STC SA3227WE

TTOO00IWE United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA322TNE This certificate issued to: . Floyd D. StIlWel Part * of the CIVil Air Regulations: See page 4 of this STC for certification basis.

Original Product Type Prertificate Number: AASW Make: Rockwell Commander Model: S-2R Pescriplion TypeSesign hange: Installation of an AiResearch TРЕ331-1-101Z, TPE331-25DA, or TPE331-25FA turboprop engine in accordance with Floyd D. Stilwell Drawing FS-105-TT, revision dated June 10, 1976, or later FAA sealed revisions. FAA approved Floyd D. Stilwell Flight Manual Supplement dated July 16, 1976, or later FAA approved revisions, is required as part of this installation.

Similalins and bandilions: The limitations and conditions of Data Sheet A4SW apply except as outlined in pages 3 through 5 of this STC. A copy of this STC must be included in the permanent records of each airplane modified in accordance with this

Palerf applicalion: March 24, 1975 Date Reissued:

Jale sf issuance: July 16, 1976 I ate amendul: September September 17; 1926; May 5, 1978;

FEDERAL AVIATION Bey directive of the Administrater 7 Signature ) PANISTRANO hef, Aircraft Engineering Division (Title) 47

United States of America Department of Transportation Federal Aviation Administration 07/16/76 (I) Supplemental Type Certificate 09/27/76 (A) (Continuation Sheet) 05/05/78 (A) 09/17/80 (A) NumbenSA3227WE May 5, 1978 1 - Rockwell Commander S-2R as modified by this STC (Restricted Category) Engine AiResearch ТРЕ331-1-101Z, ТРЕ331-25DA, or ТРЕ331-25FA Fuel AiResearch EMS 53100 (Artic type) AiResearch EMS 53111 (Type A) AiResearch EMS 53112 (Type A-1) AiResearch EMS 53113 (Class A-JP4 and Class B Type B) AiResearch EMS 53116 (Type JP-5) British D. Eng. R.D. 2482 Issue 2 British D. Eng. R.D. 2486 Issue 2 British D. Eng. R.D. 2494 Issue 4 Aviation gasoline MIL-G-5572D, Grade 80/87, not in excess of 1000 gallons per 100 hours of operation, may be used for emergency fuel operation.

ASTM D9/5, Grade 2-D, dated 1977 (Diesel Fuel). This fuel requires a separate inline 40 micron filter and water separator between the fuel supply tank and the aircratt filler port.

Fuel MIL-I-27686D or E Fuel System Icing Inhibitor, or an Additives equivalent inhibitor, may be added in a quantity not in excess of 0.15 percent by volume, to fuels not containing anti-icing inhibitors.

Shell ASA-3 anti-static additive, or equivalent, may be used in amounts to bring the fuel up to 300 conductivity units, but in no event shall the additive exceed 1 ppm.

Sohio Biobor JF Biocide Additive, or equivalent, is approved for use in the fuel at a concentration not to exceed 20 ppm of elemental Boron.

Oil Oils conforming to AiResearch Manufacturing Company of Arizona Specification EMS 53110 (Type I and Type II).

- 1-101Z -25DA -25FA Engine Ratings Takeoff 600 SHP 575 SHP Maximum Continuous 600 SHP 500 SHP Reverse 600 SHP 575 SHP

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PAGE 3 OF 5 PAGES FAA AC 73-2651

United States of America Department of Transportation Federal Aviation Administration 07/16/76 (I) Supplemental Type Certificate 09/27/76 (A) (Continuation Sheet) 05/05/78 (A) 09/17/80 (A) -1-101Z -25DA, -25FA Engine Output Shaft Speed 2000 RPM Limits Transient Overspeed (5 secs.) 2100 RPM Transient Overspeed (5 mins.) 2020 RPM Reverse 2000 RPM Torque Takeoff (5 mins.) 1890 Ft. Lbs. 1707 Ft. Lbs.

Maximum Continuous 1746 Ft. Lbs. 1313 Ft. Lbs.

Reverse 1890 Ft. Lbs. 1707 Ft. Lbs.

Exhaust Gas Takeoff (5 mins.) 590°C 571°C Temperature Maximum Continuous 580°C 535°C Starting (1 sec.) 815°C 815°C Reverse 590°C 571°C Oil Pressure Takeoff and Maximum Continuous 70 to 120 psig Idle (minimum) 40 psig OfT MIL-L-23699 -40°C to 127°C Temperature MIL-L-7808 -40°C to 93°C Propeller Hartzell HC-B3TN-5/T10282+4 Minimum length 101 inches diameter Maximum length 106 inches diameter Max. Approved 30,000 feet Al titude C.G. Range Maximum weight 6,000 pounds; Forward c.g. limit 25.5 inches and Weight aft of datum Aft c.g. limit 30.0 inches aft of datum (Datum is the leading edge of the wing) Applicability The approval of this change in type design applies to the basic aircraft of the model shown on page 1 of this STC that is otherwise unmodified. This approval should not be extended to other aircraft 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 aircraft. See "Equipment" below.

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PAGE 4 OF 5PAGES C FAA AC 73-2651

United States of America Department of Transportation Federal Aviation Administration 07/16/76 (I) Supplemental Type Certificate 09/27/76 (A) (Continuation Sheet) 05/05/78 (A) 09/17/80 (A) Number: SA3227VE May 5, 1978 Certification (a) CAR 8.10(a) (1) dated October 11, 1950.

Basis

(b) FAR 23, effective February 1, 1965, including Amendments 23-1 through 23-16 only as applies to turboprop engine installation.

(c) Special Federal Aviation Regulation 27, effective January 1, 1975, including Amendment 27-1.

Production None. An inflight operational check must be conducted in Basis accordance with FAR 91.167(a) for each aircraft modified to incorporate this Supplemental Type Certificate.

Equipment The following must be installed in the aircraft for airworthiness certificate subsequent to the incorporating of this STC:

1. The basic required equipment as prescribed in the applicable airworthiness regulations (See Certification Basisi outlined above.)

2. The additional required items shown in FAA sealed Floyd D. Stilwell Equipment List FS-206-TT.

NOTE: Equipment items approved for the basic Rockwell Commander S-2R are not eligible with this STC unless it is determined that the interrelationship between those items and the modifications covered by this STC will introduce no adverse effect on the airworthiness of that aircraft.

NOTE 1. Refer to the applicable FAA Approved Airplane Flight Manual for required placards and instruments markings.

NOTE 2. The ratings shown on the AiResearch TPE331 engine is based on the static sea level standard conditions with no external accessory loads and no air bleed.

NOTE 3. Current weight and balance data, including a list of equipment included in the certificated empty weight and loading instructions, when necessary, must be provided at the time of airworthiness certification for return to service.

FAA FORM 8110-2-1 (10-69) PAGE 5 OF 5 PAGES C FAA AC 73-2651