liberty xl-2 compliance at a gross weight of 1750 lbs

Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
EASA APPROVED
AIRPLANE FLIGHT MANUAL SUPPLEMENT
FOR
LIBERTY XL-2 COMPLIANCE AT
A GROSS WEIGHT OF 1750 LBS
Serial No.
Registration No.
When Liberty Rework Kit Instruction RKI-SIL-08-001 for a Gross Weight of
1750 LBS is installed on SN0007 and 0009 through SN0125 this supplement is applicable and must be inserted in the Liberty Aerospace XL-2 Airplane Flight Manual (AFM) Supplements Section (Section 9) P/N 135A-970500. The information contained herein supplements the EASA approved
Airplane Flight Manual P/N 135A-970-500 only in those areas listed herein.
For limitations, procedures, and performance information not contained in
this document, refer to the Liberty XL-2 EASA Approved Airplane Flight
Manual P/N 135A-970-500.
This flight manual supplement is approved by the FAA on behalf of the
European Aviation Safety Agency (EASA) using the bilateral agreement between the FAA and the DGAC-France. This flight manual was prepared in
accordance with the European requirements.
EASA Approved:
Date:
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 1 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
LIBERTY XL-2 COMPLIANCE AT A GROSS WEIGHT OF 1750 LBS
LOG OF REVISIONS
Rev.
A
B
To
Pages
Description
EASA Approval Signature
and Date
13,14
Added step
and note to
check for
proper door
closure to the
Engine Runup procedure
For: Melvin D. Taylor Manager
Atlanta Aircraft Certification
Office, FAA
Atlanta, GA
Added information and
part number
for the reinforced exhaust.
For: Melvin D. Taylor Manager
Atlanta Aircraft Certification
Office, FAA
Atlanta, GA
32
Date:
Date:
EASA APPROVED: August 18, 2009
Page 2 of 42
P/N 135A-970-509
Revision B — August 3, 2010
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
SECTION 1 - GENERAL
INTRODUCTION
NOTE
NON FACTORY INSTALLED SUPPLEMENTAL TYPE CERTIFICATE (STC)
AND FORM 337 ITEMS SHOULD BE EVALUATED BY THE MAINTENANCE TECHNICIAN TO VERIFY THAT THEY HAVE NO IMPACT ON
THE LIBERTY XL-2 COMPONENT INSTALLATION AND MAINTENANCE
REQUIRED TO COMPLY WITH THE 1750 LBS GROSS WEIGHT INCREASE AND/OR THAT THESE ITEMS DO NOT AFFECT AIRCRAFT
AIRWORTHINESS WHEN OPERATED AT 1750 LBS.
LIBERTY AEROSPACE IS NOT LIABLE FOR THE WEIGHT DISTRIBUTION AND BALANCE ARM THAT RESULT FROM NON-FACTORY STC
AND FORM 337 ITEMS.
FOR GROSS WEIGHT AT 1750 LBS REFER TO RKI-SIL-08-001:
WARNING
OPERATING THE AIRCRAFT ABOVE A WEIGHT OF 1653 LBS WITHOUT
THE FOLLOWING MANDATORY MODIFICATIONS RESULTS IN AN AIRCRAFT THAT DOES NOT COMPLY WITH THE FAA REGULATIONS AND
MAY RESULT IN AN ACCIDENT, AND SERIOUS OR FATAL INJURY.
WARNING
REMOVAL AND REPLACEMENT OF ITEMS REQUIRED FOR THE
GROSS WEIGHT INCREASE MUST BE PERFORMED BY A SUITABLY
QUALIFIED AIRCRAFT MECHANIC/TECHNICIAN. IT IS THE RESPONSIBILITY OF THE OWNER/OPERATOR TO ENSURE THAT PARTS FITTED
TO THE AIRCRAFT AT 1653 LBS ARE NOT MIXED WITH THE PARTS
REQUIRED TO SHOW COMPLIANCE WHEN OPERATED AT 1750 LBS
GROSS WEIGHT.
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 3 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
WARNING
REWORK KIT INSTRUCTION (RKI): IS THE INSTRUCTIONS, PROCEDURES AND PARTS SUPPLIED TO COMPLY WITH A SERVICE DOCUMENT.
FOR RKI-SIL-08-001 THE LIBERTY CRITICAL SERVICE BULLETINS
(CSB), SERVICE BULLETINS (SB), SERVICE INFORMATIONAL LETTERS (SIL), AND REWORK KIT INSTRUCTIONS (RKI) ARE MANDATORY FOR THE AIRCRAFT TO MEET TYPE DESIGN AND TO BE OPERATED AT A GROSS WEIGHT OF 1750 LBS.
FIGURE 1 - 1 AIRPLANE THREE VIEWS
EASA APPROVED: August 18, 2009
Page 4 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
MAXIMUM CERTIFICATED WEIGHTS
WARNING
OPERATING THE AIRCRAFT ABOVE A WEIGHT OF 1653LBS WITHOUT THE MANDATORY MODIFICATIONS RESULTS IN AN AIRCRAFT
THAT DOES NOT COMPLY WITH THE FAA REGULATIONS AND MAY
RESULT IN AN ACCIDENT, AND SERIOUS OR FATAL INJURY.
Takeoff Weight ............................................................................. 1750 lbs
Landing Weight ............................................................................ 1750 lbs
Weight in baggage compartment ................................................... 100 lbs
(See Section 6 for weight and balance limits)
STANDARD AIRPLANE WEIGHTS
Standard empty weight ................................................................ 1174 lbs
Maximum useful load ..................................................................... 576 lbs
SPECIFIC LOADINGS
Wing Loading .......................................................................15.63 lbs/sq ft
Power Loading ...................................................................... 14.00 lbs/HP
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 5 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
SECTION 2 - LIMITATIONS
AIRSPEED LIMITATIONS
Airspeed limitations and their operational significance are shown in
Table 2 - 1
SYMBOL
SPEED
KIAS
VNE
Never Exceed Speed
157
VNO
Maximum Structural Cruising Speed
122
VA
Maneuvering Speed at 1750 LBS
100
VFE
Maximum Flap Extended Speed
86
TABLE 2 - 1 AIRSPEED LIMITATIONS
AIRSPEED INDICATOR MARKINGS
Airspeed indicator markings and their color code significance are shown in
Table 2 - 2.
MARKING
KIAS
SIGNIFICANCE
White Arc
44 - 86
Flap Operating Range
Green Arc
50 - 122
Normal Operating Range
Yellow Arc
122 - 157
Operations must be conducted with
caution and only in smooth air
Red Line
157
Max Speed for all Operations
TABLE 2 - 2 AIRSPEED INDICATOR MARKINGS
EASA APPROVED: August 18, 2009
Page 6 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
POWERPLANT LIMITATIONS
PROPELLER
Propeller Manufacturer ......................... MT-Propeller Entwicklung GmbH
Propeller Model Number ................................................ MT175R127-2Ca
Number of Blades .................................................................................... 2
Propeller Diameter ............................................................................. 69 in
Propeller Type............................................. Wood/Fiberglass, Fixed Pitch
WEIGHT LIMITS
Maximum ramp weight:
Maximum takeoff weight:
Maximum landing weight:
Maximum weight in baggage compartment:
1750 lbs
1750 lbs
1750 lbs
100 lbs
WEIGHT AND CENTER OF GRAVITY LIMITS
Forward:
Mid:
Aft:
81.00 inches aft of datum at 1598 lbs.
83.00 inches aft of datum at 1750 lbs.
86.75 inches aft of datum at 1750 lbs.
FLIGHT LOAD FACTORS
Load Factor
Flaps Up
Flaps Down
Positive
3.8 G
2.0 G
Negative
-1.52 G
0.0 G
TABLE 2 - 3 FLIGHT LOAD FACTORS
Operating Altitude Limitation
Maximum Operating Altitude
P/N 135A-970-509
Initial Release
12,500 ft
EASA APPROVED: August 18, 2009
Page 7 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
MANEUVER LIMITS
This airplane is certified in the normal category, which is applicable to airplanes intended for non-aerobatic operations. These include maneuvers
incidental to normal flying, stalls, lazy eights, chandelles, and turns in which
the angle of bank does not exceed 60 degrees. No aerobatic maneuvers,
including spins, are authorized.
Normal Category Maneuvers and Recommended Entry Speeds:
Maneuvering Speed:
Chandelle: ..................................................................... 100 KIAS
Lazy Eight:..................................................................... 100 KIAS
Steep Turn:.................................................................... 100 KIAS
Stalls: ............................................................... Slow Deceleration
OTHER LIMITATIONS
FLAP LIMITATIONS
Approved takeoff setting:
10°
Performance data is presented for Flaps 10° only.
Approved landing settings:
0°, 10°, 30°
Performance data is presented for Flaps 30° only.
PLACARDS
On the instrument panel, adhered to flap position indicator:
On the VM1000 bottom bezel:
EASA APPROVED: August 18, 2009
Page 8 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
SECTION 3 - EMERGENCY PROCEDURES
AIRSPEEDS FOR EMERGENCY OPERATIONS
Maneuvering Speed:
1750 lbs ......................................................................... 100 KIAS
Best Glide Speed:
1750 lbs ........................................................................... 69 KIAS
Emergency Approach Speed Without Engine Power:
Flaps Up .......................................................................... 69 KIAS
Flaps 30° ......................................................................... 65 KIAS
DOOR OPEN IN FLIGHT
Abort takeoff if door opens during takeoff. In flight, do not allow efforts to reclose the door to interfere with the primary task of maintaining control and
flying the airplane.
1. Flaps……………………………………………………………………..10°
2. Airspeed ........................................................... REDUCE TO 65 KIAS
3. Door ...................................................................CLOSE AND LATCH
(yaw airplane in direction of open door if necessary)
If unable to latch door in flight, or if damage has occurred:
4. LAND ........................................................ AS SOON AS PRACTICAL
5. APPROACH SPEED……………………………………………...65KIAS
LANDING WITH A FLAT MAIN GEAR TIRE
1. Approach Speed .................................................................... 65 KIAS
2. Line Up.................... ON SIDE OF RUNWAY OPPOSITE FLAT TIRE
(Airplane will tend to turn toward flat tire after touchdown.)
3. Flaps .............................................................................................. 30°
4. Touchdown ...................................... GOOD SIDE MAIN TIRE FIRST
(Hold airplane off flat tire as long as possible using ailerons.)
5. Directional Control ............................................................. MAINTAIN
(Using rudder and brake on good tire side as required.)
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 9 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
LANDING WITH A FLAT NOSE TIRE
CAUTION
Do not attempt to taxi airplane with flat main or nose gear tire.
1. Approach Speed .................................................................... 65 KIAS
2. Flaps ................................................NO MORE THAN 10 DEGREES
3. Touchdown ............................................................... ON MAIN GEAR
(Hold nose wheel off the ground as long as possible)
4. Elevator................................................. MAINTAIN FULL AFT STICK
(After nose wheel touches down)
5. Brakes.....................................................USE MINIMUM REQUIRED
6. Ignition Switch...............................................................................OFF
(If operational considerations permit)
LANDING WITHOUT ELEVATOR CONTROL
Manipulating the electric pitch trim and throttle provides attitude control
should primary elevator control be lost. Make small adjustments to trim and
throttle to adjust pitch attitude and airspeed for best glide angle for landing.
Choose the longest available runway. The final power reduction after the
landing flare will cause a nose-down pitch and a possible nose wheel first
touchdown. Make a gradual power reduction while simultaneously selecting
nose-up elevator trim.
1.
2.
3.
4.
5.
Throttle................................................................................. REDUCE
Trim............................................................ NOSE UP, SLOW TO VFE
Flaps .................................................................................. FLAPS UP
Approach Speed .....70 KIAS, USE TRIM AND POWER TO ADJUST
Throttle...................................... AS REQUIRED FOR GLIDE ANGLE
EASA APPROVED: August 18, 2009
Page 10 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
ELEVATOR TRIM RUNAWAY
1. Control Stick ......................................................................RESTRAIN
(To maintain flight path and contain out-of-trim forces.)
2. Elevator Trim Switch.............. ACTUATE IN OPPOSITE DIRECTION
(This may halt trim motion and/or trip ELEV TRIM circuit breaker.)
3. ELEV TRIM Circuit Breaker...........................PULL, DO NOT RESET
4. LAND ....................................................... AS SOON AS PRACTICAL
5. USE ELEVATOR TRIM INOPERATIVE CHECKLIST
NOTE
To relieve control stick forces, if trim has runaway nose down, land with
flaps up (0°) ; if trim has runaway nose up, land with flaps (30°).
SECTION 4 - NORMAL PROCEDURES
AIRSPEEDS FOR NORMAL OPERATION
Unless otherwise noted, the following speeds are based on a maximum
weight of 1750 lbs, and may be used for any lesser weights.
Takeoff Rotation Speed (Vr):
Flaps 10°..........................................................................59 KIAS
Takeoff Climbspeed: (To clear a 50 ft obstacle)
Flaps 10° (At 50 ft) ...........................................................69 KIAS
Enroute Climb, Flaps Up:
Normal, sea level ......................................................80 - 85 KIAS
Normal, 10,000 feet MSL ..........................................75 - 80 KIAS
Best Rate of Climb Speed, Flaps Up (Vy):
Sea level ..........................................................................76 KIAS
10,000 ft ...........................................................................73 KIAS
Best Angle of Climb Speed, Flaps Up (Vx):
Sea level ..........................................................................69 KIAS
10,000 ft ...........................................................................72 KIAS
Normal Approach Speed:
Flaps Up...........................................................................80 KIAS
Flaps 10°..........................................................................70 KIAS
Flaps 30°..........................................................................65 KIAS
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 11 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
Balked Landing Climb Speed:
Wide Open Throttle, Flaps 30° ........................................ 65 KIAS
Maximum Recommended Turbulent Air Penetration (Va):
1750 lbs ......................................................................... 100 KIAS
Maximum Demonstrated 90° Crosswind Velocity:
Takeoff or Landing.......................................................... 15 Knots
NOTE
The maximum demonstrated crosswind velocity reflects the greatest
crosswind available during certification tests and is not considered a limitation.
PREFLIGHT INSPECTION
Preflight inspection path, starting in cockpit, then out and around aircraft
in clockwise direction, ending back in the cockpit.
Figure 4 - 1 WALK AROUND
CAUTION
Do not step on flap when entering or leaving the cockpit.
Use Footstep if installed.
EASA APPROVED: August 18, 2009
Page 12 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
BEFORE TAKEOFF
WARNING
If any abnormal HSA indications are observed after all operational
checks are complete, takeoff is prohibited. Abort flight and notify maintenance. Do not attempt flight until the discrepancy has been corrected.
During cold weather operations the engine should be properly warmed
up before takeoff. The minimum oil temperature for takeoff is 75°F.
1.
2.
3.
4.
Flight Controls ................................................FREE AND CORRECT
Lights .......................................................................... AS REQUIRED
Ignition Switch ............................................................. VERIFY BOTH
Flight Instruments .......................................................... SET, CHECK
ENGINE RUNUP
WARNING
If any rpm drop or engine surge occurs during the FADEC primary (PWR
A) and secondary (PWR B) power transfer check, takeoff is prohibited.
Abort flight and notify maintenance. Do not attempt flight until discrepancy has been corrected.
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
Stop into Wind .......................................................... CLEAR BEHIND
Parking Brake ................. ON, CONFIRM AIRCRAFT NOT ROLLING
Oil Press/Temp.....................................................CHECK IN GREEN
Canopy Doors (Both FWD pins and both AFT pins) ......... ENGAGED
AND SECURE
NOTE
Verify doors are closed by pushing on aft section of both doors.
Throttle ...............................................................APPROX 1700 RPM
Fuel Boost Pump Mode Switch ....................................................OFF
HSA FUEL PMP Annunciator........................................... CHECK ON
Fuel Pressure ........................................................ CHECK IN LIMITS
Fuel Boost Pump Mode Switch ................................................. AUTO
HSA FUEL PMP Annunciator......................................... CHECK OFF
FADEC PWR B Switch .................................................................OFF
Engine .................................... CHECK, NO RPM DROP OR SURGE
HSA EBAT FAIL Annunciator .......................................... CHECK ON
P/N 135A-970-509
Revision A— February 3, 2010
EASA APPROVED: August 18, 2009
Page 13 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
13. FADEC PWR B Switch .................................................................. ON
14. FADEC PWR A Switch ................................................................ OFF
15. Engine .....................................CHECK, NO RPM DROP OR SURGE
16. HSA PPWR FAIL Annunciator (EBAT FAIL may ill.).……CHECK ON
17. FADEC PWR A Switch .................................................................. ON
18. Ignition Switch ....................................................... R (right) POSITON
19. RPM Drop..............................................10 RPM MIN, 150 RPM MAX
20. HSA ................................. CHECK FADEC CAUTION ILLUMINATED
21. Ignition Switch ........................................................................... BOTH
22. Ignition Switch ......................................................... L (left) POSITION
23. RPM Drop..............................................10 RPM MIN, 150 RPM MAX
24. HSA ................................. CHECK FADEC CAUTION ILLUMINATED
25. Ignition Switch ........................................................................... BOTH
26. HSA ........................................ CHECK ALL LAMPS EXTINGUISHED
NOTE
If the ignition switch is in the R or L position for more than 30 seconds,
the red FADEC WARN annunciator will illuminate. This does not repre-
BEFORE TAKEOFF CONTINUED……..
5.
6.
Flaps……………………………………………………………….. ... 10°
Fuel Boost Pump Mode Switch………………………..VERIFY, AUTO
NOTE
The normal configuration during all stages of flight for the Fuel Boost Pump
Mode Switch is the AUTO position.
7.
8.
9.
10.
11.
Trim ..................................................SET FOR TAKEOFF POSITION
Fuel Selector Valve ......................................................... VERIFY, ON
Radios and Avionics .....................................................................SET
Transponder.................................................................................. ALT
Canopy Doors (Both FWD pins and both AFT pins)......... ENGAGED
AND SECURE
NOTE
Verify doors are closed by pushing on aft section of both doors.
12. Seat Belts & Harness ........................................................... SECURE
13. Parking Brake Lever .................................................................... OFF
14. Brakes…………………………………………………………...RELEASE
EASA APPROVED: August 18, 2009
Page 14 of 42
P/N 135A-970-509
Revision A—February 3, 2010
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
TAKEOFF
Power check: check the full-throttle engine operation early in the takeoff run.
The engine should run smoothly and all engine instruments should
read in the green. Abort takeoff at any sign of rough engine operation, sluggish acceleration, or abnormal annunciation.
Flap setting: the only approved flap setting for takeoff is 10°. Takeoff data is
only presented for flaps 10°.
Soft or rough field takeoffs are performed by lifting the airplane off the
ground as soon as practical. For takeoff on gravel or other rough surface
apply throttle slowly to allow for debris to be blown behind the propeller
rather than pulled up into it.
NORMAL TAKEOFF
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
Flaps…………………………………………………………………….10°
Heading Indicator .................................VERIFY RUNWAY HEADING
Throttle ....................................................................FULL FORWARD
WOT Annunciator............................................................. CHECK ON
Engine Instruments .................................................................CHECK
Brakes ....................RELEASE (steer with rudder only/heels on floor)
Elevator Control ............................. LIFT NOSE WHEEL (at 59 KIAS)
Climb Airspeed ...................................... ATTAIN (69 KIAS or greater)
Flaps.............................................. UP (at safe altitude and airspeed)
Climb Speed.....................................ACCELERATE TO 80 - 85 KIAS
SOFT/ROUGH FIELD TAKEOFF
1.
2.
3.
4.
5.
6.
7.
Flaps…………………………………………………………………….10°
Heading Indicator .................................VERIFY RUNWAY HEADING
Throttle ....................................................................FULL FORWARD
WOT Annunciator............................................................. CHECK ON
Steer............................... WITH RUDDER ONLY/HEELS ON FLOOR
Elevator Control ...............................HOLD FULL BACK PRESSURE
When Airplane is Airborne .................... REDUCE PITCH ATTITUDE
ACCELERATE TO 63 KIAS
8. Climb Speed ..............................63 KIAS (until obstacles are cleared)
9. Flaps .............................................. UP (at safe altitude and airspeed)
10. Climb Speed ........................................ACCELERATE TO 80-85KIAS
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 15 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
SHORT FIELD TAKEOFF
1. Flaps............................................................................................... 10°
2. Heading Indicator……………………….VERIFY RUNWAY HEADING
3. Throttle....................... FULL FORWARD WHILE HOLDING BRAKES
4. WOT Annunciator ............................................................. CHECK ON
5. Engine Instruments..................................................................CHECK
6. Brakes..................... RELEASE (steer with rudder only/heels on floor)
7. Elevator Control .................................................... SLIGHT NOSE UP
8. Rotate………………………………………………………...(at 59 KIAS)
9. Climb Airspeed................... ATTAIN (69 KIAS to clear 50 ft obstacle)
10. Flaps.............................................. UP (at safe altitude and airspeed)
11. Climb Speed.....................................ACCELERATE TO 80 - 85 KIAS
BEFORE LANDING
1.
2.
3.
4.
5.
6.
7.
Fuel Quantity.................................................... CHECK SUFFICIENT
Fuel Boost Pump Mode Switch....................................CHECK AUTO
Brakes ..............................................VERIFY PARKING BRAKE OFF
Fuel Selector Valve .......................................................... VERIFY ON
Flaps.............................................. AS DESIRED (at 86 KIAS or less)
Lights.......................................................................... AS REQUIRED
Seat Belts and Harnesses .................................................SECURED
LANDING
NORMAL LANDING
1.
2.
3.
4.
5.
6.
7.
Airspeed ................................................................. 80 KIAS (flaps up)
Flaps.............................................. AS DESIRED (at 86 KIAS or less)
Airspeed ................................................................75 KIAS (flaps 10°)
Airspeed Short Final..............................................64 KIAS (flaps 30°)
Touchdown......................................................MAIN WHEELS FIRST
Elevator Control .......................................... LOWER NOSE GENTLY
Brakes ........................................................................ AS REQUIRED
EASA APPROVED: August 18, 2009
Page 16 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
SHORT FIELD LANDING
1.
2.
3.
4.
5.
6.
Flaps...............................................................................................30°
Airspeed .........................................................65 KIAS UNTIL FLARE
Power ...........................................IDLE (after clearing any obstacles)
Touchdown..................................................... MAIN WHEELS FIRST
Brakes ..................................................................... APPLY HEAVILY
Elevator Control.................................. MAINTAIN BACK PRESSURE
CROSSWIND LANDING
1. Airspeed ................................................................................. 80 KIAS
(flaps up, during initial alignment with runway)
2. Flaps...............................................................................................10°
3. Final Approach ........ USE CRAB OR FORWARD SLIP TECHNIQUE
AS REQUIRED
4. Airspeed ................................................................................. 70 KIAS
5. During Landing .....LOWER UPWIND WING (to compensate for drift)
(use rudder to align heading with runway)
6. Touchdown........................................ UPWIND MAIN WHEEL FIRST
7. Elevator Control........................................... LOWER NOSE GENTLY
8. Aileron, Rudder .......................................................... AS REQUIRED
TO MAINTAIN STRAIGHT ROLLOUT
9. Brakes ........................................................... STEER WITH BRAKES
AS RUDDER BECOMES INEFFECTIVE
BALKED LANDING
1.
2.
3.
4.
5.
6.
7.
Throttle ............................................................................ FULL OPEN
Airspeed ................................................................................. 65 KIAS
Positive Rate of Climb……………………………...ATTAIN/MAINTAIN
Flaps.............................................................RAISE SLOWLY TO 10°
Best Angle of Climb Speed .............................ESTABLISH (69 KIAS)
Flaps (at safe altitude)………………………………………….FULL UP
Climb Speed (at safe altitude) ................ACCELERATE 80 - 85 KIAS
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 17 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
SECTION 5 - PERFORMANCE
AIRSPEED CALIBRATION
Normal Static Source
Conditions:
Power .......................................................................for level flight
Weight ........................................................................... 1750 LBS
Note:
•
Indicated airspeed values do not include instrument error.
KCAS
KIAS
50
00
56
Flaps
100
56
300
53
60
65
64.5
62.5
70
74
73.5
72
80
83
82
81
90
92
100
102
110
110
120
119
130
128
140
137
150
147
160
156
EASA APPROVED: August 18, 2009
Page 18 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
AIRSPEED CALIBRATION
Alternate Static Source
Conditions:
Power ....................................................................... for level flight
Weight ........................................................................... 1750 LBS
Vents ................................................................................... OPEN
Note:
•
Indicated airspeed values do not include instrument error.
KCAS
KIAS
50
0
48
Flaps
100
49.5
60
58
60
60
70
68
69
69
80
76
76
79
90
85
100
90
110
100
120
110
130
121
140
127
150
137
160
147
0
P/N 135A-970-509
Initial Release
300
51
EASA APPROVED: August 18, 2009
Page 19 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
STALL SPEEDS
Conditions:
Weight............................................................................1750 LBS
C.G. ...................................... Most Forward for Maximum Weight
Power.......................................................................................Idle
Bank Angle .....................................................................As Noted
STALL SPEEDS
Weight
LBS
Flaps 100
Flaps Up
Flaps 300
Bank
Angle
(deg)
KIAS KCAS
KIAS
1750
0
50
57
48
54
44
48
1750
15
53
58
49
55
46
49
1750
30
55
61
52.5
58
49
52
1750
45
64
68
59
64
54
57
1750
60
77
81
73
76
66
68
EASA APPROVED: August 18, 2009
Page 20 of 42
KCAS
KIAS KCAS
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
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............................................................................1750 LBS
Flaps ........................................................................................ 10°
Rotation Speed.................................................................59 KIAS
Speed at 50 ft above takeoff surface................................69 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 every 12 knots headwind component. For operation with tailwind component, up to 10 knots,
increase distances 10% for every 2 knots.
• For operation on dry grass runways, increase “ground roll” distances by 15%.
• For operation in air colder than this table provides, use coldest
data shown.
• For operation in air warmer than this table provides, use extreme caution.
• Data was derived from actual flight testing and does not include
data for any altitude where the temperature is below ISA -20° or
above ISA +30°.
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 21 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
NORMAL TAKEOFF DISTANCE - 1750 LBS.
Flaps 100
Rotation Speed : 59 KIAS
Press
Alt
FT
SL
TEMPERATURE - 0C
Distance
FT
Gnd Roll
Over 50FT
2000
Gnd Roll
Over 50FT
4000
Gnd Roll
Over 50FT
6000
Gnd Roll
Over 50FT
8000
Gnd Roll
Over 50FT
10000
Gnd Roll
Over 50FT
Speed at 50 ft: 69 KIAS
-5
1194
2088
1362
2367
1557
2690
1782
3062
2043
3492
2348
3989
5
1328
2318
1517
2632
1736
2996
1991
3416
2287
3902
2632
4466
15
25
1472
2564
1683
2916
1929
3324
2215
3795
2549
4343
2939
4978
1625
2826
1860
3218
2136
3675
2456
4201
2831
4814
3268
5527
35
1788
3106
2050
3541
2356
4048
2713
4635
3131
5318
3620
6114
45
1961
3403
2251
3884
2591
4446
2987
5096
3452
5855
3997
6740
NORMAL TAKEOFF DISTANCE - 1650 LBS.
Flaps 100
Rotation Speed : 57 KIAS
Speed at 50 ft: 67 KIAS
TEMPERATURE - 0C
Press
Alt
FT
SL
Distance
FT
-5
5
15
25
35
45
Gnd Roll
Over 50FT
1037
1822
1153
2023
1278
2237
1411
2466
1552
2710
1703
2969
2000
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
1182
2065
1352
2348
1547
2672
1774
3047
2039
3481
1317
2297
1508
615
1729
2980
1986
3405
2286
3896
1461
2544
1675
2901
1924
3312
2214
3789
2552
4343
1615
2809
1855
3207
2133
3666
2458
4201
2838
4822
1780
3090
2046
3532
2356
4044
2719
4640
3143
5334
1955
3389
2250
3879
2594
4046
2997
5109
3470
5880
4000
6000
8000
10000
EASA APPROVED: August 18, 2009
Page 22 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
NORMAL TAKEOFF DISTANCE - 1550 LBS.
Flaps 100
Rotation Speed : 55 KIAS
Press
Alt
FT
SL
2000
4000
6000
8000
10000
TEMPERATURE - 0C
Distance
FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Speed at 50 ft: 65 KIAS
-5
893
1576
1018
1787
1163
2031
1331
2312
1527
2636
1754
3011
5
993
1750
1133
1987
1298
2262
1488
2579
1709
2946
1967
3371
15
25
1100
1936
1258
2201
1442
2510
1656
2865
1905
3278
2196
3757
1214
2134
1390
2430
1596
2774
1835
3172
2115
3634
2442
4172
35
45
1336
2345
1532
2674
1761
3056
2028
3499
2340
4015
2705
4615
1466
2569
1682
2933
1937
3356
2232
3847
2580
4420
2987
5087
NORMAL TAKEOFF DISTANCE - 1450 LBS.
Flaps 100
Rotation Speed : 55 KIAS
Press
Alt
FT
SL
2000
4000
6000
8000
10000
TEMPERATURE - 0C
Distance
FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
P/N 135A-970-509
Initial Release
Speed at 50 ft: 65
-5
761
1351
867
1532
991
1741
1134
1981
1301
2259
1495
2580
5
846
1500
966
1703
1106
1939
1268
2210
1457
2524
1676
2888
15
25
35
937
1659
1072
1887
1229
2151
1411
2455
1623
2809
1872
3220
1034
1829
1185
2083
1360
2378
1564
2718
1802
3114
2081
3574
1138
2010
1305
2291
1501
2619
1728
2998
1994
3440
2305
3954
45
1249
2202
1434
2513
1650
2876
1902
3296
2198
3787
2545
4359
EASA APPROVED: August 18, 2009
Page 23 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
MAXIMUM RATE OF CLIMB
Conditions:
Weight............................................................................1750 LBS
Flaps .................................................................................. Up (0°)
Power................................... Full Throttle (WOT annunciator ON)
Indicated Airspeed.................................................... 76 KIAS (Vy)
Notes:
• For operation in air colder than this table provides, use coldest 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 include data for any altitude where the temperature is below
ISA -20° or above ISA +30°.
Press
Alt
FT
SL
-5
708
Maximum Rate of Climb
FT/MIN
Temperature0C
5
15
25
35
688
669
650
633
1000
660
640
621
603
585
568
2000
613
593
573
555
538
521
3000
565
545
526
508
490
473
4000
517
497
478
460
443
426
5000
468
448
429
411
394
377
6000
422
403
384
365
348
331
7000
375
355
336
318
301
284
8000
328
308
289
271
253
237
9000
280
260
242
223
206
190
10000
233
213
194
176
159
143
11000
186
166
147
129
111
12000
138
119
100
EASA APPROVED: August 18, 2009
Page 24 of 42
45
616
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
MAXIMUM CLIMB GRADIENT
Conditions:
Weight............................................................................1750 LBS
Flaps .................................................................................. Up (0°)
Power................................... Full Throttle (WOT annunciator ON)
Indicated Airspeed .................................................... 76 KIAS (Vy)
Notes:
• For operation in air colder than this table provides, use coldest data shown.
• For operation in air warmer than this table provides, use
extreme caution.
• Climb gradient data of less than 100 ft/nm are not published.
• Data was derived from actual flight testing and does not include data for any altitude where the temperature is below
ISA -20° or above ISA +30°.
Press
Alt
FT
SL
-5
558
Maximum Climb Gradient
FT/NM
Temperature0C
5
15
25
35
45
533
509
486 465 445
2000
469
445
423
402
383
365
4000
384
362
342
323
306
290
6000
319
284
266
249
233
218
8000
229
211
194
179
164
151
10000
158
142
127
113
100
88
12000
91
76
63
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 25 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
BALKED LANDING RATE OF CLIMB
Conditions:
Weight............................................................................1750 LBS
Flaps ........................................................................................ 30°
Power................................... Full Throttle (WOT annunciator ON)
Indicated Airspeed........................................................... 65 KIAS
Notes:
• For operation in air colder than this table provides, use coldest 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 include data for any altitude where the temperature is below
ISA -20° or above ISA +30°.
Press
Alt
FT
SL
Balked Landing Rate of Climb
FT/MIN
Temperature 0C
-5
5
15
25
35
45
401
382 363 345 328 311
1000
355
335
316
298
281
265
2000
308
288
270
252
235
218
3000
261
242
223
205
188
171
4000
215
195
176
158
141
124
5000
166
147
128
110
6000
121
102
EASA APPROVED: August 18, 2009
Page 26 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
BALKED LANDING CLIMB GRADIENT
Conditions:
Weight ........................................................................... 1750 LBS
Flaps.........................................................................................30°
Power ...................................Full Throttle (WOT annunciator ON)
Indicated Airspeed ...........................................................65 KIAS
Notes:
• For operation in air colder than this table provides, use coldest data shown.
• For operation in air warmer than this table provides, use
extreme caution.
• Climb gradient data of less than 100 ft/nm are not published.
• Data was derived from actual flight testing and does not include data for any altitude where the temperature is below
ISA -20° or above ISA +30°.
Press
Alt
FT
SL
Balked Landing Climb Gradient
FT/NM
Temperature 0C
-5
5
15
25
35
45
373 348
325
304 284
265
2000
278
255
234
215
197
180
4000
188
168
149
131
115
100
6000
103
85
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 27 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
LANDING DISTANCE
Landing performance charts are based on the airplane crossing the runway
threshold at 50 ft AGL and at the indicated airspeed specified in the chart.
Conditions:
Winds .....................................................................................Zero
Runway .............................................................Dry, Level, Paved
Weight ........................................................................... 1750 LBS
Flaps .................................................................... Full Down (30°)
Power .................................................................................... IDLE
Braking ........................................................................... Moderate
Speed at 50 ft above landing surface .............................. 64 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 every 12 knots headwind component. For operation with tailwind component, up to 10 knots,
increase distances 10% for every 2 knots.
• For operation on dry grass runways, increase “ground roll” distances by 15%.
• For operation in air colder than this table provides, use coldest
data shown.
• For operation in air warmer than this table provides, use extreme caution.
• Data was derived from actual flight testing and does not include
data for any altitude where the temperature is below ISA -20° or
above ISA +30°.
EASA APPROVED: August 18, 2009
Page 28 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
NORMAL LANDING DISTANCE - 1750 LBS.
Speed at 50 ft: 64 KIAS
Press
Alt
FT
Flaps 300
Speed at Touchdown 54 KIAS
TEMPERATURE - 0C
Distance
FT
-5
5
15
25
35
45
SL
Gnd Roll
Over 50FT
659
1359
684
1396
708
1433
733
1471
758
1507
782
1544
2000
Gnd Roll
Over 50FT
698
1418
725
1458
751
1498
778
1537
804
1577
831
1616
4000
Gnd Roll
Over 50FT
741
1482
769
1525
798
1567
826
1609
855
1651
883
1693
6000
Gnd Roll
Over 50FT
786
1550
817
1595
848
1641
878
1685
909
1730
940
1774
8000
Gnd Roll
Over 50FT
835
1622
868
1671
901
1719
934
1767
967
1815
1001
1862
10000
Gnd Roll
Over 50FT
888
1699
924
1751
959
1803
995
1854
1031
1905
1066
1956
NORMAL lANDING DISTANCE - 1650 LBS.
Flaps 300
Speed at 50 ft : 64 KIAS
TEMPERATURE - 0C
Press
Alt
FT
Distance
SL
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
586
1285
621
1341
659
1400
699
1463
742
1530
Gnd Roll
Over 50FT
789
1601
2000
4000
6000
8000
10000
FT
P/N 135A-970-509
Initial Release
Speed at Touchdown: 54 KIAS
-5
5
15
25
35
45
608
1320
644
1378
684
1439
726
1505
772
1574
630
1355
668
1415
709
1479
753
1546
801
1619
652
1389
691
1451
734
1517
781
1588
831
1663
673
1423
715
1487
760
1556
808
1629
860
1707
695
1457
738
1524
785
1595
835
1670
890
1751
821
1649
853
1696
885
1744
916
1791
948
1838
EASA APPROVED: August 18, 2009
Page 29 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
NORMAL LANDING DISTANCE - 1550 LBS.
Flaps 300
Speed at 50 ft. : 63 KIAS
Press
Alt
FT
Distance
SL
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
2000
4000
6000
8000
10000
FT
Speed at Touchdown: 53 KIAS
TEMPERATURE - 0C
-5
517
1217
548
1268
581
1323
617
1380
655
1442
696
1508
5
536
1249
569
1302
603
1359
641
1419
681
1484
724
1552
15
25
35
556
1281
589
1336
626
1395
665
1458
707
1525
753
1596
575
1313
610
1370
648
1431
689
1496
733
1566
781
1640
594
1344
631
1403
670
1467
713
1534
759
1606
809
1683
45
614
1375
652
1437
693
1502
737
1572
785
1647
837
1726
NORMAL LANDING DISTANCE - 1450 LBS.
Flaps 300
Speed at 50 ft. : 62 KIAS
Press
Alt
FT
Distance
SL
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
Gnd Roll
Over 50FT
2000
4000
6000
8000
10000
FT
Speed at Touchdown: 52 KIAS
TEMPERATURE - 0C
-5
453
1152
480
1199
509
1250
540
1303
573
1360
609
1421
EASA APPROVED: August 18, 2009
Page 30 of 42
5
469
1182
498
1231
528
1284
561
1339
596
1399
634
1462
15
25
35
45
486
1211
516
1262
548
1317
582
1375
619
1437
659
1502
503
1241
534
1294
567
1350
603
1410
641
1474
683
1542
520
1270
552
1325
587
1383
624
1445
664
1511
708
1582
537
1299
570
1355
606
1416
645
1480
687
1549
732
1622
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
BEST GLIDE SPEED AND DISTANCE
Aircraft Gross Weight
Best Glide Speed
1750 LBS
69 KIAS
GLIDE DISTANCE CHART
Altitude Loss
Conditions:
Flaps ........................................................................... Full Up (0°)
Power.......................................................... IDLE, Throttle Closed
Prop ............................................................................ Windmilling
Airspeed........................................................................... 69 KIAS
Flight Attitude.................................... Straight Glide (NO TURNS)
13000
12000
11000
10000
9000
8000
7000
6000
5000
4000
3000
2000
1000
0
0
2
4
6
8
10
12
14
16
18
20
Miles
WARNING
No allowance included for landing pattern, any turns and/or deviations from correct glide speed will reduce glide distance.
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 31 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
NOISE CHARACTERISTICS
The table below shows the certificated noise level for various configurations
of the Liberty XL-2 airplane. The noise levels listed in the table below are in
accordance with FAR 36 Appendix G Amendment 27 and ICAO Annex D
Chapter 10.
Propeller
MT
Dawley Exhaust
Type and Part
Number
Quiet
DEL 200201-003
(un-reinforced)
Quiet
DEL 200201-005
(reinforced)
Gross
Weight
(lbs)
Noise Level
(dB)
A Weighted
1653
74.0
Table 1 Noise Figures
The reduced sound Dawley Exhaust, P/N DEL 200201-003/5 can be identified by the baffle P/N DEL 200201-508 inside the muffler tailpipe and the
two oblong openings in the pipe
Figure 5-1
.No determination has been made by the Federal Aviation Administration
that the noise levels of this airplane are or should be acceptable or unacceptable for operation at, into, or out of, any airport. The pilot-in-command
should check with each airport for any other specific noise requirements
before take-off and landing.
EASA APPROVED: August 18, 2009
Page 32 of 42
P/N 135A-970-509
Revision B — August 3, 2010
Liberty Aerospace, Inc.
XL-2
P/N 135A-970-509
Initial Release
Section 9
SUPPLEMENTS
EASA APPROVED: August 18, 2009
Page 33 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
LOADING CHART
Use the following chart to determine the moment/1000 for fuel and payload items to complete Airplane Loading Worksheet (Table 6-4).
Weight (lb)
9.3
10
20
30
40
50
60
70
80
90
100
110
120
130
140
150
160
170
180
190
200
210
220
230
240
250
260
270
280
290
300
310
320
330
340
350
360
370
380
390
400
Pilot & CoPiBaggage
Fuel
Volume
lot
(Gallon)
STN 79.78 STN 118.0 STN 101.8
0.95
1.5
0.80
1.18
1.02
1.6
1.60
2.36
2.04
3.2
2.39
3.54
3.05
4.8
3.19
4.72
4.07
6.5
3.99
5.90
5.09
8.1
4.79
7.08
6.11
9.7
5.58
8.26
7.13
11.3
6.38
9.44
8.14
12.9
7.18
10.62
9.16
14.5
7.98
11.80
10.18
16.1
8.78
11.20
17.7
9.57
12.22
19.4
10.37
13.23
21.0
11.17
14.25
22.6
11.97
15.27
24.2
12.76
16.29
25.8
17.31
27.4
13.56
14.36
18.32
29.0
15.16
15.96
16.75
17.55
18.35
19.15
19.95
20.74
21.54
22.34
23.14
23.93
24.73
25.53
26.33
27.13
27.92
28.72
29.52
30.32
31.11
31.91
EASA APPROVED: August 18, 2009
Page 34 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
EXAMPLE AIRPLANE LOADING WORKSHEET
Instructions:
Use the following worksheet to calculate airplane weight and balance prior to
each flight. It is recommended that this page be photocopied to provide a
supply of loading worksheets. Moments for each item may be calculated
(item weight x item arm = item moment/1000) or determined from the graph
on page 6-11.
C.G. = Total Moment ÷ Total Weight
EXAMPLE WEIGHT AND BALANCE
Weight
(lbs)
Arm
(in)
Moment
(in.lbs.)
Empty Wt
1174
82.12
96410.10
Pilot
185
79.78
14759.30
Passenger
145
79.78
11568.10
120
101.80
12216.00
50
118.00
5900.00
Gal.
Fuel
(6 lbs/gal)
20
Baggage
(100 lbs
max)
Total Wt
1674
Total Moment
÷1000
Loaded C.G.
Location
140853.50
84.14
Table 6-4 Example Airplane Loading Worksheet
Use either the “Loaded Airplane Total Moment Limitations” or “Loaded Airplane Center of Gravity (ARM) Limitations” charts on the next two pages to
determine that airplane loaded weight and balance are within limitations.
P/N 135A-970-509
Initial Release
EASA APPROVED: August 18, 2009
Page 35 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
AIRPLANE LOADING WORKSHEET
Instructions:
Use the following worksheet to calculate airplane weight and balance
prior to each flight. It is recommended that this page be photocopied to
provide a supply of loading worksheets. Moments for each item may be
calculated (item weight x item arm = item moment/1000) or determined
from the graph on page 6-11.
C.G. = Total Moment ÷ Total Weight
Gal.
Weight
(lbs)
Arm
(in)
Moment
(in.lbs.)
Empty Wt
Pilot
79.78
Passenger
79.78
Fuel
(6 lbs/gal)
101.80
Baggage
(100 lbs
max)
118.00
Total Wt
Total Moment
÷1000
Loaded C.G.
Location
Table 6-5 Airplane Loading Worksheet
Use either the “Loaded Airplane Total Moment Limitations” or
“Loaded Airplane Center of Gravity (ARM) Limitations” charts on
the next two pages to determine that airplane loaded weight and
balance are within limitations.
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P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
LOADED AIRPLANE TOTAL MOMENT LIMITATIONS
Use the following chart or table to determine if the weight and moment from
the completed Airplane Loading Worksheet (Table 6-4) are within limits.
1800
1700
1600
1500
1400
1300
1200
1100
90
100
110
120
130
140
150
160
Moment/1000
Weight (lb)
Moment (in.lb / 1000)
Minimum
Maximum
1168
94.6
101.3
1200
97.2
104.1
1250
101.2
108.4
1300
105.2
112.8
1350
109.3
117.1
1400
113.3
121.5
1450
117.4
125.8
1500
121.4
130.1
1550
125.5
134.5
1598
129.4
138.6
1600
129.6
138.8
1650
134.7
143.1
1700
139.8
147.5
1750
144.8
151.8
Figure 6-4 and Table 6-6 Moment Limits
P/N 135A-970-509
Initial Release
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Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
LOADED AIRPLANE CENTER OF GRAVITY (ARM)
LIMITATIONS
The following chart illustrates the airplane center of gravity envelope as
inches from aircraft datum (and as a percentage of MAC).
WEIGHT AND CENTER OF GRAVITY LIMITS
Forward:
81.00 inches aft of datum at 1598 lbs.
Mid:
83.00 inches aft of datum at 1750 lbs.
Aft:
86.75 inches aft of datum at 1750 lbs.
1800
Aircraft Weight (lb)
1700
1600
1500
1400
1300
1200
1100
80.5
81.5
82.5
83.5
84.5
85.5
86.5
A i r cr af t C G ( i nc he s af t of da t um)
C.G. Inches AFT of Datum
1800
1700
1600
1500
1400
1300
1200
1100
16
18
20
22
24
26
28
30
A ir c r a f t C G ( % M A C )
C.G.- %MAC
Figure 6-5 Loaded Airplane C.G. Envelope
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Page 38 of 42
P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
Section 7 Airplane & Systems Description
FLAP POSITION SWITCH
To operate the flaps, a spring loaded, center flap control switch that is located on
the avionics panel right side must be held in the "retract" or "extend" position. As
flaps move, position information is provided by illuminating one of 3 indicators
above the flap control switch. Each indicator is activated by position switches that
are located in the flap actuation mechanism. As flaps reach an angle of deflection to
be reported, the corresponding position switch is depressed, which in turn activates
the appropriate position indicator. As flaps continue to move however, position
switch pressure is released extinguishing the indicator. Flap motor operation continues as long as flap control switch pressure is held. At flap full extension or full
retraction, the actuator disengages permitting actuator motor free spool operation
for as long as flap control switch pressure is applied. At the end of travel, depending on direction selected, a full extension indicator or full retraction position indicator will be illuminated. For the standard aircraft, flap positions are marked at 0
degrees, 10 degrees and 30 degrees. It is possible to release the flap control switch
at each of these positions or any point between. Flaps will hold the position
achieved when the flap control switch is released.
P/N 135A-970-509
Initial Release
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Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
Section 8 Airplane Handling Service & Maintenance
AIRPLANE INSPECTION PERIODS
All civil aircraft of U.S. Registry must undergo a complete inspection
(annual) each twelve calendar months. In addition, aircraft operated commercially (for hire) must have a complete inspection every 100 hours of operation.
For operation of an aircraft in controlled airspace under IFR, there must
also be a static pressure system check, to include the Altimeter, within the
preceding 24 calendar months.
To operate within or near Class B airspace, a transponder must be installed
in the aircraft and must have been inspected within the preceding 24 calendar months.
To operate an aircraft with a US registry there must also be an ELT inspection within 12 calendar months after the last inspection. This is to check for
proper installation, battery corrosion, operation of the controls and crash
sensor, and the presence of a sufficient signal.
The FAA may require additional one-time or recurrent inspections by the
issuance of airworthiness directives (ADs) applicable to the airplane, engine, propeller, or other components. It is the responsibility of the owner/
operator of the airplane to ensure compliance with all applicable ADs, and,
if they are repetitive, take appropriate steps to prevent inadvertent noncompliance.
LIBERTY INSPECTION PROGRAMS
In addition to the FAA requirements, Liberty Aerospace requires that propeller mounting bolt torque be checked every 25 operating hours (for wooden
or wood/composite propellers only), and requires a somewhat abbreviated
inspection of the airplane, engine, and engine components every 50 operating hours.
EASA APPROVED: August 18, 2009
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P/N 135A-970-509
Initial Release
Liberty Aerospace, Inc.
XL-2
Section 9
SUPPLEMENTS
PROPELLER CARE
The propeller should be washed and waxed using the same products
and procedures as for the painted surfaces of the airplane. Any significant scratches should be reported to maintenance. Pilots should never
attempt to sand out scratches in the propeller.
WARNING
THE AIRPLANE MUST NOT BE STARTED OR FLOWN IF ANY
SCRATCHES ARE FOUND THAT PENETRATE THROUGH THE
PAINT AND INTO THE WOOD OR COMPOSITE STRUCTURE OF
THE PROPELLER.
Detailed instructions for propeller care is obtained from the applicable
propeller manufacturer’s maintenance manual, website, or service department.
Maintenance Manual for MT-Propeller, MT175R127-2Ca Propeller.
Operation and Installation Manual
E-112 (ATA 61-01-12)
MT-Wood-Composite
Fixed Pitch Propellers
November 21, 2006
P/N 135A-970-509
Initial Release
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Page 41 of 42
Section 9
SUPPLEMENTS
Liberty Aerospace, Inc.
XL-2
THIS PAGE INTENTIONALLY LEFT BLANK
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P/N 135A-970-509
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