TYPE: Pegasus Quasar (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: BCAR Section S - Advance Issue March 1983 amended 11/10/88 (4) DEFINITION OF BASIC STANDARD: Solar WIngs Approval Submission - Document Ref No. Sw-405-32 (5) COMPLIANCE WITH THE MICROLIGHT DEFINITION (a) MTOW 382kg (b) No. Seats 2 (c) Maximum Wing Loading 25kg/m² (d) Vso 26mph CAS (e) Permitted range of pilot weights 55 90 kg per seat. (f) Typical Empty Weight (ZFW) 173 kg (g) ZFW + 172 kg crew + 1 hr fuel 357 Kg (17litres /12 kg) (h) ZFW + 86 kg pilot + full fuel 289kg (42 litres / 30kg) (i) Max ZFW at initial permit issue 180kg TADS BM38 issue 3 Page 1 of 10
(6) POWER PLANTS Designation Engine Type Reduction Gear Exhaust System Intake System Propeller Type Propeller Dia x Pitch Noise Type Cert No. Quasar Rotax 503-1V Upright (single ign.) Rotax Gearbox 2:58:1 Rotax Side Mounted (with after muffler) Rotax intake silencer with K & N Intake Filter Arplast 162 162 cm Dia Settable Pitch 14 at 53.5 cm 126M Iss 3 AAN approving configuration 21604P (7) MANDATORY LIMITATIONS: (A) Max Take-Off Weight (B) CG Limits (C) CG datum (D) Cockpit Loadings 382kg N/A Front Wheel Axle Port Starboard Total Min 55kg - 55kg Max 90kg 90kg 180kg (E) Never Exceed Speed (F) Manoeuvring Speed (G) Permitted Manoeuvres (H) Fuel Contents (Max Useable) 82mph 60mph Max 30 Nose up / 30 nose down Non Aerobatic, max 60 bank Normal acceleration flight limits, +4 / -0g 42 L TADS BM38 issue 3 Page 2 of 10
(I) Power Plant See Table Rotax 503- Engine 1V 6800 Max RPM 6500 Cont MAX CHT 250 C MAX EGT 650 C Fuel Spec Engine Oil Spec Gearbox oil spec Fuel/Oil Mix Coolant Temperature Oil Pressure Oil Temperature Fuel Pressure 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. Non Deterg 2 Stroke Self Mix EP 90 50:1 N/A N/A N/A 0.2-0.4 bar (8) INSTRUMENTS REQUIRED: ASI Altimeter RPM CHT / Compass Coolant Fuel VSI Slip ball EGT temp Pressure Required (to 100mph min.) Required Optional Optional Optional Optional Optional Optional N/A TADS BM38 issue 3 Page 3 of 10
(9) CONTROL DEFLECTIONS: N/A Weightshift flexwing, control movements limited by main structure. (10) PILOT'S NOTES, MAINTENANCE MANUALS REFERENCES: 10.1 Manuals approved for use with this aircraft. (a) Document Ref SW-406-12 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 type(s) and fuel:oil ratio. An example is shown at Annex D. (d) Switches See Annex D. TADS BM38 issue 3 Page 4 of 10
(10) MANDATORY MODIFICATIONS / SERVICE BULLETINS / AIRWORTHINESS DIRECTIVES ETC: Service Bulletin ref. Description Notes Issued SB0027 Fuel tank seal Compulsory 9/9/89 SB0028 Undercarriage strut preload Compulsory 10/1/91 SB0031 Conversion of Quasar to Quasar Optional 15/11/91 TC SB0032 Inspection of T.E. root MANDATORY 22/8/91 SB0036 New Pylon Fairing fitting Optional 18/5/92 SB0039 Brake cables MANDATORY 26/3/93 SB 0086 Inspection of swages Compulsory 20/05/97 SB0090 Roll bearing bolt security Advisory 17/09/97 SB0091 Roll bearing flange cracking Advisory 06/04/98 SB0095 Seat belt buckle on s/n 7428- Advisory 30/07/98 7456 SB0109 Component life extension Advisory 21/3/02 See Annex A for required modifications. Annual Bettsometer test is to be carried out to 1360 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: Climb Speed: Stall or Minimum Flying Speed: 500 ft/min (Rotax 503-2v engine) 46 mph (40 kts, 74 kph) IAS 26 mph (23 kts 42 kph) IAS MaxTOW at idle TADS BM38 issue 3 Page 5 of 10
Issue History Issue No Date. Reason and signatory 1 May 1990 J. Watkins 2 1 April 2003 New format J BARRATT 3 06/07/05 New company name J Barratt TADS BM38 issue 3 Page 6 of 10
Illustration of Aircraft - 3 View TADS BM38 issue 3 Page 7 of 10
ANNEX A MANDATORY MODIFICATIONS 1. Mod ref. Description Notes Issued SW0067 PICKUP PLATE AND FUEL DRAIN MINOR 11/12/90 SW0082 Q1 WING, QUASAR, SAIL T/E PATCH MINOR 05/09/91 SW0084 Q1 WING, QUASAR SAIL T/E ANTI ABRASION PATCH MINOR 05/09/91 ANNEX B - APPROVED 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. 1. Mod ref. Description Notes Issued SW0068 TWIN CARB R503 BOSCH SINGLE IGNITION MAJOR SW0069 TWIN CARB R503 DUCATI DUAL IGNITION MAJOR SW0070 PRELOAD SPACERS IN REAR U/C MINOR COMPULSORY SW0071 THROTTLE FOR ALL TYPES (HAND THROTTLE) FROM 20/01/91 MINOR SW0074 CARB. HEAT PLATE KIT MINOR SW0075 SW0076 SW0080 Q-WING, QUASAR WING EXTERNAL BUNGEE RETRACT SYSTEM SPLIT REAR WIRE SYSTEM TO LIGHTEN ROLL SPECIFICATION OF AEROQUIP 2556-4 FUEL HOSE MINOR MINOR MINOR 20/12/90 20/12/90 17/04/91 17/04/91 17/04/91 17/04/91 15/07/92 05/09/91 TADS BM38 issue 3 Page 8 of 10
SW0081 CONVERSION OF QUASAR TO QUASAR TC MINOR 05/09/91 SW0091 NEW PYLON FAIRING (SEE SB 0036) MINOR 15/07/92 SW0096 IMPROVED FRONT WHEEL & AXLE MINOR 15/07/92 SYSTEM SW0097 NEW COCKPIT TOP MOULDING WITH MINOR 15/07/92 SCREEN AND COMPASS SW0099 FITTING OF PRIMER BULB IN LINE MINOR 15/07/92 (Note see SB 110 possible blockage) PG28 QUASAR U/C LEG MATERIAL CHANGE MINOR 10.1.95 PG54 QTM/QSR SEAT CUSHION ADJUSTMENT MINOR 16.11.95 PG73 BRONZE WELD -> TIG WELD ON QTM/QSR MINOR 10.5.96 FORK LINKS PG92 Q2 SAIL TAPING & NEW SEAM LAYOUT MINOR 10.5.96 PG124 Q WING 10mm WING BOLTS MINOR 22.5.97 AX/PG126 ALL 12V AIRCRAFT BSM INDICATOR MINOR 28.5.97 AX/PG127 BRAKE RETURN SPRING ADDED MINOR 28.5.97 PG151 QTM/QSR LTS FUEL GAUGE MINOR 5.2.98 PG177 LTS FUEL GAUGE FOR PRODUCTION MINOR 8.6.98 PG/AX252 LYNX KIT FITTING MINOR 7.1.99 PG254 QUASAR SUSPENSION RUBBER MATERIAL MINOR 15.1.99 PG/AX279 NON PVC FUEL HOSES MINOR 9.3.99 PG287 USE Q2 CROSS BOOM ON Q1 WINGS MINOR 28.4.99 PG323 QUASAR UNDERCARRIAGE LAYUP MINOR 14.12.99 PG353 FITTING OF NOSE WEBBING ONTO Q1 MINOR 14.12.99 WING TADS BM38 issue 3 Page 9 of 10
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. Empty weight of the whole aircraft must not exceed 180kg. ANNEX D EXAMPLE PLACARDS TADS BM38 issue 3 Page 10 of 10
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Civil Aviation Authority EMERGENCY MANDATORY PERMIT DIRECTIVE Number: 2016-008-E Issue date: 3 October 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 Title: Type/Model Designation(s): Pegasus XL-Q variants, Pegasus Quasar variants, Pegasus Quantum variants, Pegasus Quik, Quik, Quik GT450, Quik Lite, Gemini Flash IIA, Mainair Blade variants Wing Luff Line Attachment Webbing Inspection Manufacturer: Applicability: Reason: P&M Aviation Ltd Pegasus XL-Q variants, Pegasus Quasar variants, Pegasus Quantum variants, Pegasus Quik, Quik, Quik GT450, Quik Lite, Gemini Flash IIA, Mainair Blade variants. The port inner luff line attachment webbing failed on a GT450 wing with 620 hours airtime during taxiing. The polyester webbing loop had chafed against the chrome plated brass eyelet. The webbing wear was visible from the top side, but not from the underside of the sail. A detached luff line is hazardous as it may go into the propeller. Pitch stability in a steep dive or in turbulence would also be compromised. It appears that the eyeleting process has been forming a ridge inside it capable of damaging the webbing. New tooling has been introduced at the Factory to prevent recurrence of the problem. Effective Date: 3 October 2016 Compliance/Action: Compliance is required as follows, unless previously accomplished: 1. Before further flight, inspect the luff line attachment webbings in accordance with paragraph 2.1 of P & M Aviation Ltd Service Bulletin 142. If there is no sign of damage to the webbing, the aircraft may continue in service. 2. Before further flight, inspect the luff line attachment webbings in accordance with paragraph 2.1 of P & M Aviation Ltd Service Bulletin 142. If there is no sign of damage to the webbing, the aircraft may continue in service. Mandatory Permit Directive 2016-008-E Page 1 of 2
Civil Aviation Authority Mandatory Permit Directive SARG Airworthiness Compliance/Action Cont: 3. If the inspection in paragraph 1 reveals damage to the webbing, it must be replaced or a back up load path installed in accordance with paragraph 2.3 of P & M Aviation Ltd Service Bulletin 142 before further flight. 4. 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 142. 5. Repeat the actions in paragraphs 1 and 2 at 50 flight hour intervals. ENSURE COMPLIANCE WITH THIS MPD IS RECORDED IN THE AIRCRAFT LOGBOOK Reference Publications: P & M Aviation Ltd Service Bulletin Number 142 Issue 4 dated 23 September 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: ga@caa.co.uk Mandatory Permit Directive 2016-008-E Page 2 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: 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 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) Mandatory Permit Directive 2016-011 Page 1 of 2
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 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: Remarks: P & M Aviation Ltd Service Bulletin Number 144, Issue 3, dated 27 October 2016. 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: ga@caa.co.uk Mandatory Permit Directive 2016-011 Page 2 of 2