| AD Number | 67-19-03 | Status | Active |
| Effective Date | June 10, 1967 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-431 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Bombardier Inc. |
| Model(s) | CL-44D4 |
67-19-03 CANADAIR: Amdt. 39-431, Part 39, Federal Register June 6, 1967. Applies to CL-44D4 Type airplanes.
Compliance required as indicated.
To detect cracks in the horizontal stabilizer front spar web, accomplish the following:
(a) For horizontal stabilizers with 13,500 or more hours' time in service on the effective date of this AD inspect in accordance with (c) within the next 25 hours' time in service after the effective date of this AD, unless already accomplished within the last 225 hours' time in service, and thereafter at intervals not to exceed 250 hours' time in service from the last inspection.
(b) For horizontal stabilizers with less than 13,500 hours' time in service on the effective date of this AD, inspect in accordance with (c) before the accumulation of 13,525 hours' time in service unless accomplished after the accumulation of 13,275 hours' time in service, and thereafter at intervals not to exceed 250 hours' time in service from the last inspection.
(c) Remove the horizontal stabilizer leading edge access panels, P/N 912-2 and P/N 913-2 (Station 52 to 59), and visually inspect the front spar web for cracks from Station 56 to 77, or use an FAA-approved equivalent inspection. If a crack is found comply with (d) before further flight.
(d) Repair cracked parts with an FAA-approved repair or replace the cracked part with a part of the same part number that has been inspected in accordance with (c) and found free of cracks, or with an FAA-approved equivalent part.
(e) The repetitive inspection required by (a) and (b) may be discontinued when the horizontal stabilizer front spar web is modified in accordance with an FAA-approved modification.
(f) Equivalent inspections may be approved by an FAA maintenance inspector. Equivalent repairs, parts, and modifications must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
(g) Upon request with substantiating data submitted through an FAAmaintenance inspector, the compliance times specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
This amendment effective June 10, 1967.