STC SA3385WE

This Certificate issued to Southwestern Aero Exchange, Inc.

18502 East 108th Street North Owasso, OK 74055-8124 Part * of the Civil Air Regulations. *See attached STC SA3385WE Addendum for certification basis.

A-765 Beech D18C, D18S, E18S, E18S-9700, C-45G, TC-45G, C-45H, TC-45H, TC-45J, SNB-5, JRB-6, G18S, H18 Description of Type Design Change: Installation of AiResearch TPE 331-1-101B engines and increase gross weight to 11500 pounds in accordance with FAA sealed American Turbine Engine Co. Top Drawing No. 1026, Revision C, dated January 23, 1980 or later FAA sealed revision.

See attached SA3385WE 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 SA3385WE Addendum, which is a part of this certificate.

Date of application: August 2, 1976

Date of issuance : April 15, 1977

Date reissued: May 10, 1977; Jan. 23, 1998;

May 1, 2006

Date amended:: Jul. 25, 1977; Mar. 1, 1985

( Signature)

Manager, Technical & Administrative Support Staff, Los Angeles Aircraft Certification Office ( Title)

Number SA3385WE

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA3385WE

The conditions and limitations of Aircraft Specification No. A-765 applies except as follows:

This addendum, which is part of Supplemental Type Certificate No. SA3385WE 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, G18S, H18

Engines 2 AiResearch TPE331-1-101B (tur bo-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 NOTES 6 & 7.

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%) S e e N O T E 3

Max. Allowable Measured by the torquemeter for below standard inlet air temperature and/or Power 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 second) 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 non-standard conditions.

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA3385WE (cont.)

NOTE: (cont.) Oil Inlet -40°F (-40°C) min.

Temperature +260°F (+127°C) max.

MIL-L-23699 (Mobil Jet II) oil required

Propeller and Propeller Limits The following propellers are approved for installation. Propeller assembly is complete with spinner, feathering and reversing provisions selective pitch control, negative torque control, and electrical ice control. Supplement No.

D100A to Volpar Airplane Flight Manual is required. When Hartzell HC- B3TN-5C/T10178-5Q propellers (Option III) are installed Supplement No.

D100B is required in addition to supplement no. D100A.

OPTION I Hub: Hartzell Model HC-B3TN-5C, or -5E, or -5M Blades: Hartzell Model T10176 Diameter: 96 3/8 to 99 3/8 inches, no further reduction in diameter is permitted.

Blade/Angels at 30 inch station:

High (feather) 86.5° + 0.25° Starting 3.25° + 0.50° Flight Idle 11.0° + 0.2° Reverse -10.0 + 0.5°

OPTION II Hub: Hartzell Model HF-B3TN-5C, or -5E, or -5M Blades: Hartzell Model T10178 Diameter: 93 ½ to 96 inches, no further reduction in diameter is permitted.

Blade/Angels at 30 inch station:

High (feather) 86.5° + .25° Starting 4.0° + .50° Flight Idle 11.0° + 1.00° Reverse -10.0° + 1.00°

Optional settings when modified in accordance with Volpar Service Bulletin No. 8T and 10T.

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA3385WE (cont.)

OPTION II (cont.)

High (feather) 86.5° + .20° Starting 2.5° + .20° Flight Idle 10.5° + .20° Reverse -08.0 + .20°

OPTION III Hub: Hartzell Model HC-B3TN-5C, or 5E, or 5M Blades: Hartzell Model T1078-5Q Diameter: 96 inches, no reduction in diameter is allowed.

Blade/Angles at 30 inch station:

High (feather) 86.5° + .20° Starting 2.5° + .20.2° Flight Idle 10.5° + .20.2° Reverse - 8.0 + .20.2°

Airspeed Limit 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 Propeller Options I and II Gear extended) +117.45” to +121.5” at 11500# +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.

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 Models D18C, D18S, SNB-5, JRB-6, C-45 Series Leveling lugs on Means top of fuselage, forward of cabin door. Models E18S, E18S-9700,

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA3385WE (cont.)

Leveling G18S, H18 – Two extended screws on right side of airplane at bulkhead Means (cont.) No. 8, aft of emergency exit. Plumb bob is used to level.

Certification a. Civil Air Regulation Part 3 dated November 13, 1945.

Basis 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. SA3385WE issued 04/15/77. Date of Application for Supplemental Type Certificate 08/02/76.

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).

c. Volpar Airplane Flight Manual Supplement No. D-100A is required.

In addition –

d. When Hartzell HC-B3TN-5C/T10178-5Q propellers (Option III) are installed Volpar Airplane Flight Manual Supplement No. D-100B is also required.

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 tie of original certification.

a. The certificated empty weight must include system fuel (unusable) of:

Main Tanks (2) 1 gallon Inboard Aux. (2) ½ gallon Rear Inboard 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

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA3385WE (cont.)

b. The certificated empty weight must include system oil (unusable) of 1 quart total per aircraft.

Propeller Option III Only

+117.20” to +121.5” at 11400# +107” to +121.5” at 7,740# Straight line variation between point given. Moment change due to gear retraction: -8,931 in lbs. See Volpar AFM-D-100.

Max. Operating 16,500 feet Altitude

Max. Weight Propeller Options I and II Take-off 11500# Landing 11000#

Propeller Options III Take-off 11409# Landing 11000#

Max. Zero 10, 3000# Fuel Weight

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 2 -- Outboard Aux. (2) 330 gallons 2210# optional Above weights based on 6.7#/gallon See NOTE I(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 I(b)

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA3385WE (cont.)

Control Surface Wing flaps -- Down 45° Movements Aileron tab up 22° Down 19° Aileron up 38.5° Down 21° Elevator up 35° Down 25° Rudder tab (double) right 29° Left 29° Rudder tab (single) right 27.5° Left 30 ½ ° Elevator up 12° Down 19° Rudder right 19° Left 19°

Serial No. All D18C, D18S, E18S, E18S- 9700, C-45G, TC-45G, C-45H, TC-45H, TC-45J Eligible (SNB-5), JRB-6, G18S, H18 airplanes that are eligible for airworthiness certification under Type Certificate No. 765 and have been modified in accordance with FAA Sealed American Turbine Engine Drawing List No. 1026.

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-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: 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-45H, TC-45J, SNB-5.

NOTE 5: 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-45H, TC-45J, (SNB-5), G18S, H18 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 type Design. Particular atten tion should be directed to any modifications

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA3385WE (cont.)

Which affect the engine installation, fuel system (including Type of fuel) or electrical system as approved for this STC.

See Volpar AFM D-100, P. 1-10

NOTE 6: Phillips anti-icing fuel additive PFA-55 MB may be used if concentration delivered to airplane does not exceed 0.15% by volume. No fuel system anti-icing credit is allowed.

NOTE 7 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.

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