STC SA2204WE

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA2204WE This certificate issued to: Southwestern Aero Exchange, Inc.

18502 East 108th Street North Owasso, OK 74055-8124 Part * of the Civil Air Pegulations. * See continuation sheet 7 for certification basis.

Original Product Type Certificate Number: A-765 Make: Beech Model: D18C, D18S, E185-9700, C-45G, TC-45G, C-45H, TC-45H, TC-45J, (SNB-5), JRB-6, E18S, G18S, H18 Description of Type Design Change: Installation of 2 AiResearch TPE 331-1 series Turbo Prop engines with Hartzell HCB3TN propellers; eighty-one and one-half inches extension of fuselage and ventral fin, tricycle landing gear installation and related modifications in accordance with FAA sealed Volpar, Inc. drawing 2500.

Limitations and Conditions: The conditions and limitations of Aircraft Specification No. A-765 applies except as noted on continuation sheet 3 through 10. 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.

Date of Application: 5 May 1969 Date Reissued: Jan 23, 1998; May 1, 2006 Date of Issuance: 17 July 1970 Date Amended: 27 August 1971 HOAL VES By Direction of the Administrator TAMANSTRAD Manager, Technical & Administrative Support (Signature) Staff, Los Angeles Aircraft Certification Office (Title)

TRANSFER ENDORSEMENT Transfer the ownership of the Supplemental Type Certificate Number_ to (Name of transferee) (Address of transfer) (Number and street) (City, State, and Zip code) from (Name of grantor) (Print or type) (Address of grantor) (Number and street) (City, State, and Zip code) Extent of Authority (if licensing agreement):_ Date of Transfer:

Signature of grantor (In ink):

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuatian Sheet) Number: SA2204WE Model: Beech D18S, D18C, E18S, E18S-9700, C-45G, G-45H, TC-45G, TC-45H, TC-45J, (SNB-5), JRB-6, G18S, H18 Engines 2 AiResearch TPE331-1-101B (turbo-prop) with 1:20.865 reduction gear ratio.

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 temperature above 60°F (15°C).

MIL-L-7808D and MIL-L-7808F may be used when operating in ambient temperature below 59°F (15°C).

Engine Ratings (See Level Static - See NOTE 3) Take-Off (2 min) Shaft Horsepower 620 Equivalent Shaft Horsepower 664 Propeller R.P.M. 2000(100%) Torque 1620 ft. Ibs. (56.65 psi) Maximum Shaft Horsepower 500 Continuous Equivalent Shaft Horsepower 529 Propeller R.P.M. 2000 (100%) Torque 1313 ft. Ibs. (48.0 psi) Maximum Measured by the torquemeter for below standard inlet air temperature and/or Allowable ram conditions is 620 SHP for take-off (2 minutes) and 500 SHP for max.

Power conditions while not exceeding EGT limits.

Temperature Exhaust gas temperature (standard sea level day) Limits Take-off (2 min.) 1112°F (600°C) Maximum continuous 1065° F (574°C) Starting Transient (one second) 1450° F (788°C)

47.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA2204WE 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° (-40°C) min.

+260°F (+127°C) max.

MIL-L-23699 (Mobil Jet II) oil required for operation above 60°F (15°C) ambient air temperature. MIL-L-78808F and MIL-L-7808D may be used when ambient air temperature is below 59°F (15°C).

Propeller and 2 Hartzell HC-B3TN/T10176 Propeller Limits Diameter: 99 3/8 in max., 96 3/8 in min.

(Option 1) No further reduction in diameter is permitted.

Pitch settings at 30-inch station:

Low pitch stop (min. ft. idle) 11° +0.2° Start 3.25° t....50° Reverse -8.0° ‡ ...50° Feather 86.5° + .25° Maximum allowable variation between two propellers as flight idle blade angle is 0.4° (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° Maximum allowable variation between two propellers at flight idle blade angle is 0.4° Airspeed Limits Max. operating speed 240 MPH (208 knots) (CAS) Maneuvering speed 153 MPH (133 knots) 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)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA2204WE C.G. Range +113.3 to +117 at 11,500 lbs.

(Gear Extended) +107 to +117 at 10,000 1bs. or less Straight line variation between points given.

Moment change due to gear retraction -8,931 in. Ibs.

See Volpar AFM D-109 or D-111.

Max Operating 16,500 feet Altitude Max. Weights Take-off 11,500 Ibs.

Landing 11,000 Ibs.

* Empty Wing Weight 10,500 Ibs.

NOTE: * 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.

Tank No. of Fuel Capacity/ Wt. of fuel/ Location Tanks 2 Tanks 2 Tanks Fuel Capacity Main Tanks (2) 100 gallons 670 Ibs. required Inboard Aux. (2) 152 gallons 1018 Ibs. optional Rear Inboard (2) 50 gallons 335 1bs. optional Aux.

Option I 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 Above weights based on 6.7 Ibs./gallon See NOTE 1(a) and NOTE 2.

See Volpar Airplane Flight Manual D-109 or D-111 For fuel management procedures.

Oil Capacity 3 gallons (23 Ibs.) total per aircraft Above based on 7.7 1bs./gallon See NOTE 1(b) Control Surface Wing flaps Down 45° Aileron tab up 22° Down 19° Aileron up 38.5° Down 21°

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA2204WE Control Surface Elevator tab up 12° Down 19° (Cont.) 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° Aileron-Rudder Aileron Position Rudder Travel Interconnect Rigging Table 1. Neutral 12° + 1° Right 12°+ 1° Left

2. Left Aileron Full (Up) 4° + ½° Right 19°+ 1 ½° Left Right Aileron Full (Down) Left Aileron Full (Down) 19° + 1 ½° Right 4°+ ½° Left Right Aileron Full (Up) Serial Nos. All D18C, E18S, E18S-9700, C-45G, TC-45G, C-45H, TC-45H, TC-45J (SNB-5), G18S, H18, JRB-6 airplanes that are eligible for airworthiness certification under Type Certificate No. 765 and have been modified in accordance with FAA sealed VOLPAR, INC., Summary Drawing No. 2500, revision D or subsequent FAA sealed revisions.

NOTE: Wing spar modifications in accordance with Supplemental Type Certificate Nos. 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 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, and H18, JRB-6. Two extended screws on right side of airplanes at bulkhead No. 8, aft of emergency exit. Plumb bob is used to level.

*Certification a. Part 03 of the Civil Air Regulation 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 conditions listed in FAA letters to Volpar, inc., dated 26 January 1965, and 2 June 1965.

d. SFAR 23 effective 7 January 1969.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA2204WE Supplemental Type Certificate No. SA2204WE issued 17 July 1970. Date of application for Supplemental Type Certificate 5 May 1969.

Production None Basis An in-flight operational check must be conducted in accordance with FAR

91.167(a) for each airplane modified to incorporate this Supplemental Type Certificate. When original airworthiness certification has not previously been accomplished, the applicant must comply with FAR 21.130 and 21.183

Equipment The basic required equipment as prescribed in the applicable airworthiness Regulations (See Certification Basis) and the additional items shown in Volpar Turboliner II Equipment List 2514 must be installed in the aircraft for Airworthiness certification. In addition, Volpar Airplane Flight Manual D-109 or D-111 is required. See NOTE 9 for applicability.

NOTE 1: Current weight and balance data including list for 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:

Tank No. of Fuel Capacity/ Unusable Fuel/ Location Tanks 2 Tanks 2 Tanks Main Tanks (2) 100 gallons gallon Inboard Aux. (2) 152 gallons ½ gallon Rear Inboard Aux. (2) 50 gallons ½ gallon Option 1 Outboard Aux. (2) 120 gallons 1 gallon Option 2 Outboard Aux. (2) 200 gallons 1 ½ gallons Option 3 Outboard Aux. (2) 330 gallons 2½ gallons

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

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA2204WE NOTE 2: Fuel weights in this data sheet are based on 6.7 1bs./gallon. For weight and balance calculations, fuel weights must be derived from the iSpecific Weight vs. Temperature" chart in the Volpar Airplane Flight Manual D-109 or D-111.

NOTE 3: The engine 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-109 or D-111 for nonstandard day.

NOTE 4: CAUTION:

The approval of this change in Type Design applies basically to the Beech models JRB-6, D18C, D18S, E18S, E18S-0700, C-45G, TC-45G, C-45H, TC-45H, TC-45J (SNB-5), G18S and H18 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 by 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 will, 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 anti-icing credit is allowed.

NOTE 6: Grade 80/87 octane aviation gasoline or white gasoline or white gasoline is approved for emergency use. Do not exceed 1000 gallons of operation. The amount of gasoline used must be entered in the engine log book.

NOTE 7. Information essential to the proper maintenance of these airplanes is contained in Volpar Document D-110 which must be available at the time of delivery of the airplane.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Cantinuatian Sheet) Number: SA2204WE NOTE 8: De-icer and/or anti-icing equipment items shown on OPTIONAL on Volpar Turboliner II Equipment List, Volpar Drawing No. 2514, revision E, or later FAA approved revisions, have been evaluated by FAA in accordance with SFAR 23 Section 59 only. No evaluation was accomplished in accordance with SFAR 23, Section 34. Compliance with SFAR 23, Section 48, has been shown.

NOTE 9: a. Volpar Airplane Flight Manual D-109 is required for FAR Part 135 operations on or after 1 June 1972.

b. Volpar Airplane Flight Manual D-111 may be used for FAR Part 135 operations in lieu of D-109 prior to 1 June 1972 only (reference FAR Part

135.144).

c. Volpar Airplane Flight Manual D-109 or D-111 may be used for FAR Part 91 operations.

d. The data presented in Airplane Flight Manual No. D-111 was prepared in accordance with paragraphs a, b, and c of the above Certification Basis, and that presented in Airplane Manual No. D-109 was prepared in accordance with paragraph a, b, c, and d of the above Certification Basis. The latter manual contains additional operating limitations and performance information required by Sections 19 and 20 of SFAR 23.

- END -