Homebuilt Aircraft Data Sheet - bmaa.org · british microlight aircraft association homebuilt aircraft data sheet (hads) no: hm10 issue: 15 hads hm10 issue 15 page 1 of 16 type mxp-740

BRITISH MICROLIGHT AIRCRAFT ASSOCIATION

HOMEBUILT AIRCRAFT DATA SHEET (HADS)

NO: HM10 ISSUE: 15

HADS HM10 issue 15 Page 1 of 16

TYPE MXP-740 Savannah1

(1) MANUFACTURER Individual aircraft are amateur constructed. BMAA is responsible for

continued airworthiness.

(2) UK IMPORTER UK Importer of Kits, Sandtoft Ultralights Partnership, c/o Low Lodge,

Main Street, West Haddlesey, YO8 8QA

Kits are manufactured by ICP Srl, Via Torino 12, 14020 Piovà Massaia,

Italy.

(3) CERTIFICATION BCAR SECTION S Issue 2. Except that:

Ignition switches on early aircraft may be fitted in the reverse sense so

long as the originally supplied, guarded, switches are fitted.

(4) DEFINITION OF BASIC

STANDARD

Savannah/Savannah VG/Savannah XLS Construction Manual.

(5) COMPLIANCE WITH THE MICROLIGHT DEFINITION

(a) MTOW 450 kg

(b) No. Seats 2

(c) Maximum Wing Loading ‘Classic’: 35.0 kg/m²

‘VG’ & ‘XLS’: 37.9 kg/m²

(d) Vso ‘Classic’: 28 kts CAS2

‘VG’ & ‘XLS’: 29 kts CAS

(e) Permitted range of occupant weights Min 55 kg total weight

Max 120 kg per seat

(f) Typical Empty Weight (ZFW) 261 kg

(g) ZFW + 172 kg crew + 1 hr fuel

(21 litres / 15 kg)

448 kg

(h) ZFW + 86 kg pilot + full fuel

(77 litres / 55.4 kg)

402.4 kg

(i) Max allowed ZFW at initial permit issue3 263 kg (Jabiru 2200 variants)

267 kg4 (Jabiru 2200 variants)

270 kg (Suzuki LS100 variants)

1 Note: During aircraft construction, this HADS is to be used with the Savannah stage inspection sheets, form

BMAA/AW/022 (Savannah). If there is a conflict between the two, the latest HADS will always take

precedence. 2 VSO is based upon aerodynamic stall at aft CG, apparent stall speed may increase by up to 7kts CAS at further

forward CG positions. 3 The maximum ZFW is the lower of [(a)-(172kg+1hrs fuel)] or [(a)-(86kg+full fuel)].

4 Use of the higher maximum ZFW requires maximum continuous power to be limited to 2800 rpm by placard.



NO: HM10 ISSUE: 15


(6) POWER PLANTS

Designation Savannah Jabiru(1) Savannah Jabiru(2) Savannah Jabiru(3)

(not yet approved)

Engine Type Jabiru 2200 After serial 22A710

Reduction Gear Direct Drive

Exhaust System Jabiru Tractor exhaust, stainless steel

Intake System Bing type 64/32 carb + single K&N Filter. Engine oil carb-body heater fitted.

Propeller Type GT 2 – 2 blade laminated

wood GT2/151/107

Powerfin 2 blade

square tip

Warp Drive 2 blade

(High Power Hub)

Propeller Dia x Pitch 151cm x 107cm

(59.5” x 42”)

64” x 10° 64”, pitch TBD

Noise Type Cert No. 182M Issue 1 182M Issue 1 TBA

MAAN approving 1591 1591 TBA

Designation Savannah Jabiru(4) Savannah Jabiru(5) Savannah LS(1)

Engine Type Jabiru 2200 After serial 22A710 Suzuki LS1000

(Bilsam modified)

Reduction Gear Direct Drive Internal 2.4:1

Exhaust System Jabiru Tractor exhaust, stainless steel Savannah/Suzuki,

stainless steel

Intake System Bing type 64/32 carb + single K&N Filter. Engine oil

carb-body heater fitted.

Fuel injected with Rapier

oiled filter

Propeller Type GT 2 – 2 blade laminated

wood GT2/157/98

GT 2 – 2 blade laminated

wood GT2/157/100

Kiev 273/1700

3 blade

Propeller Dia x Pitch 157cm x 98cm

(62” x 38.6”)

157cm x 100cm

(62” x 39.4”)

170cm, 21° @ 53cm

radius

Noise Type Cert No. 182M Issue 2 182M Issue 2 182M Issue 3

MAAN approving 1750 1975 1886



NO: HM10 ISSUE: 15


Designation Savannah VG

Jabiru(1)

Savannah VG

Jabiru(2)

Savannah VG

Jabiru(3)

Savannah VG

Jabiru(4)





Propeller Type Arplast Ecoprop

166 4T R110/2

2 blade

GT 2 - 2 blade

laminated wood

GT2/157/98

GT 2 - 2 blade

laminated wood

GT2/157/102

Sensenich

2A0J5R62H

2 blade

Propeller Dia x Pitch 166cm, 8.5° @ tip 157cm x 98cm

(62” x 38.6”)

157cm x 102cm

(62” x 40.2”) 60” x 13.5º

3” from tip

Noise Type Cert No. 182M Issue 4 182M Issue 4 182M Issue 4 182M Issue 4

MAAN approving 2061 2259 2306 2227

Designation Savannah VG

Jabiru(5)

Savannah XLS

Jabiru(1)





Propeller Type Hercules

2 blade, 61” x 41”

Dwg 6141373-S

Hercules

2 blade, 61” x 42”

Dwg 6142413-S

Propeller Dia x Pitch 61” x 41” 61” x 42”

Noise Type Cert No. 182M 182M

MAAN approving 2506 2433



NO: HM10 ISSUE: 15


(7) MANDATORY LIMITATIONS

(A) Max Take-Off Weight

450 kg

(B) CG Limits See Annex C

(C) CG datum See Annex C

(D) Cockpit Loadings

Min

Max

Port

55 kg

120 kg

Starboard

-

120 kg

Total

55 kg

240 kg5

(E) Never Exceed Speed ‘Classic’: 110 kts CAS (VDF 122 kts CAS)

‘VG’ & ‘XLS’: 113 kts CAS (VDF 125 kts CAS)

(F) Other limiting speeds VA: 60 kts CAS

VF: 56 kts CAS

(G) Permitted Manoeuvres Bank Limits 60°

Non Aerobatic

Normal acceleration limits, +4 / -2g

(H) Fuel Contents (Max Useable) 77 litres

5 Cockpit limit subject to overall aircraft weight and balance limits.



NO: HM10 ISSUE: 15


(I) Power Plant

Engine Jabiru 2200 Suzuki LS1000

Max RPM 3,1006 6,000 (5 mins) (5,000 continuous)

Max CHT 175°C (150°C continuous) n/a

Max EGT n/a n/a

Fuel Spec 83 MON or 90 RON minimum

unleaded to BS(EN)228 or

AVGAS 100LL.

83 MON or 90 RON minimum

unleaded to BS(EN)228 or

AVGAS 100LL.

Engine Oil Spec As required by engine manual SAE 10W/40 API SH

Gearbox oil spec n/a SAE 80W/90 API GL4

Fuel/Oil Mix 4-stroke, no oil to be used 4-stroke, no oil to be used

Max. Coolant Temperature n/a 100°C

Max. Oil Pressure 525kPa / 76psi / 5.25 bar 7 bar

Min. Oil Pressure 220 kPa / 31psi – normal use.

80 kPa / 11psi @ idle

0.5 bar

Max. Oil Temperature 118°C cont. 120°C

(8) INSTRUMENTS REQUIRED

ASI Altimeter RPM EGT Compass Slip ball

Required

to VNE + 5% CAS

(calibrated) on scale,

and VNE + 10% CAS

before stop

Required to

10,000 ft

Required to 10%

above max revs

for engine fitted.

Optional Required Required

Coolant temp CHT Oil Temp. Oil. Press. Fuel

pressure VSI

At least one required Required Required Optional

6 This RPM limit is specific to the Savannah and is less than given in the engine manual



NO: HM10 ISSUE: 15


(9) CONTROL DEFLECTIONS

Elevator UP (stick back): Note 1

30 2° Trim tab UP: Note 1

Elevator DOWN (stick forward): Note 1

23 2° Trim tab DOWN: Note 1

Ailerons (0° flap) UP: 15 2° Flaperons (MID FLAP, central stick): Note 2

18 3°

Ailerons (0° flap) DOWN: 15 2° Flaperons (FULL FLAP, central stick): Note 2

36 3°

Rudder LEFT: 25 2°

Rudder RIGHT: 25 2°

Notes:

1. These must be checked using BMAA SB 2624 - Savannah Pitch Control and Trim Systems Configuration.

2. If optional mod 1 (‘Mk 2’ flap lever) is fitted, these values become: mid flap: 16°±3°; full flap: 32°±5°.

(10) PILOT’S NOTES, MAINTENANCE MANUALS, PLACARDS

(10.1) Manuals approved for use with this aircraft

(a) MXP740 Savannah UK Operators Manual Issue 1 AL 1 (AL0 is acceptable for aircraft without

optional modification No.4 fitted), or Savannah VG Operators Manual Issue 1, dated August 2007,

or Savannah XLS Operators Manual Issue 1, dated July 2016 as applicable.

(b) Manufacturer’s engine manual (contained at Annex B of the operators manual for a particular

aircraft)

(c) Other manuals as listed at Annex F of the operators manual for a particular aircraft.

(d) Construction to:

Savannah Savannah VG Savannah XLS

ICP Savannah Construction

Manual

ICP Savannah VG Construction

Manual

ICP Savannah S

Construction Manual

SUp Savannah Construction

Manual Part 2,

Issue 2 (March 2006)

SUp Savannah VG Construction

Manual Part 2, Issue 1 (October

2007)

SUp Savannah XLS

Construction Manual Part 2,


SUp Savannah UK Build Manual


SUp Savannah VG UK Build

Manual, Issue 1 (October 2007)

SUp Savannah XLS UK

Build Manual, Issue 1

(March 2015)

(e) Maintenance may be to Microlight Maintenance Schedule MMS-1 as amended by the

Savannah/Savannah VG UK Operators Manual.

(10.2) The following placards are to be fitted:

(a) Flight Limitations Placard (to be visible to pilot) See Annex D.

(b) Engine Limitations Placard (to be located near to engine instruments) See Annex D.

(c) Fuel Limitations Placard (to be located near to filler cap)

A placard is to be fitted showing fuel capacity (77 litres), fuel type(s), fuel:oil ratio (if relevant) and if

MTOW can be exceeded with full fuel and maximum cockpit weight, the fuel loads at MTOW for

cockpit weights at 10kg intervals down to the maximum fuel load. An example is shown at Annex D.



NO: HM10 ISSUE: 15


(d) ASI Placard

A correction placard from 30 to VNE at no more than 10 kts intervals, and at Vso, Va, VF and best glide

speed, must show the corrections from IAS to CAS. For values, see the approval MAAN for the

particular aircraft. An example is shown at Annex D.

In addition the ASI dial must be marked as follows (following calibration):

- Yellow triangle at 40 kts CAS, (recommended approach speed).

- White sector from 31 kts CAS to 56 kts CAS, (flap limits).

- Amber sector from 60 kts CAS to VNE

- Red radial line at VNE

Note: It is recommended that airspeed placards are not fitted to new aircraft until after flight testing, due

to the requirement for pitot-static system calibrations.

(e) Pitch Trimmer Instructions See Annex D.

(f) Switches See Annex D.

(g) Stick position

There is to be a line marked “Take-off trim” on the cabin floor at the correct stick position on the

ground with take-off trim set. This is to be 60 mm forward of the front edge of the lateral bracket

below the front of the seats. (Bungee trim system only)

(h) Maximum continuous RPM

If the increased maximum ZFW of 267kg for the Jabiru 2200 is used, a maximum continuous power of

2800 rpm must be placarded adjacent to the tachometer.

(11) MANDATORY MODIFICATIONS / SERVICE BULLETINS / AIRWORTHINESS DIRECTIVES

ETC

See Annex A for required modifications.

MPD 2006-006 - Rear cross member modification.

MPD 2010-007 - Inspection and modification of anti-balance tab operating mechanism.

BMAA SB 1918.1 (Mandatory) – Inspection of the attachment plates of the front wing lift struts to the

main wing spar (both sides).

BMAA SB 2624 (Essential) - Savannah Pitch Control and Trim Systems Configuration

(12) MINIMUM PERFORMANCE AT MAX TAKE-OFF WEIGHT

Rate of Climb: See Annex F.

Stall or Minimum Flying Speed: Full Flaps: 28 kts CAS (29 kts CAS, VG/XLS variant)

Clean: 30 kts CAS (31 kts CAS, VG/XLS variant)

at Aft CG, see Annex D Part (d)

BMAA Approval:

B J Syson

Chief Technical Officer

12 February 2018



NO: HM10 ISSUE: 15


ISSUE HISTORY

HM10 Issue A Initial draft to permit prototype construction.

HM10 Issue B Second draft, for flight testing.

HM10 Issue C Final draft, for team checking prior to approval

HM10 Issue 1 First approval of type; configuration Jabiru(1). Authorised by MAAN 1591 Issue 1.

Signatory G B Gratton

HM10 Issue 2 Corrections from Issue 1. Authorised by MAAN 1591 Issue 2.

Signatory G B Gratton

HM10 Issue 3 Approval of Jabiru(4) configuration, authorised by MAAN 1750 Issue 1. Addition of optional

“Mk.2” flap lever.

HM10 Issue 4 Correction to powerplant configuration Jabiru(4).

HM10 Issue 5 Clarification of aileron deflections, ignition switch approval, carb heater description, fuel

capacity, addition of special inspection point 1. Change to max permitted empty weight for

Jabiru variants to 263kg (details in post-approval file 2004). Increase in maximum cockpit

loadings, addition of optional modifications 2-7 and mandatory modification 15 (authorised by

MAAN 1945).

Signatory J A F Viner.

HM10 Issue 6 Addition of optional modification 8 (authorised by MAAN 1945 Issue 2). Addition of

configuration Jabiru(5), authorised by MAAN 1975 Issue 1. Signatory J A F Viner

HM10 Issue 7 Addition of configuration LS(1), authorised by MAAN 1886. Addition of Suzuki LS1000

engine data. Revised flap settings to reflect positions achieved using optional modification 1.

Addition of MPD 2006-006 – Rear cross member modification, (BMAA SB 2013/1).

Signatory J A F Viner

HM10 Issue 8 Addition of items in Annex E. Addition of mandatory modification 16. Addition of ‘VG’

variant and associated data, including optional mods 9 & 10, authorised by MAAN 2061.


HM10 Issue 9 Update of VNE for VG variant, authorised by MAAN 2061 Issue 2.


HM10 Issue 10 Amendment of Annex E item 5. Addition of Savannah VG Jabiru(2) and VG Jabiru(3).

Correction to elevator and tab deflections in Section 9.

Corrections and improvements to wording and formatting.

Addition of MPD 2010-007 – Inspection and modification of anti-balance tab operating

mechanism.

Signatory B J Syson

HM10 Issue 11 Addition of configuration Savannah VG Jabiru(3) approved by MAAN 2306.

Addition of configuration Savannah VG Jabiru(4) approved by MAAN 2227.

Addition of MPD 2010-009 – Inspection for corrosion of the attachment plates of the front

wing lift struts to the main wing spar (both sides).

Additions to Section 11 and Annex E of this document.

Signatory B J Syson

HM10 Issue 12

Minor formatting changes. Addition of VG ASI calibration table. Correction of VG collector

tank moment arm.

Signatory B J Syson



NO: HM10 ISSUE: 15


HM10 Issue 13 Addition of VG Jabiru(5) configuration, and associated performance figures, approved by

MAAN 2506.

Signatory B J Syson

HM10 Issue 14 Addition of XLS variant and XLS Jabiru(1) configuration, and associated performance

figures. Max ZFW of 267kg for Jabiru 2200 subject to reduction in max continuous RPM.

Approved by MAAN 2433. Correction to propeller diameter and pitch for VG Jabiru(5).

Signatory B J Syson

HM10 Issue 15 BMAA SB 2624 - Savannah Pitch Control and Trim Systems Configuration. Section 9,

Control Deflections, adjusted accordingly.

Signatory B J Syson, 12 February 2018



NO: HM10 ISSUE: 15


Illustration of Aircraft - 3 View - Savannah Classic

Illustration of Aircraft – Photograph - Savannah Classic



NO: HM10 ISSUE: 15


ANNEX A

MANDATORY MODIFICATIONS

No. Brief Description of Modification

1. Introduction of lateral brackets to stiffen flap lever

2. Fitment of fuel-tap securing-bracket below floor

3. Addition of washers to flaperon linkages behind door and nylon washers fitted either side of

flaperon horn

4. Either:

(a) Soundproofing blanket fitted with Velcro to rear of baggage compartment, or

(b) Solid rear cockpit wall (standard on later models)

5. Baggage retaining net at front of baggage compartment

6. Eliminate demist vent control on top of cowling

7. Fitment of guard strip around edge of coaming

8. Choke control to be coloured distinct from cabin heat control

9. <deleted>

10. Elevator full width anti-balance tab

11. Introduction of elevator bias spring mechanism within tail (not required if optional mod 4

fitted)

12. Introduction of bungee pitch trimmer in cockpit (not required if optional mod 4 fitted)

13. Deletion of original electric pitch trimmer (optional mod 4 is different from the original

electric trimmer)

14. Marking graduations in litres alongside fuel sight tube. Means must be available to confirm

correct reading in air and on ground (e.g. two sets of markings needed, clearly separated,

respectively for the ground and flight attitudes, or “flight attitude” spirit level for use on

ground)

15. Addition of master 15A circuit breaker/fuse immediately after battery

16. Rear cross-member modification MPD 2006-006 (BMAA SB 2013)

17. MPD 2010-007 (BMAA SB 2283) - Inspection and modification of anti-balance tab operating

mechanism. This only applies to aircraft fitted with the bungee pitch trim.



NO: HM10 ISSUE: 15


ANNEX B

APPROVED OPTIONAL MODIFICATIONS

No. Brief Description of Modification

1. “Mk.2” (shorter) flap lever mechanism (mandatory modifications 1 & 3 not required when fitted)

2. Two additional fuselage ribs to Canadian sport-plane standard. (Should be incorporated in kits

from serial 01-03-51-405)

3. Doubling (two plates) of lift-strut attachment plates to Canadian sport-plane standard. (Should be

incorporated in kits from serial 01-03-51-405)

4. Electric pitch trimmer, as supplied by SUP, using an electric actuator within the horizontal

stabiliser, eliminating bungee and spring mechanisms in cockpit and fin respectively (mandatory

modifications 11 & 12 not required when fitted)

5. Brass bushing on elevator and rudder control surfaces

6. Addition of tie-down points at lift-strut/wing interface

7. Installation of wing inspection panel at lift-strut/wing interface

8. Increased thickness wing attachment brackets (3mm to 5mm) as part of Canadian sport-plane

standard. (Should be incorporated in kits from serial 01-03-51-405)

9. Jury struts (if fitted, optional modifications 3 and 8 must also be fitted)

10. Intra-rib stringers



NO: HM10 ISSUE: 15


ANNEX C

WEIGHING INFORMATION

Savannah Savannah VG/XLS

CG Datum Slat leading edge Wing leading edge

Weighing attitude All 3 wheels on a level surface

Mainwheel moment arm 0.755m aft of datum 0.655m aft of datum

Nosewheel moment arm 0.710m fwd of datum (-0.710m) 0.810m fwd of datum (-0.810m)

Fuel tank 0.595m aft of datum (77 litres

maximum capacity)

0.495m aft of datum (70 litres

maximum capacity)

Collector tank (treat as part of main fuel tank as

above)

0.87m aft of datum (7 litres maximum

capacity)

Crew 0.650m aft of datum (120kg max load

per seat, min load 55kg on pilot’s seat)

0.550m aft of datum (120kg max load

per seat, min load 55kg on pilot’s seat)

Baggage 1.42m aft of datum, max capacity 20kg 1.32m aft of datum, max capacity 20kg

Aft CG limit 0.550m aft of datum 0.445m aft of datum

Fwd CG limit 0.429m aft of datum 0.331m aft of datum

The aircraft must be shown to remain within CG limits for all permitted loadings up to and including the

maximum baggage load. The capacity of the baggage compartment may be reduced to meet this requirement,

to any value below the maximum of 20kg. The individual seat limits may be reduced, not below 86kg, if

required to stay within CG limits.



NO: HM10 ISSUE: 15


ANNEX D

EXAMPLE PLACARDS

(a) Flight Limitations Placard (to be visible to pilot)

Savannah [VG/XLS] [Engine] [Registration]

Bank angle limits:

Normal Acceleration Limits:

Empty Weight:

Max Take-Off Weight:

Minimum Cockpit Weight:

Maximum Cockpit Weight:

+/- 60°

+4 / -2g

____ kg **

450 kg

55 kg

120 kg in each seat

Aerobatics and deliberate spinning prohibited.

** This must match the most recent W&CG report for the aircraft.

(b) Engine Limitations Placard (to be located near to engine instruments)

All engine limitations must be shown as coloured markers (red for danger, amber for caution) on the

instrument displays.

(c) Fuel Limitations Placard (to be located near to filler cap)

FUEL

Capacity 77 Litres

Cockpit Weight (kg)

(including baggage)

Max. Fuel Load (litres)

260

250

….

…. or below 77 litres (full)

83 MON or 90 RON minimum unleaded to BS(EN)228 or

AVGAS 100LL

(d) ASI Placard

Savannah Classic

kt CAS

(calibrated)

28

VS0

30

VS1

40

App

46

Glide

50

Climb

56

VF

60

VA

70 80 90 100 110

VNE

kt/mph* IAS

(indicated)

Stall speeds given are at aft CG, they may appear to increase by up to 7kts CAS with forward CG

Savannah VG/XLS

kt CAS

(calibrated)

29

VS0

31

VS1

40

App

50 Glide

56

VF

60

VA &

Climb

70 80 90 100 110 113

VNE

kt/mph* IAS

(indicated)

Stall speeds given are at aft CG, they may appear to increase by up to 7kts CAS with forward CG

*delete as applicable.



NO: HM10 ISSUE: 15


(e) Pitch Trimmer Instructions

PITCH TRIM nose down nose up

Also a line must be marked “Take-off” below the stick, 60mm forward of the seat front edge bulkhead

(bungee trimmer), or one line below middle (electric trimmer).

(f) Switches

All switches are to be marked with function and sense (up=on, down=off).

Note that the originally supplied, guarded ignition switches are ‘down=on’ on early aircraft; this is

acceptable due to the mode of operation but only applies to the original-specification ignition switches.

Where possible the switches should be orientated ‘up=on’.

Electric trim switches should be orientated ‘nose up’ = lower part of switch to be pressed.

(g) Flaps

The three flap lever positions are to be marked “0”, “18” and “36”, or “0”, “16” and “32” if the Mk 2

flap lever is fitted.

(h) Baggage compartment

To be placarded with it’s limit, which may not exceed 20kg. (See Annex C above for explanation)

ANNEX E

POINTS FOR SPECIAL ATTENTION

In service, the following points have been found to be commonly recurring problems, and Inspectors must give

special attention to the following both during initial approval, and during later inspections.

1. Special check at annual / 150hr inspection for any wear in control cables where they cross.

2. MPD 2006-006 must be complied with (BMAA SB 2013/1): modification of rear cross member.

3. Note that earlier examples may be placarded to a maximum seat weight of 86kg. This may be increased to

120kg provided a new weight and balance report is prepared and all relevant placards are altered

accordingly.

4. It has been noticed on a couple of examples that the weld on the aileron torque tube (connecting the control

stick to the bell crank mounted on the rear cross member) can come into contact with the nylon bush,

causing wear on the bush. This should be checked occasionally and if necessary a new torque tube and

bush should be sourced from SUp.

5. Piano hinges on the doors and anti-balance tabs should be crimped at the ends (to retain the hinge pins) at

the factory. If crimping is not present, contact the kit importer.

6. Check for any rubbing of skins against fairings.

7. Corrected elevator and anti-balance tab deflections to be observed.

8. MPD 2010-007 must be complied with (BMAA SB 2283/1): inspection and modification of pitch anti-

balance tab mechanism (bungee pitch trim).

9. MPD 2010-009 must be complied with (BMAA SB 1918/3): inspection for corrosion and abrasion of the

attachment plates of the front wing lift struts to the main wing spar (both sides).



NO: HM10 ISSUE: 15


ANNEX F

SCHEDULED PERFORMANCE FOR APPROVED CONFIGURATIONS

Classic variant:

Configurations TODR, metres

(unfactored in

italics)

LDR, metres Climb Rate, fpm Glide Ratio

Jabiru 198 (152) 140 740 7.5:1

Suzuki LS1000 340 (262) 227 740 7.5:1

VG variant:


(unfactored in

italics)


VG Jabiru(1)-(4) 228 (175) 159 860 10:1

VG Jabiru(5) 340 (260) hard rwy 350 hard rwy 600 (ISA 2000’) 10:1

XLS variant:


(unfactored in

italics)


XLS Jabiru(1) 340 (260) hard rwy 350 hard rwy 600 (ISA 2000’) 10:1

Unless otherwise stated, all scheduled performance values are for ISA, sea-level, still-air conditions, with a short

dry-grass runway surface.

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Homebuilt Aircraft Data Sheet - bmaa.org · british microlight aircraft association homebuilt aircraft data sheet (hads) no: hm10 issue: 15 hads hm10 issue 15 page 1 of 16 type mxp-740