452
14 CFR Ch. I (1–1–24 Edition)
§ 135.153
(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; and
(88) All cockpit flight control input
forces (control wheel, control column,
rudder pedal).
(i) For all turbine-engine powered
airplanes with a seating configuration,
excluding any required crewmember
seat, of 10 to 30 passenger seats, manu-
factured after August 18, 2000—
(1) The parameters listed in para-
graphs (h)(1) through (h)(57) of this sec-
tion must be recorded within the
ranges, accuracies, resolutions, and re-
cording intervals specified in Appendix
F of this part.
(2) Commensurate with the capacity
of the recording system, all additional
parameters for which information
sources are installed and which are
connected to the recording system
must be recorded within the ranges, ac-
curacies, resolutions, and sampling in-
tervals specified in Appendix F of this
part.
(j) For all turbine-engine-powered
airplanes with a seating configuration,
excluding any required crewmember
seat, of 10 to 30 passenger seats, that
are manufactured after August 19, 2002
the parameters listed in paragraph
(a)(1) through (a)(88) of this section
must be recorded within the ranges, ac-
curacies, resolutions, and recording in-
tervals specified in Appendix F of this
part.
(k) For aircraft manufactured before
August 18, 1997, the following aircraft
types need not comply with this sec-
tion: Bell 212, Bell 214ST, Bell 412, Bell
412SP, Boeing Chinook (BV–234), Boe-
ing/Kawasaki Vertol 107 (BV/KV–107–
II), deHavilland DHC–6, Eurocopter
Puma 330J, Sikorsky 58, Sikorsky 61N,
Sikorsky 76A.
(l) By April 7, 2012, all aircraft manu-
factured before April 7, 2010, must also
meet the requirements in § 23.1459(a)(7),
§ 25.1459(a)(8), § 27.1459(e), or § 29.1459(e)
of this chapter, as applicable.
(m) All aircraft manufactured on or
after April 7, 2010, must have a flight
data recorder installed that also—
(1) Meets the requirements of
§ 23.1459(a)(3), (a)(6), and (a)(7),
§ 25.1459(a)(3), (a)(7), and (a)(8),
§ 27.1459(a)(3), (a)(6), and (e), or
§ 29.1459(a)(3), (a)(6), and (e) of this
chapter, as applicable; and
(2) Retains the 25 hours of recorded
information required in paragraph (d)
of this section using a recorder that
meets the standards of TSO–C124a, or
later revision.
[Doc. No. 25530, 53 FR 26151, July 11, 1988, as
amended by Amdt. 135–69, 62 FR 38396, July
17, 1997; 62 FR 48135, Sept. 12, 1997; Amdt. 135–
89, 68 FR 42939, July 18, 2003; Amdt. 135–113, 73
FR 12570, Mar. 7, 2008; Amdt. 135–113, 74 FR
32801, July 9, 2009]
§ 135.153 [Reserved]
§ 135.154 Terrain awareness and warn-
ing system.
(a)
Airplanes manufactured after March
29, 2002:
(1) No person may operate a turbine-
powered airplane configured with 10 or
more passenger seats, excluding any
pilot seat, unless that airplane is
equipped with an approved terrain
awareness and warning system that
meets the requirements for Class A
equipment in Technical Standard Order
453
Federal Aviation Administration, DOT
§ 135.156
(TSO)–C151. The airplane must also in-
clude an approved terrain situational
awareness display.
(2) No person may operate a turbine-
powered airplane configured with 6 to 9
passenger seats, excluding any pilot
seat, unless that airplane is equipped
with an approved terrain awareness
and warning system that meets as a
minimum the requirements for Class B
equipment in Technical Standard Order
(TSO)–C151.
(b)
Airplanes manufactured on or before
March 29, 2002:
(1) No person may operate a turbine-
powered airplane configured with 10 or
more passenger seats, excluding any
pilot seat, after March 29, 2005, unless
that airplane is equipped with an ap-
proved terrain awareness and warning
system that meets the requirements
for Class A equipment in Technical
Standard Order (TSO)–C151. The air-
plane must also include an approved
terrain situational awareness display.
(2) No person may operate a turbine-
powered airplane configured with 6 to 9
passenger seats, excluding any pilot
seat, after March 29, 2005, unless that
airplane is equipped with an approved
terrain awareness and warning system
that meets as a minimum the require-
ments for Class B equipment in Tech-
nical Standard Order (TSO)–C151.
(Approved by the Office of Management and
Budget under control number 2120–0631)
(c)
Airplane Flight Manual.
The Air-
plane Flight Manual shall contain ap-
propriate procedures for—
(1) The use of the terrain awareness
and warning system; and
(2) Proper flight crew reaction in re-
sponse to the terrain awareness and
warning system audio and visual warn-
ings.
[Doc. No. 29312, 65 FR 16755, Mar. 29, 2000]
§ 135.155 Fire extinguishers: Pas-
senger-carrying aircraft.
No person may operate an aircraft
carrying passengers unless it is
equipped with hand fire extinguishers
of an approved type for use in crew and
passenger compartments as follows—
(a) The type and quantity of extin-
guishing agent must be suitable for the
kinds of fires likely to occur;
(b) At least one hand fire extin-
guisher must be provided and conven-
iently located on the flight deck for
use by the flight crew; and
(c) At least one hand fire extin-
guisher must be conveniently located
in the passenger compartment of each
aircraft having a passenger seating
configuration, excluding any pilot seat,
of at least 10 seats but less than 31
seats.
§ 135.156 Flight data recorders: fil-
tered data.
(a) A flight data signal is filtered
when an original sensor signal has been
changed in any way, other than
changes necessary to:
(1) Accomplish analog to digital con-
version of the signal;
(2) Format a digital signal to be
DFDR compatible; or
(3) Eliminate a high frequency com-
ponent of a signal that is outside the
operational bandwidth of the sensor.
(b) An original sensor signal for any
flight recorder parameter required to
be recorded under § 135.152 may be fil-
tered only if the recorded signal value
continues to meet the requirements of
Appendix D or F of this part, as appli-
cable.
(c) For a parameter described in
§ 135.152(h)(12) through (17), (42), or (88),
or the corresponding parameter in Ap-
pendix D of this part, if the recorded
signal value is filtered and does not
meet the requirements of Appendix D
or F of this part, as applicable, the cer-
tificate holder must:
(1) Remove the filtering and ensure
that the recorded signal value meets
the requirements of Appendix D or F of
this part, as applicable; or
(2) Demonstrate by test and analysis
that the original sensor signal value
can be reconstructed from the recorded
data. This demonstration requires
that:
(i) The FAA determine that the pro-
cedure and test results submitted by
the certificate holder as its compliance
with paragraph (c)(2) of this section are
repeatable; and
(ii) The certificate holder maintains
documentation of the procedure re-
quired to reconstruct the original sen-
sor signal value. This documentation is