Section 121.344

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

(60) Primary Navigation System Reference;
(61) Icing (when an information
source is installed);
(62) Engine warning each engine vibration (when an information source is
installed);
(63) Engine warning each engine over
temp. (when an information source is
installed);
(64) Engine warning each engine oil
pressure low (when an information
source is installed);
(65) Engine warning each engine over
speed (when an information source is
installed);
(66) Yaw trim surface position;
(67) Roll trim surface position;
(68) Brake pressure (selected system);
(69) Brake pedal application (left and
right);
(70) Yaw or sideslip angle (when an
information source is installed);
(71) Engine bleed valve position
(when an information source is installed);
(72) De-icing or anti-icing system selection (when an information source is
installed);
(73) Computed center of gravity
(when an information source is installed);
(74) AC electrical bus status;
(75) DC electrical bus status;
(76) APU bleed valve position (when
an information source is installed);
(77) Hydraulic pressure (each system);
(78) Loss of cabin pressure;
(79) Computer failure;
(80) Heads-up display (when an information source is installed);
(81) Para-visual display (when an information source is installed);
(82) Cockpit trim control input position - pitch;
(83) Cockpit trim control input position - roll;
(84) Cockpit trim control input position - yaw;
(85) Trailing edge flap and cockpit
flap control position;
(86) Leading edge flap and cockpit
flap control position;
(87) Ground spoiler position and speed
brake selection;
(88) All cockpit flight control input
forces (control wheel, control column,
rudder pedal);

(89) Yaw damper status;
(90) Yaw damper command; and
(91) Standby rudder valve status.
(b) For all turbine-engine powered
transport category airplanes manufactured on or before October 11, 1991, by
August 20, 2001.
(1) For airplanes not equipped as of
July 16, 1996, with a flight data acquisition unit (FDAU), the parameters listed in paragraphs (a)(1) through (a)(18)
of this section must be recorded within
the ranges and accuracies specified in
Appendix B of this part, and - 
(i) For airplanes with more than two
engines, the parameter described in
paragraph (a)(18) is not required unless
sufficient capacity is available on the
existing recorder to record that parameter;
(ii) Parameters listed in paragraphs
(a)(12) through (a)(17) each may be recorded from a single source.
(2) For airplanes that were equipped
as of July 16, 1996, with a flight data
acquisition unit (FDAU), the parameters listed in paragraphs (a)(1)
through (a)(22) of this section must be
recorded within the ranges, accuracies,
and recording intervals specified in Appendix M of this part. Parameters listed in paragraphs (a)(12) through (a)(17)
each may be recorded from a single
source.
(3) The approved flight recorder required by this section must be installed
at the earliest time practicable, but no
later than the next heavy maintenance
check after August 18, 1999 and no later
than August 20, 2001. A heavy maintenance check is considered to be any
time an airplane is scheduled to be out
of service for 4 or more days and is
scheduled to include access to major
structural components.
(c) For all turbine-engine powered
transport category airplanes manufactured on or before October 11, 1991 - 
(1) That were equipped as of July 16,
1996, with one or more digital data
bus(es) and an ARINC 717 digital flight
data acquisition unit (DFDAU) or
equivalent, the parameters specified in
paragraphs (a)(1) through (a)(22) of this
section must be recorded within the
ranges, accuracies, resolutions, and
sampling intervals specified in Appendix M of this part by August 20, 2001.
Parameters listed in paragraphs (a)(12)

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