STC SA2414WE

This Certificate issued to Staggerwing Museum Foundation, Inc.

560 Old Shelbyville Highway Tullahoma, Tennessee 37388 Part * of the Civil Air Regulations. *See page 6 of this STC for Certification Basis Original Product Type Certificate Number :

A-765 Beech D18C, D18S, E18S, E18S-9700, G18S, H18, C-45G, TC-45G, C-45H, TC-45H, TC-45J (SNB-5), JRB-6, 3N, 3NM, 3TM Description of Type Design Change: Modifications for increase in maximum weights in accordance with FAA Sealed American Turbine Engine Company Drawing No. 1020.

This design change is applicable to aircraft with Volpar Tricycle landing gear and with UACL PT6A Series engines installed in accordance with STC SA1016WE.

Limitations and Conditions: The limitations and conditions of Aircraft Specification No.

A-765 applies except as outlined in pages 3 through 9 of this STC. A copy of this STC must be included in the permanent records of each airplane modified in accordance with this STC.

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.

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: August 9, 1971

Date of issuance: September 8, 1971

Date reissued: April 25, 2005; August 12, 2005

Date amended: July 16, 1975; August 26, 1976

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

Number SA2414WE

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA2414WE

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

This Addendum, which is a part of Supplemental Type Certificate No. SA2414WE, 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 the applicable ATECO Airplane Flight Manual.

A copy of this Addendum shall be maintained as part of the modified aircraft permanent records.

Supplemental T.C. Holder: Staggerwing Museum Foundation, Inc.

560 Old Shelbyville Highway Tullahoma, Tennessee 37388

I – Models D18C, D18S, E18S, E18S-9700, G18S, H18, C-45G, TC-45G, C-45H, TC-45H, TC-45J (SNB-5), JRB-6, 3N, 3NM, 3TM

ENGINES: 2 United Aircraft of Canada, Ltd. PT6A-20 (Turbo-prop)

FUEL: JP-1, JP-4, and JP-5 fuels conforming to P&WA Spec. #522. See NOTE 4.

ENGINE LIMITS: PT6A-20 Static Sea Level Ratings Shaft Equivalent Propeller Max. Permissible Horse- Jet Shaft Shaft Inter-Turbine power Thrust Horsepower Speed Temp. (C°.)

Takeoff (5 min.) 550 72 579 2200* 750 Max. Continuous 550 72 579 2200* 750 Starting Transient 1090 (2 sec.)

Max. reverse (1 min.) 155 (12 psi)

*See NOTE 3

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA2414WE (Continued)

OIL TEMPERATURES: Minus 40°C. to 93°C. maximum continuous Minus 40°C. to 99°C. not to exceed 5 minutes

PROPELLER AND 2 Hartzell Model HC-B3TN-3/T10173B-8 with 3 blades each PROPELER LIMITS: Diameter: 93.5 in. (Nominal). Minimum allowable for repair 93.5 in. (No reduction permitted) Pitch settings at 42 in. section: Low 19° F e a t h e r e d 8 6 °

AIRSPEED LIMITS: *V mo (maximum operating speed) 248 mph (216 knots) C V a (maneuvering speed) 1 53 mph (133 knots) CAS Vf (flap extend speed) 136 mph (118 knots) (power on) CAS 160 mph (139 knots) (power off) CAS V lo/le (landing gear operating extend speed) 160 mph (139 knots) CAS

*248 mph (216 knots) CAS sea level to 13,000 ft.

195 mph (170 knots) CAS at 25,000 ft. (straight line variation between those points)

C. G. RANGE: (+116.5) to (+120.5) @ 11,500 lbs.

(Landing Gear (+107) to (+120.5) @ 7800 lbs.

extended) Straight line variation between points given Moment change due to retracting landing gear -8,931 in. - lb.

MAXIMUM OPERATING 25,000 ft.

ALTITUDE:

*MAXIMUM WEIGHT: Takeoff 11,500 lbs.

Landing 11,000 lbs.

Zero Fuel 10,750 lbs.

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA2414WE (Continued)

*See NOTE 6.

NUMBER OF SEATS: Maximum 10 (2 crew at +97). See loading instructions for passenger loading.

MAXIMUM BAGGAGE: 300 lbs. (+270) Extra equipment installed in or aft of this area may reduce limit to placarded figure.

FUEL CAPACITY: 114 Gal (Total usable in 2 nacelle tanks 54 gal. each (Basic System) (+67.7)).

See AFM for 152 Gal. (Total usable in 2 wing tanks 76 gal. each optional systems (+126)).

See NOTE 1(a) for system fuel.

OIL CAPACITY: 7.0 Gal. (Total usable in 2 integral engine tanks of

3.5 gal. including 1 gal. in each oil cooler.)

CONTROL SURFACE Wing Flaps Maximum 45° MOVEMENTS: Aileron tab (left only) Up 22° Down 19° Aileron Up 38.5° Down 21° Elevator tab Up 8° Down 22° Elevator Up 35° Down 25° Rudder tab Right 12.5° Left 12.5° Rudder Right 20° Left 20°

SERIAL NUMBERS D18C, D18S, E18S, E18S-9700, G18S, H18, C-45G, TC-45G, ELIGIBLE: C-45H, TC-45H, TC-45J (SNB-5), JRB-6, 3N, 3NM, and 3TM airplanes that are eligible for airworthiness certification under Type Certificate No. A-765 and that have been modified in accordance with FAA sealed ATECO Top Drawing No.

1020 entitled “Westwind I @ 11,500 Lbs. Gross Take-Off Wt. and 11,000 Lbs. Maximum Landing Wt.” (See also NOTE 6)

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA2414WE (Continued)

DATA PERTAINENT TO ALL MODELS

DATUM: Located 102 in. forward of centerline of wing main spar

LEVELING MEANS: Models D18C, D18S, JRB-6, C-45G, TC-45G, C-45H, TC-45H, TC-45J (SNB-5), JRB-6, 3N, 3NM, and 3TM leveling lugs on top of fuselage, forward of entrance door. Models E18S, E18S-9700, G18S, H18 leveling means on right side of fuselage (two extended screws) at bulkhead no. 8, aft of emergency exit. Plumb bob is used to level.

PRODUCTION BASIS: None.

CERTIFICATION Part 03 of the Civil Ai r Regulations effective 13 November 1945, BASIS: CAR 3 effective 15 May 1956, as amended by 3-1 through 3-6, and Special Conditions as outlined by FAA letter to ATECO for engine installation dated 28 November 1961. Supplemental Type Certificate No. SA 2414WE issued, September 8, 1971. Date of application for Supplemental Type Certificate, 9 August 1971.

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, the following items of equipment is required:

1. Pre-stall warning indicator, Safe Flight Instrument Corporation P/N 164. Install per ATECO Drawing No. 708.

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA2414WE (Continued)

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 and corresponding center of gravity locations must include system fuel (unusable) of 33 lbs. at (+70).

(b) The certificated empty weight and corresponding center of gravity locations must include system oil (unusable) of 33 lbs. at (+45).

NOTE 2: The following placards must be displayed in front of and in clear view of the pilot:

(a) “This airplane must be operated as a normal category airplane in compliance with the operation limitations stated in form of placards, markings, and manuals”.

(b) “The Auto Pilot not to be operated”.

NOTE 3: The maximum propeller shaft overspeed limit is 110% at all ratings and may be employed for sustained periods in emergencies. 100% propeller shaft speed is defined as 2200 rpm and is the normal steady state operating limit. Gas generator speeds up to 102.7% are permissible for 10 seconds and 101.6% for unlimited periods subject to applicable temperature and other limits. 100% gas generator speed is defined at 37, 500 rpm.

NOTE 4. 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.

Number SA2414WE

SUPPLEMENTAL TYPE CERTIFICATE ADDENDUM NO. SA2414WE (Continued)

NOTE 5: The approval of this change in type design applies basically to Beech Models D18C, D18S, E18S, E18S-9700, G18S, H18, C-45G, TC-45G, C-45H, TC-45H, TC-45J, (SNB-5), JRB-6, 3N, 3NM, 3TM 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 aircraft.

NOTE 6. The aircraft must be equipped with an FAA approved wing spar reinforcement. ATECO No. 878 wing spar reinforcement (center section only) may be installed per STC SA1533WE provided aircraft incorporate outboard wing panels containing Beech P/N 181410-5 tube of .120 inch wall thickness.

NOTE 7: Higher floor loadings for cargo versions are acceptable with installation of an FAA approved heavy cargo floor.

NOTE 8: The aircraft must be equipped with FAA approved metal covered flaps.

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