# TCDS A22SO: Amphibian Aerospace Industries Inc. - Type: Type certificate data sheet - Status: Current - Holder: Amphibian Aerospace Industries Inc. - Revision: 11 - Revised: November 20, 2024 - Product: Aircraft, Large Airplane - Certification basis: Part 21, Part 25, CAR 4b - Registered aircraft: 5, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/0a/7c/0a7c64f6d132222a68d0b8e71553dbee47c9e0ce8be09394b663b0796508dfb6 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID156584545120250210163047.0001 - Page: https://openairdocs.org/tcds/A22SO ## Models (1) As the data sheet lists them. - G-111 (Albatross) ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET NO. A22SO This data sheet, which is part of type certificate No. A22SO, prescribes conditions under which the product for which the type certificate was issued, meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Amphibian Aerospace Industries, Inc. c/o Dunlap Bennett & Ludwig, PLLC 211 Church Street Leesburg, Virginia 20175 Type Certificate Holder Record Amphibian Aircraft Technologies, LLC. transferred type certificate to Amphibian Aerospace Industries, Inc. on November 20, 2024. Amphibian Aircraft International, Inc. transferred type certificate to Amphibian Aircraft Technologies, LLC. on May 1, 2016. Flying Boat, Inc. transferred type certificate to Amphibian Aircraft International, Inc. on July 1, 2010. I. - Model G-111, (Grumman), (Albatross), Transport Category, Amphibian, Approved April 29, 1980 Engine 2 Wright Aeronautical Nine Cylinder 982C9HE3, Reciprocating Engines. Fuel Minimum 100 Octane Low Lead (LL). Oil Engine: MIL-L-6082 Grade 1120 MIL-L-22851 (WEP) Propeller: MIL-O-6081 (Grade 1010) (50%) and MIL-C-6529 (Type II) (50%). For other approved oil combinations, see NOTE 3. Engine Limits BHP RPM MP Altitude Takeoff (5 minutes) 1475 2800 54.5 SL Takeoff (5 minutes) 1475 2800 54.0 1250 Ft. Critical Alt. Maximum Continuous 1275 2500 46.5 SL Maximum Continuous 1275 2500 45.5 2550 Ft. Critical Alt. Propeller and Propeller Limits 1. Number and Type Two Hamilton Standard 43D51-667 Blades Three 7113( )-5 Diameter 11 ft. 2 in. Pitch setting at 54 inch blade station Low 13° High (feathered) 84° Reverse -18° Operation between 2100 and 2200 rpm; 2550 and 2650 rpm is restricted to passing through only. 2. Number and Type Two Hamilton Standard 43D51-669 Blades Three 6915 ( )-7 Diameter 11 ft. 0 in. Pitch setting at 42 inch blade station Low 19.5° High (feathered) 89.5° Reverse -11.5° Operation between 2550 and 2650 rpm is restricted to passing through only. Avoid ground running between 1650 and 1900 rpm when off the low-pitch stop. Page No. 1 2 3 4 Rev. No. 11 5 8 9 A22SO Revision 11 Amphibian Aerospace Industries, Inc. (Grumman) G-111 (Albatross) November 20, 2024 A22SO Page 2 of 4 Airspeed Limits KIAS KCAS Vne (never exceed) 229 228 Vno (normal operating) 206 205 Va (design maneuvering) 134 133 Vfe (max. flap extended) 142 141 Vlo (max. landing gear operating) 131 130 Vle (max. landing gear extended) 151 150 Vlle (max. with landing lights extended) 120 119 Vrb (max. with rudder boost on) 150 149 Vmc (min. control speed-air) 81 80 Center of Gravity The center of gravity range is between 22.5 and 27.5 percent MAC (CG) Range (stations 296.96 and 303.54). Datum Reference Datum is 149 inches forward of jig point located in nose wheel well. The jig point is located by hanging a plumb bob from the small hole drilled in the beam on the aft bulkhead of the nose wheel well. Mean Aerodynamic Chord The leading edge of the MAC is at Station 267.33. (MAC) The length of the MAC is 131.67 inches. Leveling Means Longitudinal leveling is determined by use of plumb bob hung from small hole drilled Longitudinal in the shelf in either main wheel well. Lateral Lateral leveling is determined by use of leveling device on leveling brackets on nose wheel well bulkhead at station 150. Maximum Weights Takeoff: Landplane 30,605 pounds Seaplane 31,365 pounds Landing: Landplane 29,500 pounds Seaplane 31,365 pounds Minimum Crew Two: Pilot and Co-Pilot Number of Passengers Cargo 28 None Maximum Baggage Compartment Capacity (lbs.) Max. Loading C.G. (F.S.) I 700 50 lb/ft2 66.0 II 300 200 lb/ft2 183.5 III 300 200 lb/ft2 183.5 IV 300 200 lb/ft2 186.5 V 750 250 lb./ft2 535.0 Fuel Capacity Capacity Usable Fuel Total Fuel 662 gallons 625 gallons determined with full fuel (3,750 pounds at 297.3 (Arm)) 2 Main Tanks each 31 gallons 312.5 gallons (determine with full fuel) (1,875 pounds at 297.3 (Arm)) See NOTE 1 for Unusable Fuel Data A22SO Page 3 of 4 Oil Capacity Capacity Usable Oil Engine Total Oil 62 gallons 58 gallons (435 lbs. at 262.0) 2 Tanks ea. 31 gallons 29 gallons ( 217.5 lbs. at 262.0) See NOTE 1 for Unusable Oil Data. Propeller Total Oil 7.2 gallons 7.2 gallons (54 lbs. at 210.0) 2 Tanks ea. 3.6 gallons 3.6 gallons (27 lbs. at 210.0) Control Surface Movements Degrees Inches Ailerons Up 17 ± 1 6-1/2 ± 3/16 Down 17 ± 1 6-1/2 ± 3/16 Elevators Up 30 ± 1 12-1/16 ± 13/32 Down 20 ± 1 8-3/32 ± 13/32 Rudder Right 20 ± 1 8-3/32 ± 3/16 Left 15 ± 1 6-1/16 ± 3/16 Trim Tabs Elevator Up 5 ± 1 23/32 ± 1/8 Down 12 ± 1 1-21/32 ± 1/8 Rudder Right 16 ± 1 3-1/8 ± 3/16 Left 26 ± 1 5-1/32 ± 3/16 Aileron Up 18 ± 1 1-5/8 ± 3/32 Down 12 ± 1 1-1/16 ± 3/32 Serial Numbers Eligible 148325, 148327, 148328(See NOTE 3), 148329. (Produced under Production Certificate (PC) Number 23 issued to Grumman Aerospace Corporation, Stuart, Florida, under licensing agreement dated March 9, 1978. This PC is no longer in effect.) 51-7243, 51-7244, 51-7249, 51-7168, 137901, 141282, 148326, 9304, 9308 (Produced under Production Certificate Number 1050 issued to Grumman St. Augustine Corporation, St. Augustine, Florida, under licensing agreement dated 22 December 1981. This PC is no longer in effect.) Certification Basis FAR 21.27, effective February 1, 1965; CAR 4b, effective December 31, 1953, including amendments 1 and 2; FAR 36, effective December 1,1969, including amendments 1 through 3; FAR 25.2. Equivalent Safety Finding: CAR 4b.113 applicable for seaplane takeoff only (See AFM). Production Basis None. Prior to original certification of an aircraft, a FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data, a final inspection of the completed aircraft, and a check of the flight characteristics. A22SO Page 4 of 4 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. Approved equipment for the Model G-111 is shown in Aviation Fire Control, Inc., Report No. 16, "Equipment List." FAA approved Airplane Flight Manual, revised May 27, 1981, is also required. NOTE 1. a. Current weight and balance report including list of equipment included in certificate weight empty, and loading instructions when necessary, must be in each aircraft at the time of original certification and at all times thereafter. b. Refer to FAA Approved Airplane Flight Manual, Sections 7 and 8, for weight and balance and weighing instructions. c. The certificated empty weight must include unusable fuel of 37 gallons (222 lbs. at 300.6 inches (arm)), and unusable oil of 4 gallons (30 lbs. at 262 inches (arm)). NOTE 2. Required placards are listed in Resorts International Drawing RI100F2011. NOTE 3. Aircraft Serial No. 148328 limited to a maximum of 8900 flight hours due to the installation of 7075-T6 spar caps in center section. NOTE 4 Alternate propeller oil can be made by mixing 50% MIL-O-6081 (grade 1010) and 50% of mixture containing one part MIL-H-6083 (Type 1) and three parts MIL-L-6082 (grade 1100). NOTE 5. The intumescent nacelle paint must be inspected per (1) or (2) and if found deficient replaced before further flight: 1. Prior to the first flight of the day. 2. For a series of consecutive day flights the inspection may be conducted at a maximum interval of 24 hours from the last inspection. NOTE 6. Continuous electrical loads applied to the DC electrical system must not exceed 400 amperes. NOTE 7. Deleted ...END... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Grumman Aircraft ENG G-111](https://openairdocs.org/model/grumman-aircraft-eng-g-111): 5 aircraft (registry code 3950410) ## STCs approved under this data sheet (5) - [STC SA2622NM](https://openairdocs.org/stc/SA2622NM): Installation of Precise Flight Pulselite Control Unit in landing/taxi system. (767-200 B17) (DHC-8 101). Precise Flight Inc. - [STC ST04076CH](https://openairdocs.org/stc/ST04076CH): Deletion of the windshield wiper system. Brian Van Wagnen - [STC ST01797WI](https://openairdocs.org/stc/ST01797WI): Interior Installation. Duncan Aviation Inc - [STC SA2031SO](https://openairdocs.org/stc/SA2031SO): Installation of Emergency Escape Path Lighting System.. Jetaire Services Inc - [STC SA301NE](https://openairdocs.org/stc/SA301NE): Installation of seats and furnishings to accommodate 30 passengers and one flight attendant.. 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