132 

14 CFR Ch. I (1–1–19 Edition) 

§ 121.344 

(60) Primary Navigation System Ref-

erence; 

(61) Icing (when an information 

source is installed); 

(62) Engine warning each engine vi-

bration (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 in-
stalled); 

(72) De-icing or anti-icing system se-

lection (when an information source is 
installed); 

(73) Computed center of gravity 

(when an information source is in-
stalled); 

(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 sys-

tem); 

(78) Loss of cabin pressure; 
(79) Computer failure; 
(80) Heads-up display (when an infor-

mation source is installed); 

(81) Para-visual display (when an in-

formation source is installed); 

(82) Cockpit trim control input posi-

tion—pitch; 

(83) Cockpit trim control input posi-

tion—roll; 

(84) Cockpit trim control input posi-

tion—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 manufac-
tured on or before October 11, 1991, by 
August 20, 2001. 

(1) For airplanes not equipped as of 

July 16, 1996, with a flight data acquisi-
tion unit (FDAU), the parameters list-
ed 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 param-
eter; 

(ii) Parameters listed in paragraphs 

(a)(12) through (a)(17) each may be re-
corded from a single source. 

(2) For airplanes that were equipped 

as of July 16, 1996, with a flight data 
acquisition unit (FDAU), the param-
eters listed in paragraphs (a)(1) 
through (a)(22) of this section must be 
recorded within the ranges, accuracies, 
and recording intervals specified in Ap-
pendix M of this part. Parameters list-
ed in paragraphs (a)(12) through (a)(17) 
each may be recorded from a single 
source. 

(3) The approved flight recorder re-

quired 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 mainte-
nance 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 manufac-
tured 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 Appen-
dix M of this part by August 20, 2001. 
Parameters listed in paragraphs (a)(12) 

VerDate Sep<11>2014 

08:20 May 17, 2019

Jkt 247048

PO 00000

Frm 00142

Fmt 8010

Sfmt 8010

Y:\SGML\247048.XXX

247048