# TCDS AR-15: Steward-Davis Incorporated - Type: Type certificate data sheet - Status: Current - Holder: Steward-Davis Incorporated - Revision: 5 - Revised: September 1, 1967 - Product: Aircraft, Large Airplane - Certification basis: CAR 8 - Registered aircraft: 1, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/c3/97/c397293bcade74b5c5c4e57e92edd918430c36c54168211333ab952dd3c43626 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/F26B7B723D9EFEC38525672700600166.0001 - Page: https://openairdocs.org/tcds/AR-15 ## Models (2) As the data sheet lists them. - C-82A Jet Packet - C-82A ## 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. 5 - - - - 5 FEDERAL AVIATION ADMINISTRATION AR-15 Revision 5 FAIRCHILD C-82A C-82A Jet Packet September 1, 1967 TYPE CERTIFICATE DATA SHEET NO. AR-15 This data sheet, which is part of type certificate No. AR-15, 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 Steward-Davis Incorporated 3200 Cherry Avenue Long Beach, California 90807 I - Model C-82A, Approved July 7, 1955 Engines (a) 2 Pratt and Whitney R-2800-85H or 85D or (b) 2 Pratt and Whitney R-2800-34H or 34D Engine limits Refer to Air Force Handbook C-82A, T.O. 1C-82A-1 Propellers 2 Hamilton Standard 33E60/6801-0 (Hamilton Standard Service Bulletin 628 Item 6 Incorporated) Airspeed limits Never exceed: 240 m.p.h. IAS for Serial Nos. 44-22959 through 44-23033 265 m.p.h. IAS for Serial Nos. 44-23034 and subsequent. C.G. range (+318.7) to (+335.4) (Landing gear extended) Maximum weights The airplane may be operated over congested areas at the following weights: AAF C-82A Serial Numbers Take Off Landing 44-22959 through 44-22968 43,560 42,000 All Others 43,560 43,560 The airplane may be operated over non-congested areas at the following weights: 44-22950 through 44-22968 50,000 42,000 44-22969 through 44-22993 and 44-23004 50,000 47,200 44-22994 through 44-23058 except 44-23004 54,000 54,000 45-57733 and subsequent 54,000 54,000 Number of seats Pilot and Copilot (+126). Seats and safety belts are required for other persons as are necessary to operate aircraft for special purpose use. (See Certification basis) Fuel capacity Serial Nos. 44-22989 through 45-57737: 2488 gal. usable (two inboard fuel tanks, 642 gal. ea. and two outboard fuel tanks, 602 gal. ea.) Serial Nos. 45-57738 through 45-57782: 2600 gal. usable (two inboard tanks, 669 gals. ea. and two outboard tanks, 631 gal. ea.) AR-15 2 I - Model C-82A (cont'd) Oil capacity 110 gal. (each nacelle contains one 55 gal. tank.) Operating limitations USAF Handbook T.O. No. 1C-82A-1 as revised March 15, 1954. Additional Limitations to be prescribed at the time of airworthiness certification for the particular special purpose operations in accordance with CAR 8.30. Control surface movements Wing flaps Down 40° Aileron Up 24° Down 12° Elevator Spring Tab Up 30° Down 30° Elevator Up 35° Down 25° Rudder Right 35° Left 35° II - Model C-82A Jet Packet, Approved May 12, 1961 (See NOTE 4) Engines (a) 2 Pratt and Whitney R-2800-85H or 85D or (b) 2 Pratt and Whitney R-2800-34H or 34D or (c) 2 Pratt and Whitney R-2800-85AM2H or AM2D or (d) 2 Pratt and Whitney R-2800-34M1H or M1D and (e) 1 Westinghouse J-30 Jet engine with either (a), (b), (c), or (d) Fuel 100/130 minimum grade aviation gasoline Engine limits (a) For Pratt & Whitney R-2800-85H or 85D or Pratt & Whitney R-2800-34H or 34D, refer to Air Force Handbook C-82A, T.O. 1C-82A-1 (b) Pratt & Whitney R-2800-85AM2H or AM2D or Pratt & Whitney R-2800-34AM1H or AM2D Takeoff Dry 2100 hp., 2800 r.p.m., 54.0 in.hg., S.L. 2100 hp., 2800 r.p.m., 52.5 in.hg., 3400 ft. Wet 2400 hp., 2800 r.p.m., 56.5 in.hg., S.L. 2400 hp., 2800 r.p.m., 56.0 in.hg., 1000 ft. Maximum continuous Low blower 1800 hp., 2600 r.p.m., 45.0 in.hg., S.L. 1800 hp., 2600 r.p.m., 44.0 in.hg., 6500 ft. High blower 1600 hp., 2600 r.p.m., 46.5 in.hg., 10,000 ft., 1600 hp., 2600 r.p.m., 45.0 in.hg., 16 ,200 ft. or 1500 hp., 2500 r.p.m., 43.0 in.hg., 10,000 ft. 1500 hp., 2500 r.p.m., 42.0 in.hg., 16,000 ft. (c) Jet-Pack 1600: Oil Fuel Pressure Pressure Tail Pipe Setting R.P.M. (p.s.i.) (p.s.i.) Temperature Light-off Over 10 4 to 17 Below 700°C* 2200 Idle 6000 10 to 90 4 to 20 391° to 613°C Approach Idle 10,000 25 to 90 25 to 85 350° to 580°C Takeoff Standby 14,700 35 to 90 100 to 200 Below 675°C Normal Rated 15,700 37 to 100 100 to 210 Below 675°C Maximum (15 min.) 17,000* 40 to 125* 180 to 280 Below 700°C* Oil temperature must never exceed 120°C* *Instrument red line 3 AR-15 II - Model C-82A (cont'd) Propellers 2 Hamilton Standard 33E60/6801/0 (Hamilton Standard Service Bulletin 628 Item 6 Incorporated) Airspeed limits Never exceed: 240 m.p.h. IAS for Serial Nos. 44-22959 through 44-23033 265 m.p.h. IAS for Serial Nos. 44-23034 and subsequent. C.G. range (+318.7) to (+335.4) (Landing gear extended) Empty weight C.G. range None Maximum weights With the jet engine operating and with the servo tab installed per Dwg. SDC-140, the airplane may be operated over congested areas at the weights presented below. These weights are also the maximum allowed during operations over non-congested areas, with the jet engine operating or not operating. With the jet engine not operating during flight over congested areas, the maximum weights allowed are the same as for the C-82A over congested areas. AAF C-82A Serial Numbers Take Off Landing 44-22959 through 44-22968 50,000 42,000 44-22969 thru 44-22993 and 44-23004 50,000 47,200 44-22994 thru 44-23058 except 44-23004 54,000 54,000 45-57733 and subsequent 54,000 54,000 Number of seats Pilot and Copilot (+126). Seats and safety belts are required for other persons as are necessary to operate aircraft for special purpose use. (See Certification basis) Fuel capacity Serial Nos. 44-22989 through 45-57737 : 2488 gal. usable (two inboard fuel tanks, 642 gal. ea. and two outboard fuel tanks, 602 gal. ea.) Serial Nos. 45-57738 through 45-57782: 2600 gal. usable (two inboard tanks, 669 gals. ea. and two outboard tanks, 631 gal. ea.) Oil capacity (For jet engine) 4 gal. (For reciprocating engines) 110 gal. (Each nacelle contains one 55 gal. tank) Operating limitations USAF Handbook T.O. No. 1C-82A-1 as revised March 15, 1954; with FAA approved Steward-Davis Inc., airplane Flight Manual Supplement to USAF Handbook T.O. No. 1C-82A-1 (Report JPA 1073 dated January 19, 1962). Additional Limitations to be prescribed at the time of airworthiness certification for the particular special purpose operations in accordance with CAR 8.30. Control surface movements Wing flaps Down 40° Aileron Up 24° Down 12° Elevator Tab Up 30° Down 30° Elevator Up 35° Down 25° Rudders Right 35° Left 35° III - Model C-82A Jet Packet, Approved July 23, 1963 (See NOTE 6) Engines (a) 2 Pratt and Whitney R-2800-85H or 85D or (b) 2 Pratt and Whitney R-2800-34H or 34D or (c) 2 Pratt and Whitney R-2800-85AM2H or AM2D or (d) 2 Pratt and Whitney R-2800-34M1H or M1D and (e) 1 Westinghouse J34-WE-34-1 Jet engine with either (a), (b), (c), or (d) Fuel 100/130 minimum grade aviation gasoline AR-15 4 III - Model C-82A (cont'd) Engine limits (a) For Pratt & Whitney R-2800-85H or 85D or Pratt & Whitney R-2800-34H or 34D, refer to Air Force Handbook C-82A, T.O. 1C-82A-1 (b) Pratt & Whitney R-2800-85AM2H or AM2D or Pratt & Whitney R-2800-34 AM1H or AM2D Takeoff Dry 2100 hp., 2800 r.p.m., 54.0 in.Hg., S.L. 2100 hp., 2800 r.p.m., 52.5 in.Hg., 3400 ft. Wet 2400 hp., 2800 r.p.m., 56.5 in.Hg., S.L. 2400 hp., 2800 r.p.m., 56.0 in.Hg., 1000 ft. Maximum continuous Low blower 1800 hp., 2600 r.p.m., 45.0 in.Hg., S.L. 1800 hp., 2600 r.p.m., 44.0 in.Hg., 6500 ft. High blower 1600 hp., 2600 r.p.m., 46.5 in.Hg., 10,000 ft. 1600 hp., 2600 r.p.m., 45.0 in.Hg., 16,200 ft. or 1500 hp., 2500 r.p.m., 43.0 in.Hg., 10,000 ft. 1500 hp., 2500 r.p.m., 42.0 in.Hg., 16,000 ft. (c) Jet-Pak 3400 (J34-WE-34-1) Ratings Maximum continuous static thrust, lb., r.p.m., at sea level 2650 - 11800 Takeoff static thrust (5 minutes), lb., r.p.m. at sea level 3250 - 12500 Standby idle: Takeoff, lb., r.p.m., at sea level 1750 - 10500 Landing, lb., r.p.m., at sea level 200 - 4375 Maximum permissible temperature limits: Takeoff 682°C - 1260°F. Maximum continuous 635°C - 1175°F. Starting (5 sec.) 816°C - 1500°F. Acceleration (15 sec.) 760°C - 1400°F. Oil inlet 88°C - 190°F. Turbine inlet 810°C - 1490°F. Any engine having Engine Bulletin No. 294 incorporated will have individual turbine outlet temperature maximum values corresponding to the maximum turbine inlet temperature for takeoff on a 100°F day. Maximum continuous power is obtained at maximum continuous r.p.m. with the exhaust nozzle set for 100°F. day and the gas outlet temperature resulting, although this temperature will be lower than at takeoff. Fuel and oil inlet pressure limits: Fuel: Minimum at fuel line connection to engine 10 p.s.i.g. Operating fuel inlet gage pressure 20 + 10 p.s.i.g. Oil: Minimum at oil line connection to engine 4 p.s.i.g. Operating oil gage pressure 20 - 1 0 p.s.i.g. Propellers 2 Hamilton Standard 33E60/6801-0 (Hamilton Standard Service Bulletin 628 Item 6 Incorporated) Airspeed limits Never exceed: 240 m.p.h. IAS for Serial Nos. 44-22959 through 44-23033 265 m.p.h. IAS for Serial Nos. 44-23034 and subsequent. C.G. range (+318.7) to (+335.4) (Landing gear extended) 5 AR-15 Empty weight C.G. range None Maximum weights With the jet engine airworthy and operable and with the servo tab installed in accordance with Drawing SDC-140, the aircraft may be operated over congested areas at the following weights if the aircraft altitude is 3000 feet above the terrain or the altitude which will enable the aircraft to "drift down" outside the limits of the congested area, whichever is greater. Over congested areas with an aircraft altitude below 3000 feet above the terrain, or the "drift down" altitude, whichever is greater, the jet engine must be operating on standby power to permit flight at the following weights. The following weights are the maximum allowed during flight over uncongested areas, with or without the jet engine operating. Over congested areas with an aircraft altitude below 3000 feet above the terrain or the "drift down" altitude, whichever is greater, when the jet engine is not operating, the maximum weight allowed is the same as for the C-82A over congested areas. AAF C-82A Serial Numbers Take Off Landing 44-22959 through 44-22968 50,000 42,000 44-22969 thru 44-22993 and 44-23004 50,000 47,200 44-22994 thru 44-23058 except 44-23004 54,000 54,000 45-57733 and subsequent 54,000 54,000 No. of seats Pilot and Copilot (+126). Seats and safety belts are required for other persons as are necessary to operate aircraft for special purpose use. (See Certification basis) Fuel capacity Serial Nos. 44-22989 through 45-57737: 2488 gal. usable (two inboard fuel tanks, 642 gal. ea. and two outboard fuel tanks, 602 gal. ea.) Serial Nos. 45-57738 through 45-57782: 2600 gal. usable (two inboard tanks, 669 gals. ea. and two outboard tanks, 631 gal. ea.) Oil capacity (For jet engine) 4 gal. (For reciprocating engine) 110 gal. (Each nacelle contains one 55 gal. tank) Operating limitations USAF Handbook T.O. No. 1C-82A-1 as revised March 15, 1954; with FAA approved Steward-Davis Inc., airplane Flight Manual Supplement to USAF Handbook T.O. No. 1C-82A-1 (Report JPA 1338 dated June 14, 1963). Additional Limitations to be prescribed at the time of airworthiness certification for the particular special purpose operations in accordance with CAR 8.30. Control surface movements Wing flaps Down 40° Aileron Up 24° Down 12° Elevator Tab Up 30° Down 30° Elevator Up 35° Down 25° Rudders Right 35° Left 35° Data Pertinent to All Models Datum 317.17 inches forward of the front spar jig point. Leveling means Fuselage floor Serial Nos. eligible AAF C-82A Serial Numbers 44-22959 thru 44-23058, 45-57733 thru 45-57832, 48-568 thru 48-587 C-82A's must be modified before they are approved as Jet Packets. Certification basis CAR 8 as amended to October 11, 1950 Type Certification AR-15 issued July 7, 1955 Production basis None. No aircraft may be produced under this approval. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. AR-15 6 NOTE 1. Current weight and balance report, including list of equipment included in certificated empty weight, and loading instructions, must be provided for each aircraft at the time of original certification. NOTE 2. Night and IFR (Instrument Flight Rules) flights are permitted provided the aircraft is properly equipped for such operations in accordance with CAR 43. NOTE 3. These aircraft do not comply with international airworthiness standards of the ICAO Annex 8 Part II; therefore, flights are not authorized over foreign countries. Special permission must be obtained from foreign countries to conduct flight over their territories. NOTE 4. For aircraft to be eligible for operation under Section II, the provisions of Steward- Davis Top Drawings JPA-1109 or JPA-1110 must be incorporated. NOTE 5 Placard required on instrument panel in full view of pilot: "Avoid operation between 1550 and 1650 r.p.m." Tachometers to be marked with red arc over this restricted speed range. NOTE 6 For aircraft to be eligible for operation under Section III, the provisions of Steward-Davis Engineering Report JPA 1358 must be incorporated. .....END..... ``` ## ADs (1, in force first) - [AD 63-10-01](https://openairdocs.org/ad/63-10-01): Crankshaft Assembly · Steward-Davis C-82A and C-82A Jet Packet. Effective Jun 6, 1963 ## Registered aircraft by registry model (OpenAirDocs) - [Fairchild C-82A](https://openairdocs.org/model/fairchild-c-82a): 1 aircraft (registry code 3372004) ## STCs approved under this data sheet (4) - [STC SA4503NM](https://openairdocs.org/stc/SA4503NM): Remove original cloth covering and install Ceconite covering. Ceconite Division of Poly-Fiber 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 SA20SO](https://openairdocs.org/stc/SA20SO): Cargo compartment floor modification for special cargo.. Miami Aircraft Maint Inc - [STC SA22SO](https://openairdocs.org/stc/SA22SO): Four Aerojet General rocket engines15KS100A1 and static pressure source.. Miami Aircraft Maint 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.