STC SH248NW

This Certificate issued to Siam Hiller Holdings, Inc.

925 M Street Firebaugh, California 93622 Part * of the * Regulations. * See page 3 and 4 of this STC for certification basis.

4H11 Hiller UH-12E Description of Type Design Change: Installation and maintenance of exhaust ejector engine oil cooling system in accordance with FAA approved Soloy Conversions, Ltd. Drawing List 560-101 dated October 30, 1975, and revised December 30, 1975, or later FAA approved revision.

NOTE: Only those Hiller UH-12E rotorcraft, which have been converted to turbine power in accordance with STC SH178WE are eligible for this modification.

Limitations and Conditions: Approval of this change in type design applies to the above model rotorcraft only. This approval should not be extended to other rotorcraft of this model on which other previously 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 that rotorcraft. A copy of this Certificate must be maintained as part of the permanent records for the modified rotorcraft. The limitations and conditions of Rotorcraft Type Certificate 4H11 and STC SH178WE apply except as outlined on page 3 of this STC. 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.

This certificate and the supporting data, which is the basis for approval, shall remain in effect until surrendered, suspended, revoked or a termination date is otherwise established by the Administrator of the Federal Aviation Administration.

Date of application: October 30, 1975

Date of issuance: January 20, 1976

Date reissued: 06/02/83; 10/25/84; 05/28/91;

11/30/95; 08/19/05

Date amended: 05/28/91

( Signature) Manager, Technical & Administrative Support Staff, Los Angeles Aircraft Certification Office ( Title)

Limitations and Conditions: (Continued) The limitations and conditions described in STC SH178WE are applicable to this modification except as detailed below:

1. Engine Rating For all operation 301 shaft horsepower

2. Torque For all operation Sea Level to 3000 ft.

273 lb. ft. (72.5 psi) 12,000 ft.

200 lb. ft. (53 psi) Straight-line variation between points given.

3. Rotorcraft Flight Manual FAA approved Soloy Conversions, Ltd. Rotorcraft Flight Manual, dated April 10, 1975, with Supplement dated January 20, 1976, is required in lieu of that specified for the basic unmodified Model UH-12E. Refer to the applicable portions of this FAA approved Soloy Conversions, Ltd. Rotorcraft Flight Manual for required placards and instrument markings.

4. Inspections and Maintenance The ejector oil cooler and related brackets must be visually inspected prior to each flight as part of the normal rotorcraft preflight inspection procedure. Refer to the applicable portions of Soloy Conversions, Ltd. Maintenance Manual for the required maintenance of this assembly.

5. Certified Basis

a. Civil Air Regulations Part 6 dated December 20, 1956, with Amendments 6-1 through 6-3 thereto.

b. The following paragraphs of Federal Aviation Regulations Part 27 including Amendment 27-1 thereto:

27.45 through 27.79, 27.143, 27.361(a), 27.901 through 27.1193, 27.1305, 27.1337,

27.1351(c), 27.1353, 27.1505, 27.1509(c), 27.1521, 27.1549 through 27.1555, 27.1557,

27.1559, 27.1583(b), and (f), 27.1587, 27.1589.

c. Special Conditions 27-1-WE-1, dated August 6, 1968, and Amendment 1 thereto dated February 28, 1975.