CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM65 ISSUE: 6. Flight Design CT2K

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1 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM65 ISSUE: 6 TYPE: Flight Design CT2K (1) MANUFACTURER: P&M Aviation Ltd, Unit B, Crawford St, Rochdale. (UK type approval holder for Flight Design GMBH) (2) UK IMPORTER: P&M Aviation Ltd. (3) CERTIFICATION: BCAR section S issue 2, JAR-VLA parts C & D. (4) DEFINITION OF BASIC STANDARD: CT2K Drawings set issue 2, 18/6/01. (5) COMPLIANCE WITH THE MICROLIGHT DEFINITION (a) MTOW 450 kg (b) No. Seats 2 (c) Maximum Wing Loading (d) Vso (e) Permitted range of pilot weights (f) Typical Empty Weight (ZFW) (g) ZFW kg crew + 1 hr fuel (14litres / 10kg) (h) ZFW + 86 kg pilot + full fuel (130 litres / 93kg) (i) Max ZFW at initial permit issue 41.6 kg/m² 34 kt CAS kg per seat. (180 kg total) 264 kg 450 kg 448kg 268kg TADS BM65 Issue 6 Page 1 of 9

2 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM65 ISSUE: 6 (6) POWER PLANTS Designation Rotax 912 ULS Rotax 912 ULS Engine Type 4 cylinder 4 stroke horizontally opposed 4 cylinder 4 stroke horizontally opposed Reduction Gear 2.43:1 2.43:1 Exhaust System Rotax underslung muffler Rotax underslung muffler Intake System 2 x K&N filters 2 x K&N filters Propeller Type Propeller Dia x Pitch Neuform Novaprop TXR2 1660mm x 21 o at blade undersurface at 75% radius Warp Drive 3 bladed carbon composite 1676mm x 19 o at blade undersurface at tip Noise Type Cert No. 174M issue 1 174M issue 2 AAN approving configuration AAN BMAA-1003 (7) MANDATORY LIMITATIONS: (a) Max Take-Off Weight 450kg (b) CG Limits 410mm aft of datum (35% mac) 257mm aft of datum (22% mac) (c) CG datum (d) Cockpit Loadings (e) Never Exceed Speed Vne (f) Manoeuvring Speed Va (g) Max speed for full flap Vf (h) Max rough air speed Vc (i) Permitted Manoeuvres (j) Fuel Contents (Max Useable) Min Max Leading edge at any point of span Port 0kg 100kg 150 kt 86kt 64kt 115kt Starboard 0kg 100kg Total 55kg 180kg Non Aerobatic Normal acceleration limits, g 130ltr TADS BM65 Issue 6 Page 2 of 9

3 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM65 ISSUE: 6 (k) Power Plant See Table Engine Max RPM MAX CHT MAX EGT Rotax 912 ULS 5800 (5min) 4800 (Continuous) 135 o C 925 o C Fuel Spec 95 RON minimum unleaded to BS(EN)228 Premium, Premium plus or 97+ octane 4-star /MOGAS leaded fuel to BS 4040, or AVGAS 100LL. (Unleaded preferred see engine manual). Engine Oil Spec SAE 10W-40 To API SF or SG See engine manual viscosity table. Gearbox oil spec Fuel/Oil Mix Coolant Temperature Oil Pressure Oil Temperature Fuel Pressure Integral supply with engine N/A 135 C Normal 2-5 bar above 3,500 rpm Min 0.8bar at idle Max 7bar C bar (8) INSTRUMENTS REQUIRED: ASI Altimeter RPM CHT Compass Oil press/temp Required (0-160kt) Required C Option 0-8bar 0-150C Fuel Pressure VSI Slip ball Option Option Recommended TADS BM65 Issue 6 Page 3 of 9

4 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) (9) CONTROL DEFLECTIONS: Control Surface Datum NO: BM65 ISSUE: 6 Deflection measured at trailing edge +ve = surface downwards Ailerons Neutral, measure from flap T.E, flaps up Up -110mm ±10, Down 50mm ±5 Flaps Fuselage fairing trailing edge Flaps fully up = - 60mm +-5 (-12 o ) Flaps 0 (takeoff) = 0 mm +-5 (0 0 ) Flaps fully down = 175mm (40 0 ) Stabilator Trim tab Rudder Measure top surface of ventral fin to lower trailing edge of stabilator. With stabilator neutral (aligned with fuselage fairing) Rudder horn aligned with fin, apply full pedal deflection Up -185mm ±10, Down - 30mm ±5 Trim full nose up 7mm +-3 Trim full nose down - 25mm +-5 Left 145mm ±10, Right 145mm±10 (10) PILOT'S NOTES, MAINTENANCE MANUALS REFERENCES: 10.1 Manuals approved for use with this aircraft. (a) Cyclone Airsports manual ref : CTMan current issue. (b) Rotax 912 engine (all versions) operators manual current issue The following placards are to be fitted (see manual for full set):- On main panel: At each filler cap: LIMITATIONS CT2K MOD M198 MAX AUW 450KG MAX 100KG PER SEAT, TOTAL 180 EMPTY WEIGHT KG (MAX 268) NON-AEROBATIC, LIMITS +3.8G, -1.5G TOTAL LOAD FUEL 55- KG 130L(FULL) 130KG L 160KG L 180KG L Vso FLAPS 40 O 34KT VS1 FLAPS 0 O 40KT VS2 FLAPS 12 O 43KT VF MAX FLAPS 64KT Va MANOEUVRE 86KT Vc CRUISE 115KT Vne 150KT MAX CONTIN RPM 4800 OIL PRESS 1.5-5BAR OIL TEMP MAX 130 O C COOLANT MAX 135 O C CAPACITY 65L FUEL TYPE: Min. RON 95 EN228 PREMIUM PLUS AVGAS 100LL (SEE MANUAL) At cowl hatch: ENGINE OIL SEMI-SYNTHETIC SAE COOLANT 100% ANTI-FREEZE At baggage door: MAX BAGGAGE 25KG TOTAL Note that the empty weight in the above placards must reflect the current empty weight of the aircraft, including any modifications/repairs. TADS BM65 Issue 6 Page 4 of 9

5 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM65 ISSUE: 6 (11) MANDATORY MODIFICATIONS / SERVICE BULLETINS / AIRWORTHINESS DIRECTIVES ETC: Service Bulletin CT107 Door Latching (2 pin doors only) Issued 27/07/01 Service Bulletin CT115 Aileron and Flap Bracket Attachment Issued 20/05/04 MPD R1 Aileron and Flap Bracket Attachment Issued 12/08/04 Service Bulletin CT119 Nosewheel Assembly Issued 06/01/05 MPD Nosewheel Assembly Issued 06/01/05 Service Bulletin CT123 Inspection of Main Undercarriage Legs Issued 29/01/07 MPD Inspection of Main Undercarriage Legs Issued 02/03/07 Service Bulletin CT124 Flap Up Limit Cable Issued 05/12/06 MPD Flap Up Limit Cable Issued 08/12/06 Service Bulletin CT125 Fuel System Issued 02/07/07 Note: MPD and SB may be downloaded on the CAA and P&M Aviation Ltd. Websites: (12) MINIMUM PERFORMANCE AT MAX TAKE-OFF WEIGHT Rate of Climb: Stall or Minimum Flying Speed: 900 fpm at 55kt IAS. 34kt IAS at MTOW / idle. TADS BM65 Issue 6 Page 5 of 9

6 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP Issue No. 1 22/06/01 MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) Initial issue R J HARDY NO: BM65 ISSUE: 6 Issue History 2 31/03/03 Change of manufacturer address J BARRATT Reason & Signatory 3 13/11/03 Warp Drive 3 bladed propeller option, correction to rudder throw J BARRATT 4 31/03/05 Addition of a note in section 10.2, addition of optional modification M131 J BARRATT 5 06/07/05 New Company name P& M Aviation Ltd. J BARRATT 6 05/02/10 Increase of max empty weight to 268kg, limitation of max continuous power to 4,800 rpm, modification and MPD updates. D S CORTIZO TADS BM65 Issue 6 Page 6 of 9

7 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM65 ISSUE: 6 Illustration of Aircraft - 3 View TADS BM65 Issue 6 Page 7 of 9

8 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM65 ISSUE: 6 ANNEX A MANDATORY MODIFICATIONS 1. See section 11 above. 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). Note that other approved modifications may exist which are not listed here. Mod ref Description Notes Issued CT192 Rubber mounting of radiator Standard from s/n Optional for earlier a/c CT164 3 latch door Standard from s/n Will not fit earlier a/c 23/1/03 01/03/02 M107 Fitting of Warp Drive 3 blade propeller Optional, issue 2 onwards of handbook required 17/9/03 M110 Oil pressure switch Optional fit if analogue sensor unreliable 11/07/06 M116 Flexible fuel feed pipes Optional, recommended. 06/01/05 M131 Slipper clutch Optional, smoother starting, adds 1.8kg 02/11/04 M134 M136 M143 Plate added to U/C top fitting, vertical bolts to tunnel. New type nosewheel with integral hub Stud type retention of nose strut spring. Optional, recommended. 22/12/04 Optional, recommended. 06/01/05 Optional 14/04/05 M mm stainless aileron brackets See SB 115 issue 2 25/10/06 M186 Fuel cross feed See SB /01/07 M188 Circuit breaker panel Optional 27/02/07 M191 Standard repair schemes P&M approved repair stations only 28/02/07 TADS BM65 Issue 6 Page 8 of 9

9 CIVIL AVIATION AUTHORITY SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM65 ISSUE: 6 ANNEX C WEIGHING INFORMATION 1. CG Datum: Leading edge of wing at any point. 2. Weighing attitude: Fuselage cockpit tunnel horizontal 3. Mainwheel moment arm: 570 mm aft of datum 4. Nosewheel moment arm: -870 mm fwd of datum 5. Fuel moment arm: 300 mm aft of datum 6. Crew moment arm: 520 mm aft of datum 7. Baggage moment arm 1200 mm aft of datum (max 25kg) 8. Crew weights: Minimum 55kg / maximum 180 kg 9. Aft CG Limit: 410mm aft of datum (35% MAC) 10. Fwd CG Limit: 257mm aft of datum (22% MAC) TADS BM65 Issue 6 Page 9 of 9

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15 Civil Aviation Authority MANDATORY PERMIT DIRECTIVE Number: Issue date: 04 October 2012 In accordance with 22(1) of Air Navigation Order 2009 as amended the following action required by this Mandatory Permit Directive (MPD) is mandatory for applicable aircraft registered in the United Kingdom operating on a UK CAA Permit to Fly. Type Approval Holder s Name: P&M Aviation Title: Type/Model Designation(s): CT2K and CTSW Aircraft Fuel System Engine Fuel Feed Manufacturer: Applicability: Reason: P&M Aviation CT2K and CTSW There have been reports of engine failure as a result of fuel tank imbalance and consequent loss of fuel feed. Effective Date: 04/10/2012 The aircraft have a two tank fuel system, with a tank located in the leading edge section of each wing. The wing is relatively flat (low dihedral) such that if the aircraft is flown with one wing low at low fuel states, then that tank may not feed. If the other tank is empty then loss of fuel feed to the engine may occur. It is therefore important that the aircraft is flown to ensure fuel quantities are balanced across the two tanks in order to maintain uninterrupted fuel feed to the engine. Engine power loss from interrupted fuel feed, particularly during approach flight phases close to the ground, where engine recovery may not be possible, is an unsafe condition that requires corrective action. Compliance/Action: Compliance is required as follows, unless previously accomplished: 1. Within 2 months from the effective date of this MPD conduct the actions required in accordance with sub-paragraphs 1) to 7) of SB Within 12 months and thereafter annually or at 100 hours intervals (whichever occurs earliest), carry out the checks required in accordance with sub-paragraph 8) of SB If during a check required by sub-paragraph 8 of SB 131 any fault is found, before next flight rectify the fault. ENSURE COMPLIANCE WITH THIS MPD IS RECORDED IN THE AIRCRAFT LOGBOOK Reference Publications: P&M Aviation Service Bulletin 131 Issue 1 Mandatory Permit Directive Page 1 of 2

16 Civil Aviation Authority Mandatory Permit Directive SRG Airworthiness Division Remarks: 1. This MPD was posted on 26 July 2012 as PMPD for consultation until 25 August Enquiries regarding this Mandatory Permit Directive should be referred to: Airworthiness, Evaluation & Surveillance, Civil Aviation Authority, Safety Regulation Group, Aviation House, Gatwick Airport South, West Sussex RH6 0YR. Tel: +44 (0) Fax: +44 (0) Mandatory Permit Directive Page 2 of 2

17 Civil Aviation Authority EMERGENCY MANDATORY PERMIT DIRECTIVE Number: E Issue date: 23 November 2016 In accordance with Article 41(1) of The Air Navigation Order 2016, as amended, the following action required by this Mandatory Permit Directive (MPD) is mandatory for applicable aircraft registered in the United Kingdom operating on a UK CAA Permit to Fly. Type Approval Holder s Name: P&M Aviation Ltd Type/Model Designation(s): Various, see below Title: Manufacturer: Applicability: Clevis Pin / Split Ring Installations Inspection / Replacement P&M Aviation Ltd All Microlights where P & M Aviation Ltd is the Type Approval Holder: TADS No. Aircraft Type TADS No. Aircraft Type BM2 Gemini Sprint BM43 Mainair Mercury BM3 Tri-Flyer Sprint BM44 Pegasus Quasar 2 TC BM4 Gemini Flash BM45 Cyclone AX3//503 BM5 Panther XL-S BM46 Pegasus Quantum 15 (Rotax 2-stroke engines) BM9 Pegasus XL-R BM47 Mainair Blade BM10 Pegasus Flash BM50 Pegasus Quantum BM17 Pegasus Flash 2 BM51 Mainair Blade 912 BM14 Gemini Flash 2 BM53 Cyclone AX2000 BM16 Scorcher BM54 Mainair Rapier BM17 Pegasus Flash 2 BM56 Pegasus Quantum 15-HKS BM23 Gemini Flash 2 Alpha BM60 Mainair Blade 912S BM25 Pegasus XL-Q BM65 Flight Design CT2K (rudder control) BM27 Chaser S BM66 Pegasus Quik BM28 Pegasus Photon BM70 Quik GT450 BM31 Chaser S 1000 BM72 Flight Design CTSW (rudder control) BM33 Chaser S 508 BM77 QuikR BM37 Chaser S 447 BM80 Quik GTR BM38 Pegasus Quasar BM81 PulsR BM42 Pegasus Quasar TC BM83 Flight Design CTSL (rudder control) Mandatory Permit Directive Page 1 of 2

18 Civil Aviation Authority Mandatory Permit Directive SARG Reason: Following maintenance, a clevis pin came out of the RP-4 roll trim system pulley on a QuikR causing a left turn. The split ring securing the clevis pin had come out. It is not known if the ring was disturbed during the maintenance. The split ring which came out was the same spiral start pattern as that which has caused trouble before (see Service Bulletin 139). This pattern of ring has no positive stop, so that simple rotation of the ring (e.g. caused by it getting caught on something) will cause it to disengage. Disengagement of the split ring and subsequent clevis pin departure could affect the control of the aircraft. Effective Date: 24 November 2016 Compliance/Action: Compliance is required as follows, unless previously accomplished: 1. Before further flight, from the effective date of this MPD, inspect all clevis pin / split ring installations on the aircraft in accordance with paragraph 2 of P & M Aviation Ltd Service Bulletin If the inspection in paragraph 1 reveals any spiral start pattern split rings they must be replaced in accordance with paragraph 2 of P & M Aviation Ltd Service Bulletin 144 before further flight. 3. Record the inspection from paragraph 1 and any necessary rectification action from paragraph 2 in the aircraft technical log in accordance with paragraph 3 of P & M Aviation Ltd Service Bulletin Repeat the actions in paragraphs 1, 2 and 3 at each Permit to Fly revalidation. ENSURE COMPLIANCE WITH THIS MPD IS RECORDED IN THE AIRCRAFT LOGBOOK Reference Publications: Remarks: P & M Aviation Ltd Service Bulletin Number 144, Issue 3, dated 27 October This MPD was not posted for consultation because of the urgency of the requirement. 2. Enquiries regarding this Mandatory Permit Directive should be referred to: GA Unit, Civil Aviation Authority, Safety and Airspace Regulation Group, Aviation House, Gatwick Airport South, West Sussex, RH6 0YR. Tel: +44 (0) ga@caa.co.uk Mandatory Permit Directive Page 2 of 2