TCDS A22NM

A-1 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A22NM Revision 31 Aviat Aircraft, Inc. A-1A A-1B A-1C-180 A-1C-200 Dec 7, 2017 TYPE CERTIFICATE DATA SHEET NO. A22NM This data sheet which is part of Type Certificate No. A22NM 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 Aviat Aircraft Inc. 672 South Washington Street Afton, Wyoming 83110 Type Certificate Ownership Record Christen Industries transferred ownership of Type Certificate A22NM to Aviat, Inc. on April 4, 1991. Aviat, Inc. transferred ownership of Type Certificate A22NM to White International, LTD. on December 3, 1992. White International, LTD. transferred ownership of Type Certificate A22NM to Sky International, Inc. on January 10, 1996. Sky International, Inc. transferred ownership to Aviat Aircraft, Inc. On February 27, 2012 I - Model A-1, 2PCLM (Normal Category), Approved May 1, 1987 Engine Lycoming O-360-C1G (180 HP), or Lycoming O-360-A1P (180 HP) Fuel 100/100LL grade aviation gasoline Engine Limits For all operations, 2700 RPM Propeller and Propeller Limits Hartzell HC-C2YK-1BF/F7666A (Constant Speed) Diameter not over 76 in., not under 72 in. (See NOTE 3) Pitch settings at 30 in. station low 11.7º ± .2°, high 29.0° ± 1.0°, (See NOTE 9) Hartzell spinner assembly 836-60 (Required). Hartzell governor V3-6 or S-1-16 Placard required: "AVOID CONTINUOUS OPERATIONS BETWEEN 2000-2250 RPM" Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 18 Rev. No. 31 25 25 25 26 26 26 26 23 23 23 23 23 25 23 25 27 30 31 A22NM Page 2 of 18 Rev 25 I - Model A-1, 2PCLM (Normal Category), Approved May 1, 1987 (cont'd) Airspeed Limits (CAS) C.G. Range Empty wt. C.G. Range Datum Leveling Means Maximum Weight No. of Seats Maximum baggage Fuel Capacity Oil Capacity Control Surface Movements Serial Nos. Eligible Certification Basis Production Basis Equipment Never Exceed Maximum Structural Cruising Maneuvering Flaps Extended (+74.5) to (+78.4) at 1800 lb (+72.5) to (+78.4) at 1500 lb and below Straight line variation between points given None 60 in. forward of wing leading edge Cabin door, lower sill 1800 lb 2 (1 at +72.5 and 1 at +99.0) 50 lb (at +120.0) 52 gal. (two 26 gal. Tanks in wings at +84.0) 153 mph (133 knots) 119 mph (103 knots) 94 mph (82 knots) 73 mph (63 knots) 50 gal usable. See NOTE 1 for data on unusable fuel. 8 qts. (at +25.9) Elevator UP 29°±1° DOWN 15°±1° Ailerons UP 20° ± 2° DOWN 20° ± 2° Rudder LEFT 25° ± 2° RIGHT 25° ± 2° Flaps UP 0° DOWN 30° + 0°, -2° 1001 to 1394 Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 thru 23-31 (Normal Category) and FAR 36 amended thru 36-12,. FAR 21 amended thru 21-57. Application for Type Certificate dated November 20, 1985. Type Certificate No. A22NM issued May 1, 1987. Production Certificate No. A22NM The basic required equipment as prescribed in the applicable airworthiness regulations must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. FAA Approved Airplane Flight Manual 2. Stall Warning indicator. 3. Cylinder head temperature gage. II - Model A-1A, 2PCLM (Normal Category), Approved January 28, 1998 The A-1A is a derivative model of the A-1. The A-1A has a gross weight of 1890 lb The airframe has been modified structurally to accept this higher gross weight. Engine Lycoming O-360-A1P (180 HP) Fuel 100/100LL grade aviation gasoline Engine Limits For all operations, 2700 RPM A22NM Page 3 of 18 REV 25 II - Model A-1A, 2PCLM (cont’d) Propeller and Propeller Limits Airspeed Limits (CAS) C.G. Range Empty wt. C.G. Range Datum Leveling Means Maximum Weight No. of Seats Maximum baggage Fuel Capacity Oil Capacity Control Surface Movements Serial Nos. Eligible Certification Basis Production Basis Hartzell HC-C2YK-1BF/F7666A (Constant Speed) Diameter not over 76 in., not under 72 in. (See NOTE 3) Pitch setting at 30 in. station low 11.7° ± .2°, high 29.0° ± 1.0° Hartzell governor V3-6 or S-1-16 Placard required: "AVOID CONTINUOUS OPERATIONS BETWEEN 2000- 2250 RPM" Never Exceed 153 mph (133 knots) Maximum Structural Cruising 119 mph (103 knots) Maneuvering 99 mph (86 knots) Flaps Extended S/N 1395 to 1429 73 mph (73 knots) S/N 1430 and up 80 mph (70 knots) (see NOTE 15) (+74.5) to (+78.4) at 1890 lb (+72.5) to (+78.4) at 1500 lb and below Straight line variation between points given None 60 in. forward of wing leading edge. Cabin door, lower sill 1890 lb 2 (1 at +72.5 and 1 at +99.0) 50 lb (at +120.0) 52 gal. (two 26 gal. Tanks in wings at +84.0) 50 gal usable. See NOTE 1 for data on unusable fuel. 8 qts. (at +25.9) Elevator UP 29° ± 1° DOWN 15° ± 1° Ailerons UP 20° ± 2° DOWN 20° ± 2° Rudder LEFT 25° ± 2° RIGHT 25° ± 2° Flaps UP 0° DOWN 30° + 0°, -2° 1395 to 1467 Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 thru 23-31 (Normal Category) and FAR 36 amended thru 36-12. FAR 21 amended thru 21-57. Application for Type Certificate dated August 25, 1997. Type Certificate No. A22NM issued January 28, 1998. Production Certificate No. 704NM A22NM Page 4 of 18 REV 25 II - Model A-1A, 2PCLM (cont’d) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. FAA Approved Airplane Flight Manual 2. Stall Warning indicator 3. Cylinder head temperature gage III - Model A-1B, 2PCLM (Normal Category), Approved January 28, 1998 The A-1B is a derivative model of the A-1. The A-1B has a gross weight of 2000 lb. The airframe has been modified structurally to accept this higher gross weight. The C.G. envelope has been expanded forward and aft. NOTE: See serial numbers eligible under this model. (See Engine Option Group Configuration for optional propeller and propeller limits.) Engine Lycoming O-360-A1P (180 HP) Fuel 100/100LL grade aviation gasoline Engine Limits For all operations, 2700 RPM Propeller Hartzell HC-C2YK-1BF/F7666A (Constant Speed) and Propeller Limits Diameter not over 76 in., not under 72 in. (See NOTE 3) Pitch setting at 30 in. station low 11.7° ± .2°, high 29.0° ± 1.0° Hartzell spinner 836-60 (Required). Hartzell governor V3-6 or S-1-16 Placard required: "AVOID CONTINUOUS OPERATIONS BETWEEN 2000-2250 RPM" Airspeed Limits (CAS) Never Exceed 153 mph (133 knots) Maximum Structural Cruising 119 mph (103 knots) Maneuvering 113 mph (98 knots) Flaps Extended 80 mph (70 knots) (See Engine Option Group Configuration for Airspeed Limits.) C.G. Range (+73.6) to (+80.0) at 2000 lb (+71.0) to (+80.0) at 1530 lb and below Straight line variation between points given Empty wt. C.G. Range None Datum 60 in. forward of wing leading edge Leveling Means Cabin door, lower sill Maximum Weight 2000 lb No. of Seats 2 (1 at +72.5 and 1 at +99.0) Maximum baggage 50 lb (at +120.0) Fuel Capacity 52 gal. (two 26 gal. Tanks in wings at +84.0) 50 gal usable. See NOTE 1 for data on unusable fuel. Oil Capacity 8 quarts. (at +25.9) A22NM Page 5 of 18 REV 26 III - Model A-1B, 2PCLM (cont’d) Control Surface Movements Serial Nos. Eligible Certification Basis Production Basis Equipment Elevator UP 29° ± 1° DOWN 15° ± 1° Ailerons UP 20° ± 2° DOWN 20° ± 2° Rudder LEFT 25° ± 2° RIGHT 25° ± 2° Flaps UP 0° DOWN 30° + 0°, -2° Note: For Model A-1B, serial numbers 2285, 2288, 2289, 2291, and up, Aileron UP 15.5° ± 2° DOWN 15.5° ± 2° 2000 and up New optional rear spar material incorporated at S/N 2001. Was 6061-T6. Is: 7075-T76. (See Engine Option Group Configuration for Serial Nos. Eligible.) Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 thru 23-31 (Normal Category) and FAR 36 amended thru 36-12,. FAR 21 amended thru 21-57. Application for Type Certificate dated August 25, 1997. Type Certificate No. A22NM issued January 28, 1998. Production Certificate No. 704NM The basic required equipment as prescribed in the applicable airworthiness regulations must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. FAA Approved Airplane Flight Manual 2. Stall Warning indicator. 3. Cylinder head temperature gage. III.a - Engine Option Group Configuration without Flap (Normal Category), Approved August 18, 2003 (The Engine Option Group Configuration without Flap is a model A-1B, 2PCLM) Model A-1B, effective serial numbers NF0001 through NF0006, NF0008 and above, are equipped with all of the following optional items. Several of the Notes do not apply to Engine Option Group Configuration. Note: A -1B with Engine Option Configuration requires Approved Airplane Flight Manual dated August 18, 2003 or later FAA approved revisions. Engine Lycoming O-320-D2A (160 HP) Type Certificate Data Sheet (TCDS) E-274 Fuel 100 or 100LL grade aviation gasoline Engine Limits For all operations, 2700 RPM Propeller Sensenich 74DM6S8-0-58 Sensenich AE C-2367 FWD Bulkhead, AE A1233-5 Doubler Plate AE C2347 Spinner Dome, AE C2348 Rear Bulkhead Propeller Limits Diameter: Not over 74 in., not under 72 in. Static RPM Not over 2350 RPM, not under 2150 RPM No additional tolerance permitted. Sensenich spinner assembly C2366 (Required). Flapless Wing No Flaps or flap control system installed. Wing tips unique. A22NM Page 6 of 18 REV 26 IIIa - Engine Option Group Configuration without Flap (cont’d) Unique Engine Cowl Approved main gear tires with this option group Control Surface Movements Certification Basis 6.00 x 6 4-ply, Type III tube 8.00 x 6 4-ply, Type III tube 8.50 x 6 6-ply, Type III tube Aircraft with Engine Option Group are approved for Day VFR only. Aircraft with Engine Option Group equipped with Anti-Collision, Taxi/Landing, Position, and Instrument Flood Red/White lights are approved for both Day and Night VFR. Not approved for Instrument Flight Rules (IFR) operation under the provisions of § 91.205(d) of the Federal Aviation Regulations Elevator UP 29º ± 1º DOWN 15° ± 1° Ailerons UP 20º ± 2º DOWN 20º ± 2º Rudder LEFT 25º ± 2º RIGHT 25º ± 2º Serial Nos. Eligible NF0001 through NF0006, NF0008 and up Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 thru 23-31 (Normal Category) and FAR 36 amended thru 36-24. FAR 21 amended thru 21- 57. III.b - Engine Option Group Configuration with Flap (Normal Category), Approved October 21, 2005 (The Engine Option Group Configuration with Flap is a model A-1B, 2PCLM) Model A-1B, effective serial numbers NF0007, WF0001 and above, are equipped with all of the following optional items. Several of the Notes do not apply to Engine Option Group Configuration. Note: A-1B with Engine Option Configuration requires Approved Airplane Flight Manual dated September 23, 2005 or later FAA approved revisions. Engine Fuel Engine Limits Propeller Propeller Limits Unique Engine Cowl Approved main gear tires with this option group Lycoming O-320-D2A (160 HP) Type Certificate Data Sheet (TCDS) E-274 100 or 100LL grade aviation gasoline For all operations, 2700 RPM Sensenich 74DM6S8-0-58 Sensenich AE C-2367 FWD Bulkhead, AE A1233-5 Doubler Plate AE C2347 Spinner Dome, AE C2348 Rear Bulkhead Diameter: Not over 74 in., not under 72 in. Static RPM Not over 2350 RPM, not under 2150 RPM No additional tolerance permitted. Sensenich spinner assembly C2366 (Required). Wing with flaps effective serial numbers NF0007, WF0001 and up are equipped with balanced ailerons, without spades, long flaps, flap control system per Engineering Report 55-4, Revision D, Appendix A, dated 8-25-05 or later FAA approved revisions. 6.00 x 6 4-ply, Type III tube 8.00 x 6 4-ply, Type III tube 8.50 x 6 6-ply, Type III tube . A22NM Page 7 of 18 REV 26 III.b - Engine Option Group Configuration with Flap (Normal Category), Approved October 21, 2005 (Con’t) Aircraft with Engine Option Group are approved for Day VFR only. Aircraft with Engine Option Group equipped with Anti-Collision, Taxi/Landing, Position, and Instrument Flood Red/White lights are approved for both Day and Night VFR. Not approved for Instrument Flight Rules (IFR) operation under the provisions of § 91.205(d) of the Federal Aviation Regulations. Control Surface Movements Elevator UP 29º ± 1º DOWN 15° ± 1° Ailerons UP 15.5º ± 2º DOWN 15.5º ± 2º Rudder LEFT 25º ± 2º RIGHT 25º ± 2º Flaps UP 0º DOWN 30º + 0º , -2º IIIb - Engine Option Group Configuration with Flap (cont’d) Serial Nos. Eligible NF0007, WF0001 and up Certification Basis Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 thru 23-31 (Normal Category) and FAR 36 amended thru 36-24. FAR 21 amended thru 21- 57. IV - Model A-1C-180, 2PCLM (Normal Category), Approved September 24, 2007 The A-1C-180 is a derivative model of the A-1B. The A-1C-180 has a gross weight of 2200 lb. Structural modifications include updated landing gear per Aviat drawing 45017 (configurations: -501,-502,-503,-504,-505,- 506); and tail wheel configuration using 5-leaf spring or Alaska Bushwheel 3-leaf spring configuration per Aviat drawing 37340. An additional modification to the angle of the leading edge of the horizontal stabilizers down 3/10 of a degree using a new stabilizer “H” support tube is also incorporated. The A-1C-180 aircraft are equipped with the new wing/extended flap and spade less ailerons, new sliding windows, and the new wing flap control handle. The C.G. envelope has been reduced forward and expanded aft. NOTE: See serial numbers eligible under this model. Engine Lycoming O-360-A1P (180 HP) Fuel 100/100LL grade aviation gasoline Engine Limits Refer to each propeller and propeller limits Propeller MTV-15-B/205-58 (includes spinner) (Constant Speed) and Propeller Limits Diameter not over 80.7 in., not under 79.9 in. Pitch setting at 30 in. station low 7° ± .2°, high 24.0° ± 1.0° Takeoff & maximum continuous power 2600 RPM (Engine de-rated to 175 HP for noise) Hartzell HC-C2YK-1BF/F7666A (Constant Speed) Diameter not over 76 in., not under 72 in. Pitch setting at 30 in. station low 11.7° ± .2°, high 29.0° ± 1.0 Takeoff & maximum continuous power 2700 RPM Placard required: "AVOID CONTINUOUS OPERATIONS BETWEEN 2000- 2250 RPM" Hartzell HC-C2YR-1N/F7605 (Constant Speed) Diameter not over 76 in., not under 76 in. Pitch setting at 30 in. station low 10.5° ± .2°, high 30.0° ± 1.0° Takeoff & maximum continuous power 2700 RPM Hartzell HC-C2YR-1BF/F8477-4 (Constant Speed) Diameter not over 80 in., not under 78 in. A22NM Page 8 of 18 IV - Model A-1C-180, 2PCLM (Normal Category), Approved September 24, 2007 (con’t) REV. 26 Airspeed Limits (CAS) C.G. Range Empty wt. C.G. Range Datum Leveling Means Maximum Weight No. of Seats Maximum baggage Fuel Capacity Oil Capacity Control Surface Movements Serial Nos. Eligible Certification Basis Production Basis Equipment Pitch setting at 30 in. station low 10.3° ± .2°, high 30.9° ± 1.0 Takeoff & maximum continuous power 2600 RPM (Engine de-rated to 175 HP for noise) Hartzell spinner 836-60 or C3568-P (required for Hartzell props) Hartzell governor V3-6 or S-1-16 Never Exceed 153 mph (133 knots) Maximum Structural Cruising 119 mph (103 knots) Maneuvering 113 mph (98 knots) Flaps Extended 80 mph (70 knots) (+74.5) to (+81.0) at 2200 lb (+72.3) to (+81.0) at 1781 lb and below Straight line variation between points given None 60 in. forward of wing leading edge Cabin door, lower sill 2200 lb 2 (1 at +72.5 and 1 at +99.0) 50 lb (at +120.0) 52 gal. (two 26 gal. Tanks in wings at +84.0) 50 gal usable. See NOTE 1 for data on unusable fuel. 8 quarts. (at +25.9) Elevator UP 29° ± 1° DOWN 15° ± 1° Ailerons UP 15.5° ± 2° DOWN 15.5° ± 2° Rudder LEFT 25° ± 2° RIGHT 25° ± 2° Flaps UP 0° DOWN 30° + 0°, -2° 3000+ (See NOTE 25) Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 thru 23-31 (Normal Category) and FAR 36 amended thru 36-28. FAR 21 amended thru 21-57. Application for Type Certificate dated September 26, 2006 Type Certificate No. A22NM Reissued: September 24, 2007 Production Certificate No. 704NM The basic required equipment as prescribed in the applicable airworthiness regulations must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. FAA Approved Airplane Flight Manual 2. Stall Warning indicator. 3. Cylinder head temperature gage. A22NM Page 9 of 18 REV 23 IV.a - Increased Gross Weight Variant, 2PCLM (Normal Category), Approved January 27, 2012 (The Increased Gross Weight variant is a model A-1C-180, 2PCLM.) Model A-1C-180, effective serial numbers 3000+ are eligible for an increased in max gross weight up to 2,250 lb. No structural modifications are required to accept this higher gross weight. The gross weight increase requires the appropriate airspeed indicator (per Aviat Aircraft Drawing No. 35401 or 38401 incorporating EO Nos. 4507 or 4508 respectively) to be installed; and the Airplane Flight Manual is replaced with the latest revision of the A-1C 180 2250 Approved Airplane Flight Manual. Engine Lycoming O-360-A1P (180 HP) Fuel 100/100LL grade aviation gasoline IVa – Increased Gross Weight Variant (cont’d) Engine Limits Refer to each propeller and propeller limits Propeller MTV-15-B/205-58 (includes spinner) (Constant Speed) and Propeller Limits Diameter not over 80.7 in., not under 79.9 in. Pitch setting at 30 in. station low 7° ± .2°, high 24.0° ± 1.0° Takeoff & maximum continuous power 2600 RPM (Engine de-rated to 175 HP for noise) Hartzell HC-C2YK-1BF/F7666A (Constant Speed) Diameter not over 76 in., not under 72 in. Pitch setting at 30 in. station low 11.7° ± .2°, high 29.0° ± 1.0 Takeoff & maximum continuous power 2700 RPM Placard required: "AVOID CONTINUOUS OPERATIONS BETWEEN 2000- 2250 RPM" Hartzell HC-C2YR-1BF/F8477-4 (Constant Speed) Diameter not over 80 in., not under 78 in. Pitch setting at 30 in. station low 10.3° ± .2°, high 30.9° ± 1.0 Takeoff & maximum continuous power 2600 RPM (Engine de-rated to 175 HP for noise) Hartzell spinner 836-60 or C3568-P (required for Hartzell props) Hartzell governor V3-6 or S-1-16 Airspeed Limits (CAS) Never Exceed 145 mph (126 knots) Maximum Structural Cruising 115 mph (100 knots) Maneuvering 113 mph (98 knots) Flaps Extended 81 mph (70 knots) C.G. Range (+74.8) to (+80.0) at 2250 lb (+72.3) to (+80.0) at 1781 lb and below Straight line variation between points given Empty wt. C.G. Range None Datum 60 in. forward of wing leading edge Leveling Means Cabin door, lower sill A22NM Page 10 of 18 REV 23 IVa – Increased Gross Weight Variant (cont’d) Maximum Weight 2250 lb No. of Seats 2 (1 at +72.5 and 1 at +99.0) Maximum baggage 50 lb (at +120.0) Fuel Capacity 52 gal. (two 26 gal. Tanks in wings at +84.0) 50 gal usable. See NOTE 1 for data on unusable fuel. Oil Capacity 8 quarts. (at +25.9) Control Surface Movements Elevator UP 29° ± 1° DOWN 15° ± 1° Ailerons UP 15.5° ± 2° DOWN 15.5° ± 2° Rudder LEFT 25° ± 2° RIGHT 25° ± 2° Flaps UP 0° DOWN 30° + 0°, -2° Serial Nos. Eligible 3000+ (See NOTE 25) Certification Basis Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 thru 23-31 (Normal Category) and FAR 36 amended thru 36-28. FAR 21 amended thru 21-57. Application for Type Certificate dated May 7, 2010 Type Certificate No. A22NM Reissued: January 27, 2012 Production Basis Production Certificate No. 704NM Equipment The basic required equipment as prescribed in the applicable airworthiness regulations must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. FAA Approved Airplane Flight Manual 2. Stall Warning indicator. 3. Cylinder head temperature gage. V - Model A-1C-200, 2PCLM (Normal Category), Approved September 24, 2007 The A-1C-200 is a derivative model of the A-1B. The A-1C-200 has a gross weight of 2200 lb. Structural modifications include updated landing gear per Aviat drawing 45017 (configurations: -501,-502,-503,-504,-505,- 506); and tail wheel configuration using 5-leaf spring or Alaska Bushwheel 3-leaf spring configuration per Aviat drawing 37340. An additional modification to the angle of the leading edge of the horizontal stabilizers down 3/10 of a degree using a new stabilizer “H” support tube is also incorporated. The A-1C-200 aircraft are equipped with Lycoming IO-360-A1D6 engine, new wing/extended flap and spade less ailerons, new sliding windows, and the new wing flap control handle. The C.G. envelope has been reduced forward and expanded aft. NOTE: See serial numbers eligible under this model. Engine Lycoming IO-360-A1D6 (200 HP) Fuel 100/100LL grade aviation gasoline Engine Limits Refer to each propeller and propeller limits A22NM Page 11 of 18 REV 23 V - Model A-1C-200, 2PCLM (cont’d) Propeller and Propeller Limits Airspeed Limits (CAS) C.G. Range Empty wt. C.G. Range Datum Leveling Means Maximum Weight No. of Seats Maximum baggage Fuel Capacity Oil Capacity Control Surface Movements Serial Nos. Eligible Certification Basis Production Basis HC-C2YR-1BF/F8477-4 (Constant Speed) Diameter not over 80 in., not under 78.0 in. Pitch setting at 30 in. station low 10.3° ± .2°, high 30.9° ± 1.0° Takeoff & maximum continuous power 2700 RPM MTV-15-B/205-58 (includes spinner) (Constant Speed) Diameter not over 80.7 in., not under 79.9 in. Pitch setting at 30 in. station low 7.0° ± .2°, high 24.0° ± 1.0° Takeoff & maximum continuous power 2650 RPM (Engine de-rated to 196 HP for noise) Hartzell spinner assembly 836-60 or C3568-P (Required with Hartzell props) Hartzell governor V3-6 or S-1-16 Never Exceed 153 mph (133 knots) Maximum Structural Cruising 119 mph (103 knots) Maneuvering 113 mph (98 knots) Flaps Extended 80 mph (70 knots) (+74.5) to (+81.0) at 2200 lb (+72.3) to (+81.0) at 1781 lb and below Straight line variation between points given None 60 in. forward of wing leading edge Cabin door, lower sill 2200 lb 2 (1 at +72.5 and 1 at +99.0) 50 lb (at +120.0) 52 gal. (two 26 gal. Tanks in wings at +84.0) 50 gal usable. See NOTE 1 for data on unusable fuel. 8 quarts. (at +25.9) Elevator UP 29° ± 1° DOWN 15° ± 1° Ailerons UP 15.5° ± 2° DOWN 15.5° ± 2° Rudder LEFT 25° ± 2° RIGHT 25° ± 2° Flaps UP 0° DOWN 30° + 0°, -2° 3000+ (See NOTE 25) Part 23 of the Federal Aviation Regulations dated February 1, 1965 as amended by 23-1 thru 23-31 (Normal Category) and FAR 36 amended thru 36-28. FAR 21 amended thru 21-57. Application for Type Certificate dated September 26, 2006 Type Certificate No. A22NM Reissued: September 24, 2007. Production Certificate No. 704NM A22NM Page 12 of 18 REV 23 V - Model A-1C-200, 2PCLM (cont’d) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations must be installed in the aircraft for certification. In addition, the following items of equipment are required: 1. FAA Approved Airplane Flight Manual 2. Stall Warning indicator. 3. Cylinder head temperature gage. V.a - Increased Gross Weight Variant, 2PCLM (Normal Category), Approved January 27, 2012 (The Increased Gross Weight variant is a model A-1C-200, 2PCLM.) Model A-1C-200, effective serial numbers 3000+ are eligible for an increased in max gross weight up to 2,250 lb. No structural modifications are required to accept this higher gross weight. The gross weight increase requires the appropriate airspeed indicator (per Aviat Aircraft Drawing No. 35401 or 38401 incorporating EO Nos. 4507 or 4508 respectively) to be installed; and the Airplane Flight Manual is replaced with the latest revision of the A-1C 200 2250 Approved Airplane Flight Manual. Engine Lycoming IO-360-A1D6 (200 HP) Fuel 100/100LL grade aviation gasoline Engine Limits Refer to each propeller and propeller limits Propeller HC-C2YR-1BF/F8477-4 (Constant Speed) and Propeller Limits Diameter not over 80 in., not under 78.0 in. Pitch setting at 30 in. station low 10.3° ± .2°, high 30.9° ± 1.0° Takeoff & maximum continuous power 2700 RPM MTV-15-B/205-58 (includes spinner) (Constant Speed) Diameter not over 80.7 in., not under 79.9 in. Pitch setting at 30 in. station low 7.0° ± .2°, high 24.0° ± 1.0° Takeoff & maximum continuous power 2650 RPM