# STC SA3820SW - Type: Supplemental type certificate - Status: Current, Reissued - Holder: Greenwich Aircraft Corporation - Description: Installation of P&W Canada PT6A-65AR or PT6A-67R engines. - Status date: March 31, 2020 - Data sheets: A-669, A-669, A-669, A-669 - Certificate PDF: https://openairdocs.org/files/sha256/9a/05/9a05987ecc602feed721a209dd8de8764dc28f8109073f11e4a97fc3c7319022 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/2A7A46697491E8DB8625871A005BCD5A.0001 - Page: https://openairdocs.org/stc/SA3820SW ## ADs that name it None. ## Approved models (4) - The Boeing Company DC3A-S1C3G (TCDS A-669) - The Boeing Company DC3A-SC3G (TCDS A-669) - The Boeing Company DC3C-R-1830-90C (TCDS A-669) - The Boeing Company DC3C-S4C4G (TCDS A-669) ## What the certificate says Read from the PDF's text layer, without the form's printed wording; the layout is lost and the order can differ. The PDF is the record. FAA Form 8110-2 (7/19) Page 1 of 10 Number: SA3820SW Parts 4b of the Civil Aviation Regulations and Part 25 of the Federal Aviation Regulations. Original Product – Type Certificate Number: A-669 Make: McDonnell-Douglas Model: DC3C-SC3G, -S1C3G, -S4C4G, -R-1830-90C Installation of Pratt & Whitney Canada PT6A-65AR or PT6A-67R engines. Modified in accordance with Drawing List SA-DL1-DC3, Rev. M, dated 9/03/93, with E.O. No. B-1, dated 9/03/93 for Dwg. No. 71-70-00, and Teleflex Drawing List SK-4923-0, dated 4/9/87, or later FAA approved revisions. The following Airplane Flight Manual or later FAA Approved Revisions are required as appropriate: FAA Approved Airplane Flight Manual (AFM) dated 8/4/87, with Change 3, dated 12/14/93, when the airplane is modified in accordance with Drawing List SA-DL1-DC3, Rev. M, dated 9/03/93. (See continuation sheet 3 of 10) Date of Application: July 18, 1985 Date Reissued: 07/23/93; 9/15/93; 01/24/2020; 03/31/2020 Date of Issuance: August 4, 1987 Date Amended: 12/22/87, 7/27/89, 12/14/93 Rev. 3 Signature Title Jim Grigg Manager, Fort Worth A CO Branch, Compliance & Airworthiness Division Aircraft Certification Service Greenwich Aircraft Corporation 619 Van Buren Avenue Oxford, MS 38655 FAA Form 8110-2 (7/19) Page 10 of 10 FAA Form 8110-2 (7/19) Page 10 of 10 Transfer the ownership of Supplemental Type Certificate Number: SA3820SW To (Name and address of transferee) From (Name and address of grantor) United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3820SW FAA Form 8110-2 (7/19) Page 10 of 10 Date of Issuance: August 4, 1987 Date Amended: December 14, 1993 Date of Reissuance: March 31, 2020 The conditions & limitations of Aircraft Specification No. A-669 apply except as follows: This specification, which is a part of Supplemental Type Certificate No. SA3820SW, prescribes conditions and limitations under which the product for which the Supplemental Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations. A copy of this Supplemental Type Certificate Specification shall be maintained as part of the modified aircraft’s permanent records. Supplemental Type GREENWICH AIRCRAFT CORPORATION Certificate Holder 7727 Airport Road Waco, Texas 76708 Model: DC3C-SC3G, -S1C3G, -S4C4G, -R-1830-90C Engine: 2 Pratt & Whitney Canada PT6A-65AR, or 2 Pratt & Whitney Canada PT6A-67R Fuel: Pratt & Whitney of Canada Service Bulletin 13044 (See NOTE 9) Oil: Pratt & Whitney of Canada Service Bulletin 130001 (See NOTE 10) Engine Limits Ratings Takeoff (5 min) Shaft horsepower 1230 Maximum continuous at sea level Shaft horsepower 1165 The engine ratings are based on static sea level conditions (No external accessory loads and no airbleed). The PT6A-65AR maximum continuous rating is available to 101 deg F Air Inlet Temperature (AIT) and takeoff rating is available to 84 deg F AIT. The PT6A-67R maximum continuous rating is available to 115 deg F AIT and takeoff rating is available to 99 deg F. RPM Limits (See NOTE 5) Engine Propeller Torque Ng Np lb. ft. RPM % RPM % Takeoff (5 min) 3800 39,000 104 1700 100 Maximum Continuous 3600 39,000 104 1700 100 Transient overspeed 5100 39,000 104 1870 110 (See NOTE 5) For propeller ground operation, See NOTE 6. United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3820SW FAA Form 8110-2 (7/19) Page 10 of 10 Date of Issuance: August 4, 1987 Date Amended: December 14, 1993 Date of Reissuance: March 31, 2020 Inter-Turbine Temperature Takeoff (5 min) 820 deg C Max Continuous 820 deg C Starting transient (5 sec) 1000 deg C Fuel Pressure Fuel: Minimum pressure at inlet to the engine fuel system shall not be less than 5 p.s.i. above true vapor pressure of the fuel. For emergency operation, with airframe boost pump inoperative, the inlet pressure must be such that vapor/liquid ratio does not exceed 0.1 for continuous operation and does not exceed 0.3 for more than 10 hours in a pump overhaul life. Maximum pressure at inlet to fuel system: 50 p.s.i. Maximum 135 psig Normal 90-135 psig Minimum 60 psig Oil Inlet Temperature (See NOTE 8) Maximum 110 deg C Minimum for takeoff 0 deg C Minimum for starting -40 deg C Propeller (with PT6A-65AR) 2 Hartzell HC-B5MP-3C/M10876ASK Propeller (with PT6A-67R) 2 Hartzell HC-B5MA-3J/M10876ASK Propeller limits Diameter 110.7 – 111.2 inches Pitch settings (42 in. sta.) Low Pitch +13 deg +/- .2 deg Feather +79 deg +/- .5 deg Reverse -11 deg +/- .5 deg NOTE: Model M10876ASK propeller blades which acquire 48,000 hours total time in service must be retired. Airspeed Limits CAS kts mph VMO (maximum operating) 180 207 Va (maneuvering) 112 128 United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3820SW FAA Form 8110-2 (7/19) Page 10 of 10 Date of Issuance: August 4, 1987 Date Amended: December 14, 1993 Date of Reissuance: March 31, 2020 Vlo (landing gear operation) 144 165.5 Vle (landing gear extended) 144 165.5 Vfe (flaps extended 1/4) 135 155.5 Vfe (flaps extended 1/2) 99 114 Vfe (flaps extended 3/4 to full) 97 111.5 Maximum Operating Altitude 24,000 feet pressure altitude (See NOTE 14): C. G. Range Fuselage Sta. 239.6 inches (11% MAC) @ 18000 lbs and below. Fuselage Sta. 242.35 inches (13% MAC) @ 26900 lbs. Fuselage Sta. 263.1 inches (28% MAC) @ 26900 lbs. and below. Straight line deviation between points. Maximum Weight Takeoff 26,900 lbs. Landing 26,900 lbs. Maximum Zero Fuel Weight 25,400 lbs. Minimum Empty Weight 15,100 lbs. (See AFM) Minimum Crew 2 (pilot and copilot) Maximum Passengers See NOTE 13 Maximum Cargo See NOTE 13 **FUEL CAPACITY USABLE CAPACITY TOTAL CAPACITY** TANK U.S. GALLONS POUNDS U.S. GALLONS POUNDS Main L.H. 118 790.6 118.3 792.6 Main R.H. 118 790.6 118.3 792.6 Fwd Aux L.H. 202 1,353.4 204 1,366.8 Fwd Aux R.H. 202 1,353.4 204 1,366.8 Aft Aux L.H. 199 1,333.3 200 1,340 Aft Aux R.H. 199 1,333.3 200 1,340 NOTE: Weights based on fuel density of 6.7 pounds per U.S. Gallon. Oil capacity 1 tank integral with each engine, 2.5 U.S. Gallons United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3820SW FAA Form 8110-2 (7/19) Page 10 of 10 Date of Issuance: August 4, 1987 Date Amended: December 14 1993 Date of Reissuance: March 31, 2020 Maximum usable oil, 1.5 U.S. Gallons. Required Equipment In addition to the pertinent required basic equipment specified in CAR 4b and FAR 25 (for the turbopropeller installation) refer to “Required Equipment List” Section 6 of Airplane Flight Manual. This installation requires Goodrich H-2-445 main wheel brakes. Specification Pertinent to This Model Datum Fuselage Station “0” (40 inches aft of tip of nose). Leveling Pins on outside of fuselage at station 390.5 and 411.5 below windows (fore and aft leveling). Means Pins in left and right hand center section station 222 (lateral leveling). Control Elevator up 12 +/- 1/8 inches, down 8 +/- 1/8 in. Surface (measured from inboard trailing edge of elevator) Aileron up 13 +/- 1/8 in, down 8 +/- 1/2 in, (measured from inboard trailing edge of aileron) Rudder left 18 +/- 1/4 in., right 18 +/- 1/4 in. (measured from lower trailing edge of rudder) Elevator trim tab up 9/16 +/- 1/8 in, down 2 1/2 +/- 1/8 inches (measured from inboard trailing edge of trim tab). Certification (1) FAR 21 Subpart E – 21.10lb Basis (2) SFAR 13 effective September 10, 1954 (3) CAR 4b effective December 31, 1953, except where superseded by FAR 25 requirements. (4) FAR 25 sections as amended by Amendments 25-1 through 25-54. (5) FAR 36 including Amendments 36-1 through 36-12. (6) FAR 27 Fuel Venting and Exhaust Emission requirement for Turbine Powered Airplanes. **NOTE 1** (a) Current weight and balance report including list of equipment included in certificated weight empty, and loading instructions, 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). (b) System fuel must be included in the empty weight of the airplane. System fuel is defined as the fuel required to fill the fuel system up to the fuel tank outlet plus the fuel tank unusable fuel quantity. Full oil tank and full hydraulic tank fluids must also be included in the empty weight of the airplane. United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3820SW FAA Form 8110-2 (7/19) Page 10 of 10 Date of Issuance: August 4, 1987 Date Amended: December 14, 1993 Date of Reissuance: March 31, 2020 (c) The “unusable fuel” is that amount of fuel in the tanks which is unavailable to the engine under critical flight conditions as defined in FAR 25.959 and may be obtained by taking the difference between the total fuel capacities and “usable” tank capacities shown in this specification. The “unusable fuel” must be included in the empty weight or be suitably accounted for in the airplane weight and balance report. (d) The engines utilize fuel only from the nacelle main tanks. (e) A crossfeed system is provided to feed fuel from an opposite nacelle tank to the engine. NOTE 2 This airplane is approved for Day, Night, VFR, and IFR. Refer to Airplane Flight Manual for limitations and required operating procedures. NOTE 3 All Airworthiness Directives applicable to FAA Aircraft Specification A-669 also are effective for the DC3C as modified by this STC. The following Airworthiness Directives do not apply to DC3C aircraft modified according to this STC: 43-12-02 Engine Mount Fittings 47-06-07 Fire Ext. Trigger 47-33-02 Cowl Flap Hyd Lines 47-51-12 Carburetor Airscoop 48-05-01 Oil Shutoff Valve ‘O’ Rings 48-17-01 Fire Prevention Modifications 50-46-01 Oil Tank Standpipe 51-02-01 Ramp Type Door Rework 52-25-01 Vacuum System Rework 56-20-05 Prop Operating Limits 58-08-03 CB Fire Extinguisher System 60-16-03 Geared Rudder Tab 77-10-02 Fire Resistance of Prop Feather System United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3820SW FAA Form 8110-2 (7/19) Page 10 of 10 Date of Issuance: August 4, 1987 Date Amended: December 14, 1993 Date of Reissuance: March 31, 2020 Ailerons permanently identified as complying with the balancing procedure of this STC are considered to comply with the aileron balancing procedures specified in AD 41-47-01. The elevator and rudder balance procedures of AD 41-47-01 are still appropriate and required. NOTE 4 Airworthiness Directives currently in effect or issued subsequent to the date of this STC, which involve the Pratt & Whitney PT6A-65AR engine or the Hartzell HC-B5MP-3C/M10876B propellers, are applicable to the engines or the propellers installed under this STC, and applicability statement of such Airworthiness Directives notwithstanding. NOTE 5 Maximum overspeed limit is as specified for transient overspeed. If these limits are exceeded, consult P&WACL Maintenance Manual No. 3028042, page 604 for disposition of engine or gear reduction box. NOTE 6 Ground Operation: A. Stabilized ground operation below 900 rpm prohibited, except when propeller is feathered operation at or below 400 rpm is permissible. B. Stabilized ground operation between 1170 and 1400 rpm is prohibited. Taxi between 900 and 1170 rpm in order to keep operation through 1170 to 1400 rpm range to a minimum in cross tail winds. C. Advance through 1170 – 1400 rpm only after aircraft is lined up with the runway for takeoff. NOTE 7 Oil pressure at 75% Ng (27,000 rpm) gas generator speed and above with an oil temperature of 140 to 160 deg F: 105 – 135 p.s.i.g. Below 75% Ng (27,000 rpm) gas generator speeds: 60 p.s.i.g. (min). Extreme cold starts oil pressure may reach 200 p.s.i. NOTE 8 Oil temperature range continuous from minus 40 deg F (-40 deg C) to 210 deg F (99 deg C). **NOTE 9 APPROVED FUELS** Fuel Specification Jet A ASTM 1655 Jet A-1 ASTM 1655 Jet B ASTM 1655 JP-4 ASTM 1655 or MIL-T-5624 JP-5 MIL-T-5624 JP-8 MIL-T-83133 The use of aviation gasoline (AVGAS) is not approved. For additional information see P&WACL Service Bulletin No. 13044. United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3820SW FAA Form 8110-2 (7/19) Page 10 of 10 Date of Issuance: August 4, 1987 Date Amended: December 14, 1993 Date of Reissuance: March 31, 2020 **NOTE 10 APPROVED LUBRICATING OILS** Aeroshell Turbine Oil 500 ROYCE TURBINE OIL 500 Mobil Jet Oil II TURBONYCOIL 525-2A Mobil Jet Oil 254 Stauffer Jet II Castrol 5000 Esso/Exxon Turbo Oil 2380 Only type II oils conforming to P & WC Service Bulletin No. 13001 are acceptable. NOTE 11 Fuel anti-icing additives conforming to specifications MIL-I-27686D or MIL-I-27686E may be used, at a concentration not exceeding 0.15% by volume. NOTE 12 Noise Characteristics: No acoustical change was shown under the provisions of FAR Paragraph 21.93(b). Noise measurements taken in flyover tests have demonstrated that the noise levels of the PT6A-65AR powered aircraft are no noisier than the noise levels of the R-1830 powered aircraft, at their respective maximum takeoff and landing weights available for a sea level airport at ISA+10 deg C (ISA +18 deg F). NOTE 13 The aircraft is approved with the following limitations: “No passengers or cargo may be carried until an FAA approved interior is installed.” See FAR 91.47 for maximum passengers when an FAA approved interior is installed, except as allowed under maximum cargo. NOTE 14 Engine and airframe certificated operating temperature limits; min. -40 deg C (-40 deg F) to ISA +34 deg C (ISA +61 deg F) maximum. NOTE 15 The location of the cockpit has not been evaluated for compatibility with the icing equipment. Any approvals for flight into known icing conditions must be coordinated with the FAA Southwest Region Special Certification Office, Fort Worth, Texas. -END- ## Every issue (2) - March 31, 2020: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/9a/05/9a05987ecc602feed721a209dd8de8764dc28f8109073f11e4a97fc3c7319022) - December 14, 1993: Amended, Historical. [certificate](https://openairdocs.org/files/sha256/2e/23/2e23bda295f89528e523ea1f5e542bdab5e512aa996bab07402002deff1990fd) --- From OpenAirDocs.org, an independent open copy of FAA data. Only the Federal Register edition on govinfo.gov is the official legal text of an AD.