control
surface position;