167
Federal Aviation Administration, DOT
Pt. 60, App. B
T
ABLE
B2B—A
LTERNATIVE
D
ATA
S
OURCE FOR
FTD L
EVEL
5 S
MALL
, S
INGLE
E
NGINE
(R
ECIPROCATING
) A
IRPLANE
—Continued
QPS requirement
The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD.
Applicable test
Authorized performance range
Entry No.
Title and procedure
2.c.8. ..........
Stall warning (actuation of stall warning device) with
nominal gross weight; wings level; and a deceleration
rate of not more than three (3) knots per second.
(a) Landing configuration ................................................
40–60 knots;
±
5
°
of bank.
(b) Clean configuration ....................................................
Landing configuration speed + 10–20%.
2.c.9.b. .......
Phugoid dynamics ...........................................................
Must have a phugoid with a period of 30–60 seconds.
May not reach
1
⁄
2
or double amplitude in less than 2
cycles.
2.d. .............
Lateral Directional Tests.
2.d.2. ..........
Roll response (rate). Roll rate must be measured
through at least 30
°
of roll. Aileron control must be
deflected
1
⁄
3
(33.3 percent) of maximum travel.
Must have a roll rate of 40
°
–25
°
/second.
2.d.4.b. .......
Spiral stability. Cruise configuration and normal cruise
airspeed. Establish a 20
°
–30
°
bank. When stabilized,
neutralize the aileron control and release. Must be
completed in both directions of turn.
Initial bank angle (
±
5
°
) after 20 seconds.
2.d.6.b. .......
Rudder response. Use 25 percent of maximum rudder
deflection. (Applicable to approach or landing con-
figuration.).
2
°
–6
°
/second yaw rate.
2.d.7. ..........
Dutch roll, yaw damper off. (Applicable to cruise and
approach configurations.).
A period of 2–5 seconds; and
1
⁄
2
–2 cycles.
2.d.8. ..........
Steady state sideslip. Use 50 percent rudder deflection.
(Applicable to approach and landing configurations.).
2
°
–10
°
of bank; 4
°
–10
°
of sideslip; and 2
°
–10
°
of aile-
ron.
6. ................
FTD System Response Time
6.a. .............
Latency. Flight deck instrument systems response to an
abrupt pilot controller input. One test is required in
each axis (pitch, roll, yaw).
300 milliseconds or less.
T
ABLE
B2C—A
LTERNATIVE
D
ATA
S
OURCE FOR
FTD L
EVEL
5 S
MALL
, M
ULTI
-E
NGINE
(R
ECIPROCATING
) A
IRPLANE
QPS requirement
The performance parameters in this table must be used to program the FTD if flight test data is not used to program the FTD.
Applicable test
Authorized performance range
Entry No.
Title and procedure
1. Performance
1.c ..............
Climb
1.c.1. ..........
Normal climb with nominal gross weight, at best rate-of-
climb airspeed.
Climb airspeed = 95–115 knots.
Climb rate = 500–1500 fpm (2.5–7.5 m/sec)
1.f. ..............
Engines
1.f.1. ...........
Acceleration; idle to takeoff power ..................................
2–5 Seconds.
1.f.2. ...........
Deceleration; takeoff power to idle .................................
2–5 Seconds.
2. Handling Qualities
2.c. .............
Longitudinal Tests.
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