section 5 performance - discovery aviation€¦ · section 5 performance table of contents ......

SECTION 5

PERFORMANCE

TABLE OF CONTENTS

Introduction ............................................................................ 5 - 3 Airspeed Calibration............................................................... 5 - 4 Normal Static Source ...................................................... 5 - 4 Alternate Static Source.................................................... 5 - 5 Crosswind Component Graph ............................................... 5 - 6 Stall Speeds........................................................................... 5 - 7 Temperature Chart................................................................. 5 - 8 Takeoff Distance.................................................................... 5 - 9 Maximum Rate of Climb ...................................................... 5 - 11 Maximum Climb Gradient .................................................... 5 - 12 Balked Landing Rate of Climb ............................................. 5 - 13 Balked Landing Climb Gradient ........................................... 5 - 14 Landing Distance ................................................................. 5 - 15 Best Glide Speed and Distance........................................... 5 - 17 Noise Characteristics / Abatement ...................................... 5 - 18

P/N 135A-970-005 FAA APPROVED: 2/19/2004 Rev. C Dated: 7/26/2005 Page 5 - 1

Liberty Aerospace, Inc. Section 5 XL2 PERFORMANCE

Section 5 Liberty Aerospace, Inc. PERFORMANCE XL2

FAA APPROVED: 2/19/2004 P/N 135A-970-005 Page 5 - 2 Initial Release

THIS PAGE INTENTIONALLY LEFT BLANK

INTRODUCTION This section contains information describing the performance of the Lib-erty XL2 airplane throughout its flight envelope.

Performance information presented in this section is based on data ob-tained by flight tests. No unusual pilot techniques were used, or are re-quired to obtain published performance. Flight test data were obtained using a new aircraft and engine equipped with a representative selection of optional equipment, including avionics and antennas.

All data is applicable to aircraft with and without wheel fairings installed.

CAUTION Achievement of published performance requires pilot compliance with all conditions called out in individual performance charts and/or tables.

P/N 135A-970-005 FAA APPROVED: 2/19/2004 Rev. N Dated: 12/14/2007 Page 5 - 3


AIRSPEED CALIBRATION Normal Static Source

Conditions: Power .......................................................................for level flight Weight ...........................................................................1653 LBS

Note: • Indicated airspeed values do not include instrument error.

KIAS KCAS Flaps

0° 20° 30° 40 - - 44

50 54 54 54

60 64 63 63

70 73 72 72

80 83 81 81

90 92 - -

100 101 - -

110 110 - -

120 120 - -

130 129 - -

140 138 - -

150 146 - -

160 155 - -

FAA APPROVED: 2/19/2004 P/N 135A-970-005 Page 5 - 4 Rev. C Dated: 7/26/2005


AIRSPEED CALIBRATION Alternate Static Source

Conditions: Power....................................................................... for level flight Weight........................................................................... 1653 LBS Vents................................................................................... OPEN

Note: • Indicated airspeed values do not include instrument error.

KIAS KCAS Flaps

0° 20° 30° 40 - - 39

50 49 49 49

60 58 60 60

70 68 70 70

80 77 79 79

90 86 - -

100 95 - -

110 104 - -

120 113 - -

130 122 - -

140 130 - -

150 138 - -

160 147 - -

P/N 135A-970-005 FAA APPROVED: 2/19/2004 Rev. C Dated: 7/26/2005 - 5




CROSSWIND COMPONENT GRAPH Directions: Enter graph at wind velocity on left, read across to diagonal line showing angular difference between runway heading and wind di-rection, read down to crosswind component at bottom.

Notes: • The maximum demonstrated crosswind is 15 knots. • The demonstrated crosswind component is based on the

greatest crosswind available during flight testing and is not considered a limitation.

STALL SPEEDS Conditions:

Weight........................................................................... 1653 LBS C.G........................................ Most Forward for Maximum Weight Power.......................................................................................Idle Bank Angle...........................................................................Noted

Weight LBS

Bank Angle (Deg)

STALL SPEEDS

Flaps 0° Flaps Flaps 30° Full Up 20° Full Down

KIAS KCAS KIAS KCAS KIAS KCAS

1653

0 51 55 43 47 41 45 15 52 56 44 48 42 46 30 55 59 47 51 44 48 45 61 65 53 56 50 54 60 75 78 64 66 62 64

P/N 135A-970-005 FAA APPROVED: 2/19/2004 Rev. G Dated: 5/19/2006 Page 5 - 7




TEMPERATURE CHART This graph provides information on standard temperatures to be ex-pected at various cruise altitudes. In addition, the temperature axis of the chart may be used to convert between Fahrenheit and Celsius tem-perature values.

Enter the graph at the desired altitude on the left and read across until reaching the desired diagonal temperature line. Read down to obtain temperature at the specified altitude in degrees C or F.

FT

SL -5 23 5 41 15 59 25 77 45 113

1000 -7 19 3 37 13 55 23 73 43 109

2000 -9 16 1 34 11 52 21 70 41 106

3000 -11 12 -1 30 9 48 19 66 39 102

4000 -13 9 -3 27 7 45 17 63 37 99

5000 -15 5 -5 23 5 41 15 59 35 95

6000 -17 1 -7 19 3 37 13 55 33 91

7000 -19 -2 -9 16 1 34 11 52 31 88

8000 -21 -6 -11 12 -1 30 9 48 29 84

9000 -23 -9 -13 9 -3 27 7 45 27 81

10000 -25 -13 -15 5 -5 23 5 41 25 77

11000 -27 -17 -17 1 -7 19 3 37 23 73

12000 -29 -20 -19 -2 -9 16 1 34 21 70

13000 -31 -24 -21 -6 -11 12 -1 30 19 66

14000 -33 -27 -23 -9 -13 9 -3 27 17 63

ISA + 30°C

°C °F°F

ISA + 10°C

°C °F

ISA - 20°C ISA - 10°C ISA

°C °F °C °C °F

Press Alt


P/N 135A-970-005 FAA APPROVED: 2/19/2004 Initial Release Page 5 - 9

TAKEOFF DISTANCE Begin the flight planning process by confirming that runway length is adequate for takeoff based on gross weight, altitude, and temperature. Use correction factors provided in the following notes to compensate for headwind or tailwind components and temperature deviations. Normal takeoff assumes acceleration to best rate of climb airspeed.

Conditions: Winds .....................................................................................Zero Runway .............................................................Dry, Level, Paved Weight........................................................................... 1653 LBS Flaps ........................................................................................20° Rotation Speed ................................................................ 55 KIAS Speed at 50 ft above takeoff surface ............................... 65 KIAS Power................................... Full Throttle (WOT annunciator ON) Prior to brake release

Notes: • Increase distances 15% when CHT’s are 420°F or greater. • To be conservative, use the distance for the next higher

Pressure Altitude or Temperature than actual. For example, at a pressure altitude of 475 ft and temperature of 4°C use the takeoff distance for a pressure altitude of 1000 ft and temperature of 10°C.

• Decrease distances 10% for each 12 knots headwind com-ponent. For operation with tailwind component, up to 10 knots, increase distances 10% for each 2 knots.

• For operation on dry grass runways, increase “gnd roll” dis-tances by 15%.

• For operation in air colder than this table provides, use cold-est data shown.

• For operation in air warmer than this table provides, use extreme caution.

• Data was derived from actual flight testing and does not in-clude data for any altitude where the temperature is below ISA -20° or above ISA +30°.



TAKEOFF DISTANCE Rotation Speed: 55 KIAS Flaps 20° Speed at 50 ft: 65 KIAS

Distance Temperature - °C

FT FT 0 10 20 30 40 ISA

SL Gnd Roll 704 781 864 953 1047 822 Over 50FT 1284 1423 1571 1729 1897 1496

1000 Gnd Roll 770 855 945 1042 1145 881 Over 50FT 1399 1551 1713 1885 2068 1598

2000 Gnd Roll 838 930 1029 1134 1246 940 Over 50FT 1519 1684 1859 2046 2245 1701

3000 Gnd Roll 918 1019 1127 1243 1009 Over 50FT 1659 1838 2030 2234 1820

4000 Gnd Roll 1002 1112 1229 1355 1078 Over 50FT 1803 1998 2207 2428 1939

5000 Gnd Roll 1098 1219 1348 1486 1158 Over 50FT 1971 2184 2412 2654 2076

6000 Gnd Roll 1199 1331 1472 1622 1238 Over 50FT 2144 2376 2624 2888 2212

7000 Gnd Roll 1345 1493 1651 1820 1360 Over 50FT 2397 2657 2934 3228 2422

8000 Gnd Roll 1497 1662 1838 1481 Over 50FT 2659 2947 3255 2632

9000 Gnd Roll 1680 1865 2063 1627 Over 50FT 2974 3296 3640 2882

10000 Gnd Roll 1871 2077 2296 1773 Over 50FT 3301 3659 4040 3132

Press Alt



MAXIMUM RATE OF CLIMB Conditions:

Weight........................................................................... 1653 LBS Flaps ........................................................................... Full Up (0°) Power................................... Full Throttle (WOT annunciator ON) Indicated Airspeed .................................................... 80 KIAS (Vy)

Notes: • For operation in air colder than this table provides, use cold-

est data shown. • For operation in air warmer than this table provides, use

extreme caution. • Rate of climb data of less than 100 ft/min are not published. • Data was derived from actual flight testing and does not in-

clude data for any altitude where the temperature is below ISA -20° or above ISA +30°.

Press Alt

Maximum Rate of Climb FT/MIN

Temperature °C FT -20 0 20 40 ISA SL 753 712 672 636 682

1000 701 659 620 584 633 2000 648 606 567 532 584 3000 594 553 514 535 4000 541 500 462 486 5000 488 447 410 436 6000 436 395 358 389 7000 383 342 306 340 8000 330 290 254 292 9000 277 238 202 243 10000 224 185 150 195 11000 171 133 146 12000 119



MAXIMUM CLIMB GRADIENT Conditions:

Weight ...........................................................................1653 LBS Flaps............................................................................Full Up (0°) Power .................................. Full Throttle (WOT annunciator ON) Indicated Airspeed.....................................................80 KIAS (Vy)



extreme caution. • Climb gradient data of less than 100 ft/nm are not published. • Data was derived from actual flight testing and does not in-


Press Alt

Maximum Climb Gradient FT/NM


1000 551 499 453 412 468 2000 500 450 406 368 425 3000 450 403 362 384 4000 401 357 319 343 5000 356 314 278 304 6000 311 272 237 266 7000 269 232 200 230 8000 227 192 162 194 9000 187 155 127 160 10000 148 118 125 11000 112



BALKED LANDING RATE OF CLIMB Conditions:

Weight........................................................................... 1653 LBS Flaps ........................................................................................30° Power................................... Full Throttle (WOT annunciator ON) Indicated Airspeed ........................................................... 65 KIAS



extreme caution. • Rate of climb data of less than 100 ft/min are not published. • Data was derived from actual flight testing and does not in-


Press Alt

Balked Landing Rate of Climb FT/MIN


1000 408 370 334 302 346 2000 360 322 287 255 302 3000 311 274 239 258 4000 263 226 192 214 5000 214 177 144 169 6000 168 131 126 7000 120



BALKED LANDING CLIMB GRADIENT Conditions:

Weight ...........................................................................1653 LBS Flaps........................................................................................ 30° Power .................................. Full Throttle (WOT annunciator ON) Indicated Airspeed............................................................65 KIAS



extreme caution. • Climb gradient data of less than 100 ft/nm are not published. • Data was derived from actual flight testing and does not in-


Press Alt

Balked Landing Climb Gradient FT/NM


1000 388 339 295 258 310 2000 335 289 248 213 266 3000 285 242 204 224 4000 236 196 160 182 5000 190 152 119 143 6000 145 109 105 7000 102



LANDING DISTANCE Landing performance charts are based on the airplane crossing the run-way threshold at 50 ft AGL and at the indicated airspeed specified in the chart.

Conditions: Winds .....................................................................................Zero Runway .............................................................Dry, Level, Paved Weight........................................................................... 1653 LBS Flaps .................................................................... Full Down (30°) Power.................................................................................... IDLE Braking........................................................................... Moderate Speed at 50 ft above landing surface .............................. 65 KIAS

Notes: • To be conservative, use the distance for the next higher

Pressure Altitude or Temperature than actual. For example, at a pressure altitude of 475 ft and temperature of 4°C use the takeoff distance for a pressure altitude of 1000 ft and temperature of 10°C.

• Decrease distances 10% for each 12 knots headwind com-ponent. For operation with tailwind component, up to 10 knots, increase distances 10% for each 2 knots.

• For operation on dry grass runways, increase “gnd roll” dis-tances by 15%.

• For operation in air colder than this table provides, use cold-est data shown.

• For operation in air warmer than this table provides, use extreme caution.

• Data was derived from actual flight testing and does not in-clude data for any altitude where the temperature is below ISA -20° or above ISA +30°.



LANDING DISTANCE Speed at 50 ft: 65 KIAS Flaps 30°

Press Alt Distance

FT FT 0 10 20 30 40 ISA

SL Gnd Roll 797 826 856 885 914 841 Over 50FT 1457 1498 1539 1580 1620 1519

1000 Gnd Roll 827 857 887 918 948 867 Over 50FT 1499 1541 1584 1626 1668 1555

2000 Gnd Roll 857 888 920 951 983 892 Over 50FT 1542 1585 1629 1672 1716 1590

3000 Gnd Roll 890 922 955 988 920 Over 50FT 1587 1632 1677 1722 1628

4000 Gnd Roll 923 957 991 1024 947 Over 50FT 1633 1680 1726 1773 1666

5000 Gnd Roll 959 994 1029 1064 977 Over 50FT 1682 1730 1778 1827 1707

6000 Gnd Roll 995 1031 1068 1104 1006 Over 50FT 1732 1781 1831 1881 1747

7000 Gnd Roll 1055 1094 1133 1171 1059 Over 50FT 1822 1875 1927 1979 1827

8000 Gnd Roll 1116 1157 1199 1113 Over 50FT 1913 1968 2023 1907

9000 Gnd Roll 1184 1227 1271 1171 Over 50FT 2012 2070 2128 1994

10000 Gnd Roll 1253 1298 1344 1229 Over 50FT 2112 2174 2235 2081

Temperature - °C

BEST GLIDE SPEED AND DISTANCE

GLIDE DISTANCE CHART

Conditions: Flaps ........................................................................... Full Up (0°) Power..........................................................IDLE, Throttle Closed Prop.............................................................................Windmilling Airspeed........................................................................... 80 KIAS Flight Attitude .................................... Straight Glide (NO TURNS)

WARNING No allowance included for landing pattern, any turns and/or devia-tions from correct glide speed will reduce glide distance.

Aircraft Gross Weight Best Glide Speed

1653 LBS 80 KIAS

0

1000

2000

3000

4000

5000

6000

7000

8000

9000

10000

0 2 4 6 8 10 12 14 16 18 20

Miles

Alti

tude

Los

s

P/N 135A-970-005 FAA APPROVED: 2/19/2004 Rev. H Dated: 7/5/2006 Page 5 - 17




NOISE CHARACTERISTICS The certificated noise level for the Liberty XL2 established in accordance with FAR 36 Appendix G, through Amendment 24 is:

74.6 dB(A)

No determination has been made by the Federal Aviation Administration that the noise levels of this airplane are or should be acceptable or un-acceptable for operation at, into, or out of, any airport.

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