# TCDS A-2-575: The Boeing Company - Type: Type certificate data sheet - Status: Current - Holder: The Boeing Company - Revision: 16 - Revised: November 16, 2009 - Product: Aircraft, Small Airplane - Certification basis: CAR 4a - Registered aircraft: 336, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/b9/ee/b9ee05e4f893afcf8090e4b1b59456141895f29a0d4bfc3aca626c0bbd311393 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/2F7B28DCF1FB0B01862576AC0054A227.0001 - Page: https://openairdocs.org/tcds/A-2-575 ## Models (9) As the data sheet lists them. - SNJ-7 - AT-6F (SNJ-6) - AT-6D (SNJ-5) - AT-6A (SNJ-3) - BC-1A - AT-6C (SNJ-4) - AT-6 (SNJ-2) - AT-6B - T-6G ## 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 Rev. No. 16 16 12 12 12 12 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-2-575 Revision 16 BOEING (NORTH AMERICAN) BC-1A AT-6 (SNJ-2) AT-6A (SNJ-3) AT-6B AT-6C (SNJ-4) AT-6D (SNJ-5) AT-6F (SNJ-6) SNJ-7 T-6G November 16, 2009 AIRCRAFT SPECIFICATION NO. A-2-575 Aircraft Specification Holder The Boeing Company 4000 Lakewood Blvd. Long Beach, California 90846 Aircraft Specification Holder Rockwell International tran sferred ownership to The Boeing Company on July 23, 2009 Record North American Aviation transferred ownership to Rockwell International Corp. on February 20, 1996 I - Model BC-1A, AT-6 (Navy SNJ-2), 2 PCLM, Approved November 6, 1946 Engine Pratt & Whitney Military model R-1340-47, R-1340-49, R-1340-AN-1 or R-1340-36 Fuel 87 min. grade aviation gasoline Engine limits Maximum continuous, (Sea level) 34.0 in.Hg., 2200 rpm (550 hp) (5000 ft.) 32.5 in.Hg., 2200 rpm (550 hp) Takeoff (one minute), 36.0 in.Hg., 2250 rpm (600 hp) Airspeed limits Level flight or climb 189 mph (164 knots) True Ind. Glide or dive 226 mph (197 knots) True Ind. Flaps extended 111 mph ( 97 knots) True Ind. C.G. range (+27.3) to (+31.2) with landing gear extended. Empty weight C.G. range None Maximum weight 5340 lbs. (See NOTE 3 for crop dusters) No. seats 2 (+45 and +97) (See Items 408 and 409 for 3 or 4-place) Maximum baggage 100 lbs. (+126) Fuel capacity 170 gals. (+37) (One integral ta nk in wing center section with dividing partition) Oil capacity 15.5 gals. (-8) Control surface movements Wing flaps Down 41° Elevators Up 30° Down 20° Elevator trim tabs Up 6° Down 17° Ailerons Up 30° Down 16° Aileron balance tabs Up 13° Down 27° Rudder Right 35° Left 35° Rudder trim tab Right 4° Left 10° Note: Aileron balance tabs may be used in fixed positions as trim tabs. When rudder and aileron control systems are modified pr North American Dwg. 88-05016, pertinent control surface movements are as follows: Ailerons Up 14° Down 16° Rudder Left 30° Right 30° Serial Nos. eligible All manufacturer's seri al Nos. 55-1548 through 55-1630, 59-1631 through 59-1639, 59- 1906 through 59-1990, 65-1997 through 65-2032, 79-3983 through 79-4007. Harvard I aircraft manufactured in the United States: Manufacturer's serial Nos. 49-748 through 49- 947, 49-1053 through 49-1252 (See NOTE 4). Required equipment In addition to the pertinent require d basic equipment specified in CAR 4a, the following items of equipment must be installed: Items 1, 2, 101, 103, 104, 105, 109, 111, 201(a) or (b), 202(a) or (b), 203(a) or (b), 301(a), 405(a), (b) or (c), 406(a) or (b), 407, 602. Aluminum alloy outer wing panels and aft fuselage section are required. II - Model AT-6A (Navy SNJ-3), AT-6B, AT-6C (Navy SNJ-4), AT-6D (Navy SNJ-5), AT-6F (Navy SNJ-6), Navy SNJ-7, T-6G; 2 PCLM, Approved February 1, 1946 Engine Pratt & Whitney Military model R-1340-47, R-1340-49, R-1340-AN-1 or R-1340-36 Fuel 87 min. grade aviation gasoline Engine limits Maximum continuous, (Sea level) 34.0 in.Hg., 2200 rpm (550 hp) (5000 ft.) 32.5 in.Hg., 2200 rpm (550 hp) Takeoff (one minute), 36.0 in.Hg., 2250 rpm (600 hp) Airspeed limits Level flight or c limb 189 mph (164 knots) True Ind. Glide or dive 226 mph (197 knots) True Ind. Flaps extended 115 mph ( 97 knots) True Ind. C.G. range (+27.5) to (+32.5) with landing gear extended. Empty weight C.G. range None Maximum weight 5300 lbs. No. seats 2 (+45 and +97) (See Items 408 and 409 for 3 or 4-place) Maximum baggage 100 lbs. (+126) Fuel capacity 111 gals. (+36) (Two 55.5 gal. tanks in wing center section) (20 gal. reserve included in 55.5 gal. capacity of left tank) Note: In addition to the above, Models T- 6G incorporate an additional 29 gals. (+50). (Two internal bladder cells in outer wing panel, 14.5 gals. each side). Oil capacity 10 gals. (-9) Control surface movements Wing flaps Down 45° Elevators Up 30° Down 20° Elevator trim tabs Up 8° Down 16° Ailerons Up 29° Down 16° Aileron balance tabs Up 15° Down 30° Rudder Right 35° Left 35° Rudder trim tab Right 4° Left 10° Note: Aileron balance tabs may be used in fixed positions as trim tabs. On some of the models AT-6C and on all of the models AT-6D, AT-6F and T-6G the rudder and aileron control systems have been modi fied per North American Dwg. 88-05016. The pertinent control surface movements for these aircraft are as follows: Ailerons Up 14° Down 16° Rudder Right 30° Left 30° Serial Nos. eligible All serial numbe rs of aircraft models covered by this section. (Manufacturer's serial number will be found stamped on same identification plate with the military serial number.) Harvard II aircraft manufactured in the United States: Manufacturer's serial Nos. 66-2234 through 66-2833, 75-3048 through 75-3057, 75-3418 through 75-3507, 76-3508 through 76-3957, 81-4008 through 81-4132. (See NOTE 4). Required equipment In addition to the pertinent require d basic equipment specified in CAR 4a, the following items of equipment must be installed: 3 A-2-575 Items 1, 2, 101, 103, 104, 105, 109, 111, 201(a) or (b), 202(a) or (b), 203(a) or (b), 301(a), 405(a), (b) or (c), 406(a) or (b), 407, 602. Aluminum alloy outer wing panels and aft fuselage section are required. SPECIFICATIONS PERTINENT TO ALL MODELS Datum Leading edge of wing center section Leveling means Lugs left side rear cockpit Certification basis Airworthin ess Certificate only (CAR 4a) Export eligibility Eligible for export to all countries subject to the provisions of MOP 2-4 except as follows: (Note: Export license from St ate Department may be required) Canada - Landplane, eligible Skiplane, not eligible Equipment: A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. Propeller and Propeller Accessories 1. Propeller - Hamilton Standard, constant speed hub 12D40, 175 lbs. (-57) blades 6101-12 to -14, incl. Dia.: Max. 9'1", Min. allowable for repairs 8'10-5/8". No further reduction permitted. Pitch settings at 42 in. sta.: 11.5° low, 27° high Following placard required: (With blade models 6101-12 and -13), "Avoid ground operation between 1280 and 1800 RPM unless the aircraft is headed into the wind." (With blade model 6101-14), "Avoid ground operation between 1450 and 1800 RPM unless the aircraft is headed into the wind." 2. Constant speed governor, Ham. St d. 1M12-A, -G, or 1P12-A 5 lbs. (-50) 3. Propeller spinner (Montgomery) Part No. 42J15621 for 12 lbs. (-57) Hamilton Standard propeller Engine and Engine Accessories - Fuel and Oil System 101. Carburetor air heater 102. Air filter, Air Maze 3 lbs. (-23) 103. Engine-driven fuel pump (Army Type B-21 or F-10) 1 lb. (-30) 104. Wobble pump and strainer (Army Type D-3) 12 lbs. (+16) 105. Oil temperature regulator (8 " dia. radiator) 21 lbs. ( -9) 106. Oil dilution system 3 lbs. ( +2) 107. Exhaust gas analyzer 5 lbs. (+20) 108. Engine-driven vacuum pump (P esco Type B-12) 6 lbs. (-26) 109. Engine-driven hydraulic pump (Pesco 1P-263-E) 110. Starter (a) 12 volt (Eclipse type C-20 or H-2) 33 lbs. (-19) 111. Cylinder head temperature gages (See NOTE 2(k) for markings) Landing Gear and Floats 201. Main wheels, tires and tubes (a) 27" smooth contour wheels and br akes (AC-25258 or Hayes 131 lbs. (+10) Model 2750A) with 6-ply tires (b) 27" smooth contour wheels and brakes (AN-W-6 or Hayes 136 lbs. (+10) Model 2750A) with 8-ply tires 202. Tail wheel, tire and tube (a) 10" smooth contour wheel with 6-ply tire 6 lbs. (+234) (b) 12.5" smooth contour wheel with 6-ply tire 10 lbs. (+234) 203. Tail wheel gear (less wheel, tire and tube) (a) Steerable 26 lbs. (+230) (b) Free swivel with lock 26 lbs. (+230) Electrical Equipment (24 volt electrical system may be substituted for 12 volt system per North American Dwg. 121-954004) 301. Battery and case (a) 12 volt - 68 amp. hr. (5 hr. rate) (Exide 6-TAS-17) 71 lbs. ( -1) 302. Generator (a) 12 volt - 50 amp. (Leece-Neville E-5A) 32 lbs. (-26) 303. Landing lights 3 lbs. (+21) 304. Radio installations (a) Antenna and mast 7 lbs. (+29) (b) Marker beacon receiver and antenna 5 lbs. (+63) (c) Radio compass and loop 42 lbs. (+14) 305. Interphone 10 lbs. (+62) 306. Electric heated pitot 1 lb. ( +7) Interior Equipment 401. Fire extinguisher and bracket 7 lbs. (+101) 402. Cabin heater and ventilator 17 lbs. (-18) 403. Oxygen system (a) High pressure 30 lbs. (+136) (b) Low pressure 29 lbs. (+116) 404. Provisions for 90 lbs. of phot ographic equipment at (+113) 405. Front seat (a) Dural 8 lbs. (+52) (b) Wood 12 lbs. (+52) (c) Magnesium (Warren McArthur or Shick-Johnson) 8 lbs. (+52) 406. Rear seat (a) Swivel type 28 lbs. (+101) (b) Dural 8 lbs. (+101) 407. Safety belts, A-3,B-11, B-12, or B14 408. Two-place rear seat installation (Vent Aircra ft & Finance Co., 4600 Dehlia St., Hayden Field, Denver, Colo.) Seat kits to be installed in accordance with the manufacturer's installation instructions dated October 9, 1946. 409. "Air Tandem" Three passenger seat kit (Ralph R. Richardson, Route 1, Box 303, Port Orchard, Washington). Installation must be made per manufacturer's dwgs. and instructions as listed in Detail Folder No. RC-2 consisting of Pages 1, 1a, 1b, 2 thru 9 and three pages of Installation Instructions. Miscellaneous (Not listed above) 601. Blind flying hood 4 lbs. (+105) 602. Control surface tabs, dural or wood 603. Mooring kit 11 lbs. (+140) 604. Engine cover 15 lbs. (+140) 605 Wood horizontal stabilizer -3 lbs. (+222) NOTE 1. Current weight and balance report including list of equipment included in certificated empty weight must be in each aircraft at the time of original certification a nd at all times thereafter. If removable ballast is used to stay within the specified fo rward limit, the following placard must be installed on instrument panel and baggage compartment: "When flown solo lbs. of baggage or equivalent must be carried in baggage compartment." NOTE 2. The following must be accomplished prio r to original certification of the aircraft: (a) Aircraft must have aluminum alloy wing outer panels and fuselage aft sections. (b) Placard rear cockpit, "Solo Flying From Front Seat Only." (c) Placard both cockpits, "Intentional Spinning Prohib ited" and "Caution: Unless Left Tank is Full, use reserve or Right Tank for Take-off and Landing." (d) Placard baggage compartment: "Maximum Capacity 100 lbs. With Both Seats Occupied lbs. Maximum" The latter weight to be determined per NOTE 1, the limiting factor being the rearward center of gravity. (e) Mark fuel tank filler caps, "Fuel capacity gal., 87 min. oct." (f) Mark oil tank filler cap, "Oil capacity gal." (g) Mark instruments for approved operating limits. (h) Provide oil measuring stick for oil tank. 5 A-2-575 (i) For day operation, electrical protective devices in ci rcuits to all equipment used in such operation should be accessible to the pilot in flight. The airp lane should then be restricted to day operation. (j) In order for these aircraft to be eligible for ni ght operation, it will be necessary that the following changes b e m a d e : 1. Remove the present red and green wing position light s and cover the mounting holes with aluminum alloy plates. Install Grimes Model E wing-tip position li ghts and connect them into the present position light junction boxes located near the wing tips. Also rem ove the present two rear position lights from the fin and replace them with either Grimes lights No. A- 4060 or Grimes lights A-2063 modified specifically by Grimes for use on these airplane s. Either type of lights should have 15 candlepower lamps installed. 2. Remove position light resi stors and eliminate the work "Dim" at the position light switch. 3. Relocate all electrical circuit protectors so that they are accessible to the pilot in flight. (k) The cylinder head temperature gauge be marked to indicate a limiting temperature of 500°F. (l) On models BC-1A, AT-6 and SNJ-2 only, inspect fuel tank to determine whether gasoline can flow from one compartment into the other. If so, the followi ng placard should be placed adjacent to the fuel selector valve: "Refer to both fuel gauges to determine remaining fuel." (m) Add the following information to the engine nameplate: "C.A.A. Spec. No.5E-2." (n) Fixed ballast not to exceed 33 lbs. may be insta lled at Station 240 to prevent exceeding the forward center of gravity limit. Ballast weight installation must be approved and is to be placarded, "Removal requires weight and balance check." (o) On Model T-6G determine that the cente r wing flap is in the operative configuration. NOTE 3. Model AT-6 series aircraft certificated in the re stricted category prior to October 11, 1950 for crop dusting may continue to be operated with the following limitations: A T - 6 AT-6A, 6B, 6C (a) Maximum takeoff weight 5870 lbs. 5830 lbs. Maximum landing we ight 5340 lbs. 5300 lbs. Maneuvering speed at maxi mum weight 151 mph 151 mph (b) The following placard must be in full view of the pilot: "Maneuvering speed at maximum weight not to exceed 151 mph." Each aircraft certificated on the above basis must be s ubjected to a flight test to determine that the installed duster apparatus has no adverse effect on the flight ch aracteristics of the aircraft. In the case of identical duster installations in aircraft of the same model, the flight test need only be made to the prototype. All original certification in the restricted category after October 11, 1950 must be in accordance with CAR and C A M 8 . NOTE 4. Prior to civil certification, it must be ascertained that Harvard aircraft manufactured in the United States conform to the type design. Some of the known devi ations from the original configuration are discussed as follows: (a) The mixture control must be reworked to standa rd American system, that is "lean-aft, Rich-forward". A conversion to exact AT-6 system would be accepta ble. Any other system would have to be evaluated. (b) The long exhaust stack configurati on should be modified to the AT-6 system. Utilization of winterized stack w ould require evaluation with respect to: (1) Carbon monoxide content in the cockpit from bot h the fresh air system, heat exchanger within the stack and the stack proper. (2) Detrimental temperature effects on the fuselage sk in due to the proximity of the stack to the fuselage as well as possible adverse exhaust back pressure. (3) Determination that system was United States manufactured inasmuch as a foreign built unit would not be eligible for approval. (c) The use of Pratt & Whitney S3H1 engine is acceptable with Item 1 propeller. (d) The acceptability of engine accessories must be determined. In this regard, Technical Order 00-25-29 "Maintenance Interchangeability Cross Re ference Charts" may be utilized as a guide. (e) The use of a foreign manufactured landing gear is not considered acceptable, and therefore must be replaced by an acceptable gear manufactured in the United States. (f) The landing gear fairing and associated attachment hardware must be installed. (g) The forward control stick has a four inch hand grip which differs from the standard straight stick installation. If clearance from the structure a ppears adequate this may be considered acceptable. (h) Electrical system deviations from the approved type design data must be appropr iately changed and adjusted satisfactorily. (i) Airspeed flap speed and cylinder head gage lim its must be incorporated as in the AT-6 aircraft. Other existing difference must be satisfactorily re solved with the local FAA Engineering Office prior to certification. ......END...... ``` ## ADs (11, in force first) - [AD 2023-10-02](https://openairdocs.org/ad/2023-10-02): Indicating/Recording System, Navigation · Boeing 18, 23, 35 and 1,060 more. Effective May 26, 2023 - [AD 2011-12-01](https://openairdocs.org/ad/2011-12-01): Equipment/Furnishings · Airbus A300 B2-1A, A300 B2-1C, A300 B2-203 and 268 more. Effective Aug 1, 2011 - [AD 2005-12-51](https://openairdocs.org/ad/2005-12-51): Upper and lower wing attach angle · Autair Harvard AT-16 (Army), AT-6 (SNJ-2), AT-6A (SNJ-3) and 7 more. Effective Jun 23, 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 81-14-10](https://openairdocs.org/ad/81-14-10): Vertical and Horizontal Stabilizers · Boeing AT-6D (SNJ-5), AT-6F (SNJ-6), SNJ-7 and 1 more. Effective Jul 13, 1981 - [AD 46-11-01](https://openairdocs.org/ad/46-11-01): Landing Gear Retracting Strut · Boeing AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B and 2 more - [AD 46-17-01](https://openairdocs.org/ad/46-17-01): Flap Control Universal Joint Pins · Boeing AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B and 2 more - [AD 46-46-02](https://openairdocs.org/ad/46-46-02): Elevator Stop · Boeing AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B and 2 more - [AD 49-07-02](https://openairdocs.org/ad/49-07-02): Fuel System Placard · Boeing AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B and 2 more - [AD 50-09-01](https://openairdocs.org/ad/50-09-01): Stabilizer Spar Fittings and Shims · Boeing AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B and 2 more - [AD 50-38-01](https://openairdocs.org/ad/50-38-01): Fuselage Structure Corrosion · Boeing AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B and 3 more ## Registered aircraft by registry model (OpenAirDocs) - [North American T-6G](https://openairdocs.org/model/north-american-t-6g): 104 aircraft (registry codes 6400432, 05629FV) - [North American AT-6D](https://openairdocs.org/model/north-american-at-6d): 87 aircraft (registry code 6400416) - [North American AT-6C](https://openairdocs.org/model/north-american-at-6c): 43 aircraft (registry codes 6400412, 6400398) - [North American AT-6](https://openairdocs.org/model/north-american-at-6): 28 aircraft (registry code 6400402) - [North American AT-6F](https://openairdocs.org/model/north-american-at-6f): 22 aircraft (registry code 6400420) - [North American/Victoria MNT LT AT-6A](https://openairdocs.org/model/north-american-victoria-mnt-lt-at-6a): 20 aircraft (registry codes 6400406, 6400461) - [North American AT-6A](https://openairdocs.org/model/north-american-at-6a): 5 aircraft (registry code 6400469) - [North American Medore T-6G](https://openairdocs.org/model/north-american-medore-t-6g): 5 aircraft (registry code 6400433) - [North American AT-6B](https://openairdocs.org/model/north-american-at-6b): 3 aircraft (registry code 6400410) - [North American AT-6C(SNJ-4)](https://openairdocs.org/model/north-american-at-6c-snj-4): 3 aircraft (registry code 6400449) - [North American SNJ-7](https://openairdocs.org/model/north-american-snj-7): 2 aircraft (registry code 6400424) - [North American-Buehn T-6G](https://openairdocs.org/model/north-american-buehn-t-6g): 2 aircraft (registry code 6400438) - [North American-Kalashian T-6G](https://openairdocs.org/model/north-american-kalashian-t-6g): 2 aircraft (registry code 6400436) - [North American / Crosser G AT6A](https://openairdocs.org/model/north-american-crosser-g-at6a): 1 aircraft (registry code 6400470) - [North American-Collins AT-6A](https://openairdocs.org/model/north-american-collins-at-6a): 1 aircraft (registry code 6400405) - [North American/Case M V JR AT-6](https://openairdocs.org/model/north-american-case-m-v-jr-at-6): 1 aircraft (registry code 6400473) - [North American/Levrett AT6-C](https://openairdocs.org/model/north-american-levrett-at6-c): 1 aircraft (registry code 6400472) - [North American/Medore ART NA AT6-F](https://openairdocs.org/model/north-american-medore-art-na-at6-f): 1 aircraft (registry code 6400451) - [North American/Medore Arthur AT6-D](https://openairdocs.org/model/north-american-medore-arthur-at6-d): 1 aircraft (registry code 6400450) - [North American/Sawyer NORTH AMER AT-6D](https://openairdocs.org/model/north-american-sawyer-north-amer-at-6d): 1 aircraft (registry code 6400500) - [North American/Schwamm AT-6F](https://openairdocs.org/model/north-american-schwamm-at-6f): 1 aircraft (registry code 6400425) - [North American/Walbrun T6-G](https://openairdocs.org/model/north-american-walbrun-t6-g): 1 aircraft (registry code 6400445) - [North American/Walker/Screws AT6C](https://openairdocs.org/model/north-american-walker-screws-at6c): 1 aircraft (registry code 640041B) - [North American BC1A](https://openairdocs.org/model/north-american-bc1a): 0 aircraft (registry code 6401002) - [North American-Mckee AT-6A](https://openairdocs.org/model/north-american-mckee-at-6a): 0 aircraft (registry code 6400409) - [North American/Buehn AT-6A](https://openairdocs.org/model/north-american-buehn-at-6a): 0 aircraft (registry code 6400462) - [North American/Buehn AT-6C](https://openairdocs.org/model/north-american-buehn-at-6c): 0 aircraft (registry code 6400463) - [North American/Courtesy A/C T6G](https://openairdocs.org/model/north-american-courtesy-a-c-t6g): 0 aircraft (registry code 6400440) - [North American/Reynolds AT-6D](https://openairdocs.org/model/north-american-reynolds-at-6d): 0 aircraft (registry code 6400428) - [North American/Schmieder AT-6](https://openairdocs.org/model/north-american-schmieder-at-6): 0 aircraft (registry code 6400403) ## STCs approved under this data sheet (116, 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).. 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Aircraft Design & Certification Ltd - [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 SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber Inc. - [STC SA02658SE](https://openairdocs.org/stc/SA02658SE): Installation of Garmin GI 275 Multi-Function Display System. Garmin International Inc. - [STC SA01899WI](https://openairdocs.org/stc/SA01899WI): Installation of Garmin G3X Touch Electronic Flight Instrument System. Garmin International Inc. - [STC SA04776NY](https://openairdocs.org/stc/SA04776NY): The HIPEC Covering and Finishing System must be performed and maintained. HIPEC Aircraft Coatings 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 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 SA02430SE](https://openairdocs.org/stc/SA02430SE): Fabrication and 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 SA00410BO](https://openairdocs.org/stc/SA00410BO): Installation of an AV-30-C Multi-Mode Indicator. uAvionix Corporation - [STC SA02268CH](https://openairdocs.org/stc/SA02268CH): Installation of Airwolf Filter Corp. Air Oil Separator. Airwolf Filter Corporation - [STC SA5190NM](https://openairdocs.org/stc/SA5190NM): Installation of Gustin Aviation chip detector light system.. A & L Aircraft Parts 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 SA04362CH](https://openairdocs.org/stc/SA04362CH): Installation of the uAvionix skyBeacon Automatic Dependent Surveillance-Broadcast (ADS-B) Out. uAvionix 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 SA708GL](https://openairdocs.org/stc/SA708GL): To install model 300 scavenge oil filter system with Pratt & Whitney R-1340 engine.. Airwolf Filter Corp - [STC SA6070NM](https://openairdocs.org/stc/SA6070NM): Installation of a 'quick-disconnect drain plug' on the engine rocker sump for the oil drain retrieval system after engine shutdown.. West Coast Air Creations - [STC SA01282NY](https://openairdocs.org/stc/SA01282NY): Installation of Airwolf remote mounted engine oil filter kit AFC-K015 on aircraft powered by Pratt & Whitney radial reciprocating engine Series R-985, R-1340 and R-1830.. Airwolf Filter Corporation - [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 SA01734SE](https://openairdocs.org/stc/SA01734SE): Application of Stewart Systems synthetic fabric covering system to aircraft fuselage, wings, tail surfaces, control surfaces and related parts.. Andrew D. Humphrey - [STC SA11172SC](https://openairdocs.org/stc/SA11172SC): Installation of an ADS600-B Automatic Dependent Surveillance-Broadcast (ADS-B) Universal Access Transceiver (UAT) and Global Positioning System (GPS) antenna. NavWorx Inc - [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 SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems Inc. - [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 2](https://openairdocs.org/stc/SA01933LA-D%20PAGE%202): Installation of Garmin Model 400W / 500W Series GPS-WAAS Navigation System. Garmin International Inc - [STC SA02930NY](https://openairdocs.org/stc/SA02930NY): Installation of Insight Instrument Corporation Graphic Engine Monitor (GEM 610C) models G3, G2, and G1 and 1200C model G4 as primary Cylinder Head Temperature (CHT), Exhaust Gas Temperature (EGT), and Turbine Inlet Temperature (TIT) Instruments. Insight Instrument Corporation - [STC SA02283SE PAGE 1](https://openairdocs.org/stc/SA02283SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In Flight Data) CGR-30P. Electronics International Inc. - [STC SA02402SE PAGE 1](https://openairdocs.org/stc/SA02402SE%20PAGE%201): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) CGR-30C. Electronics International Inc. All 116: https://openairdocs.org/tcds/A-2-575/stcs.md --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.