# TCDS A12SO: Commander Aircraft Corporation

- Type: Type certificate data sheet
- Status: Current
- Holder: Commander Aircraft Corporation
- Revision: 23
- Revised: October 3, 2013
- Product: Aircraft, Small Airplane
- Certification basis: Part 21
- Registered aircraft: 523, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/40/eb/40ebc06cfeae13337b71a3b7e55eeb5e5ce22c13c3b4b587b27de7bb020aafe2
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/077E37B8A81B914C86257C2200702332.0001
- Page: https://openairdocs.org/tcds/A12SO

## Models (8)

As the data sheet lists them.

- 114A
- 112TCA
- 114B
- 112B
- 112TC
- 114
- 112
- 114TC

## 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 15 16 17 
Rev. No. 23 19 19 19 19 19 19 19 19 19 19 20 21 21 21 21 21 
 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
 
A12SO  
Revision 23  
COMMANDER  
112  
112TC  
112B 
112TCA 
114 
114A 
114B 
114TC 
 
October 3, 2013  
 
TYPE CERTIFICATE DATA SHEET A12SO 
 
This data sheet, which is part of Type Certificate No. A12SO, 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:  Commander Aircraft Corporation 
  2 Dorset Road 
  Colonia, NJ  07067 
 
Type Certificate Holder Record: CPAC, Inc. transferred to Commander Aircraft Corporation on October 3, 2013; 
  Commander Aircraft Company transferred to CPAC, Inc. on September 12, 2005; 
  Gulfstream Aerospace Corporation transferred to Commander Aircraft Company on 
December 27, 1988; 
  Gulfstream American Corporation transferred to Gulfstream Aerospace Corporation on 
February 3, 1981; 
  Rockwell International, Commander Aircraft Division transferred to Gulfstream American 
Corporation 
 
I. Model 112, 4 PCLM (Normal and Utility Category), Approved June 1, 1972 
 
Engine Lycoming I0-360-C1D6 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 rpm (200 hp) 
 
Propeller and Hartzell Constant Speed, Model HC-E2YR-1BF or HC-E2YR-1B Blade, Model F766A or  
  Propeller Limits 7666A  
 Pitch:  High 28° - 30°, Low 13° ± 0.2° at Blade Station 30 inches 
 Diameter:  Not over 76”, not under 74” 
 Governor:  Edo-Aire 34-828-014 or Edo-Aire 34-828-014-2 
 Spinner:  Hartzell C-3533 or C-3533P or Aero Commander 46390-3 
 Limitations:  Do not exceed 24” Hg. manifold pressure below 2400 rpm

2 A12SO, Rev.23 
I. Model 112 (cont’d) 
 
Airspeed Limits Never exceed 180 Kts (207 mph) CAS 
   Decrease speed 1 Kt per 1000 ft. above 10,000 ft. 
 Max. structural cruising 2550 lbs. 148 Kts (170 mph) CAS 
   Decrease speed 1 Kt per 1000 ft. above 10,000 ft. 
 Max. structural cruising 2650 lbs. 143 Kts (165 mph) CAS 
   Decrease speed 1 Kt per 1000 ft. above 10,000 ft. 
 Maneuvering (Normal 2550 lbs) 111 Kts (128 mph) CAS 
 Maneuvering (Normal 2650 lbs) 113 Kts (130 mph) CAS 
 Maneuvering (Utility) 118 Kts (136 mph) CAS 
 Flaps extended up to 20° 130 Kts (150 mph) CAS 
   20° to 35° 109 Kts (125 mph) CAS 
 Max. gear extended 130 Kts (150 mph) CAS 
 Max. gear operating 130 Kts (150 mph) CAS 
 Max. cowl flaps open 130 Kts (150 mph) CAS 
 Max. side window open 130 Kts (150 mph) CAS 
 
C.G. Range Normal Category 
 Forward: 103.5” aft of datum (18.8% MAC) at 2650 lbs. 
  101.4” aft of datum (15.0% MAC) at 2550 lbs. 
  97.0” aft of datum (7% MAC) at 2100 lbs. 
  97.0” aft of datum (7% MAC) at 1600 lbs. 
 
 Aft: 110.5” aft of datum (31.5% MAC) at 2650 lbs. 
  110.5” aft of datum (31.5% MAC) at 1600 lbs. 
 
 Utility Category 
 Forward: 100.8” aft of datum (13.9% MAC) at 2488 lbs. 
  97.0” aft of datum (7% MAC) at 2100 lbs. 
  97.0” aft of datum (7% MAC) at 1600 lbs. 
 
 Aft: 106.5” aft of datum (24.25% MAC) at 2488 lbs. 
  106.5” aft of datum (24.25% MAC) at 1600 lbs. 
 
  Straight line variations between points. 
 
Empty Weight C.G. Range None 
 
Datum 62.5” forward of firewall (front face) 
 
Leveling Means Bottom of fuselage, outer surface, from F.S. 62.5 to F.S. 97.6 
 
Maximum Weight 2550 lbs. takeoff; 2550 landing (S/N 3 thru 125). 
 See Note 4 – Normal Category 
 
No. of Seats 2 Occupants at (+ 99.0); 2 Occupants at (+ 136.0) Normal Category Only 
 
Maximum Baggage 200 lbs. (at + 164.0) Normal Category 
 0 lbs. Utility Category 
 
Fuel Capacity 64 gal. usable (2 wing tanks) at +108.6. 
 (See Note 1 for unusable fuel)(S/N 3 thru 125) 
 68 gal. usable (2 wing tanks) at +108.6. 
 (See Note 1 for unusable fuel)(S/N 126 thru 155) 
 48 gal. usable (2 wing tanks) at +108.6. 
 (See Note 1 for unusable fuel)(S/N 156 and up – Std.) 
 68 gal. usable (2 wing tanks) at +108.6. 
 (See Note 1 for unusable fuel)(S/N 156 and up – optional.) 
 
Oil Capacity 8 qts. At +46.5 (6 qts. Usable) (See Note 1 for undrainable oil).

3 A12SO, Rev.23 
I. Model 112 (cont’d) 
 
Control Surface Movements Wing Flaps Up 0° ± ½° Down 40° ± 2° 
  (Serial Numbers 1 thru 81) (See Note 5) 
 
  Up 0° ± 1° Down 35° ± 2° 
  (Serial Numbers 82 & up)  
 
 Aileron Up 20° ± 27° Down 7° ± 11° 
  (Max. up must be within 4° left to right) 
 
 Rudder Left 22° ± 2° Right 28°* ± 2° 
 
 Elevator Up 30° ± 2° Down 13° ± 2° 
 Elevator Up 15° ± 2° Down 26° ± 1° 
 *Front vertical stabilizer centerline 
 
Nose Wheel Movement Steering ± 15° 
 Castoring ± 30° 
 
Serial Numbers Eligible 1, 3 thru 489, and 13000 
 
 
II. Model 114, 4 PCLM, (Normal Category), Approved March 8, 1976, (Utility Category) Approved March 31, 1977 
 
Engine Lycoming I0-540-T4A5D or I0-540-T4B5D (S/N 1400 thru 14149) 
 Lycoming I0-540-T4B5D (S/N 14150 & Subs) 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Propeller and Hartzell Constant Speed, Model HC-C2YR-1BF/F8467-7R 
  Propeller Limits Blade:  Model F8467-7R 
 Pitch:  High 30° - 32°, Low 14.2° ± 0.1° at Blade Station 30” 
 Diameter:  Not over 77”, no reduction allowed. 
 Governor:  Edo-Aire 34-828-014-7 
 Spinner:  46390-3 
 Limitations:  None 
 
Airspeed Limits Never exceed SL – 12,500 ft. 186 Kts (214 mph) CAS 
  16,000 ft. 175 Kts (201 mph) CAS 
  20,000 ft. 161 Kts (185 mph) CAS 
  24,000 ft. 147 Kts (169 mph) CAS 
 
 Max. structural cruising SL – 12,500 ft. 148 Kts (170 mph) CAS 
  16,000 ft. 139 Kts (160 mph) CAS 
  20,000 ft. 128 Kts (147 mph) CAS 
  24,000 ft. 117 Kts (135 mph) CAS 
 
 Maneuvering (Normal) 3140 lbs. 118 Kts (135 mph) CAS 
  2658 lbs. 109 Kts (125 mph) CAS 
 
  2023 lbs. 95 Kts (109 mph) CAS 
  Straight line variation between points. 
 
 Maneuvering (Utility) 2800 lbs. 120 Kts (138 mph) CAS 
  2250 lbs. 107 Kts (124 mph) CAS 
  2023 lbs. 102 Kts (117 mph) CAS 
  Straight line variation between points.

4 A12SO, Rev.23 
II. Model 114 (cont’d) 
 
Airspeed Limits (cont’d) Flaps extended  Up to 20° 150 Kts (173 mph) CAS* 
  20° to 25° 120 Kts (138 mph) CAS 
  25° to 35° 109 Kts (125 mph) CAS 
 Max. gear extended  186 Kts (214 mph) CAS* 
 Max. gear operating  130 Kts (150 mph) CAS 
 Max. cowl flaps open (S/N 14000 thru 14149) 130 Kts (150 mph) CAS 
 Max. side window open  130 Kts (150 mph) CAS 
 * Do not Exceed Vne Schedule 
 
C.G. Range Normal Category 
 Forward: 106.91” aft of datum (25.0% MAC) at 3140 lbs. 
  101.11” aft of datum (14.5% MAC) at 2658 lbs. 
  99.75” aft of datum (12.0% MAC) at 2250 lbs. 
  99.75” aft of datum (12.0% MAC) at 2023 lbs. 
 
 Aft: 110.50” aft of datum (31.5% MAC) at 3140 lbs. 
  110.50” aft of datum (31.5% MAC) at 2503 lbs. 
  Straight line variation between points. 
 
 Utility Category 
 Forward: 102.82” aft of datum (17.57% MAC) at 2800 lbs. 
  101.11” aft of datum (14.5% MAC) at 2658 lbs. 
  99.75” aft of datum (12.0% MAC) at 2250 lbs. 
  99.75” aft of datum (12.0% MAC) at 2023 lbs. 
 
 Aft: 107.46” aft of datum (26.0% MAC) at 2800 lbs. 
  107.46” aft of datum (26.0% MAC) at 2266 lbs. 
  Straight line variations between points. 
 
Empty Weight C.G. Range None 
 
Datum 62.5” forward of firewall (front face) 
 
Leveling Means Bottom of fuselage, outer surface, from F.S. 62.5 to F.S. 97.6 
 
Maximum Weight (Normal) 3140 lbs. 
 
Maximum Weight (Utility) 2800 lbs. 
 
Maximum Zero Fuel Weight Normal Category 
  2852 lbs. Station 106.74 
  (24.69% MAC) to Sta. 110.50 (31.5% MAC) 
  2250 lbs. Sta. 99.75 (12.0% MAC) varying 
  Linearly to 2852 lbs. Sta. 106.74 (24.69% MAC) 
 
 Utility Category 
  2500 lbs. Station 102.66 
  (17.27% MAC) to Sta. 107.46 (26.0% MAC) 
  2250 lbs. Sta. 99.75 (12.0% MAC) varying 
  Linearly to 2500 lbs. Sta. 102.66 (17.27% MAC) 
 
Minimum Weight 2023 lbs. at Sta. 99.75 (12.00% MAC) to 
 (Normal & Utility) 2028 lbs. at Sta. 101.24 (14.70% MAC) to  
 2266 lbs. at Sta. 107.46 (26.00% MAC) to 
 2503 lbs. at Sta. 110.50 (31.50% MAC) – Normal Category Only. 
 Straight line variation between points.

5 A12SO, Rev.23 
II. Model 114 (cont’d) 
 
No. of Seats 2 Occupants at (+ 99.0) 
 2 Occupants at (+ 136.0) Normal Category Only 
 
Maximum Baggage 200 lbs. (at + 164.0)  
 
Fuel Capacity 68 gal. usable (2 wing tanks) at 108.6 (See Note 1 for unusable fuel). 
 
Oil Capacity 8 qts. At +43.0 (6 qts. usable) (See Note 1 for data on unusable oil). 
 
Control Surface Movements Wing Flaps Up 0° ± 1° Down 35° + 0° - 2° 
 Aileron Up 20° to 27° Down 7° to 11°  
  (Max up must be within 4° left to right) 
 Rudder Left 22° ± 2° Right 28°* ± 2° 
 Elevator Up 30° ± 2° Down 13° + 2° -1° 
 Elevator Up 15° ± 2° Down 26° ± 1° 
 *Front vertical stabilizer centerline 
 
Nose Wheel Movement Steering ± 15° 
 Castoring ± 30° 
 
Serial Nos. Eligible 14000 thru 14459 (See Note 7) 
 
III. Model 112TC, 4 PCLM (Normal Category), Approved April 27, 1976 
 
Engine Lycoming TO-360-C1A6D 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2575 rpm, 42” Hg. (210 hp) to 8,000 ft., 40” Hg. 8,001 ft. to 16,000 ft., 38” 
 Hg. 16,001 ft. to 20,000 ft. 
 
Propeller and Hartzell Constant Speed, Model HC-E2YR-1BF/F8467-7R 
  Propeller Limits Blade:  Model F8467-7R 
 Pitch:  High 29° - 32°, Low 15.0° ± 0.1° at Blade Station 30” 
 Diameter:  Not over 77”, not under 76.5” 
 Governor:  Edo-Aire 34-828-014-5 
 Spinner:  46390-3 
 Limitations: Continuous operation between 2250 and 2450 rpm with manifold pressure  
  below 20” Hg. is prohibited. Continuous operation below 2350 rpm at manifold 
  pressure above 34” Hg. is prohibited. 
 
Maximum Authorized Altitude 20,000 ft. 
 
Airspeed Limits Never exceed  180 Kts (207 mph) CAS 
 Max. structural cruising  143 Kts (165 mph) CAS 
 *Maneuvering  110 Kts (127 mph) CAS @ 2850 lbs. 
     92 Kts (106 mph) CAS @ 1998 lbs. 
 Flaps extended  Up to 20° 150 Kts (173 mph) CAS 
  20° to 25° 120 Kts (138 mph) CAS 
  25° to 35° 109 Kts (125 mph) CAS 
 Max. gear extended  180 Kts (207 mph) CAS 
 Max. gear operating  130 Kts (150 mph) CAS 
 Max. cowl flap open  130 Kts (150 mph) CAS 
 Max. side window open  130 Kts (150 mph) CAS 
 * Assume straight line variation between points.

6 A12SO, Rev.23 
III. Model 112TC (cont’d) 
 
C.G. Range Forward: 105.05” aft of datum (24.84% MAC) at 2850 lbs. 
  102.20” aft of datum (20.07% MAC) at 2608 lbs. 
  101.00” aft of datum (18.07% MAC) at 2200 lbs. 
  101.00” aft of datum (18.07% MAC) at 2005 lbs. 
 
 Aft: 109.20” aft of datum (31.77% MAC) at 2850 lbs. 
  109.20” aft of datum (31.77% MAC) at 2229 lbs. 
  Straight line variation between points. 
 
Empty Weight C.G. Range None 
 
Datum 62.5” forward of Firewall (front face) 
 
Leveling Means Bottom of fuselage, outer surface, from F.S. 62.5 to F.S. 97.6 
 
Maximum Weight 2850 lbs. 
 
Max. Zero Fuel Weight 2720 lbs. Sta. 106.20 
 (26.76% MAC) to Sta. 109.20 (31.77% MAC) 
 2200 lbs. Sta. 101.00 (18.07% MAC) varying 
 Linearly to 2331 lbs. Sta. 101.38 (18.70% MAC) 
 Varying linearly to 2720 lbs. Sta. 106.20 (26.76% MAC) 
 
Minimum Weight 2005 lbs. at Sta. 101.0” (18.07% MAC) to 
 1998 lbs. at Sta. 102.42” (20.44% MAC) to  
 2035 lbs. at Sta. 106.0” (26.42% MAC) to 
 2229 lbs. at Sta. 109.2” (31.77% MAC) 
 Straight line variation between points. 
 
No. of Seats 2 Occupants at (+ 99.0) 
 2 Occupants at (+ 136.0) 
 
Maximum Baggage 200 lbs. at (+ 164.0)  
 
Fuel Capacity 48 gal. usable (2 wing tanks) at 108.6 (Std.) 
68 gal. usable (2 wing tanks) at 108.6 (Opt.) 
 (See Note 1 for unusable fuel). 
 
Oil Capacity 8 qts. at +45.5 (6 qts. usable) (See Note 1 for undrainable oil). 
 
Control Surface Movements Wing Flaps Up 0° ± 1° Down 35° ± 2° 
 Aileron Up 20° to 27° Down 7° to 11°  
  (Max up must be within 4° left to right) 
 Rudder Left 22° ± 2° Right 28°* ± 2° 
 Elevator Up 30° ± 2° Down 13° + 2° -1° 
 Elevator Up 15° ± 2° Down 26° ± 1° 
 *Front vertical stabilizer centerline 
 
Nose Wheel Movement Steering ± 15° 
 Castoring ± 30° 
 
Serial Nos. Eligible 13001 thru 13108 
 
 
IV. Model 112B, 4 PCLM (Normal Category), Approved October 5, 1976, (Utility Category), Approved March 31, 1977 
 
Engine Lycoming IO-360-C1D6 
 
Fuel 100/130 minimum grade aviation gasoline

7 A12SO, Rev.23 
IV. Model 112B (cont’d) 
 
Engine Limits For all operations, 2700 rpm (200 hp) 
 
Propeller and Hartzell Constant Speed, Model HC-E2YR-1BF/F8467-7R or  
  Propeller Limits HC-E2YK-1BF/F8467-7R 
 Blade:  Model F8467-7R 
 Pitch:  High 29° - 32°, Low 11.6° ± 0.1° at Blade Station 30” 
 Diameter:  Not over 77”, not under 76.5” 
 Governor:  Edo-Aire 34-828-014-2 
 Spinner:  Hartzell C-3533 or C-3533P or Aero Commander 46390-3 
 Limitations:  Do not exceed 24” Hg. manifold pressure below 2350 rpm 
 
Airspeed Limits Never exceed  180 Kts (207 mph) CAS 
 Max. structural cruising  143 Kts (165 mph) CAS 
 *Maneuvering (Normal)  109 Kts (125 mph) CAS @ 2800 lbs. 
     92 Kts (106 mph) CAS @ 1998 lbs. 
 *Maneuvering (Utility)  115 Kts (133 mph) CAS @ 2700 lbs. 
     99 Kts (114 mph) CAS @ 1998 lbs. 
 Flaps extended  Up to 20° 150 Kts (173 mph) CAS 
  20° to 25° 120 Kts (138 mph) CAS 
  25° to 35° 109 Kts (125 mph) CAS 
 Max. gear extended  180 Kts (207 mph) CAS 
 Max. gear operating  130 Kts (150 mph) CAS 
 Max. side window open  130 Kts (150 mph) CAS 
 * Assume straight line variation between points. 
 
C.G. Range Normal Category 
 Forward: 104.90” aft of datum (24.58% MAC) at 2800 lbs. 
  102.20” aft of datum (20.07% MAC) at 2608 lbs. 
  101.00” aft of datum (18.07% MAC) at 2200 lbs. 
  101.00” aft of datum (18.07% MAC) at 2005 lbs. 
 
 Aft: 109.20” aft of datum (31.77% MAC) at 2800 lbs. 
  109.20” aft of datum (31.77% MAC) at 2229 lbs. 
  Straight line variation between points. 
 
 Utility Category 
 Forward: 103.28” aft of datum (21.87% MAC) at 2700 lbs. 
  102.20” aft of datum (20.07% MAC) at 2608 lbs. 
  101.00” aft of datum (18.07% MAC) at 2200 lbs. 
  101.00” aft of datum (18.07% MAC) at 2005 lbs. 
 
 Aft: 106.0” aft of datum (26.42% MAC) at 2700 lbs. 
  106.0” aft of datum (26.42% MAC) at 2035 lbs. 
  Straight line variations between points. 
 
Empty Weight C.G. Range None 
 
Datum 62.5” forward of Firewall (front face) 
 
Leveling Means Bottom of fuselage, outer surface, from F.S. 62.5 to F.S. 97.6 
 
Maximum Weight Normal - 2800 lbs. 
 Utility – 2700 lbs. 
 
Max. Zero Fuel Weight Normal Category 
 2620 lbs. Sta. 107.00 
 (28.09% MAC) to Sta. 109.20 (31.77% MAC) 
 2200 lbs. Sta. 101.00 (18.07% MAC) varying 
 Linearly to 2620 lbs. Sta. 107.00 (28.09% MAC)

8 A12SO, Rev.23 
IV. Model 112B (cont’d) 
 
Max. Zero Fuel Weight (cont’d) Utility Category 
 2292 lbs. Sta. 102.33 
 (20.29% MAC) to Sta. 106.00 (26.42% MAC) 
 2200 lbs. Sta. 101.00 (18.07% MAC) varying 
 Linearly to 2292 lbs. Sta. 102.33 (20.29% MAC) 
 
Minimum Weight 2005 lbs. at Sta. 101.0” (18.07% MAC) to 
 1998 lbs. at Sta. 102.42” (20.44% MAC) to  
 2035 lbs. at Sta. 106.0” (26.42% MAC) to 
 2229 lbs. at Sta. 109.2” (31.77% MAC) – Normal Category Only 
 Straight line variation between points. 
 
No. of Seats 2 Occupants at (+ 99.0) 
 2 Occupants at (+ 136.0) – Normal Category Only 
 
Maximum Baggage 200 lbs. at (+ 164.0)  
 
Fuel Capacity 48 gal. usable (2 wing tanks) at 108.6 (Std.) 
 68 gal. usable (2 wing tanks) at 108.6 (Opt.) 
 (See Note 1 for unusable fuel). 
 
Oil Capacity 8 qts. At +46.5 (6 qts. usable) (See Note 1 for undrainable oil). 
 
Control Surface Movements Wing Flaps Up 0° ± 1° Down 35° ± 2° 
 Aileron Up 20° to 27° Down 7° to 11°  
 (Max up must be within 4° left to right) 
 Rudder Left 23° ± 1° Right 28°* ± 2° 
 Elevator Up 30° ± 2° Down 13° + 2° -1° 
 Elevator Up 15° ± 2° Down 26° ± 1° 
 *Front vertical stabilizer centerline 
 
Nose Wheel Movement Steering ± 15° 
 Castoring ± 30° 
 
Serial Nos. Eligible 13000, 500 thru 544 (See Note 7) 
 
 
V. Model 112TCA, 4 PCLM (Normal Category), Approved December 7, 1976, (Utility Category),  
 Approved March 31, 1977 
 
Engine Lycoming TO-360-C1A6D 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2575 rpm, 42” Hg. (210 hp) to 8,000 ft., 40” Hg. 8,001 ft., 38” Hg. 16,001 
ft. to 20,000 ft. 
 
Propeller and Hartzell Constant Speed, Model HC-E2YR-1BF/F8467-7R  
  Propeller Limits Blade:  Model F8467-7R 
 Pitch:  High 29° - 32°, Low 15.0° ± 0.1° at Blade Station 30” 
 Diameter:  Not over 77”, not under 76.5” 
 Governor:  Edo-Aire 34-828-014-5 
 Spinner:  46390-3 
 Limitations: Continuous operation between 2250 and 2450 rpm with manifold pressure 
below 20” Hg. is prohibited. Continuous operation below 2350 rpm at manifold 
pressure above 34” Hg. is prohibited. 
 
Max. Authorized Altitude 20,000

9 A12SO, Rev.23 
V. Model 112TCA (cont’d) 
 
Airspeed Limits Never exceed  180 Kts (207 mph) CAS 
 Max. structural cruising  143 Kts (165 mph) CAS 
 *Maneuvering (Normal)  111 Kts (128 mph) CAS @ 2950 lbs. 
     98 Kts (113 mph) CAS @ 2300 lbs. 
     91 Kts (105 mph) CAS @ 1998 lbs. 
 *Maneuvering (Utility)  117 Kts (135 mph) CAS @ 2800 lbs. 
   115 Kts (133 mph) CAS @ 2708 lbs. 
     99 Kts (114 mph) CAS @ 1998 lbs. 
 Flaps extended  Up to 20° 150 Kts (173 mph) CAS 
  20° to 25° 120 Kts (138 mph) CAS 
  25° to 35° 109 Kts (125 mph) CAS 
 Max. gear extended  180 Kts (207 mph) CAS 
 Max. gear operating  130 Kts (150 mph) CAS 
 Max. side window open  130 Kts (150 mph) CAS 
 * Assume straight line variation between points. 
 
C.G. Range Normal Category 
 Forward: 106.29” aft of datum (26.91% MAC) at 2962 lbs. 
  102.20” aft of datum (20.07% MAC) at 2608 lbs. 
  101.00” aft of datum (18.07% MAC) at 2200 lbs. 
  101.00” aft of datum (18.07% MAC) at 2005 lbs. 
 
 Aft: 109.20” aft of datum (31.77% MAC) at 2962 lbs. 
  109.20” aft of datum (31.77% MAC) at 2229 lbs. 
  Straight line variation between points. 
 
 Utility Category 
 Forward: 104.44” aft of datum (23.82% MAC) at 2800 lbs. 
  102.20” aft of datum (20.07% MAC) at 2608 lbs. 
  101.00” aft of datum (18.07% MAC) at 2200 lbs. 
  101.00” aft of datum (18.07% MAC) at 2005 lbs. 
 
 Aft: 107.0” aft of datum (28.09% MAC) at 2800 lbs. 
  107.0” aft of datum (28.09% MAC) at 2096 lbs. 
  Straight line variations between points. 
 
Empty Weight C.G. Range None 
 
Datum 62.5” forward of firewall (front face) 
 
Leveling Means Bottom of fuselage, outer surface, from F.S. 62.5 to F.S. 97.6 
 
Maximum Weight Normal 
  Maximum Ramp – 2962 lbs. 
  Maximum Takeoff – 2950 lbs. 
 Utility 
  Maximum Gross – 2800 lbs. 
 
Max. Zero Fuel Weight Normal Category 
 2720 lbs. Sta. 106.20 
 (26.76% MAC) to Sta. 109.20 (31.77% MAC) 
 2200 lbs. Sta. 101.00 (18.07% MAC) varying 
 Linearly to 2331 lbs. Sta. 101.38 (18.70% MAC) 
 Varying linearly to 2720 lbs. Sta. 106.20 (26.76% MAC) 
 
 Utility Category 
 2500 lbs. Sta. 103.48 
 (22.20% MAC) to Sta. 107.0 (28.09% MAC) 
 2200 lbs. Sta. 101.00 (18.07% MAC) varying 
 Linearly to 2331 lbs. Sta. 101.38 (18.70% MAC) 
 Varying linearly to 2500 lbs. Sta. 103.48 (22.20% MAC)

10 A12SO, Rev.23 
V. Model 112TCA (cont’d) 
 
Minimum Weight 2005 lbs. at Sta. 101.0” (18.07% MAC) to 
  (Normal and Utility) 1998 lbs. at Sta. 102.42” (20.44% MAC) to  
 2035 lbs. at Sta. 106.0” (26.42% MAC) to 
 2229 lbs. at Sta. 109.2” (31.77% MAC) – Normal Category Only 
 Straight line variation between points. 
 
No. of Seats 2 Occupants at (+ 99.0) 
 2 Occupants at (+ 136.0) – Normal Category Only 
 
Maximum Baggage 200 lbs. at (+ 164.0)  
 
Fuel Capacity 48 gal. usable (2 wing tanks) at 108.6 (Std.) 
68 gal. usable (2 wing tanks) at 108.6 (Opt.) 
 (See Note 1 for unusable fuel). 
 
Oil Capacity 8 qts. at +45.5 (6 qts. usable) (See Note 1 for undrainable oil). 
 
Control Surface Movements Wing Flaps Up 0° ± 1° Down 35° ± 2° 
 Aileron Up 20° to 27° Down 7° to 11°  
 (Max up must be within 4° left to right) 
 Rudder Left 23° ± 1° Right 28°* ± 2° 
 Elevator Up 30° ± 2° Down 13° + 2° -1° 
 Elevator Up 15° ± 2° Down 26° ± 1° 
 *Front vertical stabilizer centerline 
 
Nose Wheel Movement Steering ± 15° 
 Castoring ± 30° 
 
Serial Nos. Eligible 13150 thru 13309 (See Note 7) 
 
 
VI. Model 114A, 4 PCLM (Normal Category), Approved January 22, 1979 
 
Engine Lycoming IO-540-T4B5D 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 rpm, (260 hp) 
 
Propeller and McCauley Constant Speed, Model B3D34C405/90DFA-13  
  Propeller Limits Blade:  Model 90DFA-13 
 Pitch:  High 33.0° ± .5°, Low 11.5° ± .2° at Blade Station 30” 
 Diameter:  Not over 77”, reduction allowed to 76” 
 Governor:  Woodward 210903 
 Spinner:  46390-501 
 Limitations:  None 
 
Airspeed Limits Never exceed SL – 12,500 ft. 186 Kts (214 mph) CAS 
  16,000 ft. 175 Kts (201 mph) CAS 
  20,000 ft. 161 Kts (185 mph) CAS 
  24,000 ft. 147 Kts (169 mph) CAS 
 
 Max. structural cruising SL – 12,500 ft. 148 Kts (170 mph) CAS 
  16,000 ft. 139 Kts (160 mph) CAS 
  20,000 ft. 128 Kts (147 mph) CAS 
  24,000 ft. 117 Kts (135 mph) CAS

11 A12SO, Rev.23 
VI. Model 114A (cont’d) 
 
Airspeed Limits (cont’d) *Maneuvering (Normal) 3250 lbs. 118 Kts (135 mph) CAS 
  2658 lbs. 109 Kts (125 mph) CAS 
  2023 lbs. 95 Kts (109 mph) CAS 
   Straight line variation between points. 
 
 Flaps extended  Up to 20° 150 Kts (173 mph) CAS* 
  20° to 25° 120 Kts (138 mph) CAS 
  25° to 35° 109 Kts (125 mph) CAS 
 Max. gear extended  186 Kts (214 mph) CAS* 
 Max. gear operating  130 Kts (150 mph) CAS 
 Max. side window open  130 Kts (150 mph) CAS 
 * Do not Exceed Vne Schedule 
 
C.G. Range Forward: 106.97” aft of datum (25.1% MAC) at 3260 lbs. 
  101.11” aft of datum (14.5% MAC) at 2658 lbs. 
  99.75” aft of datum (12.0% MAC) at 2250 lbs. 
  99.75” aft of datum (12.0% MAC) at 2096 lbs. 
 
 Aft: 110.50” aft of datum (31.5% MAC) at 3260 lbs. 
  110.50” aft of datum (31.5% MAC) at 2575 lbs. 
  Straight line variation between points. 
 
Empty Weight C.G. Range None 
 
Datum 62.5” forward of Firewall (front face) 
 
Leveling Means Bottom of fuselage, outer surface, from F.S. 62.5 to F.S. 97.6 
 
Maximum Weight Ramp – 3260 lbs. 
 Takeoff – 3250 lbs. 
 Landing – 3140 lbs. 
 
Max. Zero Fuel Weight 3000 lbs. at Sta. 106.83 (24.9% MAC) to Sta. 110.50 (31.5% MAC) 
 2450 lbs. at Sta. 100.48 (13.3% MAC) varying linearly to 3000 lbs. at Sta. 106.83 (24.9% 
MAC) 
 
Minimum Weight 2095 lbs. at Sta. 99.75” (12.00% MAC) to 
 2100 lbs. at Sta. 101.24” (14.70% MAC) to  
 2338 lbs. at Sta. 107.46” (26.00% MAC) to 
 2575 lbs. at Sta. 110.50” (31.52% MAC) 
 Straight line variation between points. 
 
No. of Seats 2 Occupants at (+ 99.0) 
 2 Occupants at (+ 136.0) 
 
Maximum Baggage 200 lbs. at (+ 164.0)  
 
Fuel Capacity 68 gal. usable (2 wing tanks) at 108.6 
 (See Note 1 for unusable fuel) 
 
Oil Capacity 8 qts. at +43.0 (6 qts. usable) (See Note 1 for undrainable oil). 
 
Control Surface Movements Wing Flaps Up 0° ± 1° Down 35° + 0° - 2° 
 Aileron Up 20° - 27° Down 7° - 11°  
 (Max up must be within 4° left to right) 
 *Rudder Left 22° ± 2° Right 28° ± 2° 
 Elevator Up 30° ± 2° Down 13° + 2° -1° 
 Elevator Up 15° ± 2° Down 26° ± 1° 
 *Front vertical stabilizer centerline

12 A12SO, Rev.23 
VI. Model 114A (cont’d) 
 
Nose Wheel Movement Steering ± 15° 
 Castoring ± 30° 
 
Serial Nos. Eligible 14500 thru 14540 
 
 
VII. Model 114B, 4 PCLM (Normal Category), Approved May 4, 1992 
 
Engine Lycoming IO-540-T4B5 
 
Fuel 100/130 minimum grade aviation gasoline 
 
Engine Limits For all operations, 2700 rpm, (260 hp) 
 
Propeller and McCauley Constant Speed, Model B3D32C419/82NHA-5  
  Propeller Limits Blade:  Model 82NHA-5 
 Pitch:  High 33.0° ± .5°, Low 12.6° ± .2° at Blade Station 30” 
 Diameter:  Not over 77”, reduction allowed to 75.5” 
 Governor:  Woodward 210903 or McCauley D-20309-37 
 Spinner:  615220-501 
 Limitations:  None 
 
Airspeed Limits Never exceed SL – 12,500 ft. 186 Kts (214 mph) CAS 
  16,000 ft. 175 Kts (201 mph) CAS 
  20,000 ft. 161 Kts (185 mph) CAS 
  24,000 ft. 147 Kts (169 mph) CAS 
 
 Max. structural cruising SL – 12,500 ft. 148 Kts (170 mph) CAS 
  16,000 ft. 139 Kts (160 mph) CAS 
  20,000 ft. 128 Kts (147 mph) CAS 
  24,000 ft. 117 Kts (135 mph) CAS 
 
 *Maneuvering (Normal) 3250 lbs. 118 Kts (135 mph) CAS 
  2658 lbs. 109 Kts (125 mph) CAS 
  2023 lbs. 95 Kts (109 mph) CAS 
  Straight line variation between points. 
 
 Flaps extended  Up to 20° 150 Kts (173 mph) CAS* 
  20° to 25° 120 Kts (138 mph) CAS 
  25° to 35° 109 Kts (125 mph) CAS 
 Max. gear extended  186 Kts (214 mph) CAS* 
 Max. gear operating  130 Kts (150 mph) CAS 
 Max. side window open  130 Kts (150 mph) CAS 
 * Do not Exceed Vne Schedule 
 
C.G. Range Forward: 106.97” aft of datum (25.1% MAC) at 3260 lbs. 
  104.05” aft of datum (19.8% MAC) at 3194 lbs. 
  101.11” aft of datum (14.5% MAC) at 2658 lbs. 
  99.75” aft of datum (12.0% MAC) at 2250 lbs. 
  99.75” aft of datum (12.0% MAC) at 2096 lbs. 
 
 Aft: 110.50” aft of datum (31.5% MAC) at 3260 lbs. 
  110.50” aft of datum (31.5% MAC) at 2575 lbs. 
  Straight line variation between points. 
 
Empty Weight C.G. Range None 
 
Datum 62.5” forward of Firewall (front face) 
 
Leveling Means Bottom of fuselage, outer surface, from F.S. 62.5 to F.S. 97.6

13 A12SO, Rev.23 
VII. Model 114B (cont’d) 
 
Maximum Weight Ramp – 3260 lbs. 
 Takeoff – 3250 lbs. 
 Landing – 3140 lbs. 
 
Max. Zero Fuel Weight 3000 lbs. at Sta. 106.83 (24.9% MAC) to Sta. 110.50 (31.5% MAC) 
 2450 lbs. at Sta. 100.48 (13.3% MAC) varying linearly to 3000 lbs. at Sta. 106.83 (24.9% 
MAC) 
 
Minimum Weight 2095 lbs. at Sta. 99.75” (12.00% MAC) to 
 2100 lbs. at Sta. 101.24” (14.70% MAC) to  
 2338 lbs. at Sta. 107.46” (26.00% MAC) to 
 2575 lbs. at Sta. 110.50” (31.52% MAC) 
 Straight line variation between points. 
 
No. of Seats 2 Occupants at (+ 99.0) 
 2 Occupants at (+ 136.0) 
 
Maximum Baggage 200 lbs. at (+ 164.0)  
 
Fuel Capacity 68 gal. usable (2 wing tanks) at 108.6 (See Note 1 for unusable fuel) 
 
Oil Capacity 8 qts. at +43.0 (6 qts. usable). (See Note 1 for undrainable oil). 
 
Control Surface Movements Wing Flaps Up 0° ± 1° Down 35° + 0° - 2° 
 Aileron Up 20° - 27° Down 7° - 11°  
 (Max up must be within 4° left to right) 
 *Rudder Left 22° ± 2° Right 28° ± 2° 
 Elevator Up 30° ± 2° Down 13° + 2° -1° 
 Elevator tab Up 15° ± 2° Down 26° ± 1° 
 *Front vertical stabilizer centerline 
 
Nose Wheel Movement Steering ± 15° 
 Castoring ± 30° 
 
Serial Nos. Eligible 14541 and Subsequent 
 
 
VIII. Model 114TC, 4 PCLM (Normal Category), Approved August 4, 1995 
 
Engine Lycoming TIO-540-AGIA 
 
Fuel 100/100LL minimum grade aviation gasoline 
 
Engine Limits For all operations, 2575 rpm, (270 hp) 
 
Propeller and McCauley Constant Speed, Model B3D32C419/G-82NHA-5  
  Propeller Limits Blade:  Model G-82NHA-5 
 Pitch:  High 33.9° ± .5°, Low 14.8° ± .2° at Blade Station 30” 
 Diameter:  Not over 77”, reduction allowed to 75.5” 
 Governor: McCauley D-20309-40 
 Spinner:  615220-501 
 Limitations:  None 
 
Maximum Authorized Altitude 25,000 ft.

14 A12SO, Rev.23 
VIII. Model 114TC (cont’d) 
 
Airspeed Limits Never exceed SL – 12,500 ft. 186 KCAS 
  15,000 ft. 176 KCAS 
  17,500 ft. 167 KCAS 
  20,000 ft. 158 KCAS 
  22,500 ft. 150 KCAS 
  25,000 ft. 141 KCAS 
 
 Max. structural cruising SL – 12,500 ft. 162 KCAS 
  15,000 ft. 153 KCAS 
  17,500 ft. 145 KCAS 
  20,000 ft. 138 KCAS 
  22,500 ft. 130 KCAS 
  25,000 ft. 122 KCAS 
 
 Maneuvering  3305 lbs. 118 KCAS 
  3000 lbs. 112 KCAS 
  2491 lbs. 102 KCAS 
 
 Flaps extended  Up to 20° 150 KCAS* 
  20° to 25° 120 KCAS 
  25° to 35° 109 KCAS 
 Max. gear extended  186 KCAS* 
 Max. gear operating  130 KCAS 
 Max. side window open  130 KCAS 
 * Do not Exceed Vne Schedule 
 
C.G. Range Forward: 100.5” aft of datum (13.4% MAC) at 2491 lbs. 
  101.1” aft of datum (14.5% MAC) at 2658 lbs. 
  103.0” aft of datum (17.8% MAC) at 3000 lbs. 
  103.7” aft of datum (19.2% MAC) at 3140 lbs. 
  104.6” aft of datum (20.8% MAC) at 3305 lbs. 
 
 Aft: 110.50” aft of datum (31.5% MAC) at 3305 lbs. 
  110.50” aft of datum (31.5% MAC) at 2491 lbs. 
  Straight line variation between points. 
 
Empty Weight C.G. Range None 
 
Datum 62.5” forward of firewall (front face) 
 
Leveling Means Bottom of fuselage, outer surface, from F.S. 62.5 to F.S. 97.6 
 
Maximum Weight Takeoff – 3305 lbs. 
 Landing – 3140 lbs. 
 
Max. Zero Fuel Weight 3000 lbs. 
 
Minimum Weight 2491 lbs. 
 
No. of Seats 2 Occupants at (+ 99.0) 
 2 Occupants at (+ 136.0) 
 
Maximum Baggage 200 lbs. at (+ 164.0)  
 
Fuel Capacity 88 gal. usable (2 wing tanks) at 108.6 
 (See Note 1 for unusable fuel) 
 
Oil Capacity 10 qts. at +43.0 (5.5 qts. usable). (See Note 1 for undrainable oil).

15 A12SO, Rev.23 
VIII. Model 114TC (cont’d) 
 
Control Surface Movements Wing Flaps Up 0° ± 1° Down 35° + 0° - 2° 
 Aileron Up 20° - 27° Down 7° - 11°  
 (Max up must be within 4° left to right) 
 *Rudder Left 22° ± 2° Right 28° ± 2° 
 Elevator Up 30° ± 2° Down 13° + 2° -1° 
 Elevator Up 15° ± 2° Down 26° ± 1° 
 *Front vertical stabilizer centerline 
 
Nose Wheel Movement Steering ± 15° 
 Castoring ± 30° 
 
Serial Nos. Eligible 20001 and Subsequent 
 
 
SPECIFICATIONS PERTINENT TO ALL MODELS 
 
Certification Basis FAR 23, effective February 1, 1965, including Amendments 1 thru 7. 
 FAR 36, effective February 3, 1975, Models 112B, 112TC, 112TCA, 114, 114A, 114B, and 
114TC 
 
Production Basis Production Certificate No. 506 (Model 112 S/N 1 thru 220) 
 Production Certificate No. 203 (Model 112 S/N 221, and Subs, Models 112B, 112TC, 
112TCA, 114, and 114A). 
 Delegation option Manufacturer No. SW-2 was authorized to issue airworthiness certificates 
under Delegation Option provisions of Part 21 of the Federal Aviation Regulations through the 
Model 114A. 
 Production Certificate No. PC7SW (Model 114B and 114TC S/N 14541 and subsequent). 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see 
Certification basis) must be installed in the aircraft for certification. This equipment must 
include a current Airplane Flight Manual. In addition, the following item is required: 
 
 Lift Detector, Safe Flight P/N 164-1, or 186-5 when installed in accordance with 
Drawing 48212. 
 
Note 1. Current weight and balance report, including 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 
locations must include undrainable oil (not included in the oil capacity) and unusable fuel as 
noted below: 
 
 Model 112 (S/N 3 thru 125) 
 Fuel (3 Gal. per tank) 36 lbs at (+112.2) 
 Oil 4 lbs at (+48.6) 
 
 Model 112 (S/N 126 thru 489) 
 Fuel (1 Gal. per tank) 12 lbs at (+112.2) 
 Oil 4 lbs at (+48.6) 
 
 Model 112B, 112TC, 112TCA, 114, 114A, & 114B 
 Fuel (1 Gal. per tank) 12 lbs at (+112.2) 
 Oil 4 lbs at (+48.6) 
 
 Model 114TC 
 Fuel (1 Gal. per tank) 12 lbs at (+112.2) 
 Oil 4.5 lbs at (+48.6)

16 A12SO, Rev.23 
SPECIFICATIONS PERTINENT TO ALL MODELS (cont’d) 
 
Note 2. (1) The following placards must be displayed in front of and in clear view of the pilot. 
 
  Models 112, 112B, 112TCA and 114, “This airplane must be operated as a Normal or 
Utility Category airplane in compliance with operating limitations stated in the Airplane 
Flight Manual.” 
 
  Model 112TC, 114A, 114B and 114TC “This airplane must be operated as a Normal 
Category airplane in compliance with operating limitations stated in Airplane Flight 
Manual.” See Approved Airplane Flight Manual/Pilots Operating Handbook for 
additional placards. “All placards required in the Approved Airplane Flight Manual must 
be installed in the appropriate location.” 
 
Note 3. Service Life – all categories 
 
 Model 112, the service life of the wing and associated structure has been established as 6945 
hours maximum. 
 
 Model 112B, the service life of the wing and associated structure has been established as 8878 
hours maximum. 
 
 Model 112TC, the service life of the wing and associated structure has been established as 
10908 hours maximum. 
 
 Model 112TCA, the service life of the wing and associated structure has been established as 
7947 hours maximum. 
 
 Model 114, the service life of the wing and associated structure has been established as 19284 
hours maximum. 
 
 Model 114A and 114B, the service life of the wing and associated structure has been 
established as 14812 hours maximum. 
 
 Model 114TC, the service life of the wing and associated structure has been established as 
10349 hours maximum. 
 
Note 4. Serial Numbers 3 thru 125 may be operated at a maximum takeoff weight of 2650 and a 
landing weight of 2550 when Rockwell International Service Letter SL-112-4 has been 
complied with. 
 
Note 5. If Service Letter SL-112-4 has been complied with, wing flap travel is limited to down  
 35° ± 2°. 
 
Note 6. CANCELLED 
 
Note 7. The following Models and Serial Numbers may be operated as Utility Category Aircraft when 
modified per Rockwell Custom Kit CK-112-6 or CK-114-1. 
 
  Model 112 B S/N 500 thru 544 
  Model 112 TCA S/N 13150 thru 13175 
  Model 114 S/N 14000 thru 14254

17 A12SO, Rev.23 
SPECIFICATIONS PERTINENT TO ALL MODELS (cont’d) 
 
Note 8. The following list of reports and drawings define the approved equipment for the applicable 
model. 
 
 Model Report No. 
 112 EG80-246 
 112TC EG80-247 
 112B EG80-263 
 112TCA EG80-264 (S/N 13001 thru 13299) 
  EG80-299 (S/N 13000 thru 13999) 
 114 EG80-248 
 114A EG80-297 
 114B Drawing No. 845001 Avionics/Instrument/Equipment Installations 
  Drawing No. 105001 Aircraft Complete 
 114TC Drawing No. 845001 Avionics/Instrument/Equipment Installations 
  Drawing No. 105001 Aircraft Complete 
 
 
 
....END....
```

## ADs (21, in force first)

- [AD 2024-14-03](https://openairdocs.org/ad/2024-14-03): Autopilot System · Garmin GFC 500 Autopilot (STC SA01866WI). Effective Aug 20, 2024
- [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 2012-02-10](https://openairdocs.org/ad/2012-02-10): Stabilizers · Commander 112, 112B, 112TC and 5 more. Effective Mar 15, 2012
- [AD 2006-12-07](https://openairdocs.org/ad/2006-12-07): ECi cylinder assemblies · Aerostar AEIO-320-D1B, AEIO-320-D2B, AEIO-320-E1A and 386 more. Effective Jul 11, 2006
- [AD 2006-03-08](https://openairdocs.org/ad/2006-03-08): Vacuum pumps · Aero Advantage 14-19, 14-19-2, 14-19-3 and 299 more. Effective Mar 10, 2006
- [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 2001-10-09](https://openairdocs.org/ad/2001-10-09): Automatic Flight Control Systems · Aerostar PA-60-700P (Aerostar 700P), 208, 208B and 15 more. Effective Jun 15, 2001
- [AD 2000-11-04](https://openairdocs.org/ad/2000-11-04): Aeroquip V-band Exhaust Clamp · Commander 114TC. Effective Jun 23, 2000
- [AD 90-04-07](https://openairdocs.org/ad/90-04-07): Wing Spars · Commander 112, 112B, 112TC and 3 more. Effective Mar 9, 1990
- [AD 88-05-06](https://openairdocs.org/ad/88-05-06): Inspect for Cracks · Commander 112, 112B, 112TC and 3 more. Effective Apr 8, 1988
- [AD 85-03-04 R2](https://openairdocs.org/ad/85-03-04-R2): Front Seat and Belt Attachment · Commander 112, 112TC and 114. Effective Apr 27, 1987
- [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 77-13-16](https://openairdocs.org/ad/77-13-16): Carburetors · Commander 112TC, 112TCA and Carburetors. Effective Jul 6, 1977
- [AD 77-01-08](https://openairdocs.org/ad/77-01-08): Engine Failure · Commander 112. Effective Jan 14, 1977
- [AD 76-23-02](https://openairdocs.org/ad/76-23-02): Cabin Vents and Air Ducts · Commander 114. Effective Nov 26, 1976
- [AD 75-22-09](https://openairdocs.org/ad/75-22-09): Ailerons · Commander 112. Effective Nov 4, 1975
- [AD 73-24-01](https://openairdocs.org/ad/73-24-01): Control Surface Hinge Failure · Commander 112. Effective Nov 19, 1973
- [AD 73-14-04](https://openairdocs.org/ad/73-14-04): Engine and Prop Controls · Commander 112. Effective Jul 3, 1973
- [AD 73-14-06](https://openairdocs.org/ad/73-14-06): Cracks in Prop Spinner Bulkhead · Commander 112. Effective Jun 26, 1973
- [AD 2011-07-13](https://openairdocs.org/ad/2011-07-13) (historical): Stabilizers · CPAC 112, 112B, 112TC and 5 more. Effective Apr 4, 2011

## Registered aircraft by registry model (OpenAirDocs)

- [Rockwell International 114](https://openairdocs.org/model/rockwell-international-114): 186 aircraft (registry code 7630314)
- [Aero Commander 112](https://openairdocs.org/model/aero-commander-112): 98 aircraft (registry code 0144701)
- [Commander 114-B](https://openairdocs.org/model/commander-114-b): 70 aircraft (registry code 0145001)
- [Rockwell International 112TC](https://openairdocs.org/model/rockwell-international-112tc): 47 aircraft (registry code 7630306)
- [Rockwell International 112TCA](https://openairdocs.org/model/rockwell-international-112tca): 43 aircraft (registry code 7630307)
- [Commander 114TC](https://openairdocs.org/model/commander-114tc): 33 aircraft (registry code 0145002)
- [Rockwell International 114A](https://openairdocs.org/model/rockwell-international-114a): 21 aircraft (registry code 7630315)
- [Rockwell International 112B](https://openairdocs.org/model/rockwell-international-112b): 16 aircraft (registry code 7630303)
- [Rockwell International 112](https://openairdocs.org/model/rockwell-international-112): 9 aircraft (registry code 7630301)
- [Aero Commander 114A](https://openairdocs.org/model/aero-commander-114a): 0 aircraft (registry code 0145003)

## STCs approved under this data sheet (245, first 50)

- [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 SA12428CH](https://openairdocs.org/stc/SA12428CH): Installation of the Lycoming Engines Electronic Ignition System (EIS). Lycoming Engines, An Operating Division of AVCO Corporation
- [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 SA01134DE](https://openairdocs.org/stc/SA01134DE): Installation of EarthX ETX680-24-TSO Lithium Battery. EarthX Inc.
- [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 SA02511SE](https://openairdocs.org/stc/SA02511SE): Installation of replacement fuel quantity indicator sending unit(s). CiES Inc.
- [STC SA01866WI](https://openairdocs.org/stc/SA01866WI): Installation of Garmin GFC 500 Autopilot with Electronic Stability and Protection. Garmin International Inc.
- [STC SA5757SW](https://openairdocs.org/stc/SA5757SW): Installation of Alcor tru-flow/ fuel flow/totalizer system.. Alcor 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 SA04378CH](https://openairdocs.org/stc/SA04378CH): Installation of an engine modified per STC SE04349CH. SureFly Partners Ltd.
- [STC SA02594SE](https://openairdocs.org/stc/SA02594SE): SkyView HDX Instrumentation and Autopilot System manufactured. Dynon Avionics
- [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 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 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 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 SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc.
- [STC SA02019WI](https://openairdocs.org/stc/SA02019WI): Installation of the Trig Avionics TX56, TX56A, TX57, or TX57A VHF Nav-Com Radio.. Peregrine
- [STC SA04400NY](https://openairdocs.org/stc/SA04400NY): Installation of the Integrated Back-up Battery System (IBBS). TCW Technologies LLC
- [STC SA01435LA](https://openairdocs.org/stc/SA01435LA): Installation of engines modified with Firewall Forward Technologies LLC modified camshaft. Centri-Lube Technologies LLC
- [STC SA02771LA](https://openairdocs.org/stc/SA02771LA): Installation of openable window. Ellis and Associates CADD/Technical Illustration
- [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 SA04586CH](https://openairdocs.org/stc/SA04586CH): Installation of Electroair Back Up Battery Panel System Control. Electroair Aquisition Corp.
- [STC SA2677CE](https://openairdocs.org/stc/SA2677CE): Installation of aileron and flap gap seals per Horton-STOL Craft Drawing List #15 with an approval date of August 18, 1994 or later FAA approved revision.. Curry Aviation LLC
- [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 SA01818WI](https://openairdocs.org/stc/SA01818WI): Installation of Garmin G5 Electronic Flight Instrument. Garmin International Inc.
- [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 SA03658NY](https://openairdocs.org/stc/SA03658NY): Installation of MT-Propeller Entwicklung GmbH's Model# MTV-12-B/188-59f 3-Blade constant speed propeller. MT- Propeller Entwicklung GmbH
- [STC SA02426AK](https://openairdocs.org/stc/SA02426AK): Approval of the FreeFlight FDL-978-TX ADS-B system installed. FreeFlight Systems
- [STC SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation
- [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 SA00249WI-D](https://openairdocs.org/stc/SA00249WI-D): Installation of Bendix/King KFC 200 Automatic Flight Control System. Honeywell International Inc
- [STC SA00817WI-D](https://openairdocs.org/stc/SA00817WI-D): Installation of Bendix/King KFC 225 Automatic flight Control System.. Honeywell International Inc
- [STC SA1229CE](https://openairdocs.org/stc/SA1229CE): Installation of King KFC-200, 2 axis(3 optional) flight control system with KCS 55/55A compass and a KI-255 (or -256) flight command indicator or a KG-258 attitude horizon gyro with a KC-292 mode controller; or stand alone electric trim.. 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 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

All 245: https://openairdocs.org/tcds/A12SO/stcs.md

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