STC SA2221NM

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number SA2221NM This certificate issued to: UNITED STATES AIRCRAFT CORPORATION Part 40 of the Civil Air Regulations. Dated December 31, 1953 (See page 3 of this STC for the completed certification basis) Original Product Type Gerlificate Number: A-669 Make: McDonnell Douglas Corporation (MDC) Minded: DC3C, S/N 26744 (DC3C-R-1830-90C) Description of Type Design Change: 205 an u or tater a prove race ons. Chired safe Al orat: Corporation engines, Hartzell HC-B5MP-3C/M1086B propellers,and associated modifications to Installation of Pratt & Whitney of Canada PT6A-45R FAA approved Airplane Flight Manual Report 0046, dated December 1, 1983, or later FAA approved revisions for USAC Model DC3-TP is required as part of this installation.

Limitations and Conditions: MDC DC3C S/N 26744 only. Data pertaining to this modification are considered The type design changes described above are applicable to inadequate for duplication on other aircraft of this type. The limitations & conditions of Aircraft Specification A-669 apply except as outlined in Supplemental Aircraft Specification SA2221N documented in the continuation sheets of this STC. A copy of this STC must be included in the permanent records of this airplane as modified in accordance with this STC.

Date of Application: April 17, 1978 Date Reissued:

Date of cassance December 1, 1983 Date Amended: NOV. 18, 1984 FEDERAL AVIATION Pry dine cith of the Administratyr TOMINISTRALO Manager, Western Aircraft Certification Office (Tstle)

47.

FAA FORK 8110-2 (10-68) Page 1 of 10

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA2221NM

CERTIFICATION BASIS (CONTINUED) Based upon the application for STC, dated April 17, 1978, the applicable régulations are:

(1) FAR 21 Subpart E - Supplemental Type Certificate includes FAR 21.111 thru

21.119, FAR 21.101(a) & (c), FAR 21.31 thru FAR 21.39, FAR 21.53, FAR 21.93(b).

(2) SFAR 13 effective September 10, 1954.

(3) CAR 4b effective December 31, 1953, except where superseded FAR 25 requirements.

(4) FAR 25 sections as amended by Amendments 25-1 thru 25-43.

(5) FAR 36 including Amendments 36-1 thru 36-9.

(6) SFAR 27 Fuel Venting and Exhaust Emission requirement for Turbine Powered Airplanes.

SUPPLEMENTAL AIRCRAFT SPECIFICATION NO. SA2221NM The conditions & limitations of Aircraft Specification No. A-669 apply except as follows:

This specification, which is a part of Supplemental Type Certificate No. SA2221NM, prescribes conditions and limitations under which the product for which the Supplemental Tupe 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 UNITED STATES AIRCRAFT CORPORATION Certificate Holder 4511 Empire Avenue Hangar Five Burbank, California 91505-1172

FAA FORM 8110-2-1 (10-69)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA2221NM Model: DC3-TP (DC3-P-1830-9DC)/C47B as modified by STC SA22211M Approved December 1, 1983.

Engine 2 Pratt & Whitney of Canada PTA6-45R.

Fuel Pratt & Whitney of Canada Service Bulletin 3044 (See NOTE 10).

011 Pratt & Whitney of Canada Service Bulletin 3011 (See NOIE 11).

Engine Limits Ratings Takeoff (5 min.)

Equivalent shaft horsepower 1254 Shaft horsepower 1198 vet thrust, ibs. 140 Maximum continuous at sea level Equivalent shaft horsepower 1070 Shaft horsepower 1020 Jet thrust, 1bs. 127 The engine ratings are based on static sea level conditions. No external accessory loads and no airbleed. The PT6A-45R maximum continuous rating.is available to 92°F Air Inlet Temperature and takeoff is available to 73F Air Inlet Temperature.

RPM Limits (See NOTE 5) TORQUE Ng Np

PSI RPM RPM Takeoff (5 min.) 44.24 39,000 104 1700 100 Maximum continuous 37.68 39,000 104 1700 100 Transient overspeed (5 sec.) 61.0 39,000 104 1870 110 (See NOTE 5).

For propeller ground operatrion (See NOTE 6).

47.

PAGE 4 OF 1OPAGES

Vinitro States of Samerica Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA2221NM Inter-Turbine Temperature Takeoff (5 min.) 845°C Max continuous 812°C Starting transient (5 sec.)

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, it 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.g.

011 Pressure (See NOTE 7).

Maximum 135 psig Normal 90-135 psig Minimum 60 psig O11 Iniet Temperature (See NOTE 8).

Maximum 99°C Minimum for takeoff +10°c Minimum for starting -40°C Propeller and 2 Hartzell HC-B5MP-3C/M10876B.

Propeller Limits Diameter 110.7 - 111.32 Pitch settings (42 in. sta.)

Low pitch +13°+ •2° Feather +79°+ -5° Reverse - 11°+ -5° 47 PAGE 5 OF 10PAGES

inited Scatco of Slmerica Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA2221NM Airspeed Limits CAS * IAS

KTS MPH KTS MPH VO (maximum operating) 187 215 184 21165 VA (maneuvering) 111 127-5 107 123 VLO (landing gear operation). 144 165.5 141 162.5 VLE (landing gear extended) 144 165.5 141 162.5 VFE (flaps extended 1/4) 135 155.5 133 153 VFE (flaps entended 1/2) 99 114 97 111.5 VFE (flaps extended 3/4 to full 97 11165 95 • 109.5 Maximum Operating Altitude 20000 feet pressure altitude (See NOTE 15).

C. G. Range Fuselage Sta. 242.35 inches (13% MAC) Fuselage Sta. 263.1 inches (28% MAC) Maximum Weight Takeoff 26,900 1bs.

Landing 26,900 1bs.

Minimum Crew 2 (pilot and copilot) Maximum Passengers See NOTE 14 Maximum Baggage Baggage Compartment "B" Max. Wt. 800 lbs.

Baggage Compartment "H" Max. Wt. 350 ibs.

(For further information see ATS Weight & Balance report 1291).

Fuel Capacity USABLE CAPACITY TOTAL CAPACITY TANK U.S.GALLONS POUNDS U.S. GALLONS POUNDS Main L.H. 185.0 1.240 195.0 1,307 Main R.H. 185.0 1,240 195.0 1,307 Auxiliary L.N. 185.5 1,243 187.0 1,253 Auxiliary R.H. 185.5 1,243 187.0 1,253 TOTAL 741.0 4,960 704.0 5,120

47.

PAGE 6 OF 1OPAGES

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA22211M NOTE: WEIGHTS BASED ON A FUEL DENSITY OF 6.7 POUNDS PER U.S.GALLON.

Oil capacity 1 tank integral with each engine, 2.5 U.S. Gallons.

Total usable oil, 1.5 U. S. Gallons.

Serial No. Eligible 26744 ONLY 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" USAC Report 0047. Dated 11/21/83. Rev. N/C.

Specifications Pertinent to this Model Datum Fuselage station "O" (40'aft of tip of nose).

Leveling Means Pins on outside of fuselage at station 3905 and 411.5 below windows (fore and aft leveling). Pins in left and right hand center section station 222 (lateral leveling).

Control Surface Elevator up 12 * 1/8 inches, down 8 + 1/8 inches. Aileron up Movements 13 * 1/8 inches, down 8 + 1/2 inches. Rudder left 26 1/4 inches, right 26 1/4 inches. (See Note 9).

Production Basis None Export Eligibility None Certification (1) FAR 21 Subpart E - Supplemental Type Certificate Basis includes FAR 21.111 through 21.119, FAR 21.101(a) & (c), FAR 21.31 through 21.39, FAR 21.93(b).

(2) SEAR 13 effective September 10, 1954.

(3) CAR 4b effective December 31, 1953, except where superceded FAR 25 requirements.

FAR 25 sections as amended by Amendments 25-1 through

25-43.

(5) FAR 36 including Amendments 36-1 through 36-9.

(6) FAR 27 Fuel Venting and Exhaust Emission requirement for Turbine Powered Airplanes.

FAA FORM 8110-2-1 (10-69) PAGE 7 OF 1OPAGES

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA2221NM 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 airpiane.

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.

(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 CAR 4b.416 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 center wing forward main tanks.

(e) A crossfeed system is provided to feed fuel from an opposite center wing forward main tank to engine.

(£) Fuel must be loaded in the following order:

(1) Fill center wing forward main tanks symmetrically.

If fuel load exceeds capacity of center wing forward tanks, service center wing auxiliary transfer tanks symmetrically.

NOTE 2 The following placards shall be placed in the locations noted:

(a) On the instrument panel in full view of the pilots: &This airplane shall be operated in compliance with the operating limitations specified in the FAA Approved Airplane Flight Manual."

(b) On upper center portion of copilot's instrument panel:

VMO Operating 184 KIAS VA Maneuvering 107 KIAS VLO Landing Gear Operation 141 KIAS

FAA FORM B110-2-1 (10-69) PAGE 8 OF10PAGES

Finitro States of Smerica Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Numbes SA2221NM NOTE 2(con't ) VLE Landing Gear Extended 141 KIAS VFE Flaps Landing 1/4 133 KIAS 1/2 97 KIAS 3/4 or Full Down 95 KIAS NOTE 3 All Airworthiness Directives applicable to FAA Aircraft specification A-669 also are effective for the DC3-C as modified by STC SA2221NM.

Airworthiness Directives currently in effect or issued subsequent to the date of this SIC, which involve the Pratt & Whitney PT6A-45R Engine or the Hartzell HC-B5MP-3C/M108768 propellers are applicable to the engines or the propellers installed under this SIC, and applicability statement of such Airworthiness Directives notwithstanding.

Maximum overspeed limit is as specified for transient overspeed. If these Amits are exceeded, consult Pratt & Whitney of Canada Maintenance Manual No. 3027042, table 603 for disposition of engine or gear reduction box.

NOTE 6 Ground Operation:

(a) Stabilized operation below 53% N. (900 RPM) prohibited, except when porpeller is feathered operation between 23.5% Np (0 to 400 RPM) is permissible

(b) Stabilized operation between 69% Np (1170 RPM) and 82% Np (1400 RPM) is prohibited.

(c) Advanced above 94% Np (1600 RPM) only after brake release for takeoff roll, otherwise, limit operation above 94% Np (1600 RPM) to functional testing performed with aircraft headed into the wind.

NOTE 7 Oil Pressurture of 140-160°F: 105-135 p.s.1.g. Below 75% Ng (27,000 RPM) 000 RPM) gas generator speed and above with an gas generator speeds: 60 p.s.i.g. (min.). Extreme cold starts oil pressure may reach 200 psi.

NOTE 8 Oil temperature range continuous from minus 40°F (-40°C) to 210°F (99°C).

Limited periods of 10 minutes of 220°F (104°C) are allowable.

NOTE 9 Travels shown are with elevator down springs and rudder return spring disconnected. See Supplemental Service Manual USAC Manual 0003 for complete rigging instructions.

47.

PAGE 90F10 PAGES

Minicco States of Simerica Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Numbex SA2221NM NOTE 10 APPROVED FUELS

FUEL SPECIFICATION Jet A ASIM 1655 Jet A-1 ASTM 1655 Jet-B ASIM 1655 JP-4 ASTM 1655 or MIL-T-5624 JP-5 . MIL-T-5624 JP-8 MIL-I-83133 The use of aviation gasoline (AVGAS) is not approved. For additional information see P & WC Service Bulletin No. 3044.

NOIE 11 APPROVED LUBRICATING OILS Aeroshell Turbine Oil 500 Mobil Jet Oil II Mobil Jet Oil 254 Stauffer Jet II Castrol 5000 Esso/Exxon Turbo Oil 2380 For additional information see P & WC Service Bulletin No. 3001.

NOTE 12 Fuel anti-icing additives conforming to specifications 3GP-526A, PFA 55MB, MIL-I-27686D or MIL-1-27686E may be used, at a concentration not exceeding 0.15% by volume.

NOTE 13 Noise Characteristics: No acoustical change was show under the provisions of FAR Paragraph 21.93(b). Noise measurements taken in flyover tests have demonstrated that the noise levels of the PT6A-45R powered aircraft are no noisier than the noise levels of the R-1830 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 baggage.

NOTE 15 ingine and airframe certificated operating temperature limits: minimum - 40 C (-40 F) to ISA +30 C (ISA +54 F) maximum.

FAA FORM B110-2-1 (10.69) This certificate may be transferred in accordance with FAR 21.97.

PAGE 100F10 PAGES