NO: BM 41 ISSUE: 7 TYPE: Shadow Series CD · civil aviation authority – safety regulation group...
Transcript of NO: BM 41 ISSUE: 7 TYPE: Shadow Series CD · civil aviation authority – safety regulation group...
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM 41 ISSUE: 7
TADS BM 41 Issue 7 Page 1 of 11
TYPE: Shadow Series CD (1) MANUFACTURER CFM Aircraft Ltd (ceased trading)
BMAA is responsible for continued airworthiness (2) UK IMPORTER None (3) CERTIFICATION BCAR Section S (First example Advanced Issue
dated March 1983 as amended 11 October 1988 along with BCAR Section C-5-4 Issue 1, paragraph 2)
(4) DEFINITION OF BASIC CFM Drawing Nos. S125-A (C) and S144-A (CD) STANDARD dated October 1989. CFM Shadow C & CD
Construction Manual C/RM – CD (5) COMPLIANCE WITH THE MICROLIGHT DEFINITION
(a) MTOW 374 kg (b) No. Seats 2 (c) Maximum Wing Loading 24.85 kg/m2 (d) Vso 35 kt IAS (e) Permitted range of pilot weights 55 – 90 kg front seat
0 – 90 kg rear seat (f) Typical Empty Weight (ZFW) 186 kg (g) ZFW + 172 kg crew + 1 hr fuel 372 kg (19 litres / 13.7 kg) (h) ZFW + 86 kg pilot + full fuel 308 kg (49.6 litres / 35.7 kg) (i) Max ZFW at initial permit issue 188.5 kg
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM 41 ISSUE: 7
TADS BM 41 Issue 7 Page 2 of 11
(6) POWER PLANTS
Designation Shadow Series C & CD
Engine Type Rotax 503-2V
Reduction Gear 2.58:1
Exhaust System Rotax Modified
Intake System Oiled Air filters
Propeller Type Precisions Props Ground Adjustable
(3 blade)
Propeller Dia x Pitch 52” x 50”
Noise Type Cert No. 123M
AAN approving configuration 22296P
(7) MANDATORY LIMITATIONS
(a) Max Take-Off Weight 374 kg (b) CG Limits Aft Limit 45.2” aft of datum Forward Limit 39.3” aft of datum (c) CG datum 24” fwd of Wing Leading Edge at
Wing Root
(d) Cockpit Loadings Front Rear Total Min 55 kg 0 kg 55 kg Max 90 kg 90 kg 180 kg
(e) Never Exceed Speed, VNE 94 kt IAS (f) Manoeuvring Speed, VA 66 kt IAS (g) Flap Limiting Speed, VF 15° deflection 57 kt IAS 30° deflection 52 kt IAS
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM 41 ISSUE: 7
TADS BM 41 Issue 7 Page 3 of 11
(h) Permitted Manoeuvres Maximum bank angle 60° Normal acceleration limits, +4 / -2g Aerobatics and Spinning prohibited
(i) Fuel Contents (Max Useable) 22.7 litres 49.6 litres if slipper tank fitted
(j) Power Plant
Engine Rotax 503-2V
Max RPM 6800
Max Continuous RPM 6000
Max CHT 250°C (480°F)
Max EGT 650°C (1200°F)
Fuel Spec 95 RON minimum unleaded to BS(EN)228, or AVGAS 100LL
Engine Oil Specification 2 Stroke
Gearbox Oil Specification API-GL5/GL6 SAE 140 EP 85W-140 EP
Fuel/Oil Mix 50:1
Fuel Pressure 0.2-0.4 bar at cruise power
(8) INSTRUMENTS REQUIRED
ASI Altimeter RPM CHT / EGT Compass Fuel Gauge VSI Slip ball
Required Required Required Required Required Required Optional Optional
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM 41 ISSUE: 7
TADS BM 41 Issue 7 Page 4 of 11
(9) CONTROL DEFLECTIONS
Elevator UP: 20° ± 2° Elevator trim tab UP: 5° * Elevator DOWN: 16° ± 2° Elevator trim tab DOWN: 35° * Ailerons UP: 20° ± 2° Flaps ZERO: In line with
wing centre section. 0°
Ailerons DOWN: 10° ± 2° Rudder LEFT: 25° ± 2° Flaps INTERMEDIATE: 15° ± 3° Rudder RIGHT: 25° ± 2° Flaps LANDING: 30° ± 3°
* The elevator trim tab deflections are shown for guidance. In practice some variation is to be expected.
(10) PILOT'S NOTES, MAINTENANCE MANUALS, PLACARDS 10.1 Manuals approved for use with this aircraft: Shadow Series C & CD Pilots Notes PN – SH/C at Amendment 5 Shadow Series C & CD Service Manual SM – SH/C at Amendment 4 Shadow Series C & CD Construction Manual C/RM – CD at Amendment 1 10.2 See Annex D for details of the placards that are to be fitted.
(11) SERVICE BULLETINS, MANDATORY MODIFICATIONS See Annex A for details. Note: MPDs may be downloaded from the CAA Website: http://www.caa.co.uk/docs/33/cap661.pdf
(12) MINIMUM PERFORMANCE AT MAX TAKE-OFF WEIGHT Rate of Climb: 500 ft/min at 60 kt IAS Stall or Minimum Flying Speed: 35 kt IAS in landing configuration
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM 41 ISSUE: 7
TADS BM 41 Issue 7 Page 5 of 11
ISSUE HISTORY
Issue No. Reason and Signatory
1 12/03/90 Initial issue T R Woods
2 18/05/90 T R Woods
3 06/11/92 T R Woods
4 13/02/97 To revise empty weight and change of manufacturer R J Hardy
5 06/12/02 To include weighing information, correction of engine temperature limits, editorial changes and the inclusion of MPD 2002-010 and BMAA SB 1661 Issue 1. J Barratt
6 05/07/04 Change to the organisation responsible for continued airworthiness support and additional MPDs J Barratt
7 01/08/11 Removal of MPD 2004-002, superseded by MPD 2004-007R1. Inclusion of all applicable MPDs, SBs and Approved Optional Mods. Correction of elevator and elevator trim tab deflections. Placard updates. Correction of climb rate. General data update, improved layout and 3-view drawing. Merging of C & CD data, though still referred to as BM40 & BM41. A C Love
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM 41 ISSUE: 7
TADS BM 41 Issue 7 Page 6 of 11
ILLUSTRATION OF AIRCRAFT – 3 VIEW
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM 41 ISSUE: 7
TADS BM 41 Issue 7 Page 7 of 11
ANNEX A SERVICE BULLETINS AND MANDATORY MODIFICATIONS
Designation Classification Subject CFM SB 7 Recommended Solar heating of upper wing surfaces coloured other than white CFM SB 8 Optional Alloy wheels CFM SB 9 Recommended Support for front hanger bracket CFM SB 10 Recommended Fore/aft wing movement CFM SB 11 Recommended Multi-strand elevator cable CFM SB 12 & MPD 1998-013 R2
Mandatory Replace/modify the rudder fin post
CFM SB 13 Recommended Rudder pedal hinges CFM SB 14 Issue 2 & MPD 2001-002 R2
Mandatory Cracking of tailplane spar leading edge spigot tubes
BMAA SB 1661 & MPD 2002-010
Mandatory Installation of ASI and altimeter correction placards
MPD 2004-007 R1 Mandatory Main undercarriage replacement with approved alternative. Implement in accordance with MAAN 1762 Issue 2 or MAAN 1773 Issue 1
MPD 2004-008 R1 Mandatory Nosewheel undercarriage. Inspect in accordance with MAAN 1762 Issue 2 Appendix A, or MAAN 1773 Issue 1 Appendix A
BMAA SB 2073 Recommended Inspection of Part F153 Hanger Tube Bracket BMAA SB 2329 Essential Horizontal Tailplane Spar and Bush Wear BMAA SB 2336 Essential Fuel Tank Deterioration
ANNEX B APPROVED OPTIONAL MODIFICATIONS
The installation of all optional modifications is to be inspected by a BMAA inspector and an entry made in the appropriate logbook(s). Involvement of the BMAA Technical Office is not required. Note that other approved modifications may exist which are not mentioned here. Contact the BMAA for details. Mod No. Subject CFM 15 / AAN 21458 Electrically operated elevator trim tab CFM 20 / AAN 21682 27 litre fuel tank in place of the rear occupant CFM 28 / AAN 23713 Modification to allow aircraft to be flown without foot controls CFM 28a / AAN 23713 Mechanically operated brakes replace pneumatic CFM 29 / AAN 27392 / MAAN 1193 Issue 5
Slipper tank
CFM 31 / AAN 25545 Multi-strand elevator cable CFM 32 / AAN 25545 Additional fuselage (shroud) window MAAN 1762 Issue 2 Crosbie replacement undercarriage and introduction of new max continuous engine
rpm (installation of this modification fulfils the requirements of MPD2004-007R1) MAAN 1773 Issue 1 Cook replacement undercarriage and introduction of new max continuous engine rpm
(installation of this modification fulfils the requirements of MPD2004-007R1)
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM 41 ISSUE: 7
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ANNEX C WEIGHING INFORMATION
CG Datum: 24” Fwd of Wing L/E at Wing Root
Weighing attitude: Weigh at main wheels and tailskid with boom level
Mainwheel moment arm: 46.75” aft of datum
Skid moment arm: 165.75” aft of datum
Main tank moment arm: 63.5” aft of datum, capacity 22.7litres (16.3kg)
Slipper tank moment arm: 42” aft of datum, capacity 26.9 litres (19.4kg)
Pilot moment arm: 7.75” aft of datum for pilots below 75 kg 9.75” aft of datum for pilots above 75 kg
Passenger moment arm: 42” aft of datum
Crew weights: Front seat: minimum 55 kg / maximum 90 kg Rear seat: minimum 0 kg / maximum 90 kg
Aft CG Limit: 45.2” aft of datum
Fwd CG Limit: 39.3” aft of datum
ANNEX D EXAMPLE PLACARDS
(a) FLIGHT LIMITATIONS PLACARD AND MARKINGS To be displayed next to the ASI.
VNE (Never exceed speed): 108 mph or 94 knots IAS (to match ASI units) VA (Manoeuvring speed): 76 mph or 66 knots IAS (to match ASI units)
Alternatively the ASI may be marked with: A red radial line at VNE
An amber radial line at VA A white arc from VS0 to VFE (b) ASI CORRECTION PLACARD To be displayed next to the ASI.
Kt IAS (ASI units)
30 35 (VS0)
40 (VS1)
50 60 climb
66 (VA)
70 80 90 94 (VNE)
Kt CAS 29 33 36 44 51 56 59 68 77 80
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
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TADS BM 41 Issue 7 Page 9 of 11
(c) ALTIMETER CORRECTION PLACARD To be displayed next to the Altimeter.
Kt IAS (ASI units) 30 40 50 60 70 80 90 94 Altimeter over-read (feet) 0 10 25 40 60 75 90 95
(d) LOADING PLACARD The placard is to be visible to the pilot.
EMPTY WEIGHT: Enter weight from current weight report MAX TAKE–OFF WEIGHT: 374 kg MINIMUM COCKPIT LOAD: 55 kg in front seat MAXIMUM COCKPIT LOAD: 90 kg in each seat (may be reduced to 86 kg pilot to satisfy cg limit)
(e) ENGINE LIMITATIONS PLACARDS AND MARKINGS To be displayed next to the engine instruments, and/or the instruments to be marked as detailed below.
MAX RPM: 6800 and/or a red radial line MAX CONT RPM: 6000 and/or an amber sector between MAX CONT and MAX RPM MAX EGT: 650°C or 1200°F (to match units of instrument) and/or a red radial line MAX CHT: 250°C or 480°F (to match units of instrument) and/or a red radial line
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM 41 ISSUE: 7
TADS BM 41 Issue 7 Page 10 of 11
(f) FUEL LIMITATIONS PLACARD This must be based on the most recent weight report for the aircraft and displayed near to the filler cap. The examples below are for an empty weight of 186 kg. Adjust accordingly using empty weight from current weight report. With Slipper Tank
FUEL Capacity 49.6 Litres
2-stroke mix 50:1 Cockpit Weight
(kg) Max. Fuel
Load (litres) 180 11 175 18 170 25 165 31 160 38 155 45 152 FULL
95 RON minimum unleaded to BS(EN)228 or AVGAS 100LL
Without Slipper Tank
FUEL Capacity 22.7 Litres
2-stroke mix 50:1 Cockpit Weight
(kg) Max. Fuel
Load (litres) 180 11 175 18 171 FULL
95 RON minimum unleaded to BS(EN)228 or AVGAS 100LL
(g) SWITCHES All switches are to be marked with function and sense (up=on, down=off). (h) MISCELLANEOUS Fireproof metal plate showing the aircraft registration to be mounted in a prominent position. The additional limitations, warnings, and secondary controls and switches are to be placarded as below;
CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)
NO: BM 41 ISSUE: 7
TADS BM 41 Issue 7 Page 11 of 11
Front Cockpit AEROBATICS AND SPINNING ARE PROHIBITED TRIM: NOSE UP NOSE DOWN THROTTLE: INCREASE DECREASE CHOKE: ON OFF EMERGENCY FUEL CUT OFF: UP FOR OFF IGNITION: ON OFF FLAPS: 0° 15° VF1: 65 mph or 57 knots IAS (to match ASI units) 30° VF0: 60 mph or 52 knots IAS (to match ASI units) Rear Cockpit MAXIMUM SEAT LOAD: 90 kg DO NOT GET OUT WHEN ENGINE IS RUNNING CD only: DO NOT ATTEMPT TO FLY THE AIRCRAFT SOLO FROM THE REAR SEAT THROTTLE: INCREASE DECREASE
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