| AD Number | 60-08-02 | Status | Active |
| Effective Date | Not specified | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | N/A |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Boeing Airplane Company, Wichita Division |
| Model(s) | 75 (Army PT-13) A75 (Army PT-13A, -13B, -13C) A75J1 (Army PT-18) A75L3 A75L300 A75N1 (Army PT-17, -17A, Navy N2S-1, -4) B75 (Navy N2S-5) B75N1 (Navy N2S-3) D75N1 (Army PT-27) E75 (Army PT-13D, Navy N2S-5, PT-13D/N2S-5) E75N1 (Army PT-13D, Navy N2S-5, PT-13D/N2S-5) IB75A |
60-08-02 BOEING: Amdt. 131 Part 507 Federal Register April 9, 1960. Applies to All Model 75 Series Aircraft Operated in Restricted Category With a Gross Weight Exceeding 3,200 Pounds.
Compliance required not later than June 1, 1960, and at each 100 hours' time in service thereafter.
Due to reports of cracked longerons, the following shall be accomplished:
Visually inspect the fuselage longerons and fuselage diagonal bracing for cracks in the vicinity of the lower wing front spar attach fittings. All cracked structural members shall be repaired or replaced in accordance with CAR 18.