STC SA3471WE

This Certificate issued to Staggerwing Museum Foundation, Inc.

560 Old Shelbyville Highway Tullahoma, Tennessee 37388 Part 03 of the Civil Air Regulations.

(See page 5 of this STC) Original Product Type Certificate Number :

A-765 Beech E18S S/N BA20 Description of Type Design Change: Modification for increase in maximum weight in accordance with FAA sealed ATE Company Drawing No. 1027NC. This change is applicable to aircraft with conventional landing gear with UACL PT6A-20 engines installed.

Limitations and Conditions: The limitations and conditions of Aircraft Specification No. A-765 applies except as outlined on page 3 through 8 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.

Date of application : April 26, 1977

Date of issuance : August 17, 1977

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

( Signature)

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

Number SA3471WE

1 – Beech E18S

Engine Two United Aircraft of Canada Ltd. PT6A-20

Fuel JP-1, JP-4 and JP-5 fuels conforming to P&W Spec. No. 522.

Oil Refer to UACL PT6 Engine Service Bulletin No. 1

Engine Rating PT6A-20 For all operations 550 shp. 579 eshp at 2, 200 rpm See NOTE 3 for applicable conditions.

Engine Limits Gas generator (N g) RPM Max. Continuous 101.6% (38, 100 rpm) Transient over speed (10 sec.) 102.7% (38, 500 rpm)

Propeller Shaft (N p)

For all forward operations 100% (2,100 rpm) Reverse 95.4% (2,100 rpm)

Torque For all forward operations 1315 lb-ft.

*Reverse 1251 lb-ft.

(*500 shp. at 2, 100 rpm)

Turbine temperature PT6A-20 (inter turbine) For all steady state operations 1380°F (750°C) Starting Transient (2 sec.) 1994°F (1090°C)

Oil temperature Maximum MIL-L23699 type oils 210°F (99°C) MIL-L-7808 type oils 185°F (85°C) Minimum -40°F (-40°C)

FAA Form 8110-2(10-68) Page 3 of 7 Number SA3471WE Propeller and Propeller Limits 2 Hartzell Model HC-B3TN-3X Series Hubs with T10173-5 blades and C-3065 Spinners. Diameter:

96.375” maximum, 94.50” minimum. Pitch settings at 30 inch station:

Low 14° Feathered 87° + 1°

Propeller Governors Woodward 210492 constant speed governors and 210507 hydraulic topping governors.

Airspeed Limits (CAS) Max. operating (V MO) Sea level to 13,000 ft. 248 mph (216 kts) 25,000 ft. 195 mph (170 kts) (Straight line variation between points given).

Maneuvering (V a) 153 mph (133 kts) Flap extend (V f) 136 mph (118 kts) Landing gear operating/ e x t e n d ( V lo/Vle) 160 mph (139 kts)

C.G. range (landing gear extended) (+113.8) to (+118.7) at 11, 230 lbs.

(+108.5) to (+118.7) at 7, 800 lbs.

Straight line variation between points given.

Moment change due to landing gear retraction +12,000 in-lb.

Empty wt.

C.G. range None

Maximum weights Takeoff 11, 230 lbs.

Landing 10, 700 lbs.

Zero fuel 10, 450 lbs.

Number of Seats Same as shown on Aircraft Specification No. A-765.

Maximum Baggage Same as shown on Aircraft Specification No. A-765.

Fuel Capacity Main tanks (2). Total usable 478 U.S. Gallons (3202 lbs.) (Arm +122) (Above weights based on 6.7 lbs. per U.S. Gallon) (See NOTE 1(a) for data on unusable fuel).

Oil Tank 2.3 U.S. Gallons (each engine) (Arm +48.0) Capacity Usable oil tank capacity 1.5 U.S. Gallons (each engine) (Arm +48.0) See NOTE 1(b) for data on unusable oil

Maximum operating Altitude 25,000 feet

Control surface Movements Same as shown on Aircraft Specification No. A-765 except:

Elevator trim tab up 8° down 22° Rudder left 19° right 19°

Serial number Eligible E18S, S/N BA20

Data Pertinent to this Model

Datum Same as shown on Aircraft Specification No. A-765.

Leveling Means Same as shown on Aircraft Specification No. A-765.

Certification Basis 1. Civil Air Regula tions Part 03 effective November 13, 1945, except where superseded by the CAR 3 requirements and Special Conditions outlined below.

2. Paragraph 3.242 only of Civil Air Regulations Part 3 effective November 1, 1949 with Amendments 3-14 thereto.

3. For the powerplant installation – Civil Air Regulations Part 3 effective May 15, 1956 including Amendments 3-1 through 3-6 thereto.

4. Special Conditions outlined by FAA letter dated November 28, 1961 to American Turbine Engine Company.

Production Basis None

Equipment The following must be installed in the aircraft for airworthiness certification subsequent to the incorporation of this STC:

1. The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis outlined above).

2. Stall warning indicator, Safe F light Instrument Corp. P/N 164 installed in accordance with American Turbine Engine Company Drawing No. 708 or Beech Model 18 Maintenance Manual.

3. Refer to the applicable drawings shown on the above noted American Turbine Engine Company Drawing No. 1027NC for additional equipment required as a result of the incorporation of this STC.

The FAA Approved American Turbine Engine Company Airplane Flight Manual Supplement ATE 900G and the Dee Howard Airplane Flight Manual No. 4 Beech Model E18S and E18S-9700 with Tricycle Landing Gear dated October 2, 1967 are required in lieu of those specified for the basic unmodified aircraft:

NOTE 1 Current weight and balance data, including a list of equipment included in the certificated empty weight and loading instructions when necessary, must be provided at the time of airworthiness certification for return to service.

(a) The certificated empty weight and corresponding center of gravity locations must include system fuel (unusable) of 40 lbs. at (+117).

(b) The certificated empty weight and corresponding center of gravity must include total system oil (unusable) at 12.4 lbs.

at (+48”).

NOTE 2 Refer to the applicable FAA Approved Airplane Flight Manual for required placards and instrument markings. All required placards must be installed in the appropriate locations.

The following placard 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 the form of placards, markings and manuals”.

NOTE 3 The ratings shown on this STC for the PT6A engine are based on static standard day conditions with no external accessory loads and no air bleed at sea level.

NOTE 4 Phillips anti-icing fuel additive PFA-55MB (MIL-L-27696D) may be used if concentration delivered to the airplane does not exceed 0.15% by volume. No fuel system anti-icing credit is allowed.

NOTE 5 The approval of this change in type design applies to the basic aircraft of the Beech E18S model noted on Page 1 of this STC that is otherwise unmodified. Except as noted below, this approval should not be extended to other aircraft of this model 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 on the airworthiness of this aircraft.

NOTE 6 The following additional modifications are required or optional as noted when this STC is incorporated:

(a) Installation of STC SA836SW is required on this model.

(b) E18 type landing gear doors, item 208 of Aircraft Specification No. A-765 or FAA approved equivalent modification, are required on this model.

(c) FAA approved wing spar reinforcement is required on this model. American Turbine Engine Co. No. 878 spar reinforcement (center section only) may be installed in accordance with STC SA1533WE provided the aircraft incorporates outboard wing panels containing Beech P/N 181410-5 tube of 0.120 inch wall thickness.

(d) Installation of extended tail wheel, item 608 of Aircraft Specification No. A-765 or FAA approved equivalent modification is required on this model.

(e) FAA approved metal covered flap installation is required on this model.

NOTE 7 Any autopilot that was approved for the unmodified aircraft of this model must be rendered inoperative unless that specific autopilot has received FAA approval for use with this aircraft when this STC is incorporated.

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