STC SA1640NM

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA1640NM This certificate issued to: Micro AeroDynamics, Inc.

4000 Airport Rd., Suite D Anacortes, WA 98221 Part 23 of the Federal Aviation Regulations, including Amendment 23-6.

Original Product -Type Certificate Number: ATSO Make: Piper Model: PA-34-200T and 220T Description of Type Design Change: Installation of a modified air induction system to the Continental TSIO-360 engine turbocharger compressor (Rajay) system in accordance with SGH, Inc., Installation Instruction and Assembly Drawing No. SGH-PA-34-1000-A.

NOTE: This installation incorporates a NASA submerged inlet; new filter and inlet plenum with pressure operated alternate air door and associated hardware as illustrated in SGH-PA-34-1000-A.

Limitations and Conditions: Approval of this change in type design applies basically to the above model aircraft only. This approval should not be extended to other aircraft on which other previously approved modifications are incorporated unless it is determined that the relationship between this change and any of those other previously approved modifications, including changes in type design, will introduce no adverse effect upon the airworthiness of that aircraft. A copy of this Certificate and Addendum shall be maintained as part of the permanent records for the modified aircraft. (Continued on Page 3).

Date of Application: April 10, 1982 Date Reissued: December 7, 1987; June 9, 1995 Date of Issuance: July 9, 1982 Date Amended: October 12,1982; January 12, 1983 FEDERAL AVIATION By Direction of the Administrator (Signature) TOMNIST RA TOP Acting Manager, Seattle Aircraft Certification Office (Title)

Alrited Bates of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA1640NM Supplemental Type Certificate ADDENDUM NO. SA1640NM The conditions and limitations of Type Certificate Data Sheet No. A7SO apply except where superseded by the following:

Supplemental Type Certificate Addendum, which is part of STC SA1640NM, prescribes the conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Federal Aviation Regulations. A copy of this STC Addendum is required to be maintained as part of the modified aircraft's permanent records.

Supplemental Type Certificate HOLDER: Micro AeroDynamics, Inc.

MODEL PA34-200T AND 220T (SENECA 11) AND 1117 PCLM (NORMAL CATEGORY) AS MODIFIED BY STC SA1640NM Placard: Affix the following placard directly below throttle quadrant:

1. Alternate Air Automatic

2. Manual Alt. Air Inop.

3. See Attached Page 4, Power Setting Table (Continued on Page 4)

47.

Turbopius® Advanced Induction Systems TURBOPLUS MODIFICATION STC SA 1640 NM POWER SETTING TABLE - T.C.M. TSIO 360E SERIES SENECA II PA 34-200T 65% POWER 75% POWER STD. (APPROX. 20.1 GPH FUEL CONS.) (APPROX. 23.1 GPH FUEL CONS.)

PRESS ALT.

ALT. TEMP RPM 2300 2400 2500 2575 2300 2400 2500 2575 FEET 2200

C F MANIFOLD PRESSURE - INCHES MERCURY S.L. 15 59 32.5 31.0 29.6 28.8 28.2 34.5 33.0 32.0 31.8 2000 11 52 31.8 30.5 29.0 28.0 27,8 34.0 32.4 31.6 31.0 4000 45 31.0 29.8 28.6 27.6 27.2 33.4 31.8 31.0 30.6 6000 37 30.4 29.0 28.0 27.0 26.8 32.6 31.0 30.4 29.9 8000 -1. 30 29.6 28.6 27.4 26.6 26.4 32.0 30.6 29.8 29.3 1--00 -5 23 29.0 27.8 26.8 26.0 26.0 31.4 30.0 29.2 28.8

30.2 -9 16 28.4 27.0 26.2 25.6 25.4 30.6 29.4 28.8 28.3

29.5 14000 -13 9 27.6 26.4 25.0 30.0 28.8 28.2 28.0

28.6 31.0 16000 -17 2 25.7 24.6 29.2 28.4 27.6

30.5 40.0 * 18000 -21 -5 25.0 24.0 28.6 27.8 27.3

29.0 30.0 35.0 37.0 20000 -25 - 12 24.4 23.8 27.2 27.0

25.5 30.0 32.0 22000 -28 -19 23.6 23.4 26.6 26.7

24.6 28.5 30.5 24000 -33 -26 22.8 24.0 26.4

28.5 25000 -34 -30 22.6 26.0 To maintain constant power, add ½" MP for each 10° F above standard. Subtract ½" MP for each 10° F below standard.

Turboplus increased altitude power settings appear in BOLD PRINT.

NOTE: Turboplus full throttle available power as recorded during test flights (STD. + 5 F day) shown in italics below power settings.

NOTE: Full throttle manifold pressure values may not be obtainable when atmospheric conditions are non-standard.

* NOTE: 200 HP available up to 16000' PAGE 4 OF 4