# TCDS 3A25: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 28 - Revised: September 20, 2024 - Product: Aircraft, Small Airplane - Certification basis: Part 23, CAR 3 - Registered aircraft: 870, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/e4/a3/e4a3205a4b4ed0afc4fa84499c727c228e40aa524a9975fbe03172d57700528b - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID105147599520241004170427.0001 - Page: https://openairdocs.org/tcds/3A25 ## Models (11) As the data sheet lists them. - 320 - 320D - 320-1 - 320B - 320E - 335 - 340A - 320C - 320F - 340 - 320A ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Rev. No. 28 25 25 25 25 25 27 25 27 27 25 27 25 27 Page No. 15 16 17 18 19 20 21 22 23 24 25 26 27 Rev. No. 25 27 25 28 25 25 25 25 25 25 25 27 27 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 3A25 Revision 28 Textron Aviation 320 320F 320-1 335 320A 340 320B 340A 320C 320D 320E September 20, 2024 TYPE CERTIFICATE DATA SHEET NO. 3A25 This data sheet which is part of Type Certificate No. 3A25 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 Textron Aviation Inc. One Cessna Boulevard Wichita, KS 67215 Type Certificate Holder Record Cessna Aircraft Company transferred to Textron Aviation Inc. on July 29, 2015 I. Model 320, Skyknight, (Norma l Category), Approved May 24, 1961 Engines Two Continental TSIO-470-B *Fuel 100/130 minimum grade aviation gasoline (See NOTE 5). *Engine Limits For all operations, 2600 rpm, 260 hp, 35 in. Hg MP Critical altitude is 16,000 ft. in standard atmosphere. Propeller and 1. Two Hartzell full-feathered, propeller: Propeller Limits Hub: HC-A2XF-2 Blade: 8433 Diameter: Not over 80 in., not unde r 78 in. (no further reduction permitted) Pitch at 30-inch station: Low pitch: 15.0° High pitch: 22.0° Feathered: 84.0°, ±2° a. Hydraulic governor: W oodward 210290, C210355, A210438, 210444. b. Propeller spinner and bulkhead assembly: Cessna 0850319-1 dome with 0850309-1 bulkhead. *Airspeed Limits Never exceed 252 m.p.h. (218 knots) (CAS) Maximum structural cruising 210 m.p.h. (183 knots) Maneuvering 167 m.p.h. (145 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) 3A25 2 Rev. 28 I. Model 320 (cont’d) *C.G. Range (+38.3) to (+41.6) at 4990 lb. (+42.1) at 4600 lb. (+32.0) to (+42.1) at 4060 lb. or less Straight line variation between points given. Empty Wt. C.G. Range None *Maximum Weight Landing: 4750 lb. Takeoff: 4990 lb. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lb. (+96) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) or 133 gal. (with 2 wing tip tanks and 2 auxiliary tanks 15.5 gal. each at +47). (See NOTE 1 for data on system fuel) Oil Capacity 6.5 gal. (3.25 gal in each engine at (-3.5), unusable 1.5 gal. per engine) (See NOTE 1 for data on system oil) Control Surface Wing flaps 45° Down Movements Main surfaces Aileron 20° Up 20° Down Elevator 25° Up 15° Down Rudder 25° Right 25° Left (Parallel to W.L.) Tab (main surface in neutral) Aileron 20° Up 20° Down Elevator 10° Up 26° Down Rudder 17° Right 22° Left (Parallel to W.L.) Serial Nos. Eligible 320-0001 thru 320-0110 II. Model 320-1, Skyknight, (Norma l Category), Approved May 10, 1962 Engines Two Continental TSIO-470-B *Fuel 100/130 minimum grade aviation gasoline (see NOTE 5). *Engine Limits For all operations, 2600 rpm, 260 hp, 35 in. Hg MP Critical altitude is 16,000 ft. in standard atmosphere. Propeller and 1. Two Hartzell full-feathered, propeller: Propeller Limits Hub: HC-A2XF-2 Blade: 8433 Diameter: Not over 80 in., not unde r 78 in. (no further reduction permitted) Pitch at 30-inch station: Low pitch: 15.0° High pitch: 22.0° Feathered: 84.0°, ±1° a. Hydraulic governor: 1) Woodward 210280, C210355, A210438, 210444. 2) McCauley DCFU290D1/T2, DCFU290D2/T2. b. Propeller spinner and bulkhead assembly: Cessna 0850319-1 dome with 0850309-1 bulkhead. Rev. 28 3 3A25 II. Model 320-1 (cont’d) *Airspeed Limits Never exceed 257 m.p.h. (224 knots) (CAS) Maximum structural cruising 210 m.p.h. (183 knots) Maneuvering 170 m.p.h. (148 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (+38.0) to (+43.1) at 5200 lb. (+43.6) at 4800 lb. (+32.0) to (+43.6) at 4300 lb. or less Straight line variation between points given. Empty Wt. C.G. Range None *Maximum Weight Landing: 5200 lb. Takeoff: 5200 lb. Number of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lb. (+96) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) or 133 gal. (with 2 wing tip tanks and 2 auxiliary tanks, 15.5 gal. each at +47) (See NOTE 1 for data on unusable fuel) Oil Capacity 6.5 gal. (3.25 ga l. in each engine at (-3.5), unusable 1.5 gal. per engine (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps 45° Down Movements Main surfaces Aileron 20° Up 20° Down Elevator 25° Up 15° Down Rudder 25° Right 25° Left (Parallel to W.L.) Tab (main surface in neutral) Aileron 20° Up 20° Down Elevator 10° Up 26° Down Rudder 17° Right 22° Left (Parallel to W.L.) Serial Nos. Eligible All Model 320 (S ection I) Serial Nos. are eligible, upon modification in accordance with Cessna AK320-28. III. Model 320A, (Normal Category), Approved May 10, 1962 Engines Two Continental TSIO-470-B *Fuel 100/130 minimum grade aviation gasoline (See NOTE 5). *Engine Limits For all operations, 2600 rpm, 260 hp, 35 in. Hg MP Critical altitude is 16,000 ft. in standard atmosphere. 3A25 4 Rev. 28 III. Model 320A (cont’d) Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. Hartzell hubs HC-A2XF-2 with 8433 blades Diameter: not over 80 in., not under 78 in. No further reduction permitted Pitch settings at 30 in. sta.: low 15.0°, high 22.0°, feathered 84 ±1° b. Hydraulic governor, Woodward 210280, C210355, A210438, 210444; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Cessna 0850319-1 dome with 0850309-1 bulkhead *Airspeed Limits Never exceed 257 m.p.h. (224 knots) (CAS) Maximum structural cruising 210 m.p.h. (183 knots) Maneuvering 170 m.p.h. (148 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (+38.0) to (+43.1) at 5200 lb. (+43.6) at 4800 lb. (+32.0) to (+43.6) at 4300 lb. or less Straight line variation between points given. Empty Wt. C.G. Range None *Maximum Weight Landing: 5200 lb. Takeoff: 5200 lb. Number of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lb. (+96), 60 lb. on upper rack (+124), 80 lb. per side on floor (+124) (See NOTE 2G for placards) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) or 133 gal. (with 2 wing tip tanks and 2 auxiliary tanks 15.5 gal. each at +47) (See NOTE 1 for data on unusable fuel) Oil Capacity 6.5 gal. (3.25 gal. in each engine (-3.5), unusable 1.5 gal. per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps 45° Down Movements Main surfaces Aileron 20° Up 20° Down Elevator 25° Up 15° Down Rudder 25° Right 25° Left (Parallel to W.L.) Tab (main surface in neutral) Aileron 20° Up 20° Down Elevator 10° Up 26° Down Rudder 17° Right 22° Left (Parallel to W.L.) Serial Nos. Eligible 320A0001 thru 320A0047 Rev. 28 5 3A25 IV. Model 320B, (Normal Category), Approved May 16, 1963 Engines Two Continental TSIO-470-C *Fuel 100/130 minimum grade av iation gasoline. See NOTE 5 *Engine Limits For all operations, 2600 rpm, 260 hp, 35 in. Hg MP Critical altitude is 16,000 ft. in standard atmosphere Propeller and 1. 2 full-feathe ring propeller installations Propeller Limits a. Hartze ll hubs HC-A2XF-2 with 8433 blades Diameter: not over 80 in., not under 78 in. No further reduction permitted Pitch settings at 30 in. sta.: low 15.0°, high 22.0°, feathered 84 ±1° b. Hydraulic governor, Woodward 210280, C210355, A210438, 210444; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Cessna 0850319-1 dome with 0850319-1 bulkhead *Airspeed Limits Never exceed 257 m.p.h. (224 knots) (CAS) Maximum structural cruising 210 m.p.h. (183 knots) Maneuvering 170 m.p.h. (148 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (+38.0) to (+43.1) at 5200 lb. (+43.6) at 4800 lb. (+32.0) to (+43.6) at 4300 lb. or less Straight line variation between points given. Empty Wt. C.G. Range None *Maximum Weight Landing: 5200 lb. Takeoff: 5200 lb. Number of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lb. on floor at (+96), 80 lb. per side on floor at (+124), 60 lb. on upper rack at (+124), 120 lb. per nacelle at (+63) Oil Capacity 6.5 gal. (3.25 ga l. in each engine at (-3.5), unusable 1.5 gal. per engine) (See NOTE 1 for data on undrainable oil) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35) or 133 gal. (with 2 wing tip tanks and 2 auxiliary tanks 15.5 gal. each at +47) (See NOTE 1 for data on unusable fuel) Control Surface Wing flaps 35° Down Movements Main surfaces Aileron 20° Up 20° Down Elevator 16.5° Up 15° Down Rudder 25° Right 25° Left (Parallel to W.L.) Tab (main surface in neutral) Aileron 20° Up 20° Down Elevator 10° Up 26° Down Rudder 17° Right 22° Left (Parallel to W.L.) Serial Nos. Eligible 320B0001 thru 320B0062 3A25 6 Rev. 28 V. Model 320C, Skyknight, (Normal Category), Approved April 24, 1964 Engines Two Continental TSIO-470-D *Fuel 100/130 minimum grade aviation gasoline (see NOTE 5). *Engine Limits For all operations, 2600 rpm, 260 hp, 35 in. Hg MP Critical altitude is 16,000 ft. in standard atmosphere. Propeller and 1. 2 McCauley full-f eathering propeller installations Propeller Limits a. McCauley hubs D2AF34C54 with 84HF blades Diameter: not over 81 in., not under 78 in. No further reduction permitted Pitch settings at 30 in. sta.: low 14.0°, high 15.6°, feathered 82.7° b. Hydraulic governor, Woodward 210280, C210355, 210444, A210438; McCauley DCFU290D1/T2, DCFU290D2/T2 c. Propeller spinner, Cessna 0850331-2 dome with 0850257-7 bulkhead *Airspeed Limits Never exceed 257 m.p.h. (224 knots) (CAS) Maximum structural cruising 210 m.p.h. (183 knots) Maneuvering 170 m.p.h. (148 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (+38.0) to (+43.1) at 5200 lb. (+43.6) at 4800 lb. (+32.0) to (+43.6) at 4300 lb. or less Straight line variation between points given. Empty Wt. C.G. Range None *Maximum Weight Landing: 5200 lb. Takeoff: 5200 lb. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lb. on floor at (+96), 80 lb. per side on floor (+124), 120 lb. per nacelle (+63) Oil Capacity 6.5 gal. (3.25 ga l. in each engine at (-3.5), unusable 1.5 gal. per engine) (See NOTE 1 for data on undrainable oil) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) or 133 gal. (with 2 wing tip tanks and 2 auxiliary tanks 15.5 gal. each at +47) (See NOTE 1 for data on unusable fuel) Control Surface Wing flaps 35° Down Movements Main surfaces Aileron 20° Up 20° Down Elevator 16.5° Up 15° Down Rudder 25° Right 25° Left (Parallel to W.L.) Tab (main surface in neutral) Aileron 20° Up 20° Down Elevator 10° Up 26° Down Rudder 17° Right 22° Left (Parallel to W.L.) Serial Nos. Eligible 320C0001 thru 320C0073 Rev. 28 7 3A25 VI. Model 320D, Skyknight, (Normal Category), Approved April 9, 1965 Engines Two Continental TSIO-520-B or TSIO-520-BB *Fuel 100/130 minimum grade aviation gasoline (see NOTE 5). *Engine Limits For all operations, 2700 rpm, 285 hp, 35 in. Hg MP Critical altitude is 16,000 ft. in standard atmosphere. Altitude Max. Allowable MP 16,000 ft. 32.0 in. Hg 18,000 ft. 30.7 in. Hg 20,000 ft. 29.0 in. Hg 22,000 ft. 26.4 in. Hg 24,000 ft. 24.3 in. Hg 26,000 ft. 22.2 in. Hg 28,000 ft. 20.2 in. Hg 30,000 ft. 18.5 in. Hg Propeller and 1. 2 full-feathering 2-bladed propeller installations Propeller Limits a. McCaul ey hubs D2AF34C71 with 84JF blades Diameter: not over 81 in., not under 79 in. No further reduction permitted Pitch settings at 30 in. sta.: low 13.3°, high 14.8°, feathered 82.7° b. Hydraulic governor, Woodward B210446, A210529 c. Propeller spinner, Cessna 0855032-1 dome with 0855032-2 bulkhead 2. 2 full-feathering 3-bladed pr opeller installations (See NOTES 7 & 8). a. McCauley hubs 3AF32C87 with 82NC-4 blades or McCauley hubs 3AF32C72 with 82N-4 blades Diameter: not over 78 in., not under 74 in. No further reduction permitted Pitch settings at 30 in. sta.: 3AF32C72 Hubs: low 12.7°, feathered 82.3° 3AF32C87 Hubs: low 13.0°, feathered 82.6° b. Hydraulic governor, Woodward B210446, A210529 c. Propeller spinner, 3-bladed, McCauley D-3534 dome with D-3537 bulkhead 3. 2 full-feathering 3-bladed propeller installations (See NOTE 8). a. McCauley hubs 3AF 32C504 with 82NEA-4 blades Diameter: not over 78 in., not under 74 in. No further reduction permitted Pitch settings at 30 in. st a.: low 13.0°, feathered 82.6° b. Hydraulic governor, Woodward B210446, A210529 c. Propeller spinner, 3-bladed, Mc Cauley D3534 dome with D3537 bulkhead *Airspeed Limits Never exceed 257 m.p.h. (224 knots) (CAS) Maximum structural cruising 210 m.p.h. (183 knots) Maneuvering 170 m.p.h. (148 knots) Flaps extended 140 m.p.h. (122 knots) Landing gear extended 140 m.p.h. (122 knots) *C.G. Range (+38.0) to (+43.1) at 5200 lb. (+43.6) at 4800 lb. (+32.0) to (+43.6) at 4300 lb. or less Straight line variation between points given. Empty Wt. C.G. Range None 3A25 8 Rev. 28 VI. Model 320D (cont’d) *Maximum Weight Landing: 5200 lb. Takeoff: 5200 lb. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. *Maximum Baggage 200 lb. on floor at (+96), 80 lb. per side on floor (+124), 120 lbs per nacelle (+63) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) or 143 gal. (with 2 wing tip tanks and 2 auxiliary tanks 20.5 gal. each at +47) (See NOTE 1 for data on unusable fuel) Oil Capacity 6.5 gal. (3.25 ga l. in each engine at (-3.5), unusable 1.5 gal. per engine) (See NOTE 1 for data on unusable oil) Control Surface Wing flaps 35° Down Movements Main surfaces Aileron 20° Up 20° Down Elevator 16.5° Up 15° Down Rudder 29.3° Right 29.3° Left (parallel to W.L.) Tab (main surface in neutral) Aileron 20° Up 20° Down Elevator 10° Up 26° Down Rudder 17° Right 22° Left (parallel to W.L.) Serial Nos. Eligible 623, 320D0001 thru 320D0130 VII. Model 320E, Executive Skyknight, (N ormal Category), Approved July 26, 1966 Engines Two Continental TSIO-520-B or TSIO-520-BB *Fuel 100/130 minimum grade aviation gasoline (see NOTE 5). *Engine Limits For all operations, 2700 rpm, 285 hp, 32 in. Hg MP Critical altitude is 16,000 ft. in standard atmosphere. Altitude Max. Allowable MP Sea level 32.0 in. Hg 16,000 ft. 32.0 in. Hg 18,000 ft. 30.7 in. Hg 20,000 ft. 29.0 in. Hg 22,000 ft. 26.4 in. Hg 24,000 ft. 24.3 in. Hg 26,000 ft. 22.2 in. Hg 28,000 ft. 20.2 in. Hg 30,000 ft. 18.5 in. Hg 32,000 ft. 17.0 in. Hg Rev. 28 9 3A25 VII. Model 320E (cont’d) Propeller and 1. 2 full-feathering 2-bladed propeller installations Propeller Limits a. McCauley Hubs D2AF34C71 with 84JF blades Diameter: not over 81 in., not under 79 in. No further reduction permitted Pitch settings at 30 in. sta.: low 13.3°, high 14.8°, feathered 82.7° b. Hydraulic governor, Woodward B210446, A210529 c. Propeller spinner, Cessna 0855032-1 dome with 0855032-2 bulkhead 2. 2 full-feathering 3-bladed propeller installations (See NOTE 8) a. McCauley hubs 3AF32C87 with 82NC-4 blades or McCauley hubs 3AF32C504 with 82NEA-4 blades Diameter: not over 78 in., not under 74 in. No further reduction permitted Pitch settings at 30 in. st a.: low 13.0°, feathered 82.6° b. Hydraulic governor, Woodward B210446, A210529 c. Propeller spinner, 3-bladed, McCauley D-3534 dome with D-3537 bulkhead *Airspeed Limits Never exceed 257 mph (224 knots) (CAS) Maximum structural cruising 210 mph (183 knots) Maneuvering 170 mph (148 knots) Flaps extended 160 mph (139 knots) Landing gear extended 160 mph (139 knots) *C.G. Range (+39.3) to (+43.1) at 5300 lb. (+43.6) at 4900 lb. (+32.0) to (+43.6) at 4300 lb. or less Straight line variation between points given. Empty Wt. C.G. Range None *Maximum Weight Landing: 5300 lb. Takeoff: 5300 lb. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lb. on floor at (+96), 80 lb. per side on floor (+124), 120 lb. per nacelle (+63) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) or 143 gal. (with 2 wing tip tanks and 2 auxiliary tanks 20.5 gal. each at +47) or 183 gal. (with 2 wing tip tanks, 2 auxiliary ta nks and 2 wing locker transfer tanks 20 gal. each at +49.0) (See NOTE 1 for data on system fuel) Oil Capacity 6.5 gal. (3.25 ga l. in each engine at (-3.5), unusable 1.5 gal. per engine) (See NOTE 1 for data on system oil) 3A25 10 Rev. 28 VII. Model 320E (cont’d) Control Surface Wing flaps 35° Down Movements Main surfaces Aileron 20° Up 20° Down Elevator 16.5° Up 15° Down Rudder 29.3° Right 29.3° Left (parallel to W.L.) Tab (main surface in neutral) Aileron 20° Up 20° Down Elevator 10° Up 26° Down Rudder 17° Right 22° Left (parallel to W.L.) Serial Nos. Eligible 320E0001 thru 320E0110 VIII. Model 320F, Executive Skyknight, (Normal Category), Approved May 10, 1967 Engines Two Continental TSIO-520-B or TSIO-520-BB *Fuel 100/130 minimum grade aviation gasoline (see NOTE 5). *Engine Limits For all operations, 2700 rpm, 285 hp, 32 in. Hg MP Critical altitude is 16,000 ft. in standard atmosphere. Altitude Max. Allowable MP Sea level 32.0 in. Hg 16,000 ft. 32.0 in. Hg 18,000 ft. 30.7 in. Hg 20,000 ft. 29.0 in. Hg 22,000 ft. 26.4 in. Hg 24,000 ft. 24.3 in. Hg 26,000 ft. 22.2 in. Hg 28,000 ft. 20.2 in. Hg 30,000 ft. 18.5 in. Hg 32,000 ft. 17.0 in. Hg Propeller and 1. 2 full-feathering 2-bladed propeller installations Propeller Limits a. McCauley Hubs D2AF34C71 with 84JF blades Diameter: not over 81 in., not under 79 in. No further reduction permitted Pitch settings at 30 in. sta.: low 13.3°, high 14.8°, feathered 82.7° b. Hydraulic governor, Woodward B210446, A210529 c. Propeller spinner, Cessna 0855032-1 dome with 0855032-2 bulkhead 2. 2 full-feathering 3-bladed propeller installations (See NOTE 8) a. McCauley hubs 3AF32C87 with 82NC-4 blades or McCauley hubs 3AF32C504 with 82NEA-4 blades Diameter: not over 78 in., not under 74 in. No further reduction permitted Pitch settings at 30 in. st a.: low 13.0°, feathered 82.6° b. Hydraulic governor, Woodward B210446, A210529 c. Propeller spinner, 3-bladed, McCauley D-3534 dome with D-3537 bulkhead *Airspeed Limits Never exceed 257 m.p.h. (224 knots) (CAS) Maximum structural cruising 210 m.p.h. (183 knots) Maneuvering 170 m.p.h. (148 knots) Flaps extended 160 m.p.h. (139 knots) Landing gear extended 160 m.p.h. (139 knots) Rev. 28 11 3A25 VIII. Model 320F (cont’d) *C.G. Range (+39.3) to (+43.1) at 5300 lb. (+43.6) at 4900 lb. (+32.0) to (+43.6) at 4300 lb. or less Straight line variation between points given. Empty Wt. C.G. Range None *Maximum Weight Landing: 5300 lb. Takeoff: 5300 lb. No. of Seats 5 (Std.) (2 at +37, 3 at +71). See Manufacturer's Weight and Balance data sheet for optional seating arrangements. Maximum Baggage 200 lb. on floor at (+96), 80 lb. per side on floor (+124), 120 lb. per nacelle (+63) Fuel Capacity 102 gal. (2 wing tip tanks, 51 gal. each at +35.0) or 143 gal. (with 2 wing tip tanks and 2 auxiliary tanks 20.5 gal. each at +47) or 183 gal. (with 2 wing tip tanks, 2 auxiliary ta nks and 2 wing locker transfer tanks 20 gal. each at +49.0) (See NOTE 1 for data on system fuel) Oil Capacity 6.5 gal. (3.25 ga l. in each engine at (-3.5), unusable 1.5 gal. per engine) (See NOTE 1 for data on system oil) Control Surface Wing flaps 35° Down Movements Main surfaces Aileron 20° Up 20° Down Elevator 16.5° Up 15° Down Rudder 29.3° Right 29.3° Left (parallel to W.L.) Tab (main surface in neutral) Aileron 20° Up 20° Down Elevator 10° Up 26° Down Rudder 17° Right 22° Left (parallel to W.L.) Serial Nos. Eligible 658, 320F0001 thru 320F0045 IX. Model 340, (Normal Category), Approved October 15, 1971 Engines Two Teledyne Continental TSIO-520-K or TSIO-520-KB *Fuel 100/130 minimum grade aviation gasoline (see NOTE 5). *Engine Limits For all operations, 2700 rpm, 285 hp, 33.0 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 rpm. Altitude (ft.) Max. Allowable MP (in. Hg) 16,000 ft. 33.0 18,000 ft. 30.2 20,000 ft. 28.0 23,000 ft. 24.5 26,000 ft. 21.5 29,000 ft. 19.0 3A25 12 Rev. 28 IX. Model 340 (cont’d) Propeller and 1. 2 full-feathering 2-bl aded propeller standard installations Propeller Limits a. McCauley hubs D2AF34C71 with 84JF-3 blades Diameter: not over 81 in., not under 79 in. No further reduction permitted Pitch settings at 30 in. st a.: low 13.3°, feathered 82.7° b. Hydraulic governor, Woodward B210446, A210529; McCauley DCFS290D1/T3, DCFUS2990D1/T3, DCFS290D7/T3, DCFUS290D7/T3 or DCFUS290D13/T3 c. Propeller spinner, McCauley D-3800 dome with D3818 bulkhead 2. 2 full-feathering 3-bladed optio nal propeller installations (See NOTE 8). a. McCauley hubs 3AF32C87 with 82NC-4 blades or McCauley hubs 3AF32C504 with 82NEA-4 blades Diameter: not over 78 in., not under 74 in. No further reduction permitted Pitch settings at 30 in. st a.: low 13.0°, feathered 82.6° b. Hydraulic governor, Woodward B210446, A210529; McCauley DCFS290D1/T3, DCFUS290D1/T3, DCFS290D7/T3, DCFUS290D7/T3 or DCFUS290D13/T3 c. Propeller spinner, McCauley D-3534 dome with D3796 bulkhead *Airspeed Limits S/N 340-0001 thru 340-0300 (CAS) Maneuvering 179 m.p.h. (155 knots) Maximum structural cruising 230 m.p.h. (200 knots) Never exceed 270 m.p.h. (234 knots) Flaps extended 15° 180 m.p.h. (156 knots) Flaps extended 45° 160 m.p.h. (139 knots) Landing gear extended 160 m.p.h. (139 knots) S/N 340-0301 and On Maneuvering 155 knots (179 m.p.h.) Maximum structural cruisi ng 200 knots (230 m.p.h.) Never exceed 234 knots (270 m.p.h.) Flaps extended 15° 160 knots (184 m.p.h.) Flaps extended 45° 140 knots (161 m.p.h.) Landing gear extended 140 knots (161 m.p.h.) *C.G. Range Landing gear extended (+150.41) to (+155.59) at 5975 lb. (T.O. and landing) to (+155.96) at 5575 lb. (+146.09) to (+155.96) at 5075 lb. or less Straight line variation between points given. Landing gear retracted moment change: +860 in.-lb. Empty Wt. C.G. Range None *Maximum Weight Landing: 5975 lb. Takeoff: 5975 lb. No. of Seats 6 (2 at +137.0, 2 at +175.0, 2 at +204.0). See Manufacturer's Equipment List for optional seating arrangements. Maximum Baggage 350 lb. at (+77.0), 240 lb. at (+184.25) and 340 lb. at (+242.0) Rev. 28 13 3A25 IX. Model 340 (cont’d) Fuel Capacity Tank Capacity (Gal) Usable (Gal) Moment Arm S/N 340-0001 and On LH tip tank 51 50 +150.25 RH tip tank 51 50 +150.25 LH aux. tank (40 gal. opt) 20.5 20 +162.25 RH aux. tank (40 gal. opt) 20.5 20 +162.25 LH wing locker tank 20.5 20 +164.25 RH wing locker tank 20.5 20 +164.25 S/N 340-0151 and On LH aux. tank (63 gal. opt) 32 31.5 +162.25 RH aux. tank (63 gal. opt) 32 31.5 +162.25 (See NOTE 1 for data on unusable fuel) Oil Capacity 26 qt. (13 qt. each engine at (+111.75), usable 5.52 qt. per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps 45° Down Movements Main surfaces Aileron 20° Up 20° Down Elevator 20° Up 15° Down Rudder (Parallel to water line) 29° Right 29° Left (Perpendicular to hinge) 32° Right 32° Left Tabs (main surface in neutral) Aileron 20° Up 20° Down Elevator 10° Up 16° Down Rudder (Parallel to water line) 16° Right 21° Left (Perpendicular to hinge) 19° Right 24° Left Serial Nos. Eligible 340-0001 thru 340-0115 (1972) 340-0151 thru 340-0260 (1973) 340-0301 thru 340-0370 (1974) 340-0501 thru 340-0555 (1975) X. Model 340A, (Normal Category ), Approved November 19, 1975 Engines S/N 340A0001 thru 340A0600 Two Teledyne Continental TSIO-520-N or TSIO-520-NB S/N 340A0601 and On Two Teledyne Continental TSIO-520-NB *Fuel 100/130 minimum grade aviation gasoline (see NOTE 5). *Engine Limits For all operations, 2700 rpm, 310 hp, 38 in. Hg MP up to critical altitude of 20,000 ft., in standard atmosphere. Above 20,000 ft., the following ma ximum MP applies for maximum r.p.m. Altitude (ft.) Max. Allowable MP (in. Hg) 20,000 ft. 38.0 22,000 ft. 35.2 24,000 ft. 32.3 26,000 ft. 29.8 28,000 ft. 27.4 30,000 ft. 25.0 3A25 14 Rev. 28 X. Model 340A (cont’d) Propeller and 1. 2 full-feathering 3-bladed pr opeller standard installations (See NOTE 9) Propeller Limits a(1) McCauley hubs 3AF32C 93 with 82NC-5.5 blades or McCauley hubs 3AF32C505 with 82NEA-5.5 blades Diameter: not over 76.5 in., not under 75 in. No further reduction permitted Pitch settings at 30 in. st a.: low 14.9°, feathered 81.2° or a(2) McCauley hubs 3AF32C93 w ith 82NC-6.5 blades or McCauley hubs 3AF32C505 with 82NEA-6.5 blades Diameter: not over 75.5 in., not under 75 in. No further reduction permitted Pitch settings at 30 in. st a.: low 15.2°, feathered 81.2° b. S/N 340A0001 thru 340A0400 Hydraulic governor, McCauley DCFS290D4/T3, DCFS290D5/T3, DCFUS290D4/T3, DCFUS290D5/T3, DCFS290D7/T3, DCFS290D8/T3, DCFUS290D7/T3, DCFUS290D8/T3, DCFUS290D12/T3 or DCFUS290D13/T3 S/N 340A0401 thru 340A1500 Hydraulic governor, McCauley DCFS290D4/T3, DCFS290D6/T3, DCFUS290D4/T3, DCFUS290D6/T3, DCFS290D7/T3, DCFS290D8/T3, DCFUS290D7/T3, DCFUS290D8/T3, DCFUS290D12/T3 or DCFUS290D13/T3 S/N 340A1501 and On Hydraulic governor, McCauley DCFS290D9/T3, DCFUS290D9/T3 c. Propeller spinner, McCauley D-3534 dome with D3796 bulkhead *Airspeed Limits Maneuvering 155 KIAS (179 m.p.h.) Maximum structural cruising 200 KIAS (230 m.p.h.) Never exceed 234 KIAS (269 m.p.h.) Flaps extended 15° 160 KIAS (184 m.p.h.) Flaps extended 45° 142 KIAS (163 m.p.h.) Landing gear extended 140 KIAS (161 m.p.h.) C.G. Range Landing gear extended (+150.41) to (+155.59) at 5990 lb. (T.O. and landing) to (+155.96) at 5590 lb. (+146.09) to (+155.96) at 5075 lb. or less Straight line variation between points given. Landing gear retracted moment change: +860 in.-lb. Empty Wt. C.G. Range None Rev. 28 15 3A25 X. Model 340A (cont’d) *Maximum Weight S/N 340A0001 thru 340A0400 Landing: 5990 lb. Takeoff: 5990 lb. S/N 340A0401 and On Landing: 5990 lb. Takeoff: 5990 lb. Ramp: 6025 lb. No. of Seats 6 (2 at +137.0, 2 at +175.0, 2 at +204.0). See Manufacturer's Equipment List for optional seating arrangements Maximum Baggage 350 lb. at (+77.0), 240 lb . at (+184.25), and 340 lb. at (+242.0) Fuel Capacity Capacity Usable Moment Tank Gal. Gal. Arm LH tip tank 51 50 +150.25 RH tip tank 51 50 +150.25 LH aux. tank (40 gal. opt) 20.5 20 +162.25 RH aux. tank (40 gal. opt) 20.5 20 +162.25 LH aux. tank (63 gal. opt) 32 31.5 +162.25 RH aux. tank (63 gal. opt) 32 31.5 +162.25 LH wing locker tank 20.5 20 +164.25 RH wing locker tank 20.5 20 +164.25 (See NOTE 1 for data on unusable fuel) Oil Capacity 26 qt. (13 qt. each engine at (+111.75), usable 5.52 qt. per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps 45° Down Movements Main surfaces Aileron 20° Up 20° Down Elevator 20° Up 15° Down Rudder (parallel to water line) 29° Right 29° Left (perpendicular to hinge) 32° Right 32° Left Tabs (main surface in neutral) Aileron 20° Up 20° Down Elevator 10° Up 16° Down Rudder (parallel to water line) 16° Right 21° Left (perpendicular to hinge) 19° Right 24° Left Serial Nos. Eligible 340A0001 thru 340A0125 (1976) 340A0201 thru 340A0375 (1977) 340A0401 thru 340A0562 (1978) 340A0601 thru 340A0801 (1979) 340A0901 thru 340A1045 (1980) 340A1201 thru 340A1280 (1981) 340A1501 thru 340A1543 (1982) 340A1801 thru 340A1817 (1984) XI. Model 335, (Normal Category), Approved October 2, 1979 Engines Two Teledyne Continental TSIO-520-EB *Fuel 100 or 100 low-lead minimum grade aviation gasoline (See NOTE 5 for optional anti-icing additive) 3A25 16 Rev. 28 XI. Model 335 (cont’d) *Engine Limits For all operations, 2700 rpm., 300 hp, 34.5 in. Hg MP up to a critical altitude of 16,000 ft. in standard a tmosphere. Above 16,000 ft. the following maximum MP applies for maximum rpm. Max. Allowable Altitude (ft.) 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 1. 2 full-feathering 3-bladed pr opeller standard installations (See NOTE 8). Propeller Limits a. McCauley hubs 3AF32C 87 with 82NC-5.5 blades or McCauley hubs 3AF32C504 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. st a.: low 14.2° feathering 81.2° b. Hydraulic governor, McCauley DCFS290D7/T3, DCFS290D8/T3, DCFUS290D7/T3, DCFUS290D8/T3, DCFUS290D12/T3 or DCFUS290D13/T3 c. Propeller spinner and bulkhead assembly, McCauley D-3534/D-3796 *Airspeed Limits Maneuvering 155 KIAS (179 m.p.h.) Max. structural crui sing 200 KIAS (230 m.p.h.) Never exceed 234 KIAS (269 m.p.h.) Flaps extended 15° 160 KIAS (184 m.p.h.) Flaps extended 45° 142 KIAS (163 m.p.h.) Landing gear extended 140 KIAS (161 m.p.h.) C.G. Range Landing gear extended (+150.41) to (+155.59) at 5990 lbs. (T.O . and landing) to (+155.96) at 5590 lbs. (+146.09) to (+155.96) at 5075 lbs. or less Straight line variation between points given. Landing gear retracted moment change: +860 in.-lb. Empty Wt. C.G. Range None *Maximum Weight Landing: 5990 lb. Takeoff: 5990 lb. Ramp: 6025 lb. No. of Seats 6 (2 at +137.0, 2 at +175.0, 2 at + 204.0). See manufacturer's equipment list for optional seating arrangements Maximum Baggage 350 lb. at (+77.0), 240 lb . at (+184.25), and 340 lb. at (+242.0) Rev. 28 17 3A25 XI. Model 335 (cont’d) Fuel Capacity Capacity Usable Moment Tank Gal. Gal. Arm LH tip tank 51 50 +150.25 RH tip tank 51 50 +150.25 LH aux tank (40 gal. opt) 20.5 20 +162.25 RH aux. tank (40 gal. opt) 20.5 20 +162.25 LH aux. tank (63 gal. opt) 32 31.5 +162.25 RH aux. tank (63 gal. opt) 32 31.5 +162.25 LH wing locker tank 20.5 20 +164.25 RH wing locker tank 20.5 20 +164.25 (See NOTE 1 for data on unusable fuel) Oil Capacity 26 qt. (13 qt. each engine at (+111.75), usable 5.52 qt. per engine) (See NOTE 1 for data on undrainable oil) Control Surface Wing flaps Down 45° +1°, -0° Movements Main surfaces Aileron Up 20° +1°, -0° Down 20° +1°, -0° Elevator Up 20° +1°, -0° Down 15° +1°, -0° Rudder (parallel to water line) Right 29° +1°, -0° Left 29° +1°, -0° (perpendicular to hinge) Right 32° +1°, -0° Left 32° +1°, -0° Tabs (main surface in neutral) Aileron Up 20° +1°, -0° Down 20° +1°, -0° Elevator Up 10° +1°, -0° Down 16° +1°, -0° Rudder (parallel to water line) Right 16° +1°, -0° Left 21° +1°, -0° (perpendicular to hinge) Right 19° +1°, -0° Left 24° +1°, -0° Serial Nos. Eligible 335-0001 thru 335-0065 Data Pertinent to All Models Datum Model 320 Series: Fu selage station 0.00 The forward face of fuselage bulkhead forward of the rudder pedals is at FS 0.00. Model 335 and Fuselage station 0.00 340 Series: The forward face of fuselage bulkhead forward of the rudder pedals is at FS 100.00. Leveling Means Model 320 Series: External splice pl ate on left side of fuselage under cabin windows. Model 335 and External leveling screws at FS 185.46 and 340 Series: FS 209.96 on W.L. 116.0 Certification Basis: Model 320 Series: CAR Part 3 effective May 15, 1956, as amended by 3-1 through 3-5. Model 340: CAR Part 3 effective May 15, 1956, as amended by 3-1 through 3-5 and 3-8, except Subpart B; and Part 23 Subpart B and 23.959, 23.1041 and 23.1305(p) of the Federal Aviation Regulations (FAR) effective February 1, 1965, as amended by 23-1 through 23-7 and the following exemption No. 1435, FAR 23.1387(d) (CAR 3.702) "Aft Position Light Vertical Angle Coverage." 3A25 18 Rev. 28 Data Pertinent to All Models Model 340A and 335: CAR Part 3 effective May 15, 1956, as amended by 3-1 through 3-5 and 3-8 except Subpart B and paragraphs 3.437(a)(b)(c)(d) (f), 3.581, and 3.666. Include the following portions of FAR 23, dated February 1, 1965, as amended by 23-1 through 23-7: Subpart B and paragraphs 23.959, 23.1041and 23.1305(p). Include paragraphs 23.1387(e) as amended by 23-12, 23.1327 as amended through 23-23, and FAR 36, dated December 1, 1969, as amended by 36-1 through 36-4 (36-10, Model 335). Findings of Equivalent Level of Safety (ELOS) were made for CAR 3.757 and 3.778(a). S/N 340-0301 and On, Models 340A and 335: Markings, placards, and manuals are primarily in knots instead of mph, as required by CAR 3, but permitted by FAR 23, Amendment 23-7. S/N 340A0201 and On, and Model 335: 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 the Pilot's Operating Handbook and Factory Kit (FK) No. 194. S/N 335-0001 and On: In addition to the above certification basis, installed oxygen systems must comply with FAR 23.1441 of Amendment 23-9 effective June 17, 1970, to make the airplane eligible for operation at altitudes where supplemental oxygen is mandatory. Application for Type Certificate dated March 31, 1960. Type Certificate No. 3A25 issued May 24, 1961, obtained by the manufacturer under Delegation Option procedures. Production Basis: Production Certificate No. 312. 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. 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. Models 320, 320-1, 320A, 320B, 320C, 320D, 320E, 320F: Stall warning indicator, Cessna Drawing No. 0511062 2. Models 340, 340A, 335: Stall warning indicator, Cessna Drawing No. 5318100 or as modified by MEB-34-06. NOTE 1. Current weight and bala nce 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: Arm 320 340, 335 Tank Weight (lb.) Series Series LH tip tank 6.0 +44.0 +150.25 RH tip tank 6.0 +44.0 +150.25 LH aux. tank (40 gal. opt) 3.0 +47.0 +162.25 RH aux. tank (40 gal. opt) 3.0 +47.0 +162.25 LH aux. tank (63 gal. opt) 3.0 N/A +162.25 RH aux. tank (63 gal. opt) 3.0 N/A +162.25 LH wing locker tank 3.0 +49.0 +173.25 RH wing locker tank 3.0 +49.0 +173.25 Oil (both engines) 1.0 - 3.5 +111.75 Rev. 28 19 3A25 Data Pertinent to All Models NOTE 2. Model 340A S/N 340A0601 and On, Model 335 The placards specified in the FAA Approved Ai rplane Flight Manual (AFM) must be displayed. Model 320 Series, 340, 340A S/N 340A0001 thru 340A0600 The following placards must be displayed as indicated: Model 320 Series 1. Operational limits (on circuit box cover) a. "This airplane must be operated as a Normal Category airplane in compliance with the operating limitations as stated in the form of pla cards, markings, and manuals (Pilot's Check List)" b. "No acrobatic maneuvers, including spins, approved" c. (1) Models 320, 320E, 320F: "Minimum spee d for single engine operation, 88 m.p.h. (CAS)" Models 320-1, 320A, 320B, 320C, 320D: "Minimum speed for single engine operation, 90 m.p.h. (CAS)" (2) Models 320, 320-1, 320A, 320B, 320C, 320D: "Maximum gear extended speed, 140 m.p.h. (CAS)" Models 320E, 320F: "Maximum g ear extended speed, 160 m.p.h. (CAS)" (3) "Maximum flap extension speed (CAS) Models 320, 320-1, 320A: 15° Flaps - 160 m.p.h. Models 320, 320-1, 320A: 45° Flaps - 140 m.p.h. Models 320B, 320C: 15° Flaps - 160 m.p.h. Models 320D, 320E, 320F: 15° Flaps - 180 m.p.h. Models 320B, 320C, 320D: 35° Flaps - 140 m.p.h. Models 320E, 320F: 35° Flaps - 160 m.p.h." (4) Models 320, 320-1, 320A, 320B: "Maximum landing light exte nsion speed, 160 m.p.h. (CAS)" (5) Models 320-1, 320A, 320B, 320C, 320D, 320E, 320F: "Maximum maneuvering speed, 170 m.p.h. (CAS)" 2. On the instrument panel a. "Open defrost or cabin air during heater operation." b. "T & B Test" "Heater Overheat" "Push, T & B Test" c. (1) On panel placard (320, 320-1, 320A) "Flap Maximum Spee d Deflection m. p.h. (CAS) 15° 160 15° - 45° 140" (2) On panel mounted instruments (a) Models 320B, 320C "Flap position 0° - 15°, blue arc 160 m.p.h. (CAS) 15° - 35°, white arc 140 m.p.h. (CAS)" (b) Model 320D: "Flap position 0° - 15°, blue arc 180 m.p.h. (CAS) 15° - 35°, white arc 140 m.p.h. (CAS)" (c) Models 320E, 320F: "Flap position 0° - 15°, blue arc 180 m.p.h. (CAS) 15° - 35°, white arc 140 m.p.h. (CAS)" d. When wing locker transfer tanks are installed: "20 gal. - Empty - LH - ON - RH - OFF – Fuel Transfer - 20 gal." 3. On foul weather window Models 320, 320-1, 320A, 320B, 320C, 320D: "Do not open above 130 m.p.h. (CAS)" 3A25 20 Rev. 28 Data Pertinent to All Models NOTE 2 (cont’d) 4. Emergency exits a. On left emergency exit: (1) "Emergency exit - pull ring - push window out" (2) "Emergency window release pull" b. On right emergency exit: Models 320-1, 320A, 320B, 320C, 320D : "Emergency exit - force to open" 5. On control lock "Control lock - remove before starting engine" 6. On floor between front seats a. (1) Models 320, 320-1, 320A, 320B, 320C, 320D: "Left engine - 50 gal. - left on tank - right on tank - both off" (2) Models 320E, 320F: "50 gal. - left main - 50 gal. right main - left engine off" b. (1) Models 320, 320-1, 320A, 320B, 320C, 320D: "Right engine - 50 gal. - left on tank - right on tank - both off" (2) Models 320E, 320F: "50 gal. right main - 50 gal. left main - right engine off" c. (1) "Set fuel selector valves to left main tank for left engine and right main tank for right engine in takeoff, landing and all normal operation" (2) Models 320, 320-1, 320A: "Takeoff and land with auxiliary fuel pumps on. Use full rich mixture and auxiliary fuel pumps when switching fuel tanks. To extend gear manually, pull out crank to engage and turn clockwise. Caution: Push button and stow crank before operating electrically. Gear switch should be in neutral before operating manual system." (3) Models 320B, 320C, 320D, 320E, 320F: "Use main tanks for takeoff, landing and first 60 minutes of flight. Take off and land with auxiliary fuel pumps on. Use full rich mixture and auxiliary fuel pumps on low when switching fuel tanks. To extend gear manually, pull out crank to engage and turn clockwise. CAUTION: Gear switch should be in neutral before operating manual system. Push button and stow crank before operating electrically." (4) If optional wing locker transfer tanks are installed: "Use main tank for takeoff, landing and emergency." "Take off and land with auxiliary fuel pumps on." "Use full rich mixture and auxiliary fu el pumps on 'Low' when switching fuel tanks." (a) "Operate on main tanks until fu el quantity is less than 30 gal. per tank." (b) "Transfer wing locker fuel while opera ting on main tanks in straight and level flight." (c) "Turn transfer pumps off when lights illuminate." (d) "Use fuel cross feel system to balance main fuel quantities if one wing locker tank does not transfer or if a single wing locker tank is installed." (e) Models 320E, 320F: "Switch to auxiliary tanks when main fuel is again less than 30 gal. per tank." "To extend gear manually, pull out crank to engage and turn clockwise. CAUTION: Gear switch should be in neutral before operating manual system. Push button and stow crank before operating electrically." 7. Baggage faciliti es (See Manufacturer's Optional Equipment List for detail requirements) a. Baggage door (1) Models 320: "Maximum capacity, 200 lbs. See Weight and Balance Data for detailed loading instructions." (2) Models 320-1, 320A, 320B, 320C, 320D , 320E, 320F: "Maximum baggage capacity, 200 lbs. (Sta. 85 - 110). See Weight and Balan ce Data for detailed loading instructions." . b. On baggage wall, Sta. 132 (1) Model 320A: "Maximum baggage capacity 60 lb. See Weight and Balance Data for detailed loading instructions." or (2) Model 320A: "Maximum baggage capacity 80 lb. See Weight and Balance Data for detailed loading instructions." or (3) Models 320A, 320B, 320C, 320D, 320E, 320F : "Maximum baggage capacity 160 lb. (Sta. 110 - 132). See Weight and Balanc e Data for detailed loading instructions." c. On nacelle baggage door (1) Models 320B, 320C, 320D, 320E, 320F: "Maximum 120 lb. baggage" (2) Models 320E, 320F (If wing locker transfer tanks are installed): "Maximum 40 lb. baggage" Rev. 28 21 3A25 Data Pertinent to All Models NOTE 2 (cont’d) 8. Adjacent to fuel strainer "Fuel strainer - drain daily. NOTE: If water is observed at the fuel strainer, fuel tank sumps must be drained." 9. On engine control pedestal a. "Nose up - takeoff - nose down" b. "Cowl flaps - pull to close" c. "L - Nose - R" d. "L - Roll - R" e. Models 320, 320-1, 320A, 320B, 320C: "L Gen - Batt - R Gen - Ammeter - Select" Models 320D, 320E, 320F: "L Alt - Batt - R Alt - Ammeter – Select" f. "Engine alternate Air - pull out" - On upper control handle "L" - On lower control handle "R" 10. At appropriate locations a. "Tank and sump drain" b. "Cross feel line drains. Drain daily." c. "Air filter" d. Models 320, 320-1, 320A, 320B, 320C, 320D: "M aximum fuel 51 gal., minimum octane 100/130" Model 320E: "Fuel - 100/130 avia tion grade, usable fuel 50 gal." e. Models 320, 320-1, 320A, 320B, 320C: "Auxiliary - maximum fuel 15.5 gal., minimum octane 100/130" Model 320D: "Auxiliary - maximum fuel 20.5 gal., minimum octane 100/130" Model 320E: "Auxiliary fuel - 100/130 aviation grade usable fuel 20 gal." f. "Power off stall speeds (CAS) Configuration Angle of Ban k 0° 20° 40° 60° Model 320 Gear Up - Flaps Up 86 89 98 121 Gear Down - Flaps 45° 76 79 87 108 Model 320-1 Gear Up - Flaps Up 88 91 100 124 Gear Down - Flaps 45° 78 81 89 111 Model 320A Gear Up - Flaps Up 86 89 98 121 Gear Down - Flaps 45° 78 81 89 111 Models 320B, 320C, 320D Gear Up - Flaps Up 87 89 99 123 Gear Down - Flaps 35° 79 82 91 112 Models 320E, 320F Gear Up - Flaps Up 85 88 98 121 Gear Down - Flaps 15° 81 83 92 114 Gear Down - Flaps 35° 74 77 85 105" g. Models 320A, 320B, 320C, 320D, 320E, 320F: "R otating beacon required for proper rudder mass balance. Do not remove." h. With optional wing locker transfer tanks , "Transfer fuel - 100/130 aviation grade minimum - usable 20 gal." i. With optional wing locker transfer tanks, "Transfer Line - Drain Daily." 11. Replace placard 2F on floor between front seats with the following placard when auxiliary tanks are installed: a. Models 320, 320-1, 320A, 320B, 320C : "Left engine - 50 gal. - left main - left auxiliary 15 gal. right main 50 gal. - off" b. Model 320D: "Left engine - 50 ga l. - left main - left auxiliary 20 gal. - right main 50 gal. – off." c. Models 320E, 320F: "50 gal. left main - 50 gal. right main - 20 gal. left auxiliary - left engine." d. Models 320, 320-1, 320A, 320B, 320C: "Right engine - 50 gal. - left main - right auxiliary 15 gal. right main 50 gal. - off" e. Model 320D: "Right engine - 50 gal. - left main - right auxiliary 20 gal. - right main 50 gal. - off" f. Models 320E, 320F: "50 gal. right main - 50 gal. left main - 20 gal. right auxiliary – right engine off" 3A25 22 Rev. 28 Data Pertinent to All Models NOTE 2 (cont’d) g. "Use main tanks for takeoff, landing and first 60 minutes of flight" h. "Set fuel selector valves to left main tank for left engine and right main tank for right engine in takeoff, landing and all normal operation." i. Models 320, 320-1, 320A: "Take off and land wi th auxiliary fuel pumps on. Use full rich mixture and auxiliary pumps when switching tanks." j. Models 320B, 320C, 320D, 320E, 320F: "Take off and land with auxiliary fuel pumps on. Use full rich mixture and auxiliary pumps on low when switching fuel tanks." k. "To extend gear manually, pull out crank to engage and turn clockwise. CAUTION: Push button and stow crank before operating elec trically. Gear switch should be in neutral before operating manual system." Model 340 Series 12. Escape hatch: a. On emergency escape hatch window trim: "EMERGENCY EXIT" - "TURN HANDLE  OPEN" - "PULL DOOR INBD AND DOWN" b. On emergency escape hatch release cover: "EMERGENCY EXIT HANDLE" c. On executive tabletop (outbd. side) and writing desktop (fwd. side): "TABLE MUST BE STOW ED DURING TAKEOFF AND LANDING" 13. On left engine fuel selector valve: a. "50 GAL. - LEFT MAIN" (Green Sector) b. "50 GAL. - RIGHT MAIN" (Yellow Sector) c. "LEFT ENGINE - OFF" (Red Sector) d. If 20 gal. auxili ary tanks are installed: "20 GAL. - LEFT AUX." (Yellow and Green Sector) e. If 31.5 gal. auxili ary tanks are installed: “31.5 GAL. - RIGHT AUX. " (Yellow and Green Sector) 14. On right engine fuel selector valve: a. "50 GAL. - RIGHT MAIN" (Green Sector) b. "50 GAL. - LEFT MAIN" (Yellow Sector) c. "RIGHT ENGINE - OFF" (Red Sector) d. If 20 gal. auxili ary tanks are installed: "20 GAL. - LEFT AUX." (Yellow and Green Sector) e. If 31.5 gal. auxili ary tanks are installed: "31.5 GAL. - RIGHT AUX. " (Yellow and Green Sector) 15. On floor forward of fuel selectors: a. (1) For optional 40-gallon auxi liary tank prior to serial 340A0401, "SET FUEL SELECTOR VALVES TO LEFT MAIN TANK FOR LEFT ENGINE AND RIGHT MAIN TANK FOR RIGHT ENGINE IN TAKEOFF, LANDING, EMERGENCY AND FIRST 60 MIN. OF FLIGHT" (2) For optional 63-gallon auxi liary tank prior to serial 340A0401, "SET FUEL SELECTOR VALVES TO LEFT MAIN TANK FOR LEFT ENGINE AND RIGHT MAIN TANK FOR RIGHT ENGINE IN TAKEOFF, LANDING, EMERGENCY AND FIRST 90 MIN. OF FLIGHT" (3) For optional 40-gallon a uxiliary tank after serial 340A0401, "SET FUEL SELECTOR VALVES TO LEFT MAIN TANK FOR LEFT ENGINE AND RIGHT MAIN TANK FOR RIGHT ENGINE IN TAKEOFF, DESCENT, LANDING, EMERGENCY AND FIRST 60 MIN. OF FLIGHT" Rev. 28 23 3A25 Data Pertinent to All Models NOTE 2 (cont’d) (4) For optional 63-gallon a uxiliary tank after serial 340A0401, "SET FUEL SELECTOR VALVES TO LEFT MAIN TANK FOR LEFT ENGINE AND RIGHT MAIN TANK FOR RIGHT ENGINE IN TAKEOFF, DESCENT, LANDING, EMERGENCY AND FIRST 90 MIN. OF FLIGHT" b. "TAKE OFF AND LAND WITH AUXILIARY FUEL PUMPS ON" c. "USE FULL RICH MIXTURE AND AUXILIARY FUEL PUMPS ON 'LOW' WHEN SWITCHING TANKS" d. "100/130 GRADE AVIATION FUEL, MINIMUM" 16. If optional wing locker tanks are installed: a. "OPERATE ON MAIN TANKS UNTIL FUEL QUANTITY IS LESS THAN 180 LB. PER TANK" b. "TRANSFER WING LOCKER FUEL WH ILE OPERATING ON MAIN TANKS IN STRAIGHT AND LEVEL FLIGHT" c. "TURN TRANSFER PUMPS OFF WHEN LIGHTS ILLUMINATE" d. "USE FUEL CROSSFEED SYSTEM TO BALANCE MAIN FUEL QUANTITIES IF ONE WING LOCKER TANK DOES NOT TRANSFER OR IF A SINGLE WING LOCKER TANK IS INSTALLED" e. "SWITCH TO AUXILIARY TANKS WHEN MAIN FUEL IS AGAIN LESS THAN 180 LB. PER TANK" 17. On floor forward of fuel selectors: a. "TO EXTEND LANDING GEAR MANUALLY: (1) PLACE GEAR SWITCH IN NEUTRAL (2) PULL GEAR MOTOR CIRCUIT BREAKER (3) PULL CRANK TO ENGAGE (4) TURN CLOCKWISE TO EXTEND (5) PUSH BUTTON AND STOW CRANK" 18. On pilot's sun visor: a. On front side, "OPERA TIONAL LIMITS ON REVERSE SIDE" On reverse side, "OPERATIONAL LIMITS" b. S/N 340-0001 through 340-0300 (1) "THIS AIRCRAFT MUST BE OPERA TED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS (Pilot's Checklist) (2) NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED. (3) MINIMUM SINGLE ENGINE CONTROL SPEED 97 M.P.H. (CAS) (4) MAXIMUM GEAR EXTENSION SPEED: 160 M.P.H. (CAS) (5) MAXIMUM FLAP EXTENSION SPEED: 15° FLAP 180 M.P.H. (CAS) (6) MAXIMUM FLAP EXTENSION SPEED: 45° FLAP 160 M.P.H. (CAS) (7) MAXIMUM MANEUVERING SPEED: 179 M.P.H. (CAS) (8) LANDING WITH CABIN PRESSURIZED PROHIBITED. (9) THE STALL WARNING SYSTEM IS INOPERATIVE WHEN THE BATTERY SWITCH IS IN THE OFF POSITION (10) POWER OFF STALLS - (CAS) ANGLE OF BANK Configuration 0° 20° 40° 60° Gear and flaps up 91 94 105 129 Gear down flaps 15° 89 92 102 126 Gear down flaps 45° 82 85 94 116 " 3A25 24 Rev. 28 Data Pertinent to All Models NOTE 2 (cont’d) c. S/N 340-0301 and On (1) "THIS AIRCRAFT MUST BE OPERA TED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS (Pilot's Checklist) (2) NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED. (3) MINIMUM SINGLE ENGINE CONTROL SPEED - 84 KCAS (4) MAXIMUM GEAR EXTENSION SPEED - 140 KCAS (5) MAXIMUM FLAP EXTENSION SPEED: 15° FLAP, 160 KCAS (6) MAXIMUM FLAP EXTENSION SPEED: 45° FLAP, 140 KCAS (7) MAXIMUM MANEUVERING SPEED: 155 KCAS (8) LANDING WITH CABIN PRESSURIZED PROHIBITED. (9) POWER OFF STALLS (KCAS) ANGLE OF BANK Configuration 0° 20° 40° 60° Gear and flaps up 79 82 91 112 Gear down flaps 15° 71 80 88 109 Gear down flaps 45° 71 74 82 101" d. S/N 340A0001 thru 340A0400 (1) "THIS AIRPLANE MUST BE OPER ATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS (Pilot's Checklist). (2) NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED. (3) AIR MINIMUM CONTROL SPEED: 82 KIAS (4) MAXIMUM GEAR OPERATING SPEED: 140 KIAS (5) MAXIMUM GEAR EXTENDED SPEED: 140 KIAS (6) MAXIMUM FLAP EXTENDED SPEED: (15° FLAP) 160 KIAS (45° FLAP) 142 KIAS (7) MAXIMUM MANEUVERING SPEED: 155 KIAS (8) LANDING WITH CABIN PRESSURIZED PROHIBITED. IDLE POWER STALL SPEEDS (KIAS) Angle of Bank Configuration 0° 20° 40° 60° Gear and flaps up 83 85 94 117 Gear down flaps 15° 76 78 87 109 Gear down flaps 45° 71 73 81 103" e. S/N 340A0401 and On (1) "THIS AIRPLANE MUST BE OPER ATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND HANDBOOKS (Pilot's Checklist). (2) NO ACROBATIC MANEUVERS, INCLUDING SPINS, APPROVED. (3) AIR MINIMUM CONTROL SPEED: 82 KIAS. (4) MAXIMUM GEAR OPERATING SPEED: 140 KIAS. (5) MAXIMUM GEAR EXTENDED SPEED: 140 KIAS. (6) MAXIMUM FLAP EXTENDED SPEED 15°: 160 KIAS. (7) MAXIMUM FLAP EXTENDED SPEED 45°: 142 KIAS. (8) MAXIMUM MANEUVERING SPEED: 155 KIAS. (9) LANDING WITH CABIN PRESSURIZED PROHIBITED. Rev. 28 25 3A25 Data Pertinent to All Models NOTE 2 (cont’d) (10) THIS AIRPLANE IS APPROVED FOR DAY/NIGHT VFR CONDITIONS. IT IS APPROVED FOR DAY/NIGHT IFR CONDITIONS AND FLIGHTS INTO ICING CONDITIONS IF THE PROPER OPTIONAL EQUIPMENT IS INSTALLED AND OPERATIONAL. IDLE POWER STALL SPEEDS (KIAS) Angle of Bank Configuration 0° 20° 40° 60° Gear up - Flaps up 83 85 94 117 Gear down - Flaps 15° 76 78 87 109 Gear down - Flaps 45° 71 73 81 103 " 19. On instrument panel: a. If locator beacon is installed: "LOCATOR BEACON" "EMER - NORM" b. "PRESS AIR PULL TO DUMP" "RAG AIR" "LEFT AIR" "RIGHT AIR" c. "PRESS" "CABIN" "DEPRESS" d. "LANDING GEAR" "UP" "DOWN" e. "CABIN AIR" "FWD" "AFT" "DEFROST" "OPEN ONE CONTROL MINIMUM FOR HEATER OPERATION" f. "CABIN HEAT" "INCR" "ON-OFF" g. "PRESS AIR" "HEAT" h. "CABIN FAN" "HIGH-OFF-LOW" i. "WEMAC BLOWER" "HIGH-OFF-LOW" j. If wing locker fuel tanks are installed: "FUEL TRANSFER" "ON" "OFF" "LH" "RH" k. Near fuel tank quantity indicator selector switch: "MAIN-AUX" "LH AUX" "RH AUX" l. If propeller unfeathering accumulators are installed: "PROPELLER UNFEATHERING ACCU MULATORS ARE INSTALLED ON THIS AIRPLANE" m. When required with optional PN101 slaved gyro: "GYRO SLAVING - FAST - NORM" n. If 76.6 cu. ft. oxygen system is installed: "USE BLUE OXYGEN CONNECTOR ONLY" (S/N 340-0151 and on and Model 340A) o. "PROP - SYNC - ON - OFF MUST BE OFF FOR TAKEOFF, LDG. AND ONE ENGINE OPERATION" (S/N 340-0001 through 340-0150) p. Near propeller synchrophaser switch: "PHASE - SYNC - OFF" "MUST BE OFF FOR TAKEOFF, LANDING AND SINGLE ENGINE OPERATION" (S/N 340A0001 through 340A0400) q. Near amber indicator light: "PROP-SYNC" (S/N 340A0001 and up) r. Near phasing knob: "PHASING" (S/N 340A0001 and up) s. Near propeller synchrophaser switc h: "PHASE - OFF" "MUST BE OFF FOR TAKEOFF, LANDING AND SINGLE ENGI NE OPERATION" (S/N 340A0401 and On). 20. On engine control pedestal: a. "PROP - SYNC - ON - OFF" "MUST BE OFF FOR TAKEOFF, LDG., AND ONE ENGINE OPERATION" b. "TAKEOFF" (Range on elevator tr im tab indicator nose 2° down to nose 8° up) c. "NOSE DOWN - NOSE UP" d. "L NOSE R" e. "L ROLL R" f. "COWL FLAP - PULL TO CLOSE" "  LOCK  " " LOCK  " g. "ALTERNATE AIR" "PULL TO DETENT FOR COLD AIR" "FULL OUT FOR HEATED AIR (SEE CHECKLIST)" 3A25 26 Rev. 28 Data Pertinent to All Models NOTE 2 (cont’d) 21. Adjacent to alternate static source selector: a. S/N 340-0001 thru 340-0500: "Alternate Static Source" "Normal" "Alternate" b. S/N 340-0501 and On and Model 340A: "Stati c Pressure Source" "Normal" "Alternate" 22. On control lock: "CONTROL LOCK - REMOVE BEFORE STARTING ENGINES" "RUDDER LOCK" 23. Flap position: a. Blue Segment - 180 m.p.h. 0° to 15° b. White Segment- 160 m.p.h. 15° to 45° 24. On rudder horn: a. S/N 340-0001 thru 340-0500: "Rotating Beacon Required for Prope r Rudder Mass Balance. Do Not Remove" b. S/N 340-0501 and On and Model 340A: "Anti-Collision Light Required for Proper Rudder Mass Balance. Do Not Remove" 25. On wing locker doors: a. "MAX. BAGGAGE - 120 lb." b. If optional wing locker tanks are installed: Change Item (a) to "MAX. BAGGAGE - 40 lb." 26. On nose bay aft partition: a. S/N 340-0001 thru 340-0500: "Maximum Bagg age Allowance XX.X With Factory Installed Optional Equipment (Maximum Capacity 350 lb.)" b. S/N 340-0501 and On and Model 340A: "M aximum Baggage XX.X. Maximum Capacity 350 lbs., Less XX.X Optional Equipment" 27. On aft cabin wall: a. "MAXIMUM BAGGAGE CAPACITY - 340 POUNDS" b. "FOR BAGGAGE LOADING SEE WE IGHT AND BALANCE SECTION OF OWNER'S MANUAL" 28. At appropriate locations (exterior): a. "TANK AND SUMP DRAINS" b. "CROSSFEED LINE DRAINS" "DRAIN DAILY" c. "AIR FILTERS" d. "FUEL - 100/130 AVIATION GRADE MINIMUM - USABLE 50 GAL." e. With 20 gal. auxiliary fuel tanks installed: "AUXILIARY FUEL - 100/130 AVIATION GRADE MINIMUM - USABLE 20 GAL." f. With optional wing locker fuel tanks installed: "TRANSFER FUEL - 100/130 AVIATI ON GRADE MINIMUM - USABLE 20 GAL." "TRANSFER LINE - DRAIN DAILY" g. "FUEL STRAINER - DRAIN DAILY" " NOTE: IF WATER IS OBSERVED AT THE FUEL STRAINER, FUEL TANK SUMPS AND CRO SSFEED LINES MUST BE DRAINED" h. "LEVEL POINT - LEVEL POINT" i. On nose gear: "  TURN LIMITS  " "TURN  LIMITS - ALL RUDDER LOCKS MUST BE REMOVED BEFORE GROUND HANDLING" j. With optional locator beacon installed: "LOCATOR BEACON" "OFF - DISA RM SWITCH - NORM - DEACTIVATE AFTER R E S C U E " "LOCATOR BEACON" " NORM - TEST & EMER - ON & TEST" k. With 31.5 gal. auxiliary fuel tanks installed: "AUXILIARY FUEL - 100/130 AVIATION GRADE MINIMUM - USABLE 31.5 GAL." Rev. 28 27 3A25 Data Pertinent to All Models NOTE 2 (cont’d) 29. On side console: a. "AMMETER SELECT - AMPS - L ALT - R ALT - BATT - VOLTS" b. "MASTER PANEL - ON - OFF" "LIGHT DIMMING CONTROLS" "SIDE CONSOLE - STA PANEL - ENGINE INSTR - RADIO PANEL - FLIGHT INSTR - COMPASS LIGHT" NOTE 3. Models 340, 340A: The servic e manual contains a structural retirement life which may not be changed without FAA Engineering approval, for the following components: Item Part Number Hours Model Windshields 5311266-1 and -2 9,000 340, 340A NOTE 4. The following information sh all be provided in the form of markings, placards, or manuals: (Pilot's Check List) a. Takeoff flap setting 0° b. Maximum positive maneuvering load factor +3.8; flap up +2.0, flap extended. c. Models 320, 320-1, 320A, 320B, 320C, 320D, 320E, 320F: Maximum loss of altitude during normal stall recovery is 400 ft. and maxi mum pitch in power off stall is 45°. d. Model 340: Maximum loss of altitude during norma l stall recovery is 350 ft. and maximum pitch in power off stall is 25°. e. Models 340, 340A: Maximu m altitude without oxygen is 23,500 ft., with oxygen 30,000 ft. f. Models 340, 340A: Landing with cabin pressurized is prohibited). g. Loading schedule information. h. Models 340A, 335: Maximum loss of alt itude during normal stall recovery is 400 ft. NOTE 5. 1%, by volume, isopropyl alcoho l approved for use as fuel anti-icing additive when used as outlined in Cessna Service Letter No. ME73-25, dated November 2, 1973, or subsequent revisions. NOTE 6. Model 340A: New propellers or propellers modi fied to Cessna Drawing 5399005 with a maximum propeller diameter of 75.5 inches and a low pitch setting of 15.2° meet ICAO, Annex 16, noise requirements. NOTE 7. McCauley Hubs 3AF32C72 can not be intermixed with other hub models on the same airplane. NOTE 8. McCauley Hubs 3AF32C87 with blades as shown and McCauley hubs 3AF32C504 with blades as shown can be intermixed on the same airplane. Refer to FAA Approved McCauley Service Letter No. 1994-1. NOTE 9. McCauley Hubs 3AF32C93 with blades as shown and McCauley hubs 3AF32C505 with blades as shown can be intermixed on the same airplane. Refer to FAA Approved McCauley Service Letter No. 1994-16. In addition to the placards specified above, the prescribed operating limitations indicated by an asterisk (*) under Sections I through XI of this data sheet must also be displayed by permanent markings. --------- END -------- ``` ## ADs (43, in force first) - [AD 2023-09-09](https://openairdocs.org/ad/2023-09-09): Exhaust Turbine System (Recip) · Aerostar PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601), PA-60-601P (Aerostar 601P) and 292 more. Effective Jul 17, 2023 - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2022-03-15](https://openairdocs.org/ad/2022-03-15): Fuel Quantity Indicator · Garmin G3X Touch Electronic Flight Instrument System (STC SA01899WI or SA02658SE). Effective Mar 21, 2022 - [AD 2016-17-08](https://openairdocs.org/ad/2016-17-08): Elevator Tab Control System · Textron 310, 310A, 310B and 46 more. Effective Sep 12, 2016 - [AD 2014-03-03](https://openairdocs.org/ad/2014-03-03): Placards and Markings · Cessna 310, 310A, 310B and 37 more. Effective Apr 7, 2014 - [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005 - [AD 2004-25-16 R1](https://openairdocs.org/ad/2004-25-16-R1): Fuel regulator shutoff valve · Bombardier CL-215-1A10, CL-215-6B11 (CL-215T Variant), CL-215-6B11 (CL-415 Variant) and 64 more. Effective Jun 20, 2005 - [AD 2005-01-19](https://openairdocs.org/ad/2005-01-19): Mode S transponders · GARMIN International GTX 330D, GTX 330, GTX 33D and 830 more. Effective Feb 23, 2005 - [AD 2004-21-05](https://openairdocs.org/ad/2004-21-05): B-Seires Combustion Heaters · Bombardier CL-215-1A10, CL-215-6B11 (CL-215T Variant), CL-215-6B11 (CL-415 Variant) and 41 more. Effective Nov 19, 2004 - [AD 98-21-21 R1](https://openairdocs.org/ad/98-21-21-R1): Electric Inflatable Door Seals · Cessna 17-30, 17-30A, 17-31 and 267 more. Effective May 1, 2000 - [AD 2000-01-16](https://openairdocs.org/ad/2000-01-16): Exhaust System · Cessna 320, 320-1, 320A and 28 more. Effective Feb 15, 2000 - [AD 98-25-02](https://openairdocs.org/ad/98-25-02): Top-mounted Antenna · Bell Helicopter Textron Canada 407, 172, 172A and 243 more. Effective Dec 22, 1998 - [AD 98-24-14](https://openairdocs.org/ad/98-24-14): Exhaust System Components · Cessna 340A and 414A. Effective Dec 21, 1998 - [AD 98-04-28](https://openairdocs.org/ad/98-04-28): AFM - Limitations Section - Icing · Cessna 310R, 335, 340A and 12 more. Effective Mar 13, 1998 - [AD 97-01-13](https://openairdocs.org/ad/97-01-13): Fuel, Oil and Hydraulic Hoses · Cessna 150, 150A, 150B and 232 more. Effective Feb 3, 1997 - [AD 96-12-22](https://openairdocs.org/ad/96-12-22): Full Flow Engine Oil Adapter · Bellanca CH-300 Pacemaker, 120, 140 and 361 more. Effective Jul 31, 1996 - [AD 90-02-13](https://openairdocs.org/ad/90-02-13): Main Landing Gear · Cessna 310, 310A, 310B and 40 more. Effective Feb 5, 1990 - [AD 87-21-02 R1](https://openairdocs.org/ad/87-21-02-R1): Fuel Filler Openings · Cessna 310D, 310E, 310F and 41 more. Effective Jun 16, 1989 - [AD 88-03-07](https://openairdocs.org/ad/88-03-07): Inspect Fuel Lines · Cessna 340, 340A and 414. Effective Feb 10, 1988 - [AD 70-03-04 R1](https://openairdocs.org/ad/70-03-04-R1): Turbosupercharger Turbine Housing · Cessna 320D, 320E, 320F and 8 more. Effective Mar 28, 1987 - [AD 76-08-02 R2](https://openairdocs.org/ad/76-08-02-R2): Wing Tip Nose Cap · Cessna 310, 310A, 310B and 41 more. Effective Jan 31, 1983 - [AD 82-26-05](https://openairdocs.org/ad/82-26-05): Rudder Balance Weight Rib · Cessna 335, 340 and 340A. Effective Dec 27, 1982 - [AD 72-14-08 R1](https://openairdocs.org/ad/72-14-08-R1): Flexible Hose Assemblies · Cessna 310, 310A, 310B and 33 more. Effective Sep 4, 1981 - [AD 81-07-11 R1](https://openairdocs.org/ad/81-07-11-R1): Balance Weight Support Structure · Cessna 335, 340 and 340A. Effective Apr 17, 1981 - [AD 80-19-10](https://openairdocs.org/ad/80-19-10): Deicer Systems In Adverse Weather · Cessna 335 and 340A. Effective Sep 29, 1980 - [AD 80-17-04](https://openairdocs.org/ad/80-17-04): Fuel Flow Transducers · Aerosonic Fuel Flow Transducers, PA-60-600 (Aerostar 600), PA-60-601 (Aerostar 601) and 9 more. Effective Aug 13, 1980 - [AD 80-13-14](https://openairdocs.org/ad/80-13-14): Fuel Flow Transducer · Cessna 310R, 335, 340A and 4 more. Effective Jul 22, 1980 - [AD 78-14-01](https://openairdocs.org/ad/78-14-01): Optional Storage/Refreshment · Cessna 340 and 340A. Effective Jul 13, 1978 - [AD 78-13-05](https://openairdocs.org/ad/78-13-05): Improperly Installed Seats · Cessna 340, 340A, 402B and 7 more. Effective Jul 5, 1978 - [AD 78-05-06](https://openairdocs.org/ad/78-05-06): Flexible Fuel Cells · Cessna 180, 182, 185 and 98 more. Effective Jun 30, 1978 - [AD 78-11-05](https://openairdocs.org/ad/78-11-05): Autopilot Actuator · Cessna 210M, 310R, 340A and 9 more. Effective Jun 5, 1978 - [AD 73-22-01](https://openairdocs.org/ad/73-22-01): Fuel In Wing Leading Edge · Cessna 340, 401, 401A and 11 more. Effective May 29, 1978 - [AD 77-06-05](https://openairdocs.org/ad/77-06-05): Fire Hazard in Oxygen System · Cessna 340A. Effective Mar 31, 1977 - [AD 75-11-01](https://openairdocs.org/ad/75-11-01): Fuel Lines · Cessna 320, 320-1, 320A and 5 more. Effective Mar 22, 1976 - [AD 76-04-03](https://openairdocs.org/ad/76-04-03): ARC PA-500A Actuators · Cessna 172L, 172M, 177B and 43 more. Effective Feb 26, 1976 - [AD 74-20-01](https://openairdocs.org/ad/74-20-01): Main Landing Gear Trunnion · Cessna 310Q, 340, 402B and 2 more. Effective Sep 25, 1974 - [AD 74-08-01](https://openairdocs.org/ad/74-08-01): Autopilot Servo Actuators · Aircraft Radio Autopilot Servo Actuators, 172L, 172M and 29 more. Effective Apr 9, 1974 - [AD 73-07-07](https://openairdocs.org/ad/73-07-07): Fuel Hoses & Electrical Wiring Chafing · Cessna 310C, 310D, 310E and 19 more. Effective Apr 6, 1973 - [AD 72-03-07](https://openairdocs.org/ad/72-03-07): Landing Gear Failure · Cessna 310, 310A, 310B and 30 more. Effective Feb 9, 1972 - [AD 71-09-01](https://openairdocs.org/ad/71-09-01): Nacelle Electrical Failures · Cessna 320, 320-1, 320A and 5 more. Effective Apr 23, 1971 - [AD 69-15-09](https://openairdocs.org/ad/69-15-09): Fuel Starvation · Cessna 310, 310A, 310B and 6 more. Effective Jul 25, 1969 - [AD 69-14-01](https://openairdocs.org/ad/69-14-01): Fuel Starvation · Cessna 310G, 310H, 310I and 22 more - [AD 2016-07-24](https://openairdocs.org/ad/2016-07-24) (historical): Elevator Tab Control System · Textron 310, 310A, 310B and 46 more. Effective Apr 26, 2016 ## Registered aircraft by registry model (OpenAirDocs) - [Cessna 340A](https://openairdocs.org/model/cessna-340a): 543 aircraft (registry codes 2076405, 2073325) - [Cessna 340](https://openairdocs.org/model/cessna-340): 164 aircraft (registry code 2076404) - [Cessna 320D](https://openairdocs.org/model/cessna-320d): 30 aircraft (registry code 2074512) - [Cessna 320E](https://openairdocs.org/model/cessna-320e): 27 aircraft (registry code 2074514) - [Cessna 335](https://openairdocs.org/model/cessna-335): 26 aircraft (registry code 2075601) - [Cessna 320C](https://openairdocs.org/model/cessna-320c): 23 aircraft (registry code 2074510) - [Cessna 320B](https://openairdocs.org/model/cessna-320b): 21 aircraft (registry code 2074508) - [Cessna 320](https://openairdocs.org/model/cessna-320): 17 aircraft (registry code 2074502) - [Cessna 320F](https://openairdocs.org/model/cessna-320f): 12 aircraft (registry code 2074516) - [Cessna 320A](https://openairdocs.org/model/cessna-320a): 6 aircraft (registry code 2074506) - [Cessna 320-1](https://openairdocs.org/model/cessna-320-1): 1 aircraft (registry code 2074504) ## STCs approved under this data sheet (389, first 50) - [STC SA02571SE](https://openairdocs.org/stc/SA02571SE): Installation of Garmin G500/G600 TXi Integrated Avionics System (Primary Flight Display, Multi-Function Display, and Engine Indicating System Display).. Garmin International Inc. - [STC SA01800SE](https://openairdocs.org/stc/SA01800SE): Fabrication and installation of new or replacement of existing instrument panel lights dimmer control.. TCW Technologies, LLC - [STC SA01861SE](https://openairdocs.org/stc/SA01861SE): Fabrication and installation of Landing Light Controller. TCW Technologies, LLC - [STC SA01844WI](https://openairdocs.org/stc/SA01844WI): Installation of Garmin GFC 600 Automatic Flight Control System. Garmin International Inc. - [STC SA02279AT](https://openairdocs.org/stc/SA02279AT): Installation of a Boom Beam bulb, starter, and ballast. Whelen Aerospace Technologies - [STC SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA12406WI](https://openairdocs.org/stc/SA12406WI): Installation of a Garmin AXIS Flight Display System. Garmin International Inc. - [STC SA02636SE](https://openairdocs.org/stc/SA02636SE): Installation of Garmin GPS 175 Navigation System and GNX 375 Navigation System with ADS-B In/Out Transponder.. Garmin International Inc. - [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA800EA](https://openairdocs.org/stc/SA800EA): Installation of Whelen Anti-Collision, Position, or Anti-Collision/Position Light System, and applicable associated power supplies. Whelen Aerospace Technologies - [STC SA00079NY](https://openairdocs.org/stc/SA00079NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K008 on single and multi engine fixed wing light aircraft incorporating Teledyne Continental reciprocating engines of 450 horsepower or less.. Airwolf Filter Corporation - [STC SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc. - [STC SA5581SW](https://openairdocs.org/stc/SA5581SW): Installation of ALCOR true-flow/ totalizer system. Alcor LLC - [STC SA02731SE](https://openairdocs.org/stc/SA02731SE): Installation of Luma Technologies LT-4300 Series LED Display Panel and/or LT-4302 LED Gear Status Annunciator. Luma Technologies LLC - [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc. - [STC SA04046CH PAGE 1](https://openairdocs.org/stc/SA04046CH%20PAGE%201): Installation of L-3 GENESIS (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc. - [STC SA02386AK](https://openairdocs.org/stc/SA02386AK): Replacement of existing landing and/or taxi light reflector and bulbs with Light Emitting Diode (LED) lighting systems. AeroLED's Holding LLC - [STC SA04568CH](https://openairdocs.org/stc/SA04568CH): Installation of the uAvionix tailBeaconX, a tail mounted position light with integrated Automatic Dependent Surveillance - Broadcast (ADS-B) Out and 1090MHz Mode-S transponder functionality. uAvionix Corporation - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA00040LB](https://openairdocs.org/stc/SA00040LB): Installation of a modified exhaust tail pipe.. Aerospace Welding Minneapolis Inc. - [STC SA02532AT](https://openairdocs.org/stc/SA02532AT): Installation of subject Michelin tires on appropriate aircraft. For Michelin 5, 6, 8, and 10-inch rim diameter tires on General Aviation Aircraft.. Michelin North America Inc. - [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine - [STC SA00756DE](https://openairdocs.org/stc/SA00756DE): Installation of Automatic Dependent Surveillance Broadcast (ADS-B) Out Equipment using a Trig Avionics TT22 Transponder and an approved Global Positioning System (GPS) Position Sensor. Peregrine - [STC SA11137SC](https://openairdocs.org/stc/SA11137SC): Installation of Plane-Power ALT-FLX alternator. Hartzell Engine Technologies, LLC - [STC SA02010WI](https://openairdocs.org/stc/SA02010WI): Installation of the Mid-Continent Instruments & Avionics MD23 FLEX Custom Function Display (CFD). Mid-Continent Instruments and Avionics - [STC SA110GL](https://openairdocs.org/stc/SA110GL): Install Cleveland conversion kit P/N 199-64. (320 SERIES S/N'S 0001-D9999 320E0001-F9999). Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA281GL](https://openairdocs.org/stc/SA281GL): Install Cleveland conversion kit P/N 199-72.. Kaman Corporation Aircraft Wheel and Brake LLC - [STC SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications Inc. - [STC SA02203AK](https://openairdocs.org/stc/SA02203AK): Installation of FlightLogic Synthetic Vision Electronic Flight Information System (EFIS-SV).. Genesys Aerosystems Inc. - [STC SA02444AK](https://openairdocs.org/stc/SA02444AK): Approval of the L-3 Communications NGT 9000/9000R ADS-B system installed. ADS-B Technologies LLC - [STC SA4222SW](https://openairdocs.org/stc/SA4222SW): Mount collision avoidance lights in engine nacelle.. Johnson Aviation Products - [STC SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc. - [STC SA04195NY](https://openairdocs.org/stc/SA04195NY): Installation of the KFC 230 Aerocruze Automatic Flight Control System (FCS) upgraded from KFC 200 FCS. Honeywell International Inc. (Bendix King) - [STC SA09856AC](https://openairdocs.org/stc/SA09856AC): Installation of BendixKing Aerowave 100 In-flight Data Link System for non-essential, non-required aircraft Cabin Systems & Equipments. Honeywell International Inc (Bendix King) - [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King) - [STC SA02265SE](https://openairdocs.org/stc/SA02265SE): Installation of a camera housing. Airborne Sensor LLC - [STC SA10822SC](https://openairdocs.org/stc/SA10822SC): Installation of EFD1000 Primary Flight Display. Aspen Avionics Inc. - [STC SA00401BO](https://openairdocs.org/stc/SA00401BO): Installation of a SkyTrax100B UAT receiver. Avidyne Corporation - [STC SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems - [STC SA10236SC](https://openairdocs.org/stc/SA10236SC): Installation of a GDC 31 Roll Steering Converter. DAC International Inc - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA1276CE](https://openairdocs.org/stc/SA1276CE): Installation of King KFC 200, 2-axis (3 optional) flight control system with a KI 255 (or -256) flight command indicator or KG-258 attitude horizon gyro and a KC-292 mode controller.. Honeywell International Inc - [STC SA01560WI-D](https://openairdocs.org/stc/SA01560WI-D): Installation of the Honeywell KFD 840 Primary Flight Display System.. Honeywell International Inc - [STC SA1551CE-D](https://openairdocs.org/stc/SA1551CE-D): Installation of King KAS 297 altitude selector option in airplanes equipped with KFC 200 Flight Control System with flight director. Honeywell International Inc - [STC SA4934NM](https://openairdocs.org/stc/SA4934NM): Installation of vortex generators on the wing and vertical stabilizer, and 5% take off gross weight increase.. Micro AeroDynamics Inc - [STC SA01714WI](https://openairdocs.org/stc/SA01714WI): Installation of a Garmin transponders: (a) GTX 330/330D/33/33D with ADS-B Out functionality; (b) GTX 335/335R/345/345R with ADS-B Out and In functionality; or (c) GTX 335R/345R with ADS-B Out functionality in select airplanes installed with G950/G1000 systems.. Garmin International Inc - [STC SA01750SE](https://openairdocs.org/stc/SA01750SE): Fabrication and Installation of Dahlia Doubler. Fliegen Works Inc. - [STC SA01751SE](https://openairdocs.org/stc/SA01751SE): Fabrication and Installation of Panida Doubler. Fliegen Works Inc. - [STC SA01752SE](https://openairdocs.org/stc/SA01752SE): Fabrication and Installation of Panida Doubler.. Fliegen Works Inc. - [STC SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation All 389: https://openairdocs.org/tcds/3A25/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.