( 1) MANUF ACTURER : WING: Southdown Sailwings TRIKE:Southdown Sailwings

Transcription

1 MICROLIGHT TYPE ACCEPTANCE DATA SHEET (TADS) NO: BMO-43 ISSUE: 4 TYPE Lightning DSjPuma Puma DS mk1 Lightning DSjPuma 440 ( 1) MANUF ACTURER : WING: Southdown Sailwings TRIKE:Southdown Sailwings (2 ) UK IMPORTER: NjA (3) CERTIFICATIONBASIS: Type Acceptance to BCAR section S advance issue 1983 selected paragraphs according to CAA letter ref 9j30jUL18 (type acceptance). (4) DEFINITION OF BASIC STANDARDS: See MAAN 1184 issue 2 (5) DIMENSIONSjWEIGHT FOR COMPLIANCEWITH MICROLIGHT DEFINITION (a) Wing area 0» (c).,span 'Standard mean chord (d) Dry empty weight (e) Max takeoff weight (f) Empty wing loading (g) Wing loading at Max weight 18.5 sq.m 10.8 m l.71m 145 kg 334 kg 8 kgjsqm 18 kg/sqm (6) POWER PLANTS DSjPuma DSjPuma DSjPuma DSjPuma DSjPuma Designation Fujii Fuji Fuji Robin Fuji Fuji Engine Type Robin Robin EC44PM Robin Robin EC44PM EC44PM EC44PM EC44PM Jj Reduction Tooth Tooth Tooth Belt Belt Belt Gear Belt Belt 2.67:1 2.85:1 2.8:1 3.2:1 2.77:1 Exhaust Nicklow Rotaflow Nicklow Nicklow Nicklow System Intake System None Propeller Nicklow Romain wood wood wood Type or Romain Propeller Dia 62"x32" 62"x27" 60"x32" 60"x36" 62"x28" x Pitch Noise Type 1M issue 1M issue 1M issue 4 23M issue 1M issue Cert No Page 1 of 5

2 MICROLIGHT TYPE ACCEPTANCE DATA SHEET (TADS) ( 6) POWER PLANTS (Cont'd) DSjPuma Designation 440 Engine Type Reduction Gear Fuji Robin EC44PH Tooth Belt 2.7:1 Exhaust Nicklow System Intake System None Propeller Type r '. Propeller Dia x Pitch Wood 59"x27" Noise Type 1M issue Cert No. 4. ~ Page 2 of 5

3 MICROLIGHT TYPE ACCEPTANCE DATA SHEET (TAOS) (7) MANDATORY LIMITATIONS: Note: Items marked "." below MUST be placarded in clear view of the pilot. ( A) Max Take-off Weight:. 334kg' (B) (C) (D) C G Limits (3-Axis Aircraft): C G Datum Cockpit Loadings: * Pront Rea r 1Jtal. Pilot and Baggage or Ballast (Min) * 55kg 0 55kg Pilot and Baggage (Max) * 80kg 80kg 160kg (E) Permanent Ballast, Weight and Position: None ( P) f '. Empty C of G (3-Axis Aircraft): (G) ',Never Exceed Speed: * 63 mph (H) Manoeuvring Speed: * 50 mph ( I ) (J) Permitted Manoeuvres: * Non-aerobatic less than +-45 degrees (pitch) and 60 degrees bank. Fuel Contents (Max Useable): * 24 Ii tres. ( K) Power Plant: See Table Engine Fuji Robin EC44PM Max RPM 7000 MAX CHT 250 C Fuel Spec Four star or premium unleaded MOGAS Oil Spec Se If mix 2 stroke. Fuel/Oil 40:1 Mix Max EGT -.\ Oil Press n/a Oil Temp nla Page 3 of 5

4 MICROLIGHT TYPE ACCEPTANCE DATA SHEET (TAOS) (8) INSTRUMENTSREQUIRED FOR TYPE ACCEPTANCE: ASI Altimeter RPH CHT yes can be on pilots no no wrist (9) CONTROLDEFLEECTlONS (3-Axis Systems): Compass no EGT no Pitch Control Up:- Down:- Tailplane Trim Up:- Down:- Ailerons Up:- Down: '- Rudder Left: - Right:- Steering Left: - Right:- I " Spoile-rs (10) PILOT'S NOTES, MAINTENANCEMANUALSREFERENCES:. Southdown sailwings Puma DS owners manual. (11 ) MANDATORYHODIFICATIONS/SERVICE BULLETINS/AIRWORTHINESS DIRECTIVES ECT: 11.1 The aircraft must be inspected to comply with the requirements of TSOOI issue 3 and WSOOI issue In particular, the hollow reduction drive shaft in a Nicklow reduction drive must be replaced with a shaft of at least EN15T, EN24T or S96 specification. The shaft must be stamped with a "T" or "S96" on the end to signify the modification has ]ji'een incorporated. The aircraft technical log must be signed off when an inspector is satisfied this modification is complied with, and that the drive is correctly reassembled The wing trailing edge can approach the propeller in downwind taxa si tuations despite a static clearance of over 200mm. In order to prevent possible propeller Isail contact, two addit ional reflex lines of 2. 5mmdiameter 7x7 galvanised or stainless cable with the appropriat~ swages and thimbles must be fitted. The two separate reflex cables must be fitted to the trailing edge at the two inboard unsupported battens, running up to the steel reflex line bracket at the top of the kingpost. The means of attachment to the sail trailing edge should be the same as that used on the existing reflex cables. The additional reflex cable tension should be set so they are just tight in the static condition with the sail unloaded. This setting should ensure that: a) the propeller/sail clearance cannot drop significantly below the static measurement. b) The reflex lines are slack in flight. Page 4 of 5

5 MICROLIGHT TYPE ACCEPTANCE DATA SHEET (TADS) Thew1ng cross-boom pull back cables must be 1nspected at least anually for fraying where they pass the kingpost, and where thay meet the crossboom swage. The cable assembly should be replaced every 200 hours The lower side rigging cables should be of twin 3mm7x7 Galvanised steel or stainless steel All crossboom p1vot bolts must be 5/1611 BSF A102 (5154 or 596 material) aircraft quality bolts fitted head uppermost. The crossboomjleading edge bolts must not be overt ightened, so as to allow~ some misalignment without bolt bending. (12) MINIMUM PERFORMANCEAT MAX TAKE-OFF WEIGHT r " Rate of Climb: 330 fpm at 35mph. Stall ing Speed: 28mph. * NOTE Wrist Altimeter permitted provided that - (a) (b) A cockpit placard states, "WRIST ALTIMETERMANDATORY" and A wr1st alt1meter 1s part of the a1rcraft equipment. Issue Issue Issue 2 Additional powerplant data 3 Addition of reflex line modification, cross boom bolt inspection and weight increase from 322 to 334 kg :1 reduction gear and 59" x 2711 prop. variant added. Signed,~ WL. S..J,. W.G.Brooks Chief Technical Officer 3 July 1996 Page 5 of 5

6 United Kingdom Civil Aviation Authority T~ f ~\~\.f ~ fo (t~) MicrolightAeropla'ne~oTseCertificate No :?~ Registration Marks 2 Constructor and Constructor's Type and Model Designation of Aeroplane G-MJRT Southdown Sail wings (' Puma DS 3 Engine Type Designation 4 Propeller Type Designation Fuji Robin Ec44PM inverted with 2.7:1 reduction gear r '" 59" diameter 27" pitch 5 Exhaust Muffler Description Nicklow exhaust muffler I.! Th -,. " h I f h N. T C. f ' N 1M issue 4 ISmicro Ig t aerop ane con orms Wit olse ype ertl Icate o. """""""""""""""""""""""""""" This Microlight Noise Certificate is issued pursuant to the Air Navigation (Noise Certification) Order 1984, in respect of the above-mentioned aeroplane, which is considered to comply with the relevant noise requirements of BCAR Section N. '" Date ~.~ """"""""""""""""""""""""""""""""... January 1988 ~~ "..fvt2.r1 for the Civil Aviation Authority CA I~~