# TCDS 3A18: Interceptor Aircraft Inc

- Type: Type certificate data sheet
- Status: Current
- Holder: Interceptor Aircraft Inc
- Revision: 19
- Revised: July 31, 2014
- Product: Aircraft, Small Airplane
- Certification basis: Part 3, CAR 3
- Registered aircraft: 83, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/71/ed/71ed2663ec920eb8e80c3c8ae25b06ecaeb94e8fd45a0557c19a2c9653f4b26a
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/AB97F6C31EA6D73786257D2A0052B9E6.0001
- Page: https://openairdocs.org/tcds/3A18

## Models (6)

As the data sheet lists them.

- 200
- 400
- 200B
- 200D
- 200C
- 200A

## 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 
Rev. No. 19 16 16 16 16 16 17 17 
Rev 19 Name corrected and address updated 
DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
3A18 
 Revision 19 
Interceptor 
(Aero Commander) 
(Meyers) 
(Interceptor) 
 200 
 200A 
 200B 
 200C 
 200D 
 400 
 
 July 31, 2014 
TYPE CERTIFICATE DATA SHEET NO. 3A18 
 
This data sheet, which is a part of Type Certificate No. 3A18, prescribes conditions and limitations under which the type 
certificate was issued meets the airworthiness requirements of the Civil Air Regulations/Federal Aviation Regulations.  
 
Type Certificate Holder Interceptor Aviation Inc. 
 6900 NW 63rd Street, Suite 100 
 Bethany, Oklahoma  73008 
 
Type Certificate ownership Record Company name/address changed to Interceptor Aviation, Inc. 901 Industrial Road, 
Augusta, KS 67010 on April 3, 2014. 
 Company name/address changed from Prop-Jets, Inc., 8901 Whetmore Road,  
San Antonio TX 78216 to Interceptor Aircraft Corporation, 29890 Bulverde Lane #14 
Bulverde, TX 78163 on October 30 2008 
 
I. Model 200, 4 PCLM (Normal Category), approved March 6, 1958 
 (The Model 200 may be converted to a Model 200A in accordance with Meyers Drawing A60B005) 
 
 Engine Continental O-470-M 
 Fuel 91/96 minimum grade aviation gasoline 
 Engine limits For all operations, 2600 rpm (240 hp) 
 Propeller and propeller limits See Note 6 
 
 Airspeed limits Never exceed 208 mph  (181 knots) 
  Maximum structural cruising 165 mph  (143 knots) 
  Maneuvering 132 mph  (115 knots) 
  Flaps extended 125 mph  (109 knots) 
  Maximum gear retraction speed 125 mph  (109 knots) 
  Maximum gear extension speed 165 mph  (143 knots) 
  Maximum gear extended speed 165 mph  (143 knots) 
 
 C.G. Range (landing gear (+31.5) to (+33.8) in. at 3000 lbs. 
   extended) (+24.6) to (+33.8) in. at 2500 lbs. 
  (+23.6) to (+33.8) in. at 2207 lbs. 
  Straight line variation between points given. 
  Moment change due to retracting landing gear +655 in.-lb. 
 
 Empty Weight C.G. Range None 
 
 Maximum Weight 3000 lbs. 
 
 No. of Seats 4  (2 at +30, 2 at +70) 
 
 Maximum Baggage 200 lb.  (+100)

2 of 8 3A18 Rev 19 
 
 Fuel Capacity 80 gal. (two 20-gal. wing tanks, 19-gal. usable in each tank, at +22), (two  
  20-gal. auxiliary wing tanks, 18.5 gal. usable in each tank at +41). 
  See NOTE 1 for unusable fuel. 
 
 Oil Capacity 3 gal.  (-23).  See NOTE 1 for data on system oil. 
 
 Control surface movements Wing flaps   Down 40° 
  Aileron tab Fixed 
  Aileron Up 22° Down   9.5° 
  Elevator tab Up   3° Down 13° 
  Elevator Up 32° Down 20° 
  Rudder Right 21° Left 21° 
 
 Serial nos. eligible 251 and 252 
 
II. Model 200A, 4 PCLM (Normal Category), approved June 18, 1959 
 (The Model 200 may be converted to a Model 200A in accordance with Meyers Drawing A60B005.) 
 
 Engine Continental IO-470-D 
 Fuel 100/130 minimum grade aviation gasoline 
 
 Engine limits For all operations, 2625 rpm (260 hp) 
 
 Propeller and propeller limits See NOTE 6. 
 
 Airspeed limits Never exceed 208 mph  (181 knots) 
  Maximum structural cruising 165 mph  (143 knots) 
  Maneuvering 132 mph  (115 knots) 
  Flaps extended 125 mph  (109 knots) 
  Maximum gear retraction speed 125 mph  (109 knots) 
  Maximum gear extension speed 165 mph  (143 knots) 
  Maximum gear extended speed 165 mph  (143 knots) 
 
 C.G. Range (landing gear (+31.5) to (+33.8) in. at 3000 lb. 
   extended) (+24.6) to (+33.8) in. at 2500 lb. 
  (+23.6) to (+33.8) in. at 2207 lb. 
  Straight line variation between points given. 
 
 Empty Wt. C.G. Range None 
 
 Maximum Weight 3000 lb. 
 
 No. seats 4  (2 at +30, 2 at +70) 
 
 Maximum Baggage 200 lb. (+100) 
 
 Fuel Capacity 80 gal. (two 20 gal. wing tanks, 18.5 gal. usable in each tank at +22), (two 20-gal.  
  auxiliary wing tanks, 18.5 gal. usable in each tank at +41) 
 
 Oil Capacity 3 gal. (-23).  See Note 1 for data on system oil. 
 
 Control Surface Movements Wing flaps   Down 40° 
  Aileron Up 22° Down   9.5° 
  Elevator tab Up   3° Down 13° 
  Elevator Up 32° Down 20° 
  Rudder Right 21° Left 21° 
 
 Serial nos. eligible 253 thru 263

3 of 8 3A18 Rev 19 
III. Model 200B, 4 PCLM (Normal Category), approved March 9, 1961 
 Model 200C, 4 PCLM (Normal Category), approved September 12, 1963 
 
 Engine Continental IO-470-D (see Note 5 for optional engine) 
 Fuel 100/130 minimum grade aviation gasoline 
 Engine limits For all operations, 2625 rpm (260 hp) 
 Propeller and propeller limits See NOTE 6 
 Airspace limits Never exceed 236 mph  (205 knots) 
  Maximum structural cruising 210 mph  (182 knots) 
  Maneuvering 132 mph  (115 knots) 
  Flaps extended 125 mph  (109 knots) 
  Maximum gear retraction speed 125 mph  (109 knots) 
  Maximum gear extension speed 170 mph  (148 knots) 
  Emergency gear extension speed 210 mph  (182 knots) 
  Maximum gear extended speed 210 mph  (182 knots) 
 
 C.G. range (landing gear (+31.5) to (+33.8) in. at 3000 lb. 
   extended) (+24.6) to (+33.8) in. at 2500 lb. 
  (+23.6) to (+33.8) in. at 2207 lb. 
  Straight line variation between points given. 
  Moment change due to retracting landing gear +655 in.-lb. 
 
 Empty Wt. C.G. Range None 
 
 Maximum weight 3000 lbs. 
 
 No. seats 4  (2 at +30, 2 at +70) 
 
 Maximum baggage 200 lbs.  (+100) 
 
 Fuel capacity 80 gal. (two 20 gal. wing tanks, 18,5 gal. usable in each tank, at +22), (two 
  20 gal. auxiliary wing tanks, 18.5 gal. usable in each tank at +41).  See NOTE 1 
  for unusable fuel. 
 
 Oil capacity 3 gal. (-23).  See NOTE 1 for data on system oil. 
 
 Control surface movements Wing flaps   Down 40° 
  Aileron Up 22° Down   9.5° 
  Elevator tab Up   3° Down 13° 
  Elevator Up 32° Down 20° 
  Rudder Right 21° Left 21° 
 
 Serial nos. eligible Model 20B:  264 thru 280 
  Model 20C:  281 thru 289, 291 
 
 
IV. Model 200D, 4 PCLM (Normal Category), approved November 25, 1964 
 
 Engine Continental IO-520-A 
 Fuel 100/130 minimum grade aviation gasoline 
 Engine limits For all operations, 2700 rpm  (285 hp) 
 Propeller and propeller limits See NOTE 6. 
 Airspeed limits Never exceed 236 mph  (205 knots) 
  Maximum structural cruising 210 mph  (182 knots) 
  Maneuvering 132 mph  (115 knots) 
  Flaps extended 125 mph  (109 knots) 
  Maximum gear retraction speed 125 mph  (109 knots) 
  Maximum gear extension speed 170 mph  (148 knots) 
  Emergency gear extension speed 210 mph  (182 knots) 
  Maximum gear extended speed 210 mph  (182 knots)

4 of 8 3A18 Rev 19 
 C.G. range (landing gear (+31.5) to (+33.8) in. at 3000 lb. 
   extended) (+24.6) to (+33.8) in. at 2500 lb. 
  (+23.6) to (+33.8) in. at 2207 lb. 
  Straight line variation between points given. 
  Moment change due to retracting landing gear +655 in.-lb. 
 
 Empty Wt. C.G. Range None 
 Maximum Weight 3000 lb. 
 No. seats 4  (2 at +30, 2 at +70) 
 Maximum baggage 200 lb.  (+100) 
 Fuel capacity 80 gal. (two 20 gal. wing tanks, 18.5 gal. usable in each tank, at +22), (two 
  20-gal. auxiliary wing tanks, 18.5 gal. usable in each tank at +41).  (See N ote 1 
  for unusable fuel. 
 Oil capacity 3 gal. (-23).  See NOTE 1 for data on system oil. 
 
 Control surface movements Wing flaps   Down 40° 
  Aileron Up 22° Down   9.5° 
  Elevator tab Up   3° Down 13° 
  Elevator Up 32° Down 20° 
  Rudder Right 21° Left 21° 
 
 Serial nos. eligible 290, 292 and up 
 
 
V. Model 400, 4 PCLM (Normal Category), approved August 20, 1971 
 Engine Garrett AirResearch TPE 331-1-101J (P/N 896380) 
 Fuel Jet fuel conforming to AirResearch Report PE-5064R (Jet A, A-1, B, JP-1, 
  JP-4, and JP-5)  (See NOTE 4.) 
 Oil MIL-L-23699A (Type II) only, as listed in AirResearch Report No. PE-5065R. 
 
Engine Limits   
Shaft 
Horsepower 
Torque 
Pressure 
(psi) 
 
 
RPM 
 
 
EGT (°C) 
 Takeoff (5 min) 400 40 2000* 578 
 Maximum continuous 400 40** 2000 556 
   *A maximum of 2020 rpm for 5 minutes is allowed. 
 **41.2 psi MCP torque pressure permitted in 96% RPM cruise. 
 
 Propeller and propeller limits a) Hartzell HC-B3TN-5C/T10178H-15 full feathering, reversible, constant speed 
   three-blade propeller. 
   Diameter:  86 inches (no reduction permitted) 
   Feathered +86.5 ±   .5° 
   Flight idle +  6.5 ±   .2° 
   Full reverse +10.5 ± 1.0° 
   Start locks +  2.5 ±   .2° 
  b) Hartzell D3434 spinner assembly 
 
 Airspeed limits Maximum operating speed 240 mph  (208 knots) 
  Maneuvering speed 155 mph  (134 knots) 
  Flaps extended 125 mph  (109 knots) 
  Maximum landing gear 165 mph  (144 knots) 
  Extension/extended 
  Maximum landing gear 132 mph  (115 knots) 
  Retraction speed 
 
 C.G. range (landing gear (+30.5) to (+33.0) in. at 4005 lb. 
   extemded) (+29.1) to (+33.0) in. at 3800 lb. 
  (+27.0) to (+33.0) in. at 2750 lb. 
  Straight line variation between points given.  Moment change due to retracting 
  landing gear +580 in.-lbs.

5 of 8 3A18 Rev 19 
 Empty Wt. C.G. Range None 
 
 Datum Front face firewall 
 
 Leveling means Two external screws on left side of fuselage below the horizontal stabilizer. 
 
 Maximum weights Ramp 4030 lbs. 
  Takeoff 4005 lbs. 
  Landing 3800 lbs. 
  Zero fuel 3200 lbs. 
 
 No. seats 4  (2 at +38, 2 at +70) 
 
 Maximum baggage 200 lbs.  (+100) 
 
 Fuel capacity 155.4 gallons at +35.9 (Two 77.7 gallon tanks, 145 gallons usable).  See NOTE 1 
  for data on system fuel. 
 
 Oil capacity 11.5 qts.  (-40.5)  See NOTE 1 for data on system oil. 
 
 Maximum operating altitude 24,000 feet 
 
 Control surface movements Wing flaps   Down 40°  ±   .5° 
  Aileron Up 22° ± 1.0° Down 9.5° ± 1.0° 
  Elevator tab Up   1° ± 1.0° Down 20°  ± 1.0° 
  Elevator Up 28° ±   .5° Down 20°  ± 1.0° 
  Rudder tab Left 20° ± 1.0° Right 10°  ± 1.0° 
  Rudder Left 15° ± 1.0° Right 35°  ± 1.0° 
 
 Serial nos. eligible 401 and up 
 
Data Pertinent to all Models (except as listed) 
 
 Datum Front face of firewall 
 
 Leveling means Two external screws on left side of fuselage below stabilizer. 
 
 Certification basis: 
   Model 200, 200A, 200B, CAR 3 effective May 15, 1956 through Amendment 3-1 effective April 1, 1957. 
   200C, 200D Type Certificate issued March 6, 1958.  Date of application for Type Certificate  
  April 30, 1957. 
  
   Model 400 CAR 3 effective May 15, 1956 through Amendment 3-1 effective April 1, 1957 and 
  paragraphs 3.197, 3.270,. 3.383, 3.395 and 3.396 of Amendment 3-2 effective 
  August 12, 1957.  Special conditions outlined in Docket 9972 dated November 12, 
  1969.  (See NOTE 7)  Type Certificate 3A18 issued March 6, 1958.  Date of 
  application for original Type Certificate April 30, 1957. 
 
 Production basis None.  Prior to original certification of each aircraft an FAA representative must 
  perform a detailed inspection for workmanship, materials and conformity with 
  approved technical data and a check of flight characteristics. 
 
Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis)  
  must be installed in the aircraft for certification.  In addition, the following items of equipment are required: 
 
  1. Pre-stall warning indicator, Safe Flight Instrument Corp. 1-02-000 (Models 200, 
   200A, 200B, 200C, and 200D)

6 of 8 3A18 Rev 19 
  2. (a) Model 200 FAA Approved Airplane Flight Manual dated March 6, 1958 
   (b) Model 200A FAA Approved Airplane Flight Manual dated June 18, 1959 
   (c) Model 200B FAA Approved Airplane Flight Manual dated March 9, 1961. 
   (d) Model 200C FAA Approved Airplane Flight Manual dated Sept 12, 1963. 
   (e) Model 200D FAA Approved Airplane Flight Manual dated Nov 25, 1964. 
   (f) Model 400 FAA Approved Airplane Flight Manual dated August 11, 1971. 
 
  3. Model 400 
   (a) Stall warning indicator, Interceptor drawing D69B031. 
   (b) See Interceptor Report 60M018 for additional equipment. 
 
NOTE 1. Current weight and balance report with list of equipment included in certificated empty weight, and loading 
  instructions when necessary must be provided for each aircraft at time of original certification.  
 
  Models 200, 200A, 200B, 200C, and 200D:  The certificated empty weight and corresponding center 
  of gravity location must include system oil of 1 lb. at -23, and unusable fuel of 18 lb. at +22, with standard 
  wing tanks.  Include additional unusable fuel at 18 lb. at -41 when auxiliary wing tanks are installe d 
  (Models 200A, 200B, 200C, and 200D). 
 
  Model 400:  The certificated empty weight and corresponding center of gravity location must include  
  system oil of 5.6 lb at -40.5, and unusable fuel of 69.7 lb. at +40.5. 
 
NOTE 2. The following placard must be displayed on the right side of the instrument panel in clear view of the pilot:  
 
  Models 200, 200A, 200B, 200C, 200D:  "THIS AIRPLANE MUST BE OPERATED AS A NORMAL  
  CATEGORY IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF  
  PLACARDS, MARKINGS, AND MANUALS." 
 
  Model 400:  "THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY IN COMPLIANCE WITH 
  THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS AND MANUALS. 
  NO ACROBATIC MANEUVERS INCLUDING SPINS APPROVED.  AIRSPEED LIMITATIONS, MAXIMUM 
  LANDING GEAR RETRACTION SPEED - 115 KTS:  MAXIMUM LANDING GEAR EXTENSION/  
  EXTENDED SPEED - 144 KTS:  MANEUVERING SPEED - 134 KTS." 
  All placards required to the approved airplane flight manual must be installed in the appropriate l ocations. 
 
NOTE 3. Model 400.  The following service life limits must be observed: 
  1. Interceptor Drawing C63R160 Left Pilot's Side window - 1000 hours 
  2. Pressurized Cabin Structure - 2000 hours 
 
NOTE 4. All fuel used in the Model 40 airplane must contain anti-icing additive meeting the requirement of PFA-55MB. 
  Concentration of this additive in the fuel in a loaded fuel tank must not be less than .035% nor more than 
  .15% by volume.  See AFM for blending instructions.  Use of AV-GAS prohibited. 
 
NOTE 5. Continental IO-520-A engine may be installed on the Model 200B when the airplane is modified in accordance  
  with Meyers Aircraft Drawing B60B010, Rev A, dated March 30, 1965.  Model 200B with Conversion #1 FAA 
  Approved Airplane Flight Manual dated March 19, 1965, is required with this modification.  Continental IO-520-A 
  engine may be installed on the Model 200C when the airplane is modified in accordance with Meyers Aircraft  
  Drawing C60B010 dated June 12, 1965.  Model 200C with Conversion #1 FAA Approved Flight Manual dated 
  June 12, 1965, is required with this modification. 
 
NOTE 6. Propellers eligible as shown: 200 200A 200B 200C 200D 
  1. McCauley constant speed 
   Propeller installation 
   (a) McCauley hub 2A3C6C18 with 900M-6 blades   X 
    Pitch settings at 36 in. sta.: 
    Low 10°, high 25° 
    63 lbs.  (-53) 
   (b) Woodward hydraulic governor 210105   X 
      3 lbs.  (-45) 
   (c) McCauley spinner 2A36   X 
      4 lbs.  (-53)

7 of 8 3A18 Rev 19 
NOTE 6. Propellers eligible as shown:   (cont'd) 200 200A 200B 200C 200D 
  2. McCauley constant speed propeller installation 
   (a) McCauley hub B2A36C31 with 90M-6 blades    X   X   X 
    Diameter:  not over 84 in., not under 82 in. 
    Pitch settings at 36 in. sta.:  Low 11°, high 27.5° 
    63 lbs.  (-53) 
   (b) Woodward hydraulic governor 210105 or E210345    X   X   X 
      3 lbs.  (-45) 
   (c) McCauley spinner 2A36    X   X   X 
      4 lbs.  (-53) 
 
  3. McCauley constant speed propeller installation 
   (a) McCauley B2A36C31-A hub with 90M-10 blades     X   X 
    Diameter:  not over 80 in., not under 80 in. 
    Pitch settings at 36 in. sta: 
      Low 11.4°, high 27.5° 
      63 lb.  (-53) 
   (b) Woodward hydraulic governor     X   X 
      210105 or E210345 
        3 lb.  (-45) 
   (c) McCauley spinner 2A36     X   X 
        4 lb.  (-53) 
 
  4. McCauley constant speed propeller installation 
   (a) McCauley D2A36C31-A hub with 90M-10 blades     X   X 
    Diameter:  not over 80 in., not under 80 in. 
    Pitch settings at 36 in. sta.: 
      Low 11.4°, high 27.5° 
      63 lb.  (-53) 
   (b) Woodward hydraulic governor 
    210105 or E2102345     X   X 
        3 lb.  (-45) 
   (c) McCauley spinner D2A36 or McCauley spinner 2A36      X   X 
    with B2792 ring 
        4 lb.  (-53) 
 
  5. McCauley constant speed propeller installation 
   (a) McCauley D2A36C33 hub with 90M-8 blades     X   X   X 
    Diameter:  not over 82 in., not under 80 in. 
    Pitch settings at 36 in. sta.: 
      Low 11.2°, high 27.5° 
   (b) Woodward hydraulic governor 210105 or E210345     X   X   X 
        3 lb.  (-45) 
   (c) McCauley spinner D2A36 or McCauley     X   X   X 
    spinner 2A36 with B2792 ring 
        4 lb.  (-53) 
 
  6. McCauley constant speed propeller installation 
   (a) McCauley D2A36C33 hub with 90M-10 blades     X   X   X 
    Diameter:  not over 80 in., not under 80 in. 
    Pitch settings at 36 in. sta.: 
      Low 11.4°, high 27.5° 
      63 lb.  (-45) 
   (b) Woodward hydraulic governor 210105 or E210345     X   X   X 
        3 lb.  (-45) 
   (c) McCauley spinner D2A36 or McCauley spinner 2A36     X   X   X 
    with B2792 ring 
        4 lb.  (-53)

8 of 8 3A18 Rev 19 
NOTE 6. Propellers eligible as shown  (cont'd): 200 200A 200B 200C 200D 
  7. Hartzell constant speed propeller installation 
   (a) Hartzell HC-82XF-1DB hub with 8433S blades   X 
    Diameter:  not over 84 in., not under 82.5 in. 
    Pitch settings at 30 in. sta.: 
      Low 12°, high 24° 
      64 lb.  (-53) 
   (b) Woodward hydraulic governor 210105   X 
        3 lb.  (-45) 
   (c) Hartzell spinner 835-3   X 
        4 lb.  (-53) 
 
  8. Hartzell constant speed propeller installation 
   (a) Hartzell HC-A2CF-1A(14) hub with 8433-4 or 
    8433R-4 blades    X   X   X 
    Diameter:  not over 80 in., not under 78 in. 
    Pitch settings at 30 in. sta.: 
      Low 14°, high 26.1° 
      64 lb.  (-53) 
   (b) Woodward hydraulic governor 210105 or E210340    X   X   X 
        3 lb.  (-45) 
   (c) Hartzell spinner 835-13    X   X   X 
        4 lb.  (-53) 
 
  9. Hartzell constant speed propeller installation 
   (a) Hartzell HC-82XF-1DB hub with 8433-4 blades     X   X 
    Diameter:  not over 80 in., not under 78 in. 
    Pitch settings at 30 in. sta.: 
      Low 14°  (-53) 
   (b) Woodward hydraulic governor 210105 or E210340     X   X 
        3 lb.  (-45) 
   (c) Hartzell spinner 835-3 or 835-13     X   X 
        4 lb.  (-53) 
 
  10. Hartzell constant speed propeller installation 
   (a) Hartzell HC-C2YF-1A hub with 8468-4 blades       X 
    Diameter:  not over 80 in., not under 80 in. 
    Pitch settings at 30 in. sta.: 
      Low 14°, high 30.5 ± 1.0° 
      51 lb.  (-53 
   (b) Woodward hydraulic governor 210105 or E210345       X 
        3 lb.  (-45) 
   (c) Hartzell spinner 835-22K       X 
        3 lb.  (-53) 
 
  11. McCauley constant speed propeller installation 
   (a) McCauley d2A34C58 hub with 90AT-8 blades     X   X   X 
    Diameter:  not over 82 in., not under 80 in. 
    Pitch settings at 36 in. sta.: 
      Low 10.3 ± 0.5°, high 27.5 ± 0.5° 
      52 lb.  (-53) 
   (b) Woodward hydraulic governor 210105 or E210345     X   X   X 
        3 lb.  (-45) 
   (c) McCauley spinner D-2771     X   X   X 
        4 lb.  (-53) 
 
   Item 11(a), 11(b), and 11(c) are eligible on Models 200B and 200C only when airplane is modified per Note 5.  
 
NOTE 7. The special conditions are only applicable with a 400 hp flat rated engine that is capable of maintaining rated 
  power up to 8000 feet pressure altitude under standard day conditions plus 40°F. 
 
....END....
```

## ADs (5, in force first)

- [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 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 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 67-23-01](https://openairdocs.org/ad/67-23-01): Main Landing Gear · Interceptor 200, 200A, 200B and 2 more. Effective Aug 15, 1967
- [AD 66-28-01](https://openairdocs.org/ad/66-28-01): Elevator Trim System · Interceptor 200, 200A, 200B and 2 more. Effective Nov 19, 1966

## Registered aircraft by registry model (OpenAirDocs)

- [Aero Commander 200D](https://openairdocs.org/model/aero-commander-200d): 54 aircraft (registry code 0140312)
- [Meyers Industries 200B](https://openairdocs.org/model/meyers-industries-200b): 11 aircraft (registry code 5650306)
- [Meyers Industries 200C](https://openairdocs.org/model/meyers-industries-200c): 8 aircraft (registry code 5650308)
- [Meyers Industries 200A](https://openairdocs.org/model/meyers-industries-200a): 5 aircraft (registry code 5650304)
- [Meyers Industries 200D](https://openairdocs.org/model/meyers-industries-200d): 4 aircraft (registry code 5650310)
- [Aero Commander 200](https://openairdocs.org/model/aero-commander-200): 1 aircraft (registry code 0140302)
- [Interceptor 400](https://openairdocs.org/model/interceptor-400): 0 aircraft (registry code 4560404)
- [Meyers Industries 200](https://openairdocs.org/model/meyers-industries-200): 0 aircraft (registry code 5650302)
- [Meyers/Diver 200D](https://openairdocs.org/model/meyers-diver-200d): 0 aircraft (registry code 5650315)

## STCs approved under this data sheet (124, 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 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 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 SA00081NY](https://openairdocs.org/stc/SA00081NY): Installation of Iceman Aviation Supplies, Inc. Carburetor Ice Detector.. 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 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 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 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 SA01967WI](https://openairdocs.org/stc/SA01967WI): Use of GAMI G100UL High Octane Unleaded Avgas. General Aviation Modifications 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 SA09902AC](https://openairdocs.org/stc/SA09902AC): Installation of BendixKing KFD 900 Flight Display System. Honeywell International Inc. (Bendix King)
- [STC SA11174SC PAGE 1](https://openairdocs.org/stc/SA11174SC%20PAGE%201): Installation of BendixKing by Honeywell KSN 770 and KSN 765 WAAS LPV approach capable nav/comm systems. Honeywell International Inc (Bendix King)
- [STC 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 SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation
- [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
- [STC SA04032CH](https://openairdocs.org/stc/SA04032CH): Install rocker switch assemblies. Electroair Acquisition Corporation
- [STC SA00744DE](https://openairdocs.org/stc/SA00744DE): Installation of the Automatic Dependent Surveillance  Broadcast (ADS-B) Out Equipment using a Trig Avionics TT31 Transponder and an approved position sensor. Peregrine
- [STC SA00765DE](https://openairdocs.org/stc/SA00765DE): Installation of Automatic Dependent Surveillance  Broadcast (ADS-B) Out functionality using the BendixKing KT74 Transponder and qualified position sensor. Peregrine
- [STC SA04165NY](https://openairdocs.org/stc/SA04165NY): Installation of Latitude Technologies Skynode S200 Satcom system must be performed. Latitude Technologies Corporation
- [STC SA01435SE](https://openairdocs.org/stc/SA01435SE): Installation of J.P. Instruments (JPI) Primary Engine Data Management System. J. P. Instruments
- [STC SA02153LA-D PAGE 1](https://openairdocs.org/stc/SA02153LA-D%20PAGE%201): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc.
- [STC SA02503AK](https://openairdocs.org/stc/SA02503AK): Installation of AMSAFE State of the Art Restraint System (SOARS) inflatable restraints. AMSAFE Inc.
- [STC SA01835WI](https://openairdocs.org/stc/SA01835WI): Installation of Trig Avionics TY-96 or TY-97 VHF Communications Radio. Peregrine
- [STC SA01933LA-D](https://openairdocs.org/stc/SA01933LA-D): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc
- [STC SA2586NM](https://openairdocs.org/stc/SA2586NM): Installation of J.P. Instruments temperature monitoring systems.. J P Instruments
- [STC SA00382BO](https://openairdocs.org/stc/SA00382BO): Installation of Globalstar Antenna and Cradle provisions to support a Globalstar GPS-1700 in non-composite airplanes. Avidyne Corporation
- [STC SA02428SE](https://openairdocs.org/stc/SA02428SE): Installation of an Air Stream Switch for an electric time recording device on non-pressurized aircraft. Henry F Rogers/David E Polley
- [STC SA00343BO](https://openairdocs.org/stc/SA00343BO): Installation of a single configuration or a dual configuration Avidyne Corporation Integrated Flight Display, Model IFD540 loaded with Release 10.0 software (or later FAA approved release). Avidyne Corporation
- [STC SA00352BO PAGE 1](https://openairdocs.org/stc/SA00352BO%20PAGE%201): Installation of an Avidyne Corporation Mode A/C/S Transponder with ADS-B Out capability, Model AXP340 loaded with Version 3.13 software (or later FAA approved version),. Avidyne Corporation
- [STC SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc
- [STC SA01969SE](https://openairdocs.org/stc/SA01969SE): Installation of a Mid-Continent MD302 Standby Attitude Module. Mid-Continent Instruments and Avionics
- [STC SA01229SE PAGE 1](https://openairdocs.org/stc/SA01229SE%20PAGE%201): Installation of GNS 480 (CNX80) GPS WAAS Navigator with integrated VHF Navigation and Communication radios. Garmin International Inc
- [STC SA02442AK PAGE 1](https://openairdocs.org/stc/SA02442AK%20PAGE%201): Approval of the L-3 Communications NGT 2000/2500 ADS-B system. ADS-B Technologies, LLC
- [STC SA01933LA-D PAGE 1](https://openairdocs.org/stc/SA01933LA-D%20PAGE%201): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation
System. Garmin International Inc
- [STC SA10682SC](https://openairdocs.org/stc/SA10682SC): Installation of alternator and voltage regulator. Hartzell Engine Technologies, LLC

All 124: https://openairdocs.org/tcds/3A18/stcs.md

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