STC SH288NW

This Certificate issued to Siam Hiller Holdings, Inc.

925 M Street Firebaugh, California 93622 Part 6 of the Civil Air Regulations. effective December 20, 1956. See page 3 and 4 of this STC for certification basis.

4H11 Hiller UH-12E Description of Type Design Change: Installation of Hiller landing gear float kit No. 44012 in accordance with FAA approved Soloy Drawing List 560-601.

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 and 4 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: February 24, 1976

Date of issuance: April 23, 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. Airspeed Limits 44012 Floats - CAS Sea level to 2,000 ft. 86 mph 12,000 ft. 62 mph Straight-line variation between points given.

2. C. G. Range 44012 Floats Longitudings (+81.0) to (+84.8) Lateral no change from SH177WE

3. Horizontal Stabilizer Rigging Minus 10° with 44012 floats installed and r o t o r c r a f t l e v e l .

4. Rotorcraft Flight Manual

FAA approval Soloy Conversions, Ltd. Rotorcraft Flight Manual, dated April 10, 1975, with Supplement dated April 23, 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.

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.

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