49-16-02: Wing fabric inspection
FAA order 49-16-02 is an airworthiness directive. The FAA's subject line: Wing fabric inspection. System: airframe structure.
What it applies to as the FAA lists it
- Kind of product
- Aircraft
- Makes
- Univair Aircraft Corporation
- Models
- 108-2, 108-3
Dates and paperwork
- Docket
- Unknown
- Status
- Current
- The FAA's document
- Read the order on the FAA's site
The order itself the regulatory text, as published
Show the full text (1,236 characters)
49-16-02 STINSON: Applies to All Models 108-2 and 108-3 Series Aircraft, Serial Numbers 2250 and Up.
Compliance required at next periodic inspection but not later than July 1, 1949.
To prevent wing fabric loosening along the upper surface of the front and rear spars in the area of the fuel tank causing a spoiler action, remove the fuel tank and inspect the upper surface wing fabric for proper installation, looseness and deterioration. The fabric should be wrapped securely around spar flange ending at spar web. If fabric is not installed in this manner or it is loose, the following shall be accomplished.
1. Resecure fabric to wing structure using at least a 4-inch width of surface tape as reinforcement. Dope to upper wing fabric along spar and wrap securely around spar flange stopping at spar web.
2. Reinstall fuel tanks.
3. Seal 1/8-inch crevice on upped wing surface (between fuel tank and spare) flush with wing contour using perma-plastic sealing compound compatible withdoped fabric surface. (3-M Weatherstrip cement manufactured by the Minnesota Mining and Manufacturing Co., or equivalent, is acceptable).
4. All rework should be in accordance with Civil Aeronautics Manual 18.
This supersedes AD 49-06-05.
Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of November 6, 2026. Connections as data: /graph/directive/49-16-02.json · aircraft systems.