TCDS 6A1

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. 6A1 This data sheet, which is a part of Type Certificate No. 6A1 prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the Airworthiness requirements of the Civil Air Regulations. Type Certificate Holder: Twin Commander Aircraft LLC 1176 Telecom Drive Creedmoor, NC 27522 Type Certificate Holder Record: Aero Design and Engineering Company, also known as Aero Commander Aircraft, transferred type certificate 6A1 to Rockwell-Standard & Associates in 1958. Rockwell transferred type certificate 6A1 to Gulfstream American Corporation on February 3, 1981. Gulfstream American Corporation transferred type certificate 6A1 to Gulfstream Aerospace Corporation on November 29, 1981. Gulfstream Aerospace Corporation transferred type certificate 6A1 to Twin Commander Aircraft Corporation on December 4, 1989. Twin Commander Aircraft Corporation transferred type certificate 6A1 to Twin Commander Aircraft LLC on June 15, 2004. I - Model L-3805 - Deleted July 29, 1969. II - Model 520, 5 PCLM (Normal Category), Approved January 31, 1952 Engines 2 Lycoming GO-435-C2 or 2 Lycoming GO-435-C2B with Bendix carburetor PS-5BD Setting 391486 or 2 Lycoming CO -435-C2B1 with Bendix carburetor PS -5BD Setting 391486. Fuel 80/87 or 91/96 min. grade aviation gasoline Engine limits Max. continuous 3000 r.p.m. (240 hp) Takeoff (5 minutes), 3400 r.p.m. (260 hp.) Propeller and 1. (For GO-435-C2 only) 2 Hartzell constant speed propellers installed in accordance Propeller limits with Rockwell Dwg. 640007. a. HC-12x20-8C hubs with 9333C-3 blades Pitch settings at 30 in. station: Low 19°, high 36° Diameter: 90 in., 2 in. cutoff permitted b. Spinner: 2 Hartzell D-163 c. Governor: 2 Hartzell A-1 and Hartzell “T-Drives” Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 Rev. No. 49 46 48 49 49 49 49 49 49 49 49 49 49 49 46 6A1 Revision 49 Twin Commander 500 500A 500B 500U 520 560 560A 560E 500S November 18, 2024 2 6A1 2. Or, (for GO-435-C2 only) 2 Hartzell feathering propellers installed in accordance with Rockwell Drawings 640008 a. HC-12x20-9C hubs with 9333C-3 blades Pitch settings at 30 in. Station: Low 19°, High 36° Diameter: 90 in., 2 in. cutoff permitted. b. Spinner: 2 Hartzell D-163 c. Governor: 2 Hartzell A-1 & Hartzell “T-Drives” 3. Or, 2 Hartzell feathering propellers installed in accordance with Rockwell Drawings 640009 and 640012. a. HC-82x20-2 hubs with 9333C-3 blades Pitch settings at 30 in. Station: Low 18°, High 28.5°, Feathered 89° Diameter: 90 in., 2 in. cutoff permitted. b. Spinner: 2 Hartzell C-888 Dome and C-807-2 Bulkhead c. Governor: 2 Hamilton Standard TQ12-G1A or 2 Woodward 210075 or 2 Woodward 210245 or 2 Hartzell A-1 and Hartzell “T-Drives” (GO-435-C2 only) 4. Or, 2 Hartzell feathering propellers installed per Rockwell Drawing 640013. a. HC-83x20-2 hubs with 8433 blades Pitch settings at 30 in. Station: Low 16°, High 26.3°, Feathered 87° Diameter: 84 in., No cutoff permitted b. Spinner: 2 Hartzell C-888-3 dome and C-807-3 bulkhead or 2 Hartzell C-888-6 dome and C-807-7 bulkhead. c. 2 Woodward 210075 or 210245 Airspeed limits Maneuvering 142 m.p.h. (124 K) True Ind. Max. structural cruising 200 m.p.h. (174 K) True Ind. Never exceed Flaps extended 20° Flaps extended 40° 270 m.p.h. (234 K) True Ind. 150 m.p.h. (130 K) True Ind. 125 m.p.h. (109 K) True Ind. Landing gear extended 180 m.p.h. (156 K) True Ind. C.G. range (+168.6) to (+175.1) (Gear extended) Effect of retracting landing gear is +4110 in.-lb. Empty Wt. C.G. Range None Datum Located 152 in. fwd. of the wing leading edge. Leveling means Longitudinal - Top of fuselage centerline, aft of wing trailing edge. Lateral - Transverse beams at front or rear of baggage compartment floor. Maximum weight 5500 lb. (See NOTE 3 for 5700 lb. maximum weight). No. of seats 5 (2 at +104 and 3 at +165) See NOTE 6 for eligibility for 6 or 7 seats. Maximum baggage 350 lb. (+200) Fuel capacity 150 gal. total (5 inter-connected tanks) (+187) 145 gal. usable fuel (See NOTE 1 for unusable fuel). Oil capacity 6 gal. total (3 gal. each engine) (+152) 4.5 gal. usable oil (See NOTE 1 for unusable oil) Control surface movements Elevator 20° ± 2 Up 15° ± 2 Down Elevator tab 2 1/2° ± 1 Up 26 1/2° ± 1/2 Down Rudder 15° ± 1 Right 15° ± 1 Left Rudder tab 13° ± 1/2 Right 26° ± 1/2 Left Aileron 23° ± 2 Up 15° ± 2 Down Flaps 40° ± 2 Down 3 6A1 Serial Nos. eligible Under the delegation option provisions of Part 21 of the Federal Aviation Regulations, Delegation Option Manufacturer No. SW-2 is authorized to approve design and production changes on airplane serial numbers 520-1 to 520-150. (See NOTES 7 and 9 for serial number variations and SW-2 status.) III - Model 560, 7 PCLM (Normal Category), Approved May 28, 1954 (Same as Model 520 except for increased weight, increased horsepower, and swept tail. Revised model incorporates structural modifications to the wing, landing gear, fuselage, vertical tail, and primary control system). Engines 2 Lycoming GO-480-B or GO-480-B1C with Bendix carburetor PS-5BD setting 391569. Fuel 80/87 or 91/96 min. grade aviation gasoline Engine limits Max continuous, 3000 r.p.m. (260 hp) Takeoff (5 minutes), 3400 r.p.m. (270 hp) Propeller and 1. 2 Hartzell feathering propellers installed in accordance with Rockwell Dwgs. Propeller limits 640009 and 640012. a. HC-82x20-2 hubs with 9333C-3 blades Pitch settings at 30 in. station: Low 18°, High 28.5°, Feathered 89° Diameter: 90 in., 2 in. cutoff permitted b. Spinner: 2 Hartzell C-888 dome and C-807-2 Bulkhead or 2 Hartzell D-163 c. Governor: 2 Hamilton Standard 1Q12-G1A or 2 Woodward 210075 or 210245 or 2 Hartzell A-1 and Hartzell “T-Drives” 2. Or, 2 Hartzell feathering propellers installed per Rockwell Dwg. 640013. a. HC-83x20-2 hubs with 8433 blades Pitch settings at 30 in. station: Low 16°, High 26.5°, feathered 87° Diameter: 84 in., No cutoff permitted. b. Spinner: 2 Hartzell C-888-3 dome and C-807-3 bulkhead or 2 Hartzell C-888-6 dome and C-807-7 bulkhead c. Governor: 2 Woodward 210075 or 210245 Airspeed Limits Maneuvering 156 m.p.h. (135 K) True Ind. Max. structural cruising 200 m.p.h. (174 K) True Ind. Never exceed 270 m.p.h. (234 K) True Ind. Flaps extended - half 150 m.p.h. (130 K) True Ind. Flaps extended - full 125 m.p.h. (109 k) True Ind. Landing gear extended 180 m.p.h. (156 K) True Ind. C.G. range (+168.6) to (+176.6) (Gear extended) Effect of retracting landing gear is +4110 in.-lb. Empty Wt. C.G. range None Datum Located 152 in. fwd. of the wing leading edge at center section Leveling means Longitudinal - Top of fuselage centerline, aft of wing trailing edge. Lateral - Transverse beams at front or rear of baggage compartment floor Maximum weight 6000 lbs. No. of seats 7 (2 at +104, 2 at +135, and 3 at +165) Maximum baggage 350 lb. (+200) Fuel capacity 150 gal. total (5 inter-connected tanks) (+187) 145 gal. usable fuel (See NOTE 1 for unusable fuel) Oil capacity 6 gal. total (3 gal each engine) (+152) 4 6A1 4 1/2 gal. usable oil (See NOTE 1 for unusable oil) Control surface Elevator 30° + 2°, -0 Up 10° ± 2° Down movements Elevator tab 2 1/2° ± 2° Up 20° ± 2° Down Rudder 15° ± 2° Right 15° ± 2 Left Rudder tab 26° ± 2 Right 26° ± 2° Left Aileron 23° ± 2° Up 15° ± 2° Down Flaps 40° ± 2° Down Serial Nos. eligible Under the delegation option provisions of Part 21 of the Federal Aviation Regulations, Delegation Option Manufacturer No. SW-2 is authorized to approve design and production changes on airplane serial numbers 560-151 to 560-230. (See NOTES 7 and 9 for serial number variations and SW-2 status.) IV - Model 560A, 7 PCLM (Normal Category), Approved July 1, 1955 (Same as Model 560 except for engine installation, longer fuselage, structural changes to the wing, new landing gear design, revised fuel and oil systems.) Engines 2 Lycoming GO-480-D1A or 2 Lycoming GO-480-C1B6 with Bendix carburetor PS-5BD setting 391621 (3-spring elevator bungee system must be incorporated per Dwg. 530000 Chg X) or 2 Lycoming GO-480-G1B6 with Bendix carburetor PS-5BD setting 391621 (oil cooler outlet gills must be changed per Service Letter 62. Oil Temp gage markings changed per Service Letter 63). Fuel 80/87 min. grade aviation gasoline 100/130 min grade (GO-480-C1B6) Engine Limits Maximum continuous Takeoff (5 minutes) 3000 r.p.m. (260 hp) 3400 r.p.m. (275 hp) Propeller and 1. 2 Hartzell feathering propellers installed per Rockwell Drawing 640013. propeller limits a. HC -83x20-2 hubs with 8433 blades Pitch settings at 30 in. station: Low 16°, High 26.5°, Feathered 87° Diameter: 84 in. No cutoff permitted. b. Spinners: 2 Hartzell C-888-3 dome and C-807-3 bulkhead or 2 Hartzell C-888-6 dome and C-807-7 bulkhead or 2 Hartzell 836-78 Assemblies c. Governors:2 Woodward 210075 or 210245 2. 2 Hartzell feathering propellers installed per Rockwell Drawing 640017 (For Lycoming GO-480-C1B6 only) a. HC-83x20-2 hubs with 8833-2 blades Pitch settings at 30 in. Station: Low 17°, Feathered 82° to 84° Diameter: 86 in., No cutoff permitted. b. Spinners: 2 Hartzell C-888-3 dome and C-807-3 bulkhead or 2 Hartzell C-888-6 dome and C-807-7 bulkhead or 2 Hartzell 836-78 Assemblies c. Governors:2 Woodward 210075 or 210245 Airspeed Limits Maneuvering 160 m.p.h. (139 K) True Ind. Max. structural cruising 210 m.p.h. (182 K) True Ind. Never exceed 270 m.p.h. (234 K) True Ind. Flaps extended - half150 m.p.h. (130 K) True Ind. Flaps extended - full 130 m.p.h. (113 K) True Ind. Loading gear extended 180 m.p.h. (156 K) True Ind. C.G. range (gear extended) (+166.4) to (+176.5) Effect of retracting landing gear is: inclined gear 6210 in. -lb., vertical g ear 5745 in. -lb. C.G. limit restriction with Lear L-2C automatic pilot installed is (+166.4) to (+175.8). Empty Wt. C.G. range None 5 6A1 Datum Located 152 in. fwd. of the wing leading edge at center section. Leveling means Longitudinal - Top of fuselage centerline, aft of wing trailing edge. Lateral - Transverse beams at front or rear of baggage compartment floor Maximum weight 6000 lbs. No. of seats 7 (2 at +94, 2 at +128, and 3 at +168) Maximum baggage 350 lb. (+200) Fuel capacity 158.5 gal. total (5 inter-connected tanks) (+187) 156 gal. usable fuel (See NOTE 1 for unusable fuel) Auxiliary fuel tanks 2@33.5 gal (Requires extra oil. See NOTE 4 for requirements) Oil capacity 8.5 gal. total (4.25 gal. each tank) (+191) 6.5 gal. required usable oil (See NOTE 1 for unusable oil and NOTE 4 for usable oil requirements with auxiliary fuel tanks installed). Control surface movements Elevator 30° + 1° Up 10° ± 2° Down -0° Elevator tab 2 1/2° + 2° Up 20° ± 2° Down -1/2° Rudder 15° + 2° Right 15° + 2° Left (Serial Nos.231-330) -0° -0° Rudder 20° + 2° Right 20° + 2° Left (Serial Nos. 331 & Subs) -0° -0° Rudder tab 26° ± 2° Right 26° ± 2° Left Aileron 23 ° ± 2° Up 15° ± 2° Down Flaps 40° ± 2° Down Serial Nos. eligible Under the delegation option provisions of Part 21 of the Federal Aviation Regulations, Delegation Option Manufacturer No. SW-2 is authorized to approve design and production changes on airplane serial numbers 560A-437 to 560A-884. (See NOTES 7 and 9 for serial number variations and SW-2 status.) V. Model 560E, 7 PCLM (Normal Category), Approved February 21, 1957 (Same as Model 560A except for engine installation, structural changes to the wing, wheel and brake installation, revised fuel system, and new landing gear location.) Engine 2 Lycoming GO-480-C1B6 or GO-480-G1B6, Bendix carburetor PS-5BD, Parts Listing No. 391621. Fuel 100/130 min. grade aviation gasoline Engine limits Maximum continuous, 3000 r.p.m. (280 hp) Takeoff (5 minutes), 3400 r.p.m. (295 hp) Propeller and 2 Hartzell feathering propeller installed per Rockwell Dwg. 640017 propeller limits a. HC -83x20-2 hubs with 8833-2 blades Pitch settings at 30 in. station: Low 17°, Feathered 82° to 84° Diameter: 86 in., No cutoff permitted b. Spinner: 2 Hartzell C-888-3 dome and C-807-3 bulkhead or 2 Hartzell C-888-6 dome and C-807-7 bulkhead or 2 Hartzell 836-78 assemblies c. Governors:2 Woodward 210075 or 210245 Airspeed limits Maneuvering 160 m.p.h. (139 K) True Ind. Max. structural cruising 210 m.p.h. (182 K) True Ind. 6 6A1 Never exceed 270 m.p.h. (234 K) True Ind. Flaps extended - half 150 m.p.h. (130 K) True Ind. Flaps extended - full 130 m.p.h. (113 K) True Ind. Landing gear extended 180 m.p.h. (156 K) True Ind. C.G. range (gear extended) (+166.0) to (+175.1) Effect of retracting landing gear is +6655 in. -lb. Empty Wt. C.G. range None Datum Located 152 in. fwd. of wing leading edge at center section. Leveling means Longitudinal - Top of fuselage centerline aft of wing trailing edge. Lateral - Transverse beams at front or rear of baggage compartment floor. Maximum weight 6500 lb. No. of seats 7 (2 at +94, 2 at +128, and 3 at +168) Maximum baggage 350 lb (+200) Fuel capacity Center tank 158.5 gal. (+187), usable fuel 156 gal. Outboard tanks, 33.5 gal. each (+178), usable fuel 33.5 gal. each. Total capacity 225.5 gal., usable fuel 223 gal. (See NOTE 1 for system fuel.) Oil capacity 8.5 gal. total (4.25 gal. each tank) (+191) 8.5 gal. usable (See NOTE 1 for system oil) Control surface movements Elevator 30° + 1° Up 10° +2° Down -0° -0° Elevator tab 2 1/2° + 2° Up 20° +2° Down -1/2° -0° Rudder 20° +2° Right 20° +2° Left -0° - 0° Rudder tab 26° + 2° Right 26° +2° Left -0° -0° Aileron 23° ± 2° Up 15° ± 2° Down Flaps 40° ± 2° Down Serial Nos. eligible Under the delegation option provisions of Pat 21 of the Federal Aviation Regulations, Delegation Option Manufacturer No. SW-2 is authorized to approve design and production changes on airplane serial numbers 560E-434 to 560E-884. (See NOTES 7 and 9 for serial number variations and SW-2 status.) VI - Model 500, 7 PCLM (Normal Category), Approved July 24, 1958 (Same as 560E except for decreased gross weight, powerplants, and 560A landing gear.) Engines 2 Lycoming O-540-A2B, Carburetor MA 4-5, Parts Listing No. 10-4057. Fuel 91/96 min. grade aviation gasoline Engine limits For all operations, 2575 r.p.m. (250 hp) Propeller and 2 Hartzell two-bladed feathering propellers propeller limits a. HC-82XX-2C1 hubs with 8433-4 blades HC-A2XX-2C1 hubs with V8433-4 blades HC-A2VK-2C1 hubs with V8433-4 blades Pitch setting at 30 in. station: Low 14°, Feathered 82° to 84° Diameter: 80 in., no cutoff permitted Note: Any combination of the three approved propellers may be used; however, for best synchronization and matched response times, the 7 6A1 propellers should be used in pairs of like model numbers. b. Spinners: 2 Hartzell 835-6 assemblies c. Governors: 2 Ham-Std. 1M12-60A or 2 Woodward 210400 Airspeed limits Maneuvering 160 m.p.h. (139 K) True Ind. Max. structural cruising 210 m.p.h. (182 K) True Ind. Never exceed 270 m.p.h. (234 K) True Ind. Flaps extended - half 150 m.p.h. (130 K) True Ind. Flaps extended - full 130 m.p.h. (113 K) True Ind. Landing gear extended 180 m.p.h. (156 K) True Ind. C.G. range (+166.0) to (+175.1) (Gear extended) Effect of retracting landing gear +6210 in. -lb. Empty Wt. C.G. range None Datum Located 152 in. fwd. of wing leading edge at center section. Leveling means Longitudinal - Top of fuselage centerline aft of wing trailing edge. Lateral - Transverse beams at front or rear of baggage compartment floor. Maximum weight 6000 lb. No. of seats 7 (2 at +94, 2 at +128, 3 at +168) Maximum baggage 350 lb. (+200) Fuel capacity 158.5 gal. total (5 inter-connected tanks) (+187) 156 gal. usable fuel Oil capacity 6 gal. total (3 gal. each engine) 9.25 qt. usable per engine Control surface Elevator 30° +1 Up 10° +2 Down movements -0 -0 Elevator tab 2 1/2° +2 Up 20° +2 Down -1/2 -0 Rudder 20° +2 Right 20° +2 Left -0 -0 Rudder tab 26° +2 Right 26° +2 Left -0 -0 Aileron 23° ± 2 Up 15° ± 2 Down Flaps 40° ± 2 Down Serial Nos. eligible Under the delegation option provisions of Part 21 of the Federal Aviation Regulations, Delegation Option Manufacturer No. SW-2 is authorized to approve design and production changes on airplane serial numbers 500-618 to 500-852. (See NOTES 7 and 9 for serial number variations and SW-2 status.) VII - Model 500A, 7 PCLM (Normal Category), Approved April 7, 1960 (Same as 500 except for fuel injection engine and new landing gear.) Engines 2 Continental IO-470-M Fuel 100/130 min. grade aviation gasoline Engine limits For all operations, 2625 r.p.m. (260 hp) Propeller and 2 Hartzell two-bladed feathering propeller 8 6A1 propeller limits a. HC-A2XF-2 hubs with 8433-4 blades, HC-A2VF - 2 hubs with V8433 - 4 blades Pitch setting at 30 in. Station: Low 12.5°, Feathered 81.0°. Diameter: 80 in., 2 in. cutoff permitted. NOTE: Letters appearing after the dash numbers of the above listed hub do not affect eligibility; however, for the best synchronization, hubs with different numbers should not be combined on the same airplane. b. Spinners: 2 Hartzell C-2530 assemblies or 2 Hartzell C-2509-1 assemblies c. Governors:2 Woodward 210310 or 210410 (Per Rockwell Dwg. 640030 when Rockwell propeller unfeathering system is installed) NOTE: Governor part numbers may differ from governor type numbers. For best synchronization, governors with different part numbers should not be combined on the same airplane. Airspeed limits Maneuvering 145 m.p.h. (126 K) True Ind. Max. structural cruising 230 m.p.h. (200 K) True Ind. Never exceed 288 m.p.h. (250 K) True Ind. Flaps extended - half 150 m.p.h. (130 K) True Ind. Flaps extended - full 136 m.p.h. (118 K) True Ind. Landing gear extended 180 m.p.h. (156 K) True Ind. C.G. range (+166.0) to (+174.4) (Gear extended) Effect of retracted landing gear +10.073 in.-lb. Empty Wt. C.G. range None Datum Located 152 in. fwd. of wing leading edge at center section. Leveling means Longitudinal - top of fuselage centerline aft of wing trailing edge. Lateral - Transverse beams at front or rear of baggage compartment floor Maximum weight 6000 lb. (See NOTE 3 for 6250 lb. maximum weight) No. of seats 7 (2 at +94, 2 at +128, 3 at +168) Maximum baggage 350 lb (+200) Fuel capacity 159.5 gal. total (5 interconnected tanks) (+187) (156 gal. usable fuel) Oil capacity 6 gal. total (12 qt. each engine) (+146) Usable oil - 8 qt. (each engine) Control surface movements Elevator 30° +1 Up 10° + 2 Down -0 -0 Elevator tab 2 1/2° + 2 Up20° + 2 Down (500A-871 thru -1/2 -0 500A-970) 26° + 2 Down (500A-971 and Rudder 20° + 2 Right -0 up) 20° +2 Left Rudder tab -0 26° + 2 Right -0 26° + 2 Left Aileron -0 23° ± 2 Up -0 15° ± 2 Down Flaps 40° ± 2 Down Serial Nos. eligible Under the delegation option provisions of Part 21 of the Federal Aviation Regulations, Delegation Option Manufacturer No. SW-2 is authorized to approve design and production changes on airplane serial numbers 500A-875 to 500A-1276-99. (See NOTES 7 and 9 for serial number variations and SW-2 status.) 9 6A1 VIII - Model 500B, 7 PCLM (Normal Category), Approved July 13, 1960 Engines 2 Lycoming IO-540-B1A5, or 2 Lycoming IO-540-B1C5 or 2 Lycoming IO-540-E1A5 or 2 Lycoming IO-540-E1B5. (See NOTE 8 for engine requirements.) Aero Commander vapor separator is required with IO-540-B1C5 and IO-540-E1A5 and IO-540-E1B5. Fuel injector is Bendix RS10B1, Parts Listing No. 391787-1. Fuel 100/130 min. grade aviation gasoline Engine limits Maximum continuous, 2575 r.p.m. (290 hp) Takeoff. 2575 r.p.m. (290 hp) Propeller and 2 Hartzell three-bladed feather propellers Propeller Limits a. HC-A3XK-2 Hubs with 8433-4 blades or HC-A3XK-2A Hubs with 8433-4 blades or HC-A3VK-2 Hubs with V8433-4 blades or HC-A3VK-2A Hubs with V8433-4 blades or HC-C3YR-2 Hubs with C8468-6R blades or HC-C3YR-2F Hubs with FC8468-6R blades or HC-C3YR-2U Hubs with C8468-6R blades or HC-C3YR-2UF Hubs with FC8468-6R blades Pitch settings at 30 In. Station: Low 12.5° to 13.0° feathered 85.5° (Aircraft S/N 893 thru 1014 may have feathered angle of 82.5° unless Service Letter 101 has been complied with). Diameter: 80 in. No cutoff permitted NOTE: Hubs with different part numbers should not be combined on the same airplane. b. Spinners: 2 Hartzell C-2513 Assemblies (for HC-A3XK and HC-A3VK series hubs 2 Hartzell C-3258 Assemblies (for HC-C3YR series hubs) c. G overnors: 2 Woodward 210400 or 210401 (Per Rockwell Dwg. 640030 when Rockwell propeller unfeathering system is installed.) NOTE: Governor part numbers may differ from governor type numbers. For best synchronization, governors with different part numbers should not be combined on the same airplane. Airspeed limits Maneuvering 155 m.p.h. (135 K) True Ind. Max. structural cruising 230 m.p.h. (200 K) True Ind. Never exceed 288 m.p.h. (250 K) True Ind. Flaps extended - half 150 m.p.h. (130 K) True Ind. Flaps extended - full 136 m.p.h. (118 K) True Ind. Landing gear extended 180 m.p.h. (156 K) True Ind. C.G. range (+166.0) to (+174.4) (Gear extended) Effects of retracted landing gear 10,073 in.-lb. A/C S/N 893 thru 1631 Forward - 166.0 inches aft of datum without Service Bulletin No. 128 (20% MAC) or No. 129 installed. Aft - 174.40 inch aft of datum (32% MAC) A/C S/N 893 thru 1631 Forward - 161.8 inches aft of datum with Service Bulletin No. 128 or (14% MAC) at 5600 lbs. No. 129 installed. -166.0 inches aft of datum (20% MAC) at 6750 lbs. Straight line variation between points Aft - 173.0 inches aft of datum (30% MAC) at 6750 lbs. C.G. variation of lighter weights: Inches aft of datum = 174.5 - 10,073/Wt. 10 6A1 Empty Wt. C.G. range None Datum Located 152 in. fwd. off wing leading edge at center section. Leveling means Longitudinal - top of fuselage centerline aft of wing trailing edge. Lateral - Transverse beams at front or rear of baggage compartment floor. Maximum weight 6750 lb. No. of seats 7 (2 at +94, 2 at +128, 3 at +168) See NOTE 5 for eligibility for 8 seats. Maximum baggage 350 lb. (+200) Fuel capacity 159.6 gal. total (5 interconnected tanks) (+187) 156.gal. usable fuel Oil capacity 6 gal. total (12 qt. each engine) (+146) Control surface movements Elevator 30° +1 Up. 10° + 2 Down -0 -0 Elevator tab 2 1/2° + 2 Up26° +2 Down -1/2 -0 Rudder 20° + 2 Right 20° + 2 Left -0 -0 Rudder tab 26° + 2 Right 26° + 2 Left -0 -0 Aileron 23° ± 2 Up 15° ± 2 Down Flaps 40° ± 2 Down Serial Nos. eligible Under the delegation option provisions of Part 21 of the Federal Aviation Regulations, Delegation Option Manufacturer No. SW-2 is authorized to: Issue Airworthiness Certificates for airplane serial numbers 500B-1551-197 to 500B-1631; and approve design and production changes on airplane serial numbers 500B-893-1 to 500B-1631. (See NOTES 7 and 9 for serial number variations and SW-2 status.) IX - Model 500U, 7 PCLM (Normal and Utility Category), Approved December 11, 1964 Engines 2 Lycoming IO-540-E1A5 or 2 Lycoming IO-540-E1B5. Rockwell Commander 4630193 vapor separator is required. Fuel injector is Bendix RS10B1, Parts Listing No. 391787-1. Fuel 100/130 min. grade aviation gasoline Engine limits Maximum continuous, 2575 r.p.m. (290 hp) Takeoff, 2575 r.p.m. (290 hp) Propeller and 2 Hartzell three-bladed feather propellers propeller limits a. HC-A3XK-2 Hubs with 8433-4 blades or HC-A3XK-2A Hubs with 8433-4 blades or HC-A3VK-2 Hubs with V8433-4 blades or HC-A3VK-2A Hubs with V8433-4 blades or HC-C3YR-2 Hubs with C8468-6R blades or HC-3YR-2F Hubs with FC8468-6R blades or HC-C3YR-2U Hubs with C8468-6R blades or HC-C3YR-2UF Hubs with FC8468-6R blades or Pitch setting at 30 in. Station: Low 12.5° to 13.0°, feathered 85.5° Diameter: 80 inch., No cutoff permitted. NOTE: Hubs with different part numbers should not be combined on the same airplane. b. Spinners: 2 Hartzell C-2513 Assemblies (for HC-A-3XK and HC-A3VK series hubs). 11 6A1 2 Hartzell C-3258 Assemblies (for HC-C3YR series hubs). c. Governors: 2 Woodward 210400 or 210401 (per Rockwell Dwg. 640030 when Rockwell propeller unfeathering system is installed.) NOTE: Governor part numbers may differ from governor type numbers. For best synchronization, governors with different part numbers should not be combined on the same airplane. Airspeed limits Maneuvering 163 m.p.h. (142 K) True Ind. Max. structural cruising 230 m.p.h. (200 K) True Ind. Never exceed 288 m.p.h. (250 K) True Ind.