STC SA02828CH

Number SA02828CH

This certificate issued to

Part 3 of the Civil Aviation Regulations.

(See Aircraft Specification No. 1A2 for complete certification basis.)

Installation of the Lycoming IO-390-A1B6 engine, MT model MTV-15-B/210-58 constant speed propeller and associated accessories per H.O. Aircraft, Inc. Installation Manual Document No. IM-390, Revision A, dated June 4, 2010, or later FAA approved revision.

1. Compatibility of this design change with previously approved modifications must be determined by the installer.

2. Verify proper aircraft Weight and Balance.

3. Full compliance with the ICA, revision A, dated June 4, 2010, and FAA approved Airplane Flight Manual Supplement, Revision B, dated June 4, 2010 or later FAA approved revisions are required.

4. 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.

H. O. Aircraft Inc.

8891 Airport Road, Box A-3 Blaine, MN 55449 1A2 Make : Piper Aircraft Model : PA-18, PA-18S, PA-18”105” Special, PA-18S”105” Special, PA-18A, PA-18”125” (Army L-21A), PA-18S”125”, PA-18AS”125”, PA-18”135” (Army L-21B), PA-18A“135”, PA-18S“135”, PA-18AS“135”, PA-18”150”, PA-18A”150”, PA-18S”150”, PA-18AS”150”, PA-19 (Army L-18C), PA-19S

Date of application : March 24, 2009

Date of issuance : May 4, 2010 Date reissued : June 14, 2010

Date amended : January 15, 2014

Original Signed By:

Timothy Smyth

(Signature) Timothy Smyth Manager, Propulsion and Program Management Branch Chicago Aircraft Certification Office

(Title)

FAA FORM 8110-2-1(10-69) PAGE 3 of 4 PAGES

Number SA02828CH Limitations and Conditions:

Engine: Lycoming IO-390-A1B6 Engine Limits: For all operations, 2700 RPM

Fuel: 100 minimum grade aviation gasoline.

Standard tanks (36 gal) - 34.4 gallons usable in all flight conditions.

“BOTH” fuel selector position is required for takeoff and landing.

Electric Fuel Boost Pump “ON” for all takeoff and landing operations.

Fuel Consumption: Operation RPM HP Fuel Cons. Gal/Hr Normal Rated 2700 210 ---- Performance Cruise (75% Rated) 2450 158 12.3 Economy Cruise (65% Rated) 2350 137 9.1

Airspeed Limits: Remain unchanged from the PA-18-150 series

Propeller: MT Composite Propeller MTV-15-B/210-58 205 cm (80.7 inch) Minimum diameter 210 cm (82.7 inch) Maximum diameter

Static RPM limits: Maximum 2700 RPM, Minimum 2450 RPM

Powerplant Instrument Markings:

Oil Temperature: Red Radial: 235°F maximum Green Arc: 165°F – 200°F

Oil Pressure: Red Radial: below 25 psi and above 115 psi Yellow Arc: 25 psi – 54 psi and 96 psi – 115 psi Green Arc: 55 psi – 95 psi

Tachometer: Red Radial: Rated engine speed 2700 RPM

Fuel Pressure: Red Radial: below 13 psi and above 45 psi Green Arc: 14 psi – 45 psi

Maximum Weight: 2000 lbs. (maximum takeoff weight)* 1900 lbs. (maximum landing weight) * Note: The 2000 pound gross weight increase IAW STC SA00997CH must be installed.

C.G. Range: Normal: (+16.2) to (+20.0) at 2000 lbs.

(+10.5) to (+20.0) at 1300 lbs. or less Straight line variation between points given Utility: (+12.3) to (+19.0) at 1500 lbs.

(+10.5) to (+19.0) at 1300 lbs. or less Straight line variation between points given

FAA FORM 8110-2-1(10-69) PAGE 3 of 4 PAGES

Number SA02828CH Limitations and Conditions:

Placards: The following placards are required:

1) Above the fuel selector:

“Takeoff and Landing on “BOTH” only”

2) At fuel tank filler on each wing tank:

“100 Grade Minimum Aviation Gasoline”

3) As near as possible to Electric Fuel Boost Pump switch and blue “on” indicator light:

“Fuel Boost Pump “ON” for all takeoff and landing operations”

ALL aircraft are required to have the following modifications or equipment:

1) Airframe tubular structure – One (1) of the following is required:

Option #1:

An original model PA-18-150 or PA-18A-150 airframe. Serial numbers eligible: 18-3771 & up

Option #2:

An airframe that has been modified IAW STC SA02128AK

Option #3:

An airframe that has been modified IAW STC SA02187AK

Option #4:

An airframe that has been modified IAW STC SA4095NM

2) The 3” extended main landing gear modification IAW STC SA02175AK or SA02152AK.

3) The 2000 pound gross weight increase modification IAW STC SA00997CH.

4) Fuel system modification IAW STC SA00415SE.

5) Two main wheel tires size: 8.00x6 minimum.

6) Scott 3200 tail wheel assembly (Item 204g on T.C. No. 1A2) or the equivalent ABI-3200 Alaska bush wheel.

7) Dual grooved pulley stabilizer adjustment cable system installed IAW Piper Drawings #14486 and #12999*

8) Torque tube assembly p/n: 13735 and stick stub assembly p/n: 13729-00 must be installed as used on PA-18 aircraft after serial number 18-1969*

9) Flaps and counter-balanced tail surfaces must be installed (Item 601 on T.C. No. 1A2)*

10) A .150” or .187” thick windshield.

*Note: Items 7, 8, 9 would have been original equipment on ALL Piper PA-18-150, 18A-150 aircraft.