# STC SA1171WE - Type: Supplemental type certificate - Status: Current, Reissued - Holder: SOUTHWESTERN AERO EXCHANGE INC., United States - Description: Installation of two AiResearch TPE331 Series engines, tricycle landing gear, wing platform modifications, and related modifications. - Applied: July 20, 1964 - Status date: May 1, 2006 - Product: Aircraft, Small Airplane - Data sheets: [TCDS A-765](https://openairdocs.org/tcds/A-765) - Certificate PDF: https://openairdocs.org/files/sha256/9a/42/9a42b812a747faa0313672b27da33d1fbf8cd6c4989ae528b6929f86853a6eeb - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/467267083E03C7278625719A0050A41D.0001 - DRS record last changed: December 5, 2025 - Page: https://openairdocs.org/stc/SA1171WE ## ADs that name it (1) - [AD 2005-18-20](https://openairdocs.org/ad/2005-18-20): "FASTprop" propeller de-icers · Hartzell PHC-C3YF-1RF/F8468A(B,K)-8R constant speed propeller (STC SA00718LA or 17 others). Effective Oct 14, 2005. Cited in the text ## Approved models (12) - Raytheon Aircraft Company C-45G ([TCDS A-765](https://openairdocs.org/tcds/A-765)) - Raytheon Aircraft Company C-45H ([TCDS A-765](https://openairdocs.org/tcds/A-765)) - Raytheon Aircraft Company D18C ([TCDS A-765](https://openairdocs.org/tcds/A-765)) - Raytheon Aircraft Company D18S ([TCDS A-765](https://openairdocs.org/tcds/A-765)) - Raytheon Aircraft Company E18S ([TCDS A-765](https://openairdocs.org/tcds/A-765)) - Raytheon Aircraft Company E18S-9700 ([TCDS A-765](https://openairdocs.org/tcds/A-765)) - Raytheon Aircraft Company G18S ([TCDS A-765](https://openairdocs.org/tcds/A-765)) - Raytheon Aircraft Company H18 ([TCDS A-765](https://openairdocs.org/tcds/A-765)) - Raytheon Aircraft Company JRB-6 ([TCDS A-765](https://openairdocs.org/tcds/A-765)) - Raytheon Aircraft Company TC-45G ([TCDS A-765](https://openairdocs.org/tcds/A-765)) - Raytheon Aircraft Company TC-45H ([TCDS A-765](https://openairdocs.org/tcds/A-765)) - Raytheon Aircraft Company TC-45J ([TCDS A-765](https://openairdocs.org/tcds/A-765)) ## What the certificate says Read from the PDF's text layer, without the form's printed wording; the layout is lost and the order can differ. The PDF is the record. This Certificate issued to Southwestern Aero Exchange, Inc. 18502 East 108th Street N. Owasso, OK 74055-8124 Part * of the Civil Air Regulations. *See attached STC SA1171WE Addendum for certification basis. 765 Beech D18C, D18S, E18S, E18S-9700, C-45G, TC-45G, TC-45C, C-45H, TC-45H, TC-45J (SNB-5), JRB-6, G18S, H18, C-45J Description of Type Design Change: Installation of two AiResearch TPE331 series engines, tricycle landing gear, wing platform modifications, and related modifications. See attached SA1171WE Addendum for required descriptive data. Limitations and Conditions 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. See Attached STC SA1171WE Addendum, which is a part of this certificate. Date of application : July 20, 1964 Date of issuance : February 17, 1966 Date reissued: January 23, 1998; May 1, 2006 Date amended: Jun. 9, 1966; Aug. 10, 1966; Dec. 5, 1966; Aug. 2, 1968; Jan. 22, 1969; Mar. 5, 1985 ( Signature) Manager, Technical & Administrative Support Staff, Los Angeles Aircraft Certification Office ( Title) **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1171WE** The conditions and limitations of Aircraft Specification No. A-765 applies except as follows: This addendum, which is part of Supplemental Type Certificate NO. SA1171WE, prescribes conditions and limitations under which the product for which the Supplemental Type Certificate was issued meets the airworthiness requirements of the Civil Air Regulations. I-Models: Beech JRB-6, D18C, D18S, E18S, E18S-9700, C-45G, TC-45G, C-45H, TC-45H, TC-45J (SNB-5), C-45J, G-18S, H18 Engines (Option 1) 2 AiResearch TPE331-25 (turbo-prop) with 1:20.865 reduction gear ratios. Fuel Aviation Turbine Fuels ASTM Designation D1655-63T, Types Jet A, Jet B and Jet A-1. Military Fuels MIL-J-5624F-2, Grades JP-4, JP-5 and MIL-F-5616-1, Grade JP-1. See NOTES 8 and 10. Engine Limits Static Sea Level Rating Shaft Equivalent Horsepower Shaft Horsepower RPM Take-off (5 min) 575 605 2000 (100%) Max Continuous 500 529 2000 (100%) See NOTE 3 Max. Allowable Measured by the torquemeter for below standard inlet air Power temperatures and/or ram conditions is 575 SHP for take-off (5min.) and 500 SHP for Max. continuous while not exceeding EGT limits Temperature Limits Exhaust gas temperature (standard sea level day) Takeoff (5 min) 1060°F (571°C) Maximum 995 °F (535°C) continuous Starting Transient (one second) 1500°F (815°C) NOTE: EGT limits vary with ambient temperature and pressure. Refer to the applicable FAA Approved Airplane Flight Manual for actual limits under non standard conditions. Oil Inlet -40°F (-40°C) min Temperature +260°F (+127°C) max. MIL-L23699 (Mobil Jet II) oil required. **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1171WE** Engine (Option 2) 2 AiResearch TPE331-47-A or TPE331-47-B (turbo-prop) with 1:20.865 reduction gear ratio. Fuel Aviation Turbine Fuels ASTM Designation D1655-63T, Type Jet A, Jet B and Jet A-1, Military Fuels MIL-L-5624F-2 Grades JP-4, JP-5 and MIL-F-5616-1, Grade JP-1 See NOTE 8 and 10125 Engine Limits Static Sea Level Rating Shaft Equivalent Horsepower Shaft Horsepower RPM Take-off (5 minutes) 575 605 2000 (100%) Max. Continuous 500 529 2000 (100%) S e e N O T E 3 Max. Allowable Measured by the torquemeter for below standard inlet air temperature Power and/or ram conditions is 575 SHP for take-off (5 minutes) and 500 SHP for max. continuous while not exceeding EGT limits. Temperature limits Exhaust gas temperature (standard sea level day) Takeoff (5 min.) 1070°F (577°C) Maximum 1026°F (552°C) Continuous Starting Transient (one second) 1500°F (815°C) NOTE: EGT Limits vary with ambient temperature and pressure. Refer to the applicable FAA Approved Airplane Flight Manual for actual limits under non standard conditions. Oil Inlet -40°F (-40°C) min. Temperature +260°F (+127°C) max. MIL-L-23699 (Mobile Jet II) oil required Engines (Option 3) 2 AiResearch TPE- 331-1-101B (turbo prop) with 1:20.865 reduction gear ratio. Fuel Aviation Turbine Fuels, ASTM Designation D1655-63T, Types Jet A, Jet B and Jet A-1. Military Fuels MIL-J-5624F-2, Grades JP-4, JP-5 and MIL-F- 5616-1, Grade JP-1. See NOTE 8 and 10. Number SA1171WE **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1171WE** Engine Limits Static Sea Level Rating Shaft Equivalent Hoursepower Shaft Horsepower RPM Take-off (5 min) 575 605 2000 (100%) Max. Continuous 500 529 2000 (100%) S e e N O T E 3 Max. Allowable Measured by the torquemeter for below standard inlet air temperature Power and/or ram conditions is 575 SHP for take-off (5 min.) and 500 SHP for Max. continuous while not exceeding EGT limits. Temperature Exhaust gas temperature (standard sea level day) Limits Takeoff (5 min.) 1100°F (596°C) Maximum 1060°F (571°C) continuous Starting Transient (one sec.) 1450°F (788°C) NOTE: EGT limits vary with ambient temperature and pressure. Refer to the applicable FAA Approved Airplane Flight Manual for actual limits under nonstandard conditions. Oil Inlet -40°F (-40°C) min. Temperature +260°F (+127°C) max. MIL-L-23699 (Mobil Jet II) oil required Propeller and Hub: Hartzell Model HC-B3TN-5C, or -5E, or -5M Propeller Limits Blades: Hartzell Model T10176 (Option 1) Diameter: 101-3/8” Max., 96-3/8” Min. No further reduction in diameter is permitted. Single rotation three blades assembly with gov. setting of 2000 p.r.p.m. (41.730 e.r.p.m.).feathering and reversing provisions, selective pitch control, negative torque control and electrical ice control. Blade Station at which pitch settings (degrees) are measured is 30 inch station. a. Low pitch stop (min. Flt. Idle) 11. ° + 1° b. Start 3.25° + .50° c. Reverse -10° + 1° d. Feather 86.5° + .25° Eligible with TPE331-25, TPE331-47 or TPE331-1-101B engines. Number SA1171WE **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1171WE** Propeller and HUB: Hartzell Model HC-B3TN-5C, or -5E, or -5M Propeller Limits BLADES: Hartzell Model T10178 (Option 2) Diameter 96” Max. 93-1/2” Min. No further reduction in diameter is permitted. Singles rotation three blade assembly with gov. setting of 2000 p.r.p.m. (41,730 e.r.p.m.) Propeller assembly is complete with spinner, feathering the reversing provisions, selective pitch control, negative torque control, and electrical ice control. Blade Stations at which pitch settings (degrees) are measured is 30 inch station. a. Low pitch stop (min. Flt. Idle) 11. ° + 1°. b. Start 4.° 10.5° c. Reverse -10° + 1° d. Feather 86.5° + .25° Eligible with TPE331-25, TPE331-47 or TPE331-1-101B engines. Supplement No. 1 to Volpar Airplane Flight Manual No. D-100 is required when these propellers are installed. Airspeed Limits Max. operating speed 240 MPH (208 knots) Maneuvering speed 153 MPH (133 knots) Flaps extend speed a. Power off 140 MPH (122 knots) b. Power on 120 MPH (104 knots) Landing gear operating speed 160 MPH (139 knots) Landing gear extend speed 160 MPH (139 knots) C.G. Range +114.08” to +121.5” at 10,286# (Gear extended) +107” to +121.5’ at 7,740# Straight line variation between points given. Moment change due to gear retraction: -8,931 in lbs. See Volpar AFM D-100. Max. Operating 16,500 feet Altitude Max. Weight Take-off 10,286# Landing 9,772# Max. Zero Fuel 9,000# **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1171WE** Fuel Capacity Main Tanks (2) 100 gallons 670# required Inboard Aux. (2) 152 gallons 1018# required Rear Inboard Aux. (2) 50 gallons 335# optional Option 1--- Outboard Aux. (2) 120 gallons 805# optional Option 2--- Outboard Aux. (2) 200 gallons 1340# optional Option 3--- Outboard Aux. (2) 330 gallons 2210# optional Above weight based on 6.7#/gallon See NOTE 1(a) and NOTE 2 See Volpar Airplane Flight Manual D-100 for fuel management procedures. Oil Capacity 3 gallons (23#) total per aircraft Above based on 7.7#/gallons See NOTE 1(b) Control Surface Wing flaps -- Down 45° Aileron tab up 22° Down 19° Aileron up 38 1/2° Down 21° Elevator tab up 12° Down 19° Elevator up 35° Down 25° Rudder tab (double) right 29° Left 39° Rudder tab (single) right 27 1/2° Left 30 1/2° Rudder right 19° Left 19° Serial Nos. Eligible All D18C, D18S, E 18S, E18S-9700, C-45G, TC-45G, C45H, TC-45H, TC-45J, (SNB-5), JRB-6, G18S, H18, C-45J airplanes that are eligible for airworthiness certification under Type Certificate No. 765 and have been modified in accordance with FAA Sealed Volpar Drawing List No. 1800, dated June 23, 1965 or later FAA Approved revision. Inspection Period The repetitive inspection specified in AD-64-21-02 and AD-64-21-03 must be accomplished at intervals not to exceed 400 hours time in service. All other items in AD-64-21-02 and AD-64-21-03 remain t h e s a m e . **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1171WE** Data Pertinent to all Models Datum Located 102 in. forward of centerline of wing main spar. (Placard demoting datum installed on bottom of fuselage). Leveling Means Models D18C, D18S, SNB- 5, JRB-6, C-45 Series Leveling lugs on top of fuselage, forward of cabin door. Models E18S, E18S-9700, G18S, H18. Two extended screws on right side of airplane at bulkhead No. 8, aft of emergency exit. Plumb bob is used to level. Certification Basis a. Civil Air Regulation Part 3 dated November 13, 1945. b. CAR 3 dated May 15, 1956, plus Amendments 3-1 through 3-8 as applicable to the powerplant installation. c. Those conditions listed in FAA letters to Volpar, Inc. dated January 26, 1965, and June 2, 1965. Supplemental Type Certificate NO. SA1171WE issued 02-17-66. Date of Application for Supplemental Type Certificate 07-20-64. Equipment The basic required equipment as described in the applicable Airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition: a. Volpar Aircraft Flight Manual D-100 is required. b. Goodrich wheel 3-1174 and brake 2-993 assembly are required. (Tri-gear configuration) a. Volpar Airplane Flight Manual Supplement No. 1 is required for Hartzell HC-B3TN/T10178 propellers. b. Volpar Airplane Flight Manual Supplement No. 3 is required for TPE331-47-A and TPE331-47-B engines. c. Volpar Airplane Flight Manual Supplement No. 4 is required for TPE331-1-101B engines. NOTE 1 Current weight and balance data including list of equipment included in the certificated empty weight and loading instructions when necessary, must be provided for each aircraft at the time of original certification. b. The certificated empty weight must include system fuel (unusable) of : Number SA1171WE **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1171WE** NOTE 1: Main Tanks (2) 1 gallon (cont.) Inboard Aux. (2) ½ gallon Rear Inb’d Aux. (2) ½ gallon Option 1 - Outb’d Aux. (2) 120 gallons 1 gallon Option 2 - Outb’d Aux. (2) 200 gallons 1 ½ gallons Option 3 - Outb’d Aux. (2) 330 gallons 2 ½ gallons c. The certificated empty weight must include system oil (unusable) of 1 quart total per aircraft. NOTE 2: Fuel weight in this data sh eet is based on 6.7#/gallon. For weight and Balance calculations, fuel weights must be derived from the “Specific Weight vs. Temperature” chart, P. 2-3 in the Volpar Airplane Flight Manual D-100. NOTE 3: The Engine Limit ratings of this data sheet are based on static sea level conditions, compressor inlet air (dry) 15°C, 29.92 in. hg. no external Accessory loads, no air bleed or anti-icing airflow. See Volpar AFM D-100, for non-standard day. NOTE 4: Deleted NOTE 5: FAA has determined that the interrelationship between this change and STC SA305WE (raised cabin) will introduce no adverse effect upon the airworthiness of Beech Models D18C, D18S, C-45G, TC-45G, C-45H, TC-34H, TC-45J (SNB-5). NOTE 6: CAUTION The approval of this change in Type Design applies basically to the Beech Models JRB-6, D18C, D18S, E18S, E18S-9700, C-45G, TC-45G, C-45H, TC-45H, TC-45J(SNB-5), G18S, H18, C-45J series aircraft only. This approval should not be extended to other specific airplanes of these models 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 airplane. The above applies, as well, to modifications subsequently added to aircraft incorporating this change in Number SA1171WE **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1171WE** NOTE 6 See Volpar AFM-D-100, P. 1-10. (cont.) Particular attention should be direct ed to any modifications which affect the engine installation, fuel system (incl uding type of fuel) or electrical system as approved for this STC. NOTE 7: Deleted NOTE 8: Phillips anti-icing fuel additive PFA-55 MB may be used in concentration delivered to airplane does not exceed 0.15% by volume. No fuel system antiicing credit is allowed. NOTE 9: Deleted NOTE 10: Grade 80/87 octane aviation gasoline or white gasoline is approved for emergency use. Do not exceed 1000 gallons per engine per 100 hours of operation. The amount of gasoline used must be entered in the engine log book. - END - ## Every issue (1) - May 1, 2006: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/9a/42/9a42b812a747faa0313672b27da33d1fbf8cd6c4989ae528b6929f86853a6eeb) --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.