STC SA3634SW
FAA DRS lists SA3634SW as Current · Reissued, held by Sierra Industries Ltd., for Textron Aviation 206H, Textron Aviation P206A, and Textron Aviation P206B, and 10 more aircraft configurations. Recorded change: Install three auxiliary bladder type fuel tanks in each wing. Snapshot dated June 30, 2026.
Recorded modification
What the FAA record covers
Install three auxiliary bladder type fuel tanks in each wing.
SA3634SW identifies the approval, recorded holder, named aircraft, and modification scope. It does not confirm kit availability, serial-number effectivity, data rights, price, or installation authority.
Applicability
Aircraft named in FAA DRS
Named aircraft: Textron Aviation 206H, Textron Aviation P206A, and Textron Aviation P206B, and 10 more aircraft configurations. Confirm the approved model list, serial effectivity, configuration, and certificate revision.
Buyer checks
Confirm before sourcing
- 01Does it cover the exact Textron Aviation 206H and Textron Aviation P206A, and 11 more aircraft configurations model, serial range, and configuration?
- 02Which tanks, plumbing, usable-fuel assumptions, and inspections apply?
- 03Who can legally supply the design data, kit, instructions, and ICAs?
- 04What parts, labor, conformity, and return-to-service work are excluded?
Related fuel systems STCs
Installation of BFGoodrich No. 20191 remote fuel height measurement sticks.
FAA holder: BF Goodrich Aerospace
Modification in accordance with FAA approved SIE Drawing List 9000 N/C,, dated August 7, 1991, or later FAA approved revisions, to permit an increased maximum zero fuel weight (MZFW), and maximum landing weight (MLW) of DC-8-61 airplanes.
FAA holder: Structural Integrity Engineering
Approval of maximum zero fuel weight increase from 138,000 pounds to 146,000 pounds. (727-200 SERIES S/N 19483, 19484, 19486, 19491, 20180, 20184, 20185, 20187, 20995, 20996, 19480, 19492, 19481, 19482, 19485, 20191 ONLY).
FAA holder: Structural Integrity Engineering
Approval of maximum zero fuel weight and maximum landing weight (Flaps 30) increases to 157,500 pounds and 166,000 pounds, respectively. (727-200 SERIES S/N 22080 ONLY).
FAA holder: Structural Integrity Engineering