TYPE CERTIFICATE DATA SHEET NO. A7CE

II - Model 401, Model 401A, Model 401B (cont'd) Airspeed Limits Maneuvering 180 m.p.h. (156 knots) (CAS) Maximum structural cruising 230 m.p.h. (200 knots) Never exceed 266 m.p.h. (231 knots) Landing gear operating 160 m.p.h. (139 knots) Landing gear extended 160 m.p.h. (139 knots) Flaps extended 15° 180 m.p.h. (156 knots) Flaps extended 45° 160 m.p.h. (139 knots) Minimum control 95 m.p.h. ( 83 knots) C.G. Range (Landing (+150.8) to (+158.1) at 6300 lb. Gear Extended) (+158.5) at 5900 lb. or less (+147.5) at 5000 lb. or less Straight line variation between points given Landing gear retracted moment change: +837 in.-lb. Empty Wt. C.G. Range None Leveling Means External screw heads on right side of fuselage at stations +213.65 and +238.00 on W.L. +93.80 Maximum Weight Landing 6200 lb., takeoff 6300 lb. No. of Seats 6, 7 or 8 (2 at +137.0, 2 at +175.6, 2 at +215.5, 1 or 2 at +238.0) (See manufacturer's equipment list for optional seating arrangements) Maximum Baggage 350 lb. (+71.0), 240 lb. (+186.0), 340 lb. (+246.5) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. ea., 50 gal. usable at +152.0) See NOTE 1 for data on unusable fuel Oil Capacity 26 qt. (13 qt. in ea. engine at +113.5; usable 6.5 qt. per engine) See NOTE 1 for data on undrainable oil Control Surface Movements Wing flaps Down 45°, +1°, -0° Main surfaces Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 25°, +1°, -0° Down 15°, +1°, -0° Rudder Right 32°, +1°, -0° Left 32°, +1°, -0° (Read degrees normal to rudder hinge line) Tab (main surface in neutral) Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 5°, +1°, -0° Down 30°, +1°, -0° Rudder Right 7°, +1°, -0° Left 9°, +1°, -0° (Read degrees normal to rudder hinge line) Serial Nos. Eligible Model 401: 401-0001 through 401-0322 Model 401A: 401A0001 through 401A0132 Model 401B: 401B0001 through 401B0221 III - Model 402 (Normal Category), Approved September 20, 1966 Model 402A (Normal Category), Approved January 3, 1969 Model 402B (Normal Category), Approved November 12, 1969 Engines Two Continental TSIO-520-E or TSIO-520-EB (In any combination) Fuel Grade 100 or 100LL aviation gasoline Page 5 of 24 A7CE, Rev. 47 III - Model 402, Model 402A, Model 402B (cont'd) Engine Limits For all operations, 2700 r.p.m. (300 hp.) 34.5 in. Hg. Mp. up to critical altitude of 16,000 ft. in standard atmosphere. Above 16,000 ft. the following maximum Mp. applies for maximum r.p.m. Altitude (ft.) Max. Allowable Mp. (in. Hg.) 16,000 34.5 18,000 31.8 20,000 29.5 22,000 27.3 24,000 25.1 26,000 23.0 28,000 22.0 30,000 19.0 Propeller and Two McCauley full-feathered 3-bladed propeller installations Propeller Limits (a) McCauley hub 3AF32C87 with 82NC-5.5 blades or McCauley hub 3AF32C504 with 82NEA-5.5 blades Diameter: not over 76.5 in., not under 74.0 in. (no further reduction permitted) Pitch settings at 30 in. station: low 14.2°, +0.2° feathering 81.2°, +0.3° (b) Model 402, 402A and 402B, S/N 402B0001 thru 402B1200 Hydraulic governor, Woodward B210444, C210439, B210446F or A210529H; McCauley DCF290D1/T3, DCF290D2/T3, DCFS290D1/T3, DCFS290D2/T3, DCFU290D1/T3, DCFU290D2/T3, DCFUS290D1/T3, DCFUS290D2/T3, DCF290D7/T3, DCFS290D7/T3,DCFU290D7/T3, DCFU290D13/T3, DCFUS290D7/T3, or DCFUS290D13/T3. Model 402B, S/N 402B1201 through 402B1300 Hydraulic governor, Woodward B210444, C210439; McCauley DCF290D1/T3, DCF290D2/T3, DCFU290D1/T3, DCFU290D2/T3, DCFS290D4/T3, DCFUS290D4/T3, DCFS290D5/T3, DCFUS290D5/T3, DCF290D7/T3, DCFU290D7/T3, DCFS290D7/T3, DCFUS290D7/T3, DCFU290D13/T3, or DCFUS290D13/T3. For aircraft modified by SK414-10B, DCFS290D6/T3, DCFUS290D6/T3, DCFS290D8/T3 or DCFUS290D8/T3. Model 402B, S/N 402B1301 and up Hydraulic governor, Woodward B210444, C210439; McCauley DCF290D1/T3, DCF290D2/T3, DCFU290D1/T3, DCFU290D2/T3, DCFS290D4/T3, DCFUS290D4/T3, DCFS290D6/T3, DCFUS290D6/T3, DCF290D7/T3, DCFU290D7/T3, DCFS290D7/T3, DCFUS290D7/T3, DCFS290D8/T3, DCFUS290D8/T3, DCFU290D13/T3, DCFUS290D12/T3, or DCFUS290D13/T3. (c) Propeller spinner and bulkhead assembly, McCauley D-3534/D-3537, D-3534/D-3796, or D-5212/D5214. A7CE, Rev. 47 Page 6 of 24 III - Model 402, Model 402A, Model 402B (cont'd) Airspeed Limits Model 402, S/N 402-0001 and up (CAS) Model 402A, S/N 402A0001 and up Model 402B, S/N 402B0001 through 402B0500 Maneuvering 180 m.p.h. (156 knots) Maximum structural cruising 230 m.p.h. (200 knots) Never exceed 266 m.p.h. (231 knots) Landing gear operating 160 m.p.h. (139 knots) Landing gear extended 160 m.p.h. (139 knots) Airspeed Limits (Cont.) Flaps extended 15° 180 m.p.h. (156 knots) (CAS) Flaps extended 45° 160 m.p.h. (139 knots) Minimum control 95 m.p.h. ( 83 knots) Model 402B, S/N 402B0501 through 402B1000 Maneuvering 156 KCAS (180 m.p.h.) Maximum structural cruising 200 KCAS (230 m.p.h.) Never exceed 231 KCAS (266 m.p.h.) Landing gear operating 140 KCAS (161 m.p.h.) Landing gear extended 140 KCAS (161 m.p.h.) Flaps extended 15° 160 KCAS (184 m.p.h.) Flaps extended 45° 140 KCAS (161 m.p.h.) Minimum control 83 KCAS ( 95 m.p.h.) (IAS) Model 402B, S/N 402B1001 and up Maneuvering 156 KIAS (180 m.p.h.) Maximum structural cruising 199 KIAS (229 m.p.h.) Never exceed 230 KIAS (265 m.p.h.) Landing gear operating 140 KIAS (161 m.p.h.) Landing gear extended 140 KIAS (161 m.p.h.) Flaps extended 15° 160 KIAS (184 m.p.h.) Flaps extended 45° 140 KIAS (161 m.p.h.) Minimum control 82 KIAS ( 94 m.p.h.) C.G. Range (Landing (+150.8) to (+159.7) at 6300 lb. Gear Extended) (+160.2) at 5900 lb. or less (+147.5) at 5000 lb. or less Straight line variation between points given Landing gear retracted moment change: +837 in.-lb. Empty Wt. C.G. Range None Leveling Means External screw heads on right side of fuselage at stations +213.65 and +238.00 on W.L. +93.80 Maximum Weight Models 402, 402A, 402B, S/N 402B0001 through 402B1300 Landing 6200 lb., takeoff 6300 lb. Model 402B, S/N 402B1301 and up Landing 6200 lb., ramp 6335 lb., takeoff 6300 lb. No. of Seats Model 402 9 (2 at +137.0, 2 at +166.0, 2 at +193.0, 2 at +220.0, 1 at +247.0) Model 402A and 402B, S/N 402B0001 through 402B0300 9 or 10 (2 at +137.0, 2 at +166.0, 2 at +193.0, 2 at +220.0, 1 or 2 at +247.0) Page 7 of 24 A7CE, Rev. 47 III - Model 402, Model 402A, Model 402B (cont'd) Model 402B, S/N 402B0301 and up 6, 7 or 8 (2 at +137.0, 2 at +175.0, 2 at +218.0, 1 or 2 at +261.0) 9 (with photographic provisions option) (2 at +137.0, 2 at +162.0, 2 at +190.0, 2 at +218.0, 1 at +246.0) 10 (2 at +137.0, 2 at +162.0, 2 at +190.0, 2 at +218.0, 2 at +246.0) (See manufacturer's equipment list for optional seating arrangements) Maximum Baggage Models 402, 402A and 402B, S/N 402B0001 through 402B0300 350 lb. (+71.0), 240 lb. (+186.0), 170 lb. (+247.0) Model 402B, S/N 402B0301 and up 250 lb. (+32.0), 350 lb. (+71.0), 240 lb. (+186.0), 400 lb. (+266.0), 100 lb. (+282.0) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. ea., 50 gal. usable at +152.0) See NOTE 1 for data on unusable fuel Oil Capacity 26 qt. (13 qt. in ea. engine at +113.5; usable 6.5 qt. per engine) See NOTE 1 for data on undrainable oil Control Surface Movements Wing flaps Down 45°, +1°, -0° Main surfaces Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 25°, +1°, -0° Down 15°, +1°, -0° Rudder Right 32°, +1°, -0° Left 32°, +1°, -0° (Read degrees normal to rudder hinge line) Tab (main surface in neutral) Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 5°, +1°, -0° Down 30°, +1°, -0° Rudder Right 7°, +1°, -0° Left 9°, +1°, -0° (Read degrees normal to rudder hinge line) Serial Nos. Eligible Model 402: 402-0001 through 402-0322 Model 402A: 402A0001 through 402A0129 Model 402B: 402B0001 through 402B1384 IV - Model 421 (Normal Category), Approved May 1, 1967 Model 421A (Normal Category), Approved November 19, 1968 Engines Two Continental GTSIO-520-D, reduction gear ratio .667:1 Fuel Grade 100 or 100LL aviation gasoline Engine Limits For all operations, 2275 propeller r.p.m. (375 hp.) 39.5 in. Hg. Mp. up to critical altitude of 16,000 ft. in standard atmosphere. Above 16,000 ft. the following maximum Mp. applies for maximum r.p.m. Model 421 Model 421A Altitude (ft.) Max. Allowable Mp. (in. Hg.) Altitude (ft.) Max. Allowable Mp. (in. Hg.) 16,000 39.5 16,000 39.5 18,000 32.5 18,000 37.5 20,000 32.5 20,000 35.5 22,000 30.0 22,500 32.5 24,000 27.0 24,000 30.5 26,000 24.5 26,000 28.0 28,000 22.0 28,000 25.5 30,000 20.0 30,000 23.0 A7CE, Rev. 47 Page 8 of 24 IV - Model 421, Model 421A (cont'd) Propeller and Two McCauley full-feathered 3-bladed propeller installations Propeller Limits (a) McCauley hub 3AF34C92 with 90LF-0 blades or McCauley hub 3AF37C516 with 90LFB-0 blades. Diameter: not over 90.0 in., not under 88.0 in. (no further reduction permitted) Pitch settings at 30 in. station: low 16.9°, +0.2° feathering 84.5°, +0.3°, (b) Hydraulic Governor Woodward 210594, 210595, 210596, or 210597. (c) Propeller spinner and bulkhead assembly, McCauley D-3573/D-3576, for use with C92 Model propeller, or McCauley D-7229 spinner and bulkhead assembly for use with C516 Model propeller. Airspeed Limits Maneuvering 184 m.p.h. (160 knots) (CAS) Maximum structural cruising 230 m.p.h. (200 knots) Never exceed 272 m.p.h. (236 knots) Landing gear operating 165 m.p.h. (143 knots) Landing gear extended 165 m.p.h. (143 knots) Flaps extended 15° 180 m.p.h. (156 knots) Flaps extended 45° 165 m.p.h. (143 knots) Minimum control 106.5 m.p.h. (93 knots) C.G. Range (Landing Model 421 Model 421A Gear Extended) (+151.9) to (+155.5) at 6800 lb. (+152.1) to (+155.5) at 6840 lb. (+155.7) at 6400 lb. or less (+155.7) at 6500 lb. or less (+144.3) at 5200 lb. or less (+144.3) at 5200 lb. or less Straight line variation between points given Landing gear retracted moment change: +889 in.-lb. Empty Wt. C.G. Range None Leveling Means External screw heads on right side of fuselage at stations +213.29 and +238.55 on W.L. +93.80 Maximum Weight Model 421 Landing 6500 lb., takeoff 6800 lb. (See NOTE 4 for takeoff 6840 lb.) Model 421A Landing 6500 lb., takeoff 6840 lb. No. of Seats Model 421 6 (2 at +137.0, 2 at +175.5, 2 at +215.5) Model 421A 6 or 7 (2 at +137.0, 2 at +175.5, 2 at +215.5, 1 at +246.5) (See manufacturer's equipment list for optional seating arrangement) Maximum Baggage 350 lb. (+71.0), 240 lb. (+186.0), 340 lb. (+246.5) Fuel Capacity 175 gal. (2 wing tip tanks, 51 gal. ea., 50 gal. usable at +152.0 and 2 wing tanks, 36.5 gal. ea., 35 gal. usable at +164.0) See NOTE 1 for data on unusable fuel Oil Capacity 26 qt. (13 qt. in ea. engine at +115.4; usable 7.0 qt. per engine) See NOTE 1 for data on undrainable oil Page 9 of 24 A7CE, Rev. 47 IV - Model 421, Model 421A (cont'd) Control Surface Movements Wing flaps Down 45°, +1°, -0° Main surfaces Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 25°, +1°, -0° Down 15°, +1°, -0° Rudder Right 25°, +1°, -0° Left 25°, +1°, -0° (Read degrees normal to rudder hinge line) Tab (main surface in neutral) Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 10°, +1°, -0° Down 26°, +1°, -0° Rudder Right 11°, +1°, -0° Left 16°, +1°, -0° (Read degrees normal to rudder hinge line) Serial Nos. Eligible Model 421: 421-0001 through 421-0200 Model 421A: 421A0001 through 421A0158 V - Model 414 (Normal Category), Approved September 24, 1969 Engines Two Continental TSIO-520-J or TSIO-520-JB (In any combination) (S/N 414-0001 through 414-0800) Two Continental TSIO-520-N or TSIO-520-NB (In any combination) (S/N 414-0801 and up) Fuel Grade 100 or 100LL aviation gasoline Engine Limits For all operations, 2700 r.p.m. (310 hp.) 36.0 in. Hg. Mp. (S/N 414-0001 through 414-0800) 38.0 in. Hg. Mp. (S/N 414-0801 and up) up to critical altitude of 20,000 ft. in standard atmosphere. Above 20,000 ft. the following maximum Mp. applies for maximum r.p.m. S/N 414-0001 through 414-0800 Altitude (ft.) Max. Allowable Mp. (in. Hg.) 20,000 36.0 22,000 33.6 24,000 31.2 26,000 28.8 28,000 26.4 30,000 24.0 S/N 414-0801 and up Altitude (ft.) Max. Allowable Mp. (in. Hg.) 20,000 38.0 22,000 35.2 24,000 32.3 26,000 29.8 28,000 27.4 30,000 25.0 Propeller and Two McCauley full-feathered 3-bladed propeller installations Propeller Limits (a) McCauley hub 3AF32C93 with 82NC-5.5 blades or McCauley hub 3AF32C505 with 82NEA-5.5 blades Diameter: not over 76.5 in., not under 74.5 in. (S/N 414-0001 through S/N 414-0800), not under 75.0 in. (S/N 414-0801 and up) (no further reduction permitted) Pitch settings at 30 in. station: low 14.9°, +0.2°, feathering 81.2°, +0.3° A7CE, Rev. 47 Page 10 of 24 V - Model 414 (Normal Category), Approved September 24, 1969 Propeller and (b) Model 414 S/N 414-0001 thru 414-0800 Propeller Limits Hydraulic governor, Woodward B210444, C210439, B210446F, or A210529H McCauley DCF290D1/T3,DFC290D2/T3, DCF290D7/T3, DCFU290D1/T3, DCFS290D1/T3, DCFUS290D1/T3, DCFS290D2/T3, DCFU290D2/T3, DCFU290D7/T3, DCFU290D13/T3, DCFS290D7/T3, DCFUS290D2/T3, DCFUS290D7/T3 or DCFUS290D13/T3 Model 414 S/N 414-0801 and up McCauley DCFS290D4/T3, DCFUS290D4/T3, DCFS290D5/T3, DCFUS290D5/T3, DCFS290D7/T3, or DCFUS290D7/T3, DCFS290D8/T3, DCFUS290D8/T3, DCFUS290D12/T3, or DCFUS290D13/T3 (c) Propeller spinner and bulkhead assembly, McCauley D-3534/D-3537, D-3534/D-3796, or D-5212/D-5214. Airspeed Limits S/N 414-0001 through 414-0450 (CAS) Maneuvering 180 m.p.h. (156 knots) Maximum structural cruising 230 m.p.h. (200 knots) Never exceed 266 m.p.h. (231 knots) Flaps extended 15° 180 m.p.h. (157 knots) Flaps extended 45° 160 m.p.h. (139 knots) Landing gear operating 160 m.p.h. (139 knots) Landing gear extended 160 m.p.h. (139 knots) Minimum control 97 m.p.h. ( 84 knots) S/N 414-0451 through 414-0800 Maneuvering 156 KCAS (180 m.p.h.) Maximum structural cruising 200 KCAS (230 m.p.h.) Never exceed 231 KCAS (266 m.p.h.) Flaps extended 15° 160 KCAS (184 m.p.h.) Flaps extended 45° 140 KCAS (161 m.p.h.) Landing gear operating 140 KCAS (161 m.p.h.) Landing gear extended 140 KCAS (161 m.p.h.) Minimum control 84 KCAS ( 97 m.p.h.) (IAS) S/N 414-0801 and up Maneuvering 160 KIAS (184 m.p.h.) Maximum structural cruising 205 KIAS (236 m.p.h.) Never exceed 236 KIAS (272 m.p.h.) Flaps extended 15° 164 KIAS (189 m.p.h.) Flaps extended 45° 147 KIAS (169 m.p.h.) Landing gear operating 143 KIAS (165 m.p.h.) Landing gear extended 143 KIAS (165 m.p.h.) Minimum control 82 KIAS ( 94 m.p.h.) C.G. Range (Landing (+150.9) to (+159.7) at 6350 lb. Gear Extended) (+160.2) at 5950 lb. or less (+147.5) at 5000 lb. or less Straight line variation between points given Landing gear retracted moment change: +837 in.-lb. Empty Wt. C.G. Range None Leveling Means External screw heads on right side of fuselage at stations +213.29 and +238.55 on W.L. +93.80 Page 11 of 24 A7CE, Rev. 47 V - Model 414 (cont'd) Maximum Weight Landing 6200 lb., takeoff 6350 lb. No. of Seats S/N 414-0001 through 414-0350 6 or 7 (2 at +137.0, 2 at +175.5, 2 at +215.5, 1 at +246.5) S/N 414-0351 and up 6 (2 at +137.0, 2 at +175.0, 2 at +218.0) 7 (with toilet option) (2 at +137.0, 2 at +175.0, 2 at +218.0, 1 at +250.0) (See manufacturer's equipment list for optional seating arrangements) Maximum Baggage S/N 414-0001 through 414-0350 350 lb. (+71.0), 240 lb. (+186.0), 340 lb. (+246.5) S/N 414-0351 and up 350 lb. (+71.0), 240 lb. (+186.0), 400 lb. (+266.0), 100 lb. (+282.0) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. ea., 50 gal. usable at +152.0) See NOTE 1 for data on unusable fuel Oil Capacity 26 qt. (13 qt. in ea. engine at +113.5; usable 6.5 qt. per engine) See NOTE 1 for data on undrainable oil Control Surface Movements Wing flaps Down 45°, +1°, -0° Main surfaces Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 25°, +1°, -0° Down 15°, +1°, -0° Rudder Right 32°, +1°, -0° Left 32°, +1°, -0° (Read degrees normal to rudder hinge line) Tab (main surface in neutral) Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 5°, +1°, -0° Down 30°, +1°, -0° Rudder Right 11°, +1°, -0° Left 16°, +1°, -0° (Read degrees normal to rudder hinge line) Serial Nos. Eligible 414-0001 through 414-0965 VI - Model 421B, Golden Eagle, (Normal Category), Approved April 28, 1970 Engines Two Continental GTSIO-520-H reduction gear ratio .667:1 Fuel Grade 100 or 100LL aviation gasoline Engine Limits For all operations, 2275 propeller r.p.m. (375 hp.) 39.5 in. Hg. Mp. up to critical altitude of 18,000 ft. in standard atmosphere. Above 18,000 ft. the following maximum Mp. applies for maximum r.p.m.: Altitude (ft.) Max. Allowable Mp. (in. Hg.) 18,000 39.5 20,000 37.5 22,000 35.5 24,000 33.5 25,000 32.5 26,000 31.3 28,000 28.5 30,000 25.5 A7CE, Rev. 47 Page 12 of 24 VI - Model 421B (cont'd) Propeller and Two McCauley full-feathered 3-bladed propeller installations Propeller Limits (a) McCauley hub 3AF34C92 with 90LF-0 blades or McCauley hub 3AF37C516 with 90LFB-0 blades Diameter: not over 90.0 in., not under 88.0 in. (no further reduction permitted) Pitch settings at 30 in. station: low 16.9°, +0.2° feathering 84.5°, +0.3° (b) Model 421B S/N 421B0001 thru 421B0500 Hydraulic governor Woodward 210594, 210595, 210596 or 210597 Model 421B S/N 421B0501 and up McCauley DCF290D2/T4, DFC7290D2/T4, DCFS290D2/T4, DCFUS290D2/T4, DCF290D7/T4, DCFU290D7/T4, DCFS290D7/T4, DCFUS290D7/T4, DCFU290D13/T4 or DCFUS290D13/T4. (c) Propeller spinner and bulkhead assembly, McCauley D-3534/D-3796. Airspeed Limits Model 421B: S/N 421B0001 through 421B0500 (CAS) Maneuvering 175 m.p.h. (152 knots) Maximum structural cruising 230 m.p.h. (200 knots) Never exceed 274 m.p.h. (238 knots) Landing gear operating 165 m.p.h. (143 knots) Landing gear extended 165 m.p.h. (143 knots) Flaps extended 15° (S/N 421B0001 through 421B0200) 180 m.p.h. (156 knots) Flaps extended 15° (S/N 421B0201 through 421B0500) 200 m.p.h. (174 knots) Flaps extended 45° 165 m.p.h. (143 knots) Minimum control 100 m.p.h. ( 87 knots) Model 421B: S/N 421B0501 and up Maneuvering 152 KCAS (175 m.p.h.) Maximum structural cruising 200 KCAS (230 m.p.h.) Never exceed 238 KCAS (274 m.p.h.) Landing gear operating 145 KCAS (167 m.p.h.) Landing gear extended 145 KCAS (167 m.p.h.) Flaps extended 15° 175 KCAS (202 m.p.h.) Flaps extended 45° 145 KCAS (167 m.p.h.) Minimum control (S/N 421B0501 through 421B0800) 87 KCAS (100 m.p.h.) Minimum control (S/N 421B0801 and up) 82 KCAS ( 94 m.p.h.) C.G. Range (Landing S/N 421B0001 through 421B0200 Gear Extended) 6, 7, or 8 Place 10 Place (+151.8) to (+156.4) at 7250 lb. (+151.8) to (+157.7) at 7250 lb. (+156.7) at 6850 lb. or less (+158.0) at 6850 lb. or less (+147.1) at 6100 lb. or less (+147.1) at 6100 lb. or less S/N 421B0201 and up (+152.6) to (+156.5) at 7450 lb. (+152.6) to (+157.8) at 7450 lb. (+156.7) at 7050 lb. or less (+158.0) at 7050 lb. or less (+147.1) at 6100 lb. or less (+147.1) at 6100 lb. or less Straight line variation between points given Landing gear retracted moment change: +889 in.-lb. Page 13 of 24 A7CE, Rev. 47 VI - Model 421B (cont'd) Empty Wt. C.G. Range None Leveling Means External screw heads on right side of fuselage at stations +213.9 and +238.55 on W.L. +93.80 Maximum Weight Landing 7200 lb., takeoff 7250 lb. (S/N 421B0001 through 421B0200) Landing 7200 lb., takeoff 7450 lb. (S/N 421B0201 and up) No. of Seats S/N 421B0001 through 421B0300 6, 7, or 8 (2 at +137.0, 2 at +175.5, 2 at +215.5, 2 at +245.7) or 10 (2 at +137.0, 2 at +161.0, 2 at +190.0, 2 at +218.0, 2 at +249.0) S/N 421B0301 and up 6, 7, or 8 (2 at +137.0, 2 at +175.0, 2 at +218.0, 2 at +261.0) or 10 (2 at +137.0, 2 at +162.0, 2 at +190.0, 2 at +218.0, 2 at +246.0) (See manufacturer's equipment list for optional seating arrangements) Maximum Baggage S/N 421B0001 through 421B0300 250 lb. (+32.0), 350 lb. (+71.0), 400 lb. (+186.0), 340 lb. (+246.5) S/N 421B0301 and up 250 lb. (+32.0), 350 lb. (+71.0), 400 lb. (+186.0), 400 lb. (+266.0), 100 lb. (+282.0) Fuel Capacity 175 gal. (2 wing tip tanks, 51 gal. ea., 50 gal. usable at +152.0 and 2 wing tanks, 36.5 gal. ea., 35 gal. usable at +164.0) See NOTE 1 for data on unusable fuel Oil Capacity 26 qt. (13 qt. in ea. engine at +115.4; usable 7.0 qt. per engine) See NOTE 1 for data on undrainable oil Control Surface Movements Wing flaps Down 45°, +1°, -0° Main surfaces Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 25°, +1°, -0° Down 15°, +1°, -0° Rudder Right 25°, +1°, -0° Left 25°, +1°, -0° (S/N 421B0001 through 421B0800) Right 32°, +1°, -0° Left 32°, +1°, -0° (S/N 421B0801 and up) (Read degrees normal to rudder hinge line) Tab (main surface in neutral) Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 12°, +1°, -0° Down 20°, +1°, -0° Rudder Right 11°, +1°, -0° Left 16°, +1°, -0° (Read degrees normal to rudder hinge line) Serial Nos. Eligible 421B0001 through 421B0970 VII - Model 421C, Golden Eagle, (Normal Category), Approved October 28, 1975 Engines Two Continental GTSIO-520-L reduction gear ratio .667:1 (S/N 421C0001 through 421C1000) Two Continental GTSIO-520-N reduction gear ratio .667:1 (S/N 421C1001 and up) Fuel Grade 100 or 100LL aviation gasoline A7CE, Rev. 47 Page 14 of 24 VII - Model 421C (cont'd) Engine Limits For all operations, 2235 propeller r.p.m. (375 hp.) 39.0 in. Hg. Mp. up to critical altitude of 20,000 ft. in standard atmosphere. Above 20,000 ft. the following maximum Mp. applies for maximum r.p.m.: Altitude (ft.) Max. Allowable Mp. (in. Hg.) 20,000 39.0 22,000 36.5 24,000 34.0 25,000 32.5 26,000 31.0 28,000 28.0 30,000 25.0 Propeller and Two McCauley full-feathering 3-bladed propeller installations Propeller Limits (a) McCauley hub 3FF32C501 with 90UMB-0 blades Diameter: not over 90.0 in., not under 88.0 in. (no further reduction permitted) Pitch settings at 30 in. station: low 16.6°, +0.2°, feathering 84.6°, +0.3° (b) S/N 421C0001 through 421C0800 Hydraulic Governor McCauley DCF290D2/T6, DCFU290D2/T6, DCFS290D2/T6, DCFUS290D2/T6, DCF290D7/T6, DCFU290D7/T6 or DCFU290D13/T6, DCFS290D7/T6, DCFUS290D7/T6 or DCFUS290D13/T6 S/N 421C0801 and up Hydraulic Governor McCauley DCF290D7/T6, DCFU290D7/T6 or DCFU290D13/T6, DCFS290D9/T6, DCFUS290D9/T6 (c) Propeller spinner and bulkhead assembly, McCauley D-3534/D-4506 or McCauley D-5212/D-5217 Airspeed Limits Maneuvering 151 KIAS (174 m.p.h.) (IAS) Maximum structural cruising 201 KIAS (231 m.p.h.) Never exceed 240 KIAS (276 m.p.h.) Landing gear operating 176 KIAS (203 m.p.h.) Landing gear extended 176 KIAS (203 m.p.h.) Flaps extended 15° 176 KIAS (203 m.p.h.) Flaps extended 45° 146 KIAS (168 m.p.h.) Minimum control 80 KIAS ( 92 m.p.h.) C.G. Range (Landing 6, 7, 8, 9 or 10 Place Gear Extended) (+152.6) to (+158.0) at 7450 lb. (+147.1) at 6100 lb. or less Straight line variation between points given Landing gear retracted moment change: +917 in.-lb. (S/N 421C0001 through 421C0800) +1318 in.-lb. (S/N 421C0801 and up) Empty Wt. C.G. Range None Leveling Means External screw heads on right side of fuselage at stations +213.9 and +238.55 on W.L. +93.80 Maximum Weight S/N 421C0001 through 421C0400 Landing 7200 lb., takeoff 7450 lb. S/N 421C0401 and up Landing 7200 lb., takeoff 7450 lb., ramp 7500 lb. Page 15 of 24 A7CE, Rev. 47 VII - Model 421C (cont'd) No. of Seats 6, 7 or 8 (2 at +137.0, 2 at +175.0, 2 at +218.0, 1 at +261.0) or 10 (2 at +137.0, 2 at +162.0, 2 at +190.0, 2 at +218.0, 2 at +246.0) (See manufacturer's equipment list for optional seating arrangements) Maximum Baggage 250 lb. (+32.0), 350 lb. (+71.0), 400 lb. (+186.0), 400 lb. (+266.0), 100 lb. (+282.0) Fuel Capacity 213.4 gal. (2 wing tanks, 106.7 gal. ea., 103.0 gal. usable at +161.0) See NOTE 1 for data on unusable fuel Oil Capacity 26 qt. (13 qt. in ea. engine at +115.4; usable 7.0 qt. per engine) See NOTE 1 for data on undrainable oil Control Surface Movements Wing flaps Down 45°, +1°, -0° Main surfaces Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 25°, +1°, -0° Down 15°, +1°, -0° Rudder Right 32°, +1°, -0° Left 32°, +1°, -0° (Read degrees normal to rudder hinge line) Tab (main surface in neutral) Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 12°, +1°, -0° Down 20°, +1°, -0° Rudder Right 11°, +1°, -0° Left 16°, +1°, -0° (Read degrees normal to rudder hinge line) Serial Nos. Eligible 421C0001 through 421C1807 VIII - Model 414A, Chancellor, (Normal Category), Approved September 30, 1977 Engines Two Continental TSIO-520-N or TSIO-520-NB (In any combination) (S/N 414A0001 through 414A0200) Two Continental TSIO-520-NB (S/N 414A0201 and up) Fuel Grade 100 or 100LL Aviation Gasoline Engine Limits For all operations, 2700 r.p.m., 310 hp., 38.0 in. Hg. Mp. up to critical altitude of 20,000 ft. in standard atmosphere. Above 20,000 ft. the following maximum Mp. applies for maximum r.p.m.: Altitude (ft.) Max. Allowable Mp. (in. Hg.) 20,000 38.0 22,000 35.2 24,000 32.3 26,000 29.8 28,000 27.4 30,000 25.0 Propeller and Two McCauley full-feathering three-bladed propeller installations Propeller Limits (a) McCauley hub 3AF32C93 with 82NC-5.5 blades or McCauley hub 3AF32C505 with 82NEA-5.5 blades Diameter: not over 76.5 in., not under 75.0 in. (no further reduction permitted) Pitch settings at 30 in. station: low 14.9°, +0.2°, feathering 81.2°, +0.3° or (b) McCauley hub 3AF32C93 with 82NC-5.5 blades or McCauley hub 3AF32C505 with 82NEA-5.5 blades Diameter: not over 75.5 in., not under 75 in. Pitch settings at 30 in. station: low 15.2°, +0.2° feathered 81.2°, +0.3° A7CE, Rev. 47 Page 16 of 24 VIII - Model 414A (cont'd) Propeller and (c) S/N 414A0001 through 414A0801 Propeller Limits Hydraulic governor McCauley DCF290D2/T3, DCFU290D2/T3, DCFS290D4/T3, DCFUS290D4/T3, DCFS290D6/T3, DCFUS290D6/T3, DCF290D7/T3, DCFU290D7/T3, DCFU290D13/T3, DCFS290D7/T3, DCFUS290D7/T3, DCFUS290D13/T3, DCFS290D8/T3, DCFUS290D8/T3 or DCFUS290D12/T13 S/N 414AC0801 and up Hydraulic governor McCauley DCF290D2/T3, DCFU290D2/T3, DCF290D7/T3, DCFU290D7/T3 or DCFU290D13/T3, DCFS290D9/T3, DCFUS290D9/T3 (d) Propeller spinner and bulkhead assembly, McCauley D-3534/D-3796, or McCauley D-5212/D-5214 Airspeed Limits Maneuvering 145 KIAS (167 m.p.h.) (IAS) Max. structural cruising 203 KIAS (234 m.p.h.) Never exceed 237 KIAS (273 m.p.h.) Landing gear operating 177 KIAS (204 m.p.h.) Landing gear extended 177 KIAS (204 m.p.h.) Flaps extended 15° 177 KIAS (204 m.p.h.) Flaps extended 45° 146 KIAS (168 m.p.h.) Minimum control 79 KIAS ( 91 m.p.h.) C.G. Range (Landing (+151.3) to (+160.0) at 6750 lb. Gear Extended) (+147.8) at 5800 lb. or less Straight line variation between points given Landing gear retracted moment change: +917 in.-lb. Empty Wt. C.G. Range None Leveling Means External screw heads on right side of fuselage at stations +213.29 and +238.55 on W.L. +93.80 Maximum Weight Ramp 6785 lb., takeoff and landing 6750 lb. No. of Seats 6, 7 or 8 (2 at +137.0, 2 at +175.0, 2 at +218.0, Optional: 1 or 2 at +261.0 or with toilet option, 1 at +250.0) (See manufacturer's equipment list for optional seating arrangements) Maximum Baggage 250 lb. (+32.0), 350 lb. (+71.0), 400 lb. (+186.0), 400 lb. (+266.0), 100 lb. (+282.0) Fuel Capacity S/N 414A0001 through 414A0200 213.4 gal. (2 wing tanks, 106.7 gal. ea., 103.0 gal. usable at +161.0) See NOTE 1 for data on unusable fuel S/N 414A0201 through 414A0400 213.4 gal. (2 wing tanks, 106.7 gal. ea., 102.0 gal. usable at +161.0) See NOTE 1 for data on unusable fuel S/N 414A0401 and up 213.4 gal. (2 wing tanks, 106.7 gal. ea., 103.0 gal. usable at +161.0) See NOTE 1 for data on unusable fuel Oil Capacity 26 qt. (13 qt. in ea. engine at +110.9; usable 6.5 qt. per engine) See NOTE 1 for data on undrainable oil Page 17 of 24 A7CE, Rev. 47 VIII - Model 414A (cont'd) Control Surface Movements Wing flaps Down 45°, +1°, -0° Main surfaces Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 25°, +1°, -0° Down 15°, +1°, -0° Rudder Right 32°, +1°, -0° Left 32°, +1°, -0° (Read degrees normal to rudder hinge line) Tab (main surface in neutral) Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 12°, +1°, -0° Down 20°, +1°, -0° Rudder Right 11°, +1°, -0° Left 16°, +1°, -0° (Read degrees normal to rudder hinge line) Serial Nos. Eligible 414A0001 through 414A1212 IX - Model 402C, Businessliner/Utililiner, (Normal Category), Approved September 25, 1978 Engines Two Continental TSIO-520-VB rated at 325 hp. Fuel Grade 100 or 100LL aviation gasoline Engine Limits Takeoff and engine inoperative, 2700 r.p.m., 39.0 in. Hg. Mp. up to 12,000 ft. Above 12,000 ft. the following maximum Mp. applies for maximum r.p.m. Altitude (ft.) Max. Allowable Mp. (in. Hg.) S.L. to 12,000 39.0 14,000 37.2 16,000 37.2 18,000 32.0 20,000 29.5 22,000 27.0 24,000 25.0 26,000 23.0 28,000 21.0 30,000 19.0 Propeller and Two McCauley full-feathering three-bladed propeller installations Propeller Limits (a) McCauley hub 3AF32C93 with 82NC-5.5 blades or McCauley hub 3AF32C505 with 82NEA-5.5 blades Diameter: not over 76.5 in., not under 75.0 in. (no further reduction permitted) Pitch settings at 30 in. station: low 14.9°, +0.2°, feathering 82.2°, +0.3° or (b) McCauley hub 3AF32C93 with 82NC-6.5 blades or McCauley hub 3AF32C505 with 82NEA-6.5 blades Diameter: not over 75.5 in., not under 75.0 in. Pitch settings at 30 in. station: low 15.2°, +0.2°, feathering 82.2°, +0.3° (c) S/N 402C0001 through 402C0600 Hydraulic governor, Woodward B210444, C210439; McCauley DCF290D7/T3, DCFUS290D7/T3, DCFU290D13/T3, DCFS290D7/T3, DCFUS290D7/T3, DCFUS290D13/T3, DCFUS290D8/T3, or DCFUS290D12/T3 S/N 689, and 402C0601 and up Hydraulic governor, Woodward B210444, C210439; McCauley DCF290D7/T3, DCFU290D7/T3 or DCFU290D13/T3, DCFS290D9/T3, DCFUS290D9/T3 (d) Propeller spinner and bulkhead assembly; McCauley D-3534/D-3537, D-3534/D-3796, or D-5212/D-5214 A7CE, Rev. 47 Page 18 of 24 IX - Model 402C (cont'd) Airspeed Limits Maneuvering 150 KIAS (173 m.p.h.) (IAS) Max. structural cruising 205 KIAS (236 m.p.h.) Never exceed 235 KIAS (270 m.p.h.) Landing gear operating 180 KIAS (207 m.p.h.) Landing gear extended 180 KIAS (207 m.p.h.) Flaps extended 15° 180 KIAS (207 m.p.h.) Flaps extended 45° 149 KIAS (172 m.p.h.) Minimum control 80 KIAS ( 92 m.p.h.) C.G. Range (Landing (+151.58) to (+160.67) at 6850 lb. Gear Extended) (+149.08) at 5800 lbs. or less Straight line variation between points given Landing gear retracted moment change: +917 in.-lb. Empty Wt. C.G. Range None Leveling Means External screw heads on right side of fuselage at stations +213.65 and +238.00 on W.L. +93.80 Maximum Weight Ramp, 6885 lbs., takeoff and landing 6850 lbs. No. of Seats 6, 7 or 8 (2 at +137.0, 2 at +175.0, 2 at +218.0, 1 or 2 at +261.0) 9 (with photographic provisions option) (2 at +137.0, 2 at +162.0, 2 at +190.0, 2 at +218.0, 1 at +246.0) 10 (2 at +137.0, 2 at +162.0, 2 at +190.0, 2 at +218.0, 2 at +246.0) (See manufacturer's equipment list for optional seating arrangements) Maximum Baggage 250 lbs. (+32.0), 350 lbs. (+71.0), 400 lbs. (+186.0), 400 lbs. (+266.0), 100 lbs. (+282.0) Fuel Capacity S/N 402C0001 through 402C0200 213.4 gal. (2 wing tanks, 106.7 gal. ea., 102 gal. usable at +161.0) See NOTE 1 for data on unusable fuel S/N 689, and 402C0201 and up 213.4 gal. (2 wing tanks, 106.7 gal. ea., 103 gal. usable at +161.0) See NOTE 1 for data on unusable fuel Oil Capacity 26 qt. (13 qt. in ea. engine at +110.9; usable 6.5 qt. per engine) See NOTE 1 for data on undrainable oil Control Surface Movements Wing flaps Down 45°, +1°, -0° Main surfaces Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 25°, +1°, -0° Down 15°, +1°, -0° Rudder Right 32°, +1°, -0° Left 32°, +1°, -0° (Read degrees normal to rudder hinge line) Tab (main surface in neutral) Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 12°, +1°, -0° Down 20°, +1°, -0° Rudder Right 11°, +1°, -0° Left 16°, +1°, -0° (Read degrees normal to rudder hinge line) Serial Nos. Eligible 689, 402C0001 through 402C1020 Page 19 of 24 A7CE, Rev. 47 X - Model 425, Corsair or Conquest I (See NOTE 7), (Normal Category), Approved July 1, 1980 Engines Two Pratt & Whitney Aircraft of Canada, Ltd., PT6A-112 turboprop Fuel Aviation turbine fuel Jet A, Jet A-1, or Jet B, JP-4, JP-5 or JP-8. For required use of anti-icing additives and emergency use of aviation gasoline, refer to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual. Engine Limits Operating Limits Shaft Horsepower Power Ng Gas Generator Speed (% rpm) Indicated Torque (ft.-lbs.) Prop. Shaft Speed (rpm) Maximum Permissible Interturbine Temp. (°C.) Takeoff static & max. continuous 450* 101.6 1244 1900 725 Starting (2 sec.) - - - - - - - - 1090 Maximum reverse 430 101.6 1244 1815 725 *Flat Rated: The engines may produce more power than that for which the airplane has been certificated. Under these conditions, the placarded torquemeter, ITT, or Ng limitations shall not be exceeded. Propeller and (1) Two Hartzell three-bladed, full-feathered, reversible Propeller Limits Hub: HC-B3TN-3C Blade: T10178B-8R Diameter: Not over 93-3/8 in., not under 91 inches; no further reduction permitted Pitch at 30-inch station: Low pitch 20.2° Feathered 86.7° Reverse -10.9° (2) Two McCauley three-bladed, full-feathered, reversible Hub: 3GFR34C701 Blade: 93KB-0 Diameter: Not over 93 inches, not under 90-5/8 inches; no further reduction permitted Pitch at 30-inch station: Low pitch 18.5° Feathered 85.5° Reverse -13.5° Propellers may be interchanged in any combination. Airspeed Limits VMO (Max Operating) 230 knots 265 m.p.h. (IAS) Sea level to 21,800 ft. MMO Above 21,800 ft. .52 mach VA (Maneuvering) at 8200 lbs. 154 knots 177 m.p.h. VA (Maneuvering) at 8600 lbs. 157 knots 181 m.p.h. VFE (Flaps extended) 45° (Landing) 145 knots 169 m.p.h. 15° (Takeoff & Approach) 175 knots 201 m.p.h. VMCA (Min. control speed) Air at 8200 lbs. 90 knots 104 m.p.h. VMCA (Min. control speed) Air at 8600 lbs. 92 knots 106 m.p.h. VLE (Landing gear extended) 175 knots 201 m.p.h. A7CE, Rev. 47 Page 20 of 24 X - Model 425 (cont'd) C.G. Range (Landing S/N 425-0001 through 425-0176 (See NOTE 7) Gear Extended) (155.66) to (160.04) at 8200 lbs. (150.65) to (160.04) at 6478 lbs. or less S/N 425-0177 and up (156.81) to (160.04) at 8600 lbs. (150.65) to (160.04) at 6478 lbs. or less Straight line variation between points given Moment change due to retracting landing gear (+1448 in.-lb.) Empty Wt. C.G. Range None Leveling Means External screw heads on right side of fuselage at stations +213.9 and +238.55 on W.L. +93.80 Maximum Weight S/N 425-0001 through 425-0176 S/N 425-0177 (See NOTE 7) and up Takeoff 8200 lbs. 8600 lbs. Landing 8000 lbs. 8000 lbs. Zero fuel 6740 lbs. 7000 lbs. Ramp 8275 lbs. 8675 lbs. No. of Seats 6, 7 or 8 (2 at +137.0, 2 at +175.0, 2 at +218.0, 2 at +261.0) See manufacturer's equipment list for optional seating arrangements Maximum Baggage 250 lb. (+32.0), 350 lb. (+71.0), 400 lb. (+266.0), 100 lb. (+282.0) Fuel Capacity 2497.8 lb. (372.8 gal.) total in two wing tanks, 1248.9 lb. (186.4 gal.) each; 2452.2 lb. (366.0 gal.) usable total, 1226.1 lb. (133 gal.) in each tank at +163.3. Fuel weight based on 6.70 lb./gal. See NOTE 1 for data on unusable fuel. Oil Capacity 5.28 gal. total, 5.28 gal. usable (2.3 gal. in each engine-mounted tank at +125.3). See NOTE 1 for data on undrainable oil. Maximum Operating 30,000 ft. Altitude Control Surface Movements Wing flaps Down 45°, +1°, -0° Main surfaces Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 19°, +1°, -0° Down 15°, +1°, -0° Rudder Right 32°, +1°, -0° Left 32°, +1°, -0° (Read degrees normal to rudder hinge line) Tab (main surface in neutral) Aileron Up 20°, +1°, -0° Down 20°, +1°, -0° Elevator Up 6°, +1°, -0° Down 15°, +1°, -0° Rudder Right 11°, +1°, -0° Left 16°, +1°, -0° (Read degrees normal to rudder hinge line) Serial Nos. Eligible 425-0001 through 425-0236 Data Pertinent to All Models Datum 100.00 in. forward face of fuselage bulkhead forward of rudder pedals. Page 21 of 24 A7CE, Rev. 47 X - Model 425 (cont'd) Certification Basis Models 401, 401A, 401B, 402, 402A, 402B, 411, 411A, 414, 421, 421A: Part 3 of the Civil Air Regulations dated May 15, 1956, as amended by 3-1 through 3-5 and 3-8. Model 421B: Part 3 of the Civil Air Regulations dated May 15, 1956, except Subpart B, as amended by 3-1 through 3-5 and 3-8; Subpart B, paragraphs 23.25 through 23.253 of the Federal Aviation Regulations dated February 1, 1965, as amended by 23-1 through 23-7. Models 414A and 421C: Part 3 of the Civil Air Regulations dated May 15, 1956, as amended by 3-1 through 3-5 and 3-8, excluding the following portions: Subpart B and paragraphs 3.356, 3.357, 3.358, 3.359, 3.411, 3.429, 3.433, 3.434, 3.435, 3.436, 3.437, 3.445, 3.581, 3.582, 3.583, 3.584, 3.585, 3.587, 3.628, 3.666, 3.672, 3.673, 3.674, 3.675, 3.700(c), 3.728, 3.767(a) and 3.767(b). Include the following portions of FAR 23 dated February 1, 1965, as amended by 23-1 through 23-14; Subpart B and paragraphs 23.729, 23.901, 23.909, 23.951, 23.954, 23.955, 23.959, 23.973, 23.1041, 23.1043, 23.1047, 23.1143, 23.1305, 23.1387(e), 23.1435 and 23.1557(c); as amended by 23-1 through 23-21, paragraph 23.1385(c); as amended by 23-1 through 23-23, paragraph 23.1327. Add paragraph 23.1559(b) for Model 414A only. Findings of Equivalent Level of Safety were made for CAR 3.637, 3.757, and 3.778(a). Model 402C: Part 3 of the Civil Air Regulations dated May 15, 1956, as amended by 3-1 through 3-5 and 3-8, excluding the following portions: Subpart B and paragraphs 3.356, 3.357, 3.358, 3.359, 3.411, 3.429, 3.433, 3.434, 3.435, 3.436, 3.437, 3.445, 3.581, 3.582, 3.583, 3.584, 3.585, 3.587, 3.628, 3.666, 3.672, 3.673, 3.674, 3.675, 3.700(c), 3.728, 3.767(a) and 3.767(b). Include the following portions of FAR 23 dated February 1, 1965, as amended by 23-1 through 23-14: Subpart B and paragraphs 23.729, 23.901, 23.909, 23.951, 23.954, 23.955, 23.959, 23.973, 23.1041, 23.1043, 23.1047, 23.1143, 23.1305, 23.1387(e), 23.1435, 23.1557(c), and 23.1559(b); as amended by 23-1 through 23-21, paragraph 23.1385(c); as amended by 23-1 through 23-23, paragraph 23.1327. Part 36 of the Federal Aviation Regulations dated December 1, 1969, as amended by 36-1 through 36-7. Findings of Equivalent Level of Safety were made for CAR 3.637, 3.757, and 3.778(a). Model 425: Part 3 of the Civil Air Regulations dated May 15, 1956, as amended by 3-1 through 3-6 and 3-8 as follows: Paragraphs 3.0 through 3.20, 3.291 through 3.307, 3.317 through 3.347, 3.371 through 3.401, 3.651, 3.652, 3.655(c) and (d), 3.661, 3.662, 3.668, 3.686 through 3.699, 3.711 through 3.728, 3.749, 3.791, and 3.792; the following portions of FAR 23 dated February 1, 1965, as amended by 23-1 through 23-21: Paragraphs 23.21 through 23.33, 23.45(a) through (d), 23.49 through 23.179, 23.181(a), 23.201 through 23.572, 23.629, 23.723 through 23.735, 23.865, 23.867, 23.901 through 23.1017, 23.1019(a)(1) and (2), 23.1019(a)(4) and (5), 23.1019(b), 23.1021 through 23.1203, 23.1303(a) through (d), 23.1305(a) through (u) and (w), 23.1323, 23.1325, 23.1327, 23.1329, 23.1335, 23.1337, 23.1351 through 23.1357, 23.1385 through 23.1401, 23.1441 through 23.1449, 23.1501 through 23.1521, 23.1524, 23.1525, 23.1527(b), and 23.1529 through 23.1589; Paragraph 25.831(d) of FAR 25 dated February 1, 1965, as amended by 25-1 through 25-43; FAR 36 dated December 1, 1969, as amended by 36-1 through 36-10; SFAR No. 27, Fuel Venting and Exhaust Emission Requirements for Turbine Engine Powered Airplanes, effective February 1, 1974, as amended by SFAR's 27-1, 27-2, and 27-3; plus Special Conditions 23-93-CE-12 as amended by Amendment No. 1 dated June 25, 1980. (See NOTE 3.) A7CE, Rev. 47 Page 22 of 24 X - Model 425 (cont'd) Certification Basis Model 414A (S/N 414A0401 and up, Model 421C (S/N 421C0801 and up) In addition to the above certification basis, compliance with FAR 36, dated December 1, 1969, as amended by 36-1 through 36-10 (414A only) and 36-1 through 36-4 (421C only) has been demonstrated. Model 402B, S/N 402B0501 and up Model 402C Model 414, S/N 414-0451 and up Model 414A Model 421B, S/N 421B0501 and up Model 421C Model 425 Markings, placards and manuals are primarily in knots instead of m.p.h. as required by CAR 3, but permitted by FAR 23, Amendment 23-7. Model 402B, S/N 402B1001 and up Model 414, S/N 414-0801 and up Findings of equivalent level of safety were made for CAR 3.757 and 3.778(a). Model 402B, S/N 402B0801 and up Model 402C Model 414, S/N 414-0601 and up Model 414A Model 421B, S/N 421B0801 and up Model 421C Model 425 In addition to the above certification basis, compliance with ice protection has been demonstrated in accordance with FAR 23.1419 of Amendment 23-14 effective December 20, 1973, when ice protection equipment is installed in accordance with Cessna Drawing 5914105 for 425, 5114400 for all other models, Factory Kit (FK) No. 194, Pilot's Operating Handbook and/or FAA Approved Airplane Flight Manual. Aircraft which have been modified in compliance with Accessory Kit (AK) No. 421-106 are considered to be equivalent to those with Factory Kit (FK) No. 194. Application for Type Certificate dated September 18, 1961. Type Certificate No. A7CE issued August 17, 1964, obtained by the manufacturer under delegation option procedures. Production Basis Production Certificate No. 312 issued and Delegation Option Manufacturer No. CE-3 authorized to issue airworthiness certificates under delegation option provisions of Part 21 of the Federal Aviation Regulations. Effective February 15, 1985, and on, Production Certificate No. 4 is applicable to all spares production. See NOTE 8 for specific effectivity of P.C. 4 on new airplane serials. 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, the following item of equipment is required. 1. Stall warning indicator, Cessna dwg. 5018100 (401, 402, 411, 411A) Stall warning indicator, Cessna dwg. 5118000 (421) Stall warning indicator, Cessna dwg. 5618002 (414) Stall warning indicator, Cessna dwg. 5218016 (401A, 402A, 401B, 402B0001 through 402B0300) Stall warning indicator, Cessna dwg. 5118310 (421A) Stall warning indicator, Cessna dwg. 5118402 (421B0001 through 421B0300) Stall warning indicator, Cessna dwg. 5618021 (414-0351 and up, 421B0301 and up) Stall warning indicator, Cessna dwg. 5218031 (402B0301 and up) Stall warning indicator, Cessna dwg. 5118627 (421C) Stall warning indicator, Cessna dwg. 5618041 (402C, 414A, 425) or Angle of Attack Indicator System, Cessna Dwg. 0800302, Model 402B, 402C, 414, 414A, 421B, 421C. Page 23 of 24 A7CE, Rev. 47 NOTE 1. Current weight and balance report together 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. The certificated empty weight and corresponding center of gravity location must include undrainable oil (not included in oil capacity) and unusable fuel as follows: (a) Fuel. 12 lb. (tip) at (+152.0) (401, 401A, 401B, 402, 402A, 402B, 411, 411A, 414, 421, 421A, 421B) 18 lb. (wing, standard 73 gal. at +164.0) (411, 411A, 421, 421A, 421B) 24 lb. (wing, optional 100 gal. at +164.0) (411, 411A, 421, 421A, 421B, 402A, 402B, 414) 6 lb. (wing, optional 63 gal. at +164.0) (402B0301 and up and 414-0351 and up) 44 lb. (wing, 7.4 gal. at +165.2) (402C, S/N 689, and 402C0201 and up; 414A, S/N 414A0401 and up; 421C) 68 lb. (wing, 11.4 gal. at +165.2) (414A, S/N 414A0001 through S/N 414A0200) 56 lb. (wing, 9.4 gal. at +165.0) (402C, S/N 402C0001 through 402C0200; 414A, S/N 414A0201 through 414A0400) 45.6 lb. (wing, 6.8 gal. at +166.2) (425) (b) If optional wing locker transfer tanks are installed 3.0 lb. (each 26 gal. tank) at (+176.0) (411, 411A, 421, 421A, 421B) 3.0 lb. (each 20 gal. tank) at (+175.0) (401, 401A, 401B, 402, 402A, 402B, 414) 2.0 lb. (each 28 gal. tank) at (+176.0) (421C0001 and up) (c) Oil - 0.0 lb. NOTE 2. The placards specified in the FAA Approved Airplane Flight Manual must be displayed. NOTE 3. Service information The appropriate airplane service manual contains structural retirement lives, which may not be changed without FAA Engineering approval, for the following components: Part Number Hours Model Windshield 5111604-1 & -2 13,200 414, 414A, 421A, 421B, 421C, 425 Windshield, heated 9910013-1 13,200 421, 421A (S/N 421A0001 through 421A0117) Windshield, heated 9910071-1 13,200 414, 421A, 421B S/N 414-0001 through 414-0600, 421A0118 through 421B0800) Windshield, heated 9910214-1 & -2 13,200 414, 414A, 421B, 421C (S/N 414-0601 and up, 421B0801 through 421C0800) Windshield, heated 9910460-1 & -200 13,200 421C (S/N 421C0801 and up), 425 Upper cabin door 5111545-3 8,000 421 (S/N 421-0001 through 421-0079) latch pins Upper cabin door 5111545-6 8,000 421 (S/N 421-0080 and up), 421A latch pins Wing 5922125 not 10,200 425 (S/N -0002 thru -0176 except modified by SK425-48 airplanes incorporating SK425-17) Wing 5922125 not 9,300 425 (S/N -0177 and On and airplanes modified by SK425-48 -0002 thru -0176 incorporating SK425-17) Wing 5922125 modified by 30,000 425 SK425-48 Wing carry-thru 5911004, 5111225 30,000 425 A7CE, Rev. 47 Page 24 of 24 NOTE 3. (cont'd.) For Model 425 aircraft that have exceeded the structural retirement life prior to the availability of Cessna Service Kit SK425-48, the service kit is to be installed according to the following schedule: A. For airplanes 425-0177 and on, and airplanes 425-0002 through 425-0176 incorporating SK425-17: Exceeding 12, 500 hours, accomplish SK425-48 within 100 hours or 12 months after SK 425-48 was issued, whichever comes first. Exceeding 9,300 hours but less than 12,500 hours, accomplish SK425-48 within 400 hours or 24 months after SK425-48 was issued whichever comes first. Between 8,900 and 9,300 hours when SK425-48 was issued, accomplish within 400 hours of operation. For airplanes with less than 8,900 hours when SK425-48 was issued, accomplish at 9,300 hours. B. For airplanes -0002 through -0176, except airplanes incorporating SK425-17: Exceeding 12,500 hours, accomplish SK425-48 within 100 hours or 12 months after SK425-48 was issued whichever comes first. Exceeding 10, 200 hours but less than 12,500 hours, accomplish SK425-48 within 400 hours or 24 months after SK425-48 was issued whichever comes first. Between 9,800 and 10,200 hours when SK425-48 was issued, accomplish within 400 hours of operation. For airplanes with less than 9,800 hours when SK425-48 was issued, accomplish 10,200 hours. Model 425 Special Conditions 23-93-CE-12, required, in part, that Cessna establish mandatory inspections of the Horizontal Tail Assembly in order to maintain continued structural integrity. Therefore, inspections are required for the horizontal stabilizer, elevators, elevator tab and tab actuator system. In order to comply with these requirements, airplanes must be inspected in accordance with inspection Item Codes A273002, A273101, A273102, B273109 and A551001 as contained in Model 425 Maintenance Manual, Part Number D2535-3-13, Revision 3 (or later revision). These inspection criteria are contained in Chapter 5, Subsection 5-10-01, and are applicable to Zones 331 and 332. All approved airplane inspection programs must include these mandatory inspections. NOTE 4. Model 421, Serial Nos. 421-0001 and up, approved for 6840 lb. takeoff weight with C.G. range as follows when appropriate airplane flight manual, pilot's checklist, weight and balance form, and other documents are provided as specified in Cessna Service Kit SK421-12. C.G. Range (Landing Gear Extended) (+152.1) to (+155.5) at 6840 lb. (+155.7) at 6500 lb. (+144.3) to (+155.7) at 5500 lb. Straight line variation between points given NOTE 5. McCauley propellers with 3AF32C87 and 3AF32C504 hubs may be interchanged in any combination. This also applies to propellers with 3AF32C93 and 3AF32C505m hubs; 3AF34C92 and 3AF37C516 hubs; 3AF34C74 and 3AF37C510 hubs. NOTE 6. Model 425 aircraft in compliance with Cessna Drawing 5700018 are eligible for certification in The Netherlands. NOTE 7. Model 425 S/N 425-0001 through 425-0176 (Corsair) are eligible for the maximum weights and C.G. range applicable to S/N 425-0177 and up (Conquest I), when modified in accordance with Cessna Service Kit SK425-17, and will be renamed Conquest I. NOTE 8. Production Certificate No. 4 effective at Serials 402C1005 and on, 414A1208 and on, 421C1801 and on, and 425-0228 and on. .....END.....