46-33-02: Fuselage Bulkhead Flange Stiffener
FAA order 46-33-02 is an airworthiness directive. The FAA's subject line: Fuselage Bulkhead Flange Stiffener. System: airframe structure.
What it applies to as the FAA lists it
- Kind of product
- Aircraft
- Makes
- Swift Museum Foundation, Inc.
- Models
- GC-1A, GC-1B
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 (752 characters)
46-33-02 GLOBE: (Was Mandatory Note 2 of AD-766-5.) Applies to Models GC-1A, GC-1B Aircraft Serial Numbers 3 to 174 Inclusive.
Compliance required prior to October 1, 1946.
Install stiffeners, Globe P/N 11-213-1471-1 R & L, on the flange of the upper bulkhead at fuselage Station 167, with six rivets per stiffener, to prevent the formation of cracks originating at the joggles in the flange outboard of the stabilizer attachment points. Any crack should be stop drilled. If it extends into the web of the bulkhead an 0.040-inch 24ST alclad reinforcing plate extending to the flange should be installed on the web with rivets spaced not more than 3/4 inches apart.
(Globe Customer Service Maintenance Bulletin No. 2 covers this same subject.)
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/46-33-02.json · aircraft systems.