STC SA2515NM

This Certificate issued to MILE HIGH GLIDING, INC.

5534 Independence Road Boulder, Colorado 80301

Part * of the * Air Regulations Original Product Type Certificate Number :

* *see attached FAA Approved Model List (AML) No.

* SA2515NM for list applicable aircraft make and models

* and applicable airworthiness regulations Description of Type Design Change : Installation of Hoffmann HO 4/27 BHM-185 fixed pitch propeller in accordance with FAA Mile High G liding, Inc. Report No. 2501 dated June 18, 1984, or later FAA approved revision. FAA Approve d Airplane Flight Manual supplements are required for normal category as listed in the Approved Model List.

Limitations and Conditions : This approval should not be extended to other specific airplanes of these models on which other previously approve d modifications are incorporated unless it is determined that the interrelationship between th is change and any of those other previously approved modifications will introduce no adverse e ffect upon the airworthiness of that airplane.

modification will introduce no adverse effect upon the airworthiness of these aircraft. 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.

Date of application : June 18, 1984

Date of issuance : September 25, 1984

Date reissued : March 11, 2004

Date amended : March 11, 2004, December 30, 2011

(Signature) Thomas A. Enyart Manager, Propulsion Branch Los Angeles Aircraft Certification Office ( Title)

NOTE:

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Number SA2515NM

Supplemental Type Certificate Addendum No. SA2515NM

The limitations and conditions of Type Certificate Data Sheets 2A10/2A8 apply except as follows:

This Addendum, which is part of Supplemental Type Certificate No. SA2515NM, prescribes limitations and conditions under which the product for which the STC was issued meets the airworthiness requirements of the Civil Air Regulations (CAR). A copy of this Addendum shall be maintained as part of the modified aircraft’s permanent records.

II - Model PA-25-235 1PCLM as modified by STC SA2515NM

Engine Lycoming O-540-B2B5 or O-540-B2C5 (Ref.)

Engine Limits For all operations, 2575 rpm (235hp) (Ref.)

III-Model PA-25-260 1PCLM as modified by STC SA2515NM

Engine Lycoming O-540-G1A5 or -G2A5

Engine Limits For all operations, 2575 rpm (250hp)

Data pertinent to all models

Propeller and Propeller Limits Hoffmann HO 4/27 BHM-185-110 through 125 [in 1 centimeter increments (PA-25-235)] Hoffmann HO 4/27 BHM-185-115 through 130 [in 1 centimeter increments (PA-25-260)] and PA-25-235 when STC SA1432GL or SA1456GL are installed.

Static rpm at maximum permissible throttle setting for PA-25-235:

Not over 2385, not under 2285 for -110 pitch, decrease limits by 5 rpm for each centimeter increase in pitch up to: Not over 2310, not under 2210 for -125 pitch

Number SA2515NM

NOTE: When STC SA1432GL or SA1456GL are installed refer to pitch and rpm limits for PA-25-260.

Static rpm at maximum permissible throttle setting for PA-25-260:

Not over 2435, not under 2335 for -115 pitch, decrease limits by 5 rpm for each centimeter increase in pitch up to: Not over 2360, not under 2260 rpm for -130 pitch

Diameter: Not over 73 inches, not under 73 inches. Spinner (optional): Hoffmann FP-30-64

Center of Gravity Range Restricted Category (+86.2 to +92.5) at 2,000 lb.

(+85.6 to +92.5) at 1,793 lb. or less Straight line variation between points given.

Normal Category (+86.2 to 90.3) in at 2,000 lb.

(+85.6 to 90.3) in. at 1,793 lb. or less Straight line variation between points given.

Maximum Weight 2,000 lb.

Maximum Cargo None

Data Pertinent to All Models

Power Plant Instrument Markings Tachometer: Maximum (red radial) 2575 rpm Normal (green arc) 500 to 2575 rpm

Serial number eligible This installation is eligible only on aircraft that have been modified for the special operation of Glider Towing in accordance with an FAA Form 337 approved by an FAA Aviation Safety Inspector.

Noise Characteristics: This change in design has been substantiated to be a non-acoustical change in accordance with § 21.93(b).