STC SA3226NM

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA3226NM This certificate issued to: FLINT AERO, INC.

1942 Joe Crosson Drive El Cajon, California 92020-1236 Certifies that the change in the type design for the following product with the limitations and conditions therefor as specified hereon meets the airworthiness requirement's of Part 3 of the Civil Air Pegulations. Effective May 15, 1956 Original Product Type Certificate Number: 3A21 Make: CESSNA Model: See Page 3 of this STC Description of Type Design Change: Installation of 16.25 gallon usable fuel-containing lightning resistant wing tips in accordance with FAA sealed Flint Aero Master Drawing List MDL FALS210 N/C, dated February 18, 1986 or later approved FAA revisions. FAA approved flint Aero Flight Manual supplement dated January 16, 1984 or later approved revisions is required as part of this installation for those airplanes with Flight Manuals.

Limitations and Conditions: The limitations and conditions of Data Sheet 3A21 apply except as outlined on Page 3 of the 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: January 11, 1983 Date Reissued: Jan. 21, 1987, July 13, 1990, Feb. 25, 2000 Date of Issuance: February 27, 1986 Date Amended:

FEDERAL AVIATION By Direction of the Administrator * Wichael O. Murphy (Signature) TOMNISTRATO Staff, Los Angeles Aircraft Certification Office Manager, Technical & Administrative Support

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3226NM (A) 01/11/83 (I) 02/27/86 (R) 01/21/87, 07/13/90, 02/25/2000 Models 210G T210G 210H T210H 210J T210J 210K T210K 210L T210L 210M T210M P210N 210N T210N Limitations and Conditions:

Fuel Capacity 188 gal. (117 gal. usable); two 45 gal. main tanks in wings at (+43) and two 16.5 gal. (16.25 gal. usable) aux. tank in wings at (+49.5).

Placards The following placards are required in the locations noted:

Adjacent to each auxiliary tank shut-off switch:

Aux. fuel 16.25 U.S. Gals. Transfer aux. fuel only in level flight when main tank is half empty and when main tank is not supplying engine.

Auxiliary fuel switch must be off during takeoff, landing, filling, and when empty."

Adjacent to each auxiliary tank filler: "16.5 U.S. Gal. *Min Grade Av.

gasoline or Jet A fuel as applicable. Aux. Fuel switch must be off before filling."

* Insert grade number on placards for main tanks.

Adjacent to the airspeed indicator (Models T210G, T210H, T210J, T210K, T210L, T210M, P210N, and T210N only): Reduce Vne 5MPH per 1,000 feet above 18,000 feet."

In full view of the pilot:

(a) For Models 210G, T210G, 210H, T210H, 210J, and T210J: Design weights 3400 Ibs. max. provided each wing tip contains 7 gals. Or more fuel. 3240 Ibs. max. with no fuel in wing tips"

(b) For Models 210K T210K, 210L, T210L, 210M, T210M, and 210N:

iDesign weights 3800 Ibs. max. provided each wing tip contains 7 gals.

Or more fuel and main tanks are 2/3 full or more. 3530 Ibs. max. with no fuel in wing tips."

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA3226NM (A) 01/11/83 (I) 02/27/86 (R) 01/21/87, 07/13/90, 02/25/2000 Limitations and Conditions: (cont'd)

(c) For Models P210N and T210N:

Wing Tip Aux. Tank Weight Limits Aux. Fuel Tank Max. T. O. Weight Max. Ldg. Weight Either is less 3730 Ibs. 3530 Ibs.

Than 7 gals.

Both are 7 gals. 4000 Ibs. 3800 Ibs.

or more Limitation of The approval of this change in type design applies to the noted Applicability Cessna models that are otherwise unmodified and should not be Extended to other aircraft of these models on which other aircraft of these models on which other modifications are incorporated unless it is determined that the interrelationship between this change and any previously approved modifications will introduce no adverse effect on the airworthiness of these aircraft.

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