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CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP MICROLIGHT TYPE APPROVAL DATA SHEET (TADS) NO: BM 10 ISSUE:5 TADS BM 10 issue 5 Page 1 of 12 TYPE: Pegasus Flash (1) MANUFACTURER: Solar Wings Ltd, now supported by P & M Aviation Ltd, Unit B, Crawford St, Rochdale, Lancashire OL16 5NU (2) UK IMPORTER: N/A (3) CERTIFICATION: Section S Issue: Advance Issue March 1983 list of section S Blue papers and additional CAA Requirements Nil (4) DEFINITION OF BASIC STANDARD: Solar Wings Modification No 0002 SW/405/6 (5) COMPLIANCE WITH THE MICROLIGHT DEFINITION (a) MTOW 344kg (b) No. Seats 2 (c) Maximum Wing Loading 22.1kg/m² (d) Vso 28mph CAS (e) Permitted range of pilot weights 55-90 kg per seat. (f) Typical Empty Weight (ZFW) 150Kg (g) ZFW + 172 kg crew + 1 hr fuel (16litres /12kg) 334 kg (h) ZFW + 86 kg pilot + full fuel (24 litres / 17 kg) 253 kg (i) Max ZFW at initial permit issue 160 kg

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CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 1 of 12

TYPE: Pegasus Flash (1) MANUFACTURER:

Solar Wings Ltd, now supported by P & M Aviation Ltd, Unit B, Crawford St, Rochdale, Lancashire OL16 5NU

(2) UK IMPORTER: N/A

(3) CERTIFICATION:

Section S Issue: Advance Issue March 1983 list of section S Blue papers and additional CAA Requirements Nil

(4) DEFINITION OF BASIC STANDARD:

Solar Wings Modification No 0002 SW/405/6

(5) COMPLIANCE WITH THE MICROLIGHT DEFINITION

(a) MTOW 344kg

(b) No. Seats 2

(c) Maximum Wing Loading 22.1kg/m²

(d) Vso 28mph CAS

(e) Permitted range of pilot weights 55-90 kg per seat.

(f) Typical Empty Weight (ZFW) 150Kg

(g) ZFW + 172 kg crew + 1 hr fuel (16litres /12kg)

334 kg

(h) ZFW + 86 kg pilot + full fuel (24 litres / 17 kg)

253 kg

(i) Max ZFW at initial permit issue 160 kg

CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 2 of 12

(6) POWER PLANTS

Designation

Pegasus Flash

Engine Type Rotax 447

Reduction Gear 2.58:1

Exhaust System Rotax

Intake System Rotax intake silencer with K&N

filter

Propeller Type Newton

Propeller Dia x Pitch 62”x 38”

Noise Type Cert No. 19M

AAN approving configuration

19641P

(7) MANDATORY LIMITATIONS:

(A) Max Take-Off Weight

344kg

(B) CG Limits N/A (C) CG datum Front Wheel axle

(see annex C).

(D) Cockpit Loadings

Min

Max

Port 70kg 90kg

Starboard - 90kg

Total 70kg 90kg

(E) Never Exceed Speed 89mph (F) Manoeuvring Speed 89mph (G) Permitted Manoeuvres 30° Nose up / 30° nose down

450 Max bank angle Non Aerobatic Normal acceleration flight limits, +4 / -0g

(H) Fuel Contents (Max Useable) 24 litres

CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 3 of 12

(I) Power Plant See Table

Engine Rotax 447

Max RPM 6800

6500 contin

MAX CHT 2500C

MAX EGT 6500C

Fuel Spec 83 MON or 90 RON minimum unleaded to BS(EN)228 or 97+ octane 4-star /MOGAS leaded fuel to BS 4040, or AVGAS 100LL.

Engine Oil Spec Non-dterg 2 stroke self mix

Gearbox oil spec EP90, AP1-GL3 or higher

Fuel/Oil Mix 50:1

Coolant Temperature N/A

Oil Pressure N/A

Oil Temperature N/A

Fuel Pressure 0.2-0.4 bar

(8) INSTRUMENTS REQUIRED:

ASI

Altimeter RPM CHT / EGT

Compass Coolant temp

Fuel Pressure

VSI Slip ball

Required (to 100

mph min.)

Required (may be

wrist type)

Optional Optional Optional Optional Optional Optional Optional

(9) CONTROL DEFLECTIONS: (trikes) Conditions - trike on level surface Wing At Zero Keel Incidence Roll - ±210

Pitch - 13.5o total from front strut to seat structure.

CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 4 of 12

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

10.1 Manuals approved for use with this aircraft. (a) SW-4060-3 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, fuel types and fuel:oil ratio. An example

is shown at Annex D. If MTOW can be exceeded with full fuel and maximum cockpit weight, the fuel loads at MTOW for fuel capacity in increments of 10 litres intervals down to the maximum fuel load. An example is shown at Annex D.

(d) Switches See Annex D.

CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 5 of 12

(11) MANDATORY MODIFICATIONS / SERVICE BULLETINS / AIRWORTHINESS DIRECTIVES ETC:

a) See Annex A for required modifications.

b) Service Bulletins Bulletin No Title Notes Date 0002 Fuel system cleaning/ inspection Mandatory 06-07-86 0003 Westach instrument wiring Advisory 26-2-87 0004 Throttle stop Advisory 29-4-87 0005 Front fork bolt Advisory 29-4-87 0006 Front forks Advisory 29-4-87 0007 Securing ring on nose pin Advisory 29-4-87 0008 Spark plug caps Advisory 26-2-87 0010 Brake mod 0016, 0017 Advisory 14-4-87 0011 New fuel tank mod. 08, 09 Advisory 14-4-87 0012 Improved fuel system mod 10, 11 Advisory 14-4-87 0014 Improved vent system Compulsory 29/4/87 0015 Exhaust system Advisory 29/4/87 0025 Flight Limitations Mandatory 07-10-89 0029 Tyre Pressures Advisory 20-1-91 0109 Component life extension Advisory 21-3-02

Annual Bettsometer test is to be carried out to 1050 grammes with wing sails fitted and tensioned to flight. Test must be to both upper and lower surfaces.

(12) MINIMUM PERFORMANCE AT MAX TAKE-OFF WEIGHT Rate of Climb: 594 fpm at 40mph IAS. Stall or Minimum Flying Speed: 28mph IAS at MTOW / idle.

CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 6 of 12

Issue History

Issue No. Reason and signatory

1 04/12/85 Initial issue

W A BEVAN

2 28/10/86 W A BEVAN

3 07/02/91 K D RUSSELL

4 31/03/03 New format J BARRATT

5. 06/07/05 New company name J Barratt

CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 7 of 12

Illustration of Aircraft - 3 View – Pegasus Flash (XL-R trike is identical except for the Flash wing adapter ring on the top of the pylon)

CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 8 of 12

CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 9 of 12

CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 10 of 12

ANNEX A – MANDATORY MODIFICATIONS

Mod ref. Description Notes Issued

0018 Fuel tank breather Mandatory 30/3/89

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

SW003 Fitting of Flash 2 wing Optional 28/2/89

SW0016 Fitting of front brake Optional 1/11/88

SW0045 Brake reinforcement To increase life of brake 14/2/90

ANNEX C

WEIGHING INFORMATION

1. The CG of the trike is not critical as it only affects the speed range, not the trim.

2. No significant masses should be attached to the wing.

3. Empty weight of the whole aircraft must not exceed 160kg.

CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 11 of 12

ANNEX D

EXAMPLE PLACARDS

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

(b) Engine Limitations Placard (to be located near to engine instruments) A placard showing the limitations for all indicated engine parameters is to be mounted

close to the engine instruments. This requirement need not be complied with for limitations shown as coloured markers (red for danger, amber for caution) on the instrument displays.

CIVIL AVIATION AUTHORITY – SAFETY REGULATION GROUP

MICROLIGHT TYPE APPROVAL DATA SHEET (TADS)

NO: BM 10 ISSUE:5

TADS BM 10 issue 5 Page 12 of 12

(c)Fuel Limitations Vs Max Cockpit Load Placard (to be visible to the pilot) Only required if max cockpit load, full fuel and ZFW can exceed Max AUW

Empty Wt Kg Date

Fuel Load (litres)

Max Cockpit Wt (kg)

65 55 45 35 25 15 5

(d) Fuel Limitations Placard (to be located near to filler cap) There must also be a fuel cock on/off placard fitted.

FUEL

Capacity 24 Litres (50:1 2 Stroke oil)

83 MON or 90 RON minimum unleaded to BS(EN)228 or 97+ octane 4-star / MOGAS leaded

fuel to BS 4040, or AVGAS 100LL (e) Switches All switches are to be marked with function and sense (up=on, down=off).

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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]

Mandatory Permit Directive 2017-004-E Page 1 of 3

Civil Aviation Authority

EMERGENCY MANDATORY PERMIT DIRECTIVE Number: 2017-004-E Issue date: 15 May 2017

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: Rigging Cables with Roll Swaged End Terminals – Inspection / Replacement

Manufacturer: P&M Aviation Ltd

Applicability: All Microlights of the following types where P & M Aviation Ltd are the Type Approval Holder: TADS No. Aircraft Type BM4 BM10 BM14 BM16 BM17 BM23 BM43

Gemini Flash Pegasus Flash Gemini Flash 2 Scorcher Pegasus Flash 2 Gemini Flash 2 Alpha Mainair Mercury

BM47 Mainair Blade BM51 Mainair Blade 912 BM54 Mainair Rapier BM60 Mainair Blade 912S BM70 Quik GT450 BM77 QuikR BM80 Quik GTR BM81 PulsR

Civil Aviation Authority Mandatory Permit Directive Safety and Airspace Regulation Group

Mandatory Permit Directive 2017-004-E Page 2 of 3

Reason: A P&M Quik GT450 in a flying school had a partial failure of a lower side rigging cable (Part No. YQD-045) when recovering from a spiral manoeuvre, within the limits of the flight envelope. These cables are arranged in pairs, to give a backup load path. The second cable carried the load and the aircraft landed safely. This is the only recorded lower side cable failure since 1984. The partial failure was at the edge of the roll swaged terminal end. The alternative cable terminations using Nicopress sleeves and thimbles allow more progressive flexing of the cable. The incident Quik GT450 lower side rigging cables had been in use for 1050 hours and 9 years. The aircraft had been subject to an accident and rebuilt once in its life. It was also operated quite near the coast where it is probable that sea air chlorides could have affected the material. There were corrosion pits in the S316 stainless steel material which accelerate fatigue failures. CLSCC (Chloride Stress Corrosion Cracking) is known to affect stainless steel. The cable fitting was at the bottom end of the cable, where solutions can wick down it and collect. The strand failures were caused by bending and tensile fatigue because of cracks propagating from scratches and corrosion pits on the surface. All the remaining cables had broken strands at the edge of the roll swaged terminals. Some of these strands had been failed for some time, as shown by discolouration of the failure surfaces. The cable is 7 cores of 7 strands construction. Failure of a lower rigging cable would potentially reduce the integrity of the wing and hazard the aircraft.

Effective Date: 15 May 2017

Civil Aviation Authority Mandatory Permit Directive Safety and Airspace Regulation Group

Mandatory Permit Directive 2017-004-E Page 3 of 3

Compliance/Action: Compliance is required as follows, unless previously accomplished:

1. Before further flight, for lower side, front and rear rigging cables with roll swaged terminal ends with more than 750 flying hours or 7 years of service, whichever comes first, visually inspect at the edge of the roll-swaged terminal(s) using a magnifying glass with a power of at least 3x. Inspect closely for damage i.e. broken strands, corrosion, mechanical damage or slippage. If any damage is found, replace the affected cable before further flight. If no damage is found, replace the cable within 25 flying hours. See paragraphs 1 and 2 of P & M Aviation Ltd Service Bulletin 147 including the warning in paragraph 2.

2. Within 25 flying hours, for lower side, front and rear rigging cables

with roll swaged terminal ends with less than 750 flying hours and less than 7 years of service, visually inspect at the edge of the roll-swaged terminal(s) using a magnifying glass with a power of at least 3x. Inspect closely for damage i.e. broken strands, corrosion, mechanical damage or slippage. If any damage is found, replace the affected cable before further flight. If no damage is found, replace the cable at 750 flying hours or 7 years of service, whichever comes first. See paragraphs 1 and 2 of P & M Aviation Ltd Service Bulletin 147 including the warning in paragraph 2.

3. Removal and replacement of any airframe structural cable requires a duplicate inspection - see paragraph 3 of P & M Aviation Ltd Service Bulletin 147.

4. Record the inspection from paragraph 1 or paragraph 2 and any necessary rectification action in the aircraft technical log in accordance with paragraph 3 of P & M Aviation Ltd Service Bulletin 147.

5. Repeat the inspection in paragraph 2 at each Permit to Fly

revalidation and replace damaged cables as necessary. Replace the cables at 750 flying hours or 7 years of service, whichever comes first.

ENSURE COMPLIANCE WITH THIS MPD IS RECORDED IN THE AIRCRAFT LOGBOOK

Reference Publications:

P & M Aviation Ltd Service Bulletin Number 147 Issue 1 dated 10 May 2017

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]