- Effective
- February 20, 1974
- Models
- CL-44D4, CL-44J
- Data sheet
- TCDS1A20
- Product
- Aircraft · Large airplane
- Amendment
- 39-1788
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. The FAA’s own copy is the authoritative one. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
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|---|---|---|---|
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On this page
The airworthiness directive
74-04-05 CANADAIR: Amdt. 39-1788. Applies to all CL-44D4 and CL-44J airplanes with more than 20,000 hours' time in service. To detect cracks in the main landing gear uplock attachment fitting, P/N 44-10162 and -1, accomplish the following:
1. Within the next 100 hours' time in service after the effective date of this AD, unless accomplished within the last 400 hours' time in service, and at intervals thereafter not to exceed 500 hours' time in service, inspect the main landing gear uplock attachment fitting, P/N 44-10162 and -1 at the four corners of the lug for cracks using a dye penetrant inspection with a glass of at least 10-power or an approved equivalent inspection.
2. Cracked parts must be replaced before further flight, or repaired before further flight as specified in paragraphs 1(a) and (b) of the Inspection Procedure of Canadair's Service Information Circular 374-CL-44 or with an approved equivalent repair.
3. The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA maintenance inspector.
4. Equivalent inspections, parts or repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
This amendment is effective February 20, 1974.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.