STC SA5090NM

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Number: SA5090NM This certificate issued to: FLINT AERO, INC.

1942 Joe Crosson Drive El Cajon, California 92020-1236 Part 23 of the Federal Aviation Regulations. (See Type Certificate Data Sheet) Original Product Type Certificate Number: AGCE, A23EU Make: CESSNA Model: See Page 3 of this STC Description of Type Design Change: Installation of a nineteen and a half (19.5U.S.) gallons wing tip fuel tank on each wing tip in accordance with FAA Approved Flint Aero Master Drawing List No. FA 337, Rev. 'E" ", dated April 10, 1991 and Rev. "G", dated May 28, 1992, or later FAA approved revision.

FAA Approved Flint Aero Supplemental Airplane Flight Manuals No. 337.11 dated June 7, 1991, No.

337.12, dated June 7, 1991, and Airplane Flight Manual Supplement No. 337.13, dated June 7, 1991, or later approved revision(s) are required as part of this installation.

Limitations and Conditions: The limitations and conditions of Data Sheet A6CE and A23EU apply, except as outlined in this STC. This approval is limited to aircraft specifically identified above. Aircraft which have previously approved modifications shall not be modified by this STC, unless it is determined that the interrelationship between this change and any previously approved modifications will introduce no adverse effect upon the airworthiness of the aircraft. 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: March 2, 1989 Date Reissued: February February 2000 Date of Issuance: June 17, 1991 Date Amended: May 29, 1992 FEDERAL AVIATION By Direction of the Administrator MedralO. Murpla agnature TOMINSTRATO Manager, Technical & Administrative Support Staff, Los Angeles Aircraft Certification Office (Title)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA5090NM (A) 03/02/89 (I) 06/17/91 (A) 05/29/92 (R) 02/25/2000 TCDS No. A6CE Models 337, 337A, 337B, 337C, 337D, 337E, 337F, 337G, 337H, M337B, P337H, T337E, 1337F, 1337G, T337H, and T337H-SP TCDS No. A23EU Models F337E, FT337E, FT337F, F337F, F337G, FT337GP, F337H, FT337HP Limitations and Conditions:

Fuel Capacity Add39.0 U.S. gallons (38.6 gallons usable), two 19.5 gallons wing tip tanks at station +150.0" to quantities shown in Type Certificate Data Sheet A6CE.

Placards The following placards are required in the locations noted:

Adjacent to fuel selector valve cover at appropriate locations:iTotal wing tip fuel 39 U.S.

gallons (38.6 gallons usable). Transfer wing tip fuel only in level flight when main tank is 11 U.S. gallons below full and is a selected engine fuel source, or 20 U.S. gallons below full when not a selected engine fuel source. Wing tip fuel tank pump switches must be off during takeoff, landing, refueling, and when empty".

Forward of each wing tip fuel tank filler: 19.5 U.S. gallons (19.3 gallons usable), 100LL or 100/130 minimum grade aviation gasoline".

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

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA5090NM (A) 03/02/89 (I) 06/17/91 (A) 05/29/92 (R) 02/25/2000 Limitations and Conditions: (Continued) At wing tip fuel tank pump switches:

iLeft Wing Tip Fuel Right Wing Tip Fuel

19.5 gallons 19.5 gallons

19.3 gallons usable 19.3 gallons usable ON ON OFF OFF" Installed near wing tip fuel gauge:

¿'Left Wing Tip Fuel Right Wing Tip Fuel

19.3 U.S. gallons usable 19.3 U.S. gallons usable" Installed adjacent to each wing tip fuel tank leak detection drain (3 per side): Fuel or vapor from drain requires immediate repairs."

Installed adjacent to appropriate wing tip tank pump circuit breakers or fuses:Tip tank L pump, Tip tank R pump."

Near the airspeed indicator (for turbocharged models only): "Reduce Vne and Vno by 5 KIAS (6 MPH) per 1000 feet (Hp) above 18,000 feet (Hp)."

Gross Weight and Weight and Balance Limits:

See the appropriate FAA Approved Flint Aero Supplemental Airplane Flight Manuals or Airplane Flight Manual Supplement (Report No. 337.11, 337.12, or 337.13).

Maximum Zero Fuel Weight Limits: 4,330 Ibs.

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA5090NM (A) 03/02/89 (I) 06/17/91 (A) 05/29/92 (S) 02/25/2000 Limitations and Conditions: (Continued) Fuel Loading Limits:

At weights between 4,330 Ibs. and 4, 630 Ibs., there must be at least 12 U.S. gallons of fuel in each wing tip tank.

Fuel Transfer Limits:

- Do not transfer wing tip tank fuel until weight is below 4330 pounds.

- Do not transfer wing tip tank fuel until the main fuel tank on that side is at least 11 gallons below full and is the selected engine fuel source.

- Do not transfer wing tip tank fuel to a main tank that is not a selected engine fuel source until that main tank quantity is at least 20 gallons below full.

- Do not transfer wing tip fuel unless in level flight or on the ground.

- Do not transfer wing tip fuel during tank off, landing, refueling, and when empty.

Airplane Flight Manual (AFM) The below FAA Approved Flint Aero AFM Supplement and Supplemental AFM's are required for the following aircraft models:

Flint Aero AFM Model

1. 337.11 337, A,B,C,D (S/N 337-0001 through 337-1193, except 337-0306 and 337-0569) 337E,F,G (S/N 33700306, 33701194 through 33701671, except 33701449) M337B T337E, T337F, T337G (S/N 3370001 through 3370225 and 3370677, except 370196) F337E, (S/N F3370001 through F3370024)

FAA Form B110-2(10-68) Page 5 of 7

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA5090NM (A) 03/02/89 (I) 06/17/91 (A) 05/29/92 (R) 02/25/2000 Limitations and Conditions: (Continued) FT337E (S/N FT3370001 through FT3370024) Flint Aero AFM Model FT337F (S/N FT3370025 through FT3370055) F337F (S/N F3370025 through F3370055) F337G (S/N F3370056 through F3370076) FT337GP (S/N FP3370001 through FP3370015)

2. 337.12 337G (S/N 33701672 through 33701815 and P33701449) T337G (S/N P3370226 through P3370292) 337H (S/N 33701816 through 33701874) T337H (S/N 33701816 through 33701874, except 33701854) P337H(S/N P3370293 through P3370318) F337G (S/N F3370077 through F3370084) FT337GP (S/N FP3370016 through FP3370018, FP3370023) F337H (S/N F3370085 and up) FT337HP (S/N FP3370023 and up)

3. 337.13 337H - Cessna P/N D1567-13PH (S/N 33701875 through 33701921) 337H - Cessna P/N D1578-13PH (S/N 33701922 and up, except 33701923 through 33701927) P337H - Cessna P/N D1569-13PH (S/N P3370319 through P3370341 and P3370196) P337H - Cessna P/N D1580-13PH (S/N P3370342 and up) T337H - Cessna P/N D1568-13PH (S/N 33701875 through 33701919, 33701921 and 33701854) T337H - Cessna P/N D1579-13PH (S/N 33701922 through 33701950, except 33701923 through 33701927) T337H-SP - Cessna P/N D1579-13PH and Supplement D1579-13PHH (S/N 33701920, 33701923 through 33701927, 33701951)

United States of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate (Continuation Sheet) Number: SA5090NM (A) 03/02/89 (I) 06/17/91 (A) 05/29/92 (R) 02/25/2000 Limitations and Conditions: (Continued) T337H-SP - Cessna P/N D1579-13PH and Supplement D1579-13PHH2 (S/N33701952 and up) Limitation of Applicability The approval of this change in type design applies to the basic Cessna 337 series. This approval should not be extended to 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 modification will introduce no adverse effect on the airworthiness of these aircraft.

NOTE: No acoustical change was shown under the provisions of FAR Paragraph 21.93(b), Amendment 21-63.

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