flight design ctsl - british microlight aircraft association · 95 ron minimum unleaded to bs(en)...

CIVIL AVIATION AUTHORITY – SAFETY AND AIRSPACE REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM-83 ISSUE: 1

TADS BM-83 Issue 1 1 of 12

TYPE: Flight Design CTSL

(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 6, CS-VLA Parts C & D

(4) DEFINITION OF BASIC STANDARD:

AE 0110 0001, revision 0, dated 25-Mar-14

(5) COMPLIANCE WITH THE MICROLIGHT DEFINITION:

(a) MTOW 472.5 kg

(b) No. Seats 2

(c) Maximum Wing Loading 47.2 kg/m²

(d) Vso 34 kt CAS

(e) Permitted range of pilot weights 55 – 100 kg per seat 180 kg total

(f) Typical Empty Weight (ZFW) 288 kg

(g) ZFW + 172 kg crew + 1 hr fuel (14 litres / 10 kg)

469 kg

(h) ZFW + 86 kg pilot + full fuel (62 litres / 44.6 kg)

467.6kg

(i) Max ZFW at initial permit issue 291 kg



NO: BM-83 ISSUE: 1


(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 Neuform Novaprop TXR2 Warp Drive 3 bladed carbon composite

Propeller Dia x Pitch 1660mm x 21o at blade undersurface at 75% radius

1676mm x 19o at blade undersurface at tip

Noise Type Cert No. 174M issue 1 174M issue 2

AAN approving configuration BMAA-1068 issue 2 BMAA-1068 issue 2

(7) MANDATORY LIMITATIONS:

(a) Max Take-Off Weight 472.5kg ( nb mandatory parachute fit)

(b) CG Limits Aft limit FWD Limit

450mm aft of datum (38% mac) 271mm aft of datum (23% mac)

(c) CG datum Leading edge at any point of span

(d) Cockpit Loadings Min Max

Port 0kg 100kg

Starboard 0kg 100kg

Total 55kg 180kg

(e) Never Exceed Speed 150 kt

(f) Manoeuvring Speed Va 89 kt

(g) Max speed for full flap Vf 66 kt

(h) Max rough air speed Vc 118 kt

(i) Permitted Manoeuvres Non Aerobatic Normal acceleration limits, +3.8 -1.5g

(j) Fuel Contents (Max Usable) 130 ltr



NO: BM-83 ISSUE: 1


(I) Power Plant See Table

Engine Rotax 912 ULS

Max RPM 5800 (5min) 4400 (Continuous)

MAX CHT 135oC

MAX EGT 880oC

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 Integral supply with engine

Cylinder Head Temperature 135o C

Coolant Temperature 50 – 135o C (100% Glycol) 50 – 120oC ( 50% ethylene glycol/water)

Oil Pressure Normal 2-5 bar above 3,500 rpm Min 0.8bar at idle

Max 7bar

Oil Temperature 50 – 130o C

Fuel Pressure 0.15 – 0.4 bar

(8) INSTRUMENTS REQUIRED:

ASI Altimeter RPM CHT Coolant Oil press/temp Slip ball Compass

Yes (32-160kt)

Yes Yes Yes Yes if water in coolant

Yes Recommended Recommended



NO: BM-83 ISSUE: 1


(9) CONTROL DEFLECTIONS:

Control Surface Datum Deflection

Ailerons Neutral, measure from flap T.E ,flaps up Up 27o Down 12o +-2 o

Flaps Fuselage fairing trailing edge Flaps fully up = -12o +- 2 o Flaps 0 (takeoff) = 00 +-2 o Flaps fully down = 350 +-2 o

Stabilator Fairing on fuselage align With stabilator

Up 13.5 o +-2 o Down 9 o +-2 o

Trim tab With stabilator full up And trim full down With stabilator full down And trim full up

45mm +-5mm 45mm +-5mm

Rudder Rudder horn aligned with fin, apply full pedal deflection

Left 140mm ±11mm, Right 140mm ±11mm

(10) PILOT'S NOTES, MAINTENANCE MANUALS REFERENCES:

10.1 Manuals approved for use with this aircraft (a) P&M Aviation Ltd manual ref : CTSL Man current issue (b) Rotax 912 engine (all versions) operators manual current issue



NO: BM-83 ISSUE: 1


10.2 The following placards are to be fitted (see manual for full set)

Main Placard, LH window pillar by pilot’s head:

On main panel: At each filler cap:

LIMITATIONS: CTSL

P&M SERIAL NO EMPTY WEIGHT (MAX EMPTY WEIGHT 291.5KG) MAX AUW 472.5KG

TOTAL LOAD FUEL 55- KG 130L(FULL) KG 72L KG 31L 172 KG 13L

Vso FLAPS 35O 34KT VS1 FLAPS –12O 48KT VFe MAX FLAPS 66KT Va MANOEUVRE 89KT Vc CRUISE 118KT Vne 150KT MAX CONTIN RPM 4400 OIL PRESS (3500+ rpm) 2-5BAR OIL TEMP MAX 130OC CHT MAX 135 OC COOLANT (WATER/GLYCOL) 120 OC COOLANT (100% GLYCOL) 135 OC NON-AEROBATIC, NO INTENTIONAL SPINS. MANOEUVRE LIMITS +3.8G, -1.5G



NO: BM-83 ISSUE: 1


At cowl hatch: At baggage door:

At throttle control console:



NO: BM-83 ISSUE: 1


Flap, magnetos, fuel valve and circuit breakers on main panel lower section:

Adjacent to parachute handle between seats:

WARNING – EMERGENCY PARACHUTE REMOVE PIN BEFORE FLIGHT.

1) TURN IGNITION OFF 2) PULL HANDLE



NO: BM-83 ISSUE: 1


On fuselage top, behind wing on the parachute panel:



NO: BM-83 ISSUE: 1


(11) MANDATORY MODIFICATIONS / SERVICE BULLETINS / AIRWORTHINESS DIRECTIVES ETC: Nil (12) MINIMUM PERFORMANCE AT MAX TAKE-OFF WEIGHT

Rate of Climb: 1000 fpm at 60kt IAS Stall or Minimum Flying Speed: 34kt IAS at MTOW / idle



NO: BM-83 ISSUE: 1


Issue History

Issue No. Reason and signatory

1 05 Jan 2015 Initial Issue A C Love



NO: BM-83 ISSUE: 1


ANNEX A – MANDATORY MODIFICATIONS

None

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

BMAA AAN 1018 Manual trim option As per CTSW 22/06/06

ANNEX C - WEIGHING INFORMATION

1. CG Datum: Leading edge of wing at any point (except stall strips)

2. Weighing attitude: Fuselage cockpit tunnel horizontal

3. Mainwheel moment arm: 584 mm aft of datum

4. Nosewheel moment arm: -883 mm fwd of datum

5. Fuel moment arm: 210 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 180kg

9. Aft CG Limit: 450mm aft of datum (38% MAC)

10. Fwd CG Limit: 271mm aft of datum (23% MAC)



NO: BM-83 ISSUE: 1


ANNEX D - GENERAL ARRANGEMENT DRAWING

EXAMPLE PLACARDS

Mandatory Permit Directive 2016-011 Page 1 of 2

Civil Aviation Authority

EMERGENCY MANDATORY PERMIT DIRECTIVE Number: 2016-011-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: Clevis Pin / Split Ring Installations – Inspection / Replacement

Manufacturer: P&M Aviation Ltd

Applicability: 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 15-912 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)

Civil Aviation Authority Mandatory Permit Directive SARG

Mandatory Permit Directive 2016-011 Page 2 of 2

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 144.

2. 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 144.

4. 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:

P & M Aviation Ltd Service Bulletin Number 144, Issue 3, dated 27 October 2016.

Remarks: 1. 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)1293 573988 E-mail: [email protected]

flight design ctsl - british microlight aircraft association · 95 ron minimum unleaded to bs(en)...

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