# STC SA1223WE - Type: Supplemental type certificate - Status: Current, Reissued - Holder: SOUTHWESTERN AERO EXCHANGE INC., United States - Description: See STC SA1223WE Addendum. - Applied: April 1, 1966 - Status date: May 1, 2006 - Product: Aircraft, Small Multi-Engine - Certification basis: Part 3, Part 21 - Data sheets: [TCDS A-765](https://openairdocs.org/tcds/A-765) - Certificate PDF: https://openairdocs.org/files/sha256/c9/65/c9655badc85c0a0a5495f2660a0445708246cc784fb14fd19b0f98df603912ee - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/68FC2E8CB3654B1A8625719A0050E211.0001 - DRS record last changed: December 6, 2025 - Page: https://openairdocs.org/stc/SA1223WE ## ADs that name it (0) None. ## Approved models (1) - Raytheon Aircraft Company C-45H ([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 North Owasso, OK 74055-8124 Part CAR 3 of the Civil Air Regulations. A-765 BEECH C-45H Description of Type Design Change: See attached STC SA1223WE Addendum, which is a part of this certificate. 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 SA1223WE Addendum, which is a part of this certificate. This certificate and the supporting data, which is the basis for approval, shall remain in effect until surrendered, suspended, revoked or a termination date is otherwise established by the Administrator of the Federal Aviation Administration. Date of application: April 1, 1966 Date of issuance: June 3, 1966 Date reissued: Jan. 23, 1998; May 1, 2006 ( Signature) Manager, Technical & Administrative Support Staff, Los Angeles Aircraft Certification Office ( Title) Number SA1223WE **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1223WE** The conditions and limitations of Aircraft Specification No. A-765 applies except as follows: This data sheet, which is a part of Supplemental Type Certificate No SA1223WE, prescribes conditions and limitations under which the product for which the STC was issued meets the airworthiness requirements of the Civil Air Regulations. The information contained herein is in addition to the conditions and limitations listed in Volpar Flight Manual D-102 dated 06-03-66. Supplemental T. C. Holder: Southwestern Aero Exchange, Inc. 18502 East 108 th Street North Owasso, OK 74055-8124 I – Models: Beech C-34H with STC SA305WE required. (Raised cabin). Engines 2 AiResearch TPE331-47 (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 and Military Fuels MIL-J-45624, Grades JP-4, JP-5, MIL-F-5616-1, Grade JP-1. Engine Limits Static Sea Level Rating Shaft Equivalent Horsepower Shaft Horsepower RPM Takeoff (5 minutes) 575 605 2000 Max. Continuous 500 529 2000 (100%) 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. Max. Permissible a. Max. EGT Temp: Take-off 1070°F (577°C) Temperatures See NOTE 3 Max. Continuous 1026°F (552°C) b. Max. Transient: (not to exceed 1 sec.) 1500°F (815°C) c. Oil Inlet Temp: MIL-L23699 (Mobil Jet II) minus 40°F (-40°C) minimum, 260°F (127°C) maximum. **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1223WE** Propeller and 2 Hartzell HC B3TN-5/T10176 Propeller Limits Diameter: 101-3/8” Max., 99-3/8” Min. No further reduction in diameter is permitted. Single 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 and reversing provisions, selective pitch control, negative torque control, and electrical i c e c o n t r o l . 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° +.25° c. Reverse -10° +1° d. Feather 86.5° +.25° Airspeed Limits Max. operating speed 240 MPH (208 knots) Maneuvering speed 153 MPH (104 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-102, P. 1-8, dated 06-03-66. Max. Operating Altitude 16, 500 ft. Max. Weight Take-off 10,286# Landing 9,772# Max. Zero Fuel Weight 9,000# Number SA1223WE **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1223WE** Fuel Capacity Main tanks (2) 100 gallons 670# required Outb’d Aux. (2) 200 gallons 1340# optional Inb’d Aux. (2) 152 gallons 1018# required Rear Ind’b Aux (2) 50 gallons 335# optional Total per aircraft 502 gallons 3363# Above weights based on 6.7#/gallons See NOTE 1(a) and NOTE 2 Oil Capacity 3 gallons (23#) total per aircraft Above based on 7.7#/gallons See NOTE 1(b) Control Surface Movements Wing Flaps __ Down 45° Aileron Tab (left only) Up 22° Down 19° Aileron Up 38 1/2° Down 21° Elevator tab Up 12° Down 19° Elevator Up 35° Down 25° Rudder tab Right 29° Left 29° Rudder Right 19° Left 19° Serial Nos. Eligible All serial numbers lis ted for C-45H in Aircraft Specification A-765. Inspection Period The repetitive inspection specified in AD-64-21-03 must be accomplished at intervals not to exceed 400 hours time in service. All other items in AD-64-21-03 remain the same. Data Pertinent to all Models Datum Located 102in. forward of intersection of wing main beam and side of fuselage. Leveling Means Leveling lugs on top of fuselage, forward of entrance door. Certification Basis a. Civil Air Re gulation Part 3 dated November 13, 1945. b. CAR # 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 ADDENDUM NO. SA1223WE** Supplemental Type Certificate No. SA1223WE issued 06-03-66. Date of Application for Supplemental Type Certificate 04-01-66. 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 Airplane Flight Manual D-102 dated 06-03-66, is required. b. Goodrich wheel 3-1174 and brake 2-993 assembly are required. NOTE 1. Current weight and balance data including list of equipment included in certificated empty weight and loading instructions when necessary, must be provided for each aircraft at the time of original certification. a. The certificated empty weight must include system fuel (unusable) of: Main tanks (2) 1 gallon Outb’d Aux. (2) 1 ½ gallons Inb’d Aux. (2) ½ gallon Rear Inb’d Aux. (2) ½ gallon Total per aircraft 3 ½ gallons b. The certificated empty weight include system oil (unusable) of 1 quart total per aircraft. NOTE 2. Fuel weight in this data sheet 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-102 dated 06-03-66. NOTE 3. The Engine Limit ratings for 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-102 dated 06-03-66 for non-standard day. NOTE 4. See Volpar AFM D-102, P. 2-9 and P. 2-13 dated 06-03-66 for fuel management procedures. **SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA1223WE** **NOTE 5. CAUTION** The approval of this change in Type Design applies basically to the Beech Model C-45H 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 to the Type Design. See Volpar AFM D-102, P. 1-10, dated 06-03-66. Particular attention should be directed to any modifications which affect the engine installation, fuel system (including type of fuel) or electrical system as approved for this STC. - END - ## Every issue (1) - May 1, 2006: Reissued, Current. [certificate](https://openairdocs.org/files/sha256/c9/65/c9655badc85c0a0a5495f2660a0445708246cc784fb14fd19b0f98df603912ee) --- 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.