TCDS A73EU

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A73EU Revision 7 Slingsby Aviation Ltd T67M260 T67M260-T3A March 27, 2007 TYPE CERTIFICATE DATA SHEET No. A73EU This data sheet, which is part of Type Certificate No. A73EU, prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder. Slingsby Aviation Ltd. Ki rkbymoorside YOR K Y O6 6EZ EN GLAND I. Model T67M260 - 2PLCM (Acrobatic Category) - Approved December 15, 1993. Engine. Tex tron Lycoming AEIO-540-D4A5. Fuel. A vgas 100LL Engine Limits. For all operations 2700 rpm (260 hp) Propeller. H offman HO-V123K-KV/180DT Spi nner T67G-50-401 Diameter 70.9 in. (No further reduction permitted) Pitch setting at 75% radius: Low 10°, 40', ±10' High 30°, 45', ±20' Governor. W oodward C210988 Airspeed Limits (KIAS). VNE (Never exceed) 195 V NO (Max structural cruising) 156 V A (Maneuvering) 140 V FE (Flaps extended 18º) 120 V FE (Flaps extended 40º) 98 C.G. Range. Ins aft of datum: Forward Limit: (+28.0) at 2175 lb or less ( +30.8) at 2550 lb St raight line variation between these points PAGE NO. 1 2 3 4 5 6 7 8 8 8 REV. NO. 7 3 3 7 7 4 4 4 5 6 A73EU Page 2 of 8 I. Model T67M260 (cont’d) Aft Limit: (+32.5) at 2430 lb or less ( + 3 2 . 4 ) a t 2 5 5 0 l b Straight line variation between these points Datum. Forward Face of Frame 1 Leveling Means. Fore and Aft - Fuselage incidence board T67B-88-307 L a t e r a l - T o p o f F r a m e 4 Empty Weight C.G. Range. None Maximum Weight. 2550 lb Number of Seats. 2 (See Flight Manual for Weight and Balance) Maximum Baggage. 66 lb (+72.3) Fuel Capacity. 42.54 US Gals in two 21.27 US Gal Tanks in Wing (+29.1). 41.54 US Gals usable. See Note 1 for Volume of unusable fuel. Oil Capacity. 1 2 U S Q u a r t s ( - 2 4 ) 6 US Quarts minimum permissible. Control Surface Movements. Wing Flaps: Up 0 T a k e o f f 1 8 º , + 1 °,−2° L a n d 4 0 º , + 1 °,−3° A i l e r o n s : U p 1 4 º , ±1° Down 11.75º, ±1° E l e v a t o r s : U p 2 2 º , ±1° Down 20º, ±1° Elevator Trim Tab Up 19º min Down 31º, +2 °,−1° R u d d e r : L e f t 3 0 º , + 1 ° Right 30º, +1 ° II. Model T67M260-T3A - 2PLCM (Acrobatic Category) - Approved December 15, 1993. (Military use only) Engine. Textron Lycoming AEIO-540-D4A5. Fuel. A v g a s 1 0 0 L L Engine Limits. For all operations 2700 rpm (260 hp) Propeller. Hoffman HO-V123K-KV/180DT Spinner T67G-50-401 Diameter 70.9 in. (No further reduction permitted) Pitch setting at 75% radius: Low 10°, 40', ±10' High 30°, 45', ±20' Governor. Woodward C210988 A73EU Page 3 of 8 II. Model T67M260-T3A (cont’d) Airspeed Limits (KIAS). V NE (Never exceed) 195 V NO (Max structural cruising) 156 V A (Maneuvering) 140 V FE (Flaps extended 18º) 120 V FE (Flaps extended 40º) 98 C.G. Range. Ins aft of datum: Forward Limit: (+28.0) at 2175 lb or less ( + 3 0 . 8 ) a t 2 5 5 0 l b Straight line variation between these points Aft Limit: (+32.5) at 2430 lb or less ( + 3 2 . 4 ) a t 2 5 5 0 l b Straight line variation between these points Datum. Forward Face of Frame 1 Leveling Means. Fore and Aft - Fuselage incidence board T67B-88-307 L a t e r a l - T o p o f F r a m e 4 Empty Weight C.G. Range. None Maximum Weight. 2550 lb Number of Seats. 2 (See Flight Manual for Weight and Balance) Maximum Baggage. 66 lb (+72.3) Fuel Capacity. 42.54 US Gals in two 21.27 US Gal Tanks in Wing (+29.1). 41.54 US Gals usable. See Note 1 for Volume of unusable fuel. Oil Capacity. 1 2 U S Q u a r t s ( - 2 4 ) 6 US Quarts minimum permissible. Control Surface Movements. Wing Flaps: Up 0 T a k e o f f 1 8 º , + 1 °,−2° L a n d 4 0 º , + 1 °,−3° A i l e r o n s : U p 1 4 º , ±1° Down 11.75º, ±1° E l e v a t o r s : U p 2 2 º , ±1° Down 20º, ±1° Elevator Trim Tab Up 19º min Down 31º, +2 °,−1° R u d d e r : L e f t 3 0 º , + 1 ° Right 30º,+1 ° Certification Basis 1. 14 CFR Section 21.29 and 14 CFR Part 23, effective February (T67M260) 1, 1965, including Amendments 23-1 through 23-42. 2. Special Condition: "Evaluation of Composite Structure" (Docket No. 088 CE, Special Condition 23-ACE-57) published in the Federal Register on 12 August 1992 and effective 11 September 1992. A73EU Page 4 of 8 3. 14 CFR Part 36, effec tive 1 December 1969, including Amendments 36-1 through Amendment 20. 4. Equivalent Safety Finding. In respect of FAR 23.777(c)(4), “Power Lever Finding,” No. 92-2, issued by Small Airplane Directorate, ACE-100 on 14 April 1992, found that the location of the powerplant controls in the cockpit provided equivalent safety. Certification Basis 1. 14 CFR Section 21.29 and 14 CFR Part 23, effective February (T67M260-T3A) 1, 1965 including Amendments 23-1 through 23-42, except Section 23.562. 2. Special Condition: "Evaluation of Composite Structure" (Docket No. 088 CE, Special Condition 23-ACE-57) published in the Federal Register on 12 August 1992 and effective 11 September 1992. 3. 14 CFR Part 36, effec tive 1 December 1969, including Amendments 36-1 through Amendment 20. 4. Equivalent Safety Finding. In respect of FAR 23.777(c)(4), “Power Lever Finding,” No. 92-2 issued by Small Airplane Directorate, ACE-100 on 14 April 1992, found that the location of the powerplant controls in the cockpit provided equivalent safety. The United Kingdom CAA originally type certificated this aircraft under is type certificate Number BA17. The FAA validated this product under U.S. Type Certificate number A73EU. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of the United Kingdom CAA. Type Certificate. Type Certificate A73EU was issued pursuant to FAR 21.29 in validation of a United Kingdom Civil Aviation Authority Certification of compliance with the aforem entioned certification basis, and in accordance with the standard airw orthiness certificate provisions of F A R 2 1 . 1 8 3 ( c ) . Serial Nos. Eligible. The United Kingdom Certificate of Airworthiness for Export issued to aircraft manufactured at Kirkbymoorside in the United Kingdom and endorsed as noted under "Import Requirements", must be submitted for each individual aircraft for which application of certification is made. Serial Nos. for production of the T67M260 Model have not been identified. Serial numbers must be identified prior to production. All Mandatory Service Bulletins and UK CAA AD’s must be incorporated for import into the United States prior to issuance of an Export Certificate . of Airworthiness. A civilian version of the Airplane Flight manual must be FAA approved. Slingsby T67M260-T3A airplane models completely manufactured in the United Kingdom have the following serial numbers: No. 2109 and 2110. (Used by U.S. Air Force only) Airplanes assembled by Northrop Worldwide Aircraft Services Inc, in A73EU Page 5 of 8 accordance Licensing Agreement SAL/NWASI, dated 8 February 1994 and under FAA Production Certificate No. PC9SW. These airplanes have the following serial numbers: No. 2123 thru 2233. (Used by U.S. Air Force only) Additional numbers may be added by petition submitted by the Type Certificate holder. Import Requirements. A United States Airworthiness Cer tificate may be issued on the basis of United Kingdom Certificate of Airworthiness for Export signed by a representative of the United Kingdom Civil Aviation Authority on behalf of the European Community containing the following statement; "The airplane covered by this certificate has been examined, tested and found to conform to the 14 CFR Part 23 type design approved under U.S. Type Certificate A73EU and is to be in a condition for safe operation". Any imported aircraft must also meet the requirements of Note 10 of this Type Certificate Data Sheet. Service Information. Service bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals, which contain a statement that the document is CAA approved, or CAA approved through the Manufacturers CAA Approval Ref. DAI 2243/46, is accepted by the FAA and are considered FAA approved. These approvals pertain to the type design only. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or – for approvals made before September 28, 2003 – by the United Kingdom CAA. • Service bulletins, • Structural repair manuals, • Vender manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such document s and considers the FAA-approved unless on of the following conditions exits: • The documents change the limitations, performance, or procedures of the FAA approved manuals: or • The documents make an acoustical or emissions change to this product’s U. S. type certificate as defined in 14 CFR 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case-by-case to EASEA to approve on Behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. Equipment. The basic equipment prescribed in the applicable airworthiness (All Models) requirements (See Certificatio n Basis) must be installed in the aircraft for airworthiness certification. Th is equipment must include Airplane Flight Manual T.O. 1T-3A-1 dated 9 December 1993 or later CAA approved revision. The equipment required to be fitted and functioning for a particular flight is stated in the Minimum Equipment List, T67G-900-014 Issue 4, dated 24 March 1995, or later CAA A73EU Page 6 of 8 approved revision. NOTES Pertain to all models unless otherwise specified NOTE 1. Current weight and balance report, including list of equipment included in certificated empty weight and loading instructions when necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and correspo nding center of gravity location must include unusable fuel of 1.0 US Gallon (+29.1) and full oil of 12 US Quarts (-24). NOTE 2. The following placards must be displayed in full view of the pilot: "THIS AIRPLANE MUST BE OPERATED AS AN ACROBATIC CATEGORY AIRPLANE IN COMPLIANCE WITH THE APPROVED AIRPLANE FLIGHT MANUAL." All markings and placards required in the approved Airplane Flight Manual must be installed in the appropriate locations. Each individual airplane will be supplied with placards that specifies the kind of operation such as VFR, IFR, day or night, to which the operation of the airplane is limited by the equipment installed. NOTE 3. Airplane is limited to 18,000 flight hours. The temperature of the structure for operations must not exceed 122 °F (50°C) for aerobatic flight and 131°F (55°C) for all other flights. Additional Instructions for Continued Airworthiness and Service Life Limits of components are contained in the Maintenance Schedule T67M260/MS, dated October 9, 1993. Revisions to Airworthiness Limitations must be FAA approved or CAA approved for the FAA. NOTE 4. Paint specification. Paints containing UV protection must be used for repairs. The recommended paint specification is white polyurethane FE102. NOTE 5. Paint schemes. Restrictions on paint sc hemes which define the areas where only colors approved by the aircraft manufacturer may be used are given in the T67M260 Maintenance Manual, Fig. 1-6 Paint Restrictions. These restrictions must be observed. NOTE 6. Prior to the initial issue of an Airworthiness Certificate, each airplane must be test flown to T67M260 Production Flight Test Schedule No. 1, Issue 3 and found to be satisfactory. After the test schedule has been completed an external inspection must be made to verify that no structural damage has occurred. NOTE 7. Compliance with JAR 23.221, “Spinning,” must be demonstrated before the issue of a United Kingdom Certificate of Airworthiness. NOTE 8. The T67M260 and T67M260-T3A are identical except for "Cockpit Arrangement Drawing". T67M260 Dwg No. T67G-18-001 T67M260-T3A Dwg No. T67G-18-005 This difference is installation of a fire extinguisher and first aid kit in the T67M260. NOTE 9. For the model T67M260-T3A, six-inch aircraft registration marks may be used vice A73EU Page 7 of 8 12-inch marks required by regulations when operated as a military aircraft. The purpose and rationale is stated in petition approv ed by FAA Acting Deputy Director, Aircraft Certification Service on May 28, 1993. NOTE 10. All T67M260-T3A aircraft manufactured under this Type Certificate A73EU listed under “Serial Numbers Eligible” are presently maintained and operated as trainers by the United States Air Force. None are in civilian use. Prior to any future release to civilian use, all USAF operated aircraft designated under ”Serial Numbers Eligible” must meet conformity inspection to the Type Design. Compliance with FAR 23.562 must be completed. In addition, all aircraft, must incorporate the Slingsby Mandatory Service and Modification Bulletins listed below which have been UK CAA approved: Service/Mod Bulletin Subject UK CAA AD SB 52, Issue 3 Elevator Horn Water Ingress 010-05-94 *M606 SB 54 Inspection of Wing Fuel Tank Drain Valves 011-05-94 M593 SB 62 Flap Lever Proof Test 005-11-94 M645 SB 64 Inspection of Elevator Bearing Plate 006-11-94 Service/Mod Bulletin Subject UK CAA AD M576 Introduction of Rudder Pedal Pad with Chamfered Side Plate 013-05-94 M636 Introduction of Improved Low Level Fuel Sensor 007-10-94 SB 65 Nose Landing Gear Inspection and Modification 001-12-94 M646 SB 72, Issue 2 Inspection of Thermostatic Bypass Valves Mandatory Textron Lycoming Service Bulletin SB 79, Issue 2 Inspection of Control Column to Seat Clearance and Seat 008-04-95 M665 Attachment Integrity. Introduction of Locating Spigot on seat 009-04-95 SB 83, Issue 2 Inspection for Foul Between No 2 Rudder Pedal Pivot 006-02-96 * M671 and Nosewheel Steering Arm SB 84 Inspection of Rib 2 Lower Flange Bond to Wing Skin 010-07-95 * M678 SB 87, Issue 2 Reduced Structural Temperature Limitation from 55°C 002-09-95 *M683 to 50°C and Prohibited Flight Temperature Limitation from 65°C to 55°C. See Note 3. SB88, Issue 2 Rudder pedal to Mixture Potential Foul 007-08-96 M687 A/B A73EU Page 8 of 8 * SB 94 / M695 Inspection of Elevator Pushrod to Control Column 007-07-96 Assembly Pivot Bolt to Seat Clearance SB 105 Inspection of Control Surfaces for Rubbing Marks No CAA AD SB 120, Issue 3 Inspection of Rudder Bar Support Brackets 012-01-97 (Only welded brackets are allowed if cracks are found) SB 139 Inspection of Steering Arm on Fairey Hydraulics Nose Leg 003-09-97 (No cracks are allowed, parts must be replaced and inspections continued every 150 hours per SB) SB 150 Inspection of Elevator Lever Stiffnut at Frame 7 002-12-97 M783 Introduction of Split Pin into Elevator Pushrod Bellcrank No CAA AD Pivot Bolt at Frame 7 Service/Mod Bulletin Subject UK CAA AD M830 Introduction of STC Fuel System Modification No CAA AD M890 Introduction of Re-routed Fuel Tank Vent System, Re- No CAA AD introduction Of Low Fuel Warning Lights and Electric Fuel Pump Limited To 35 lbs/in² Output Pressure-Post Mod M830 Aircraft M898, Issue 2 Deletion of Fuel Filter Drain Ref SAIC Fuel Modification 010-02-2000 M992 Introduction of fasteners to front of Frame 2 to 3 trim panel for added security 005-03-2003 SB 175 Inspection of Control Column Housing Brazing No CAA AD SB 179 Inspection of Tailplane Attachment Brackets No CAA AD SB 180 Inspection of alternator/starter wiring loom ‘p’-clipping at engine 008-04-2003 * Mod Bulletin is specified in Service Bulletin, but no Mod Bulletin exists. Service Bulletin incorporates action required by Mod Bulletin. If maintenance records for the aircraft show that a Mod Bulletin has been incorporated, the associated Service Bulletin has also been incorporated. .....END....