# TCDS G1NE: K & L Soaring LLC - Type: Type certificate data sheet - Status: Current - Holder: K & L Soaring LLC - Revision: 3 - Revised: November 29, 2010 - Product: Aircraft, Glider - Certification basis: Part 21, Part 23 - Data sheet PDF: https://openairdocs.org/files/sha256/3d/c4/3dc43c8e5ac7cbd6a7db462ce06729e5818e99ae568c5f4068905fbab2a86991 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/E0239737FE4A00258625780E005DA810.0001 - Page: https://openairdocs.org/tcds/G1NE ## Models (1) As the data sheet lists them. - SGM 2-37 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 Rev No. 3 3 1 1 1 1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION G1NE Revision 3 K & L Soaring, LLC SGM 2-37 November 29, 2010 TYPE CERTIFICATE DATA SHEET NO. G1NE This data sheet which is a part of type certificate No. G1NE, 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 K & L Soaring, LLC 5996 State Route 224 Cayuta, New York 14824 Type Certificate Holder Record Schweizer Aircraft Corporation Elmira Corning Regional Airport P.O. Box 147 Elmira, New York 14902 I - Model SGM 2-37, 2 PCLM, Approved March 22, 1983 Type Sailplane, utility category (motorglider) Engine Lycoming O-235-L2C (with Slick mags.) Fuel 100/130 minimum grade aviation gasoline Engine Limits For all ope rations, 2600 R.P.M. (112 H.P.) Propeller & Propeller Limits Sensenic h 72CK-0-50 (2) bladed, fixed pitch Diameter: 72 in. maximum, 70 in. minimum Static RPM at max. permissible throttle setting: 2450 RPM maximum, 2300 RPM minimum Airspeed Limits (CAS) VS (Stall) 48 mph (42 kts.) VSO (Stall, dive brakes open) 52 mph (45 kts.) VA (Maneuvering) 90 mph (78 kts.) VRA (Rough Air) 100 mph (87 kts.) VNE (Never exceed) 135 mph (117 kts.) VDB (Dive brakes open) 135 mph (117 kts.) C.G. Range +82.45 (22.6% MAC) to +86.20 ( 31.7% MAC) at max. gross weight or less. Maximum Weight 1850 lb. for airc raft having wing modifications detailed on dwgs. 37401R, 37402R, and 37408R. Maximum Baggage 1850 lb. gross weight aircraft: 100 lbs. (+110.00) (20 lbs./sq. ft. maximum) No. of Seats 2 (For CG locations see Weight and Balance Section in Pilot's Operating Handbook) G1NE 2 ____________________________________________________________________________________________________ Fuel Capacity 1850 lb. gross weight aircraft: 15.6 gal. (1.4 gal. unusable) with single ta nk in left hand portion of wing center section (+80.30); 31.2 gal. (2.8 gal. unusable) with two 15. 6 gal. tanks in wing center section (+80.30) Oil Capacity 6 qt., 2 qt. unusable (+19.6) (See Note 1) Control Surface Movements Stabilator: Up 19 1/2  (+0, -3), anti-servo/trim tab up 55.1 +/-3 relative to stabilator Down 9 1/2  (+0. -3); anti-servo/trim tab down 30.7 +/-3 relative to stabilator Rudder: Left 28  to 30, Right 28 to 30 Aileron: Up 30 1/2  to 33 1/2, Down 10 to 13 Dive Brakes: Upper: Up 87  to 97 Lower: Down 68  to 78 Anti-servo trim tab: Up 3.6  (+2, -0), Down 16.5 (+2, -0), relative to stabilator with stabilator at neutral position Serial Nos. Eligible S/N 1 and up Data Pertinent to All Models Datum 70.39 inches ahead of wing leadi ng edge at center section (F.S. 0.00) Mean Aerodynamic Chord 41.38 inches (Leading edge of M.A.C. 73.10 inches aft of datum) Leveling Means See Weight & Balan ce Section in Pilot's Operating Handbook Certification Basis FAR 21.23 and in accordance with AC 21.23-1, JAR 22, revised April 1, 1980, plus the additional criteria specified in paragraph 5e(6) of Advisory Circular 21.23-1, dated January 12, 1981, and the following: FAR 23.483 and FAR 23.485, since JAR 22 re fers to single centerline wheel landing gear. FAR 23.473 through 23.497, and 23.723 thr ough 23.727, in lieu of JAR 22.473 through 22.497, and 22.721 through 22.725, respectively. FAR 23.221 for normal category airplanes, including a placard prohibiting intentional spins, in lieu of JAR 22.221 and 22.223. A glide ratio not exceeding 10:1 at a speed of 1.3 V s, in lieu of the value of 7:1 of JAR 22.75. FAR 23, Appendix A, para graph A 23.11, using the acrobatic load factor of Nz=6, in lieu of JAR 22.423, 22.425, 22.441, and 22.443, for vertical and horizontal tail design. In lieu of JAR 22.71, W/ b2 in metric units equal to 3 or less, was used as an equivalent method to differentiate powered sailplane s from FAR 23 small airplanes in accordance with AWS-1 memorandum to ANE-170, dated October 5, 1984. Production Basis None Equipment The basic required equipment as pr escribed in the applicable airworthiness requirements (see Certification Basis) must be installed in the aircraft for certification. NOTE 1. Pilot's Operating Handbook, Report No. 37-17, date d Oct. 5, 1984, Reissue (1), dated March 9, 1988, 3 G1NE including current weight and balance report with 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 and kept in the aircraft thereafter. The certificated empty weight and corresponding center of gravity location must include unusable fuel of 8.4 lbs. (+78.00), with a single tank or 16.8 lbs. (+ 78.80), with two tanks, and system oil of 11.25 lb. (+19.6). NOTE 2 The following placards must be displayed in locations as indicated: In full view of the pilot: EXCEPT AS MAY BE OTHERWISE INDICA TED ON A PLACARD, THE MARKINGS AND PLACARDS INSTALLED IN THIS MOTORGLIDER CONTAIN OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERAT ING THIS MOTORGLIDER IN THE UTILITY CATEGORY. OTHER OPERATING LIMITATIONS WHICH MUST BE COMPLIED WITH WHEN OPERATING THIS MOTORGLIDER IN THIS CATEGORY ARE CONTAINED IN THE PILOTS OPERATING HANDBOOK. THIS MOTORGLIDER IS APPROVED FOR FLIGHT IN DAY/VFR ONLY. FLIGHT INTO KNOWN ICING CONDITIONS IS PROHIBITED. In full view of the pilot: TAKEOFF CHECK LIST FUEL - ON/QUANTITY DIVE BRAKES - CLOSED STATIC DRAIN - CLOSED TRIM - SET MIXTURE - RICH CONTROLS - FREE ELECTRIC FUEL PUMP - ON CANOPY - LATCHED CARBURETOR HEAT - OFF ALTIMETER - SET ENGINE GAGES - CHECKED PARKING BRAKE - OFF BELTS & HARNESS - FASTENED LANDING CHECK LIST BELTS & HARNESS - FASTENED TRIM - AS REQUIRED MIXTURE - RICH FUEL - ON ELECTRIC FUEL PUMP - ON PARKING BRAKE - OFF In full view of the pilot: N-NUMBER FLIGHT LIMITS & NORMAL OPERATING SPEEDS MODEL SGM 2-37 SER. NO. IAS NEVER EXCEED SPEED (VNE) 136 mph MANEUVERING SPEED (VA) 89 mph ROUGH AIR SPEED (VRA) 101 mph MAX. DIVE BRAKES OPEN 136 mph MAX. GROSS WEIGHT 1850 lbs STALL SPEED (BRAKES CLOSED) 53 mph LANDING APPROACH MINIMUM 66 mph BEST GLIDE 62 mph MINIMUM SINK 60 mph DEMONSTRATED CROSSWIND COMPONENT 17 mph G1NE 4 _____________________________________________________________________________________________________ NOTE 2 (cont) AEROBATIC MANEUVERS PROHIBITED SPINS PROHIBITED DAY V.F.R. NON-ICING ONLY TIRE PRESSURE 35 psi FOR IN-FLIGHT STARTS AND OTHER CONDITIONS SEE PILOTS OPERATING HANDBOOK Above parking brake control: PARKING BRAKE TO BE OFF PRIOR TO LANDING. TO LOCK - PRESS PEDAL, PULL AND HOLD CONTROL. TO UNLOCK - PRESS PEDAL OR RELEASE CONTROL. In full view of pilot next to corresponding controls: For aircraft S/N 1 thru 4 and 6 thru 9: INCREASE RICH THROTTLE MIXTURE DECREASE LEAN For aircraft S/N 5, 10, & up: THROTTLE MIXTURE PUSH OPEN PULL LEAN On console next to trim wheel: UP NOSE DOWN TRIM Adjoining dive brake controls: OPEN DIVE CLOSED  BRAKE  On overhead structure next to latch mechanism: LOCK CANOPY UNLOCK  LATCH  5 G1NE Also on overhead structure is a red canopy latch indicator line. NOTE 2 (cont) On instrument panel in full view of pilot: FUEL PUMP MASTER PRIMER CABIN HEAT PULL FOR HEAT MIC. ON ON JACK OFF OFF On instrument panel under corresponding breaker: For aircraft S/N 1 thru 4 AND 6 thru 9: MAIN, ALT., FLD, START, INST., RADIO, FUEL PUMP For aircraft S/N 5, 10, & up optional: if equipped MAIN, ALT., FIELD, START, GAUGES, FUEL PUMP, TURN COORD., TRANSPONDER, RADIO In full view of the pilot, above the fuel indictor gauge(s): For aircraft having one-tank fuel system: FUEL REMAINING WHEN THE QUANTITY INDI CATOR READS ZERO CANNOT BE USED SAFELY IN FLIGHT. 14.2 U.S. GAL. USABLE FUEL GRADE (MIN. OCTANE).....100/130 - GREEN For aircraft having optional two-tank fuel system: FUEL REMAINING WHEN THE QUANTITY INDI CATORS READ ZERO CANNOT BE USED SAFELY IN FLIGHT 28.4 U.S. GAL. USABLE FUEL GRADE (MIN. OCTANE).....100/130 GREEN In full view of the pilot, below the throttle quadrant: For aircraft having one tank fuel system: FUEL ON OFF For aircraft having optional two-tank fuel system: FUEL L R OFF G1NE 6 ________________________________________________________________________________________________ NOTE 2 (Cont) In full view of the pilot, n ear the carburetor heat control: For aircraft S/N 1 thru 4 and 6 thru 9: OFF CARB. HEAT ON For aircraft S/N 5, 10, and up: CARB HEAT PULL ON In full view of the pilot, above static system drain: STATIC DRAIN In baggage compartment: MAX. BAGGAGE COMPARTMENT LOAD 100 LBS. DI STRIBUTE LOAD AT 20 LBS./SQ. FT. MAX. Note 3. An approved Safety Belt and shoul der harness is required for each occupant. Note 4. All SGM 2-37 motorgliders, serial numbers 1 and up, have been modified to a maximum gross weight of 1850 pounds. The pilot's operating Handbook, dated Oc tober 5, 1984, and reissued March 9 1988, supersedes all preceding handbooks and is a pplicable to all SGM 2-37 motorgliders. ...END... ``` ## ADs (1, in force first) - [AD 87-02-01](https://openairdocs.org/ad/87-02-01): Tow-Release Installation Inspection · K & L Soaring SGM 2-37, SGS 1-23, SGS 1-23D and 32 more. Effective Jan 21, 1987 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.