# TCDS 4A24: Atlantic Coast Seaplanes LLC - Type: Type certificate data sheet - Status: Current - Holder: Atlantic Coast Seaplanes LLC - Revision: 9 - Revised: April 14, 2008 - Product: Aircraft, Small Airplane - Certification basis: Part 21, Part 23, CAR 3 - Registered aircraft: 4, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/65/6b/656b8c2661633ed0ef047f44926ac064478031efc835d18fff7a4daa86d5d8fb - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C736225D8F22B0F68625742F004B0D6B.0001 - Page: https://openairdocs.org/tcds/4A24 ## Models (4) As the data sheet lists them. - G-21E - G-21D - G-21C - G-21G ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 4 5 6 7 8 9 Rev. No. 8 7 7 7 7 7 7 7 7 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION 4A24 Revision 9 Atlantic Coast Seaplanes LLC G-21C, G-21D G-21E, G-21G April 14, 2008 TYPE CERTIFICATE DATA SHEET NO.4A24 This data sheet which is a part of type certificate No. 4A 24 prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Civil Air Regulations. Type Certificate Holder A tlantic Coast Seaplanes LLC 3623 N. Elm Street, Suite 200 P. O. Box 41027 Greensboro, NC 27455 Type Certificate Holder Record: A.G. McKinnon transferred 4A24 to Viking Air Limited on June 6, 1984 Viking Air Limited transferred 4A24 to Aero Planes, Inc on September 4, 1998 TC 4A24 was reissued to Aero Planes, LLC on May 5, 2000 Aero Planes, LLC transferred 4A24 to Atlantic Coast Seaplanes LLC on September 27, 2007. TC 4A24 reissued to Atlantic Coast Seaplanes LLC on March 7, 2008. I - Model G-21C (Normal Category) Approved 7 November 1958 Engines Four Lycoming GSO-480-B2D6 Fuel 100/130 minimum grade aviation gasoline Engine limits (Straight line manifold pre ssure variation with altitudes as shown). H.P. R.P.M. MP ALT. Takeoff (5 minutes) 340 3400 48.0 S.L. Takeoff (5 minutes) 340 3400 44.5 8000 Maximum continuous 320 3200 45.0 S.L. Maximum continuous 320 3200 43.0 7500 Propeller and Four Hartzell constant sp eed propellers, hubs HC-83XF-3A, blades propeller limits 9333CH-0. Diameter: Max. 93 in., min. allowable for repairs 91 in. No further reduction permitted. Pitch settings at 30 in. station: Low 17.5°, feathered 85°, reverse -23° Placard required: "Avoid continuous operati on between 2800 and 3100 R.P.M." Airspeed limits Vne Never exceed 264 m.p.h. (229 knots) Vno Maximum structural cr uising 211 m.p.h. (183 knots) Va Maneuvering 174 m.p.h. (151 knots) Vfe Flaps extended 137 m.p.h. (119 knots) Vlo Landing gear operation 211 m.p.h. (183 knots) Vle Landing gear extended 211 m.p.h. (183 knots) Vmc Minimum control 123 m.p.h. (107 knots) C. G. range* (+22.0) (17.0% MAC) to (+29.6) (24.9% MAC) (Landing gear extended) *NOTE: The main gear retracts parallel to the wing reference axis; hence, this has no effect on airplane C.G. Empty weight C.G. range None Page 2 of 9 4A24 I - Model G-21C (cont'd) Maximum weights Takeoff 12499 lb. Landing (on land) 12000 lb. Landing (on water) 12499 lb. Maximum zero fuel weight 11500 lb. Minimum crew One No. of seats 9. (2 at -5, 2 at +24, 2 at +62, 1 at +118, 1 at +127, and 1 at +136) Maximum baggage Fwd. compartment 300 lb. (-65) Aft compartment 400 lb. (+169) Fuel capacity See NOTE 1(b) for information relative to usable fuel. Total Usable 2 main tanks 184 gal. ea. (+30) 183 gal. ea. 1 aux. tank 82 gal. (+30) 81 gal. Total usable fuel 447 gal. Oil capacity 24 gal. (6 gal. per engine) (+3) Control surface movements Wing flaps Down 40° Main surfaces Aileron Up 22° Down 17° Elevator Up 26° Down 21° Rudder Right 23° Left 17° **Tabs Elevator Up 16-1/2° Down 22-1/2° Rudder Right 17-1/2° Left 21° **Set rudder tab 2-1/2° to the left, with indicator (in cockpit) set on 0° or takeoff position. Left a nd right travel taken from this position. Serial Nos. eligible 1202, 1204 II - Model G-21D (Normal Category) Approved 29 June 1960 The Model G-21D differs from the Model G-21C in that the bow has been lengthened 36 in. to accommodate increased passenger load ing and the horizontal stabilizer and rudder tab have been increased in span for the increased controllability. Engines Four Lycoming GSO-480-B2D6 Fuel 100/130 minimum grade aviation gasoline Engine limits (Straight line manifold pre ssure variation with altitudes as shown). H.P. R.P.M. MP ALT. Takeoff (5 minutes) 340 3400 48.0 S.L. Takeoff (5 minutes) 340 3400 44.5 8000 Maximum continuous 320 3200 45.0 S.L. Maximum continuous 320 3200 43.0 7500 Propeller and Four Hartzell constant sp eed propellers, hubs HC-83XF-3A, blades propeller limits 9333CH-0. Diameter: Max. 93 in., min. allowable for repairs 91 in. No further reduction permitted. Pitch setting at 30 in. station: Low 17.5°, feathered 85°, reverse -23° Placard required: "Avoid continuous operati on between 2800 and 3100 R.P.M." Page 3 of 9 4A24 II - Model G-21D (cont'd) Airspeed limits Vne Never exceed 264 m.p.h. (229 knots) Vno Maximum structural cr uising 211 m.p.h. (183 knots) Va Maneuvering 174 m.p.h. (151 knots) Vfe Flaps extended 137 m.p.h. (119 knots) Vlo Landing gear operation 211 m.p.h. (183 knots) Vle Landing gear extended 211 m.p.h. (183 knots) Vmc Minimum control 123 m.p.h. (107 knots) C. G. range* (+19.6) (14.5% MAC) to (+29.5) (24.8% MAC) (Landing gear extended) *NOTE: The main gear retracts par allel to the wing reference axis; hence, this has no effect on airplane C.G. Empty weight C.G. range None Maximum weights Takeoff 12499 lb. Landing (on land) 12000 lb. Landing (on water) 12499 lb. Maximum zero fuel weight 11500 lb. No. of seats 14, (2 at -100.5, 2 at -64.5, 2 at -5, 2 at +29, 2 at +91, 2 at +147.5, and 2 at +177) Maximum baggage Fwd. compartment 300 lb. (-80) Fuel capacity See NOTE 1(b) for in formation relative to unusable fuel. Total Usable 2 main tanks 170 gal. ea. (+30) 168.5 gal. ea. Total usable fuel 337 gal. Oil capacity 24 gal. (6 gal. per engine) (+3) Control surface movements Wing flaps Down 40° Main surfaces Aileron Up 22° Down 17° Elevator Up 26° Down 21° Rudder Right 23° Left 17° **Tabs Elevator Up 16-1/2° Down 22-1/2° Rudder Right 17-1/2° Left 21° **Set rudder tab 6° to the left, with indicator (in cockpit) set on 0° or takeoff position. Left a nd right travel taken from this position. Serial Nos. eligible 1251 through 1255 III - Model G-21E (Normal Category) Approved July 17, 1969 The Model G-21E is similar to the Model G- 21C except for the engine installation and re lated changes. A Model G-21C that has b een modified in accordance with Supplemental Type Certificate No. SA1320WE is identical to the Model G-21E. Engines 1. Two United Aircraft of Canada Lts. PT6A-20 Fuel JP-4 and JP-5 fuels conforming to Pr att & Whitney Aircraft Specification No. 522. Oil Refer to UACL PT6 Engine Service Bulletin No. 1001 for eligible oils. (Not eligible with MIL-L-7808 type oils.) Page 4 of 9 4A24 III - Model G-21E (cont'd) Engine ratings (Static Sea Level) Shaft Jet Equivalent Propeller Horse- Thrust Shaft Speed power Lb. Horsepower RPM For all operations except reverse 550 72 579 2200 For reverse (one min.) 500 2100 Engine limits for all operations Gas Inter Turbine Torque Propeller Generator Temperature Lb-Ft RPM RPM Deg. Cent. 1315 2200 38,100* 750** *Maximum gas generator oversp eed limit - 38,500 rpm for 10 seconds. **Maximum inter turbine temperatur e during starting - 1994°F. (1090°C) for two seconds. Oil temperature Minus 40°F. (-40°C) Minimum Plus 210°F. ( 99°C) Maximum Oil pressure At 28,000 rpm gas genera tor speed and higher - 65 psi Minimum 85 psi Maximum Below 28,000 rpm gas genera tor speed - 40 psi Minimum 2. Two United Aircraft of Canada Ltd. PT6A-27 installed in accordance with the McKinnon Master Drawing List MPD 90996 dated May 1, 1970, or subsequent FAA approved revisions. Fuel JP-4 and JP-5 fuels conforming to Pr att & Whitney Aircraft Specification No. 522. Oil Refer to UACL PT6 Engine Service Bulletin No . 1 for eligible oils. (Not eligible with MIL-L-7808 type oils.) Engine ratings (Static Sea Level) Shaft Jet Equivalent Propeller Horse- Thrust Shaft Speed power Lb. Horsepower RPM For all operations except reverse 680 90 715 2200 For reverse (one min.) 620 2100 Engine limits (Max for all operations unless Gas Inter Turbine noted otherwise) Torque Propeller Generator Temperature Lb-Ft RPM RPM Deg. Cent. 1628 2200 38,100* 1336 °F. (725°C)** *Maximum gas generator oversp eed limit - 38,500 rpm for 10 seconds. Minimum gas generator speed for idle - 19,000 rpm **Maximum inter turbine temperatur e during starting - 1994°F. (1090°C) for two seconds. Maximum inter turbine temperature for idle - 122 F. (660 °C.) Page 5 of 9 4A24 III - Model G-21E (cont'd) Oil temperature Minus 40°F. (-40°C.) Minimum Plus 210°F. ( 99°C.) Maximum Oil pressure At 27,000 rpm gas generato r speed and higher: 80 psi Minimum and oil temperature of 140 - 160°F 100 psi Maximum Below 27,000 rpm gas genera tor speed 40 psi Minimum Propeller and Two Hartzell constant sp eed propellers, hubs HC-B3TN-3, blades propeller limits T10178HB. Diameter: Max. 96 in. No further reduction permitted. Pitch setting at 30 in. station: Low (flight idle) 20° +0° -0.5°, high (feather) 86° + 1°, reverse -11.0° + 0.5° Airspeed limits Maximum operati ng speed *211 m.p.h. (183 knots) Maneuvering speed 174 m.p.h. (151 knots) Flaps extended speed 110 m.p.h. ( 96 knots) Landing gear operating speed 160 m.p.h. (139 knots) Landing gear extended speed 160 m.p.h. (139 knots) *236 m.p.h. (205 knots) when PT6A-27 engines are installed C.G. range With PT6A-20 engines +21.5 to +29.5 at 10,500 lb. +19.6 to +29.5 at 8,562 lb. Straight line variation between points given With PT6A-27 engines +22.0 to +29.5 at all weights Empty weight C.G. range None Maximum weights Takeoff 10,500 lb. Landing (on land) 10,500 lb. Landing (on water) 10,500 lb. Zero fuel weight, land & water 10,182 lb. Minimum crew One No. of seats 9. (2 at -5, 2 at +24, 2 at +62, 1 at +118, 1 at +127, and 1 at +136) Maximum baggage Fwd. compartment 602 lb. (-65) Aft compartment 400 lb. (+169) Fuel capacity 1. Two main tanks (+30) Total 110 gal., 715 lb. each Usable 108.5 gal., 705 lb. each 2. Two outboard auxiliary tanks (+30) Total 60 gal., 390 lb. each Usable 60 gal., 390 lb. each 3. Optional Main Tanks in lieu of Item 1 above (+30) Total 168 gal., 1092 lb. each Usable 166.5 gal., 1082 lb. each NOTE: Fuel quantity must not exceed weights shown. See NOTE 1 for system fuel. Page 6 of 9 4A24 III - Model G-21E (cont'd) Oil capacity 4.6 gallons total in two integral engine tanks of 2.3 gallons each 3.0 gallons total usable See NOTE 1 for system oil. Control surface movements All controls plus (+) or minus (-) 1° Aileron Up 20° Down 20° Elevator Up 23° Down 20° Rudder Right 27° Left 26° Flaps Down 60° Elevator tab Up 10° Down 30° *Rudder tab Right 15° Left 25° *Set rudder tab 2-1/2° to the left, with indicator (in cockpit) set on 0° (takeoff position). Left and right travel taken from this position. Control surface Elevator + 90 + 21 in. lb. mass balane Rudder +130 + 20 in. lb. Aileron 0 + 10 - 13.6 in. lb. Serial Nos. eligible 1211 through 1225 IV - Model G-21G (Normal Category) Approved August 29, 1969 The Model G-21G is similar to the Model G- 21E except for the engine installation, revised fuel system, increased weights and ai rspeed limits, and related changes. Engines Two United Aircraft of Canada Ltd. PT6A-27 Optional: Two United Aircra ft of Canada Ltd. PT6A-28 Fuel JP-4 and JP-5 fuels conforming to Pratt & Whitney Aircraft Specification No. 522. Oil Refer to UACL PT6 Engine Service Bulletin No. 1001 for eligible oils. (Not eligible with MIL-L-7808 type oils.) Engine ratings (Static Sea Level) Shaft Jet Equivalent Propeller Horse- Thrust Shaft Speed power Lb. Horsepower RPM For all operations except reverse 680 90 715 2200 For reverse (one min.) 620 2100 Engine limits (Max. for all operations unless Gas Inter Turbine noted otherwise.) Torque Propeller Generator Temperature Lb-Ft RPM RPM Deg. Cent. PT6A-27: 1628 2200 38,100* 1336 °F. (725°C)** PT6A-28: 1628 2200 38,100* 1382 °F. (750°C)** *Maximum gas generator oversp eed limit - 38,500 rpm for 10 seconds. Minimum gas generator speed for idle - 19,000 rpm **Maximum inter turbine temperatur e during starting - 1994°F. (1090°C) for two seconds. Maximum inter turbine temperature for idle - 122 F (660 °C.) Page 7 of 9 4A24 IV - Model G-21G (cont'd) Oil temperature Minus 40°F. (-40°C) Minimum Plus 210°F. ( 99°C) Maximum Oil pressure At 27,000 rpm gas generato r speed and higher; - 80 psi Minimum and oil temperature of 140 - 160°F. 100 psi Maximum Below 27,000 rpm gas generato r speed - 40 psi Minimum Propeller and Two Hartzell constant sp eed propellers, hubs HC-B3TN-3, blades propeller limits T10178HB. Diameter: 96 in. No further reduction permitted. Pitch settings at the 30 in. station: Low (flight idle) 20° +0° -0.5°, High (feather) 86° + 1°, reverse -11.0° + 0.5° Airspeed limits (EAS) Maximum ope rating speed 236 m.p.h. (205 knots) Maneuvering speed 174 m.p.h. (151 knots) Flaps extended speed 110 m.p.h. ( 96 knots) Landing gear operating speed 160 m.p.h. (139 knots) Landing gear extended speed 160 m.p.h. (139 knots) C.G. range (+22.0) (17.0% MAC) to (+29.9% MAC) Empty weight C.G. range None Maximum weights Takeoff 12,500 lb. Landing (on land) 12,000 lb. Landing (on water) 12,500 lb. Zero fuel weight, land & water 10,182 lb. Alternate weight limits for airplanes asse mbled without full main cabin floor sealing. Takeoff (on land) 12,500 lb. Takeoff (on water) 10,500 lb. Landing (on land) 12,000 lb. Landing (on water) 10,500 lb. Zero fuel weight, land & water 10,182 lb. Minimum crew One No. of seats Ten. (2 at -5, 2 at +29, 2 at +91, 2 at +147.5, and 2 at +177) Maximum baggage Fwd. compartment 602 lb. (-65) Fuel capacity 1. Two inboard main tanks (+30) Total 168 gal., 1092 lb. each Usable 166.5 gal., 1082 lb. each 2. Two outboard main tanks (+30) Total 125 gal., 812 lb. each Usable 118 gal., 767 lb. each 3. Optional outboard tanks in lieu of Item 2 above (+30) Two outboard auxiliary tanks (+30) Total 60 gal., 390 lb. each Usable 60 gal., 390 lb. each Total fuel for items 1 and 2: 586 gal. with 569 gal useable Total fuel for items 1 and 3: 456 gal. with 453 gal useable See NOTE 1(b) for system fuel. Oil capacity 4.6 gallons total in two integral engine tanks of 2.3 gallons each 3.0 gallons total usable See NOTE 1(c) for system oil Maximum operating altitude 20,000 ft. Page 8 of 9 4A24 IV - Model G-21G (cont'd) Control surface movements All controls plus (+) or minus (-) 1° Aileron Up 20° Down 20° Elevator Up 30° Down 20° Rudder Right 27° Left 26° Flaps Down 60° Elevator tab Up 10° Down 30° Rudder tab* Right 15° Left 25° Set rudder tab 2-1/2° to the left, with the indicator (in cockpit) set on 0° takeoff position. Left a nd right travel taken from this position. Control surfaces Elevator +90 + 21.0 in. lb. mass balance Rudder +130 + 20.0 in. lb. Aileron 0 + 10.0 in. lb. - 13.6 in. lb. Serial Nos. eligible 1201, 1203, 1205, 1226 through 1250 DATA PERTINENT TO ALL MODELS Datum Wing leading edge at side of fuselage (+5.7 in forward MAC leading edge where length = 95.9 in MAC) Leveling means 6 in above floor at sta. 9 (Instrument Panel) and sta. 11. Wing level right side fuselage at sta. 12. Certification basis Models G-21C and G-21D CAR 3 effective May 15, 1956 with no amendments. Models G-21E and G-21G (1) For the powerplant installati on - FAR 23 including Amendments 23-1 through 23-6 (2) For areas other than the powerplant installation - CAR 3 effective May 15, 1956 with no amendments. (3) Special Conditions dated May 5, 1969. (4) Exemption No. 555 from FAR 21.19(b) issued July 6, 1966. Type Certificate No. 4A24 issued November 7, 1958, amended June 29, 1960, amended July 17, 1958, amended August 29, 1969. Application for type certificate dated February 21, 1957. Production basis Production Certificate No. 409. Since the Model G-21C, G-21D, G-21E a nd G-21G are conversion of the basic Grumman Models G-21 and G-21A (Type Cer tificate No. 654), the applicable portions of the following Airworthiness Directives must be complied with: 49-16-1, 53-20-2, 53-24-1, and 63-27-2. Equipment The basic required equipm ent 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) Approved equipment as show n in the following McKinnon Reports: (a) Model G-21C - No. MC-3-3-29 (b) Model G-21D - No. MC-14-20 (c) Model G-21E - No. MPD-90010 (d) Model G-21G - No. MPD-90110 (2) FAA Approved Airplane Flight Manual. Page 9 of 9 4A24 NOTE 1. (a) Current weight and balance report including lis t of equipment included in certificated empty weight, 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 operators having an approved weight control system. (b) The certificated empty weight and corresponding cen ter of gravity location must include system fuel (unusable) of 18 lb. at (+30) for Models G-21C and G-21D and 20 lb. at (+30) for Model G-21E and 110 lb. at (+30) for the Model G-21G with 586 gal tota l fuel and 20 lb at (+30) for the Model G-21G with 456 gal total fuel. (c) The certificated empty weight and corresponding cen ter of gravity locations must include system oil (unusable) of 12 lb. at (-42.5) for Models G-21E and G-21G. NOTE 2. The following placards must be installed in full view of the pilot unless noted otherwise: (1) "This airplane must be operated as a normal cat egory airplane in compliance with the FAA Approved Airplane Flight Manual. No acroba tic maneuvers including spins are approved." (2) Model G-21C only - "Use auxiliary tank for cruise only." (3) Model G-21C and G-21D with Lycoming GS O-480-B2D6 engine - "Avoid continuous operation between 2800 and 3100 rpm." (4) Models G-21C and G-21D only - "Maximum capacity 300 lb." adjacent to forward baggage compartment. (5) Models G-21E and G-21G only - "Maximum capacity 602 lb." adjacent to forward baggage compartment. (6) Models G-21C and G-21E only - "Maximum capac ity 400 lb." adjacent to rear baggage compartment. .....END..... ``` ## ADs (1, in force first) - [AD 73-07-05](https://openairdocs.org/ad/73-07-05): Elevator or Rudder Torque Tube Assys · Atlantic Coast Seaplanes G-21C, G-21D, G-21E and 1 more ## Registered aircraft by registry model (OpenAirDocs) - [Mckinnon G21G](https://openairdocs.org/model/mckinnon-g21g): 2 aircraft (registry code 5550120) - [Grumman/Mckinnon Enterprises G21G](https://openairdocs.org/model/grumman-mckinnon-enterprises-g21g): 1 aircraft (registry code 395069H) - [Mckinnon G-21C](https://openairdocs.org/model/mckinnon-g-21c): 1 aircraft (registry code 5550104) - [Mckinnon G-21E](https://openairdocs.org/model/mckinnon-g-21e): 0 aircraft (registry code 5550105) - [Mckinnon G21C](https://openairdocs.org/model/mckinnon-g21c): 0 aircraft (registry code 5550102) - [Mckinnon G21D](https://openairdocs.org/model/mckinnon-g21d): 0 aircraft (registry code 5550202) ## STCs approved under this data sheet (33) - [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 SA04837NY](https://openairdocs.org/stc/SA04837NY): Installation of AeroLED's Holdings, LLC., position lights, navigation lights, strobe lights and beacon lights. AeroLED's Holdings, LLC - [STC SA02019SE-D](https://openairdocs.org/stc/SA02019SE-D): Installation of Garmin Model GTN 625/635/650; 725/750 Navigation System. Garmin International Inc. - [STC SA02679SE](https://openairdocs.org/stc/SA02679SE): Increase in gross weight to 12,500 pounds. Snow Goose Aviation LLC - [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 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 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 SA00344BO PAGE 1](https://openairdocs.org/stc/SA00344BO%20PAGE%201): Installation of Parmetheus Plus LED PAR36 and PAR46 taxi and landing lights.. Whelen Aerospace Technologies - [STC SA02632SE](https://openairdocs.org/stc/SA02632SE): Installation of a Pratt and Whitney PT6A-35 engine flat rated to existing horsepower of the original Pratt and Whitney PT6A-28 and associated instrument marking changes.. Teufel Nursery Inc - [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 SA02212AK](https://openairdocs.org/stc/SA02212AK): Replacement of existing landing and/or taxi light reflector and bulbs with high intensity discharge (HID) lighting systems. Seaplanes North LLC - [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 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 SA02119SE PAGE 1](https://openairdocs.org/stc/SA02119SE%20PAGE%201): Installation of Garmin GDL 88 ADS-B UAT Transceiver System. Garmin International Inc - [STC SA02121SE](https://openairdocs.org/stc/SA02121SE): Installation of Garmin GTS 825 (TAS) or GTS 855 (TCAS I) Traffic System. Garmin International Inc - [STC ST02540AT-D](https://openairdocs.org/stc/ST02540AT-D): Installation of replacement fuel tank sealant system. FFC Manufacturing - [STC SA593CH](https://openairdocs.org/stc/SA593CH): Install Champion SlickSTART magneto booster system.. Champion Aerospace LLC - [STC SA1751WE](https://openairdocs.org/stc/SA1751WE): Increase in main fuel tank capacity to 336 gallons.. Atlantic Coast Sea Planes LLC - [STC SA1320WE](https://openairdocs.org/stc/SA1320WE): G-21C: Installation of two United Aircraft of Canada Drawing List Model PT6A-20 engines. G-21D: installation of two United Aircraft of Canada Ltd Model PT6A-20 engines, Alvarez-Calderon wing flaps, and related changes.. Atlantic Coast Sea Planes LLC - [STC SP00400SE](https://openairdocs.org/stc/SP00400SE): Installation of various propeller electrical de-icer models. SMR Technologies - [STC SA01606SE](https://openairdocs.org/stc/SA01606SE): Installation of an electrical/electronics system including contemporary electronic appliances, control devices and interface wiring in accordance with Teufel Nursery, Inc. MDL G21G-00006-01, Revision -1, dated August 12, 2005 or later approved MDL on Aero Planes, LLC, Model G-21G, s/n 1201.. Teufel Nursery Inc - [STC SA8075SW](https://openairdocs.org/stc/SA8075SW): Installation of fiberglass covering. (M-62 SERIES PT-19) (G-73 SCHWEIZER). Razorback Fabrics Inc - [STC SA1008WE](https://openairdocs.org/stc/SA1008WE): Installation of Poly-Fiber covering material.. Poly-Fiber Inc. - [STC SA02168AK](https://openairdocs.org/stc/SA02168AK): Installation of hourmeter airspeed switch. For unpressurized aircraft only. Pressurized aircraft must have pressurization system deactivated.. Avalaska Inc - [STC SA812NE](https://openairdocs.org/stc/SA812NE): Installation of BF Goodrich Model 6975-1 De-Icer kit or BF Goodrich Model 6975-10 De-Icer kit.. BF Goodrich Aerospace - [STC SA3494SW-D](https://openairdocs.org/stc/SA3494SW-D): Installation of a century automatic flight system.. Century Flight Systems 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 SA2809WE](https://openairdocs.org/stc/SA2809WE): Installation of AiResearch TPE331-2UA-203D engines, increase in fuselage length.. McKinnon Enterprises Inc - [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 --- 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.