50-09-01: Stabilizer Spar Fittings and Shims
FAA order 50-09-01 is an airworthiness directive. The FAA's subject line: Stabilizer Spar Fittings and Shims. It names North American AT-6 Texan: about 228 aircraft on the U.S. register today, though an order usually covers particular versions or serial numbers rather than every one. System: airframe structure.
What it applies to as the FAA lists it
- Kind of product
- Aircraft
- Makes
- The Boeing Company
- Models
- AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), BC-1A
- On this site
- North American AT-6 Texan 228 registered
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 (1,536 characters)
50-09-01\tNORTH AMERICAN: Applies to all Army Model BC-1A, AT-6, -6A, -6B, - 6C; Navy SNJ-2, -3 and -4 Aircraft. \n\n\tTo be accomplished prior to original certification.\n \n\tInspect the horizontal stabilizer rear spar connection for cracked fittings and the installation of shims as follows: \n\n\t(1)\tRemove the fuselage to vertical stabilizer fairing assembly and the rear fairing assemblies at the horizontal stabilizer. \n\n\t(2)\tRemove the 1/4-inch bolts which attach the rear spar connection fitting to the spar assembly. \n\n\t(3)\tRemove paint from connection fittings and inspect for cracks. Check with a machinist's square or other means to determine if fitting is preset. Replace any cracked or preset fitting and repaint all others. New fittings may be made of 24 ST or X4130 bar stock to the same dimensions as the old fittings. \n\n\t(4)\tInspect the fit between the spar and the sides of the base fitting with a feeler gage. Also inspect the fit between fitting P/N 77-21021 and the spar. If gaps exist, shims are necessary. \n\n\t(5)\tFabricate 24ST shims 3 1/8 inches x 15/16 inch and of necessary thickness, and place on either side of spar flanges maintaining a parallel overall dimension to fit inside of fitting P/N 77-21021 within maximum clearance of 0.010. \n\n\t(6)\tDrill holes through the shims to match those in the fitting. Remove all chips and reinstall the various parts. \n\n\t(North American Service Bulletin dated March 6, 1946, covers this subject also.) \n\n\tThis supersedes AD 45-44-03.
Related safety bulletins advice on the same designs, not orders
2018-11-21SW-18-31 · NAVIGATION, ATTITUDE, AND DIRECTION DATA SYSTEM
2018-02-09CE-18-10 · Fuel System - Selector Valve Placard
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/50-09-01.json · aircraft systems.