528 

14 CFR Ch. I (1–1–19 Edition) 

Pt. 135, App. F 

Parameters Range 

Accuracy sensor input to 

DFDR readout 

Sampling inter-

val (per second) 

Resolution

2

 

read out 

Altitude ....................................

¥

1,000 ft to max certifi-
cated altitude of air-
craft.

±

100 to 

±

700 ft (See Table 1, 

TSO-C51a).

1 ........................

5

′ 

to 30

′

. 

Airspeed .................................

As the installed meas-

uring system.

±

3% .......................................

1 ........................

1 kt 

Heading ..................................

360

°

................................

±

2

°

.........................................

1 ........................

0.5

°

. 

Normal Acceleration (Vertical) 

¥

3g to + 6g ...................

±

1% of max range excluding 

datum error of 

±

5%.

8 ........................

0.01g 

Pitch Attitude ..........................

±

75

°

................................

±

2

°

.........................................

2 ........................

0.5

° 

Roll Attitude ............................

±

180

°

..............................

±

2

°

.........................................

2 ........................

0.5

°

. 

Radio Transmitter Keying .......

On-Off (Discrete) ............

................................................

1 ........................

0.25 sec 

Power in Each Engine: Free 

Power Turbine Speed 

and 

Engine Torque.

0–130% (power Turbine 

Speed) Full range 
(Torque).

±

2% .......................................

1 speed 1 

torque (per 
engine).

0.2%

1

to 0.4%

1

 

Main Rotor Speed ..................

0–130% ..........................

±

2% .......................................

2 ........................

0.3%

1

 

Altitude Rate ...........................

±

6,000 ft/min ...................

As installed ............................

2 ........................

0.2%

1

 

Pilot Input—Primary Controls 

(Collective, Longitudinal Cy-
clic, Lateral Cyclic, Pedal)

3

.

Full range .......................

±

3% .......................................

2 ........................

0.5%

1

 

Flight Control Hydraulic Pres-

sure Low.

Discrete, each circuit ......

................................................

1 ........................

Flight Control Hydraulic Pres-

sure Selector Switch Posi-
tion, 1st and 2nd stage.

Discrete ..........................

................................................

1 ........................

AFCS Mode and Engagement 

Status.

Discrete (5 bits nec-

essary).

................................................

1 ........................

Stability Augmentation System 

Engage.

Discrete ..........................

................................................

1 ........................

SAS Fault Status ....................

Discrete ..........................

................................................

0.25 ...................

Main Gearbox Temperature 

Low.

As installed .....................

As installed ............................

0.25 ...................

0.5%

1

 

Main Gearbox Temperature 

High.

As installed .....................

As installed ............................

0.5 .....................

0.5%

1

 

Controllable Stabilator Posi-

tion.

Full Range ......................

±

3% .......................................

2 ........................

0.4%

1

. 

Longitudinal Acceleration .......

±

1g ..................................

±

1.5% max range excluding 

datum error of 

±

5%.

4 ........................

0.01g. 

Lateral Acceleration ................

±

1g ..................................

±

1.5% max range excluding 

datum of 

±

5%.

4 ........................

0.01g. 

Master Warning ......................

Discrete ..........................

................................................

1 ........................

Nav 1 and 2 Frequency Se-

lection.

Full range .......................

As installed ............................

0.25 ...................

Outside Air Temperature ........

¥

50 

°

C to + 90 

°

C .........

±

2

° 

c ......................................

0.5 .....................

0.3

° 

c 

1

Per cent of full range. 

2

This column applies to aircraft manufactured after October 11, 1991. 

3

For all aircraft manufactured on or after December 6, 2010, the sampling interval per second is 4. 

[Doc. No. 25530, 53 FR 26154, July 11, 1988; 53 FR 30906, Aug. 16, 1988; Amdt. 135–113, 73 FR 12571, 
Mar. 7, 2008; 73 FR 15281, Mar. 21, 2008; Amdt. 135–121, 75 FR 17047, Apr. 5, 2010] 

A

PPENDIX

F 

TO

P

ART

135—A

IRPLANE

F

LIGHT

R

ECORDER

S

PECIFICATION

 

The recorded values must meet the designated range, resolution and accuracy requirements during static and dynamic condi-

tions. Dynamic condition means the parameter is experiencing change at the maximum rate attainable, including the maximum 
rate of reversal. All data recorded must be correlated in time to within one second. 

Parameters Range 

Accuracy (sensor 

input) 

Seconds per 

sampling interval 

Resolution Remarks 

1. Time or Rel-

ative Time 
Counts

1

.

24 Hrs, 0 to 

4095.

±

0.125% Per 

Hour.

4 ........................

1 sec .................

UTC time preferred when 

available. Counter incre-
ments each 4 seconds of 
system operation. 

2. Pressure Alti-

tude.

¥

1000 ft to max 
certificated alti-
tude of aircraft. 
+ 5000 ft.

±

100 to 

±

700 ft 

(see table, 
TSO C124a or 
TSO C51a).

1 ........................

5

′ 

to 35

″

.............

Data should be obtained 

from the air data computer 
when practicable. 

3. Indicated air-

speed or Cali-
brated airspeed.

50 KIAS or min-

imum value to 
Max V

so

ü

and 

V

so

to 1.2 V.

D

.

±

5% and 

±

3% ....

1 ........................

1 kt ....................

Data should be obtained 

from the air data computer 
when practicable. 

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