# TCDS A-684: Textron Aviation Inc. - Type: Type certificate data sheet - Status: Current - Holder: Textron Aviation Inc. - Revision: 6 - Revised: November 27, 2017 - Product: Aircraft, Small Airplane - Registered aircraft: 1, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/42/00/4200c67601720bcc37341fb7fecd76c594763d8699835d615f2566265aefb3b8 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/00900B34D67162AA862581EF0060CBBF.0001 - Page: https://openairdocs.org/tcds/A-684 ## Models (6) As the data sheet lists them. - SA18D - A18A - SA18A - A18D - S18D - 18D ## 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. 6 1 1 1 1 1 1 5 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A-684 Revision 6 Textron Aviation 18D S18D A18A SA18A A18D SA18D November 27, 2017 TYPE CERTIFICATION DATA SHEET NO. A-684 This data sheet which is a part of Type Certificate No. A-684 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 Textron Aviation Inc. One Cessna Boulevard Wichita, KS 67215 Type Certificate Holder Record Beech Aircraft Corporation transferred to Raytheon Aircraft Company on April 15, 1996 Raytheon Aircraft Company transferred to Hawker Beechcraft Corporation on March 26, 2007 Hawker Beechcraft Corporation transferred to Beechcraft Corporation on April 12, 2013 Beechcraft Corporation transferred to Textron Aviation Inc. on October 12, 2016 I. Model 18D, 11 PCLM, Approved June 15, 1938; Model S18D, 11 PCSM, Approved June 15, 1939 Engines Two (2) Jacobs L-6, L-6M or L-6MB Fuel 80 min. octane aviation gasoline. Engine limits Maximum continuous, (Sea level) 24.5 inHg, 2100 rpm (300 hp) (Straight line manifold pressure variation with altitude to 3700 ft.) 23.5 inHg, 2100 rpm (300 hp) Take-off (one minute), 26.0 inHg, 2200 rpm (330 hp) Airspeed limits (Landplane) (Serial Nos. 222, 225 and on) Level flight or climb 211 mph True Ind. Glide or dive 253 mph True Ind. Flaps extended 117 mph True Ind. (Other Serial Nos.) Level flight or climb 183 mph True Ind. Glide or dive 219 mph True Ind. Flaps extended 117 mph True Ind. (Seaplane) Level flight or climb 170 mph True Ind. Glide or dive 207 mph True Ind. Flaps extended 117 mph True Ind. Ceiling (Landplane) 3800 ft. usable, in standard air at an indicated airspeed of 90 mph at 200 lbs. with either engine inoperative and the inoperative propeller idling in positive high pitch at 700 rpm. (Seaplane) 0 ft. absolute, either engine inoperative. C.G. range (Landplane) (+2.5) to (+17.4) (Seaplane) (+2.5) to (+15.5) A-684 2 Rev. 6 I. Model 18D, Model S18D (cont’d) Maximum weight (Landplane) 6700 lbs. or 7200 lbs. when equipped with heavy duty tires and appropriate stencil. (Seaplane) 7170 lbs. No. seats 11 maximum (2 crew at -14). See Items 113 and 208 for location of passenger seats. Baggage Maximum capacity 1100 lbs. Fwd. compt. 600 lbs. (-74) or 300 lbs. (-85) with Item 205(a). Rear compt. 300 lbs. (+141) Nacelle compts. (Item 222) 100 lbs. each (+27) Fuel capacity 160 gals. (Two wing tanks, 80 gals. each) (+24) Oil capacity 16 gals. (8 gal. tank in each nacelle at 4 1/2 gals.) (-30) See Item 210 for optional tanks. Control surface movements Not available Serial Nos. eligible 62 and on (See NOTE 3 showing modifications made to Serial Nos. 222, 225 and on). Required equipment (Landplane) Items 101, 102, 103, 104, 105, 106, (107 and 108 required only with battery ignition engines), 109, 110(a)(b), 111(a), 112, 113, 114(a)(b). (Seaplane) Items 101, 104, 106, (107 and 108 required only with battery ignition engines), 109, 110(a)(b), 111, 112, 113, 151 , 152. II. Model A18D, 11 PCLM and Model SA18D, 11 PCSM, Approved May 7, 1940 Model A18D same as Model 18S, TC 710, except engine installations and wing skin thickness. Engines Two (2) Jacobs L-6, L-6M or L-6MB Fuel 80 min. octane aviation gasoline. Engine limits Maximum continuous, (Sea level) 24.5 inHg, 2100 rpm (300 hp) (Straight line manifold pressure variation with altitude to 3700 ft.) 23.5 inHg, 2100 rpm (300 hp) Take-off (one minute), 26.0 inHg, 2200 rpm (330 hp) Airspeed limits (Landplane) Level flight or climb 211 mph True Ind. Glide or dive 253 mph True Ind. Flaps extended 117 mph True Ind. (Seaplane) Level flight or climb 170 mph True Ind. Glide or dive 207 mph True Ind. Flaps extended 117 mph True Ind. Ceiling 0 ft. absolute, either engine inoperative. Rev. 6 3 A-684 II. Model A18D, Model SA18D (cont’d) C.G. range (Landplane) (+5.6) to (+16.3) at 7500 lbs. (+2.5) to (+16.3) at 5900 lbs. or less Straight line variation between points given. 5900 6100 6300 6500 6700 6900 7100 7300 7500 3 5 7 9 11 13 15 17 FRONT LIMIT REAR LIMIT INCHES LBS. (Seaplane) (+2.5) to (+15.5) Maximum weight (Landplane) 6700 lbs. or 7500 lbs. when equipped with heavy duty tires and appropriate stencil. (Seaplane) 7170 lbs. No. seats 11 maximum (2 crew at -14). See Items 113 and 208 for location of passenger seats. Baggage Maximum capacity 1100 lbs. Fwd. compt. 600 lbs. (-74) or 300 lbs. (-85) with Item 205(a). Rear compt. 300 lbs. (+141) Nacelle comps. (Item 222) 100 lbs. each (+27) Fuel capacity 160 gals. (Two wing tanks, 80 gals. each) (+24) Oil capacity 16 gals. (8 gal. tank in each nacelle at 4 1/2 gals.) (-30) See Item 210 for optional tanks. Control surface movements Not available Serial Nos. eligible 222, 225 and on (See NOTE 3 showing modifications made) Required equipment (Landplane) Items 102, 103, 104, 105, 106, (107 and 108 required only with battery ignition), 109, 110(a)(b), 111(a), 112, 113, 114(b), 201, 225. (Seaplane) Items 104, 106, (107 and 108 required only with battery ignition engines), 109, 110(a)(b), 111, 112, 113, 151 152, 201, 225. III. Model A18A, 11 PCLM, and Model SA18A, 11 PCSM, Approved May 7, 1940 Model A18A same as Model 18S, TC 710, except engine installations and wing skin thickness. Engines Two (2) Wrights R-760E-2 (-48.5) Fuel 80 min. octane aviation gasoline. A-684 4 Rev. 6 III. Model A18A, Model SA18A (cont’d) Engine limits Maximum continuous, 2200 rpm (320 hp) Take-off (one minute), 2400 rpm (350 hp) Airspeed limits (Landplane) Level flight or climb 211 mph True Ind. Glide or dive 253 mph True Ind. Flaps extended 117 mph True Ind. (Seaplane) Level flight or climb 170 mph True Ind. Glide or dive 207 mph True Ind. Flaps extended 117 mph True Ind. Ceiling (Landplane) 3100 ft. usable, in standard air at an indicated airspeed of 95 mph at 7500 lbs. with either engine inoperative and the inoperative engine at maximum continuous power. (Leading edge deicers installed but not operating.) (Seaplane) 0 ft. absolute, either engine inoperative. C.G. range (Landplane) (+5.6) to (+16.3) at 7500 lbs. (+2.5) to (+16.3) at 5900 lbs. or less Straight line variation between points given. For figure see Section II. (Seaplane) (+2.5) to (+15.5) Maximum weight (Landplane) 6700 lbs. or 7500 lbs. when equipped with heavy duty tires and appropriate stencil. (Seaplane) 7170 lbs. No. seats 11 maximum (2 crew at -14). See Items 113 and 208 for location of passenger seats. Baggage Maximum capacity 1100 lbs. Fwd. compt. 600 lbs. (-74) or 300 lbs. (-85) with Item 205(a) Rear compt. 300 lbs. (+141) Nacelle compts. (Item 222) 100 lbs. each (+27) Fuel capacity 160 gals. (Two wing tanks, 80 gals. each) (+24) Oil capacity 16 gals. (8 gal. tank in each nacelle at 4 1/2 gals.) (-32) See Item 210 for optional tanks. Control surface movements Not available Serial Nos. eligible 222, 225 and on (See NOTE 3 showing modifications made) Required equipment (Landplane) Items 102, 103, 104, 105, 106, 109, 110(a)(b) , 111(b), 112, 113, 114(b), 201, 225. (Seaplane) Items 104, 106, 109, 110(a)(b), 111, 113, 151, 152, 201 , 225. Rev. 6 5 A-684 Data Specifications Pertinent to All Models Datum Centerline of the wing main beam at the fuselage. Leveling means Not available. Certification Basis Type Certificate No. 684 (Aero. Bulletin 7A) Production Basis None. Prior to original certification of each aircraft manufactured subsequent to August 7, 1945, a CAA representative mus 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 same information) except as follows: (a) Canada: Landplane and seaplane - eligible Skiplane - not eligible. However, structure complies with Canadian requirements for ski installation when Item 219 is installed, with tread of 155 in. and pedestal height of 13 in., and distances from ski bottom to V-Brace attachment, with gear in half-deflected position, as follows: Distance 48.5 in., Maximum weight 6700 lbs. 37.3 in., Maximum weight 7200 lbs. Equipment A plus (+) or minus (-) sign preceding the weight of an item indicates net weight change when that item is installed. 18D, S18D A18A A18D, SA18D SA18A Propellers and Propeller Accessories (Except De-Icing Equipment) 111. Two propellers - controllable metal 108 lbs. ea. (a) Ham. Std. hubs 2B20, blades 6135A-9 or -10 (-66) ----- Dia.: 8'3-1/8" max., 8'7/8" min. Low pitch settings: 15°, high 16°, 11°, high 13° (With Item 201) measured at the 42-inch station. (b) Ham. Std. hubs 2B20, blades 6135A-12 or -13 ----- (-68) Dia.: 8'1/8" max., 7'9-7/8" min. Low pitch settings: 15.5°, high 16.5°. 11.5°, high 13.5° (With Item 201) measured at the 42-inch station. 201. Two constant speed governors 10 lbs. ea. (-36) (-63) Engines and Engine Accessories - Fuel and Oil Systems 101. Two engine ring cowls 50 lbs. (-52) (-52) 104. Two oil radiators (Harrison 3074510) 20 lbs. (-61) (-61) 110. Fuel pumps (a) Wobble (Type D-2) 4 lbs. (-22) (-22) (b) Two engine-driven (Pesco R-400-BC) 3 lbs. ea. (-37) (-35) 112. Two carburetor heaters 5 lbs. ea. (-42) (-40) 205. Fuel tanks (a) 50 gal. (One tank in nose of fuselage) 32 lbs. (-64) (-64) When this item is installed: (1)Forward baggage is 300 lbs. maximum (-85) (2) Placard as follows (unless otherwise substantiated): At main fuel valve, "Use Nose Tank First." At nose filler cap, "Fill Main Wing Tanks First." (b) Two 25 gal. wing tanks, rear 30 lbs. (+53) (+53) A-684 6 Rev. 6 Specifications Pertinent to All Models (cont’d) Engines and Engine Accessories - Fuel and Oil Systems (cont’d) 209. Vacuum pumps (a) Pesco 5 lbs. ea. (-36) (-34) (b) Romec 5 lbs. ea. (-36) (-34) (c) Adapter, 3-way 8 lbs. ea. (-36) ----- (d) Adapter, 2-way 5 lbs. ea. (-36) ----- 18D, S18D A18A A18D, SA18D SA18A 210. Oil tanks (a) 10 gal. (5 gal. tank in each nacelle) 4 1/2 lbs. ea. (-30) (-32) (b) 17 gal. (8 1/2 gal. tank in each nacelle) 8 lbs. ea. (-10) (-10) (c) 13 gal. (6 1/2 gal. tank in each nacelle) (-30) (-32) 214. Mixture analyzer (a) Indicator 2 lbs. (-42) (-42) (b) Cells and tubing (Cambridge) - two required 5 lbs. ea. (-11) (-11) (c) Cells and tubing (Breeze) - two required 8 lbs. ea. (-11) (-11) 217. Two starters (Eclipse E80) 40 lbs. (-38) (-38) 225. Two engine ring cowls (with flaps) 47 lbs. ea. (-44) (-49) 226. Two oil radiators (Harrison 3074510) 10 lbs. ea. (-25) (-25) 301. Two 78 gal. fuel tanks (Replacing std. 80 gal. tanks) No weight change Landing Gear and Floats 102. 5 in. wheels (Goodyear 5HBM) and 29x13-5 H.D. tires 122 lbs. (- 9) (- 9) (For weights above 7200 lbs. stencil on landing gear fork must state, "Use Heavy Duty Tires Only".) 103. 12x5-3 tail wheel with H.D. tire 9 lbs. (+261) (+261) (Wheel must be placarded for H.D. tire) 114. Shock absorbers (a) Dwg. 188400 (less wheel, brake and tire) 79 lbs. ea. (-12) (-12) (b) Dwg. 188400A (less wheel, brake and tire) 86 lbs. ea. (-12) (-12) 151. Edo model 55-7170 floats with water rudders (Dwg. No. 55-S-007); auxiliary seaplane fin (Dwg. No. S-186221) (For all airplanes of serial No. 178 or under, seaplane center section spar, Dwg. No. S-18422 Rev. B or 18110 Rev. E, is also required.) 211. Dual brake installation (Dwg. No. 187480) 4 lbs. (-44) (-44) 219. Skiplane landing gear (Dwgs. 18800K or 188000K, 18110 Rev. C; shock struts 7466 or 188400K) 232. 5 in. wheels, (Goodyear A5HBM-10) +10 lbs. (- 9) (- 9) Electrical Equipment 105. Two landing gear operating motors (Dumore D-5) 18 lbs. (-12) (-12) 106. Wing flap operating motor (Dumore 3549) 8 lbs. (-12) (-12) 107. Two generators - 15 amp. (Eclipse) 30 lbs. (-38) (-34) 108. Two batteries (Exide 6TS-13-1) 72 lbs. (-18) (-18) 109. Bonding and shielding 30 lbs. (-58) (-46) 203. Generators (a) 25 amp. (Eclipse) 20 lbs. (-38) (-34) (b) 50 amp. (Eclipse) 32 lbs. (-38) (-34) Rev. 6 7 A-684 Specifications Pertinent to All Models (cont’d) Electrical Equipment (cont’d) 206. Battery (In right and/or left wing leading edge near fuselage (-18) or aft main spar in cabin (+7)) (a) Reading 6-ARL-11 46 lbs. ea. (b) Reading 6-ARL-9 56 lbs. ea. (c) Exide 6XT-13 64 lbs. ea. (d) Exide 6-TS-7-1 26 lbs. ea. 218. Two landing lights (Grimes ST-1000 or ST-1220) 10 lbs. (+36) (+36) 220. Landing gear motor, Elec. Spec. HCA (modified) 14 lbs. (-15) (-15) 221. Wing flap motor, Dumore 4289 (modified) 5 lbs. (- 8) (- 8) 18D, S18D A18A A18D, SA18D SA18A Interior Equipment 113. Four standard or parachute passenger seats with 17 lbs. ea. (+37, +86) or safety belts (Dwg. 18051-1) (+34, +45, +79, +92) 202. Flares (Wiley A-8) 36 lbs. (-52) or (+160) 208. Seats (Dwg. 18051, Arrangements (2) to (7)) Number and location will be shown on weight and balance report. (2) 6 seats (+22, +54, +86) 17 lbs. ea. (3) 6 seats (locations and weights as in (2)) with 1 extra chair (18 lbs. at +115)) (4) 6 seats (+22, +54, +86, +25, +59, +92) 17 lbs. ea. (5) 6 seats (locations and weights as in (2)) with 2 folding chairs (7 lbs. ea. at +118) (6) 3 place couch (39 lbs. with safety belts, at +41) (left side) (+15, +41, +67), with from 1 to 5 seats at any of the following locations: (+22, +25, +54, +59, +86, +92, +115, +118) (7) 2, 3 or 4 place couch (40 lbs., with safety belts as required) (left side) (+12, +32, +52, +72) with from 1 to 5 seats at any of the following locations: (+22, +25, +45, +54, +59, +86, +92, +113, +115, +118) 212. Toilet Equipment 7 lbs. (+106) or (+140) 216. Parachutes (Back pack 24 ft. will fit std. seat) 15 lbs. ea. 223. Two cabin heaters 10 lbs. ea. (-16) (-16) 224. Camera installation equipment (Dwg. I18045) (a) Operator's seat 17 lbs. (+45) (+45) (b) Camera and supports (Maximum weight) 97 lbs. (+13) (+13) (c) Structural revisions 14 lbs. (0) (0) 228. Heating system converted to ventilating system -16 lbs. (-20) (-20) (Dwg. I183950) 230. Mail compartment installation 8 lbs. (+17) (+17) 231. Photographic version (Models A18A and A18D only) (a) Fuselage alteration - includes camera wells in roof, floor, and door, and rerouted control cables (Dwgs. 184000P and 187000P) No weight change (b) Camera installation 352 lbs. (+ 66) (+ 66) (c) Photographer's chair and safety belt 20 lbs. (+100) (+100) A-684 8 Rev. 6 Specifications Pertinent to All Models (cont’d) Deicing Equipment 213. Deicer installation (Model A18A only) A. Surface (Maximum weight may be increased 45 lbs. for complete installation.) (a) 2 wing boots (removable) 14 lbs. ea. ----- (+12) (b) 2 stabilizer boots (removable) 4 lbs. ea. ----- (+244) (c) Valves, pumps, lines, etc. (fixed) 47 lbs. ----- (0) B. Propeller anti-icer (a) Anti-icer fluid tanks, pump and lines 11 lbs. ----- (-10) (b) Anti-icer fluid 20 lbs. ----- (- 5) Miscellaneous (not listed above) 152. Replacement - "V" Brace Seaplane Dwg. No. S-18811 222. Nacelle baggage compartments; seaplane, skiplane or fixed landing gear only (Dwg. No. I18024) 229. Twin venturi installation (Dwg. 18439) 2 lbs. (-38) (-38) 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). NOTE 2. The following placards are required at the locations noted: (a) When auxiliary 50 gal. fuel tank, Item 205(a), is installed: (1) Forward baggage is 300 lbs. maximum (-85). (2) Placard as follows (unless otherwise substantiated): At main fuel valve, "Use Nose Tank First." At nose filler cap, "Fill Main Wing Tanks First." (b) Placard lavatory door as follows: "This room not to be occupied during take-off and landing." (c) Placard fuel tank filler cap as follows: "80 octane minimum." (d) For weights above 7200 lbs., wheels must be placarded for heavy duty tires. NOTE 3. Serial Nos. 222, 225 and on, incorporate revised engine nacelles, cowling, tail surfaces and control system, and minor structural changes. ---- END ---- ``` ## ADs (7, 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 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 83-21-06 R1](https://openairdocs.org/ad/83-21-06-R1): Crew Seats · AMI Industries Crew Seats, 18A, 18D and 2 more. Effective Apr 26, 1984 - [AD 75-27-09 R2](https://openairdocs.org/ad/75-27-09-R2): Wing Structure · Textron 18A, 18D, 18S (Army C-45C) and 27 more. Effective Aug 21, 1980 - [AD 77-19-07](https://openairdocs.org/ad/77-19-07): Control Column Assembly · Textron 18A, 18D, 18S (Army C-45C) and 27 more. 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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 2](https://openairdocs.org/stc/SA02283SE%20PAGE%202): 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. - [STC SA02717NY PAGE 1](https://openairdocs.org/stc/SA02717NY%20PAGE%201): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC - [STC SA02717NY PAGE 2](https://openairdocs.org/stc/SA02717NY%20PAGE%202): Installation of VoiceFlight Systems LLC VFS101 Speech Recognition Module. VoiceFlight Systems LLC - [STC SA02825NY PAGE 1](https://openairdocs.org/stc/SA02825NY%20PAGE%201): Installation of Aerospace Logic Aircraft Instruments. Aerospace Logic Inc. - [STC SA01692SE](https://openairdocs.org/stc/SA01692SE): Installation of a Garmin GMX 200 Multi-Function Display. Garmin International Inc - [STC SA03148NY](https://openairdocs.org/stc/SA03148NY): The installation of the Latitude Technologies Corporation S100 Tracking System. Latitude Technologies Corporation - [STC SA02016SE-D](https://openairdocs.org/stc/SA02016SE-D): Installation of Garmin GTS 800, GTS 820 or GTS 850 Traffic System. Garmin International Inc - [STC SA01487SE-D](https://openairdocs.org/stc/SA01487SE-D): Installation of a GDL 69 or GDL 69A XM Satellite Receiver. Garmin International Inc - [STC SA00243BO](https://openairdocs.org/stc/SA00243BO): Installation of Centurion Consulting, Inc. GPS Steering Assist Module (SAM) with roll steering (p/n 0025-5100), or without roll steering (p/n 0025-5200).. Icarus Avionics, LLC - [STC SA1315WE](https://openairdocs.org/stc/SA1315WE): Installation of Mixture Monitor (exhaust gas temperature probe, gage and selector) in accordance with Delta Products Part Lists A-192 and A-193, or in accordance with Tri-Star Corporation Mixture Monitor Installation Instructions dated December 9, 1981, or later FAA approved revision and/or Drawing List MM-127 dated November 15, 1981, or later FAA approved revision in aircraft models listed in Master Eligibility List P-80-A-6 revised March 29, 1968, copy attached, or later FAA approved revision.. Universal Corporation - [STC SA00068SE](https://openairdocs.org/stc/SA00068SE): Installation of fuel flow/pressure instruments. (W/TSIO-360-MB1). Electronics International Inc. - [STC SA02110CH](https://openairdocs.org/stc/SA02110CH): Installation of a Time Trac Data Recorder. P2 Incorporated - [STC SA01988SE](https://openairdocs.org/stc/SA01988SE): Installation of Electronics International Inc. Glass Panel Engine Monitor (with In-Flight Data) MVP-50P.. Electronics International Inc. - [STC SA01473SE](https://openairdocs.org/stc/SA01473SE): Installation of a GTX 32 (mode C), GTX 33 (mode S), or GTX 33D (mode S with diversity) Remote Transponde. Garmin AT Inc. - [STC SA1512WE](https://openairdocs.org/stc/SA1512WE): Installation of exhaust gas temperature monitoring systems Model EGT-1.. K S Avionics Inc - [STC SA2557NM](https://openairdocs.org/stc/SA2557NM): Installation of KS Avionics EGT/CHT-2( ) combined exhaust gas and cylinder head temperature monitoring system.. K S Avionics Inc - [STC SA01695SE](https://openairdocs.org/stc/SA01695SE): Installation of an antenna. Garmin AT Inc. - [STC SA814SO](https://openairdocs.org/stc/SA814SO): Installation of wing spar strap Kit No. K7312.. Staggerwing Museum Foundation Inc. - [STC ST01468CH](https://openairdocs.org/stc/ST01468CH): Installation of various SMR Technologies electrical propeller deicer models.. SMR Technologies - [STC SA01487SE](https://openairdocs.org/stc/SA01487SE): Installation of a GDL 69 or GDL 69A XM Satellite Receiver in accordance with Garmin Supplemental Type Certificate Master Data List, P/N 005-C0217-00, Revision A, dated December 20, 2004, or later FAA approved revision.. Garmin AT Inc. All 67: https://openairdocs.org/tcds/A-684/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.