STC SA4366WE

Number SA4366WE

Flint Aero, Inc.

1942 Joe Crosson Drive El Cajon, California 92020-1236 This Certificate issued to

Part 3* of the Civil Air Regulations and Part 23* of the Federal Aviation Regulations. *Certification basis is set forth in Type Certificate Data Sheet A4CE, Revision 37.

A4CE

Cessna

U206F, TU206F, U206G, TU206G, 206H, T206H Original Product Type Certificate Number:

Description of Type Design Change: Installation of

14.9 gallon usable fuel-containing wing tips in accordance with FAA sealed Flint Aero, Inc. Master Drawing List MDL FA3330, no revision, dated June 18, 1981 or later approved FAA revisions, or Flint Aero Master Drawing List Number FA050-11, Revision “B”, dated September 4, 2007, or later FAA Approved Revision. Increase in the gross weight from 3,600 to 3,800 pounds for landplane, floatplane, amphibian, and ski plane versions of models U206F, TU206F, U206G, TU206G as applicable per TCDS A4CE and the Flight Manuals. Increase in the gross weight from 3,600 to 3,800 pounds for landplane versions of the 206H and T206H. Flint Aero, Inc. FAA Approved Supplemental Airplane Flight Manual, dated December 7, 1987 for models U206F, TU206F, U206G, TU206G, or Flint Aero, Inc. FAA Approved Flight Manual Appendix Report, 050.06, dated July 19, 2001 or Report 050.04, dated July 20, 2001 for models 206H and T206H, or later approved revisions, is required as part of this installation.

Limitations and Conditions: The limitations and conditions of Data Sheet A4CE apply, except as outlined on page 3 of this STC. (Continued on Page 3)

Date of application: June 18, 1981

Date of issuance: August 28, 1981 Date reissued: June 15, 1990, February 25, 2000

Date amended: December 7, 1987, September 7, 2000, October 16, 2001, February 5, 2008

( Signature) Manager, Airframe Branch Los Angeles Aircraft Certification Office

( Title)

Number SA4366WE

REISSUE: 6/15/90, 2/25/00

Limitations and Conditions: (Continued)

The installation should not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previously approved configuration will not introduce any adverse effect upon the airworthiness of the aircraft.

The approval of this modification applies to the above noted airplane model series only. 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. A copy of this STC must be included in the permanent records of each airplane modified in accordance with this STC.

Fuel Capacity: Noted in Type Certificate A4CE for specific model plus two 15 U.S. gallon (14.9 gallon usable) auxiliary wing tip tanks at (F.S. +53).

Placards: The following placards are required in locations noted:

On instrument panel in clear view of the pilot: “Total wing tip fuel 30 U.S. gallons

(29.8 gallon usable). Transfer fuel during level flight. Transfer fuel when main tank contains not less than 5.0 gallons and is at least 15.0 gallons below full. Wing tip fuel switch must be off during takeoff, landing, refueling, and when empty.

Monitor main fuel tank gauge while transferring wing tip fuel to prevent over filling”

Adjacent to the airspeed indicator: “Reduce V ne5 MPH per 1,000 above 18,000 Feet.” (Turbocharged models only).

Forward of each wing tip tank filler: “15.0 U.S. Gallons (14.9 gallon usable) 100LL or 100/130 min. grade aviation gasoline.”

Adjacent to wing tip fuel tank pump switches: “Wing tip fuel tank pumps must be off during takeoff, landing, refueling a nd when empty. Monitor main fuel tank gauge while transferring wing tip fuel to prevent over filling.”

At wing tip fuel tank pump switches: “Left (right) wing tip fuel. 15.0 U.S.

gallons. 14.9 gallons usable. On. Off.”

Adjacent to each wing tip fuel tank leak detection drain (3 per side): “Fuel or vapor from drain requires immediate repairs.”

Number SA4366WE

REISSUE: 6/15/90, 2/25/00

Limitations and Conditions: (Continued)

Adjacent to appropriate wing tip tank pump circuit breakers or fuses: “Tip tank L (R) pump.”

Gross Weight: 3,800 pounds or 3,600 pounds; see Limitation of Applicability.

Center of Center of gravity range, inches aft of datum.

Gravity:

Forward: 33.0 inches aft of datum at 2,500 lbs. or less, with straight line variation to 44.4 inches aft of datum at 3,800 lbs. or 42.5 inches aft of datum at 3,600 lbs.

Aft: 49.7 inches aft of datum at all weights.

Reference datum: Front face of firewall at all weights.

Limitation of The approval of this change in type design applies to the basic Cessna 206 series Applicability: airplanes of the models shown a bove. Flint Aero, Inc. FAA Approved Supplemental Flight Manual, dated December 7, 1987, or later approved revisions, is required as part of this insta llation on Models U206F, TU206F, U206G, and TU206G.

Flint Aero, Inc. FAA Approved Flight Manual Appendix, Report Number 050.04 or

050.06, or later FAA Approved revisions, are required as part of this installation on Model 206H and T206H. The appropria te Airplane Flight Manual selected and Maximum Takeoff Gross Weight (M TOGW) allowable is dependent upon the airplane serial number and the status of incorporation of Cessna Aircraft Company Accomplishment Instruction AI 206-57-01 as shown in the table below.

Number SA4366WE

REISSUE: 6/15/90, 2/25/00

Limitations and Conditions: (Continued)

Applicability Table 206H/T206H S/N (“T” prefixes included) AI 206-57-01 Incorporated?

AFM Appendix MTOGW 20608001-20608059 Not Required FA 050.04 3,800 lb.

20608060-20608091 No FA 050.06 3,600 lb.

20608060-20608091 Yes FA 050.04 3,800 lb.

20208092-20608100 Not Required FA 050.04 3,800 lb.

20608101-20608158 No FA 050.06 3,600 lb.

20608101-20608158 Yes FA 050.04 3,800 lb.

20608159 and subs Not Required FA 050.04 3,800 lb.

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