# TCDS 6A1: Twin Commander Aircraft LLC

- Type: Type certificate data sheet
- Status: Current
- Holder: Twin Commander Aircraft LLC
- Revision: 49
- Revised: November 18, 2024
- Product: Aircraft, Small Airplane
- Certification basis: CAR 3
- Registered aircraft: 216, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/e5/69/e5693f7beb0ab9075c7dc6193b97359a15d8eb2afb2c78e182105ee397a5d60a
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID126841833820241120192424.0001
- Page: https://openairdocs.org/tcds/6A1

## Models (9)

As the data sheet lists them.

- 500
- 500A
- 500B
- 500U
- 520
- 560
- 560A
- 560E
- 500S

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
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. 
 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 Serial No. 1635 thru 1780 Forward - 166.0 inches aft of datum 
without Service Bulletin No. 128 or (20% MAC) 
No. 129 installed. Aft - 174.40 inches aft of datum 
(32% MAC) 
Aircraft Serial No. 1635 thru 1780 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 at lighter weights: 
Inches aft of datum = 174.5 - 10,073/Wt. 
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 6750 lbs. 
 
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. total (12 qt. each engine) (+146) 
 
Control surface Elevator 30° + 1 Up 10° + 2 Down 
movements   - 0  - 0 
Elevator tab 2 1/2° + 2 Up 26° + 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 
 
S
erial 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 and approve design and production changes on airplane serial 
numbers 500U-1635 thru 1780. (See NOTES 7 and 9 for serial number variations and 
SW-2 status.)

12 6A1 
 
 
X  - MODEL 500S, 7 PCLM (Normal and Utility Category), Approved March 15, 1968 
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 1. 2 Hartzell three-bladed feathering propellers 
propeller limits a. HC-A3XK-2 hubs with 8433-4 blades or HC-A3VK-2 hubs with V8433-4 
blades 
Pitch setting at 30 in. Station: Low 12.5° to 13.0°, Feathered 85.5° 
Diameter: 80 in., no 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-2513 assemblies 
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. 
2. 2 Hartzell three-bladed feathering propellers 
a. HC-3YR-2 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°, Feather 85.5°. 
Diameter: 80 in. no cutoff permitted 
NOTE: Letters appearing after dash numbers of the above listed hubs do not 
affect eligibility; however, for best synchronization, hubs with 
different numbers should not be combined on same airplane. 
b. Spinner: 2 Hartzell C-3258 assemblies 
c. Governors: 2 Woodward 210400 or 210401 (Per Rockwell Dwg. 640030 
when Rockwell propeller unfeathering system is installed). 
NOTE: G overnor part numbers may differ from  governor type numbers. For 
best synchronization, governors with different part numbers should 
not be combined on the same airplane. 
 
(With Prop Sync. System): One each Woodward 210585 and 
210586 (per Rockwell Dwg. 890314 without prop unfeathering 
system) or one each Woodward 210584 and 210587 (per Rockwell 
Dwg. 890314 with prop unfeathering per Rockwell Dwg. 640030.) 
 
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. 
 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 (+174.0) (Gear extended) 
Effects of retracted landing gear 10,073 in.-lb. 
A/C S/N 1755 thru 3155 Forward - 166.0 in. Aft of Datum 
Without SB 128 or 129  (20% MAC) 
installed. Gear Extended Aft - 174.4 in. Aft of Datum 
(32% MAC) 
A/C S/N 1755 thru 3155 Forward 161.8 in. Aft of Datum(14% MAC) at 5600 lbs

13 6A1 
 
 
 With SB 128 or 129 installed  166.0 in. Aft of Datum (20% MAX) at 6750 lbs 
and 3156 and Subs.  Straight Line Variation Between Points 
Gear Extended Aft - 173.0 in. Aft of Datum (30% MAC) at 6750 lbs 
   C.G. Variation at Lighter Weights: In Aft of 
   Datum = 174.5-10,073/Wt 
 
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 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 500 lb (+214) 
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 Up 26° + 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 and approve design and production change on airplane 
serial numbers 500S-1755, 1756, 1767, 1781 thru 1876 and 3050 through 3323. 
(See NOTES 7 and 9 for serial number variations and SW-2 status.) 
 
 
Specifications Pertinent to All Models 
Certification Basis Type Certificate No. 6A1 
Application for Type Certificate November 5, 1945. 
Civil Air Regulations (CAR) Part 3, Normal Category: 
Model 520: CAR 3 effective November 1, 1949, through Amendment 3-6 dated 
June 4, 1951. 
Model 560: CAR 3 effective November 1, 1949, through Amendment 3-11 
dated May 17, 1954, except paragraph 3.668 of Amendment 3-7, 
dated March 5, 1952. 
Model 560A: CAR 3 effective November 1949, through Amendment 3-12 dated 
May 18, 1954, except paragraph 3.668 of Amendment 3-7 dated 
March 5, 1952. 
Model 560E: CAR 3 effective November 1, 1949, through Amendment 3-12 
dated May 18, 1954, and CAR 3.431 as amended May 15, 1956. 
Model 500: CAR 3 effective November 1, 1949, through Amendment 3-12 
dated May 18, 1954, and CAR 3.431 as amended May 15, 1956. 
Model 500A: CAR 3 effective May 15, 1956, including Amendments 3-3 and 3-4 
effective October 6, 1958.

14 6A1 
 
Model 500B CAR 3 effective May 15, 1956, including Amendments 3-3 and 3-4 
effective October 6, 1958. 
 
CAR 3, Normal and Utility Category: 
Model 500S: CAR 3 effective May 15, 1956, including Amendments 3-3 and 3-4 
effective October 6, 1958. 
Model 500U: CAR 3 effective May 15, 1956, including Amendments 3-3 and 3-4 
effective October 6, 1958. 
 
Production Basis Production Certificate No. 203. 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations  
(see Certification Basis) must be installed in this aircraft for certification. This 
equipment must include a current airplane flight manual. 
In addition, the following item(s) are required: 
Stall warning system 167 detector Safe Flight Mod. “S” indicator per 
Rockwell Drawings 850016 and 850017. 
 
NOTE 1: Current weight and balance report, including list of equipment included in certificated 
empty weight, and loading instructions, must be provided for each aircraft at the time 
of original airworthiness certification and at all times thereafter. 
 
The certificated empty weight and corresponding center of gravity location must include 
unusable fuel (included in total fuel capacity) and undrainable oil (including in total oil 
capacity) as follows: 
Model 
Fuel 
Oil 
520 
30 lb.(+186) 
10 lb.(+152) 
560 
30 lb.(+186) 
10 lb.(+152) 
560A 
15 lb.(+187) 
15 lb.(+191) 
560E 
15 lb.(+187) 
15 lb.(+191) 
500 
15 lb. (+187) 
0 lb. 
Model 500A 500B 500U 500S 
 
Fuel 
5630127 
Fuel Sump 
22 lb.(+187) 
5630127 
Fuel Sump 
22 lb.(+187) 
5630127 
Fuel Sump 
22 lb.(+187) 
5630127 
Fuel Sump 
22 lb. (+187). 
Oil 0 lb. 0 lb. 0 lb. 0 lb. 
 
5630184 
 
5630184 
 
5630184 
 
5630184 
Fuel Sump Fuel Sump Fuel Sump Fuel Sump 
17.5 lb.(+187) 17.5 lb.(+187) 17.5 lb.(+187) 17.5 lb.(+187) 
0 lb. 0 lb. 0 lb. 0 lb. 
 
NOTE 2: On Models 520, 560, 560A, 560E, 500, 500A, 500B, 500U and 500S, the placards 
specified in the Airplane Flight Manual must be displayed in front of and in clear view 
of the pilot. 
NOTE 3: (a) Airplane serial numbers 520-31 through 520-150 eligible for a maximum weight of 
5700 lb. when modified in accordance with Aero Commander Drawing SC26-520. 
The C.G. range then becomes: (+169.15) to (+176.5). 
(b) Airplane serial numbers 500A-875-2 and up eligible for a maximum weight of 6250 
lb. when modified in accordance with Aero Commander Service Change No. 50, 
dated 12 August 1960. The C.G. range then becomes (+168.1) to (+174.4). 
 
NOTE 4: Model 680 outboard fuel tank are eligible on Model 560A with no increase in unusable 
fuel. However, when outboard tanks installed, 4.25 gal. of oil must be carried in each 
oil tank rather than 3.25 gal. as required for center fuel tank only. Oil dip sticks are 
calibrated for both 3.25 and 4.25 gal. 
 
NOTE 5: The Models 500B, 500U, and 500S are eligible as eight-place aircraft when modified in 
accordance with Aero Commander Drawing 6100023. No weight and balance or gross 
weight change is required for this modification.

15 6A1 
 
NOTE 6: Emergency exit in accordance with Rockwell Installation Drawing 5870041. Only 
airplanes with structural provision for center seats re. Rockwell Dwg. 5870027 eligible 
as 6 or 7 place. 
 
NOTE 7: In some cases the serial number contains the basic number plus a dash followed by a 
second set of numbers. This second number is a model unit number and the basic serial 
number applies with or without the second number. Example as follows: Aircraft: 
500B-1551-197 can be referred to as S/N 1551-197 or by S/N 1551. 
NOTE 8: Any combination of these engines is eligible to be installed on Model 500B aircraft. 
See Aero Commander Service Change No. 77 for proper engine accessories. 
 
NOTE 9: Delegation Option Authorization No. SW-2 expired July 17, 1986. 
 
 
 
 
...END...
```

## ADs (39, 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 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 2006-16-18 R1](https://openairdocs.org/ad/2006-16-18-R1): Installing a warning placard on the TAWS/RMI · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 100 more. Effective Jul 18, 2008
- [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 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 98-08-25 R1](https://openairdocs.org/ad/98-08-25-R1): Nose Landing Gear (NLG) Drag Link Bolt · Twin Commander 500-S, 500-U, 680-F and 9 more. Effective Jan 5, 1999
- [AD 98-20-34](https://openairdocs.org/ad/98-20-34): Airplane Flight Manuals--Severe Icing Conditions · Twin Commander 500, 500-A, 500-B and 24 more. Effective Nov 3, 1998
- [AD 98-14-03](https://openairdocs.org/ad/98-14-03): Transponders · Cessna 172, 172A, 172B and 230 more. Effective Aug 16, 1998
- [AD 98-07-17](https://openairdocs.org/ad/98-07-17): Flap System · Twin Commander 500, 500-A, 500-B and 27 more. Effective May 29, 1998
- [AD 98-08-19](https://openairdocs.org/ad/98-08-19): Wing to Fuselage Attachment Brackets and Straps · Twin Commander 500, 500-A, 500-B and 27 more. Effective May 18, 1998
- [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 94-04-13](https://openairdocs.org/ad/94-04-13): Spar Cap · Twin Commander 500, 500-A, 500-B and 17 more. Effective Apr 12, 1994
- [AD 94-04-14](https://openairdocs.org/ad/94-04-14): Spar Cap · Twin Commander 500-S, 500-U, 680-FL(P) and 6 more. Effective Apr 12, 1994
- [AD 94-04-15](https://openairdocs.org/ad/94-04-15): Spar Cap · Twin Commander 500, 560-A, 560-E and 3 more. Effective Apr 12, 1994
- [AD 94-04-11](https://openairdocs.org/ad/94-04-11): Spar Cap · Twin Commander 500-S and 690B. Effective Apr 11, 1994
- [AD 87-21-07 R1](https://openairdocs.org/ad/87-21-07-R1): Fuel Filler Openings · Twin Commander 500, 500-A, 500-B and 16 more. Effective May 5, 1989
- [AD 75-12-09 R2](https://openairdocs.org/ad/75-12-09-R2): Inadvertent Structural Failure · Twin Commander 500, 500-A, 500-B and 12 more. Effective Nov 28, 1981
- [AD 81-19-04](https://openairdocs.org/ad/81-19-04): Hose Assembly · Rajay Hose Assemblies, 500A, 500B and 87 more. Effective Sep 17, 1981
- [AD 79-07-02](https://openairdocs.org/ad/79-07-02): Batteries · Aircraft Parts & Development A, A-2, A-3 and 149 more. Effective Apr 3, 1979
- [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 75-12-10](https://openairdocs.org/ad/75-12-10): Autopilots · M7 Aerospace 60, 95-C55, 95-C55A and 17 more. Effective Jun 11, 1975
- [AD 73-06-02](https://openairdocs.org/ad/73-06-02): Fuel Siphoning · Twin Commander 500, 500-A, 500-B and 13 more. Effective Mar 19, 1973
- [AD 67-28-01](https://openairdocs.org/ad/67-28-01): Lower Front Spar Cap · Twin Commander 560-E, 680, 680-E and 1 more. Effective Oct 10, 1967
- [AD 67-26-04](https://openairdocs.org/ad/67-26-04): Altimeters · Bell Helicopter Textron Canada 206A, 150G, 172H (USAF T-41A) and 36 more
- [AD 67-22-01](https://openairdocs.org/ad/67-22-01): Main Landing Gear · Twin Commander 500-A, 500-B, 560-F and 4 more. Effective Aug 28, 1967
- [AD 64-02-01](https://openairdocs.org/ad/64-02-01): Main Landing Gear · Twin Commander 500-A, 500-B, 560-F and 2 more. Effective Feb 20, 1964
- [AD 63-08-01](https://openairdocs.org/ad/63-08-01): Fuel Gaging System · Twin Commander 520. Effective Apr 9, 1963
- [AD 62-08-02](https://openairdocs.org/ad/62-08-02): Fuel Line Modification · Twin Commander 520 and 560. Effective Apr 11, 1962
- [AD 61-14-01](https://openairdocs.org/ad/61-14-01): Engine Mount Inspection · Twin Commander 500, 500-A and 500-B. Effective Aug 8, 1961
- [AD 56-02-01](https://openairdocs.org/ad/56-02-01): Augmentor Tube Support Clamps · Twin Commander 560-A
- [AD 57-09-01](https://openairdocs.org/ad/57-09-01): Aileron Bellcrank Casting · Twin Commander 520, 560, 560-A and 1 more
- [AD 57-15-01](https://openairdocs.org/ad/57-15-01): Landing Gear Retaining Pins · Twin Commander 560-A, 560-E and 680
- [AD 58-01-01](https://openairdocs.org/ad/58-01-01): Fuel Vent Line Replacement · Twin Commander 520, 560, 560-A and 2 more
- [AD 59-04-01](https://openairdocs.org/ad/59-04-01): Stabilizer Rivets · Twin Commander 500, 560, 560-A and 4 more
- [AD 59-06-01](https://openairdocs.org/ad/59-06-01): Elevator Front Spar · Twin Commander 500
- [AD 59-16-01](https://openairdocs.org/ad/59-16-01): Fuel Line Routing · Twin Commander 500, 520, 560 and 5 more
- [AD 98-08-25](https://openairdocs.org/ad/98-08-25) (historical): Nose Landing Gear (NLG) Drag Link Bolt · Twin Commander 500-S, 500-U, 680-F and 9 more. Effective May 18, 1998
- [AD 96-12-08](https://openairdocs.org/ad/96-12-08) (historical): Nose Landing Gear (NLG) Drag Link Bolt · Twin Commander 500-S, 500-U, 680-F and 8 more. Effective Jun 27, 1996
- [AD 94-04-17](https://openairdocs.org/ad/94-04-17) (historical): Flap System Cable · Twin Commander 500, 500-A, 500-B and 27 more. Effective Apr 15, 1994

## Registered aircraft by registry model (OpenAirDocs)

- [Aero Commander 500-B](https://openairdocs.org/model/aero-commander-500-b): 85 aircraft (registry code 0141106)
- [Aero Commander 500 S](https://openairdocs.org/model/aero-commander-500-s): 45 aircraft (registry code 0141107)
- [Aero Commander 500-A](https://openairdocs.org/model/aero-commander-500-a): 23 aircraft (registry code 0141104)
- [Rockwell International 500-S](https://openairdocs.org/model/rockwell-international-500-s): 19 aircraft (registry code 7630410)
- [Aero Commander 500](https://openairdocs.org/model/aero-commander-500): 12 aircraft (registry code 0141102)
- [Aero Commander 520](https://openairdocs.org/model/aero-commander-520): 12 aircraft (registry code 0141202)
- [Aero Commander 560-A](https://openairdocs.org/model/aero-commander-560-a): 10 aircraft (registry code 0141404)
- [Aero Commander 560-E](https://openairdocs.org/model/aero-commander-560-e): 5 aircraft (registry code 0141406)
- [Aero Commander 500-U](https://openairdocs.org/model/aero-commander-500-u): 3 aircraft (registry code 0141108)
- [Aero Commander 560](https://openairdocs.org/model/aero-commander-560): 2 aircraft (registry code 0141402)

## STCs approved under this data sheet (372, 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 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 SA04652CH](https://openairdocs.org/stc/SA04652CH): To allow use of 100R grade aviation fuel meeting Swift Fuel, LLC specification. Swift Fuels LLC
- [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 SA8453SW](https://openairdocs.org/stc/SA8453SW): Replace the o-ring seals in the landing gear lower strut.. Metrea Special Aerospace ISR Inc.
- [STC SA02738CH](https://openairdocs.org/stc/SA02738CH): Installation of L-3 Communications Avionics Systems. Acron Aviation Inc.
- [STC SA04046CH PAGE 2](https://openairdocs.org/stc/SA04046CH%20PAGE%202): Installation of L-3 GENESIS  (TM) Electronic Standby Instrument System (ESI-500/MAG-500). Acron Aviation Inc.
- [STC SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [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 SA01757WI](https://openairdocs.org/stc/SA01757WI): To allow the use of UL91 or UL94 (minimum) grade aviation fuel. Swift Fuels LLC
- [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc.
- [STC SA00103DE](https://openairdocs.org/stc/SA00103DE): Installation of Infrared Imaging System and Recording System and Monitors, for  (S/N 1555-198). Dart Aerospace Company
- [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 SA136SO](https://openairdocs.org/stc/SA136SO): Installation of Turbosupercharged GO-480-D1A engines.. TALCO Aviation
- [STC SA193SO](https://openairdocs.org/stc/SA193SO): Installation of turbocharged Lycoming GO-480-C1B6 or GO-480-G1B6 engines, per STC SE124SO.. TALCO Aviation
- [STC SA257CE](https://openairdocs.org/stc/SA257CE): Installation of turbocharged Lycoming engines, Model IO-540-A1A5 with Hartzell HC-A3VK-2/V7636D propellers.. TALCO Aviation
- [STC SA683WE](https://openairdocs.org/stc/SA683WE): Installation of turbocharged Continental IO-470-M engines. TALCO Aviation
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC
- [STC SA04192NY](https://openairdocs.org/stc/SA04192NY): KFD 900 Primary Flight Display System Additional Functions. Honeywell International Inc
- [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 SA1686WE](https://openairdocs.org/stc/SA1686WE): Installation of Vibration Isolation Products (VIP) engine mount P/Ns VIP 50525-1 and VIP 50545-1 on various aircraft as shown on FAA Approved Model List (AML) No. SA1686WE.. FTG, Inc.
- [STC SA1904WE](https://openairdocs.org/stc/SA1904WE): Installation of Vibration Isolation Products (VIP) engine mount P/N VIP-50804-10 on various aircraft as shown on FAA Approved Model List (AML) No. SA1904WE.. FTG, Inc.
- [STC SA706GL](https://openairdocs.org/stc/SA706GL): Install Cleveland conversion kit P/N 199-122 (for aircraft using MIL-H05606 brake fluid), or199-122A (for aircraft using 'Skydrol' brake fluid).. Kaman Corporation Aircraft Wheel and Brake LLC
- [STC SA1457GL](https://openairdocs.org/stc/SA1457GL): Installation of a Cleveland nose wheel.. 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 SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King)
- [STC SA11174SC PAGE 2](https://openairdocs.org/stc/SA11174SC%20PAGE%202): 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 SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems
- [STC SA09763DS](https://openairdocs.org/stc/SA09763DS): Installation of an S-TEC 01326 Digital Flight Control System (DFCS). S-TEC Corporation
- [STC SA02700SE](https://openairdocs.org/stc/SA02700SE): Installation of a Supplemental Lighting System. Aviation Specialties Unlimited Inc.
- [STC SA01831WI](https://openairdocs.org/stc/SA01831WI): To allow the use of UL91 (minimum) grade aviation fuel. Petersen Aviation Inc
- [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 SA09906AC](https://openairdocs.org/stc/SA09906AC): Reduce maximum number of seats to 5 passenger seats with a total occupancy maximum of 6 occupants. Direct-To Aviation Services 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 SA03286CH](https://openairdocs.org/stc/SA03286CH): Install an electronic engine ignition system. Electroair Acquisition Corporation

All 372: https://openairdocs.org/tcds/6A1/stcs.md

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