STC SA4840NM

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number SA 4840NM This certificate issued to: Basler Turbo Conversions, Inc.

255 W. 35" Avenue Oshkosh, WI 54903 Certifies that the change in the type design for the following product with the limitations and condition's therefer as specified hereen meets the airverthiness requirenents of Part 46 of the Bivil Air Pegulations. daled September 1.

1953 (Lee page 4 of this IT for the complete certification basis) Original Product --Type Fertificate Number: A-669 Make: The Boeing Company Model:

See Page 3 Description of Type Design Change:

Installation of Pratt & Whitney of Canada PT6A-67R engines, Hartzell HC-B5MA-3/M11276 or HC-BSMA-3()/M11691N, K model propellers, modified fuel system, revised electrical system, and forward fuselage extension in accordance with FAA approved Basler Turbo Conversions, Inc., Master Drawing List Douglas DC3C Re-Engining Document No. BTC-1001, Revision N, dated February 1, 1992, or later FAA approved revision.

1. This approval should not be extended to other specific airplanes of this model on which other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of the aircraft.

(See continuation pages 3 through 6 for additional limitations and conditions)

suspended, revsked or a ternination date is otherwise established by the Administrater of the Federal Aviation Date of Application: April 18, 1988 Date Reissued:

Date of Issuance: February 27, 1990 Date Amended: December 11, 1990;

March 27, 1992;

December 15, 2003;

November 20, 2012;

FEDERAL AVIATION August 21, 2015 dion of the odministrater * (orgnamare) TOMNISTRATIO Roy Boffo Acting Manager, Powerplant and Program Management Branch Chicago Aircraft Certification Office

FAR FORM 8110-2 (10-68) PAGE 1 of 10 PAGES

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

FAA Form 8110-2-1 (10-69) PAGE 2 of 6 PAGES

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number SA4840NM Date of Amendment: August 21, 2015 Limitations and Conditions: (Continued)

2. A copy of this Supplemental Type Certificate shall be maintained as part of the modified aircraft's permanent records.

3. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.

4. Model: DC3C-SC3G, S1C3G, S4C4G, R-1830-43A, R-1830-49, R-1830-57, R-1830-65, R-1830-67, R-1830-75, R-1830-82, R-1830-90C, R-1830-90D, R-1830-92, R-1830-94, R-1830-96. R-2000-7M2, R-2000-D5 When modified by this STC (SA4840NM), the modified aircraft model is unofficially known as DC3-TP67.

5. A Flight Manual Supplement, FAA approved for use with STC SA4840NM, is required on board for operation of the modified aircraft.

Limitations and Conditions: of Aircraft Specification No. A-669 apply except as noted herein and denoted within the Flight Manual Supplement utilized to satisfy Limitation 5 above.

Control Surface Elevator up 12 + 1/8 inches, down 8 + 1/8 inches.

Movements: Aileron up 13 + 1/8 inches, down 8 ‡ ½ inches.

Rudder left 26 + ¼ inches, right 26 ‡ ¼ inches.

Production Basis: None. An inflight operational check must be conducted in accordance with FAR 91.401 for each aircraft modified. When original airworthiness certification has not previously been accomplished the applicant must also comply with FAR

FAA FORM 8110-2-1 (10-69) PAGE 3 of 6 PAGES

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA4840NM Date Amended: August 21, 2015 Limitations and Conditions: (Continued) Certification Basis:

(1) SFAR 13 effective December 30, 1964

(2) CAR 4b effective September 1, 1953, except where superseded by FAR 25 requirements.

(3) FAR 25 sections as amended by Amendments 25-1 through 25-63. Regulations:

25.33, 25.101 thru 25.105, 25.107 thru 25.111, 25.113 thru 25.125, 25.149, 25.251,

25.253, 25.361, 25.363, 25.367, 25.371, 25.613 thru 25.619, 25.629, 25.279(e),

25.777 thru 25.781, 25.863 thru 25.867, 25.901, 25.903, 25.905 thru 25. 933(a),

25.937 thru 25.977, 25.981 thru 25. 999, 25.1011 thru 25.1041, 25.1043, 25.1045 thru 25.1093, 25.1103 thru 25.1123, 25.1141 thru 25.1145, 25.1149 thru 25.1155,

25.1163, 25.1165, 25.1181 thru 25.1191, 25.1193 thru 25.1203, 25.1301 thru

25.1321, 25.1337 thru 25.1351, 25.1353, 25.1355 thru 25.1363, 25.1501, 25.1505,

25.1521, 25.1527 thru 25.1533, 25.1549 thru 25.1557, 25.1563, 25.1581 thru

(4) FAR 36, See Amendment 36-17

(5) FAR 34, Unamended.

NOTE 1

(a) Current weight and balance report and loading instructions must be in each aircraft at the t time of original certification and at all times thereafter.

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.

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 from the center wing main (forward) tanks only.

FAA FORM 8110-2-1 (10-69) PAGE 4 of 6 PAGES

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA4840NM Date Amended: August 21, 2015 Limitations and Conditions: (Continued) A crossteed system is provided to feed fuel from the opposite center wing main (forward) tank to engine.

(‡) Fuel must be loaded in the following manner:

Fill left and right main tanks first. Additional fuel may then be loaded in either the center wing auxiliary tanks, or if installed the optional auxiliary tanks located in the outer wing.

NOTE: Fuel loaded in the outer wing auxiliary tanks must be loaded symmetrically.

NOTE 2 All Airworthiness Directives applicable to FAA Aircraft Specification A-669 also are effective for the DC3C as modified by this STC. The following Airworthiness Directive do not apply to DC3C aircraft modified according to this STC SA4840NM 47-06-07 - Fire extinguisher trigger 47-33-02 - Cowl flap liner 47-51-12 - Carburetor Airscoop 48-05-01 - Oil shutoff valves 48-17-01 - Fire prevention modifications 50-46-01 - Oil tank standpipe 52-25-01 - Vacuum system rework 52-20-05 - Propeller operating limits 58-08-03 - CB fire extinguish system 77-10-02 - Fire resistant propeller featuring line New doublers and angles per Douglas Service Bulletin DC-3 No. 262 are required on Aircraft modified in accordance with this STC.

Ailerons permanently identified as complying with the balancing procedures 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 3 Airworthiness Directives (AD) currently in effect or issued subsequent to the date of this STC, which involved the Pratt & Whitney PT6A-67R engine or the Hartzell HC-B5MA- 3/M11276 or Hartzell HC-B5MA-3()/M11691N, K model propellers are applicable to the engines or the propellers installed under this STC, and the applicability statement of such AD(s) notwithstanding.

FAA FORM 8110-2-1 (10-69) PAGE 5 of 6 PAGES

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA4840NM Date Amended: August 21, 2015 Limitations and Conditions: (continued) NOTE 4 Maximum overspeed limit is as specified for transient overspeed. If these limits are exceeded, consult Pratt and Whitney of Canada Maintenance Manual No. 3036132, for disposition of engine or gear reduction box.

NOTE 5 For Ground Operations: Hartzell HC-B5MA-3/M11276

(a) Stabilized operation between 400 and 900 propeller RPM is prohibited.

(b) Stabilized ground operation between 1050 and 1200 propeller RPM is prohibited, and above 1600 RPM unless headed into the wind.

For Ground Operations: Hartzell HC-B5MA-3()/M11691()

(a) Stabilized ground operation between 400 to 900 propeller RPM is prohibited.

(Propeller may be operated below 400 RPM if feathered)

(b) Stabilized engine ground operation is prohibited above 1600 propeller RPM (except for takeoff and functional checks and must be headed into the wind.)

NOTE 6 APPROVED FUELS

FUEL SPECIFICATION Jet A ASTM D1655 Jet A-1 ASTM D1655 Jet A-2 ASTM D1655 Jet B ASTM D1655 JP-4 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& WC Service bulletin No. 14004.

NOTE 7 Fuel anti-icing additive is required. The additive concentration, by volume, shall be in a minimum of 0.060% and and or maximum of 0.15%. The approved additives are:

Phillips PFA 55 MB MIL-I-27686D Prist (Ethylene Glycol Monomethyl Ester as defined in MIL-1-27686E) NOTE 8 No cargo or passenger interior configuration as been approved as part of this STC.

...END...

FAA FORM 8110-2-1 (10-69) PAGE 6 of 6 PAGES