STC SA1636WE

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA1636WE This certificate issued to: Southwestern Aero Exchange, Inc.

18502 East 108h Street N.

Owasso, OK 74055-8124 Part * of the Civil Abir Pegulations. *See page 6 of this STC for certification basis.

Original Product Type Certificute Number: A-765 Model: D18C, D18S, E18S, E185-9700, G18S, H18, C-45G, . TC-45G, C-45H, TC-45H, TC-45J (SNB-5), JRB-6 Description of Type Design Change: Installation of AiResearch TРE331 series engines, tricycle landing gear and ventral fin, extension of fuselage and related changes. See page 6 of this STC for required 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.

The conditions and limitations of Aircraft Specification No. A-765 applies except as noted on page 3 through 8 of this STC.

See attached STC SA1636WE Addendum, which is a part of this certificate.

Date of Application: December 28, 1966 Date Reissued: January 23, 1998; September 27, 2004 May 1, 2006 Date of Issuance: March 29, 1968 Date Amended: August 1, 1968; April 20, 1972 FEDERAL AVIATION By Direction of the Administrator (Signature) * TOMINISTRATO Manager, Technical & Administrative Support Staff, Los Angeles Aircraft Certification Office (Title)

United States of America Heparimeni ai Granspariation » Jederal Abialim Administration Supplemental Type Certificate Number: SA1636WE Supplemental Type Certificate ADDENDUM NO. SA1636WE Model: Beech D18C, D18S, E18S, E18S-9700, G18S, H18, C-45G, TC-45G, C-45H, TC-45H, TC-45J (SNB-5), JRB-6 Engines 2 AiResearch TPE331-1-101B conforming to AiResearch Equipment List No.

893401-1.

Fuel Aviation Turbine Fuels ASTM Designation D1655-66T, Type Jet A, Jet B and Jet A-1. Military Fuels MIL-J-5624G-1, Grades JP-4, JP-5 and MIL-F-5616 1, Grade JP-1 See NOTES 5 and 6.

Oil MIL-L-23699A (Mobil Jet II) required when operating in ambient temperatures above 59°F (15°C).

MIL-L-7808D and MIL-L7808F may be used in lieu of MIL-L-23699A when operating in ambient temperature at or below 59°F (15°C).

Engine Takeoff Shaft Horsepower 575 Limits (5 min.) Equivalent Shaft Horsepower 605 Maximum Shaft Horsepower 500 Continuous Equivalent Shaft Horsepower 529 Propeller R.P.M. Maximum 2000(100%) Torque Takeoff (5 min.) 1510 lb. Ft.

(52.8 psi) Maximum continuous 1313 Ib. Ft.

(48.0 psi) Turbine Takeoff (5 min.) 1100°F (596°C) Temperature Maximum continuous 1060°F (571°C) (See NOTE 3) Starting transient (1 sec.) 1450°F (788°C) Oil Inlet -40°F (-40°C) minimum Temperature +260°F (+127°C) maximum with MIL-L-23699A oil +200°F (+93°C) maximum with MIL-L-7808 oils.

Finiten States O1 Americs Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA1636WE Supplemental Type Certificate ADDENDUM NO. SA1636WE Propeller and 2 Hartzell HC-B3TN/T10176 Propeller Diameter: 99 3/8 in. Max. 96 3/8 in Min.

Limits No further reduction in diameter is permitted.

(Option 1) Pitch settings at 30-inch station:

Low pitch stop (min. Flt. Idle) 11.0° + 1° Start 3.25° + .50° Reverse -8.0 ‡ .5° Feather 86.5 + 25° (Option 2) 2 Hartzell HC-B3TN/T10178H Diameter: 96 in. max. 93 ½ in. Min.

No further reduction in diameter is permitted.

Pitch settings at 30-inch station:

Low pitch stop (min. Flt. Idle) 10.5 + 2° Start 2.5 + 2° Reverse -8.5 + .2° Feather -86.5 + .25° Airspeed Max. operating speed 240 MPH (208 knots) Limits Maneuvering speed 153 MPH (133 knots) (CAS) Flaps extend speed

a. Power Off 165 MPH (143 knots)

b. Power On 134 MPH (116 knots) Landing gear operating speed 160 MPH (139 knots) Landing gear extend speed 160 MPH (139 knots) C. G. Range +113.3 to +117 at 11,500 Ibs.

(Gear Extended) +107 to +117 at 10,000 Ibs. or less Straight line variation between points given.

Moment change due to gear retraction -8.931 in. Ibs.

See Volpar AFM D-105.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA1636WE Supplemental Type Certificate ADDENDUM NO. SA1636WE Max. Operating 16,500 feet Altitude Max. Weights Takeoff 11,500 Ibs.

Landing 11,000 Ibs.

Empty Wing Weight 10,500 Ibs.

The term "maximum zero fuel weight" is not utilized because of the possibility of operating the aircraft with either the wing baggage or auxiliary fuel tank configuration.

Fuel Capacity No Tank of Fuel Capacity/ Wt. Of Fuel/ Location Tanks 2 Tanks 2 Tanks Main Tanks (2) 100 gallons 670 Ibs. required Inboard Aux. 152 gallons 1018 Ibs. optional Rear Inboard Aux. (2) 50 gallons 335 Ibs. optional Option 1 - Outboard Aux. (2) 120 gallons 804 Ibs. optional Option 2 - Outboard Aux. (2) 200 gallons 1340 Ibs. optional Option 3 - Outboard Aux. (2) 330 gallons 2210 Ibs. optional See NOTE 1(a) and NOTE 2.

See Volpar Airplane Flight Manual D-105 for fuel management procedures.

Oil Capacity 3 gallons (23 1bs.) total per aircraft Above based on 7.7 1bs./gallons See NOTE 1(b).

Control Wing flaps Down 45° Surface Aileron tab up 22° Down 19°

• Movements Aileron up 38.5° Down 21° Elevator tab up 12° Down 19° (See NOTE 7) Elevator up 35° Down 25° Rudder tab (Double) right 29° Left 29° Rudder tab (Single) right 28-33° Left 28-33° Rudder right 19° Left 19°

rited Sinies WE America Deparimeni nf Granzparialim - Hederal Abialim Adminiziratim Supplemental Type Certificate Number: SA1636WE Supplemental Type Certificate ADDENDUM NO. SA1636WE Serial Nos. All D18C, D18S, E18S, E18S-9700, G18S, H18, C-45G, TC-45G, C-45H, Eligible TC-45H, TC-45J (SNB-5), and JRB-6 airplanes that are eligible for (See NOTE 4) airworthiness certification under Type Certificate No. 765 and have been modified in accordance with FAA sealed Aircraft Technical Service Summary Drawing No. 874, revision Q, subsequent FAA sealed revision.

Wing spar modifications in accordance with Supplemental Type Certificates No. SA832SW and SA895SW are also required.

Data pertinent to all models Datum Located 102 in. forward of centerline of wing main spar. (Placard denoting Datum installed on bottom of fuselage) Leveling Models D18C, D18S, SNB-5, JRB-6, C-45 series - leveling lugs on top of Means fuselage forward of cabin door. Models E18S, E18S-9700, G18S and H18 - Two extended screws on right side of airplane at bulkhead No. 8, aft of Emergency exit. Plumb bob is used to level.

Certification a. Civil Air Regulations Part 3, effective 13 November 1945.

Basis b. CAR 3 dated 15 May 1956 plus amendments 3-1 through 3-8 as applicable to the powerplant installation.

c. Those special conditions listed in FAA letters to Volpar, In., dated 26 January 1965, and 2 June 1965.

Supplemental Type Certificate No. SA1636WE issued 29 March 1968. Date of application of Supplemental Type Certificate 28 December 1966.

Equipment The basic required equipment as described in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for airworthiness certification. In addition:

a. Volpar Aircraft Flight Manual D-105 plus revision 11 is required.

b. Goodrich wheel 3-1174 brake 2-993 assembly and 8.50-10 Type III 10 PR tire.

Lines States OLAmerica Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA1636WE Supplemental Type Certificate ADDENDUM NO. SA1636WE 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.

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

No.

Tank of Fuel Capacity/ Unusable Fuel/ Location Tanks 2 Tanks 2 Tanks Main Tanks (2) 100 gallons 1 gallon Inboard Aux. (2) 152 gallons /½ gallon Rear Inb'd Aux. (2) 50 gallons ½ gallon Option 1 - Outb'd Aux. (2) 120 gallons 1 gallon Option 2 - Outb'd Aux. (2) 200 gallons 1½ gallons Option 3 - Outb'd Aux. (2) 330 gallons 2 ½ gallons

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

NOTE 2. Fuel weights in this data sheet are based on 6.7 Ibs./gallon. For weight and balance calculations, fuel weights must be derived from theSpecific Weight vs. Temperature chart, P. 2-14 in the Volpar Airplane Flight Manual D-105.

NOTE 3. The turbine temperature (EGT) limits vary with ambient temperature. Refer to the OAT-EGT gage on the cockpit instrument panel and/or the applicable FAA Approved Airplane Flight Manual for the EGT limit for each ambient temperature.

NOTE 4. CAUTION:

The approval of this change in the Type Design applies basically to the Beech models noted on page 1 of this STC 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 by

United States of America Department of Transportation - Jeeral Abialim Administraiim Supplemental Type Certificate Number: SA1636WE Supplemental Type Certificate ADDENDUM NO. SA1636WE NOTE 4. CAUTION: (CONTINUED) the installer 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. This determination should include consideration of significant changes in weight distribution such as an increase in the fixed disposable weight in the fuselage. The above applies, as well, to modifications subsequently added to aircraft incorporating this change in Type Design.

NOTE 5. Philips 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 antiicing credit is allowed.

NOTE 6. 80/87 minimum grade 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.

NOTE 7. Aileron-Rudder Interconnect Rigging Table Aileron Position Rudder Travel

1. Neutral

2. Left Aileron Full Up Right Aileron Full Down

3. Left Aileron Full Down 12°+ Right, 12°+ 1° Left 4°+ 1/2° Right, 19°+ 1-1/2° Left 19°+ 1-1/2° Right, 4°+ 1/2° Left Right Aileron Full Up

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