# TCDS A-722: Cessna Aircraft Company - Type: Type certificate data sheet - Status: Current - Holder: Cessna Aircraft Company - Revision: 8 - Revised: March 10, 1954 - Product: Aircraft, Small Airplane - Registered aircraft: 37, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/3f/87/3f87e9a0f0c82b15fa7373ce06226bc7c1e529e27a4077d9b44e2b255c202560 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/65DEA925DDA108B08625724300680BDF.0001 - Page: https://openairdocs.org/tcds/A-722 ## Models (1) As the data sheet lists them. - T-50 (Army AT-17 and UC-78 series; Navy JRC-1) ## 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. 8 8 8 8 8 8 DEPARTMENT OF COMMERCE CIVIL AERONAUTICS ADMINISTRATION A-722 Revision 8 CESSNA T-50 (Army AT-17) and UC-78 series and Navy JRC-1) March 10, 1954 AIRCRAFT SPECIFICATION NO. A-722 Manufacturer Cessna Aircraft Company Wichita, Kansas I - Model T-50 (Army AT-17 and UC-78 series, Navy JRC-1), 5 PCLM, Approved March 24, 1940. See NOTE 2 for modifications required for conversion of military models. Engines 2 Jacobs L-4MB. (See Items 226 and 228 for optional engines) Fuel 73 min. octane aviation gasoline Engine limits Maximum continuous, 2000 rpm (225 hp) Take-off (one minute), 2200 rpm (245 hp) Airspeed limits For 5,100 lbs. maximum weight - Level flight or climb 175 mph (152 knots) True Ind. Glide or dive 200 mph (174 knots) True Ind. Flaps extended 108 mph ( 94 knots) True Ind. For 5,400 lb. and 5,700 lb. maximum weight - Level flight or climb 168 mph (146 knots) True Ind. Glide or dive 200 mph (174 knots) True Ind. Flaps extended 112 mph ( 97 knots) True Ind. Usable ceiling (May be realized under conditions shown) (With 5,100 lb. weight) Ceiling Weight RPM Manifold T.I.A.S. Idling Propeller (ft.) (lb.) Pressure (mph) (knots) Propeller Installed 4,000 5,100 2,000 Full throttle 84 73 High pitch 680 rpm Item 102 900 5,100 1,930 Full throttle 87 76 470 RPM Item 208 Operating conditions: (1) Standard air (2) Either engine inoperative (3) Carburetor air intake on "cold air" (4) No de-icers Usable ceiling for 5,400 lb. and 5,700 lb. included in pertinent CAA Approved Operating Manual. C.G. range (landing (-4.8) to (+3.1) with unbalanced elevator (Item 601) gear extended) (-4.6) to (+3.5) with balanced elevator (Item 602) Maximum weight For Model T-50: With Item 603 installed - 5,100 lb. With Items 209 and 604 installed - 5,400 lb. (Passenger) With Items 209 and 604 installed - 5,700 lb. (Cargo only) With Items 209, 602, 604 and 605 installed - 5,700 lb. (Passenger or Cargo) For Army AT-17 and UC-78 and Navy JRC-1: With Item 603 installed - 5,100 lb. With Item 604 installed - 5,400 lb. (Passenger) With Item 604 installed - 5,700 lb. (Cargo only) With Items 602, 604 and 605 installed - 5,700 lb. (Passenger or Cargo) A-722 2 No. seats 5 (two front at -14, three rear at +36) Maximum baggage 350 lbs. (300 lbs. aft of cabin at +65: 50 lbs. on cabin baggage shelf at +65) Fuel capacity 120 gals. (two 60 gal. wing tanks at +21.5). See Item 207 for auxiliary fuel tank. Oil capacity 10 gal. (two nacelle tanks, 5 gal. each) (-34) ((-27) when Item 209 is installed) Control surface movements Elevator 25° up 25° down Elevator tab 5° up 18° down Aileron 25° up 25° down Rudder 25° right 25° left Rudder tab 25° right 25° left Wing flaps 35° or 40° down (See Item 605 for ` increased travel) Serial Nos. eligible 1000 to 1029, 1100 and up and all AAF and Navy numbers. Use manufacturer's number if available. See NOTE 2 for required modifications for conversion of military models. Required equipment Items 101; 102; 103; 104; 105; 106(a) or (b); 107(a) or (b); 108; 109; 110; 111; 112; 113; 114; 115(a) or (b); 117; 118; 119; 401 (when maximum weight exceeds 5,100 lb.); 601 or 602, and 603 or 604. SPECIFICATIONS PERTINENT TO ALL MODELS Datum Centerline of top of front spar. Datum is marked on fuselage front spar fitting, at bottom of spar Leveling means Lugs located on left side of baggage compartment Certification basis Type Certificate No. 722 (CAR 4a) Production basis None. Prior to original certification a CAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data, and a check of the flight characteristics. Export eligibility Eligible for export to all countries, subject to the provisions of ASR 312 (MOP 2-4 contains the same information) except as follows: (a) Canada - Landplane - eligible - Skiplane - not eligible (b) Great Britain and Australia - Serial Nos. 1001 to 1029, 1100 and up Equipment: A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. Approval for the installation of all items of equipment listed herein has been obtained by the aircraft manufacturer except those preceded by an asterisk (*). The asterisk denotes that approval has been obtained by other than the aircraft manufacturer. Propellers and Propeller Accessories 103. Two propellers controllable metal (Ham. Std. hubs 2B20, 208 lb. (-75) blades 6135A-15 or 6135A-16. Dia. 7'9-1/8" max., 7'6-7/8" min. For interchangeable blade models see Propeller Specification No. 255 (NOTE 6). Low pitch setting 12° or 13°, high pitch setting 27° or 28°.) 104. Two constant speed propeller controls - Hamilton Standard 1A4-G5 8 lb. (-43) 121. Two Montgomery Spinners for Hamilton Standard 2B20 Propeller 15 lb. (-75) 208. Two propellers (incl. hub) - any fixed pitch wood which is eligible -132 lb. (-75) for the engine power and speed and which meets the following limits: Static r.p.m. at maximum permissible throttle setting: Not over 1950, not under 1810. No additional tolerance permitted. Diameter: Not over 97 in., not under 87 in. for T-50 Diameter: not over 93 in., not under 87 in. for AT-17 and UC-78 (Note S & S propeller 210E, 93 in. dia., 76 in. pitch, meets the above limits and is eligible.) 3 A-722 Engines and Engine Accessories - Fuel and Oil System 101. Two engine cowls (NACA type with baffles and inner cowl) 72 lb. (-55) 102. Two exhaust collector rings 22 lb. (-51) 105. Two starters (Eclipse E-80 or J-1) 39 lb. (-42) 115. Fuel pumps - engine-driven: (a) (1) Two Pesco M400 (may be replaced by Items 120 or 223) 1.5 lb. ea. (-38) and (2) Either two Pesco R-400BLH or 2P-R400BLYA 2.5 lb. ea. (-45) or (b) Four Pesco R-400BLH or 2P-R400BLYA 2.5 lb. ea. (-45) 116. Engine shielding (both engines) 20 lb. (-59) 117. Two oil strainer (Jacobs) 2 lb. ea. (-41) 118. Two carburetor air scoop assemblies 4 lb. ea. (-51) 119. Two carburetor air heaters 6 lb. ea. (-51) 120. One AN-4009 wobble pump (replaces two Pesco M400 pumps in Item 115(a)) 3 lb. (-14) Item 115(a)) 205. Vacuum pumps and optional oil separator: (a) Pesco 194-B or Romec RD4500 4 lb. (-45) (b) Pesco B-2A 4 lb. (-38) 206. Cabin heater with: (a) Muff on only one engine 5 lb. (-32) (b) Muff on both engines 10 lb. (-32) 207. Auxiliary fuel tank: (a) 39 gal. 25 lb. (+34) (b) 30 gal. 20 lb. (+34) 209. Revised engine mounts, nacelles and landing gears - 5 lb. (-20) (Dwgs. 51215, 51067 and 51102, and 51174 respectively) 212. Two oil dilution installations 2 lb. (-34) 213. Two oil heater muff system installations 5 lb. (-36) 214. Lux twin engine fire extinguisher system 24 lb. (0) 219. Two oil hopper tank installations 4 lb. (-27) 220. Two oil radiator installations forward of firewall 19 lb. (-35) 221. Two air mazes (Carburetor intake) 5 lb. (-69) 223. Romec F4B fuel pump (Each Romec F4B pump may replace one No weight change Pesco M400 in Item 115(a)) 225. Mixture analyzer: (a) Indicator 2 lb. (-37) (b) Cells and tubing (Cambridge) - two required 5 lb. ea. (-30) *226. Engines - 2 Lycoming R-680-E3 +12 lbs. (-54) Limits (91 min. octane fuel): Maximum continuous, 2200 rpm (285 hp) Take-off (one minute), 2300 rpm (300 hp) With Ham. STd. 2B20/6135A-9 to -15 propeller (diameter 98.75" maximum, 91.0" minimum) with constant speed governor (Item 104) Pitch settings at 42 in. sta: (with 6135A-9 blades) Low 8°, High 20° or Low 11°, High 26° (with 6135A-15 blades) Low 14°, High 26° Eligible only on aircraft incorporating the 5,700 lb. wings (Item 604). An approved engine mount must be used and the lower members of the rear nacelle truss just aft of the front spar and forward of the middle cluster joint must be adequately reinforced. Item 403 required in lieu of Item 401. The installation of this item has been approved for Serv-Aero Engineering, P.O. Box 478, Dos Palos, California. This company has CAA approval of a conversion kit consisting of structural drawings AE-LC100 and AE-LC200 describing the required modification to the engine mount and nacelle, installation instructions, and photographs identifying their exhaust collector rings, engine cowling and carburetor air heaters. 227. Two (2) Davis aircraft exhaust silencers Model D-450-78 14 lbs. (-50) A-722 4 228. Engines - 2 Jacobs R-755A2 No weight change Limits (80 minimum octane fuel) Maximum continuous, 28 in.Hg., 2200 rpm (285 hp) Take-off (one minute), 2200 rpm (300 hp) With Hamilton Standard 2B20/6135A-15 propeller (diameter 93-1/8 in. max., 91-1/8 in. minimum) with constant speed governor (Item 104) Pitch settings at 42 in. sta: Low 12.5°, High 27° Eligible only on airplanes having 5,700 lb. wings (Item 604) and oil radiator installations (Item 220). Item 404 required in addition to Item 401. Landing Gear 109. 7.50-10 wheels (Goodyear 10HBM) with 8.50-10, 6-ply, H.D. tires 80 lbs. (-19) and 7.50-10 tubes (wheels must be placarded for these tires) 110. 12.5 in. smooth contour tail wheel with 4-ply tire and tube 10 lbs. (+279) 111. Two landing gear struts (Bendix R-107-2423-E; 65000 or 67650) 44 lbs. (+16) 112. Manual landing gear retracting mechanism 3 lbs. (-10) 113. Landing gear operating motor (Eclipse Y-150 or 455) 19 lbs. (-10) 204. 8.50-10 puncture-proof tubes +11 lbs. (-19) 210. Co-pilot's brakes 3 lbs. (-48) 222. 7.50-10 wheels (Hayes 751A) with 8.50-10, 6-ply, H.D. tires +9 lbs. (-19) and 7.50-10 tubes (wheels must be placarded for these tires) *229. Skis - Federal Model A-5800 Use actual weight Installation to be in accordance with Federal Aircraft Works Dwg. 11G265A. Electrical Equipment 106. One generator - engine-driven: (a) Eclipse LV-180 (15 amp., 12 volt) 16 lbs. (-45) or (b) Leece-Neville L-3 (25 amp., 24 volt) 24 lbs. (-45) 107. Battery - 75 lb. maximum (variable location (-16), (+6), (+10)) Use actual weight (a) 12 volt system - min. 33 amp. hr. (5 hr. rate) (b) 24 volt system - min. 17 amp. hr. (5 hr. rate) 108. Battery box 7 lbs. 202. Landing lights: (a) Two Grimes ST-1220 14 lb. (-6) or (+9) (b) Two Grimes Type B-3 or G-300 114 lbs. (+9) 216. Generator - engine-driven (a) Eclipse 309 (25 amp., 12 volt) (replacing Item 106(a)) +5 lbs. (-45) Interior Equipment 201. Flares: (a) Four 1 1/2 minute with case 20 lbs. (+116) (b) Three 1 1/2 minute with case 15 lbs. (+116) (c) One 3 minute with case 23 lbs. (+116) 215. Bucket seat with upholstering (replacing standard seat 15 lbs. at (-9)) -8 lbs. (-10) 5 A-722 401. CAA Approved Operating Manual, latest revision of Cessna Report No. 260 (NOTE: This does not take the place of the Form ACA-309) *402. Cabin heater - Surface Combustion Heater Package, Model 15. 18 lbs. (+8) Surface Combustion Installation and Service Instructions JL52-116 as amended 1-10-47. (This item not eligible for new installations after April 1, 1951) 403. CAA Approved Operating Manual (Servo-Aero Engineering). Required with Item 226 in lieu of Item 401. 404. CAA Approved Operating Manual Supplement (Jacobs Aircraft Engine Co.) dated April 10, 1952. This supplement may be obtained from Jacobs Aircraft Engine Co., Pottstown, Pa. (Required with Item 228.) Miscellaneous (not listed above) 114. Flap motor (Dumore Type KL) 6 lbs. (+46) 211. Turret top windows +2 lbs. (-20) 218. Flap motor (Dumore EI-YD or E2-YD or E2Y2P)- 3 lbs. (+49) 224. Two flap motors (Dumore EI-YD) No weight change 601. Unbalanced elevator (no balance area at tip of elevator ahead of hinge line) with balance weight on elevator walking beam 602. Balanced elevator with elevator bungee spring installed and horizontal stabilizer incidence set in accordance with Cessna Dwg. No. 10002-14 603. 5,100 lb. wing. See NOTE 3 for means of identifying wing. 604. 5,700 lb. wing. See NOTE 3 for means of identifying wing. 605. New flap limit switch brackets and revised adjustment of flap limit switches, in accordance with Cessna Dwg. No. 10002-28 and Service Bulletin No. 99 providing increase in flap travel from 35° (old setting) to 40° (new setting) *606. Large cargo door and interior flooring. Install in accordance Use actual wt. change with Decatur Aviation Co. Dwgs. 1 through 12. *607. Large access door and cargo floor. Install in accordance with Use actual wt. change Rapidair, Inc., Springfield, Missouri installation instructions, photographs and Dwg. No. 100-1, Sheets one through eight, dated December 4, 1953, "Easy Access Cargo and Ambulance Door - Cessna T-50" and Dwg. No. 101-1, Sheets one through eleven, dated December 5, 1953, "Cessna T-50 Cargo Floor." Note: Loading to be in accordance with weight control provisions. NOTE 1. Current weight and balance report including list of equipment included in certificated weight empty, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter (except in the case of air carrier operators having an approved weight control system). The C.G. limits were determined with the landing gear extended. The airplane must be loaded so that its C.G. position with the landing gear extended is always between the limits shown. NOTE 2. Army models AT-17 and UC-78 Series and Navy JRC-1 airplanes are eligible for certification under the conditions outlined below. These airplanes are similar to the model T-50 except for revised wing structure, power plant installation, 24 volt electrical and battery installations, revised rear seat, revised safety belt attachments, fuselage members at windshield eliminated, revised landing gear structure, balanced type elevators, and various items of Army equipment such as generators, batteries, instruments, safety belts (B-11), landing lights, flap motor(s), fuel pumps, oil radiators, etc. Prior to certification all Army models AT-17 and UC-78 Series, and Navy JRC-1 airplanes must be modified as follows: (a) Replacement and rewiring of master switch. (Reference: Cessna Dwg. No. 10002-4). (b) Removal of navigation light resistors. (Reference: Cessna Dwg. No. 10002-4). (c) Replacement of navigation light switches. (Reference: Cessna Dwg. No. 10002-4). (d) Add sealing plates for selector valve box. (Reference: Cessna Dwg. No. 10002-3). (e) Replace present tail light with Grimes model C tail light. (f) Install a placard reading: "Intentional Spinning Prohibited." A-722 6 (g) Modify horizontal tail surfaces to comply with either Item 601 or Item 602. (h) Install the following placard on the instrument panel in full view of the pilot: "This Airplane shall be operated in accordance with the CAA Approved Operating Manual (Part I). This Manual shall be carried in the pilot's compartment at all times." (See Item 401 or 403). (i) Upon completion of conversion to certificated status it should be ascertained that the manufacturer's serial number and original date of manufacture are shown on the original name plate or an additional name plate with this information may be added. (j) Add etched datum plate on fuselage front spar fitting on bottom of spar. (k) If AN-3033-5 to -8 wing tip lights are installed the sand blasted area on the inside of the streamlined glass cover should be painted black. As an alternative the streamlined glass cover may be replaced by a glass globe and a streamlined metal cover which can be obtained from the light manufacturer. (l) Inspect the leading edges of all wings by removing the nacelle cowling forward of the front spar and the inspection plate from the rib on the first nose rib assembly outboard of the nacelle. If the rib spacing in the leading edge is approximately 4 inches the wing is satisfactory. If the rib spacing is approximately 8 inches the wing must be modified in accordance with Cessna Service Bulletins No. 40 dated February 24, 1943, and No. 48 dated August 20, 1943, revised May 1, 1944. NOTE 3. (a) In order to determine whether the airplane is eligible for certification at a maximum weight in excess of 5,100 lbs., the wings can be identified by the following salient features: (1) 5,700 lb. wings have a laminated (8 to 10-ply) birch plywood reinforcement on the rear face of the rear spar (instead of a spruce block found on the 5,100 lb. wing) extending continuously through the center section from nacelle to nacelle. Ends of this plywood plate are scarfed out just inboard of each nacelle bearing block. (2) Continuous plywood flanges 1 to 1 1/2 x 1/16 inch are found on both sides of the lower cap strip of wing ribs between the front and rear spar on 5,700 lb. wings. (3) The diagonal in the nose ribs of the 5,700 lb. wing is 5/16 x 7/16 instead of 5/16 x 5/16 found in the 5,100 lb. wing. (b) Wings identified by the above specifications are wing assemblies No. 55700 and when installed, the airplane may be certificated at a maximum weight of 5,400 or 5,700 lbs. depending upon the items installed as specified under "Maximum Weight" on Page 1 of this specification. (c) Wings with the rear spar and reinforcing plate on the rear face made of spruce block only are wing assemblies No. T-50100 or 53600. These are not eligible for weights in excess of 5,100 lb. (d) When the airplane is certificated the 1/2 inch red letters immediately forward of the Army markings on the trailing edge of the wing which read "Max. gross weight 5,200 lb." or "5,300 lb." or "5,700 lb." should be removed from the wing. NOTE 4. Model T-50 (also exported RCAF T-50) airplanes having wing leading edges modified in accordance with Cessna Service Bulletin No. 48 except for the leading edge cover of 1/16 3-ply birch plywood laid with the face grain spanwise are considered to be suitably modified. NOTE 5. Aircraft eligible for 5,700 lbs. maximum weight which were certificated in restricted category for dusting, spraying, seeding, etc., prior to October 11, 1950, may continue to be operated with the following limitations: (a) Maximum take-off weight 6270 lbs. Maximum maneuvering speed 125 mph True Ind. (b) The following placard must be installed in full view of the pilot: "Maximum maneuvering speed 125 mph." All original certification in the restricted category after October 11, 1950, must be in accordance with CAR and CAM 8. ....END.... ``` ## ADs (13, in force first) - [AD 46-01-01](https://openairdocs.org/ad/46-01-01): Flap Chain · Cessna T-50 - [AD 46-01-02](https://openairdocs.org/ad/46-01-02): Wing Covering · Cessna T-50 - [AD 46-12-01](https://openairdocs.org/ad/46-12-01): Fabric Inspection · Cessna T-50 - [AD 46-46-03](https://openairdocs.org/ad/46-46-03): Aileron And Flap Hinge Brackets · Cessna T-50 - [AD 47-05-01](https://openairdocs.org/ad/47-05-01): Fuel Shutoff Valve Handle · Cessna T-50 - [AD 47-30-02](https://openairdocs.org/ad/47-30-02): Brake Pedal Links · Cessna T-50 - [AD 47-30-03](https://openairdocs.org/ad/47-30-03): Wing Inspection for Identification · Cessna T-50 - [AD 47-30-04](https://openairdocs.org/ad/47-30-04): Landing Gear Chains · Cessna T-50 - [AD 51-18-01](https://openairdocs.org/ad/51-18-01): Rudder Torque Tube · Cessna T-50 - [AD 51-25-01](https://openairdocs.org/ad/51-25-01): Horizontal Stabilizer · Cessna T-50 - [AD 53-06-01](https://openairdocs.org/ad/53-06-01): Landing Light Motor Circuit · Cessna T-50 - [AD 53-18-01](https://openairdocs.org/ad/53-18-01): Goodrich Wheel Bearing · Cessna T-50 - [AD 56-21-02](https://openairdocs.org/ad/56-21-02): Spar Deterioration · Cessna T-50 ## Registered aircraft by registry model (OpenAirDocs) - [Cessna T-50](https://openairdocs.org/model/cessna-t-50): 37 aircraft (registry code 2071302) - [Cessna / Larson T 50](https://openairdocs.org/model/cessna-larson-t-50): 0 aircraft (registry code 2071303) ## STCs approved under this data sheet (48) - [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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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 SA00478CH](https://openairdocs.org/stc/SA00478CH): Installation of Cooper Superflite 102 Fabric.. Aviation Products Systems 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 SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc - [STC SA02015SE-D](https://openairdocs.org/stc/SA02015SE-D): Installation of Garmin G500 Primary Flight Display (PFD) and Multifunction Display (MFD) System.. Garmin International Inc - [STC SA02033AT](https://openairdocs.org/stc/SA02033AT): Modification to install an air-oil separator to prevent oil from being aspirated from the engine breather line.. M-20 Oil Separators LLC - [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc - [STC SA01122WI](https://openairdocs.org/stc/SA01122WI): Installation of Cleveland Wheel and Brake Assembly kit for installation on Cessna T-50, serial number 6516 ONLY.. Harley Charles - [STC SA01123WI](https://openairdocs.org/stc/SA01123WI): Installation of Airwolf Oil Filter AFC-K017 and VAP Oil PN U-3140 cooler as replacements for obsolete parts on Cessna T-50, serial number 6516 ONLY.. Harley Charles - [STC SA166CH](https://openairdocs.org/stc/SA166CH): Surrendered and incorporated into STC SA00478CH.. Cooper Aviation Supply Company, Inc. - [STC SA02520AT](https://openairdocs.org/stc/SA02520AT): Installation of M-20 Oil Separator, model 600-WP.. M-20 Oil Separators LLC - [STC SA00128BO](https://openairdocs.org/stc/SA00128BO): Installation of Cleveland wheel and brake assembly 20-148.. Air Ads, Inc. - [STC SA71GL](https://openairdocs.org/stc/SA71GL): Installation of air filters. Brackett Aero Filters Inc. - [STC ST00108BO](https://openairdocs.org/stc/ST00108BO): Installation of Cleveland wheel and brake assembly 20-148.. Cedric M Abbott - [STC SA02095AK](https://openairdocs.org/stc/SA02095AK): Installation of hourmeter airspeed switch.. Avalaska Inc - [STC SA2-952](https://openairdocs.org/stc/SA2-952): Installation of fiberglass covering.. Razorback Fabrics Inc - [STC SA1351WE](https://openairdocs.org/stc/SA1351WE): Replace existing fabric on wings, fuselage, empennage, and/or control surfaces, with Ceconite101 material. (262A Series -12). Ceconite Inc - [STC SA4-1210](https://openairdocs.org/stc/SA4-1210): Installation of Eonnex cover on aircraft surfaces.. Ceconite, Inc - [STC SA4-1347](https://openairdocs.org/stc/SA4-1347): Ceconite 101 covering of entire airplane.. Cooper Engineering Corporation - [STC SA4-161](https://openairdocs.org/stc/SA4-161): Fiberglass fabric on fuselage, ailerons, flaps, empennage and wings.. Whitehall Pacific Avn Inc - [STC SA1-196](https://openairdocs.org/stc/SA1-196): Fiberglass application over fabric.. Anita H Paner - [STC SA02153LA-D](https://openairdocs.org/stc/SA02153LA-D) (historical): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System. Garmin International Inc - [STC SA02153LA](https://openairdocs.org/stc/SA02153LA) (historical): Installation of Garmin G600 Primary Flight Display (PFD) and Multifunction Display (MFD) System.. Garmin AT Inc. --- 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.