STC SA4-228

United States Of America Department of Transportation - Federal Aviation Administration Supplemental Type Certificate This certificate has been reissued to replace the original certificate reported as lost.

This Certificate issued to Preferred Improvements, LLC 11234 Hackett Rd. P. O. Box 12 Kidron, Ohio 44636 Kidron, Ohio

Part 4a* of the Civil Air Regulations.

*(CAR 4a, Bulletin 7a and Special Regulations 407) Original Product Type Certificate Number :

A-669 Boeing DC-3A, DC-3C, and DC-3D Description of Type Design Change: Installation of main landing gear doors, actuating system, main landing gear assist bungee, oil cooler fairing and oil cooler fixed section for aircraft equipped with P & W R-1830-75, -92 or -94 engines. Installation in accordance with drawings and instructions listed on Ben Howard and Associates Sealed Data List No. 1004-A.

(1) The approval of this change in type design applies basically to standard Model DC-3A, DC-3C and DC-3D airplanes only. This approval should not be extended to other specific airplanes of these models on which other previous approved modifications are incorporated, unless it is determined that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect upon the airworthiness of the airplane.

A copy of this STC must be included in the permanent records of the modified aircraft. 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.

(See Continuation Sheet on Page 3).

Date of application : May 27, 1957

Date of issuance : June 13, 1957

Date reissued : September 27, 1974 February 25, 2016

Date amended : March 3, 1958

(Signature) Manager, Airframe Branch Los Angeles Aircraft Certification Office (Title)

Transfer the ownership of the Supplemental Type Certificate Number to (Name of transferee) (Address of transfer) (Number and street)

(City, State, and Zip code) from (Name of grantor) (Print or type) (Address of grantor) (Number and street)

(City, State, and Zip code) Extent of Authority (if licensing agreement):

Signature of grantor (In ink):

United States Of America Department of Transportation - Federal Aviation Administration Supplemental Type Certificate Number SA4-228 Continuation Sheet 1

(2) For Model DC-3A aircraft equipped with the original DC-3 type landing gear rubber bungee system, this installation must be made in accordance with the drawings and instructions listed on Data List No. 1004-A, Sheets 1A and 1B.

(3) For Model DC-3A, DC-3C and DC-3D aircraft equipped with the Douglas C-47 type hydraulic bungee system, this installation must be made in accordance with drawings and instructions listed on Data List No. 1004-A, Sheets 2A and 2B.

(4) This installation is acceptable for operation at approved gross weights in excess of 25,200 pounds in accordance with Aircraft Specification No. A-669 provided the aircraft also incorporates one of the following combinations.

(a) For aircraft equipped with P&W R-1830-92 engines: STC SA4-138, “Installation of Engine Cowling, Baffles, Siamese Type Exhaust System and Modified Cowl Flaps”

(b) For aircraft equipped with P&W R-1830-92 engines: (Alternate Installation STC SA4-151, “Installation of Siamese Type Exhaust System”, and STC SA4-279, “Installation of Engine Cowling and Baffles”

(c) For aircraft equipped with P&W Super R-1830-92 engines : STC SA4-151, “Installation of Siamese Type Exhaust System,” and STC SA4-309, “Installation of Engine Cowling and Baffles”

(d) For aircraft equipped with P&W R-1830-75 or -94 engines: STC SA4-151, “Installation of Siamese Type Exhaust System”, and STC SA4-272, “Installation of Engine Cowling and Baffles”

(5) If the installation is not made in conjunction with one of the above combinations, that is, if either or both the standard DC-3 cowling or the standard DC-3 exhaust system are installed, the maximum takeoff weight must be limited to 25,200 pounds and the engine powers must be limited to the same powers as permitted for the P&W R-1830-92 engine installation.

(6) The following airspeed (TIAS) limits apply:

Aircraft Weights SPEEDS Up to and Including 25,200 pounds Weights in excess of 25,200 pounds

VL(Level flight or climb) 195 mph (170 knots) 183 mph (159 knots) Vne (Never exceed) 233 mph (202 knots) 219 mph (190 knots) Vlo (Gr. Operating speed) 150 mph (130 knots) 150 mph (130 knots) Vlo (Gr. Extended speed) 150 mph (130 knots) 150 mph (130 knots)

Aircraft placards and Airplane Flight Manual, when required, must be revised accordingly.

END