TCDS A-804

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION AIRCRAFT SPECIFICATION NO. A-804 Type Certificate Holder W.Z.D. Enterprises Inc. 501 Hungerford Dr. Suite 436 Rockville, MD 20850 JGS Properties, LLC transferred to W.Z.D. Enterprises Inc. on December 27, 2017. Quartz Mountain Aerospace, Inc. name changed to JGS Properties, LLC on November 22, 2011. Luscombe Aircraft Corporation name change to Quartz Mountain Aerospace, Inc. on March 13, 2006. Land-Air & Leasing, Inc. transferred to Luscombe Aircraft Corporation on August 10, 1995. Richard S. Kettles transferred to Land-Air & Leasing, Inc. on April 8, 1992. Luscombe Aircraft re-issued to Richard S. Kettles. I. Model 11A, 4 PCL (Normal Category), approved October 4, 1948 Engine Continental E165-2 (see Item 106 for optional engines) Fuel 80 min. octane aviation gasoline Engine Limits For all operations, 2050 rpm (165 hp) Propeller Limits Static rpm at maximum permissible throttle setting, not over 1825, not under 1725. No additional tolerance permitted. Diameter, not over 80 in., not under 78.5 Airspeed Limits Maneuvering 114 mph ( 99 knots) True Ind. Maximum structural cruising 145 mph (126 knots) True Ind Never exceed 180 mph (157 knots) True Ind. Flaps extended 100 mph ( 87 knots) True Ind. Page No. 1 2 3 4 5 6 7 Rev. No. 22 12 9 16 21 21 20 Rev 22 Changes TC holder transferred to W.Z.D. Enterprises Inc. A-804 Revision 22 W.Z.D. Enterprises Inc. 11A 11E June 5, 2018 A-804 2 of 7 RONT IMIT REA LIMI I. Model 11A, 4 PCL (Normal Category) Cont. C.G. Range (+83.7) to (+87.9) at 2280 lbs. (+76.9) to (+87.9) at 1700 lbs. or less Straight line variation between points given. 2300 2100 LBS. 1900 1700 1500 76 78 80 82 84 86 88 90 INCHES Empty Weight C.G. Range (+76.0) to (+79.0) at 1450 lbs. empty weight (+76.0) to (+77.5) at 1250 lbs. empty weight Straight line variation between points given. When empty weight C.G. falls within this range, computation of critical fore and aft C.G. positions is unnecessary. Range is not valid for nonstandard arrangements. 1500 LBS. 1400 F L R 1300 T 1200 75 76 77 78 79 80 INCHES Maximum Weight 2280 lbs. No. of Seats 2 (+86) and 2 (+122) Maximum Baggage 100 lbs. (+123) Fuel Capacity 40 gal. (Two 20 gal. tanks in wings) (+86) Oil Capacity 2.5 gal. (+35) Control Surface Movements Ailerons Up 15 ± 1 Down 9 ± 1 Elevators Up 29 ± 1 Down 13 ± 1 Rudder Right 15 + 0 Left 15 + 0 - 1 - 1 Wing Flaps Down 35 ± 1 Elevator Tabs Up 12 ± 1 Down 40 ± 1 The airplane control system must be rigged and maintained in accordance with the Rigging Instructions of Luscombe Model 11A Flight Manual, Section II. RE AR LI M IT FRO NT LI M IT A-804 3 of 7 I. Model 11A, 4 PCL (Normal Category Cont. Serial Nos. eligible 11-104 and up manufactured prior to October 29, 1956. Required equipment In addition to the pertinent required basic equipment specified in CAR 3, the following items of equipment must be installed: 1, 102, 103, 104, 105, 201(a), 202(a), 204(a), 402(a) For night flying, cabin dome light and instrument lights or equivalent to provide illumination of all placards and instruments are required in addition to equipment required by Part 43. Specifications Datum 100 in. forward of vertical bulkhead forming the rear frame of main door. Leveling means Floor at front seat attaching angles. Certification basis Type Certificate No. 804 (CAR 3, Normal Category) Export eligibility Eligible for export to all countries subject to the provisions of MOP 2-4 except as follows: Canada - Landplane eligible Skiplane not eligible Equipment A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. Approval for the installation of all items of equipment listed herein has been obtained by the aircraft manufacturer except those items preceded by an asterisk (*). The asterisk denotes that approval has been obtained by someone other than the aircraft manufacturer. An item marked with an asterisk may not have been manufactured under a CAA monitored or approved quality control system, and therefore attention should be paid to workmanship and conformity with pertinent data called for in this specification. Propellers and Propeller Accessories 1. Propeller - Sensenich Model 80EY80 or any other fixed pitch wood propeller rated for required hp and rpm and meeting the propeller limits under Section 1. 22 lbs. (+5) 2. Propeller - Hartzell automatic two-position, Hub Model HC-42XF-2, blades model 8428-1 Diameter: Not over 83 in., not under 81.5 in. Blade angle at 30" station: Low 15, high 22.2 Propeller to be installed and operated in accordance with the above limitations and approved Hartzell service instructions. CAA Approved Flight Manual Revision pages 1.1 and 6.1, dated April 21, 1949, must be inserted in Item 402(a) when this propeller is installed. 59 lbs. (+5) 3. Spinner - Hartzell Propeller (Luscombe Dwg. 11-6402) 2 lbs. (+5) 4. Propeller - Hartzell automatic two-position, Hub Model HC-42XF-2, Blades 8433-1 (Eligible only on E-185-2 engine with dampered crankshaft identified by the letter "D" after the engine serial number.) Diameter: Not more than 83 in., not less than 81.5 in. Blade angle at 30" station: Low 17; high 24. Counterweight length 3.490". Low rpm (high pitch) to high rpm (low pitch) latch operation - not less than 1550 rpm Item 402(b) required when this propeller is installed. 59 lbs. (+5) A-804 4 of 7 I. Model 11A, 4 PCL (Normal Category) Cont. Engine and Engine Accessories - Fuel and Oil System 101. Starter (Delco-Remy #1109660) Solenoid type 21 lbs. (+42) 102. Oil radiator - (Harrison #7434) 7 lbs. (+43) 103. Carburetor air heater 1 lb. (+23) 104. Kay exhaust muffler system 12 lbs. (+30) 105. Carburetor air filter 1 lb. (+18) 106. Continental E185-2 engine No change Fuel: 80 Octane minimum Engine limits: For all operations 2300 rpm (185 hp). When the E185-2 engine is installed, the airplane fuel system and oil cooling system must comply with Luscombe Dwgs. 11-6601C (Arrangement 2), 11-1702C, and 11-6701C. Landing Gear 201. 2 Main wheel-brake assemblies, 6.00-6 Type III 14 lbs. (+65) (a) Goodyear Model L6HBD Wheel Assembly #511413-M Brake Assembly #9520292 202. (a) 2 Main Wheel 4-ply-rating tires, 7.00-6 Type III (with regular tubes) 19 lbs. (+65) 204. Tail Wheel Assembly (a) Maule, Model SFS-12, steerable 5 lbs. (+266) Tire size 6.00 X 2.50 *(b) Scott, Model 3200, steerable 8 lbs. (+266) Tire size 8.50 X 2.50 Electrical Equipment 301. Generator, 12 volt (Delco-Remy #1101879) 14 lbs. (+42) 302. Battery - Willard Manifold Venti Type AW-12-25 12 volt 25 amph. hr. (a) With Item 1 installed 22 lbs. (+46) (b) With Item 2 installed 22 lbs. (+152) 303. Voltage regulator (Delco-Remy #1118200) 2 lbs. (+49) 304. Battery Solenoid - Cutler Hammer (#6042-H109A) 1 lb. (+49) 305. 2 Landing lights - Luscombe Dwg. #11-8105 with G.E. Lamp #4509 2 lbs. (+13) Interior Equipment 401. Cabin heater Luscombe Dwg. 11-8602 2 lbs. (+49) 402. (a) FAA Approved Airplane Flight Manual dated May 26, 1948 *(b) Airplane Operation Limitations Supplement to Item 402(a) for Hartzell Snap-O-Matic propeller on Luscombe 11A, dated October 10, 1949. II. Model 11E, 4 PCL (Normal Category) Approved December 17. 2002: Changes to the Model 11A include engine change, electrical system changed to a 24 volt system, landing gear configuration changed from conventional to tricycle, installation of a composite cowl, installation of a modified windshield, change from hydraulically driven flaps to electrically driven, installation of electrically driven elevator trim in lieu of the mechanical trim, installation of a new interior including three point seat belts. Engine One, Teledyne Continental IO-360-ES, TCDS E1CE Fuel 100/100LL minimum grade aviation gasoline Engine Limits For all operations, 2550 RPM (185 HP) Propeller 1. McCauley Model 1B235/EFC7667 A-804 5 of 7 II. Model 11E, 4 PCL (Normal) Cont. 2. Sensenich Model 76EC-8-0-66 Spinner 1, McCauley Model D4245 (McCauley propeller) 2, Sensenich C-2347 (Sensenich propeller) Propeller Limits 1. McCauley: Static RPM at full throttle: Not more than 2200 rpm, not less than 2100 rpm. Max rpm of 2250 rpm is permissible when airfield pressure altitude is above 5000 ft. Diameter: Not over 76 inches; not under 74 inches 2. Sensenich: Static RPM at full throttle: Not more than 2250 rpm, not less than 2150 rpm. Avoid continuous static operations (over 5 minutes) above 2100 rpm. Diameter: Not over 76 inches; not under 74 inches Airspeed Limits Maneuvering 114 mph ( 99 knots) Calibrated Maximum structural cruising 150 mph (130 knots) Calibrated Never Exceed 180 mph (157 knots) Calibrated Flaps Extended 100 mph ( 87 knots) Calibrated C.G. Range Forward Limits Linear variation from 83.7 inches aft of Refererence datum at 2280 lbs to 78.3 inches aft of datum at 1819 lbs; 78.3 inches aft of datum at 1817 lbs or less. Aft Limit 87.9 inches aft of datum Empty Weight C.G. Range None Reference Datum 100 in. forward of vertical bulkhead forming the rear frame of main door. Leveling Means Two leveling screw heads which protrude at same waterline on right side of fuselage located directly below right rear cabin window. Maximum Weight 2280 lbs. No. of Seats 4 (2 at 86 inches aft of datum and 2 at 122 inches aft of datum) Maximum Baggage 100 lbs. at 128 inches aft of datum Fuel Capacity 42 gallons total; 40 gallons useable (Two 21 gallon tanks in wings at +86.8 inches aft of datum) See NOTE 1 for data on weight and balance. Oil Capacity 2.0 gallons total; 1.25 gallons useable (+25 inches aft of datum) See NOTE 1 for data on weight and balance. Control Surface Movements Ailerons Up 15° ± 1º Down 9º ± 1º Elevators Up 29º ± 1º Down 13º ± 1º Rudder Right 15º ± 1º Left 15º ± 1º Wing Flaps Down 25º ± 1º Elevator Tab Up 12 º± 1º Down 40º ± 1º The airplane control system must be rigged and maintained in accordance with the rigging instructions of Quartz Mountain Aerospace Maintanence Manual P/N AMN-11E- 1 for Model 11E.. Serial Nos. Eligible 1001 to 1004, 1006 to 1013, and 1016. Serial numbers 00995 and 00996 are not eligible for Standard Airworthiness Certificates. Serial numbers 1005, 1014, 1015, 1017 and subsequent are not eligible for Standard A-804 6 of 7 II. Model 11E, 4 PCL (Normal) Cont. Airworthiness Certificates unless conformity to type design data is determined by the FAA (contact the Fort Worth Manufacturing Inspection Office at 817-222-5180). An applicant for a Standard Airworthiness Certificate must provide type design data and evidence of Type Certificate holder permission to use the type design data. Certification Basis CAR 3 dated December 15, 1946, as amended by 3-1 through 3-4 and the following sections of Part 23 effective February 1, 1965: Section 23.75, 23.867, and 23.954 as amended through Amendment 23-7. Section 23.561(b)(2) as amended through Amendment 23-36. Section 23.853 as amended through Amendment 23-34 Section 23.1143 as amended through Amendment 23-29. Section 23.1147 as amended through Amendment 23-33. Section 23.1307 as amended through Amendment 23-23. Section 23.1309 as amended through Amendment 23-41. Section 23.1359 as amended through Amendment 23-49. Sections 23.1, 23.2, 23.3, 23.21, 23.33, 23.51, 23.65, , 23.77, 23.671, 23.673, 23.683, 23.685, 23.689, 23.697, 23.699, 23.781, 23.905, 23.907, 23.925, 23.951, 23.959 23.961, 23.963, 23.969, 23.971, 23.973, 23.975, 23.977, 23.991, 23.993, 23.995, 23.997, 23.999, 23.1011, 23.1017, 23.1019, 23.1021, 23.1023, 23.1041, 23.1043 23.1047, 23.1091, 23.1105, 23.1121, 23.1123, 23.1125, 23.1141, 23.1145, 23.1149, 23.1163, 23.1165, 23.1183, 23.1191, 23.1193, 23.1301, 23.1327, , 23.1357, 23.1367, 23.1381, 23.1385, 23.1387, 23.1389, 23.1391, 23.1393, 23.1395, 23.1397, 23.1413, 23.1529, 23.1547, 23.1549, and 23.1589 as amended through 23-46. Sections 23.901, 23.903, 23.943, 23.955, 23.965, 23.967, 23.1093, 23.1103, 23.1303, 23.1305, 23.1311, 23.1321, 23.1322, 23.1323, 23.1325, 23.1337, 23.1351, 23.1353, 23.1361, 23.1365, 23.1383, 23.1401, 23.1431, 23.1543, 23.1545, 23.1555, 23.1581, 23.1583, 23.1585, and 23.1587 as amended through 23-54. Part 36 of the Federal Aviation Regulations effective December 1, 1969, plus any amendments in effect at the time of certification. Equivalent Level of Safety Findings ELOS #ACE-02-09 Rev. A dated December 5, 2002 – CAR 03.135-N Spins ELOS #ACE-07-16, Dated January 16, 2007 – 14 CFR Part 23 §23.1326 (b)(1), Amendment 23-49, Pitot Heat Indication Systems. ELOS #ACE-07-17, Dated January 17, 2007 – 14 CFR Part 23 §23.1353(h), Amendment 23-49, Storage Battery Design and Installation. Application Date: Application for Amended Type Certificate for the Luscombe 11E was August 12, 1994. Type Certificate No. A-804 was provisionally amended July 25, 2002 for the Luscombe 11E, final Amended Type Certification adding the Model 11E was completed December 17, 2002. Production Basis None. Prior to original certification of each aircraft, an FAA representative must perform a detailed inspection for workmanship, materials, conformity with the approved technical data, and a check of the flight characteristics. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition to the above required equipment, the following equipment is also required: 1. The latest FAA approved revision on Airplane Flight Manual Part No. AFM-LAC-1 for Model 11E. Design Data The airplane shall be manufactured in accordance with the latest FAA approved revision of Quartz Mountain Aerospace Master Drawing List, Document No. 11E-MDL A-804 7 of 7 NOTE 1. A 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 corresponding center of gravity location must include unusable fuel of 12 lbs. at 86.8 inches aft of datum and full oil of 16.7 lbs. at 25 inches aft of datum. NOTE 2. The placards specified in the latest revision of the “FAA Aprroved Flight Manual for the Quartz Mountain Aerospace 11E,” Document No. AFM-LAC-1, must be displayed. NOTE 3. In accordance with FAR 23.1529, Instructions for Continued Airworthiness acceptable to the Administrator must be available at delivery of first aircraft or issuance of a standard certificate of airworthiness which ever occurs later. …END…