| AD Number | 52-05-02 | Status | Active |
| Effective Date | Not specified | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | N/A |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Martin-Marietta Corporation |
| Model(s) | 202 202A |
52-05-02 MARTIN: Applies to All Models 202 and 202A Aircraft.
Compliance required as indicated.
Due to a reported occurrence of cracks in the center wing rear spar lower chord fitting at the Station 187 rib, the following shall be accomplished:
A. Inspect within the next 100 hours. Inspect the fittings (P/N 2021U44473 and 2021U44474) with a 10-power magnifying glass after removal of the paint with a solvent. Pay particular attention to the intersection of the spar leg with the other legs of the fittings.
B. If cracks are discovered in the base or extending into the base of a fitting, the part must be replaced.
C. If cracks are found in the vertical legs only, the part can either be replaced or remain installed in the airplane. If remaining installed, the fitting must be inspected every 85 hours in accordance with items A and B. Other inspection intervals may be approved based on the evaluation of the actual crack location by the manufacturer.
D. For fittings that do not show any cracks, loosen the two bolts through the fitting, the spar stiffener and the spar chord tang. Also loosen the two spar web splice bolts through the fitting, the spar web stiffeners and rib 187 web. If any gap appears between the fitting and its mating surfaces, install shims so as to reduce this gap to less than 0.010 inch.
E. New parts installed shall be shimmed in accordance with item D.
(Glenn L. Martin Service Instruction Letter No. 17 covers this same subject.)