TCDS A7EA

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A7EA This data sheet which is a part of type certificate No. A7EA prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder NZSkydive Limited Trading as Pacific Aerospace 333 Airport Road Hamilton 3282 New Zealand Type Certificate Holder Record Pacific Aerospace Ltd. transferred TC A7EA to NZSkydive Limited on November 29, 2021. Found Aircraft Canada, Inc. transferred TC A7EA to Pacific Aerospace Ltd on November 23, 2017. I - Model FBA-2C, 5 PCLM (Normal Category), Approved June 23, 1965 by the FAA and February 19, 1964 by the Canadian Department of Transport (DOT) Engine Lycoming O-540-A1C5 Fuel 91-96 minimum grade aviation gasoline Engine limits Maximum for all operations, 250 hp. at 2575 r.p.m. Full throttle at sea level Propeller and McCauley variable pitch Model 2D36C28/80MM-6 Propeller limits Diameter: Maximum 74 inches, minimum 73 inches No reduction in minimum size allowed Pitch setting at Station 30.0: low 15.7°, high 32.0° Constant speed governor Woodward 210395 Hartzell Constant Speed HC-927K-1D/8847-0 70 lb. (-63.0 in.) Diameter: maximum 88 inches, minimum 88 inches Pitch setting at Station 30.0 inches: low 12°, high 26.4° Woodward constant speed governor B210340 Airspeed limits Vne (never exceed) 155.3 m.p.h. (135 knots) (CAS) Vno (max. structural cruising) 123.3 m.p.h. (107 knots) VA (maneuvering) 130 m.p.h. (112.5 knots) Vfe (flaps extended) 108.0 m.p.h. (93.5 knots) C.G. range Landplane and Skiplane (See Note 4 for Ski Installations) (Landing Gear Fixed) Gross Weight Forward Limit Aft Limit 2850 lb. +17.0 in. +24.5 in. 2250 or less +15.3 in. +24.5 in. Seaplane (See Note 5 for Float Installations) Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 Rev. No. 11 11 8 8 11 8 8 8 8 11 8 10 8 8 8 8 8 A7EA Revision 11 NZSkydive Limited FBA-2C, FBA-2C1 FBA-2C2, FBA-2C3 FBA-2C4, FBA-2C3T FBA-2C4T March 30, 2022 A7EA Page 2 of 17 Serial Nos. eligible 3 to 27 inclusive. II - Model FBA-2C1, (Bush Hawk) (Normal Category), Approved March 3, 2000 by the FAA and March 5, 1999 by the Canadian Department of Transport (DOT) Engine Lycoming I0-540-D4A5 (260 HP) or Lycoming I0-540-L1C5 (300 HP) Fuel 100LL or 100 (Formerly 100/130) Grade aviation fuel Engine limits Maximum for all operations; Full throttle at sea level I0-540-D4A5: 260 HP at 2700 r.p.m. I0-540-L1C5: 300 HP at 2700 r.p.m. Propeller and Hartzell 3-blade variable pitch HC-C3YR-1RF/F8468A-2R Propeller Limits Diameter: Maximum 84 inches, Minimum 83 inches Pitch setting at Station 30.0: low 10.3° high 31.0° Constant Speed Governor, Hartzell V-5-4 Gross Weight Forward Limit Aft Limit 2850 lb. +17.0 in. +24.5 in. 2250 or less +15.3 in. +24.5 in. Straight line variation between points given Empty Weight C.G. Range None Datum Main landing gear beam center line M.A.C. 62.3 in. Leveling means Aircraft cabin floor level - laterally and longitudinally Maximum weight Landplane and Skiplane 2850 lb. Seaplane 2850 lb. (See Note 3 for eligibility at 3,000 lbs.) Minimum crew 1 Pilot Number of Seats 5, including pilot (2 at +17.8 in., 3 at +61.75 in.) Maximum baggage 150 lb. at +92.5 in. Fuel capacity 56.0 Imperial gallons (67.3 U.S. gallons) total (+22.2 in.) 28 Imperial gallons (33.6 U.S. gallons) each wing tank. 55.0 Imperial gallons (66.1 U.S. gallons) usable. Oil capacity 10.5 Imperial quarts (12.6 U.S. quarts) max. (-38.8 in.) Control surface Wing Flaps 0° up 32° down Movements Aileron 18° up 12° Elevator (0° Stab.) 29.5° up 21.5° Stabilizer 3° up 5° Rudder 30° left 30° down down down right A7EA Page 3 of 17 Airspeed Limits With 260 HP I0-540-D4A5 engine (CAS) Vne (never exceed) 162 m.p.h. (141 knots) Vno (max. structural cruising) 145 m.p.h. (126 knots) VA (maneuvering) 135 m.p.h. (117 knots) Vfe (flaps extended) 118 m.p.h. (103 knots) With 300 HP I0-540-L1C5 engine Vne (never exceed) 162 m.p.h. (141 knots) Vno (max. structural cruising) 145 m.p.h. (126 knots) VA (maneuvering) 135 m.p.h. (117 knots) Vfe (flaps extended) 118 m.p.h. (103 knots) C.G. range Landplane and Skiplane (Landing Gear Fixed) Gross Weight Forward Limit Aft Limit 3200 lbs. +17.0 in. +24.5 in. 1900 +17.0 in. +24.5 in. Seaplane Gross Weight Forward Limit Aft Limit 3500 lbs. +17.0 in. +23.5 in. 1900 +17.0 in. +23.5 in. Straight line variation between points given. Additional limitations for specific ski and float installations may be contained in Notes 4 and 5. Empty Weight None C.G. Range Datum Land Plane: Main Wheel Axle Sea Plane: Lower Forward Corner of Front Door M.A.C. 62.3 in. Leveling Means Aircraft cabin floor level – laterally and longitudinally. Maximum Weight Landplane and skiplane 3,200 lbs. Seaplane 3500 lbs. (see Note 5 for specific weight limitation with each float installation.) Minimum crew 1 Pilot Number of Seats 5, including pilot. (2 at +17.8 in., and 3 at +62 in.) Maximum Baggage 250 lbs. at 94 in. Fuel Capacity At +21.8 in Usable Liters 372 Imp. Gals. 81.9 U.S. Gals. 98.3 Unusable 6 1.4 1.7 Total 378 83.3 100.0 Oil Capacity 11.4 liters / 10 imperial quarts / 12 U.S. quarts maximum (at -40 in.) Control Surface Movements Wing Flaps Aileron 0° 18° up up 8,15,22,32 12° down down Elevator (0° Stab.) Stabilizer Rudder 29.5° 6° 30° up up left 21.5° 4° 30° down down right Serial Numbers Eligible 28 through 99 A7EA Page 4 of 17 III- Model FBA-2C2, (Bush Hawk XP) (Normal Category), Approved January 11, 2005 by the FAA and May 14, 2004 by the Canadian Department of Transport (DOT) Engine Lycoming I0-540-L1C5 (300 HP) Fuel 100LL or 100 (Formerly 100/130) Grade aviation fuel Engine limits Maximum for all operations 2700 r.p.m. Propeller and 1. Hartzell 3-blade variable pitch HC-C3YR-1RF/F8468A-2R Propeller Limits Diameter: Maximum 84 inches, Minimum 83 inches Pitch setting at Station 30.0: low 10.3° high 31.0° Constant Speed Governor, Hartzell V-5-4 2. Hartzell 3-blade variable pitch HC-C3YR-1RF/F8068 Diameter: Maximum 82 inches, Minimum 81 inches Pitch setting at Station 30.0: low 12.3° high 31.0° Constant Speed Governor, Hartzell V-5-4 Airspeed Limits Vne (never exceed) 182 m.p.h. (158 knots) Vno (max. structural cruising) 161 m.p.h. (140 knots) VA (maneuvering) 131 m.p.h. (114 knots) Vfe (flaps extended) 132 m.p.h. (115 knots) C.G. range Landplane (Landing Gear Fixed) Gross Weight Forward Limit Aft Limit 3500 lbs. +20.5 in. +24.5 in. 2750 lbs +17.0 in. +24.5 in. 1950 lbs +17.0 in. +24.5 in. Seaplane Gross Weight Forward Limit Aft Limit 3800 lbs. +20.5 in +23.5 in. 2750 lbs +17.0 in. +23.5 in. 2250 lbs +17.0 in. +23.5 in. Straight line variation between points given. Gross weight and c.g. may vary depending on the installation of Optional Equipment. Empty Weight None C.G. Range Datum Landplane: Main wheel axle. Seaplane: Lower forward corner of the front door. M.A.C. 62.3 in. Leveling Means Aircraft cabin floor level – laterally and longitudinally. Maximum Weight Landplane3,500 lbs. Seaplane 3,800 lbs. (see Note 5 for specific weight limitation with each float installation.) Minimum crew 1 Pilot Number of Seats 5, including pilot. (2 at +17.8 in., and 3 at +62 in.) Maximum Baggage 250 lbs. at 94 in. A7EA Page 5 of 17 Fuel Capacity At +21.8 in. Liters Imp. Gals. U.S. Gals. Usable 372 81.9 98.3 Unusable 6 1.4 1.7 Total 378 83.3 100.0 Oil Capacity 11.4 liters / 10 imperial quarts / 12 U.S. quarts maximum (at -40 in.) Control Surface Movements Wing Flaps Aileron 0° 18° up up 30° 12° down down Elevator (0° Stab.) 29.5° up 21.5° down Stabilizer 3° up *** 5° down *** Rudder 24° left 24° right *** UP and DOWN refer to the leading edge of the stabilizer Serial Numbers 100 and subsequent. Eligible IV. MODEL FBA-2C3 (Expedition E350) (Normal Category), Approved December 23, 2008 by the FAA and July 25, 2008 by the Canadian Department of Transport (DOT). This model is the 315 HP tricycle landing gear equipped version of the FBA-2C2. Engine Lycoming IO-580-B1A (315 HP) Fuel 100LL or 100 (Formerly 100/130) Grade aviation fuel Engine Limits Maximum 2700 r.p.m. for all operations Propeller and Hartzell 3-blade variable pitch HC-C3YR-1RF/F8068 Propeller Limits Diameter: Maximum 82 ins., Minimum 81 ins. Pitch setting at Station 30.0: Low 12.3° High 31.0° Constant Speed Governor, Hartzell V-5-4 Airspeed Limits Knots (CAS) V NE (Never Exceed) 188 VA (Maneuvering) 117 VNO (Max. Structural Cruise) 153 VFE Flaps Extended) 115 C.G. Range Landplane Gross Weight Fwd. Limit Aft Limit 3800 lbs. (1724 kg) +20.5 in. +24.5 in. 2600 lbs. (1179 kg) +15.0 in. +24.5 in. 2200 lbs. (997 kg) +15.0 in. +24.5 in. Straight line variation between points Seaplane See the Optional Equipment section for specific float installations. Empty Weight None C.G. Range Datum Landplane: ½” aft of the lower hinge pin on front door. Seaplane: Same as above. Levelling Means Aircraft cabin floor level - laterally and longitudinally. A7EA Page 6 of 17 Maximum Weight Landplane 3,800 lbs. (1724 kg) Seaplane 3,800 lbs. (1724 kg) *** *** Gross weight and C of G limits may vary depending on the option installed. Minimum Crew 1 Pilot Number of Seats 5, including pilot. (2 at +17.8 in., and 3 at +62 in.) Maximum Baggage 250 lbs. (113 kg) at 94 in. Fuel Capacity At +21.8 in. Litres U.S. Gals. Usable 372 98.3 Unusable 6 1.7 Total 378 100.0 Oil Capacity 10.4 litres / 11 U.S. quarts maximum (at -40 in.) Control Surface Wing Flaps 0° Up 30° Down Aileron 18° Up 12° Down Elevator (0 Stab.) 33° Up 22° Down Stabilizer 3° Up*** 5° Down*** Rudder 24° Left 28° Right *** Up and Down refer to the leading edge of the stabilizer Serial Numbers Serial number 300 and subsequent. Eligible V. MODEL FBA-2C4 (Normal Category), Approved July 2, 2012, by the FAA and June 5, 2012 by the Canadian Department of Transport (DOT). This model is a tail wheel landing gear version of the FBA-2C3. Engine Lycoming IO-580-B1A (315 HP) Fuel 100LL or 100 (Formerly 100/130) Grade aviation fuel Engine Limits Maximum 2700 r.p.m. for all operations Propeller and Hartzell 3-blade variable pitch HC-C3YR-1RF/F8068 Propeller Limits Diameter: Maximum 82 ins., Minimum 81 ins. Pitch setting at Station 30.0: Low 12.3° High 31.0° Constant Speed Governor, Hartzell V-5-4 Airspeed Limits Knots (CAS) V NE (Never Exceed) 188 VA (Maneuvering) 117 VNO (Max. Structural Cruise) 153 VFE Flaps Extended) 115 C.G. Range Landplane Gross Weight Fwd. Limit Aft Limit 3800 lbs. (1724 kg) +20.5 in. +24.5 in. 2600 lbs. (1179 kg) +15.0 in. +24.5 in. 2200 lbs. (997 kg) +15.0 in. +24.5 in. Straight line variation between points Seaplane See the Optional Equipment section for specific float installations. A7EA Page 7 of 17 Empty Weight None C.G. Range Datum Landplane: ½” aft of the lower hinge pin on front door. Seaplane: Same as above. Levelling Means Aircraft cabin floor level – laterally and longitudinally. Maximum Weight Landplane 3,800 lbs. (1724 kg) Seaplane 3,800 lbs. (1724 kg) *** *** Gross weight and C of G limits may vary depending on the option installed. Minimum Crew 1 Pilot Number of Seats 5, including pilot. (2 at +17.8 in., and 3 at +62 in.) Maximum Baggage 250 lbs. (113 kg) at 94 in. Fuel Capacity At +21.8 in. Litres U.S. Gals. Usable 372 98.3 Unusable 6 1.7 Total 378 100.0 Oil Capacity 10.4 litres / 11 U.S. quarts maximum (at -40 in.) Control Surface Wing Flaps 0° Up 30° Down Aileron 18° Up 12° Down Elevator (0 Stab.) 33° Up 22° Down Stabilizer 3° Up*** 5° Down*** Rudder 24° Left 28° Right *** Up and Down refer to the leading edge of the stabilizer Serial Numbers Serial number 4000 and subsequent. Eligible VI MODEL FBA-2C3T (Normal Category), Approved July 2, 2012, by the FAA and June 5, 2012 by the Canadian Department of Transport (DOT). This model is the 300 HP turbocharged engine equipped version of the FBA-2C3. Engine Lycoming TIO-540-AH1A (300 HP) Fuel 100LL or 100 (Formerly 100/130) Grade aviation fuel Engine Limits Maximum 2500 r.p.m. for all operations Propeller and Hartzell 3-blade variable pitch HC-C3YR-1RF/F8068+2 Propeller Limits Diameter: Maximum 84 ins., Minimum 83 ins. Pitch setting at Station 30.0: Low 12.3° High 41.5° Airspeed Limits Knots (CAS) V NE (Never Exceed) 188 from S/L to 14,000 ft MSL Linearly reducing from 188 @ 14,000 ft to 150 @ 25,000 ft. VA (Maneuvering) 117 VNO (Max. Structural Cruise) 153 from S/L to 14,000 ft MSL Linearly reducing from 153 @ 14,000 ft to 122 @ 25,000 ft. A7EA Page 8 of 17 VFE (Flaps Extended) 115 C.G. Range Landplane Gross Weight Fwd. Limit Aft Limit 3800 lbs. (1724 kg) +20.5 in. +24.5 in. 2600 lbs. (1179 kg) +15.0 in. +24.5 in. 2200 lbs. (997 kg) +15.0 in. +24.5 in. Straight line variation between points Seaplane See the Optional Equipment section for specific float installations. Empty Weight None C.G. Range Datum Landplane: ½” aft of the lower hinge pin on front door. Seaplane: Same as above. Levelling Means Aircraft cabin floor level – laterally and longitudinally. Maximum Weight Landplane3,800 lbs. (1724 kg) Seaplane 3,800 lbs. (1724 kg) *** *** Gross weight and C of G limits may vary depending on the option installed. Minimum Crew 1 Pilot Number of Seats 5, including pilot. (2 at +17.8 in., and 3 at +62 in.) Maximum Baggage 250 lbs. (113 kg) at 94 in. Fuel Capacity At +21.8 in. Litres U.S. Gals. Usable 372 98.3 Unusable 6 1.7 Total 378 100.0 Oil Capacity 10.4 litres / 11 U.S. quarts maximum (at -40 in.) Control Surface Wing Flaps 0° Up 30° Down Aileron 18° Up 12° Down Elevator (0 Stab.) 33° Up 22° Down Stabilizer 3° Up*** 5° Down*** Rudder 24° Left 28° Right *** Up and Down refer to the leading edge of the stabilizer Serial Numbers Serial number 0001 and subsequent. Eligible VII MODEL FBA-2C4T (Normal Category), Approved July 2, 2012, by the FAA and June 5, 2012 by the Canadian Department of Transport (DOT). This model is the 300 HP turbocharged engine equipped version of the FBA-2C4. Engine Lycoming TIO-540-AH1A (300 HP) Fuel 100LL or 100 (Formerly 100/130) Grade aviation fuel Engine Limits Maximum 2500 r.p.m. for all operations Propeller and Hartzell 3-blade variable pitch HC-C3YR-1RF/F8068+2 Propeller Limits Diameter: Maximum 84 ins., Minimum 83 ins. A7EA Page 9 of 17 Pitch setting at Station 30.0: Low 12.3° High 41.5° Airspeed Limits Knots (CAS) V NE (Never Exceed) 188 from S/L to 14,000 ft MSL Linearly reducing from 188 @ 14,000 ft to 150 @ 25,000 ft. VA (Maneuvering) 117 VNO (Max. Structural Cruise) 153 from S/L to 14,000 ft MSL Linearly reducing from 153 @ 14,000 ft to 122 @ 25,000 ft. VFE (Flaps Extended) 115 C.G. Range Landplane Gross Weight Fwd. Limit Aft Limit 3800 lbs. (1724 kg) +20.5 in. +24.5 in. 2600 lbs. (1179 kg) +15.0 in. +24.5 in. 2200 lbs. (997 kg) +15.0 in. +24.5 in. Straight line variation between points Seaplane See the Optional Equipment section for specific float installations. Empty Weight None C.G. Range Datum Landplane: ½” aft of the lower hinge pin on front door. Seaplane: Same as above. Levelling Means Aircraft cabin floor level – laterally and longitudinally. Maximum Weight Landplane3,800 lbs. (1724 kg) Seaplane 3,800 lbs. (1724 kg) *** *** Gross weight and C of G limits may vary depending on the option installed. Minimum Crew 1 Pilot Number of Seats 5, including pilot. (2 at +17.8 in., and 3 at +62 in.) Maximum Baggage 250 lbs. (113 kg) at 94 in. Fuel Capacity At +21.8 in. Litres U.S. Gals. Usable 372 98.3 Unusable 6 1.7 Total 378 100.0 Oil Capacity 10.4 litres / 11 U.S. quarts maximum (at -40 in.) Control Surface Wing Flaps 0° Up 30° Down Aileron 18° Up 12° Down Elevator (0 Stab.) 33° Up 22° Down Stabilizer 3° Up*** 5° Down*** Rudder 24° Left 28° Right *** Up and Down refer to the leading edge of the stabilizer Serial Numbers Serial number 0001 and subsequent. Eligible A7EA Page 10 of 17 Data Pertinent To All Models (Except As Indicated) Import Requirements Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document), and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2, Airworthiness Certification of Aircraft, for requirements for issuance of an airworthiness certificate for imported aircraft. Certification Basis FBA-2C CAR 3 dated May 15, 1956 and Amendments 3-1 to 3-7 inclusive. Type Certificate No. A7EA issued June 23, 1965. Date of Application for Type Certificate February 11, 1963. FBA-2C1 Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended by 23-1 through 23-6 except as follows: FAR 23.51; 23.65; 23.75; 23.77; 23.611; 23.619; 23.623; 23.683; 23.689; 23.775; 23.871; 23.954; 23.1147; 23.1323; and 23.1563 amended by amendment 23-7. FAR 23.1524 amended by amendment 23-10. FAR 23.771 and 23.1365 amended by amendment 23-14. FAR 23.607; 23.675; 23.685; 23.733; and 23.1309 amended by amendment 23-17. FAR 23.959 amended by amendment 23-18. FAR 23.1301 amended by amendment 23-20. FAR 23.1353; 23.1541; and 23.1559 amended by amendment 23-21. FAR 23.603; 23.605; 23.863; and 23.1545 amended by amendment 23-23. FAR 23.1529 amended by amendment 23-26. FAR 23.995; 23.1143; 23.777; 23.779; and 23.781 amended by amendment 23-29. FAR 23.1; 23.853; and 23.1165; amended by amendment 23-34. FAR 23.787 amended by amendment 23-36. FAR 23.1311 and 23.1321 amended by amendment 23-41. FAR 23.301; 23.331; 23.351; 23.421; 23.423; 23.425; 23.427; 23.441; 23.443; 23.677; 23.701; 23.735 and 23.831 amended by amendment 23-42. FAR 23.901; 23.903; 23.905; 23.925; 23.951; 23.953; 23.955; 23.957; 23.963; 23.965; 23.967; 23.971; 23.973; 23.975; 23.977; 23.991; 23.993; 23.997; 23.999; 23.1093; 23.1145; 23.1303; 23.1322; 23.1337; 23.1351; 23.1357; 23.1361; and 23.1385 amended by amendment 23-43. FAR 23.562(a) and 23.562(e) amended by amendment 23-44. FAR 23.33; 23.305; 23.321; 23.397; 23.561; 23.572; 23.613; 23.621; 23.655; 23.731; and 23.1549 amended by amendment 23-45. FAR 23.783; 23.805; 23.807 and 23.811 amended by amendment 23-46. FAR 36 dated December 1,1969, as amended by Amendment 36-1 through 36-22. FBA-2C2 The Certification Basis for the model FBA-2C1, except as follows: FAR 23.49; 23.141; and 23.867 amended by amendment 23-7. FAR 23.1397; 23.1401 amended by amendment 23-11. FAR 23.345; 23.723 amended by amendment 23-23. FAR 23.2 amended by amendment 23-36. FAR 23.1305; 23.1307; 23.1365; 23.1387; 23.1389; 23.1391; 23.1393; 23.1395, and 23.1431 amended by amendment 23-43. FAR 23.25; 23.207; and 23.473 amended by amendment 23-45. FAR 36 dated December 1,1969, as amended by Amendment 36-1 through 36-22. FBA-2C3 Part 23 of the U. S. Federal Aviation Regulations effective February 1, 1965, as amended by 23-1 through 23-6 except as follows: As amended by Amendment 23-7 23.141, 23.395, 23.505, 23.619, 23.623, 23.625, 23.683, 23.689, 23.726, 23.727, 23.871, 23.954, 23.1147 23.1505 A7EA Page 11 of 17 As amended by Amendment 23-10 23.1524 As amended by Amendment 23-11 23.1397, 23.1401 As amended by Amendment 23-14 23.507, 23.509, 23.771, 23.1017, 23.1182 As amended by Amendment 23-17 23.675, 23.685, 23.1125 As amended by Amendment 23-20 23.1301, 23.1327, 23.1547 As amended by Amendment 23-21 23.29, 23.1501, 23.1541 As amended by Amendment 23-23 23.603, 23.605 As amended by Amendment 23-26 23.1529 As amended by Amendment 23-29 23.995, 23.1143 As amended by Amendment 23-33 23.781 As amended by Amendment 23-34 23.1, 23.333, 23.863, 23.1165, 23.1523 As amended by Amendment 23-36 23.2 As amended by Amendment 23-42 23.331, 23.351, 23.421, 23.423, 23.425, 23.427, 23.445, 23.831 As amended by Amendment 23-43 23.905, 23.943 23.951, 23.957, 23.961, 23.967, 23.971, 23.977, 23.991, 23.993, 23.997, 23.999, 23.1011, 23.1103, 23.1123, 23.1145, 23.1193, 23.1303, 23.1307, 23.1322, 23.1331, 23.1357, 23.1385, 23.1387, 23.1389, 23.1391, 23.1393, 23.1395, 23.1431 As amended by Amendment 23-44 23.562(a), 23.562(e) As amended by Amendment 23-45 23.23, 23.305, 23.321, 23.361, 23.397, 23.485, 23.523, 23.525, 23.527, 23.529, 23.531, 23.613, 23.621, 23.655, 23.731, 23.733, 23.737, 23.751, 23.753, 23.773, 23.851, 23.1507, 23.1525, 23.1527, 23.1549, 23.1557 As amended by Amendment 23-46 23.805, 23.811 As amended by Amendment 23-48 23.301, 23.335, 23.337, 23.341, 23.343, 23.345, 23.347, 23.349, 23.371, 23.391, 23.393, 23.399, 23.441, 23.443, 23.455, 23.473, 23.499, 23.521, 23.561, 23.572, 23.573, 23.607, 23.611, 23.657, 23.673, 23.725, 23.865 As amended by Amendment 23-49 23.677, 23.701, 23.723, 23.729, 23.735, 23.745, 23.775, 23.783, 23.785, 23.787, 23.807, 23.853, 23.855, 23.867, 23.1309, 23.1311, 23.1321, 23.1323, 23.1351, 23.1353, 23.1359, 23.1361, 23.1365, 23.1383 As amended by Amendment 23-50 23.3, 23.25, 23.33, 23.45, 23.49, 23.51, 23.53, 23.63, 23.65, 23.69, 23.71, 23.73, 23.75, 23.77, 23.201, 23.203, 23.207, 23.237, 23.1325, 23.1511, 23.1521, 23.1543, 23.1545, 23.1553, 23.1555, 23.1559, 23.1563, 23.1567, 23.1581, 23.1583, 23.1585, 23.1587, 23.1589 As amended by Amendment 23-51 23.777, 23.779, 23.907, 23.925, 23.955, 23.959, 23.963, 23.965, 23.973, 23.975, 23.1041, 23.1043, 23.1047, 23.1091, 23.1093, 23.1105, 23.1107, 23.1121, 23.1181, 23.1183, 23.1191, 23.1337 As amended by Amendment 23-52 23.1305 As amended by Amendment 23-53 23.901 As amended by Amendment 23-54 23.903 Airworthiness Manual Chapter 516, Change 516-06, Volume I, Aircraft Noise, effective 23 November 1999. A7EA Page 12 of 17 For aircraft equipped with a Garmin G500, G500TXi or G600 avionics system (which includes a Garmin 430W, 530W, 6XX or 7XX Navigator), the additional certification basis, for installation specific items only, is amended to include the following regulations at the amendment level stated: 23.1303 as amended by Amendment 23-49 23.1307 as amended by Amendment 23-49 23.1308 as amended by Amendment 23-57 23.1431 as amended by Amendment 23-49 For aircraft equipped with an S-Tec autopilot system, the additional certification basis, for installation specific items only, is amended to include the following regulations at the amendment level stated: 23.1329 as amended by Amendment 23-49 23.1335 as amended by Amendment 23-20 FBA-2C4 The Certification Basis for the model FBA-2C3 with the addition of the following requirement: 23.497 Supplementary conditions for tail wheels (Amdt. 23-48) FBA-2C3T The Certification Basis for the model FBA-2C3 with the addition of the following requirements: 23-909 Turbocharger systems (Amdt 23-43) 23.939 Powerplant operating characteristics (Amdt 23-42) 23.1441 Oxygen equipment and supply (Amdt 23-43) 23.1443 Minimum mass flow of supplemental oxygen (Amdt. 23-62) 23.1445 Oxygen distribution system (Amdt. 23-62) 23.1447 Equipment standards for oxygen dispensing units (Amdt. 23-62) 23.1449 Means for determining use of oxygen (Amdt. 23-9) 23.1451 Fire protection for oxygen equipment (Amdt. 23-49) 23.1453 Protection of oxygen equipment from rupture (Amdt. 23-49) FBA-2C4T The Certification Basis for the model FBA-2C3 with the addition of the following requirements: 23.497 Supplementary conditions for tail wheels (Amdt. 23-48) 23-909 Turbocharger systems (Amdt 23-43) 23.939 Powerplant operating characteristics (Amdt 23-42) 23.1441 Oxygen equipment and supply (Amdt 23-43) 23.1443 Minimum mass flow of supplemental oxygen (Amdt. 23-62) 23.1445 Oxygen distribution system (Amdt. 23-62) 23.1447 Equipment standards for oxygen dispensing units (Amdt. 23-62) 23.1449 Means for determining use of oxygen (Amdt. 23-9 23.1451 Fire protection for oxygen equipment (Amdt. 23-49) 23.1453 Protection of oxygen equipment from rupture (Amdt. 23-49) Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification